5. Inspection Tasks Packages

050011 1A CHECK PKG TO25-004-01 DETAILED INSPECTION - INSPECT (DETAILED) THE

CAPTAIN, FIRST OFFICER, FIRST OBSERVER, AND SECONDOBSERVER (IF INSTALLED) SEAT HARNESSES, CROTCHSTRAPS, AND SHOULDER BELTS (AS APPLICABLE) FORWEAR, CONDITION, AND SECURITY.

25-026-01 GENERAL VISUAL INSPECTION - INSPECT (GENERALVISUAL) THE CARGO COMPARTMENT FLOOR PANELS,CEILING AND SIDEWALL LINERS FOR HOLES/TEARS,CONDITION AND SECURITY.

27-038-01 OPERATIONAL CHECK - OPERATIONALLY CHECK THESTANDBY RUDDER SYSTEM.

27-134-01 SERVICE - SERVICE THE TRAILING EDGE FLAP BALLSCREWNUT RESERVOIR.

29-006-01 DISCARD - DISCARD THE ELECTRIC MOTOR DRIVENHYDRAULIC PUMP CASE DRAIN FILTERS.

29-018-01 GENERAL VISUAL INSPECTION - INSPECT (GENERALVISUAL) THE DELTA "P" INDICATION OF "A & B" HYDRAULICSYSTEM RETURN FILTER MODULE.

32-056-01 RESTORE - RESTORE THE NOSE GEAR DOWN AND LOCKEDVIEW WINDOW BY CLEANING.

32-058-01 RESTORE - RESTORE THE MAIN GEAR DOWN AND LOCKEDVIEW WINDOW BY CLEANING.

33-004-01 OPERATIONAL CHECK - OPERATIONALLY CHECK THEINTERIOR EMERGENCY LIGHTS.

49-106-01 VISUALLY CHECK - VISUALLY CHECK THE APU FUELCONTROL INLET FILTER DELTA-P INDICATOR.

49-126-01 DETAILED INSPECTION - INSPECT (DETAILED) THE APU OILMAGNETIC CHIP DETECTOR FOR METAL PARTICLES.

49-130-01 SERVICE - SERVICE APU OIL BY CHECKING FOR CORRECTLEVEL AND REPLENISHING AS REQUIRED.

49-132-01 VISUALLY CHECK - VISUALLY CHECK THE APU OIL FILTERELEMENT DELTA-P INDICATOR.

52-802-01 ACCOMPLISH - EXTERNAL - ZONAL (GV) FORWARD GALLEYSERVICE DOOR

52-806-01 ACCOMPLISH - EXTERNAL - ZONAL (GV) FORWARD ENTRYDOOR

52-810-01 ACCOMPLISH - EXTERNAL - ZONAL (GV) AFT ENTRY DOOR 52-816-01 ACCOMPLISH - EXTERNAL - ZONAL (GV) AFT GALLEY

SERVICE DOOR

Task Relations

Parent Task No. Child Task DescriptionParent Task Description Child Task No.Relationship

Model: BOEING 737-300/400/500

8/29/2013 9:06:47 PM COPYRIGHT 2002 DANIEL SYSTEMS, INC. Page 1 Of 196

52-842-01 ACCOMPLISH - EXTERNAL - ZONAL (GV) FORWARD CARGODOOR

52-846-01 ACCOMPLISH - EXTERNAL - ZONAL (GV) AFT CARGO DOOR 53-328-01 GENERAL VISUAL INSPECTION - EXTERNAL-GENERAL

VISUAL INSPECTION: INSPECT THE FORWARD AND AFTCARGO DOOR STOP PAD FITTINGS.

53-334-01 GENERAL VISUAL INSPECTION - EXTERNAL-GENERALVISUAL INSPECTION: INSPECT THE ENTRY AND GALLEYDOOR STOP PAD FITTINGS, LATCHES, AND HINGES.

54-818-01 ACCOMPLISH - INTERNAL - ZONAL (GV) AFT STRUT FAIRING- ENGINE NO. 2 (EZAP)

71-012-01 VISUALLY CHECK - VISUALLY CHECK THE LEFT ENGINEINLET COWL (INNER AND OUTER SKIN).

71-012-02 VISUALLY CHECK - VISUALLY CHECK THE RIGHT ENGINEINLET COWL (INNER AND OUTER SKIN).

79-010-01 DETAILED INSPECTION - INSPECT (DETAILED) THE LEFTENGINE OIL SCAVENGE PARTICLE TRAPS (SCREEN ANDMAGNETIC PLUG).

79-010-02 DETAILED INSPECTION - INSPECT (DETAILED) THE RIGHTENGINE OIL SCAVENGE PARTICLE TRAPS (SCREEN ANDMAGNETIC PLUG).

79-014-01 DETAILED INSPECTION - INSPECT (DETAILED) THE LEFTENGINE OIL SCAVENGE FILTER CLOGGING INDICATOR ONTHE LUBRICATION UNIT.

79-014-02 DETAILED INSPECTION - INSPECT (DETAILED) THE RIGHTENGINE OIL SCAVENGE FILTER CLOGGING INDICATOR ONTHE LUBRICATION UNIT.

79-018-01 DETAILED INSPECTION - INSPECT (DETAILED) THE MAINLEFT ENGINE OIL FILTER BYPASS INDICATOR.

79-018-02 DETAILED INSPECTION - INSPECT (DETAILED) THE MAINRIGHT ENGINE OIL FILTER BYPASS INDICATOR.

80-002-01 DETAILED INSPECTION - INSPECT (DETAILED) THE LEFTENGINE STARTER OIL MAGNETIC CHIP DETECTOR FORMETAL CHIPS.

80-002-02 DETAILED INSPECTION - INSPECT (DETAILED) THE RIGHTENGINE STARTER OIL MAGNETIC CHIP DETECTOR FORMETAL CHIPS.

80-004-01 SERVICE - SERVICE LEFT ENGINE STARTER OIL BYCHECKING FOR CORRECT LEVEL AND REPLENISHING ASREQUIRED.

Task Relations


Model: BOEING 737-300/400/500


80-004-02 SERVICE - SERVICE RIGHT ENGINE STARTER OIL BYCHECKING FOR CORRECT LEVEL AND REPLENISHING ASREQUIRED.

24-026-01 (001.1) RESTORE STANDBY POWER STORAGE BATTERY 21-020-01 DETAILED INSPECTION - INSPECT (DETAILED) THE AIR

COOLING SYSTEM WATER SEPARATOR INDICATION DISK(WITH THE AIR CONDITIONING SYSTEM OPERATIVE).

21-026-01 SERVICE - SERVICE THE AIR CYCLE MACHINE OIL BYCHECKING FOR CORRECT LEVEL AND REPLENISHING ASREQUIRED.

21-028-01 SERVICE - SERVICE THE RAM AIR TURBO FAN OIL BYCHECKING FOR CORRECT LEVEL AND REPLENISHING ASREQUIRED.

21-032-01 OPERATIONAL CHECK - OPERATIONALLY CHECK THEELECTRONIC/ELECTRICAL EQUIPMENT COOLING SYSTEMALTERNATE SUPPLY FAN/ CHECK VALVE.

23-006-01 OPERATIONAL CHECK - OPERATIONALLY CHECK THEVOICE RECORDER.

050012 2A CHECK PKG TO21-042-01 RESTORE - RESTORE THE CABIN TEMPERATURE SENSOR

FILTER BY CLEANING. 24-004-02 SERVICE - SERVICE THE RIGHT ENGINE CSD INPUT SPLINE

OIL BY CHECKING FOR CORRECT LEVEL ANDREPLENISHING AS REQUIRED.

ICA-25-053-03 PERFORM AN OPERATIONAL CHECK OF THE SLIDINGCARPET SYSTEM USING THE TESTING PROCEDURES INTHE MANUAL 25-53-00

ICA-25-053-02 LUBRICATE THE SLIDING CARPET SIDE LH AND RH GUIDETRACKS WITH DOOR-EASE LUBRICANT OR DRY SILICONESPRAY, OR EQUIVALENT

ICA-25-053-01 PERFORM A GENERAL VISUAL INSPECTION OF THESLIDING CARPET SYSTEM FOR DAMAGE, SECURITY OFINSTALLATION, AND GENERAL CONDITION.

24-008-02 DETAILED INSPECTION - INSPECT (DETAILED) THE RIGHTENGINE CSD DRIVE LINE OIL FILTER DIFFERENTIALPRESSURE INDICATOR.

24-012-01 GENERAL VISUAL INSPECTION - INSPECT (GENERALVISUAL) THE LEFT ENGINE GENERATOR DRIVE OIL COOLERBYPASS RELIEF VALVE FOR CONDITION AND SECURITY OFINSTALLATION.

Task Relations


Model: BOEING 737-300/400/500


24-012-02 GENERAL VISUAL INSPECTION - INSPECT (GENERALVISUAL) THE RIGHT ENGINE GENERATOR DRIVE OILCOOLER BYPASS RELIEF VALVE FOR CONDITION ANDSECURITY OF INSTALLATION.

24-018-01 DETAILED INSPECTION - INSPECT (DETAILED) THE LEFTENGINE VSCF GENERATOR DRIVE LINE OIL FILTERDIFFERENTIAL PRESSURE INDICATOR.

24-020-01 SERVICE - SERVICE THE LEFT ENGINE VSCF GENERATORCASE OIL AND INPUT SPLINE CAVITY OIL BY CHECKING FORCORRECT LEVEL AND REPLENISHING AS REQUIRED.

25-020-01 OPERATIONAL CHECK - OPERATIONALLY CHECK THELAVATORY WASTE COMPARTMENT FLAPPER DOORSPRING.

25-022-01 DETAILED INSPECTION - INSPECT (DETAILED) THELAVATORY WASTE COMPARTMENT DOOR SEALS ANDWASTE COMPARTMENT ACCESS DOOR LATCHINGMECHANISM FOR WEAR, CONDITION AND SECURITY.

25-054-01 VISUALLY CHECK - VISUALLY CHECK THE LIFE RAFTPRESSURE BOTTLE FOR PROPER PRESSURE.

25-066-01 OPERATIONAL CHECK - OPERATIONALLY CHECK THEEMERGENCY (EVACUATION SIGNAL SYSTEM) ALERT PANEL.

26-010-01 VISUALLY CHECK - VISUALLY CHECK ENGINE FIRE BOTTLEPRESSURE GAUGE FOR CORRECT PRESSURE.

26-072-01 VISUALLY CHECK - VISUALLY CHECK THE LAVATORY FIREEXTINGUISHING HEAT TAPE FOR CONDITION ANDEXPOSURE TO HEAT.

27-108-01 LUBRICATE - LUBRICATE THE STABILIZER TRIM ACTUATORAND ACTUATOR GIMBAL PINS.

27-194-01 LUBRICATE - LUBRICATE THE LEADING EDGE SLATACTUATION SYSTEM.

32-036-01 SERVICE - SERVICE THE BRAKE ACCUMULATORPRECHARGE PRESSURE AS REQUIRED.

49-104-01 GENERAL VISUAL INSPECTION - INSPECT (GENERALVISUAL) THE APU GEARBOX ASSEMBLY FOR GENERALCONDITION AND EVIDENCE OF OIL LEAKS.

49-108-01 GENERAL VISUAL INSPECTION - INSPECT (GENERALVISUAL) THE APU FUEL SYSTEM COMPONENTS, SEALS,LINES AND INTERFACE CONNECTIONS FOR LEAKS.

49-118-01 DETAILED INSPECTION - INSPECT (DETAILED) THE APUSURGE CONTROL VALVE AIR FILTER AND CLEAN ASREQUIRED.

Task Relations


Model: BOEING 737-300/400/500


49-128-01 GENERAL VISUAL INSPECTION - INSPECT (GENERALVISUAL) THE APU EXTERNAL PLUMBING, PACKINGS ANDCOMPONENTS FOR EVIDENCE OF OIL LEAKS.

49-134-01 DISCARD - DISCARD THE APU OIL AND FILTER ELEMENT. 52-004-01 LUBRICATE - LUBRICATE THE ENTRY AND SERVICE DOOR

UPPER AND LOWER HINGE GIMBALS, GUIDE PLATE ANDARM ASSEMBLIES, LATCH CRANK BEARINGS, LATCHROLLERS, GATE HINGES, PUSH RODS, AND THE FORWARDENTRY DOOR BODY TORQUE TUBE.

52-008-01 DETAILED INSPECTION - INSPECT (DETAILED) THEFORWARD ENTRY DOOR CENTERING GUIDE STUD ANDNYLON GUIDE FOR CONDITION.

52-010-01 DETAILED INSPECTION - INSPECT (DETAILED) THE AFTENTRY AND SERVICE DOOR CENTERING GUIDE BEARINGS(3 DOORS ONLY) FOR CONDITION.

52-074-01 LUBRICATE - LUBRICATE THE AIRSTAIR DOOR SYSTEM,(INCLUDES TWO ROLLERS, AND THE CARRIAGE DRIVEBALL). (IF AIRSTAIR SYSTEM OR PARTIAL AIRSTAIRSSYSTEM WITH ROLLERS AND CARRIAGE DRIVE INSTALLED).

54-300-01 DETAILED INSPECTION - EXTERNAL-DETAILEDINSPECTION: INSPECT THE PYLON SKIN IN AREAS OFATTACHMENT TO THE FORWARD ENGINE MOUNTBULKHEAD AT NAC. STA. 196.

54-302-01 DETAILED INSPECTION - INTERNAL-DETAILED INSPECTION:INSPECT THE PYLON UPPER LINK AND ATTACH FITTINGSAND FUSE PINS AT WBL 191, MIDSPAR CHORDS ANDFORWARD TANG OF THE MID-SPAR FITTINGS AT WBL 183.4AND 198.6 (WITH FUSE PINS INSTALLED).

54-314-01 DETAILED INSPECTION - INTERNAL-DETAILED INSPECTION:INSPECT THE PYLON MIDSPAR FITTINGS AND FUSE PINS(PYLON AND WING) AT WBL 183.4 AND 198.6 (WITH FUSEPINS INSTALLED).

72-010-01 DETAILED INSPECTION - INSPECT (DETAILED) THE LEFTENGINE INLET AND FAN BLADES.

72-010-02 DETAILED INSPECTION - INSPECT (DETAILED) THE RIGHTENGINE INLET AND FAN BLADES.

72-024-01 DETAILED INSPECTION - INSPECT (DETAILED) THE LEFTENGINE INLET FOR DAMAGE AND/OR MISSING ABRADABLEMATERIAL.

72-024-02 DETAILED INSPECTION - INSPECT (DETAILED) THE RIGHTENGINE INLET FOR DAMAGE AND/OR MISSING ABRADABLEMATERIAL.

Task Relations


Model: BOEING 737-300/400/500


72-044-01 SPECIAL DETAILED INSPECTION - INSPECT (SPECIALDETAILED) THE LEFT ENGINE HPT NOZZLE FOR DISTRESSUSING A BORESCOPE.

72-044-02 SPECIAL DETAILED INSPECTION - INSPECT (SPECIALDETAILED) THE RIGHT ENGINE HPT NOZZLE FOR DISTRESSUSING A BORESCOPE.

72-046-01 SPECIAL DETAILED INSPECTION - INSPECT (SPECIALDETAILED) THE LEFT ENGINE HPT BLADES FOR CRACKINGAND DISTRESS USING A BORESCOPE.

72-046-02 SPECIAL DETAILED INSPECTION - INSPECT (SPECIALDETAILED) THE RIGHT ENGINE HPT BLADES FOR CRACKINGAND DISTRESS USING A BORESCOPE.

80-006-01 DISCARD - DISCARD THE LEFT ENGINE STARTER OIL. 80-006-02 DISCARD - DISCARD THE RIGHT ENGINE STARTER OIL. 27-195-01 LUBRICATE - LUBRICATE THE KRUEGER FLAP ACTUATION

MECHANISM. 050013 3A CHECK PKG TO

25-074-01 DETAILED INSPECTION - INSPECT (DETAILED) THE SMOKEHOODS FOR CONDITION AND PRESENCE.

25-070-01 OPERATIONAL CHECK - OPERATIONALLY CHECK THEEMERGENCY FLASHLIGHTS.

32-024-01 FUNCTION CHECK - FUNCTIONALLY CHECK THE MAINLANDING GEAR MANUAL EXTENSION SYSTEM.

32-024-02 FUNCTION CHECK - FUNCTIONALLY CHECK THE NOSELANDING GEAR MANUAL EXTENSION SYSTEM.

050031 1C CHECK PKG TO27-072-01 OPERATIONAL CHECK - OPERATIONALLY CHECK

(HYDRAULIC POWER OFF) THE ELEVATOR CONTROLSURFACES OVER THE FULL RANGE OF TRAVEL AND CHECKFOR FREEDOM OF MOVEMENT.

27-074-01 GENERAL VISUAL INSPECTION - INSPECT (GENERALVISUAL) THE ELEVATOR POWER CONTROL UNITS WITHHYDRAULIC POWER ON.

27-080-01 OPERATIONAL CHECK - OPERATIONALLY CHECK THEELEVATOR TAB CONTROL SYSTEM.

27-082-01 GENERAL VISUAL INSPECTION - INSPECT (GENERALVISUAL) THE ELEVATOR TAB CONTROL MECHANISM.

27-092-01 FUNCTION CHECK - FUNCTIONALLY CHECK THE STALLWARNING SYSTEM.

Task Relations


Model: BOEING 737-300/400/500


27-096-01 DETAILED INSPECTION - INSPECT (DETAILED) THESTABILIZER TRIM JACKSCREW INCLUDING UPPER ANDLOWER GIMBALS

27-098-01 OPERATIONAL CHECK - OPERATIONALLY CHECK THESTABILIZER TRIM LIMIT SWITCHES (FLAPS UP AND FLAPSDOWN).

27-100-01 OPERATIONAL CHECK - OPERATIONALLY CHECK THECONTROL COLUMN STABILIZER TRIM CUTOUT SWITCHINGMODULE.

27-102-01 OPERATIONAL CHECK - OPERATIONALLY CHECK THESTABILIZER TRIM AISLE STAND OVERRIDE SWITCH.

27-104-01 DETAILED INSPECTION - INSPECT (DETAILED) THEFORWARD STABILIZER TRIM MECHANISM RETENTIONTURNBUCKLE AND TURNBUCKLE ATTACHMENT POINTS.

27-106-01 OPERATIONAL CHECK - OPERATIONALLY CHECK THECONTROL COLUMN STABILIZER TRIM ARM ANDDIRECTIONAL SWITCHES FOR MOVEMENT OF A SINGLESWITCH TO CAUSE STABILIZER MOVEMENT.

27-112-01 GENERAL VISUAL INSPECTION - INSPECT (GENERALVISUAL) THE STABILIZER TRIM FORWARD MECHANISM.

27-114-01 FUNCTION CHECK - FUNCTIONALLY CHECK THESTABILIZER TRIM GEARBOX AUXILIARY BRAKE.

27-118-01 DETAILED INSPECTION - INSPECT (DETAILED) THETRAILING EDGE FLAP CONTROL UNIT FOLLOW-UP CABLERUN.

27-124-01 OPERATIONAL CHECK - OPERATIONALLY CHECK THETRAILING EDGE FLAP BYPASS VALVE.

27-142-01 LUBRICATE - LUBRICATE THE TRAILING EDGE FLAPACTUATION COMPONENTS.

27-150-01 GENERAL VISUAL INSPECTION - INSPECT (GENERALVISUAL) THE TRAILING EDGE FLAP TRANSMISSIONS.

21-018-01 (001.1) RESTORE LEFT PRIMARY HEAT EXCHANGER 21-018-01 (002.1) RESTORE RIGHT PRIMARY HEAT EXCHANGER 21-018-01 (003.1) RESTORE LEFT SECONDARY HEAT EXCHANGER 21-018-01 (004.1) RESTORE RIGHT SECONDARY HEAT EXCHANGER 20-010-01 RESTORE (CLEAN) THE FORWARD LAVATORY

COMPARTMENT AREAS UNDER THE TOILET AND SINK.(EZAP)

20-022-01 RESTORE (CLEAN) THE AFT RIGHT LAVATORYCOMPARTMENT (IF INSTALLED) AREAS UNDER THE TOILETAND SINK. (EZAP)

Task Relations


Model: BOEING 737-300/400/500


52-036-01 LUBRICATE - LUBRICATE THE OVER WING EMERGENCYEXIT HATCH ROLLERS AND PIVOT FITTINGS.

52-048-01 LUBRICATE - LUBRICATE THE CARGO COMPARTMENTDOOR LATCH TUBE BEARINGS.

52-050-01 LUBRICATE - LUBRICATE THE CARGO COMPARTMENTDOOR COUNTERBALANCE MAIN BEARING.

52-068-01 LUBRICATE - LUBRICATE THE E/E ACCESS DOOR HANDLELATCHING MECHANISM (RACK AND PINION GEAR AND THELOCK PINS).

52-070-01 GENERAL VISUAL INSPECTION - INSPECT (GENERALVISUAL) THE E/E ACCESS DOOR PRESSURE SEAL FORDEGRADATION.

52-078-01 DETAILED INSPECTION - INSPECT (DETAILED) THEAIRSTAIR SYSTEM (EXTENDED) FOR CONDITION (IFAIRSTAIRS SYSTEM INCLUDING STAIRS IS INSTALLED).

52-080-01 GENERAL VISUAL INSPECTION - INSPECT (GENERALVISUAL) THE AIRSTAIR DOOR PRESSURE SEAL FORDEGRADATION (IF AIRSTAIRS SYSTEM OR PARTIALAIRSTAIRS SYSTEM IS INSTALLED).

52-300-01 DETAILED INSPECTION - EXTERNAL-DETAILEDINSPECTION: INSPECT THE FORWARD AND AFT CARGODOOR STOP PIN FITTINGS.

52-304-01 GENERAL VISUAL INSPECTION - EXTERNAL-GENERALVISUAL INSPECTION: INSPECT THE FORWARD AND AFTCARGO DOOR SKINS AND EDGE FRAMES.

52-308-01 DETAILED INSPECTION - EXTERNAL-DETAILEDINSPECTION: INSPECT THE ENTRY AND GALLEY SERVICEDOOR STOP PIN FITTINGS.

52-310-01 GENERAL VISUAL INSPECTION - EXTERNAL-GENERALVISUAL INSPECTION: INSPECT THE ENTRY AND GALLEYSERVICE DOOR SKINS AND EDGE FRAMES.

52-322-01 GENERAL VISUAL INSPECTION - EXTERNAL-GENERALVISUAL INSPECTION: INSPECT THE OVER WING ESCAPEHATCH SKIN, EDGE FRAMES.

52-326-01 GENERAL VISUAL INSPECTION - EXTERNAL-GENERALVISUAL INSPECTION: INSPECT THE FORWARD ACCESSDOOR AND ELECTRICAL/ELECTRONIC ACCESS DOOR SKINAND EDGE FRAMES.

52-330-01 GENERAL VISUAL INSPECTION - EXTERNAL-GENERALVISUAL INSPECTION: INSPECT THE FORWARD AIRSTAIRDOOR SKIN, EDGE FRAMES, AND DOOR STOP PIN FITTINGS(IF AIRSTAIR OR AIRSTAIR PROVISIONS INSTALLED).

Task Relations


Model: BOEING 737-300/400/500


52-804-01 ACCOMPLISH - INTERNAL - ZONAL (GV) FORWARD GALLEYSERVICE DOOR

52-808-01 ACCOMPLISH - INTERNAL - ZONAL (GV) FORWARD ENTRYDOOR

52-812-01 ACCOMPLISH - INTERNAL - ZONAL (GV) AFT ENTRY DOOR 20-050-01 INSPECT (DETAILED) THE GENERATOR POWER FEEDERS,

IGNITION LEADS, ELECTRIC STARTER WIRES ANDCONNECTED EWIS ON THE APU. (EZAP)

20-052-01 INSPECT (DETAILED) THE EXPOSED (UNPRESSURIZED)PORTIONS OF THE CONTROL CABLES IN THE FUSELAGEAND EMPENNAGE.

20-058-01 INSPECT (DETAILED) THE EXPOSED PORTIONS OF THELANDING GEAR MANUAL EXTENSION CONTROL CABLES.

21-004-01 OPERATIONAL CHECK -OPERATIONAL CHECK THEOUTFLOW VALVE, VALVE SELECTOR PANEL, OUTFLOWVALVE SELECTOR PANEL INDICATOR AND THE OUTFLOWVALVE INDICATOR FEEDBACK ASSEMBLY IN THE MANUALMODE (MANUAL MODE FOR DIGITAL CONTROLLERS ANDMANUAL AC AND DC MODE FOR ANALOG CONTROLLERS).

21-022-01 DISCARD - DISCARD THE AIR CYCLE MACHINE OIL. 21-024-01 DISCARD - DISCARD THE RAM AIR TURBOFAN OIL. 21-030-01 LUBRICATE - LUBRICATE THE RAM AIR INLET

COMPONENTS AND EXHAUST LOUVERS. 21-034-01 OPERATIONAL CHECK - OPERATIONALLY CHECK THE

ELECTRONIC/ELECTRICAL EQUIPMENT COOLING SYSTEMALTERNATE BLOWERS.

21-036-01 RESTORE - RESTORE THE EFIS COOLING AIR CLEANERAND THE EADI AND EHSI INLET AND OUTLET SCREENS BYCLEANING.

21-040-01 RESTORE - RESTORE THE EQUIPMENT COOLING SYSTEMLOW FLOW SENSOR BY CLEANING.

23-008-01 FUNCTION CHECK - FUNCTIONALLY CHECK THE VOICERECORDER FOR AUDIO FIDELITY.

23-014-01 OPERATIONAL CHECK - OPERATIONALLY CHECK THEOXYGEN MASK MICROPHONE.

24-006-02 DISCARD - DISCARD THE RIGHT ENGINE CSD LINE ANDINTEGRAL OIL FILTER ELEMENTS AND CSD CASE OIL.

24-016-01 DISCARD - DISCARD THE LEFT ENGINE VSCF GENERATORDRIVE LINE OIL FILTER ELEMENT AND VSCF CASE OIL.

24-028-01 FUNCTION CHECK - FUNCTIONALLY CHECK THE EXTERNALPOWER RECEPTACLE PINS FOR EXCESSIVE WEAR.

Task Relations


Model: BOEING 737-300/400/500


25-002-01 FUNCTION CHECK - FUNCTIONALLY CHECK THEHORIZONTAL ADJUSTMENT HOLES IN THE CAPTAINS ANDFIRST OFFICER SEAT TRACKS FOR ELONGATION ANDVERIFY THE CAPTAIN AND FIRST OFFICER SEAT TRACKSFOR WEAR, CONDITION, AND SECURITY.

25-006-01 OPERATIONAL CHECK - OPERATIONALLY CHECK THECAPTAIN, FIRST OFFICER, AND THE FIRST OBSERVER SEATHARNESS INERTIA REELS.

25-008-01 DETAILED INSPECTION - INSPECT (DETAILED) THEPASSENGER SEAT BELTS FOR WEAR, CONDITION, ANDSECURITY WITH SEAT BELTS INSTALLED.

25-010-01 OPERATIONAL CHECK - OPERATIONALLY CHECK THEPASSENGER SEAT BREAK-OVER FEATURE ON ALL SEATSADJACENT (FORWARD AND AFT) TO ALL OF THEEMERGENCY EXITS.

25-012-01 DETAILED INSPECTION - INSPECT (DETAILED) THEPASSENGER SEAT BACK RECLINE AND RECLINERESTRICTION MECHANISMS FOR CONDITION, SECURITY,AND PROPER OPERATION.

25-014-01 DETAILED INSPECTION - INSPECT (DETAILED) THEATTENDANT SEAT BOTTOMS FOR PROPER RETRACTION,CONDITION, AND SECURITY.

25-016-01 DETAILED INSPECTION - INSPECT (DETAILED) THEATTENDANT SEAT HARNESS FOR WEAR, CONDITION, ANDSECURITY WITH HARNESS INSTALLED.

25-018-01 OPERATIONAL CHECK - OPERATIONALLY CHECK THEATTENDANT SEAT HARNESS INERTIA REEL LOCK FEATUREAND THE INERTIA REEL.

25-024-01 GENERAL VISUAL INSPECTION - INSPECT (GENERALVISUAL) THE ELECTRONIC COMPARTMENT MOISTURESHROUDS.

25-038-01 DETAILED INSPECTION - INSPECT (DETAILED) THEEMERGENCY ESCAPE SLIDE COMPARTMENTS AND THEESCAPE SLIDE COMPONENTS, WITHOUT REMOVING THESLIDE, FOR SECURITY AND CONDITION.

25-060-01 OPERATIONAL CHECK - OPERATIONALLY CHECK THEPOWER MEGAPHONES.

25-068-01 VISUALLY CHECK - VISUALLY CHECK THE DETACHABLEEMERGENCY EQUIPMENT (GLOVES, SMOKE GOGGLES,CRASH AXE, FLASHLIGHTS AS APPLICABLE) FORCONDITION AND PRESENCE.

26-070-01 DETAILED INSPECTION - INSPECT (DETAILED) THE FUSIBLETIPS AND DISCHARGE TUBES OF LAVATORY FIRE BOTTLE.

Task Relations


Model: BOEING 737-300/400/500


27-004-01 OPERATIONAL CHECK - OPERATIONALLY CHECK THEAILERON TRANSFER MECHANISM.

27-006-01 GENERAL VISUAL INSPECTION - INSPECT (GENERALVISUAL) THE AILERON TRANSFER MECHANISM.

27-012-01 DETAILED INSPECTION - INSPECT (DETAILED) THE AILERONARTIFICIAL FEEL AND CENTERING SPRINGS.

27-014-01 OPERATIONAL CHECK - OPERATIONALLY CHECK(HYDRAULIC POWER OFF) THE AILERON CONTROLSURFACES FOR FULL RANGE OF TRAVEL AND FREEDOM OFMOVEMENT.

27-018-01 LUBRICATE - LUBRICATE THE AILERON MECHANICALCONTROL PATH.

27-020-01 DETAILED INSPECTION - INSPECT (DETAILED) THE AILERONBALANCE BAY SEALS.

27-026-01 GENERAL VISUAL INSPECTION - INSPECT (GENERALVISUAL) THE AILERON SYSTEM MECHANICAL COMPONENTSFROM THE CONTROL WHEEL TO THE AILERON POWERCONTROL UNIT.

27-028-01 GENERAL VISUAL INSPECTION - INSPECT (GENERALVISUAL) THE AILERON SYSTEM MECHANICAL COMPONENTSFROM THE POWER CONTROL UNIT TO THE AILERONS.

27-030-01 DETAILED INSPECTION - INSPECT (DETAILED) THE AILERONCONTROL CABLES BETWEEN THE AILERONS AND THEPOWER CONTROL UNIT.

27-032-01 GENERAL VISUAL INSPECTION - INSPECT (GENERALVISUAL) THE FORWARD RUDDER MECHANICAL CONTROLPATH.

27-034-01 LUBRICATE - LUBRICATE THE RUDDER FEEL ANDCENTERING SPRING SLIDER.

27-040-01 GENERAL VISUAL INSPECTION - INSPECT (GENERALVISUAL) THE STANDBY RUDDER POWER CONTROL UNITWITH HYDRAULIC POWER ON.

27-046-01 DETAILED INSPECTION - INSPECT (DETAILED) THESTANDBY RUDDER FORE AND AFT ATTACHMENT FITTINGSAND BOLTS.

27-050-01 OPERATIONAL CHECK - OPERATIONALLY CHECK THERUDDER TRIM THROUGH THE FULL RANGE OF TRAVEL.

27-052-01 LUBRICATE - LUBRICATE THE RUDDER MAIN POWERCONTROL UNIT ROD END AND RUDDER HINGES.

27-058-01 DETAILED INSPECTION - INSPECT (DETAILED) THE AFTRUDDER CONTROL COMPONENTS.

Task Relations


Model: BOEING 737-300/400/500


27-066-01 OPERATIONAL CHECK - OPERATIONALLY CHECK THERUDDER PRESSURE REDUCER.

27-068-01 LUBRICATE - LUBRICATE THE ELEVATOR MECHANICALCONTROL PATH.

27-070-01 GENERAL VISUAL INSPECTION - INSPECT (GENERALVISUAL) THE ELEVATOR MECHANICAL CONTROL PATH.

54-812-01 ACCOMPLISH - INTERNAL - ZONAL (GV) FORWARD STRUTFAIRING - ENGINE NO. 2

54-814-01 ACCOMPLISH - INTERNAL - ZONAL (GV) FAN COWLSUPPORT BEAM - ENGINE NO. 2

54-816-01 ACCOMPLISH - INTERNAL - ZONAL (GV) STRUT TORQUEBOX - ENGINE NO. 2 (EZAP)

55-306-01 GENERAL VISUAL INSPECTION - EXTERNAL-GENERALVISUAL INSPECTION: INSPECT THE HORIZONTALSTABILIZER EXTERNAL SURFACES INCLUDING SKINS,ELEVATORS, TRAILING EDGE BEAMS AND PANELS.

55-320-01 GENERAL VISUAL INSPECTION - EXTERNAL-GENERALVISUAL INSPECTION: INSPECT THE VERTICAL STABILIZEREXTERIOR SURFACE INCLUDING SKINS, TRAILING EDGEPANELS, AND RUDDER.

55-802-01 ACCOMPLISH - INTERNAL - ZONAL (GV) VERTICALSTABILIZER (EZAP)

55-804-01 ACCOMPLISH - EXTERNAL - ZONAL (GV) VERTICALSTABILIZER

55-808-01 ACCOMPLISH - EXTERNAL - ZONAL (GV) VERTICALSTABILIZER TIP

55-810-01 ACCOMPLISH - EXTERNAL - ZONAL (GV) RUDDER 55-812-01 ACCOMPLISH - INTERNAL - ZONAL (GV) HORIZONTAL

STABILIZER - LEFT 55-814-01 ACCOMPLISH - EXTERNAL - ZONAL (GV) HORIZONTAL

STABILIZER- LEFT 55-816-01 ACCOMPLISH - INTERNAL - ZONAL (GV) HORIZONTAL

STABILIZER - RIGHT 55-818-01 ACCOMPLISH - EXTERNAL - ZONAL (GV) HORIZONTAL

STABILIZER - RIGHT 55-820-01 ACCOMPLISH - EXTERNAL - ZONAL (GV) HORIZONTAL

STABILIZER - ELEVATOR - LEFT 55-822-01 ACCOMPLISH - EXTERNAL - ZONAL (GV) HORIZONTAL

STABILIZER - ELEVATOR - RIGHT

Task Relations


Model: BOEING 737-300/400/500


56-002-01 LUBRICATE - LUBRICATE THE INSIDE MECHANISMS OF THEPILOTS AND CO-PILOTS #2 SLIDING WINDOWS.

56-004-01 LUBRICATE - LUBRICATE THE EXTERNAL RELEASEMECHANISM OF THE CO-PILOTS #2 SLIDING WINDOW.

27-152-01 GENERAL VISUAL INSPECTION - INSPECT (GENERALVISUAL) THE TRAILING EDGE FLAP DRIVE TORQUE TUBES.

27-154-01 GENERAL VISUAL INSPECTION - INSPECT (GENERALVISUAL) THE TRAILING EDGE FLAP RIGHT ANGLE GEARBOX.

27-156-01 GENERAL VISUAL INSPECTION - INSPECT (GENERALVISUAL) THE TRAILING EDGE FLAP LANDING GEAR BEAMANGLE GEARBOX.

27-158-01 GENERAL VISUAL INSPECTION - INSPECT (GENERALVISUAL) THE TRAILING EDGE FLAP FORWARD CONTROLQUADRANT.

27-160-01 GENERAL VISUAL INSPECTION - INSPECT (GENERALVISUAL) THE TRAILING EDGE FLAP POSITION TRANSMITTERGEARBOX.

27-170-01 DETAILED INSPECTION - INSPECT (DETAILED) THE SPOILERCONTROL CABLES BETWEEN THE SPOILER MIXER ANDSPOILER ACTUATORS.

27-172-01 LUBRICATE - LUBRICATE THE SPEED BRAKE LEVER BRAKEMECHANISM.

27-174-01 LUBRICATE - LUBRICATE THE GROUND AND FLIGHTSPOILER MECHANICAL CONTROL PATH INCLUDING:GROUND SPOILER ACTUATOR PILLOW BLOCKS.

27-176-01 GENERAL VISUAL INSPECTION - INSPECT (GENERALVISUAL) THE GROUND AND FLIGHT SPOILER ACTUATORS.

27-178-01 GENERAL VISUAL INSPECTION - INSPECT (GENERALVISUAL) THE AUTO SPEED BRAKE ELECTRIC ACTUATOR,ACTUATOR ROD END AND FORWARD ATTACHMENT POINT.

27-180-01 OPERATIONAL CHECK - OPERATIONALLY CHECK THESPEED BRAKE REFUSED TAKEOFF SYSTEM.

27-184-01 GENERAL VISUAL INSPECTION - INSPECT (GENERALVISUAL) THE LEADING EDGE FLAP/SLAT ACTUATORS ANDEXTENSION MECHANISMS.

27-188-01 OPERATIONAL CHECK - OPERATIONALLY CHECK THELEADING EDGE FLAPS AND SLATS FOR UNCOMMANDEDEXTENSION WITH STANDBY HYDRAULIC POWER.

27-190-01 OPERATIONAL CHECK - OPERATIONALLY CHECK THELEADING EDGE FLAP AND SLAT ALTERNATE EXTENSIONSYSTEM.

Task Relations


Model: BOEING 737-300/400/500


27-192-01 FUNCTION CHECK - FUNCTIONALLY CHECK THE AUTOSLATSYSTEM.

28-002-01 FUNCTION CHECK - FUNCTIONALLY CHECK THE LEFT WINGFUEL SURGE TANK PRESSURE RELIEF VALVE.

28-002-02 FUNCTION CHECK - FUNCTIONALLY CHECK THE RIGHTWING FUEL SURGE TANK PRESSURE RELIEF VALVE.

28-004-01 DETAILED INSPECTION - INSPECT (DETAILED) THE LEFTWING FUEL SURGE TANK VENT FLAME ARRESTORS FORCLOGGING, CONDITION AND SECURITY.

28-004-02 DETAILED INSPECTION - INSPECT (DETAILED) THE RIGHTWING FUEL SURGE TANK VENT FLAME ARRESTORS FORCLOGGING, CONDITION AND SECURITY.

28-006-01 RESTORE - RESTORE (CLEAN) THE LEFT WING ENGINEFUEL FEED SYSTEM WATER SCAVENGE EJECTOR PUMP.

28-006-02 RESTORE - RESTORE (CLEAN) THE RIGHT WING ENGINEFUEL FEED SYSTEM WATER SCAVENGE EJECTOR PUMP.

29-010-01 DISCARD - DISCARD THE LEFT ENGINE DRIVEN HYDRAULICPUMP CASE DRAIN FILTERS.

29-010-02 DISCARD - DISCARD THE RIGHT ENGINE DRIVENHYDRAULIC PUMP CASE DRAIN FILTERS.

29-012-01 DETAILED INSPECTION - INSPECT (DETAILED) THEHYDRAULIC RESERVOIR PRESSURIZATION MODULE VENTCAPS FOR CLOGGED CONDITION.

29-014-01 RESTORE - RESTORE THE HYDRAULIC RESERVOIRPRESSURIZATION MODULE FILTER BY CLEANING.

29-016-01 OPERATIONAL CHECK - OPERATIONALLY CHECK THEELECTRIC MOTOR DRIVEN HYDRAULIC PUMP GROUNDFAULT PROTECTION SYSTEM.

29-042-01 OPERATIONAL CHECK - OPERATIONALLY CHECK THEHYDRAULIC POWER TRANSFER UNIT AND CONTROLSYSTEM TO INCLUDE A VISUAL CHECK OF THE CONTROLVALVE FOR PROPER POSITION.

31-010-01 FUNCTION CHECK - FUNCTIONALLY CHECK THE CABINALTITUDE WARNING SWITCH.

31-012-01 FUNCTION CHECK - FUNCTIONALLY CHECK THE FLIGHTDATA RECORDER SYSTEM TO VERIFY THAT ALL REQUIREDPARAMETERS ARE RECORDED (DATA CHECKEDOFF-AIRCRAFT).

32-804-01 ACCOMPLISH - EXTERNAL - ZONAL (GV) LEFT MAINLANDING GEAR AND LANDING GEAR DOORS

Task Relations


Model: BOEING 737-300/400/500


32-808-01 ACCOMPLISH - EXTERNAL - ZONAL (GV) RIGHT MAINLANDING GEAR AND LANDING GEAR DOORS (EZAP)

33-002-01 LUBRICATE - LUBRICATE THE OUTBOARD LANDING LIGHTMECHANISM.

33-008-01 OPERATIONAL CHECK - OPERATIONALLY CHECKEMERGENCY LIGHTS USING FLIGHT DECK AND ATTENDANTPANEL SWITCHES.

33-010-01 FUNCTION CHECK - FUNCTIONALLY CHECK EMERGENCYLIGHT BATTERY PACKS FOR CAPACITY (15 MINUTES) ANDONE DEEP CYCLE.

34-006-01 OPERATIONAL CHECK - OPERATIONALLY CHECK THE EFISTRANSFER SWITCH.

35-006-01 VISUALLY CHECK - VISUALLY CHECK (CROSS CHECK) THEFLIGHT CREW OXYGEN BOTTLE PRESSURE INDICATOR ANDTHE CONTROL COMPARTMENT FLIGHT CREW OXYGENINDICATOR.

35-012-01 OPERATIONAL CHECK - OPERATIONALLY CHECK EACHFLIGHT CREW OXYGEN MASK/REGULATOR (APPLICABLE TOOUT OF THE BOX ASSEMBLY).

35-016-01 GENERAL VISUAL INSPECTION - INSPECT (GENERALVISUAL) THE BOX STOWED FLIGHT CREW OXYGEN MASKS.

49-097-01 GENERAL VISUAL INSPECTION - INSPECT (GENERALVISUAL) THE VISIBLE PORTIONS OF THE UPPER & LOWERAPU SHROUDS & THE LOCK HANDLE ASSEMBLY.

49-098-01 GENERAL VISUAL INSPECTION - INSPECT (GENERALVISUAL) THE APU INTAKE DOOR AND ATTACHMENTS.

49-114-01 DISCARD - DISCARD THE APU STARTER BRUSHES ANDINSPECT (DETAILED) THE STARTER EXTERIOR CONDITION.

49-116-01 DETAILED INSPECTION - INSPECT (DETAILED) THE APUIGNITER PLUG.

49-117-01 OPERATIONAL CHECK - OPERATIONALLY CHECK THE APUCOOLING AIR SHUT-OFF VALVE.

49-120-01 GENERAL VISUAL INSPECTION - INSPECT (GENERALVISUAL) THE APU EXHAUST AFT FAIRING ASSEMBLYCOOLING AIR INTAKE.

49-122-01 GENERAL VISUAL INSPECTION - INSPECT (GENERALVISUAL) THE APU EXHAUST HEAT SHIELD ASSEMBLY. ALSOINSPECT THE DUCT ALIGNMENT ASSEMBLY IF INSTALLED.

Task Relations


Model: BOEING 737-300/400/500


49-124-01 GENERAL VISUAL INSPECTION - INSPECT (GENERALVISUAL) THE APU EXHAUST DRIP PAN ASSEMBLY ANDEXHAUST DUCT MUFFLER/FELT LINER ASSEMBLY. ALSOINSPECT THE BONDING JUMPERS IF INSTALLED.

52-002-01 LUBRICATE - LUBRICATE THE ENTRY AND SERVICE DOORHANDLE MECHANISMS AND TORQUE TUBE HANDLE BOXBEARINGS (ALL 4 DOORS), AND THE FORWARD ENTRYDOOR STOP RODS.

72-050-02 DETAILED INSPECTION - INSPECT (DETAILED) THE RIGHTAFT ENGINE MOUNT LUGS FOR STRUCTURAL INTEGRITYAND DEFORMATION.

73-006-01 DISCARD THE LEFT ENGINE FUEL FILTER CARTRIDGE(ELEMENT).

73-006-02 DISCARD THE RIGHT ENGINE FUEL FILTER CARTRIDGE(ELEMENT).

74-008-01 DETAILED INSPECTION - INSPECT (DETAILED) THE LEFTENGINE IGNITER PLUGS.

74-008-02 DETAILED INSPECTION - INSPECT (DETAILED) THE RIGHTENGINE IGNITER PLUGS.

74-010-01 DETAILED INSPECTION - INSPECT (DETAILED) THE LEFTENGINE IGNITION LEADS.

74-010-02 DETAILED INSPECTION - INSPECT (DETAILED) THE RIGHTENGINE IGNITION LEADS.

76-002-01 DETAILED INSPECTION - INSPECT (DETAILED) THE LEFTENGINE CONTROL CABLES (EXPOSED) IN THE WINGFORWARD OF THE FRONT SPAR.

76-002-02 DETAILED INSPECTION - INSPECT (DETAILED) THE RIGHTENGINE CONTROL CABLES (EXPOSED) IN THE WINGFORWARD OF THE FRONT SPAR.

78-004-01 DETAILED INSPECTION - INSPECT (DETAILED) THE LEFTENGINE TURBINE EXHAUST FIRE SEAL (SEAL SPRINGS,SEAL CARRIER, AND CLAMP STRIP).

78-004-02 DETAILED INSPECTION - INSPECT (DETAILED) THE RIGHTENGINE TURBINE EXHAUST FIRE SEAL (SEAL SPRINGS,SEAL CARRIER, AND CLAMP STRIP).

78-006-01 DETAILED INSPECTION - INSPECT (DETAILED) THE LEFTENGINE THRUST REVERSER FIRE SEAL.

78-006-02 DETAILED INSPECTION - INSPECT (DETAILED) THE RIGHTENGINE THRUST REVERSER FIRE SEAL.

78-008-01 OPERATIONAL CHECK - OPERATIONALLY CHECK THE LEFTENGINE THRUST REVERSER SYNC LOCKS.

Task Relations


Model: BOEING 737-300/400/500


78-008-02 OPERATIONAL CHECK - OPERATIONALLY CHECK THERIGHT ENGINE THRUST REVERSER SYNC LOCKS.

78-010-01 FUNCTION CHECK - FUNCTIONALLY CHECK THE LEFTENGINE THRUST REVERSER HYDRAULIC LOCKINGACTUATOR (LOCKING/AUTO RESTOW FUNCTION).

78-010-02 FUNCTION CHECK - FUNCTIONALLY CHECK THE RIGHTENGINE THRUST REVERSER HYDRAULIC LOCKINGACTUATOR (LOCKING/AUTO RESTOW FUNCTION).

52-818-01 ACCOMPLISH - INTERNAL - ZONAL (GV) AFT GALLEYSERVICE DOOR

52-820-01 ACCOMPLISH - EXTERNAL - ZONAL (GV) RIGHTEMERGENCY EXIT HATCH

52-828-01 ACCOMPLISH - EXTERNAL - ZONAL (GV) LEFT EMERGENCYEXIT HATCH

52-844-01 ACCOMPLISH - INTERNAL - ZONAL (GV) FORWARD CARGODOOR

52-848-01 ACCOMPLISH - INTERNAL - ZONAL (GV) AFT CARGO DOOR 53-300-01 GENERAL VISUAL INSPECTION - EXTERNAL-GENERAL

VISUAL INSPECTION: INSPECT THE EXTERIOR SURFACE OFTHE FUSELAGE FROM BS 178 TO BS 1217 AND LANDINGGEAR BAYS INCLUDING SKIN PANELS AND SKIN SPLICES,CUT-OUTS, FORWARD FACE OF THE FORWARD PRESSUREBULKHEAD AT BS 178, LOWER SURFACE OF THE PRESSUREDECK FROM BS 663.75 TO BS 727, BS 663.75 AND BS 727BULKHEADS, THE EXTERIOR OF THE KEEL BEAM FROM BS663.75 TO BS 727, AND LANDING GEAR SUPPORTSTRUCTURE.

53-306-01 GENERAL VISUAL INSPECTION - INTERNAL-GENERALVISUAL INSPECTION: INSPECT THE AREAS UNDER GALLEYSAND LAVATORIES (IF INSTALLED).

53-330-01 DETAILED INSPECTION - EXTERNAL-DETAILEDINSPECTION: INSPECT THE FORWARD AND AFT CARGODOOR STOP PAD FITTINGS.

53-338-01 DETAILED INSPECTION - EXTERNAL-DETAILEDINSPECTION: INSPECT THE ENTRY AND GALLEY SERVICEDOOR SURROUND STRUCTURE INCLUDING DOOR STOPPAD FITTINGS, LATCHES, AND HINGES.

53-352-01 GENERAL VISUAL INSPECTION - EXTERNAL-GENERALVISUAL INSPECTION: INSPECT STRINGER 18A WEB, CHORDAND LINKS.

53-354-01 GENERAL VISUAL INSPECTION - EXTERNAL-GENERALVISUAL INSPECTION: INSPECT TRUNNION BEAM SUPPORTFRAME, STA. 706.

Task Relations


Model: BOEING 737-300/400/500


53-356-01 GENERAL VISUAL INSPECTION - EXTERNAL-GENERALVISUAL INSPECTION: INSPECT THE LOWER FRAME, STA.695.

53-360-01 GENERAL VISUAL INSPECTION - EXTERNAL-GENERALVISUAL INSPECTION: INSPECT THE SIDE STRUT SUPPORTFRAME, STA. 685.

53-362-01 GENERAL VISUAL INSPECTION - EXTERNAL-GENERALVISUAL INSPECTION: INSPECT THE PRESSURE DECKATTACHMENT-TO-REAR SPAR EXTENSION.

53-364-01 GENERAL VISUAL INSPECTION - EXTERNAL-GENERALVISUAL INSPECTION: INSPECT THE FLAP TRACK FITTINGS.

53-366-01 GENERAL VISUAL INSPECTION - EXTERNAL-GENERALVISUAL INSPECTION: INSPECT THE UPPER DOOR SKINPANEL, STA. 888 TO 1016 (STR. 4-14).

53-368-01 GENERAL VISUAL INSPECTION - EXTERNAL-GENERALVISUAL INSPECTION: INSPECT THE LOWER DOOR SKINPANEL, STA. 888 TO 1016 (STR. 14-24).

53-800-01 ACCOMPLISH - EXTERNAL - ZONAL (GV) FLIGHTCOMPARTMENT

53-802-01 ACCOMPLISH - INTERNAL - ZONAL (GV) FLIGHTCOMPARTMENT

53-806-01 ACCOMPLISH - INTERNAL - ZONAL (GV) - FORWARDLAVATORY (IF INSTALLED) (EZAP)

53-810-01 ACCOMPLISH - EXTERNAL - ZONAL (GV) FORWARD HALFOF CABIN - AFT OF CONTROL CABIN TO BS 627.5

53-812-01 ACCOMPLISH - INTERNAL - ZONAL (GV) FORWARD HALF OFCABIN - AFT OF CONTROL CABIN TO BS 627.5

53-816-01 ACCOMPLISH - EXTERNAL - ZONAL (GV) AFT HALF OFCABIN - BS 627.5 TO AFT BULKHEAD

53-818-01 ACCOMPLISH - INTERNAL - ZONAL (GV) AFT HALF OF CABIN- BS 627.5 TO AFT BULKHEAD

53-822-01 ACCOMPLISH - INTERNAL - ZONAL (GV) AFT GALLEY (IFINSTALLED)

53-824-01 ACCOMPLISH - INTERNAL - ZONAL (GV) AFT LAVATORY (IFINSTALLED) (EZAP)

53-826-01 ACCOMPLISH - INTERNAL - ZONAL (GV) AFT LEFT GALLEY(IF INSTALLED)

53-830-01 ACCOMPLISH - INTERNAL - ZONAL (GV) AFT RIGHT GALLEY(IF INSTALLED)

Task Relations


Model: BOEING 737-300/400/500


53-832-01 ACCOMPLISH - INTERNAL - ZONAL (GV) AFT RIGHTLAVATORY (IF INSTALLED) (EZAP)

53-834-01 ACCOMPLISH - INTERNAL - ZONAL (GV) AFT LAVATORY(EZAP)

53-838-01 ACCOMPLISH - INTERNAL - ZONAL (GV) RADOME 53-840-01 ACCOMPLISH - INTERNAL - ZONAL (GV) LOWER NOSE

COMPARTMENT (EZAP) 53-844-01 ACCOMPLISH - INTERNAL - ZONAL (GV) ELECTRICAL

COMPARTMENT (EZAP) 53-846-01 ACCOMPLISH - INTERNAL - ZONAL (GV) ELECTRICAL

COMPARTMENT ACCESS DOOR 53-848-01 ACCOMPLISH - INTERNAL - ZONAL (GV) FORWARD

AIRSTAIR COMPARTMENT (EZAP) 53-858-01 ACCOMPLISH - INTERNAL - ZONAL (GV) AIR CONDITIONING

DISTRIBUTION BAY (EZAP) 53-860-01 ACCOMPLISH - INTERNAL - ZONAL (GV) RAM AIR DUCT

(EZAP) 53-862-01 ACCOMPLISH - INTERNAL - ZONAL (GV) AIR CONDITIONING

EQUIPMENT BAY (EZAP) 53-864-01 ACCOMPLISH - INTERNAL - ZONAL (GV) KEEL BEAM (EZAP) 53-874-01 ACCOMPLISH - INTERNAL - ZONAL (GV) AFT CARGO

COMPARTMENT EQUIPMENT BAY (EZAP) 53-888-01 ACCOMPLISH - INTERNAL - ZONAL (GV) TAIL

COMPARTMENT - AREA AFT OF PRESSURE BULKHEAD ANDABOVE APU COMPARTMENT (EZAP)

53-890-01 ACCOMPLISH - INTERNAL - ZONAL (GV) APUCOMPARTMENT (EZAP)

53-892-01 ACCOMPLISH - INTERNAL - ZONAL (GV) TAIL CONE (EZAP) 54-804-01 ACCOMPLISH - INTERNAL - ZONAL (GV) FORWARD STRUT

FAIRING - ENGINE NO. 1 54-806-01 ACCOMPLISH - INTERNAL - ZONAL (GV) FAN COWL

SUPPORT BEAM - ENGINE NO. 1 54-808-01 ACCOMPLISH - INTERNAL - ZONAL (GV) STRUT TORQUE

BOX - ENGINE NO. 1 (EZAP) 54-810-01 ACCOMPLISH - INTERNAL - ZONAL (GV) AFT STRUT FAIRING

- ENGINE NO. 1 (EZAP) 78-012-01 GENERAL VISUAL INSPECTION - INSPECT (GENERAL

VISUAL) THE LEFT ENGINE THRUST REVERSER CONTROLVALVE MODULE.

Task Relations


Model: BOEING 737-300/400/500


78-012-02 GENERAL VISUAL INSPECTION - INSPECT (GENERALVISUAL) THE RIGHT ENGINE THRUST REVERSER CONTROLVALVE MODULE.

79-016-01 DISCARD THE LEFT ENGINE OIL SCAVENGE FILTERELEMENT.

79-016-02 DISCARD THE RIGHT ENGINE OIL SCAVENGE FILTERELEMENT.

79-020-01 DISCARD THE MAIN LEFT ENGINE OIL SUPPLY FILTERELEMENT.

79-020-02 DISCARD THE MAIN RIGHT ENGINE OIL SUPPLY FILTERELEMENT.

28-007-01 OPERATIONAL CHECK - OPERATIONALLY CHECK THE LEFTENGINE SUCTION FEED SYSTEM.

28-007-02 OPERATIONAL CHECK - OPERATIONALLY CHECK THERIGHT ENGINE SUCTION FEED SYSTEM.

52-CMR-01 FUNCTIONALLY CHECK OF THE LOCKING AND UNLOCKINGLATCH BOLT MECHANISM ON THE FLIGHT DECK DOORDECOMPRESSION PANEL.

55-302-01 INTERNAL DETAILED INSPECTION ; INSPECT THEHORIZONTAL STABILIZER CENTERSECTION-TO-HORIZONTAL STABILIZER FRONT AND REARSPAR ATTACHMENT FITTINGS.

32-015-00 INSPECT (DETAILED) NOSE LANDING GEAR AXLE. 20-039-01 INSPECT (GENERAL VISUAL) ALL VISIBLE EWIS IN THE MAIN

WHEEL WELLS. (EZAP) 20-072-01 INSPECT (GENERAL VISUAL) A/C GENERATOR POWER

FEEDERS AND CONNECTED EWIS IN THE LEFT INBOARDLEADING EDGE. (EZAP)

20-074-01 INSPECT (GENERAL VISUAL) A/C GENERATOR POWERFEEDERS AND CONNECTED EWIS IN THE RIGHT INBOARDLEADING EDGE. (EZAP)

20-080-01 INSPECT (GENERAL VISUAL) THE EWIS AND WIRE BUNDLESCONNECTED TO THE ELEVATOR PCUS. (EZAP)

ICA-25-053-04 PERFORM A DETAILED INSPECTION OF THE SLIDINGCARPET SYSTEM TO DETECT OBVIOUS DAMAGE,CORROSION, SECURITY AND GENERAL CONDITION

ICA-25-053-05 PERFORM A FUNCTIONAL CHECK OF THE SLIDING CARPETSYSTEM TO DETERMINE IF ONE OR MORE FUNCTIONS OFAN ITEM PERFORM WITHIN SPECIFIED LIMITS

Task Relations


Model: BOEING 737-300/400/500


56-006-01 OPERATIONAL CHECK - OPERATIONALLY CHECK THEINSIDE RELEASE MECHANISMS FOR THE PILOTS ANDCOPILOTS #2 SLIDING WINDOWS AND OPERATIONALLYCHECK THE CO-PILOTS #2 SLIDING WINDOW FROM THEOUTSIDE.

56-010-01 GENERAL VISUAL INSPECTION - INSPECT (GENERALVISUAL) THE PILOTS AND CO-PILOTS #2 SLIDING WINDOWSILL DRAIN FOR OBVIOUS DAMAGE, CLOGGING,CONDITION, AND SECURITY.

57-308-01 DETAILED INSPECTION - INTERNAL-DETAILED INSPECTION:INSPECT THE EXTERNAL WING SKIN SURFACE AROUNDFLAP TRACK ATTACH POINTS.

57-334-01 GENERAL VISUAL INSPECTION - INTERNAL-GENERALVISUAL INSPECTION: INSPECT THE MAIN FLAP TRACKS,AND FORWARD AND REAR SPAR ATTACH FITTINGS.

57-338-01 GENERAL VISUAL INSPECTION - INTERNAL-GENERALVISUAL INSPECTION: INSPECT THE STABILIZING LINKSBETWEEN THE MAIN LANDING GEAR BEAM AND THE REARSPAR AT THE REAR SPAR BRACKETS.

57-340-01 GENERAL VISUAL INSPECTION - INTERNAL-GENERALVISUAL INSPECTION: INSPECT THE MAIN LANDING GEARBEAM INBOARD SUPPORT LINK.

57-802-01 ACCOMPLISH - EXTERNAL - ZONAL (GV) LEFT WING TIP 57-806-01 ACCOMPLISH - EXTERNAL - ZONAL (GV) OUTBOARD

LEADING EDGE INCLUDING SLATS - LEFT WING 57-808-01 ACCOMPLISH - INTERNAL - ZONAL (GV) OUTBOARD

LEADING EDGE - LEFT WING (SLATS DEPLOYED - REMOVALOF INTERNAL SLAT PANELS NOT REQUIRED). (EZAP)

57-810-01 ACCOMPLISH - EXTERNAL - ZONAL (GV) INBOARD LEADINGEDGE INCLUDING KRUEGER FLAPS - LEFT WING

57-812-01 ACCOMPLISH - INTERNAL - ZONAL (GV) INBOARD LEADINGEDGE INCLUDING KRUEGER FLAPS - LEFT WING (FLAPSDEPLOYED) (EZAP)

57-814-01 ACCOMPLISH - EXTERNAL - ZONAL (GV) FUEL VENT SURGETANK - LEFT WING

57-818-01 ACCOMPLISH - EXTERNAL - ZONAL (GV) MAIN FUEL TANK -LEFT WING

57-822-01 ACCOMPLISH - EXTERNAL - ZONAL (GV) WING TRAILINGEDGE, AILERON AND CONTROL TAB - LEFT WING

57-824-01 ACCOMPLISH - INTERNAL - ZONAL (GV) WING TRAILINGEDGE, AILERON AND CONTROL TAB (AILERON CONTROLAREA ONLY) - LEFT WING

Task Relations


Model: BOEING 737-300/400/500


57-828-01 ACCOMPLISH - EXTERNAL - ZONAL (GV) WING TRAILINGEDGE, OUTBOARD FLAP AND SPOILERS - LEFT WING(FLAPS EXTENDED, SPOILERS RAISED)

57-830-01 ACCOMPLISH - INTERNAL - ZONAL (GV) WING TRAILINGEDGE, OUTBOARD FLAP AND SPOILERS - LEFT WING(FLAPS EXTENDED)

57-834-01 ACCOMPLISH - EXTERNAL - ZONAL (GV) WING FIXEDTRAILING EDGE BETWEEN FLAPS - LEFT WING

57-838-01 ACCOMPLISH - EXTERNAL - ZONAL (GV) WING TRAILINGEDGE INBOARD FLAP AND SPOILERS AND REAR SPAR TOLANDING GEAR SUPPORT BEAM - LEFT WING (FLAPSEXTENDED, SPOILERS RAISED)

57-840-01 ACCOMPLISH - INTERNAL - ZONAL (GV) WING TRAILINGEDGE INBOARD FLAP AND SPOILERS - LEFT WING (FLAPEXTENDED, SPOILERS RAISED)

57-846-01 ACCOMPLISH - EXTERNAL - ZONAL (GV) RIGHT WING TIP 57-850-01 ACCOMPLISH - EXTERNAL - ZONAL (GV) OUTBOARD

LEADING EDGE INCLUDING SLATS - RIGHT WING 57-852-01 ACCOMPLISH - INTERNAL - ZONAL (GV) OUTBOARD

LEADING EDGE - RIGHT WING (SLATS DEPLOYED -REMOVAL OF INTERNAL SLAT PANELS NOT REQUIRED).(EZAP)

57-854-01 ACCOMPLISH - EXTERNAL - ZONAL (GV) INBOARD LEADINGEDGE INCLUDING KRUEGER FLAPS - RIGHT WING

57-856-01 ACCOMPLISH - INTERNAL - ZONAL (GV) INBOARD LEADINGEDGE INCLUDING KRUEGER FLAPS - RIGHT WING (FLAPSDEPLOYED) (EZAP)

57-858-01 ACCOMPLISH - EXTERNAL - ZONAL (GV) FUEL VENT SURGETANK - RIGHT WING

57-862-01 ACCOMPLISH - EXTERNAL - ZONAL (GV) MAIN FUEL TANK -RIGHT WING

57-866-01 ACCOMPLISH - EXTERNAL - ZONAL (GV) WING TRAILINGEDGE, AILERON AND CONTROL TAB - RIGHT WING

57-868-01 ACCOMPLISH - INTERNAL - ZONAL (GV) WING TRAILINGEDGE, AILERON AND CONTROL TAB (AILERON CONTROLAREA ONLY) - RIGHT WING

57-872-01 ACCOMPLISH - EXTERNAL - ZONAL (GV) WING TRAILINGEDGE, OUTBOARD FLAP AND SPOILERS - RIGHT WING(FLAPS EXTENDED, SPOILERS RAISED)

Task Relations


Model: BOEING 737-300/400/500


57-874-01 ACCOMPLISH - INTERNAL - ZONAL (GV) WING TRAILINGEDGE, OUTBOARD FLAP AND SPOILERS - RIGHT WING(FLAPS EXTENDED)

57-878-01 ACCOMPLISH - EXTERNAL - ZONAL (GV) WING FIXEDTRAILING EDGE BETWEEN FLAPS - RIGHT WING

57-882-01 ACCOMPLISH - EXTERNAL - ZONAL (GV) WING TRAILINGEDGE INBOARD FLAP AND SPOILERS AND REAR SPAR TOLANDING GEAR SUPPORT BEAM - RIGHT WING (FLAPSEXTENDED, SPOILERS RAISED)

57-884-01 ACCOMPLISH - INTERNAL - ZONAL (GV) WING TRAILINGEDGE INBOARD FLAP AND SPOILERS - RIGHT WING (FLAPSEXTENDED, SPOILERS RAISED)

70-826-01 ACCOMPLISH - EXTERNAL - ZONAL (GV) THRUSTREVERSER - ENGINE NO. 1 (THRUST REVERSER IN STOWEDAND DEPLOYED POSITION) (EZAP)

70-828-01 ACCOMPLISH - EXTERNAL - ZONAL (GV) THRUSTREVERSER - ENGINE NO. 1 (INNER AND OUTER EXTERIORSURFACES)

70-830-01 ACCOMPLISH - EXTERNAL - ZONAL (GV) ENGINE NO. 1(EZAP)

70-838-01 ACCOMPLISH - EXTERNAL - ZONAL (GV) THRUSTREVERSER - ENGINE NO. 2 (THRUST REVERSER IN STOWEDAND DEPLOYED POSITION) (EZAP)

70-840-01 ACCOMPLISH - EXTERNAL - ZONAL (GV) THRUSTREVERSER - ENGINE NO. 2 (INNER AND OUTER EXTERIORSURFACES)

70-842-01 ACCOMPLISH - EXTERNAL - ZONAL (GV) ENGINE NO. 2(EZAP)

71-016-01 FUNCTION CHECK - FUNCTIONAL CHECK OF THE LEFTSTRUT DRAINS FOR BLOCKAGE.

71-016-02 FUNCTION CHECK - FUNCTIONAL CHECK OF THE RIGHTSTRUT DRAINS FOR BLOCKAGE.

72-018-01 LUBRICATE - LUBRICATE THE LEFT ENGINE FAN BLADEDOVETAIL PER MANUFACTURER'S INSTRUCTION.

72-018-02 LUBRICATE - LUBRICATE THE RIGHT ENGINE FAN BLADEDOVETAIL PER MANUFACTURER'S INSTRUCTION.

72-026-01 DETAILED INSPECTION - INSPECT (DETAILED) THE LEFTFORWARD ENGINE MOUNT ATTACHMENT FOR SECURITY,MISSING OR LOOSE BOLTS, DEFORMATION, AND GAPS ATCONNECTING JOINTS.

Task Relations


Model: BOEING 737-300/400/500


72-026-02 DETAILED INSPECTION - INSPECT (DETAILED) THE RIGHTFORWARD ENGINE MOUNT ATTACHMENT FOR SECURITY,MISSING OR LOOSE BOLTS, DEFORMATION, AND GAPS ATCONNECTING JOINTS.

72-050-01 DETAILED INSPECTION - INSPECT (DETAILED) THE LEFTAFT ENGINE MOUNT LUGS FOR STRUCTURAL INTEGRITYAND DEFORMATION.

050032 2C CHECK PKG TO54-316-01 DETAILED INSPECTION NO. 1 ENGINE -

INTERNAL-DETAILED INSPECTION: INSPECT THE PYLONOVERWING ATTACH FITTING COVERED BY THE FAIRINGAFT OF THE WING FRONT SPAR AT WBL 191.

54-316-01 DETAILED INSPECTION NO. 2 ENGINE -INTERNAL-DETAILED INSPECTION: INSPECT THE PYLONOVERWING ATTACH FITTING COVERED BY THE FAIRINGAFT OF THE WING FRONT SPAR AT WBL 191.

21-002-01 DISCARD - DISCARD THE RECIRCULATION SYSTEM FILTER. 23-004-01 FUNCTION CHECK - FUNCTIONALLY CHECK THE

RESISTANCE OF STATIC DISCHARGERS. 26-002-01 OPERATIONAL CHECK - OPERATIONALLY CHECK THE

LAVATORY SMOKE DETECTORS. 26-004-01 RESTORE - RESTORE THE LAVATORY SMOKE DETECTOR

GRILL BY CLEANING. 26-018-01 FUNCTION CHECK - FUNCTIONALLY CHECK THE ENGINE

SQUIB FIRING CIRCUIT USING THE ENGINE FIRE HANDLESWITCH.

26-024-01 FUNCTION CHECK - FUNCTIONALLY CHECK THE ENGINEFIRE EXTINGUISHING DISTRIBUTION LINES FOR LEAKAGEAND AIRFLOW.

26-026-01 OPERATIONAL CHECK - OPERATIONALLY CHECK THEENGINE FIRE HANDLE FOR ENGINE SHUTDOWN ANDISOLATION.

26-028-01 OPERATIONAL CHECK - OPERATIONALLY CHECK THEENGINE FIRE HANDLE LOCK OVERRIDE.

26-030-01 GENERAL VISUAL INSPECTION - INSPECT (GENERALVISUAL) THE ENGINE FIRE EXTINGUISHER DISTRIBUTIONSYSTEM AND FIRE BOTTLES.

26-036-01 FUNCTION CHECK - FUNCTIONALLY CHECK THE APU SQUIBFIRING CIRCUIT USING THE APU FIRE HANDLE SWITCH.

26-038-01 OPERATIONAL CHECK - OPERATIONALLY CHECK APU FIREHANDLE FOR APU SHUTDOWN AND ISOLATION.

Task Relations


Model: BOEING 737-300/400/500


26-040-01 OPERATIONAL CHECK - OPERATIONALLY CHECK APUREMOTE CONTROL PANEL.

26-042-01 GENERAL VISUAL INSPECTION - INSPECT (GENERALVISUAL) THE REMOTE APU CONTROL PANEL.

26-046-01 OPERATIONAL CHECK - OPERATIONALLY CHECK THE APUFIRE HANDLE LOCK OVERRIDE.

26-050-01 GENERAL VISUAL INSPECTION - INSPECT (GENERALVISUAL) THE APU FIRE EXTINGUISHER DISTRIBUTIONSYSTEM AND FIRE BOTTLE.

26-060-01 OPERATIONAL CHECK - OPERATIONALLY CHECK THECARGO FIRE EXTINGUISHING ARM SWITCHES TO VERIFYCIRCUITRY.

26-062-01 OPERATIONAL CHECK - OPERATIONALLY CHECK THECARGO FIRE EXTINGUISHING DISCHARGE SWITCH TOVERIFY CIRCUITRY.

27-182-01 LUBRICATE - LUBRICATE THE GROUND SPOILERINTERLOCK VALVE CABLE.

28-018-01 OPERATIONAL CHECK - OPERATIONALLY (BITE) CHECKTHE FUEL QUANTITY INDICATING SYSTEM.

29-036-01 OPERATIONAL CHECK - OPERATIONALLY CHECK THESTANDBY HYDRAULIC SYSTEM.

32-002-01 SERVICE - SERVICE THE MAIN LANDING GEAR SHOCKSTRUT.

32-003-01 FUNCTION CHECK - FUNCTIONALLY CHECK THE MLGTORSION LINK APEX JOINT FOR EXCESSIVE WEAR ANDGAP.

32-012-01 SERVICE - SERVICE THE NOSE LANDING GEAR SHOCKSTRUT.

32-028-01 DETAILED INSPECTION - INSPECT (DETAILED) THE FOREAND AFT BRAKE CONTROL LINKAGE.

32-030-01 DETAILED INSPECTION - INSPECT (DETAILED) THE BRAKEMETERING VALVE AND LINKAGE.

32-042-01 DETAILED INSPECTION - INSPECT (DETAILED) THEPARKING BRAKE MECHANICAL CONTROL PATH.

32-044-01 FUNCTION CHECK - FUNCTIONALLY CHECK THE BRAKEACCUMULATOR BLEED DOWN RATE.

32-053-01 DETAILED INSPECTION - INSPECT (DETAILED) THE NOSEWHEEL STEERING ACTUATOR AND ASSOCIATEDHARDWARE.

Task Relations


Model: BOEING 737-300/400/500


32-054-01 DETAILED INSPECTION - INSPECT (DETAILED) THE NOSEWHEEL STEERING MECHANICAL CONTROL PATH.

32-055-01 DETAILED INSPECTION - INSPECT (DETAILED) THE RUDDERPEDAL STEERING INTERCONNECT MECHANICAL CONTROLPATH.

33-006-01 FUNCTION CHECK - FUNCTIONALLY CHECK THESELF-ILLUMINATING EXIT SIGNS (DISCARD WHENILLUMINATION IS BELOW REQUIRED MINIMUM).

38-002-01 OPERATIONAL CHECK - OPERATIONALLY CHECK THEFORWARD POTABLE WATER DRAIN VALVE FOR EVIDENCEOF LEAKAGE.

53-854-01 ACCOMPLISH - INTERNAL - ZONAL (GV) FORWARD CARGOCOMPARTMENT (EZAP)

53-870-01 ACCOMPLISH - INTERNAL - ZONAL (GV) AFT CARGOCOMPARTMENT (EZAP)

57-320-01 DETAILED INSPECTION - INTERNAL-DETAILED INSPECTION:INSPECT THE MAIN AND AUXILIARY SLAT TRACKS.

54-304-01 DETAILED INSPECTION NO. 2 ENGINE -INTERNAL-DETAILED INSPECTION: INSPECT THE PYLONFIREWALL INCLUDING MID AND LOWER SPARS AND MIDSTRUT BULKHEAD, AND ENGINE SUPPORT STRUCTUREINCLUDING FORE AND AFT ENGINE MOUNTS, LINKS,ATTACH FITTINGS, THRUST LINKS, EVENER BAR, ANDVIBRATION ISOLATOR (WITH ENGINE REMOVED).

54-304-01 DETAILED INSPECTION NO. 1 ENGINE -INTERNAL-DETAILED INSPECTION: INSPECT THE PYLONFIREWALL INCLUDING MID AND LOWER SPARS AND MIDSTRUT BULKHEAD, AND ENGINE SUPPORT STRUCTUREINCLUDING FORE AND AFT ENGINE MOUNTS, LINKS,ATTACH FITTINGS, THRUST LINKS, EVENER BAR, ANDVIBRATION ISOLATOR (WITH ENGINE REMOVED).

54-306-01 DETAILED INSPECTION NO. 2 ENGINE -INTERNAL-DETAILED INSPECTION: INSPECT THE FORWARDENGINE MOUNT BULKHEAD AT NAC. STA. 196.

54-306-01 DETAILED INSPECTION NO. 1 ENGINE -INTERNAL-DETAILED INSPECTION: INSPECT THE FORWARDENGINE MOUNT BULKHEAD AT NAC. STA. 196.

54-308-01 SPECIAL DETAILED INSPECTION NO. 1 ENGINE -INTERNAL-SPECIAL DETAILED INSPECTION: INSPECT THEFORWARD AND AFT ENGINE MOUNT CONE BOLTS AND AFTENGINE MOUNT HANGER BEAM AND TANGENT LINKS INAREAS OF ATTACHMENTS (WITH ENGINE REMOVED).

Task Relations


Model: BOEING 737-300/400/500


54-308-01 SPECIAL DETAILED INSPECTION NO. 2 ENGINE -INTERNAL-SPECIAL DETAILED INSPECTION: INSPECT THEFORWARD AND AFT ENGINE MOUNT CONE BOLTS AND AFTENGINE MOUNT HANGER BEAM AND TANGENT LINKS INAREAS OF ATTACHMENTS (WITH ENGINE REMOVED).

54-310-01 DETAILED INSPECTION RIGHT - INTERNAL-DETAILEDINSPECTION: INSPECT THE UPPER SPAR CROWN CHORD;MID AND LOWER SPARS; BULKHEADS AT NAC. STA. 196,235, 254 AND 278; MID-SPAR FITTINGS AT WBL 183.4 AND198.6; AND LOWER SPAR (DIAGONAL BRACE) ATTACHFITTING AT NAC. STA. 278

54-310-01 DETAILED INSPECTION LEFT - INTERNAL-DETAILEDINSPECTION: INSPECT THE UPPER SPAR CROWN CHORD;MID AND LOWER SPARS; BULKHEADS AT NAC. STA. 196,235, 254 AND 278; MID-SPAR FITTINGS AT WBL 183.4 AND198.6; AND LOWER SPAR (DIAGONAL BRACE) ATTACHFITTING AT NAC. STA. 278

54-312-01 DETAILED INSPECTION NO. 2 ENGINE -INTERNAL-DETAILED INSPECTION: INSPECT THE PYLON AFTBULKHEAD AT NAC. STA. 278, DIAGONAL BRACE AND FUSEPINS, AND SIDE BRACE LINKS INCLUDING THE ATTACHFITTINGS TO WING AND PYLON (WITH FUSE PINSINSTALLED).

54-312-01 DETAILED INSPECTION NO. 1 ENGINE -INTERNAL-DETAILED INSPECTION: INSPECT THE PYLON AFTBULKHEAD AT NAC. STA. 278, DIAGONAL BRACE AND FUSEPINS, AND SIDE BRACE LINKS INCLUDING THE ATTACHFITTINGS TO WING AND PYLON (WITH FUSE PINSINSTALLED).

54-318-01 DETAILED INSPECTION NO. 1 ENGINE -INTERNAL-DETAILED INSPECTION: INSPECT THE PYLONSKIN NORMALLY COVERED BY THE THRUST REVERSERAND THRUST REVERSER/STRUT FAIRINGS.

54-318-01 DETAILED INSPECTION NO. 2 ENGINE -INTERNAL-DETAILED INSPECTION: INSPECT THE PYLONSKIN NORMALLY COVERED BY THE THRUST REVERSERAND THRUST REVERSER/STRUT FAIRINGS.

050033 3C CHECK PKG TO35-050-01 VISUALLY CHECK - VISUALLY CHECK THE PASSENGER,

LAVATORY AND ATTENDANT OXYGEN MASKS FORCLEANLINESS, CONDITION, AND SECURITY.

35-052-01 GENERAL VISUAL INSPECTION - INSPECT (GENERALVISUAL) THE PORTABLE OXYGEN CYLINDERS FORPRESENCE, CONDITION AND SECURITY.

Task Relations


Model: BOEING 737-300/400/500


38-008-01 FUNCTION CHECK - FUNCTIONALLY CHECK THE POTABLEWATER TANK PRESSURE RELIEF VALVE.

49-096-01 GENERAL VISUAL INSPECTION - INSPECT (GENERALVISUAL) THE APU FORE AND AFT MOUNTS.

49-110-01 DETAILED INSPECTION - INSPECT (DETAILED) THE APUFUEL CONTROL HIGH PRESSURE FILTER ELEMENT FOREVIDENCE OF FUEL PUMP DEGRADATION.

49-112-01 DETAILED INSPECTION - INSPECT (DETAILED) THE APUFUEL MANIFOLDS FOR CHAFING AND LEAKAGE.

52-038-01 OPERATIONAL CHECK - OPERATIONALLY CHECK THE OVERWING EMERGENCY EXIT HATCHES.

52-040-01 GENERAL VISUAL INSPECTION - INSPECT (GENERALVISUAL) THE EMERGENCY EXIT HATCH PRESSURE SEALFOR DEGRADATION.

52-044-01 OPERATIONAL CHECK - OPERATIONALLY CHECK THECARGO COMPARTMENT DOOR SNUBBER.

52-072-01 GENERAL VISUAL INSPECTION - INSPECT (GENERALVISUAL) THE FORWARD ACCESS DOOR PRESSURE SEALFOR DEGRADATION.

52-306-01 GENERAL VISUAL INSPECTION - INTERNAL-GENERALVISUAL INSPECTION: INSPECT THE FORWARD AND AFTCARGO DOOR INTERNAL STRUCTURE.

52-332-01 GENERAL VISUAL INSPECTION - INTERNAL-GENERALVISUAL INSPECTION: INSPECT THE FORWARD AIRSTAIRDOOR INTERNAL STRUCTURE AND LATCH BRACKETS (IFAIRSTAIR OR AIRSTAIR PROVISIONS INSTALLED).

52-338-01 GENERAL VISUAL INSPECTION - INTERNAL-GENERALVISUAL INSPECTION: INSPECT THEELECTRICAL/ELECTRONIC ACCESS DOOR INTERNALSTRUCTURE.

52-340-01 GENERAL VISUAL INSPECTION - INTERNAL-GENERALVISUAL INSPECTION: INSPECT THE FORWARD ACCESSDOOR INTERNAL STRUCTURE.

53-306-01 GENERAL VISUAL INSPECTION - INTERNAL-GENERALVISUAL INSPECTION: INSPECT THE AREAS UNDER GALLEYSAND LAVATORIES (IF INSTALLED).

53-310-01 GENERAL VISUAL INSPECTION - INTERNAL-GENERALVISUAL INSPECTION: INSPECT THE FUSELAGE LOWERLOBE FORWARD OF THE BILGE FROM BS 178 TO BS 380BELOW S-17, AND AREA ABOVE THE BILGE BS 380 TO BS540 FROM S-17 TO S-26 AND BS 727 TO BS 1016 FROM S-17TO S-25 INCLUDING SKIN PANELS, FRAMES,

Task Relations


Model: BOEING 737-300/400/500


53-314-01 GENERAL VISUAL INSPECTION - INTERNAL-GENERALVISUAL INSPECTION: INSPECT THE BILGE FROM BS 380 TOBS 540 BELOW S-26 AND BS 727 TO BS 1016 BELOW S-25INCLUDING SKIN PANELS, FRAMES, BULKHEADS,STRINGERS, SHEAR TIES, DOUBLERS, AND SKIN CUTOUTS.

53-316-01 GENERAL VISUAL INSPECTION - INTERNAL-GENERALVISUAL INSPECTION: INSPECT THE FUSELAGE WINGSTRUCTURE UNDER WING-TO-BODY FAIRINGS ANDAIR-CONDITIONING ACCESS DOORS INCLUDING SKINPANELS, SKIN SPLICES AND JOINTS, FRONT SPAR AT BS540 AND REAR SPAR AT BS 663.75 INCLUDING WING SPARTER

24-014-01 (001.1) FUNCTIONALLY CHECK NO.1 ENGINE GENERATORCONTROL UNIT (OFF-AIRCRAFT) PER MANUFACTURER'SCOMPONENT MAINTENANCE MANUAL


24-014-01 (003.1) FUNCTIONALLY CHECK APU GENERATOR CONTROL UNIT (OFF-AIRCRAFT) PER MANUFACTURER'S COMPONENTMAINTENANCE MANUAL

20-032-01 RESTORE (CLEAN) THE FORWARD AIRSTAIRCOMPARTMENT. (EZAP)

20-034-01 RESTORE (CLEAN) THE AREAS BEHIND THE FORWARDCARGO COMPARTMENT CEILING. (EZAP)

20-040-01 RESTORE (CLEAN) THE AREAS BEHIND THE AFT CARGOCOMPARTMENT CEILING. (EZAP)

20-044-01 RESTORE (CLEAN) THE AFT CARGO COMPARTMENTEQUIPMENT BAY. (EZAP)

20-046-01 INSPECT (DETAILED) THE GENERATOR POWER FEEDERSAND CONNECTED EWIS ONENGINE NO. 1. (EZAP)

20-048-01 INSPECT (DETAILED) THE GENERATOR POWER FEEDERSAND CONNECTED EWIS ONENGINE NO. 2. (EZAP)

20-054-01 INSPECT (DETAILED) THE CONTROL CABLES IN THEPRESSURIZED AREA OF THE FUSELAGE AND EMPENNAGE(NOT INCLUDING THE CABLES ABOVE THE WHEEL WELLAND CENTER WING SECTION).

20-060-01 INSPECT (DETAILED) THE LANDING GEAR MANUALEXTENSION CONTROL CABLES (NOTINCLUDING THE CABLES ABOVE THE WHEEL WELL ANDCENTER WING SECTION).

Task Relations


Model: BOEING 737-300/400/500


21-038-01 FUNCTION CHECK - FUNCTIONALLY CHECK THEELECTRICAL/ELECTRONIC EQUIPMENT COOLING SYSTEM.

24-010-02 OPERATIONAL CHECK - OPERATIONALLY CHECK THERIGHT ENGINE CSD GENERATOR DISCONNECT (WITHENGINE RUNNING).

24-022-01 OPERATIONAL CHECK - OPERATIONALLY CHECK THE LEFTENGINE VSCF GENERATOR DISCONNECT (WITH ENGINERUNNING).

24-024-01 FUNCTION CHECK - FUNCTIONALLY CHECK THE STANDBYPOWER SYSTEM.

25-028-01 GENERAL VISUAL INSPECTION - INSPECT (GENERALVISUAL) THE CARGO DOOR RESTRAINT SYSTEM FORCONDITION AND SECURITY.

27-022-01 FUNCTION CHECK - FUNCTIONALLY CHECK THE AILERONTAB FREEPLAY.

27-024-01 FUNCTION CHECK - FUNCTIONALLY CHECK THE AILERONSURFACE FREEPLAY.

27-054-01 FUNCTION CHECK - FUNCTIONALLY CHECK THE RUDDERSURFACE FREEPLAY.

27-056-01 DETAILED INSPECTION - INSPECT (DETAILED) THE RUDDERDUAL LOAD PATH FEEL AND CENTERING COMMAND ANDGROUND PATH COMPONENTS.

27-060-01 DETAILED INSPECTION - INSPECT (DETAILED) THE DUALLOAD PATH RUDDER PCU INPUT COMPONENTS (IFINSTALLED).

27-084-01 FUNCTION CHECK - FUNCTIONALLY CHECK OF THEELEVATOR TAB FREEPLAY.

27-086-01 FUNCTION CHECK - FUNCTIONALLY CHECK THE ELEVATORSURFACE FREEPLAY.

27-088-01 DETAILED INSPECTION - INSPECT (DETAILED) THE DUALLOAD PATH ELEVATOR PUSHROD (DOGBONE) AND ATTACHBOLTS.

27-090-01 DETAILED INSPECTION - INSPECT (DETAILED) THE DUALLOAD PATH FEEL AND CENTERING COMMAND ANDGROUND PATH COMPONENTS.

27-120-01 DETAILED INSPECTION - INSPECT (DETAILED) THE AFTFLAP DRIVE CABLE RUN.

27-122-01 FUNCTION CHECK - FUNCTIONALLY CHECK THE TRAILINGEDGE FLAP ALTERNATE DRIVE SYSTEM.

27-128-01 FUNCTION CHECK - FUNCTIONALLY CHECK THE TRAILINGEDGE FLAP LOAD RELIEF SYSTEM.

Task Relations


Model: BOEING 737-300/400/500


27-130-01 OPERATIONAL CHECK - OPERATIONALLY CHECK THETRAILING EDGE FLAP CONTROL CABLE TENSION SWITCH.

27-132-01 SERVICE - SERVICE THE TRAILING EDGE FLAPTRANSMISSIONS.

27-136-01 SERVICE - SERVICE THE ALTERNATE TRAILING EDGE FLAPDRIVE UNIT GEARBOX.

27-138-01 LUBRICATE - LUBRICATE THE TRAILING EDGE FLAP POWERUNIT GEARBOX.

27-144-01 LUBRICATE - LUBRICATE THE TRAILING EDGE FLAPLANDING GEAR BEAM ANGLE GEARBOX.

27-146-01 LUBRICATE - LUBRICATE THE TRAILING EDGE FLAP RIGHTANGLE GEARBOX.

27-168-01 FUNCTION CHECK - FUNCTIONALLY CHECK THE TORQUEOF THE SPOILER RATIO CHANGER NO-BACK ASSEMBLY.

28-012-01 FUNCTIONALLY CHECK - FUNCTIONALLY CHECK(RESISTANCE MEASUREMENT) FUEL PUMPS BONDRESISTANCE TO STRUCTURE. (SFAR 88)

28-016-01 FUNCTIONALLY CHECK - FUNCTIONALLY CHECK(RESISTANCE MEASUREMENT) THE APU DC FUEL PUMPMOTOR BONDING STRAP (IF INSTALLED). (SFAR 88)

29-004-01 DISCARD - DISCARD THE ELECTRIC MOTOR DRIVENHYDRAULIC PUMP PRESSURE FILTERS.

29-008-01 DISCARD - DISCARD THE ENGINE DRIVEN HYDRAULICPUMP PRESSURE FILTERS.

31-008-01 FUNCTION CHECK - FUNCTIONALLY CHECK THE LANDINGGEAR WARNING SYSTEM.

32-026-01 OPERATIONAL CHECK - OPERATIONALLY CHECK THELANDING GEAR TRANSFER VALVE.

35-042-01 VISUALLY CHECK - VISUALLY CHECK THE TEMPERATURESENSITIVE TAPE AND POSITION OF THE FIRING PINS ONEACH PASSENGER CABIN (INCLUDING LAVATORY ANDCABIN ATTENDANTS), CHEMICAL OXYGEN GENERATOR.

35-046-01 OPERATIONAL CHECK - OPERATIONALLY CHECK THEPASSENGER OXYGEN SYSTEM MANUAL DEPLOYMENTMODE.

35-048-01 FUNCTION CHECK - FUNCTIONALLY CHECK THEPASSENGER OXYGEN SYSTEM AUTOMATIC DEPLOYMENTMODE.

Task Relations


Model: BOEING 737-300/400/500


53-320-01 GENERAL VISUAL INSPECTION - INTERNAL-GENERALVISUAL INSPECTION: INSPECT INTERIOR OF SECTION 48FROM BS 1016 TO BS 1156 INCLUDING SKINS, FRAMES,DOUBLERS, SHEAR TIES; THE AFT FACE OF THE AFTPRESSURE BULKHEAD, STRINGERS, STRINGER SPLICEFITTINGS, VERTICAL STABILIZER-TO-BODY ATTACH

53-322-01 GENERAL VISUAL INSPECTION - INTERNAL-GENERALVISUAL INSPECTION: INSPECT INACCESSIBLE AREAS OFTHE APU INLET DUCT, FUSELAGE FRAMES, STRINGERSAND CHORDS BEHIND TORQUE BOX WEB FROM BS 1088 TOBS 1156.

53-332-01 DETAILED INSPECTION - INTERNAL-DETAILED INSPECTION:INSPECT THE FORWARD AND AFT CARGO DOOR CUTOUTS.

53-336-01 DETAILED INSPECTION - INTERNAL-DETAILED INSPECTION:INSPECT THE ENTRY AND GALLEY SERVICE DOORCUTOUTS AND SURROUND STRUCTURE INCLUDING DOORSTOP PAD FITTINGS, LATCHES, AND HINGES.

53-372-01 GENERAL VISUAL INSPECTION - INTERNAL-GENERALVISUAL INSPECTION: INSPECT THE UPPER AND LOWER SILLBEAMS OF CARGO DOOR OPENINGS.

53-374-01 GENERAL VISUAL INSPECTION - INTERNAL-GENERALVISUAL INSPECTION: INSPECT THE KEEL BEAM.

57-306-01 GENERAL VISUAL INSPECTION - EXTERNAL-GENERALVISUAL INSPECTION: INSPECT THE EXTERIOR WINGSURFACES FROM WING-TO-BODY FAIRINGS TO WING TIPINCLUDING UPPER AND LOWER IN-SPAR SKINS ANDFASTENERS, AND LEADING AND TRAILING EDGESTRUCTURE.

57-314-01 GENERAL VISUAL INSPECTION - INTERNAL-GENERALVISUAL INSPECTION: INSPECT THE WING LEADING EDGECAVITY INCLUDING FRONT SPAR CHORDS AND WEB,FLAPS, SLATS, SKINS, ENGINE PYLON ATTACHMENTS ANDSUPPORT FITTINGS AND SLAT SUPPORT RIBS.

57-336-01 GENERAL VISUAL INSPECTION - INTERNAL-GENERALVISUAL INSPECTION: INSPECT THE FLAP TRACKATTACHMENT TO FLAP TRANSMISSION.

57-804-01 ACCOMPLISH - INTERNAL - ZONAL (GV) LEFT WING TIP 57-832-01 ACCOMPLISH - INTERNAL - ZONAL (GV) WING TRAILING

EDGE, OUTBOARD FLAP AND SPOILERS - LEFT WING (EZAP)57-836-01 ACCOMPLISH - INTERNAL - ZONAL (GV) WING FIXED

TRAILING EDGE BETWEEN FLAPS - LEFT WING (EZAP)

Task Relations


Model: BOEING 737-300/400/500


57-842-01 ACCOMPLISH - INTERNAL - ZONAL (GV) WING TRAILINGEDGE, INBOARD FLAP AND SPOILERS - LEFT WING (FLAPSEXTENDED, SPOILERS RAISED) (EZAP)

57-848-01 ACCOMPLISH - INTERNAL - ZONAL (GV) RIGHT WING TIP 57-876-01 ACCOMPLISH - INTERNAL - ZONAL (GV) WING TRAILING

EDGE, OUTBOARD FLAP AND SPOILERS - RIGHT WING(EZAP)

57-880-01 ACCOMPLISH - INTERNAL - ZONAL (GV) WING FIXEDTRAILING EDGE BETWEEN FLAPS - RIGHT WING (EZAP)

57-886-01 ACCOMPLISH - INTERNAL - ZONAL (GV) WING TRAILINGEDGE, INBOARD FLAP AND SPOILERS - RIGHT WING (FLAPSEXTENDED, SPOILERS RAISED) (EZAP)

70-822-01 ACCOMPLISH - EXTERNAL - ZONAL (GV) LEFT HAND FANCOWL - ENGINE NO. 1 (INNER AND OUTER EXTERIORSURFACE)

70-824-01 ACCOMPLISH - EXTERNAL - ZONAL (GV) RIGHT HAND FANCOWL - ENGINE NO. 1 (INNER AND OUTER EXTERIORSURFACE)

70-834-01 ACCOMPLISH - EXTERNAL - ZONAL (GV) LEFT HAND FANCOWL - ENGINE NO. 2 (INNER AND OUTER EXTERIORSURFACE)

70-836-01 ACCOMPLISH - EXTERNAL - ZONAL (GV) RIGHT HAND FANCOWL - ENGINE NO. 2 (INNER AND OUTER EXTERIORSURFACE)

73-008-01 FUNCTION CHECK - FUNCTIONALLY CHECK THE LEFTENGINE FUEL FILTER DIFFERENTIAL PRESSURE SWITCHWARNING SYSTEM.

73-008-02 FUNCTION CHECK - FUNCTIONALLY CHECK THE RIGHTENGINE FUEL FILTER DIFFERENTIAL PRESSURE SWITCHWARNING SYSTEM.

76-004-01 DETAILED INSPECTION - INSPECT (DETAILED) THE LEFTENGINE CONTROL CABLES (NON-EXPOSED) IN THE WINGFORWARD OF THE FRONT SPAR.

76-004-02 DETAILED INSPECTION - INSPECT (DETAILED) THE RIGHTENGINE CONTROL CABLES (NON-EXPOSED) IN THE WINGFORWARD OF THE FRONT SPAR.

79-022-01 FUNCTION CHECK - FUNCTIONALLY CHECK THE MAIN LEFTENGINE OIL FILTER BYPASS PRESSURE DIFFERENTIALSWITCH.

79-022-02 FUNCTION CHECK - FUNCTIONALLY CHECK THE MAINRIGHT ENGINE OIL FILTER BYPASS PRESSUREDIFFERENTIAL SWITCH.

Task Relations


Model: BOEING 737-300/400/500


57-310-01 INTERNAL GENERAL VISUAL INSPECTION INSPECT THEWING TRAILING EDGE CAVITY INCLUDING ALL FIXEDTRAILING EDGESTRUCTURE, REAR SPAR, MAIN LANDING GEAR SUPPORTSTRUCTURE, SKINS, RIBS, AILERONS, SPOILERS, FLAPS,INTERIORSTRUCTURE OF THE MID FLAP, FLAP TRACK CARRIAGESAND CARRIAGE SPINDLES AND FLAP TRACK CARRIAGERETAINER BOLTS ANDTHRUST BEARING RETENTION BOLTS.

28-012-02 FUNCTIONALLY CHECK - FUNCTIONALLY CHECK(RESISTANCE MEASUREMENT) FUEL PUMPS BONDRESISTANCE TO STRUCTURE. (SFAR 88)

21-005-01 DISCARD APU BLEED AIR DUCT FLEXIBLE PRESSURE SEAL 20-035-01 INSPECT (DETAILED) AC GENERATOR POWER FEEDERS

AND CONNECTED EWIS BEHIND THE CEILING PANELS INFORWARD CARGO COMPARTMENT. (EZAP)

20-066-01 INSPECT (GENERAL VISUAL) THE EXPOSED EWIS ABOVETHE APU UPPER SHROUD. (EZAP)

20-076-01 INSPECT (GENERAL VISUAL) THE NO. 1 ENGINE POWERFEEDERS AND CONNECTED EWIS IN THE STRUT TORQUEBOX. (EZAP)

20-078-01 INSPECT (GENERAL VISUAL) THE NO. 2 ENGINE POWERFEEDERS AND CONNECTED EWIS IN THE STRUT TORQUEBOX. (EZAP)

ICA-25-053-06 RESTORE THE SLIDING CARPET SYSTEM. DO THENECESSARY WORK TO RETURN THE ITEM TO A SPECIFICSTANDARD. MAY INCLUDE CLEANING, REPAIR, COMPLETEOVERHAUL OR REPLACEMENT OF PARTS

050034 4C CHECK PKG TO27-062-01 OPERATIONAL CHECK - OPERATIONALLY CHECK THE

RUDDER POWER CONTROL UNIT FORCE FIGHT MONITOR. 20-018-01 INSPECT (DETAILED) THE POWER FEEDERS AND

CONNECTED EWIS IN THE AFT MAIN CABIN CEILING. (EZAP) 29-040-01 DISCARD - DISCARD THE STANDBY HYDRAULIC SYSTEM

CASE DRAIN FILTER. 29-046-01 DISCARD - DISCARD THE HYDRAULIC POWER TRANSFER

UNIT PRESSURE FILTER. 52-302-01 DETAILED INSPECTION - INTERNAL-DETAILED INSPECTION:

INSPECT THE FORWARD AND AFT CARGO DOOR STOP PINFITTINGS.

Task Relations


Model: BOEING 737-300/400/500


52-312-01 GENERAL VISUAL INSPECTION - INTERNAL-GENERALVISUAL INSPECTION: INSPECT ENTRY AND GALLEYSERVICE DOOR INTERNAL STRUCTURE.

52-324-01 GENERAL VISUAL INSPECTION - INTERNAL-GENERALVISUAL INSPECTION: INSPECT THE OVER WING ESCAPEHATCH INTERNAL STRUCTURE.

52-822-01 ACCOMPLISH - INTERNAL - ZONAL (GV) EMERGENCY EXITHATCH

52-830-01 ACCOMPLISH - INTERNAL - ZONAL (GV) EMERGENCY EXITHATCH

53-302-01 GENERAL VISUAL INSPECTION - INTERNAL-GENERALVISUAL INSPECTION: INSPECT THE FLIGHT CREWCOMPARTMENT FROM BS 178 TO BS 270 INCLUDING SKINS,FRAMES, STRINGERS, DOUBLERS, SHEAR TIES, WINDOWCUTOUTS, AFT FACE OF THE FORWARD PRESSUREBULKHEAD, AND FLOOR.

53-304-01 GENERAL VISUAL INSPECTION - INTERNAL-GENERALVISUAL INSPECTION: INSPECT THE INTERIOR OF FUSELAGEUPPER LOBE FROM BS 270 TO BS 1016 ABOVE S-17INCLUDING SKIN PANELS, FRAMES, STRINGERS,DOUBLERS, SHEAR TIES, WINDOW CUT-OUTS, ANDFORWARD FACE OF THE AFT PRESSURE BULKHEAD ANDPRESSURE

53-340-01 GENERAL VISUAL INSPECTION - EXTERNAL-GENERALVISUAL INSPECTION: INSPECT THE OVERWING ESCAPEHATCH CUTOUTS AND DOOR STOP PAD FITTINGS.

53-346-01 GENERAL VISUAL INSPECTION - INTERNAL-GENERALVISUAL INSPECTION: INSPECT THE WING-TO-BODY DRAGANGLES.

53-350-01 GENERAL VISUAL INSPECTION - INTERNAL-GENERALVISUAL INSPECTION: INSPECT STRINGER 18A WEB, CHORD,AND LINKS.

53-804-01 ACCOMPLISH - INTERNAL - ZONAL (GV) FLIGHT CONTROLCABIN (WITH ACCESS PROVIDED) (EZAP)

53-814-01 ACCOMPLISH - INTERNAL - ZONAL (GV) FORWARD HALF OFCABIN - AFT OF CONTROL CABIN TO BS 627.5 INCLUDING:AREA ABOVE CENTER SECTION WING BOX (EZAP)

53-820-01 ACCOMPLISH - INTERNAL - ZONAL (GV) AFT HALF OF CABIN- BS 627.5 TO AFT BULKHEAD INCLUDING: AREA ABOVECENTER SECTION WING BOX AND PRESSURE DECK ABOVEMAIN LANDING GEAR WHEEL WELL (EZAP)

53-878-01 ACCOMPLISH - INTERNAL - ZONAL (GV) FORWARDWING-TO-BODY FAIRING - LEFT (EZAP)

Task Relations


Model: BOEING 737-300/400/500


53-880-01 ACCOMPLISH - INTERNAL - ZONAL (GV) FORWARDWING-TO-BODY FAIRING - RIGHT (EZAP)

53-882-01 ACCOMPLISH - INTERNAL - ZONAL (GV) AFT WING-TO-BODYFAIRING - LEFT (EZAP)

20-012-01 RESTORE (CLEAN) THE LOWER AREAS BEHIND THEFORWARD PASSENGER CABIN SIDEWALLS. (EZAP)

20-016-01 RESTORE (CLEAN) THE LOWER AREAS BEHIND THE AFTPASSENGER CABIN SIDEWALLS. (EZAP)

20-028-01 RESTORE (CLEAN) THE ELECTRONIC COMPARTMENT.(EZAP)

20-030-01 INSPECT (DETAILED) THE EWIS BEHIND THE ELECTRONICEQUIPMENT RACKS. (EZAP)

21-012-01 GENERAL VISUAL INSPECTION - FUNCTIONALLY CHECKTHE CABIN POSITIVE PRESSURE RELIEF VALVES

23-002-01 OPERATIONAL CHECK - OPERATIONALLY CHECK THEPASSENGER ADDRESS SPEAKERS.

26-006-01 OPERATIONAL CHECK - OPERATIONALLY CHECK THE APUREMOTE FIRE DETECTION SYSTEM (FIRE DETECTIONMODULE).

26-008-01 OPERATIONAL CHECK - OPERATIONALLY CHECK THE APUREMOTE FIRE DETECTION SYSTEM (APU REMOTE FIRECONTROL PANEL).

27-036-01 FUNCTION CHECK - FUNCTIONALLY CHECK THE RUDDERPOWER CONTROL UNIT INTERNAL LEAKAGE TO INCLUDETHE POWER CONTROL UNIT IN A LOADED CONDITION.

53-884-01 ACCOMPLISH - INTERNAL - ZONAL (GV) AFT WING-TO-BODYFAIRING - RIGHT (EZAP)

55-300-01 DETAILED INSPECTION - INTERNAL-DETAILED INSPECTION:INSPECT THE FUSELAGE TO VERTICAL STABILIZER FRONTAND REAR SPAR ATTACHMENT FITTINGS

55-304-01 GENERAL VISUAL INSPECTION - INTERNAL-GENERALVISUAL INSPECTION: INSPECT THE HORIZONTALSTABILIZER MAIN BOX, INCLUDING SKINS, RIBS ANDSTIFFENERS, FRONT SPAR CHORDS AND WEB, AND REARSPAR CHORDS AND WEB.

55-310-01 GENERAL VISUAL INSPECTION - INTERNAL-GENERALVISUAL INSPECTION: INSPECT THE STABILIZER TRAILINGEDGE CAVITY, INCLUDING BALANCE PANELS AND WEIGHTS,RIBS, ELEVATOR ATTACH POINTS, ELEVATOR REAR SPARAT TRIM TAB BAY, REAR SPAR CHORDS AND WEB ANDTRAILING EDGE BEAMS.

Task Relations


Model: BOEING 737-300/400/500


55-316-01 GENERAL VISUAL INSPECTION - INTERNAL-GENERALVISUAL INSPECTION: INSPECT THE HORIZONTALSTABILIZER LEADING EDGE INCLUDING RIBS, LEADINGEDGE SKINS, AND FRONT SPAR CHORDS AND WEB.

55-318-01 GENERAL VISUAL INSPECTION - INTERNAL- GENERALVISUAL INSPECTION: INSPECT THE VERTICAL STABILIZERMAIN BOX INCLUDING FRONT SPAR CHORDS AND WEB,SKINS, STRINGERS, RIBS AND STIFFENERS, REAR SPARCHORDS AND WEB.

55-322-01 GENERAL VISUAL INSPECTION - INTERNAL -GENERALVISUAL INSPECTION: INSPECT THE VERTICAL STABILIZERTRAILING EDGE CAVITY INCLUDING TRAILING EDGEPANELS, RIBS, RUDDER ATTACH POINTS, AND VERTICALSTABILIZER REAR SPAR CHORDS AND WEB.

55-324-01 GENERAL VISUAL INSPECTION - INTERNAL-GENERALVISUAL INSPECTION: INSPECT THE VERTICAL STABILIZERLEADING EDGE INCLUDING FRONT SPAR CHORDS ANDWEB, RIBS AND LEADING EDGE SKINS.

57-300-01 GENERAL VISUAL INSPECTION - INTERNAL-GENERALVISUAL INSPECTION: INSPECT THE INTERIOR OF WINGCENTER SECTION INCLUDING SKINS, STRINGERS, SPANWISE BEAMS, FRONT AND REAR SPAR CHORDS AND WEBS.

D6-38669-02 ACCOMPLISH THE FOLLOWING: BEGIN THE COMPLETEREPAIR EXAMINATION AND THE REPAIR ASSESMENTPROCESS AS PER BOEING REPAIR ASSESMENTGUIDELINES (D6-38669)

55-302-01 INTERNAL DETAILED INSPECTION ; INSPECT THEHORIZONTAL STABILIZER CENTERSECTION-TO-HORIZONTAL STABILIZER FRONT AND REARSPAR ATTACHMENT FITTINGS.

20-014-01 INSPECT (DETAILED) THE POWER FEEDERS ANDCONNECTED EWIS IN THE FORWARD MAIN CABIN CEILING.(EZAP)

29-038-01 DISCARD - DISCARD THE STANDBY HYDRAULIC SYSTEMPRESSURE FILTER.

050035 5C CHECK PKG TO21-016-01 FUNCTION CHECK - FUNCTIONALLY CHECK THE CABIN

NEGATIVE PRESSURE RELIEF VENT DOOR 57-302-01 INTERNAL GENERAL VISUAL INSPECTION : INSPECT THE

INTERIOR OF OUTBOARD MAIN WING BOX INCLUDINGSKINS, STRINGERS,RIBS, FRONT AND REAR SPAR CHORDS AND WEBS, LOWERSKIN AT FUEL TANK AND BOOST PUMP ACCESS DOORS.

Task Relations


Model: BOEING 737-300/400/500


25-032-01 DETAILED INSPECTION - INSPECT (DETAILED) THEEMERGENCY EXIT HATCH ESCAPE STRAPS FOR CONDITIONAND SECURITY.

25-034-01 DETAILED INSPECTION - INSPECT (DETAILED) THE FLIGHTCOMPARTMENT EMERGENCY ESCAPE LANYARDS FORCONDITION AND SECURITY.

26-054-01 FUNCTION CHECK - FUNCTIONALLY CHECK THE CARGOFIRE EXTINGUISHING SYSTEM TUBING FOR EVIDENCE OFLEAKAGE OR BLOCKAGE.

27-010-01 FUNCTIONALLY CHECK - THE AILERON PCU INTERNALHYDRAULIC LEAKAGE IN A LOADED CONDITION.

27-042-01 FUNCTION CHECK - FUNCTIONALLY CHECK THE STANDBYPOWER CONTROL UNIT INTERNAL LEAKAGE TO INCLUDERUDDER IN A LOADED CONDITION.

27-064-01 OPERATIONAL CHECK - OPERATIONALLY CHECK THERUDDER POWER CONTROL UNIT OVERRIDES.

27-076-01 FUNCTIONALLY CHECK - THE INTERNAL LEAKAGE OF THEELEVATOR POWER CONTROL UNITS IN A LOADEDCONDITION.

27-186-01 FUNCTIONALLY CHECK - FOR INTERNAL LEAKAGE OF THELEADING EDGE FLAP AND SLAT ACTUATORS.

28-014-01 FUNCTION CHECK - FUNCTIONALLY (PRESSURE DECAY)CHECK THE APU FUEL LINE SHROUD.

29-002-01 FUNCTION CHECK - FUNCTIONALLY CHECK THE "A" AND "B"HYDRAULIC SYSTEMS INTERNAL LEAKAGE RATE.

29-034-01 FUNCTION CHECK - FUNCTIONALLY CHECK THE STANDBYHYDRAULIC SYSTEM INTERNAL LEAKAGE RATE.

57-304-01 DETAILED INSPECTION - INTERNAL-DETAILED INSPECTION:INSPECT THE INTERIOR OF INBOARD MAIN WING BOXSTRINGER END FITTINGS AND FUEL TANK DRAIN TUBES ATWBL 70.5.

57-826-01 ACCOMPLISH - INTERNAL - ZONAL (GV) WING TRAILINGEDGE, AILERON AND CONTROL TAB - LEFT WING

57-870-01 ACCOMPLISH - INTERNAL - ZONAL (GV) WING TRAILINGEDGE, AILERON AND CONTROL TAB - RIGHT WING

22-002-01 DETAILED INSPECTION - INSPECT (DETAILED) THE AILERONAND ELEVATOR AUTOPILOT SERVO ACTUATOR INPUTLEVER SHEAR RIVETS FOR WEAR.

050036 6C CHECK PKG TO

Task Relations


Model: BOEING 737-300/400/500


20-062-01 INSPECT (DETAILED) THE LANDING GEAR MANUALEXTENSION CONTROL CABLES ABOVE THE WHEEL WELLAND CENTER WING SECTION.

20-056-01 INSPECT (DETAILED) THE CONTROL CABLES ABOVE THEWHEEL WELL AND CENTER WING SECTION.

27-126-01 FUNCTION CHECK - FUNCTIONALLY CHECK THE TRAILINGEDGE FLAP BALLSCREW ACTUATOR BACKLASH.

27-162-01 GENERAL VISUAL INSPECTION - INSPECT (GENERALVISUAL) THE TRAILING EDGE FLAP CONTROL VALVETOWER SHAFT.

28-008-01 DETAILED INSPECTION - INSPECT (DETAILED) IN TANKTUBING AND EQUIPMENT STATIC BONDING STRAPS ANDCLAMPS FOR CONDITION, SECURITY AND OTHERDEGRADATION. (SFAR 88)



28-020-01 DETAILED INSPECTION - INSPECT (DETAILED) THE IN-TANKFQIS EXPOSED ELECTRICAL WIRING INTERCONNECTIONSYSTEM (EWIS) AND EWIS SUPPORT FOR DAMAGE,ADEQUATE SEPARATION FROM STRUCTURE AND PROPERSECURITY. (SFAR 88) (EZAP)

28-020-02 DETAILED INSPECTION - INSPECT (DETAILED) THE IN-TANKFQIS EXPOSED ELECTRICAL WIRING INTERCONNECTIONSYSTEM (EWIS) AND EWIS SUPPORT FOR DAMAGE,ADEQUATE SEPARATION FROM STRUCTURE AND PROPERSECURITY. (SFAR 88) (EZAP)

28-020-03 DETAILED INSPECTION -INSPECT (DETAILED) THE IN-TANKFQIS EXPOSED ELECTRICAL WIRING INTERCONNECTIONSYSTEM (EWIS) AND EWIS SUPPORT FOR DAMAGE,ADEQUATE SEPARATION FROM STRUCTURE AND PROPERSECURITY. (SFAR 88) (EZAP)

29-032-01 DISCARD - DISCARD THE HYDRAULIC RESERVOIR FILLFILTER.

32-060-01 RESTORE - RESTORE THE LANDING GEAR CONTROLLEVER POSITION SWITCH BY CLEANING.

Task Relations


Model: BOEING 737-300/400/500


36-002-01 FUNCTION CHECK - FUNCTIONALLY CHECK(OFF-AIRPLANE) THE PRE-COOLER CONTROL VALVE ANDWING TAI SOLENOID.

36-004-01 FUNCTION CHECK - FUNCTIONALLY CHECK(OFF-AIRPLANE) THE PRE-COOLER CONTROL VALVESENSOR.

38-004-01 DISCARD - DISCARD THE POTABLE WATER BLEED AIRIN-LINE FILTER.

38-006-01 DISCARD - DISCARD THE POTABLE WATER AIRCOMPRESSOR INLET FILTER.

49-102-01 LUBRICATE - LUBRICATE THE APU INLET DOOR VORTEXGENERATOR HINGE PIN.

53-856-01 ACCOMPLISH - INTERNAL - ZONAL (GV) FORWARD CARGOCOMPARTMENT (EZAP)

53-872-01 ACCOMPLISH - INTERNAL - ZONAL (GV) AFT CARGOCOMPARTMENT (EZAP)

53-876-01 ACCOMPLISH - INTERNAL - ZONAL (GV) CENTER SECTIONFUEL TANK (EZAP)

54-322-01 DETAILED INSPECTION - INTERNAL -DETAILED INSPECTION:INSPECT THE STRUT-TO-WING ATTACH FITTINGSINCLUDING WING FITTINGS AND EXPOSED SKIN WITH THEPYLONS REMOVED.

55-806-01 ACCOMPLISH - INTERNAL - ZONAL (GV) VERTICALSTABILIZER LEADING EDGE

57-816-01 ACCOMPLISH - INTERNAL - ZONAL (GV) FUEL VENT SURGETANK - LEFT WING

57-820-01 ACCOMPLISH - INTERNAL - ZONAL (GV) MAIN FUEL TANK -LEFT WING (EZAP)

57-860-01 ACCOMPLISH - INTERNAL - ZONAL (GV) FUEL VENT SURGETANK - RIGHT WING

57-864-01 ACCOMPLISH - INTERNAL - ZONAL (GV) MAIN FUEL TANK -RIGHT WING (EZAP)

28-003-01 FUNCTIONALLY CHECK - FUNCTIONALLY CHECK(RESISTANCE MEASUREMENT) THE BONDING RESISTANCEBETWEEN THE PRESSURE RELIEF VALVE AND THESTRUCTURE. (SFAR 88)

28-005-01 FUNCTIONALLY CHECK - FUNCTIONALLY CHECK(RESISTANCE MEASUREMENT) THE BONDING BETWEENTHE LOWER AIR VENT STACK AND THE DOOR STRUCTURE.(SFAR 88)

Task Relations


Model: BOEING 737-300/400/500


28-025-01 DETAILED INSPECTION - INSPECT (DETAILED) IN-TANK FQISCOMPONENTS FOR CHAFING, RUBBING, ADEQUATESEPARATION FROM THE STRUCTURE AND CONDITION /SECURITY. (SFAR 88)

28-025-02 DETAILED INSPECTION - INSPECT (DETAILED) IN-TANK FQISCOMPONENTS FOR CHAFING, RUBBING, ADEQUATESEPARATION FROM THE STRUCTURE AND CONDITION /SECURITY (SFAR 88).

28-025-03 DETAILED INSPECTION - INSPECT (DETAILED) IN-TANK FQISCOMPONENTS FOR CHAFING, RUBBING, ADEQUATESEPARATION FROM THE STRUCTURE AND CONDITION /SECURITY. (SFAR 88)

28-030-01 FUNCTIONALLY CHECK - FUNCTIONALLY CHECK(RESISTANCE MEASUREMENT) THE BONDING BETWEENTHEOVERWING FILLER AND THE STRUCTURE. (SFAR 88)

28-035-01 FUNCTIONALLY CHECK - FUNCTIONALLY CHECK(RESISTANCE MEASUREMENT) THE BONDING RESISTANCEBETWEEN THE HYDRAULIC LINE FITTING AT THE FUEL TANKWALL PENETRATIONS AND THE ADJOINING STRUCTURE.(SFAR 88)

28-045-01 FUNCTIONALLY CHECK - FUNCTIONALLY CHECK(RESISTANCE MEASUREMENT) THE BONDING OF FUELINGSHUTOFF SOLENOID VALVES TO ADJOINING STRUCTURE.(SFAR 88)

28-050-01 FUNCTIONALLY CHECK - FUNCTIONALLY CHECK(RESISTANCE MEASUREMENT) THE BONDING RESISTANCEBETWEEN THE FUELING RECEPTACLE (MANIFOLD) AND THESTRUCTURE. (SFAR 88)

28-055-01 FUNCTIONALLY CHECK - FUNCTIONALLY CHECK(RESISTANCE MEASUREMENT) THE BONDING RESISTANCEBETWEEN THE APU SHUTOFF VALVE ACTUATOR AND THEADJOINING STRUCTURE (IFINSTALLED). (SFAR 88)

28-060-01 FUNCTIONALLY CHECK - FUNCTIONALLY CHECK(RESISTANCE MEASUREMENT) MOTOR OPERATED VALVEBOND RESISTANCE TO STRUCTURE. (SFAR 88)

20-037-01 INSPECT (DETAILED) AC GENERATOR POWER FEEDERSAND CONNECTED EWIS BEHIND THE SIDEWALL PANELS INFORWARD CARGO COMPARTMENT. (EZAP)

20-068-01 INSPECT (GENERAL VISUAL) EWIS LOCATED IN THEDENSER AREAS OF THE LEFT WING LEADING EDGE FROMWSTA 253 TO WSTA 500. (EZAP)

Task Relations


Model: BOEING 737-300/400/500


20-070-01 INSPECT (GENERAL VISUAL) EWIS LOCATED IN THEDENSER AREAS OF THE RIGHT WING LEADING EDGE FROMWSTA 253 TO WSTA 500. (EZAP)

35-014-01 (001.1) FUNCTIONAL CHECK CAPT OXYGEN REGULATOR/MASKPER MANUFACTURER'S MANUAL (OFF AIRPLANE)

35-014-01 (002.1) FUNCTIONAL CHECK F/O OXYGEN REGULATOR/MASK PERMANUFACTURER'S MANUAL (OFF AIRPLANE)

35-014-01 (003.1) FUNCTIONAL CHECK 1ST OBS OXYGEN REGULATOR/MASKPER MANUFACTURER'S MANUAL (OFF AIRPLANE)

35-014-01 (004.1) FUNCTIONAL CHECK 2ND OBS OXYGEN REGULATOR/MASKPER MANUFACTURER'S MANUAL (OFF AIRPLANE)

20-002-01 RESTORE (CLEAN) THE AREAS BEHIND THE RUDDERPEDALS AND CENTER CONSOLE. (EZAP)

20-004-01 RESTORE (CLEAN) THE AREAS UNDER THE RACEWAYCOVER PLATES ON BOTH SIDES OF THE FLIGHTCOMPARTMENT. (EZAP)

20-006-01 RESTORE (CLEAN) THE AREAS IN THE P6 AND P18 PANELS.(EZAP)

20-008-01 INSPECT (DETAILED) THE WIRE BUNDLES ANDCONNECTED EWIS IN THE P6 AND P18 PANELS. (EZAP)

20-024-01 RESTORE (CLEAN) THE AREA OF THE LOWER NOSECOMPARTMENT. (EZAP)

20-026-01 INSPECT (DETAILED) THE POWER FEEDERS ANDCONNECTED EWIS IN THE LOWER NOSE COMPARTMENT.(EZAP)

20-036-01 RESTORE (CLEAN) THE AREAS BEHIND THE FORWARDCARGO COMPARTMENT SIDEWALL PANELS. (EZAP)

20-038-01 RESTORE (CLEAN) THE AREAS BEHIND THE FORWARDCARGO COMPARTMENT AFT BULKHEAD ACCESS PANELS.(EZAP)

20-042-01 RESTORE (CLEAN) THE AREAS BEHIND THE AFT CARGOCOMPARTMENT SIDEWALL PANELS. (EZAP)

21-014-01 DISCARD - DISCARD THE CABIN POSITIVE PRESSURERELIEF VALVE FILTER.

050130 10C CHECK PKG TO27-094-01 (001.1) RESTORE STABILIZER TRIM ACTUATOR PER THE

MANUFACTURER'S COMPONENT MAINTENANCE MANUAL(DISCONNECT CLUTCH)

27-116-01 (001.1) RESTORE STABILIZER TRIM ACTUATOR PER THECOMPONENT MAINTENANCE MANUAL (PRIMARY BRAKEAND JACKSCREW INNER LOAD PATH)

Task Relations


Model: BOEING 737-300/400/500


29-020-01 FUNCTION CHECK - FUNCTIONALLY CHECK(OFF-AIRCRAFT) THE NOSE LANDING GEAR "A" HYDRAULICSYSTEM UP LINE FUSE.

27-002-01 FUNCTION CHECK - FUNCTIONALLY CHECK(OFF-AIRCRAFT) OF THE LEADING EDGE FLAPS AND SLATS"B" SYSTEM HYDRAULIC SYSTEM FUSES.

32-040-01 OPERATIONAL CHECK - OPERATIONALLY CHECK THEBRAKE ACCUMULATOR ISOLATION VALVE.

29-056-01 FUNCTION CHECK - FUNCTIONALLY CHECK "A & B"HYDRAULIC SYSTEM CASE DRAIN WARNING SWITCHES.

27-008-01 FUNCTION CHECK - FUNCTIONALLY CHECK THE AILERONTRANSFER MECHANISM.

27-016-01 FUNCTION CHECK - FUNCTIONALLY CHECK THE AILERONSYSTEM CONTROL WHEEL FORCES.

27-110-01 LUBRICATE - LUBRICATE THE FORWARD STABILIZER TRIMMECHANISM DRIVE TRAIN.

27-140-01 LUBRICATE - LUBRICATE THE TRAILING EDGE FLAPPOSITION TRANSMITTER GEARBOX.

27-164-01 OPERATIONAL CHECK - OPERATIONALLY CHECK THETRAILING EDGE FLAP TRANSMISSION NO-BACK BRAKES.

27-166-01 FUNCTION CHECK - FUNCTIONALLY CHECK OF THETRAILING EDGE FLAP ASYMMETRY SHUTOFF SYSTEM

29-022-01 FUNCTION CHECK - FUNCTIONALLY CHECK(OFF-AIRCRAFT) THE THRUST REVERSER "A" HYDRAULICSYSTEM FUSES.

29-024-01 FUNCTION CHECK - FUNCTIONALLY CHECK(OFF-AIRCRAFT) THE LEADING EDGE "B" HYDRAULICSYSTEM FUSES.

29-026-01 FUNCTION CHECK - FUNCTIONALLY CHECK(OFF-AIRCRAFT) THE BRAKE "A" HYDRAULIC SYSTEMFUSES.

29-028-01 FUNCTION CHECK - FUNCTIONALLY CHECK(OFF-AIRCRAFT) THE BRAKE "B" HYDRAULIC SYSTEMFUSES.

29-030-01 FUNCTION CHECK - FUNCTIONALLY CHECK(OFF-AIRCRAFT) THE RUDDER "B" HYDRAULIC SYSTEMFUSE.

29-044-01 FUNCTION CHECK - FUNCTIONALLY CHECK THEHYDRAULIC POWER TRANSFER UNIT.

Task Relations


Model: BOEING 737-300/400/500


29-048-01 OPERATIONAL CHECK - OPERATIONALLY CHECK THEHYDRAULIC POWER TRANSFER UNIT ISOLATION CHECKVALVE.

29-050-01 FUNCTION CHECK - FUNCTIONALLY CHECK(OFF-AIRCRAFT) THE LEADING EDGE STANDBY HYDRAULICSYSTEM FUSE.

29-052-01 FUNCTION CHECK - FUNCTIONALLY CHECK(OFF-AIRCRAFT) THE THRUST REVERSER STANDBYHYDRAULIC SYSTEM FUSES.

050132 12C CHECK PKG TO27-148-01 LUBRICATE - LUBRICATE THE TRAILING EDGE FLAP DRIVE

TORQUE TUBE COUPLINGS. 32-034-01 OPERATIONAL CHECK - OPERATIONALLY CHECK THE

ALTERNATE BRAKE CONTROL SYSTEM. 28-010-02 DETAILED INSPECTION - INSPECT (DETAILED) THE FUEL

BOOST PUMP WIRES. NO. 2 TANK. (SFAR 88) 28-010-01 DETAILED INSPECTION - INSPECT (DETAILED) THE FUEL

BOOST PUMP WIRES. NO. 1 TANK. (SFAR 88) 28-010-03 DETAILED INSPECTION - INSPECT (DETAILED) THE FUEL

BOOST PUMP WIRES. CENTER TANK.(SFAR 88) 050POS POST FLIGHT CHECK PKG TO

05-POS-01 ACCOMPLISH POST FLIGHT CHECK 050PRE PREFLIGHT CHECK PKG TO

24-030-01 OPERATIONAL CHECK - OPERATIONALLY CHECK STANDBYPOWER SYSTEM. ONE MECHANIC CHECK IS EQUIVALENTTO THE TWO MECHANIC CHECK.

32-048-01 VISUALLY CHECK - VISUALLY CHECK NOSE AND MAINLANDING GEAR TIRES FOR CONDITION, WEAR, CUTS, ANDTREAD DEPTH.

05-PRE-01 ACCOMPLISH PREFLIGHT CHECK 32-050-01 GENERAL VISUAL INSPECTION - INSPECT (GENERAL

VISUAL) THE NOSE AND MAIN LANDING GEAR WHEELASSEMBLIES.

32-046-01 SERVICE - CHECK NOSE AND MAIN LANDING GEAR TIRESFOR PROPER INFLATION AND SERVICE AS REQUIRED.

050SVC SERVICE CHECK PKG TO24-002-02 SERVICE - SERVICE THE RIGHT ENGINE CSD CASE OIL BY

CHECKING FOR CORRECT LEVEL AND REPLENISHING ASREQUIRED.

Task Relations


Model: BOEING 737-300/400/500


79-012-02 GENERAL VISUAL INSPECTION - INSPECT (GENERALVISUAL) THE RIGHT ENGINE COWLING FOR EVIDENCE OFOIL SEAL DRAIN LEAKAGE.

32-014-01 RESTORE - RESTORE THE EXPOSED SURFACES OF THENOSE LANDING GEAR SHOCK STRUT PISTON BY CLEANING.

32-032-01 GENERAL VISUAL INSPECTION - INSPECT (GENERALVISUAL) THE BRAKE WEAR PINS FOR MINIMUM EXTENSION.

32-038-01 GENERAL VISUAL INSPECTION - INSPECT (GENERALVISUAL) THE BRAKE ASSEMBLY.

32-800-01 ACCOMPLISH - EXTERNAL - ZONAL (GV) NOSE LANDINGGEAR (FROM THE GROUND) (EZAP)

32-802-01 ACCOMPLISH - EXTERNAL - ZONAL (GV) LEFT MAINLANDING GEAR AND LANDING GEAR DOORS (FROM THEGROUND) (EZAP)

32-806-01 ACCOMPLISH - EXTERNAL - ZONAL (GV) RIGHT MAINLANDING GEAR AND LANDING GEAR DOORS (FROM THEGROUND)

52-800-01 ACCOMPLISH - EXTERNAL - ZONAL (GV) DOORS (FROM THEGROUND, DOORS CLOSED)

52-840-01 ACCOMPLISH - EXTERNAL - ZONAL (GV) DOORS (FROM THEGROUND, DOORS CLOSED)

53-836-01 ACCOMPLISH - EXTERNAL - ZONAL (GV) LOWER FUSELAGE(FROM THE GROUND, NO ADDITIONAL ACCESS PANELSREQUIRED)

53-842-01 ACCOMPLISH - EXTERNAL - ZONAL (GV) NOSE WHEELWELL AND LANDING GEAR DOORS (EZAP)

53-850-01 ACCOMPLISH - EXTERNAL - ZONAL (GV) FORWARDAIRSTAIR

53-852-01 ACCOMPLISH - INTERNAL - ZONAL (GV) FORWARD CARGOCOMPARTMENT (NO CARGO LINERS REMOVED)

53-866-01 ACCOMPLISH - EXTERNAL - ZONAL (GV) MAIN LANDINGGEAR WHEEL WELL (FROM THE GROUND) (EZAP)

53-868-01 ACCOMPLISH - INTERNAL - ZONAL (GV) AFT CARGOCOMPARTMENT (NO CARGO LINERS REMOVED)

53-886-01 ACCOMPLISH - EXTERNAL-ZONAL (GV) AREA AFT OFPRESSURE BULKHEAD. INSPECTION IS ACCOMPLISHEDFROM THE GROUND, WITHOUT THE USE OF STANDS ORLADDERS. NO ADDITIONAL ACCESS PANELS REQUIRED

55-800-01 ACCOMPLISH - EXTERNAL - ZONAL (GV) VERTICAL ANDHORIZONTAL STABILIZERS (FROM THE GROUND, NOADDITIONAL ACCESS PANELS REQUIRED)

Task Relations


Model: BOEING 737-300/400/500


57-800-01 ACCOMPLISH - EXTERNAL - ZONAL (GV) LEFT WINGSURFACE (FROM THE GROUND, CONTROL SURFACESEXTENDED, NO ADDITIONAL ACCESS REQUIRED).

57-844-01 ACCOMPLISH - EXTERNAL - ZONAL (GV) RIGHT WINGSURFACE (FROM THE GROUND, CONTROL SURFACESEXTENDED, NO ADDITIONAL ACCESS REQUIRED).

70-820-01 ACCOMPLISH - EXTERNAL - ZONAL (GV) POWERPLANT NO.1 (FROM THE GROUND, NO ACCESS PANELS REQUIRED)

70-832-01 ACCOMPLISH - EXTERNAL - ZONAL (GV) POWERPLANT NO.2 (FROM THE GROUND, NO ACCESS PANELS REQUIRED)

72-002-01 GENERAL VISUAL INSPECTION - INSPECT (GENERALVISUAL) THE LEFT ENGINE INLET AND FAN BLADES.

72-002-02 GENERAL VISUAL INSPECTION - INSPECT (GENERALVISUAL) THE RIGHT ENGINE INLET AND FAN BLADES.

72-048-01 GENERAL VISUAL INSPECTION - INSPECT (GENERALVISUAL) THE LEFT ENGINE LPT STAGE 4 BLADES.

72-048-02 GENERAL VISUAL INSPECTION - INSPECT (GENERALVISUAL) THE RIGHT ENGINE LPT STAGE 4 BLADES.

79-008-01 SERVICE - SERVICE LEFT ENGINE OIL BY CHECKING FORCORRECT LEVEL AND REPLENISHING AS REQUIRED.

79-008-02 SERVICE - SERVICE RIGHT ENGINE OIL BY CHECKING FORCORRECT LEVEL AND REPLENISHING AS REQUIRED.

79-012-01 GENERAL VISUAL INSPECTION - INSPECT (GENERALVISUAL) THE LEFT ENGINE COWLING FOR EVIDENCE OF OILSEAL DRAIN LEAKAGE.

32-004-01 RESTORE - RESTORE THE EXPOSED SURFACES OF THEMAIN LANDING GEAR SHOCK STRUT PISTON BY CLEANING.

1974-08-09 R2 LAVATORY PAPER OR LINEN WASTE RECEPTACLE FIREPREVENTION (SUPERSEDED BY FAA AD 1974-08-09 R3)

PRIMARY TO1974-08-09 R2 PARA (E) INSPECT INSPECTION OF LAVATORY WASTE

RECEPTACLES (SUPERSEDED BY FAA AD 1974-08-09 R3) 1974-08-09 R3 LAVATORY PAPER OR LINEN WASTE RECEPTACLE FIRE

PREVENTION ACD (TWO WAY) TO

737-25-1104 LAVATORY DOOR ASHTRY INSTALLATION SERVICEBULLETIN

737-25-1102 R1 NO SMOKING IN LAVATORY PLACARD INSTALLATIONSERVICE BULLETIN

1988-22-11 R1 PREVENT RAPID DECOMPRESSION OF THE AIRPLANE ACD (TWO WAY) TO737-53A1177 R7 FUSELAGE - SKIN - REPAIR METHODS FOR CRACKS IN

LOWER SKINS AT LAP JOINTS AND WINDOW CORNERSSERVICE BULLETIN

Task Relations


Model: BOEING 737-300/400/500


1989-09-03 PREVENT DECOMPRESSION OF THE AIRPLANE ACD (TWO WAY) TO737-53A1177 R7 FUSELAGE - SKIN - REPAIR METHODS FOR CRACKS IN


1990-06-02 PREVENT STRUCTURAL FAILURE ACD (TWO WAY) TO737-57A1271 R3 WINGS - TRAILING EDGE AND TRAILING EDGE DEVICES -

TRAILING EDGE FLAPS - OUTBOARD FLAP, INBOARD TRACKINSPECTION/OVERHAUL/REPLACEMENT AT WBL 254SERVICE BULLETIN

1990-25-14 PREVENT THE OCCURRENCE OF FIRE AND SMOKE IN THEPASSENGER CABIN AND COCKPIT

ACD (TWO WAY) TO737-25-1274 EQUIPMENT/FURNISHINGS - PASSENGER COMPARTMENT -

INSPECTION AND REWORK OF FORWARD LOWEREDCEILING PANEL SERVICE BULLETIN

1991-07-04 PREVENT RAPID DECOMPRESSION OF THE AIRPLANE ACD (TWO WAY) TO737-53A1177 R7 FUSELAGE - SKIN - REPAIR METHODS FOR CRACKS IN


1991-08-12 PREVENT INABILITY OF THE AIRPLANE TO CARRYFAIL-SAFE LOADS DUE TO DISBONDED DOUBLERS

ACD (TWO WAY) TO737-53A1177 R7 FUSELAGE - SKIN - REPAIR METHODS FOR CRACKS IN


1992-24-04 PREVENT UNCOMMANDED DEPLOYMENT OF THE THRUSTREVERSER

ACD (TWO WAY) TO737-78A1055 R3 EXHAUST - THRUST REVERSER CONTROL SYSTEM -

MODIFICATION OF TEE AND RESTRICTOR FITTINGS ONTHRUST REVERSER - CFM56 ENGINES SERVICE BULLETIN

1992-25-09 PREVENT DECOMPRESSION OF THE AIRPLANE ACD (TWO WAY) TO737-53A1177 R7 FUSELAGE - SKIN - REPAIR METHODS FOR CRACKS IN


1993-05-05 PREVENT ENGINE FLAMEOUT DURING AIRPLANE DESCENTIN MODERATE TO SEVERE INCLEMENT WEATHERCONDITIONS

ACD (TWO WAY) TO

737-77-1031 ENGINE INDICATING - POWER - REMOVAL OF 45% N1PLACARD IF TWO ENGINES MODIFIED FOR INCREASEDCAPABILITY IN HAIL, RAIN AND SLEET ARE INSTALLEDSERVICE BULLETIN

1994-06-11 PREVENT DRAINAGE FROM A FUEL LINE LEAK WITHIN THEWING LEADING EDGE FROM ENTERING THE TURBINEEXHAUST AREA

ACD (TWO WAY) TO

737-57-1221 WINGS - LEADING EDGE PANEL SEALING AND DRAIN HOLEPLUGGING SERVICE BULLETIN

Task Relations


Model: BOEING 737-300/400/500


1995-09-01 PREVENT THE FAILURE OF THE FIREPROOF INSULATIONTOPCOAT INSTALLED ON THE FIREWALLS FOR THE THRUSTREVERSER FAN COWLS

ACD (TWO WAY) TO

737-78A1056 R1 EXHAUST - THRUST REVERSER - APPLICATION OF A FIRERESISTANT TOP COAT TO THE THRUST REVERSER INNERFAN DUCT WALLS SERVICE BULLETIN

1995-10-05 PREVENT REDUCED CONTROLLABILITY OF THE AIRPLANE ACD (TWO WAY) TO737-27A1191 FLIGHT CONTROLS - HORIZONTAL STABILIZER -

HORIZONTAL STABILIZER TRIM CONTROL SYSTEM -REPLACEMENT OF THE STABILIZER TRIM ELECTRICACTUATOR SERVICE BULLETIN

1996-25-17 PREVENT RESTRICTION OF ELEVATOR CONTROL DURINGTAKEOFF, CLIMBOUT, AND LANDING

ACD (TWO WAY) TO737-27A1194 FLIGHT CONTROLS - ELEVATOR AND TAB -

INSPECTION/MODIFICATION OF THE FEEL AND CENTERINGUNIT SERVICE BULLETIN

1999-01-16 PREVENT DAMAGE TO THE ENGINES, AIRFRAME ACD (TWO WAY) TO737-38-1043 WATER / WASTE - POTABLE WATER SYSTEM - PASSENGER

WATER SYSTEM - INFLIGHT POTABLE WATER DRINAAGECHANGE SERVICE BULLETIN

1999-10-12 DETECT AND CORRECT CORROSION AND CRACKING OFTHE ACTUATOR BEAM ARM OF THE MAIN LANDING GEAR(MLG)

PRIMARY TO

1999-10-12 PARA (B)&(C) DETAIL VISUAL INSPECTION DETECT AND CORRECTCORROSION AND CRACKING OF THE ACTUATOR BEAM ARMOF THE MAIN LANDING GEAR (MLG) AND AN ULTRASONICINSPECTION OF THE ACTUATOR BEAM ARM CLEVIS

1999-10-12 PARA (A) VISUAL DETECT AND CORRECT CORROSION ANDCRACKING OF THE ACTUATOR BEAM ARM OF THE MAINLANDING GEAR (MLG) AND ULTRASONIC INSPECTION

1999-10-12 DETECT AND CORRECT CORROSION AND CRACKING OFTHE ACTUATOR BEAM ARM OF THE MAIN LANDING GEAR(MLG)

ACD (TWO WAY) TO

737-32A1224 R3 LANDING GEAR - MAIN GEAR AND DOORS - MAIN GEARTRUNNION PIN, ACTUATOR BEAM ARM, AND ACTUATORBOLT ASSEMBLIES REWORK SERVICE BULLETIN

1999-10-13 PREVENT FAILURE OF THE TRAILING EDGE FLAP LIMITSWITCH

ACD (TWO WAY) TO737-27A1227 FLIGHT CONTROLS - TRAILING EDGE FLAP AND

HORIZONTAL STABILIZER TRIM SYSTEMS - S245 FLAP LIMITSWITCH INSPECTION AND R850 RELAY INSTALLATIONSERVICE BULLETIN

1999-23-20 PREVENT A SHORT CIRCUIT AND OVERHEATING OF THETRANSIENT SUPPRESSION DIODE

ACD (TWO WAY) TO

Task Relations


Model: BOEING 737-300/400/500


737-28-1115 R1 FUEL - DISTRIBUTION - REPLACEMENT OF THE REFUELVALUE ACTUATOR SUPPRESSION DIODES SERVICEBULLETIN

1999-24-08 PREVENT FAILURE OF ALL ELECTRICALLY POWEREDAIRPLANE SYSTEMS, WHICH COULD RESULT IN THEINABILITY TO CONTINUE SAFE FLIGHT AND LANDING

PRIMARY TO

1999-24-08 PARA (G) DIODE TEST PREVENT FAILURE OF ALL ELECTRICALLYPOWERED AIRPLANE SYSTEMS, WHICH COULD RESULT INTHE INABILITY TO CONTINUE SAFE FLIGHT AND LANDING

1999-24-08 PARA (E) REPORT PREVENT FAILURE OF ALL ELECTRICALLYPOWERED AIRPLANE SYSTEMS, WHICH COULD RESULT INTHE INABILITY TO CONTINUE SAFE FLIGHT AND LANDING SUBMITION

1999-24-08 PARA (C) DIODE TEST PREVENT FAILURE OF ALL ELECTRICALLYPOWERED AIRPLANE SYSTEMS, WHICH COULD RESULT INTHE INABILITY TO CONTINUE SAFE FLIGHT AND LANDING

1999-24-08 PARA (A)&(B) REPLACE PREVENT FAILURE OF ALL ELECTRICALLYPOWERED AIRPLANE SYSTEMS, WHICH COULD RESULT INTHE INABILITY TO CONTINUE SAFE FLIGHT AND LANDING THE AIRPLANE BATTERY

1999-24-08 PARA (F) REPLACE PREVENT FAILURE OF ALL ELECTRICALLYPOWERED AIRPLANE SYSTEMS, WHICH COULD RESULT INTHE INABILITY TO CONTINUE SAFE FLIGHT AND LANDING AIRPLANE BATTERY

1999-24-08 PREVENT FAILURE OF ALL ELECTRICALLY POWEREDAIRPLANE SYSTEMS, WHICH COULD RESULT IN THEINABILITY TO CONTINUE SAFE FLIGHT AND LANDING

ACD (TWO WAY) TO

737-24A1136 R2 ELECTRICAL POWER - AC GENERATION SYSTEM -GENERATOR CONTROL UNIT - REPLACEMENT SERVICEBULLETIN

1999-25-02 SPOILER MIXER TO AILERON CONTROL QUADRANT,INSPECTION / REPAIR

ACD (TWO WAY) TO737-27A1213 R1 FLIGHT CONTROLS - FLIGHT SPOILER CONTROL SYSTEM -

INSPECTION OF THE SPOILER MIXER FOR CORRECTINSTALLATION OF FASTENERS SERVICE BULLETIN

1999-26-21 PREVENT ELECTRICAL ARCING DUE TO CHAFING BETWEENCERTAIN HYDRAULIC HOSES AND ADJACENT WIREBUNDLES

ACD (TWO WAY) TO

737-29-1076 R1 HYDRAULIC POWER-B SYSTEM MOTOR DRIVEN PUMP WIREBUNDLE INSPECTION AND CLAMP INSTALLATION SERVICEBULLETIN

2000-04-02 PREVENT FUEL SUCTION FEED OPERATION ON BOTHENGINES WITHOUT FLIGHT CREW INDICATION

ACD (TWO WAY) TO

Task Relations


Model: BOEING 737-300/400/500


737-28A1114 R3 FUEL - INDICATING - FUEL QUANTITY INDICATING SYSTEM -REPLACEMENT OF FUEL LOW PRESSURE SWITCHES ANDINSPECTION OF FUEL BOOST PUMPS SERVICE BULLETIN

2000-05-29 DETECT FATIGUE CRACKING OF THE FORWARD PRESSUREBULKHEAD

ACD (TWO WAY) TOICA-REP-53-041-01 INSPECT FUSELAGE SECTION 41- REPAIR OF CRACK ON

FORWARD PRESSURE BULKHEAD SKIN AT BS 178 ANDLBL5.7

737-53A1173 FUSELAGE - BODY STATION 178 BULKHEAD - INSPECTION,REPAIR AND PREVENTIVE MODIFICATION SERVICEBULLETIN

2000-07-06 PREVENT FATIGUE CRACKING OF THE LOWER CORNERSOF THE DOOR FRAME AND CROSS BEAM OF THE FORWARDCARGO DOOR

ACD (TWO WAY) TO

737-52-1100 R4 DOORS - FORWARD CARGO - LOWER FORWARD AND AFTCORNER INSPECTION MODIFICATION, AND REPLACEMENTSERVICE BULLETIN

737-52A1100 R5 DOORS - FORWARD CARGO - LOWER FORWARD AND AFTCORNER INSPECTION, MODIFICATION AND REPLACEMENTSERVICE BULLETIN

2000-14-13 REPLACE DOOR HANDLE MOUNT HUB ENTRY, GALLEY ANDSERVICE DOORS

ACD (TWO WAY) TO737-25-1322 EQUIPMENT/FURNISHINGS - PASSENGER COMPARTMENT -

PASSENGER CABIN LINING AND INSULATION - DOORHANDLE MOUNTING HUB ASSEMBLY REPLACEMENTSERVICE BULLETIN

2000-19-05 PREVENT DETACHMENT OF AN ELEVATOR TAB PUSH RODDUE TO A DETACHED NUT AT EITHER END ATTACHMENT OFA PUSH ROD

ACD (TWO WAY) TO

737-22A1130 AUTO FLIGHT - AUTO THROTTLE COMPUTER -REPLACEMENT OF THE AUTO THROTTLE COMPUTERSERVICE BULLETIN

2000-23-34 PREVENT A SEVERE ASYMMETRIC THRUST CONDITIONDURING FLIGHT WHICH COULD RESULT IN LOSS OFCONTROL OF THE AIRPLANE

ACD (TWO WAY) TO

737-22A1130 AUTO FLIGHT - AUTO THROTTLE COMPUTER -REPLACEMENT OF THE AUTO THROTTLE COMPUTERSERVICE BULLETIN

2000-26-05 PREVENT POTENTIAL IGNITION OF FIBERGLASSINSULATION IN THE ENVIRONMENTAL CONTROL SYSTEM(ECS) DUCTS

ACD (TWO WAY) TO

737-21A1129 AIR CONDITIONING - DISTRIBUTION - DUCT INSULATIONREPLACEMENT SERVICE BULLETIN

Task Relations


Model: BOEING 737-300/400/500


2001-01-13 DETECT AND CORRECT CHAFING AND TO PREVENTELECTRICAL CONTACT BETWEEN THE FUEL QUANTITYINDICATING SYSTEM (FQIS) WIRING AND THESURROUNDING STRUCTURE

ACD (TWO WAY) TO

737-28A1168 R2 FUEL QUANTITY INDICATING SYSTEM (FQIS) INSPECTIONOF THE WIRING HARNESS IN WING TANK NUMBER # 2SERVICE BULLETIN

2001-02-01 DETECT FATIGUE CRACKING OF THE FORWARD PRESSUREBULKHEAD

ACD (TWO WAY) TO737-53A1208 FUSELAGE-BODY STATION 178

BULKHEAD-INSPECION,REPAIR,AND PREVENTIVEMODIFICATION SERVICE BULLETIN

2001-10-14 FIND AND FIX INCORRECT INSTALLATION OF THE RELEASEPIN IN THE GENERATOR FIRING MECHANISM OF THECHEMICAL OXYGEN GENERATOR

ACD (TWO WAY) TO

737-35-1076 OXYGEN - PASSENGER - PASSENGER OXYGEN SYSTEM -INSPECTION OF THE RELEASE PIN LOCATION IN THEOXYGEN GENERATOR FIRING PIN SERVICE BULLETIN

2001-11-07 PREVENT FAILURE OF THE MOTOR OPERATED HYDRAULICSHUTOFF VALVES

ACD (TWO WAY) TO737-29A1078 R2 HYDAULIC POWER - DC MOTOR OPERATED SHUTOFF

VALVE (SENSITIVE LOCATIONS) REPLACEMENT SERVICEBULLETIN

2001-13-07 PREVENT INABILITY TO SHUT OFF THE FLOW OF FUEL TOAN ENGINE AFTER AN UNCONTAINED ENGINE FAILURE

ACD (TWO WAY) TO737-28-1164 R1 FUEL - ENGINE FUEL FEED SYSTEM SERVICE BULLETIN

2001-15-01 ESCAPE SLIDE LATCH ASSEMBLY MODIFICATION ACD (TWO WAY) TO737-25-1405 R2 EQUIPMENT/FURNISHINGS - EMERGENCY -

DOOR-MOUNTED ESCAPE SYSTEM - LATCH ASSEMBLYMODIFICATION SERVICE BULLETIN

2001-22-13 PREVENT LOSS OF RUDDER CONTROL IMPROPERTORQUED FASTENERS

ACD (TWO WAY) TO737-27A1214 R1 FLIGHT CONTROLS - RUDDER AND RUDDER TRIM CONTROL

SYSTEM - RUDDER PEDAL PUSHROD FASTENERREPLACEMENT SERVICE BULLETIN

2002-02-08 PREVENT THE LOOSENING AND LOSS OF SUPPORT PINRETAINING BOLT

ACD (TWO WAY) TO737-57A1260 R2 WINGS - MAIN LANDING GEAR SUPPORT BEAM RETAINING

PIN - BOLT AND SELF-LOCKING NUT REPLACEMENTSERVICE BULLETIN

2002-05-07 TO FIND AND FIX DISCREPANCIES OF THE INBOARDTRACKS OF THE OUTBOARD FLAPS, WHICH COULD RESULTIN LOSS OF THE OUTBOARD TRAILING EDGE FLAPS ANDCONSEQUENT REDUCED CONTROLLABILITY OF THEAIRPLANE (SUPERSEDED BY AD 2013-09-02)

ACD (TWO WAY) TO

Task Relations


Model: BOEING 737-300/400/500


737-57A1271 R3 WINGS - TRAILING EDGE AND TRAILING EDGE DEVICES -TRAILING EDGE FLAPS - OUTBOARD FLAP, INBOARD TRACKINSPECTION/OVERHAUL/REPLACEMENT AT WBL 254SERVICE BULLETIN

2002-07-08 FIND AND FIX CRACKING OF CERTAIN FUSELAGE LAPJOINTS

PRIMARY TO2002-07-08 PARA (N) HFEC FIND AND FIX CRACKING OF CERTAIN FUSELAGE LAP

JOINTS INSPECTION OF WINDOW CORNERS 2002-07-08 PARA (M) LFEC FIND AND FIX CRACKING OF CERTAIN FUSELAGE LAP

JOINTS INSPECTION 2002-07-08 FIND AND FIX CRACKING OF CERTAIN FUSELAGE LAP

JOINTS ACD (TWO WAY) TO

737-53A1177 R7 FUSELAGE - SKIN - REPAIR METHODS FOR CRACKS INLOWER SKINS AT LAP JOINTS AND WINDOW CORNERSSERVICE BULLETIN

2002-07-10 PREMATURE CRACKING OF FUSELAGE LAP JOINT REPAIRS ACD (TWO WAY) TO737-53A1177 R6 FUSELAGE - SKIN - REPAIR METHODS FOR CRACKS IN

LOWER SKINS AT LAP JOINTS (SUPERSEDED BY SB737-53A1177 R7) SERVICE BULLETIN


2002-10-11 DETECT AND CORRECT CORROSION OR CRACKING OF THEAFT PRESSURE BULKHEAD AT BODY STATION (BS) 1016

PRIMARY TO2002-10-11 PARA (B) ACCOMPLISH DETECT AND CORRECT CORROSION OR

CRACKING OF THE AFT PRESSURE BULKHEAD AT BODYSTATION (BS) 1016 DRAIN HOLE ENLARGEMENT

2002-10-11 PARA (A) INITIAL INSPECTION DETECT AND CORRECT CORROSIONOR CRACKING OF THE AFT PRESSURE BULKHEAD AT BODYSTATION (BS) 1016

2002-10-11 PARA (E) (F) DETAILED INSPECTION DETECT AND CORRECTCORROSION OR CRACKING OF THE AFT PRESSUREBULKHEAD AT BODY STATION (BS) 1016

2002-10-11 DETECT AND CORRECT CORROSION OR CRACKING OF THEAFT PRESSURE BULKHEAD AT BODY STATION (BS) 1016

ACD (TWO WAY) TO737-53A1075 R3 FUSELAGE AFT PRESSURE BULKHEAD INSPECTION,

MODIFICATION AND REPAIR SERVICE BULLETIN 2002-10-12 PREVENT A DISCONNECTED AILERON TAB ACD (TWO WAY) TO

737-27-1223 FLIGHT CONTROLS - AILERON & AMP; AILERON TRIMCONTROL SYSTEM, AILERON TAB CONTROL ROD BARRELINSPECTION OR REPLACEMENT SERVICE BULLETIN

2002-18-02 PREVENT JAMMING 1ST OFFICER CONTROL WHEEL DUE TOFOREIGN OBJECTS

ACD (TWO WAY) TO

Task Relations


Model: BOEING 737-300/400/500


737-27A1238 FLIGHT CONTROLS - LATERAL TRANSFER MECHANISM,LOWER BEARING SUPPORT INSPECTION, ANDMODIFICATION SERVICE BULLETIN

2003-03-05 FATIGUE CRACKING ROD ENDS OF ACTUATORS OF THELEADING EDGE SLATS

ACD (TWO WAY) TO737-27A1243 FLIGHT CONTROLS - LIFT AUGMENTATION - LEADING EDGE

FLAPS AND SLATS - INSPECTION ANDREPAIR/REPLACEMENT FOR VIBRO-ENGRAVED ROD ENDSSERVICE BULLETIN

2003-07-12 PREVENT FAILURE OF LANDING GEAR PARTS ACD (TWO WAY) TO737-32-1322 R1 LANDING GEAR - MAIN AND NOSE LANDING GEAR - LIFE

LIMITED COMPONENTS TRACKING AND SERIAL NUMBERADDITION SERVICE BULLETIN

2003-08-15 TO FIND AND FIX CRACKING OF THE FUSELAGE LAP JOINTS(SUPERSEDED BY AD 2013-09-01)

ACD (TWO WAY) TO737-53A1255 R2 FUSELAGE - SKIN - CROWN SKIN LAP JOINT - INSPECTION

FOR LOWER ROW CRACKING AT STRINGERS S-4, S-10, S-14BETWEEN STA 360 AND STA 908 SERVICE BULLETIN

737-53A1255 FUSELAGE - SKIN - INSPECTION FOR CROWN SKIN LAPJOINT CRACKING (SUPERSEDED BY SB 737-53A1255 R1)SERVICE BULLETIN

D-2003-172 R1 ¿BERLAPPENDE VERBINDUNGEN DER RUMPFBEPLANKUNGBEI DEN L¿NGSTR¿GERN S-4, S-10 UND S-14 (FUSELAGESKIN - LAP JOINTS AT STRINGERS S-4, S-10 AND S-14).RISSBILDUNG IM BEREICH DER UNTERENBEFESTIGUNGSREIHE DER ¿BERLAPPENDEN BEPLANKUNGUND DEN INNEREN L¿NGSTR¿GER-CLIPS K¿NNEN ZUEINER RAPIDEN DEKOMPRESSION DER DRUCKKABINE IMFLUGE F¿HREN. (SUPERSEDED BY D-2003-172 R2) GERMANAD

2003-14-06 DETECT AND CORRECT FATIGUE CRACKS IN THE LAPJOINTS AND CONSEQUENT RAPID DECOMPRESSION OFTHE AIRPLANE

ACD (TWO WAY) TO

737-53-1179 FUSELAGE - BONDED SKIN DOUBLERS (TEAR STRAPS) -DELAMINATION INSPECTION AND REPAIR SERVICEBULLETIN


2003-20-13 PREVENT A REDUCTION IN FLIGHT CREW VISIBILITY DUETO STALLED WIPER MOTOR DURING HEAVY PRECIPATIONAND A PERIOD OF SUBSTANIAL CREW WORKLOAD.

ACD (TWO WAY) TO

737-30A1052 ICE AND RAIN PROTECTION - WINDOWS, WINDSHIELDS ANDDOORS - WINDSHIELD WIPER SYSTEM - WIRING CHANGESERVICE BULLETIN

Task Relations


Model: BOEING 737-300/400/500


2003-26-01 TO DETECT AND CORRECT LOOSE BOLTS COMMON TO THEFLANGE OF THE RUDDER FRONT SPAR AND MAIN THRUSTHINGE AND ACTUATOR ASSEMBLY

ACD (TWO WAY) TO

737-55A1087 STABILIZER - RUDDER - MAIN ACTUATOR AND AUXILIARYACTUATOR ATTACH FITTINGS - INSPECTION FOR LOOSEBOLTS SERVICE BULLETIN

2003-26-08 PREVENT RUPTURE OF THE PORTABLE WATER TANKDURING FLIGHT (MODIFICATION HAS NOT BEENACCOMPLISHED)

ACD (TWO WAY) TO

737-38A1038 WATER / WASTE - AIR SUPPLY - WATER TANKPRESSURIZATION SYSTEM - REPLACE THE PRESSURERELIEF VALVE SERVICE BULLETIN

2004-02-08 PREVENT FORWARD DOOR ESCAPE SLIDES FROM FALLINGOUT OF THEIR COMPARTMENTS INTO THE AIRPLANEINTERIOR AND INFLATING

ACD (TWO WAY) TO

737-25-1430 R1 EQUIPMENT AND FURNISHING - EMERGENCY - FORWARDENTRY AND SERVICE DOOR - REPLACEMENT OF THEESCAPE SLIDE COMPARTMENT HINGE ASSEMBLY SERVICEBULLETIN

2004-03-34 R1 PREVENT THE LATCH CABLE ASSEMBLY FROMDISCONNECTING FROM THE LATCH BLOCK ASSEMBLY OFTHE DOOR MOUNTED ESCAPE SLIDES

ACD (TWO WAY) TO

737-25-1434 EQUIPMENT AND FURNISHINGS - EMERGENCY - FORWARDAND AFT ENTRY AND SERVICE DOORS REPLACEMENT OFTHE ESCAPE SLIDE LATCH CABLE ASSEMBLY - MOUNTINGFASTENERS SERVICE BULLETIN

2004-04-03 TO PREVENT UNCOMMANDED MOVEMENT OF THEFLIGHTCREW SEATS DURING ACCLERATION AND TAKEOFF

ACD (TWO WAY) TO737-25A1363 R3 EQUIPMENT/FURNISHINGS - FLIGHT COMPARTMENT -

CAPTAIN AND FIRST OFFICER CREW SEATS - INSPECTIONAND INSTALLATION OF THE REAR TRACK LOCK BRACKETTHROUGH BOLTS SERVICE BULLETIN

737-25A1363 R1 EQUIPMENT/FURNISHINGS - FLIGHT COMPARTMENT -CAPTAIN AND FIRST OFFICER CREWSEATS - INSPECTIONAND INSTALLATION OF THE REAR TRACK LOCK BRACKETTHROUGH BOLTS SERVICE BULLETIN

2004-10-06 ENSURE ADEQUATE ELECTRICAL BONDING BETWEEN THEPENETRATION FITTINGS OF THE HYDRAULIC HEATEXCHANGER AND THE REAR SPAR OF THE FUEL TANKS OFTHE LEFT AND RIGHT WINGS

ACD (TWO WAY) TO

737-29A1096 R2 HYDRAULIC POWER - HYDRAULIC SYSTEM A AND B -HYDRAULIC HEAT EXCHANGER - PREPARATION ANDMEASUREMENT OF THE ELECTRICAL BONDING FAYSURFACES AT THE HYDRAULIC FITTING PENETRATIONSINTO THE FUEL TANKS SERVICE BULLETIN

Task Relations


Model: BOEING 737-300/400/500


2004-15-04 PREVENT CONTAMINATION OF THE FUELING FLOATSWITCH BY MOISTURE OR FUEL, AND CHAFING OF THEFLOAT SWITCH WIRING AGAINST THE FUEL TANK CONDUIT

ACD (TWO WAY) TO

737-28A1141 R2 FUEL - PRESSURE FUELING SYSTEM - IMPROVED FUELINGFLOAT SWITCH AND WIRING PROVISION INSTALLATIONSERVICE BULLETIN

2004-18-06 FIND AND FIX FATIGUE CRACKING OF CERTAIN UPPER ANDLOWER SKIN PANELS OF THE FUSELAGE

ACD (TWO WAY) TO737-53A1210 R1 FUSELAGE-SKIN-FUSELAGE SKIN INSPECTION AND REPAIR

SERVICE BULLETIN 737-53A1177 R7 FUSELAGE - SKIN - REPAIR METHODS FOR CRACKS IN


2004-19-10 PREVENT FAILURE OF THE OUTER AND INNER HINGE PINSDUE TO CORROSION OR CRACKING

PRIMARY TO2004-19-10 PARA (H)(I) DETAIL INSPECTION PREVENT FAILURE OF THE OUTER

AND INNER HINGE PINS DUE TO CORROSION OR CRACKINGAND MAGNETIC PARTICLE INSPECTION (PART 3 OF ASB)

2004-19-10 PARA (F)(G) DETAIL INSPECTION PREVENT FAILURE OF THE OUTERAND INNER HINGE PINS DUE TO CORROSION OR CRACKINGAND MAGNETIC PARTICLE INSPECTION (PART 2 OR 3 OFASB)

2004-19-10 PARA (A) DETAIL INSPECTION PREVENT FAILURE OF THE OUTERAND INNER HINGE PINS DUE TO CORROSION OR CRACKINGOF THE PIVOT HINGE PIN JOINTS

2004-19-10 PREVENT FAILURE OF THE OUTER AND INNER HINGE PINSDUE TO CORROSION OR CRACKING

ACD (TWO WAY) TO737-55A1077 STABILIZERS - HORIZONTAL STABILIZER - HINGE PIN

INSPECTION AND CORROSION PREVENTION SERVICEBULLETIN

2004-23-07 PREVENTION OF GALLEY FROM SHIFTING ACD (TWO WAY) TO737-53-1154 R2 FUSELAGE - GALLEY NO. 2 UPPER ATTACHMENT SUPPORT -

BODY STATIONS 344 TO 360 BETWEEN RIGHT STRINGERS 3AND 7 SERVICE BULLETIN

2005-03-02 PREVENT LOOSENED OR DISCONNECTED OVERHEADDUCTS FROM CAUSING CEILING PANELS TO DROP BELOWTHE MINIMUM HEIGHT OF THE EVACUATION ZONE FOR THEPASSENGER CABIN

ACD (TWO WAY) TO

737-21-1131 R2 AIR CONDTIONING - DISTRIBUTION - PASSENGER CABINCONDITIONED AIR DISTRIBUTION SYSTEM - OVERHEADDUCT LANYARD INSTALLATION SERVICE BULLETIN

2005-04-01 PREVENT ARCING OR SPARKING AT THE INTERFACEBETWEEN THE BULKHEAD FITTING OF THE ENGINE FUELFEED TUBE AND THE FRONT SPAR INSIDE THE FUEL TANK

ACD (TWO WAY) TO

Task Relations


Model: BOEING 737-300/400/500


737-28A1174 R2 FUEL - ENGINE FUEL FEED SYSTEM, ADDITION OF BONDINGBETWEEN ENGINE FUE FEED LINE FITTING AND WINGFRONT SPAR SERVICE BULLETIN

2005-07-12 DETECT AND CORRECT FATIGUE CRACKING OF THE AFTFRAME AND FRAME SUPPORT STRUCTURE OF THEFORWARD GALLEY DOOR

ACD (TWO WAY) TO

737-53A1241 R1 FUSELAGE - FRAMES AND BULKHEADS - STA 277 TO STA328 FRAME INSPECTIONS, STRINGER 7R TO 17R -FORWARD GALLEY DOOR CUTOUT SERVICE BULLETIN

2005-07-19 FIND AND FIX FATIGUE CRACKING IN THE FUSELAGE SKIN,DOUBLER, BEARSTRAP, AND FRAMES

ACD (TWO WAY) TO737-53A1228 FUSELAGE - MAIN CARGO DOOR CUTOUT, FORWARD

CARGO DOOR CUTOUT, AFT CARGO DOOR CUTOUT - SKIN,BEARSTRAP AND FRAME INSPECTIONS SERVICE BULLETIN

2005-13-27 DETECT AND CORRECT FATIGUE CRACKING OF THEFUSELAGE SKIN (SUPERSEDED BY FAA AD 2012-26-02)

ACD (TWO WAY) TO737-53A1234 R2 FUSELAGE - SKIN - CRACKS AT CHEM-MILLED STEPS -

INSPECTION AND REPAIR SERVICE BULLETIN 2005-19-25 DETECT AND CORRECT FATIGUE CRACKS OF THE

COUNTERSUNK RIVET HOLES,

ACD (TWO WAY) TO

737-53-1230 FUSELAGE - SKIN - RADIO ALTIMETER ANTENNA CUTOUT -LOWER LOBE SKIN CRACKS AT BLO SERVICE BULLETIN

2006-03-12 PREVENT CHAFED WIRE BUNDLES NEAR THE CENTER FUELTANK

ACD (TWO WAY) TO737-28-1208 R2 FUEL - INDICATING - WING CENTER TANK WIRE BUNDLES

INSPECTION AND CLAMPS CHANGE SERVICE BULLETIN 2006-12-23 PREVENT EXCESSIVE IN-FLIGHT VIBRATIONS OF THE

ELEVATOR TAB PRIMARY TO

2006-12-23 PARA (I) INSPECTION PREVENT EXCESSIVE IN-FLIGHT VIBRATIONSOF THE ELEVATOR TAB OF THE ELEVATOR TAB ASSEMBLY

2006-12-23 PARA (F) DETAILED/FREE-PLAY INSPECTION PREVENT EXCESSIVEIN-FLIGHT VIBRATIONS OF THE ELEVATOR TAB OF THEELEVATOR TAB ASSEMBLY PER WORK PACKAGE I

2006-12-23 PARA (G) DETAILED/FREE-PLAY INSPECTION PREVENT EXCESSIVEIN-FLIGHT VIBRATIONS OF THE ELEVATOR TAB OF THEELEVATOR TAB ASSEMBLY PER WORK PACKAGE II

2006-12-23 PREVENT EXCESSIVE IN-FLIGHT VIBRATIONS OF THEELEVATOR TAB

ACD (TWO WAY) TOD-2003-021 R2 SCHARNIERE UND AUSLENKMECHANISMUS DER

H¿HENRUDERHILFSKLAPPEN GERMAN AD

Task Relations


Model: BOEING 737-300/400/500


737-55A1070 R4 STABILIZERS - ELEVATOR - TAB ASSEMBLY - INSPECTIONOF ELEVATOR TAB HINGE AND ELEVATOR TAB CONTROLMECHANISM SERVICE BULLETIN

2006-12-23 PARA (F) DETAILED/FREE-PLAY INSPECTION PREVENT EXCESSIVEIN-FLIGHT VIBRATIONS OF THE ELEVATOR TAB OF THEELEVATOR TAB ASSEMBLY PER WORK PACKAGE I

ACD (TWO WAY) TO

737-55A1070 R4 TABLE1.1

ACCOMPLISH STABILIZERS - ELEVATOR - TAB ASSEMBLY -INSPECTION OF ELEVATOR TAB HINGE AND ELEVATOR TABCONTROL MECHANISM SERVICE BULLETIN ACTIONS, PART4, FOLLOWED BY PART 1,PART 2,PART 3 FOLLOWED BYPART 5 FOR AIRPLANES THAT HAVE NOT BEEN INSPECTEDIN ACCORDANCE WITH SB 737-55A1070 REV. 1

2006-12-23 PARA (G) DETAILED/FREE-PLAY INSPECTION PREVENT EXCESSIVEIN-FLIGHT VIBRATIONS OF THE ELEVATOR TAB OF THEELEVATOR TAB ASSEMBLY PER WORK PACKAGE II

ACD (TWO WAY) TO

737-55A1070 R4 TABLE 2 ACCOMPLISH STABILIZERS - ELEVATOR - TAB ASSEMBLY -INSPECTION OF ELEVATOR TAB HINGE AND ELEVATOR TABCONTROL MECHANISM SERVICE BULLETIN ACTION PART 6FOLLOWED BY TABLE 4 FOR ALL AIRPLANES THAT HAVEELEVATOR/TAB CONFIGURATION 21OR 31 AS DETERMINEDFROM PART 4

2006-15-18 PREVENT A SINGLE FAULT FAILURE IN FLIGHT FROMSIMULATING A TEST CONDITION

ACD (TWO WAY) TO737-33-1132 R3 LIGHTS - MASTER DIM AND TEST - SUPPLY TEST GROUND

SIGNAL WIRING SEPARATION SERVICE BULLETIN 2006-21-01 PREVENT EXCESSIVE VIBRATION OF THE AIRFRAME

DURING FLIGHT PRIMARY TO

2006-21-01 PARA (G) FREEPLAY CHECK PREVENT EXCESSIVE VIBRATION OFTHE AIRFRAME DURING FLIGHT

2006-21-01 PARA (I) LUBRICATE PREVENT EXCESSIVE VIBRATION OF THEAIRFRAME DURING FLIGHT

2006-21-01 PARA (G) FREEPLAY CHECK PREVENT EXCESSIVE VIBRATION OFTHE AIRFRAME DURING FLIGHT

ACD (TWO WAY) TO737-27-1272 FLIGHT CONTROLS - AILERON AND AILERON TRIM

CONTROL SYSTEM - AILERON BALANCE TAB FREEPLAYCHECK AND LUBRICATION SERVICE BULLETIN

2007-03-03 PREVENT FATIGUE CRACKS IN CERTAIN VERTICAL BEAMWEBS

PRIMARY TO2007-03-03 PARA (I) TERMINATING ACTION PREVENT FATIGUE CRACKS IN

CERTAIN VERTICAL BEAM WEBS - REPLACE THE VERTICALBEAMS AT BUTTOCK LINES (BL) 5.7 AND 17.0 OF THE BS 178BULKHEAD

2007-03-03 PARA (F) HFEC PREVENT FATIGUE CRACKS IN CERTAIN VERTICALBEAM WEBS AND DETAILED INSPECTION TO DETECTCRACKS IN THE BS 178 VERTICAL BEAM WEBS

Task Relations


Model: BOEING 737-300/400/500


2007-03-03 PREVENT FATIGUE CRACKS IN CERTAIN VERTICAL BEAMWEBS

ACD (TWO WAY) TO737-53A1225 R1 FUSELAGE - FRAMES AND BULHEADS - CRACKS IN

VERTICAL BEAM WEBS AT STATION 178 PRESSUREBULKHEAD - INSPECTION, REPAIR AND PREVENTIVEMODIFICATION SERVICE BULLETIN

2007-03-07 PREVENT FAILURE OF ONE OF THE TWO INPUT CONTROLRODS OF THE MAIN RUDDER PCU

ACD (TWO WAY) TO737-27-1255 R4 FLIGHT CONTROLS - RUDDER AND RUDDER TRIM CONTROL

SYSTEM - INSTALLATION OF AN ENHANCED RUDDERCONTROL SYSTEM (RSEP) SERVICE BULLETIN

737-27-1264 R3 FLIGHT CONTROLS - RUDDER AND RUDDER TRIM CONTROLSYSTEM - REPLACEMENT OF THE P5-3 PANEL (RSEP)SERVICE BULLETIN

2007-07-02 PREVENT FAILURE OF THE ACTIVATION MECHANISM OFTHE CHEMICAL OXYGEN GENERATOR

ACD (TWO WAY) TO737-25-1548 R1 EQUIPMENT AND FURNISHINGS - PASSENGER

COMPARTMENT - MODIFICATION OF THE OXYGENACTIVATION MECHANISM WITHIN THE PASSENGERSERVICE UNITS SERVICE BULLETIN

2007-16-05 FIND AND FIX DISCREPANCIES OF THE ELEVATOR TABCONTROL ROD ASSEMBLY

ACD (TWO WAY) TO737-27A1266 R1 FLIGHT CONTROLS - ELEVATOR AND TAB CONTROL

SYSTEM - INSPECTION OF THE TAB CONTROL RODS ANDCONTROL ROD JAM NUTS (SUPERSEDED BY SB737-27A1266 R2) SERVICE BULLETIN

737-27A1266 R2 FLIGHT CONTROLS - ELEVATOR AND TAB CONTROLSYSTEM - INSPECTION OF THE TAB CONTROL RODS ANDCONTROL ROD JAM NUTS SERVICE BULLETIN

2007-24-02 DETECT AND CORRECT CHAFING OF THE FUEL BOOSTPUMP ELECTRICAL WIRING AND LEAKAGE OF FUEL INTOTHE CONDUIT, AND TO PREVENT ELECTRICAL ARCINGBETWEEN THE WIRING AND THE SURROUNDING CONDUIT

PRIMARY TO

2007-24-02 PARA (F) DETAIL INSPECTION DETECT AND CORRECT CHAFING OFTHE FUEL BOOST PUMP ELECTRICAL WIRING AND LEAKAGEOF FUEL INTO THE CONDUIT, AND TO PREVENTELECTRICAL ARCING BETWEEN THE WIRING AND THESURROUNDING CONDUIT (AD 2007-11-07)

2007-24-02 PARA (G) REPORT DETECT AND CORRECT CHAFING OF THE FUELBOOST PUMP ELECTRICAL WIRING AND LEAKAGE OF FUELINTO THE CONDUIT, AND TO PREVENT ELECTRICAL ARCINGBETWEEN THE WIRING AND THE SURROUNDING CONDUIT (AD 2007-11-07)

Task Relations


Model: BOEING 737-300/400/500


2007-24-02 PARA (I) & (J) ACCOMPLISH DETECT AND CORRECT CHAFING OF THEFUEL BOOST PUMP ELECTRICAL WIRING AND LEAKAGE OFFUEL INTO THE CONDUIT, AND TO PREVENT ELECTRICALARCING BETWEEN THE WIRING AND THE SURROUNDINGCONDUIT

2007-24-02 PARA (K) REPORT DETECT AND CORRECT CHAFING OF THE FUELBOOST PUMP ELECTRICAL WIRING AND LEAKAGE OF FUELINTO THE CONDUIT, AND TO PREVENT ELECTRICAL ARCINGBETWEEN THE WIRING AND THE SURROUNDING CONDUIT

2007-24-02 DETECT AND CORRECT CHAFING OF THE FUEL BOOSTPUMP ELECTRICAL WIRING AND LEAKAGE OF FUEL INTOTHE CONDUIT, AND TO PREVENT ELECTRICAL ARCINGBETWEEN THE WIRING AND THE SURROUNDING CONDUIT

ACD (TWO WAY) TO

737-28A1263 R2 FUEL - ENGINE FUEL FEED SYSTEM - FUEL BOOST PUMPELECTRICAL WIRE AND SLEEVE IN FUEL TANK CONDUIT(INSPECTION / REPLACEMENT) SERVICE BULLETIN

2007-26-04 PREVENT CRACKING OF THE STA 259.5 CIRCUMFERENTIALBUTT SPLICE

ACD (TWO WAY) TO737-53-1267 FUSELAGE - SKIN - CIRCUMFERENTIAL BUTT SPLICE -

INSPECTION AND PREVENTIVE MODIFICATION SERVICEBULLETIN

2008-03-20 PREVENT THE ESCAPE SLIDE FROM BEING UNUSABLEDURING AN EMERGENCY EVACUATION AND CONSEQUENTINJURY TO PASSENGERS OR CREWMEMBERS

ACD (TWO WAY) TO

737-25-1567 R1 EQUIPMENT / FURNISHINGS - DOOR MOUNTED ESCAPESYSTEM - FORWARD SERVICE DOOR SLIDE COMPARTMENTCHANGE SERVICE BULLETIN

2008-04-21 PREVENT FAILURE OF THE MAIN DECK FLOOR BEAMS ATCERTAIN BODY STATIONS DUE TO FATIGUE CRACKING

ASSOCIATED -(ONE WAY) TO737-57-1210 R2 WINGS - CENTER WING BOX - FLOOR (SUPERSEDED BY SB

737-57-1210 R3) SERVICE BULLETIN 2008-04-21 PREVENT FAILURE OF THE MAIN DECK FLOOR BEAMS AT

CERTAIN BODY STATIONS DUE TO FATIGUE CRACKING ACD (TWO WAY) TO

D-2008-139 R1 INSPEKTION / INSTANDSETZUNG DES BBL 0.07FU¿BODENTR¿GERS VON RUMPFSTATION STA651 BISSTA676 UND STA698 BIS STA717 GERMAN AD

737-57-1210 R3 PARA (E) DETAILED INSPECTION WINGS - CENTER WING BOX -FLOOR BEAM INSPECTION, MODIFICATION AND REPAIR(SUPERSEDED BY SB 737-57-1210 R4) SERVICE BULLETIN FOR CRACKS IN THE FLOOR BEAM

737-57-1210 R4 WINGS - CENTER WING BOX - FLOOR BEAM INSPECTION,MODIFICATION AND REPAIR SERVICE BULLETIN

Task Relations


Model: BOEING 737-300/400/500


2008-05-06 DETECT AND CORRECT FATIGUE CRACKING OF THE UPPERAND LOWER CHORDS AND WEB OF THE LONGITUDINALFLOOR BEAMS

ACD (TWO WAY) TO

737-57-1296 R1 WINGS - CENTER WING BOX - LONGITUDINAL FLOOR BEAMSBETWEEN BODY STATION 656 AND BODY STATION 727 -INSPECTION, REPAIR AND PREVENTIVE MODIFICATIONSERVICE BULLETIN

D-2008-148 R1 WINGS - CENTER WING BOX - LONGITUDINAL FLOOR BEAMWEB / UPPER CORD / LOWER CORD - INSPECTION / REPAIRGERMAN AD

2008-06-29 DETECT AND CORRECT LOOSE OR MISSING PARTS FROMTHE MAIN SLAT TRACK DOWNSTOP ASSEMBLIES(SUPERSEDED BY FAA AD 2013-15-14)

ACD (TWO WAY) TO

737-57A1301 R2 WINGS - FLIGHT SURFACES - LEADING EDGE SLATS - MAINTRACK DOWNSTOP ASSEMBLY INSPECTION ANDMODIFICATION (SUPERSEDED BY SB 737-57A1301 R3)SERVICE BULLETIN

737-57A1301 WINGS - FLIGHT SURFACES - LEADING EDGE SLATS - MAINTRACK DOWNSTOP ASSEMBLY INSPECTION SERVICEBULLETIN

2008-08-10 DETECT AND CORRECT OUTBOARD STABILIZING FITTINGAND STRESS CORROSION CRACKING OF THE BOLTSATTACHING THE FITTING TO THE WING REAR SPAR

PRIMARY TO

2008-08-10 PARA (G) ACCOMPLISH DETECT AND CORRECT OUTBOARDSTABILIZING FITTING AND STRESS CORROSION CRACKINGOF THE BOLTS ATTACHING THE FITTING TO THE WINGREAR SPAR REPLACEMENT/REPETITIVE INSPECTIONS

2008-08-10 PARA (L) ACCOMPLISH DETECT AND CORRECT OUTBOARDSTABILIZING FITTING AND STRESS CORROSION CRACKINGOF THE BOLTS ATTACHING THE FITTING TO THE WINGREAR SPAR TORQUE CHECK (GROUPS 1 THROUGH 5)

2008-08-10 PARA (I) ACCOMPLISH DETECT AND CORRECT OUTBOARDSTABILIZING FITTING AND STRESS CORROSION CRACKINGOF THE BOLTS ATTACHING THE FITTING TO THE WINGREAR SPAR GENERAL VISUAL INSPECTION (AIRPLANESIDENTIFIED AS GROUP 9)

2008-08-10 PARA (H) ACCOMPLISH DETECT AND CORRECT OUTBOARDSTABILIZING FITTING AND STRESS CORROSION CRACKINGOF THE BOLTS ATTACHING THE FITTING TO THE WINGREAR SPAR ALTERNATIVE INSPECTION

2008-08-10 DETECT AND CORRECT OUTBOARD STABILIZING FITTINGAND STRESS CORROSION CRACKING OF THE BOLTSATTACHING THE FITTING TO THE WING REAR SPAR

ACD (TWO WAY) TO

Task Relations


Model: BOEING 737-300/400/500


737-57A1266 WINGS - ATTACH FITTINGS - LANDING GEAR ATTACHFITTINGS, MLG BEAM OUTBOARD STABLIZING FITTINGREPLACEMENT SERVICE BULLETIN

D-2008-181 R1 ¿U¿ERER STABILIZING-FITTING UNDBEFESTIGUNGSBOLZEN AM TRAGFL¿CHENHINTERHOLMZUR AUFNAHME DER HYDRAULISCHENHAUPTFAHRWERK-EINFAHRZYLINDER - AUSWECHSLUNG /INSPEKTIONEN GERMAN AD

737-57A1266 R1 WINGS - ATTACH FITTINGS - LANDING GEAR ATTACHFITTINGS, MLG BEAM OUTBOARD STABILIZING FITTINGREPLACEMENT SERVICE BULLETIN

2008-09-13 MAINTAIN THE CONTINUED STRUCTURAL INTEGRITY OFTHE ENTIRE FLEET OF MODEL 737-300, -400, AND -500SERIES AIRPLANES.

PRIMARY TO

2008-09-13 PARA (H) ACCOMPLISH MAINTAIN THE CONTINUED STRUCTURALINTEGRITY OF THE ENTIRE FLEET OF MODEL 737-300, -400,AND -500 SERIES AIRPLANES. INITIAL INSPECTIONS

2008-09-13 PARA (I) ACCOMPLISH MAINTAIN THE CONTINUED STRUCTURALINTEGRITY OF THE ENTIRE FLEET OF MODEL 737-300, -400,AND -500 SERIES AIRPLANES. INSPECTION (FOR ANY SSI THAT HAS BEEN REPAIRED ORALTERED BEFORE THE EFFECTIVE DATE OF THIS AD)

2008-09-13 PARA (G) REVISE MAINTAIN THE CONTINUED STRUCTURALINTEGRITY OF THE ENTIRE FLEET OF MODEL 737-300, -400,AND -500 SERIES AIRPLANES. FAA-APPROVED MAINTENANCE INSPECTION PROGRAM

2008-09-13 MAINTAIN THE CONTINUED STRUCTURAL INTEGRITY OFTHE ENTIRE FLEET OF MODEL 737-300, -400, AND -500SERIES AIRPLANES.

ACD (TWO WAY) TO

737-52A1153 DOORS - AFT CARGO - CROSS BEAM E, ADJACENT LOWERCORNER FRAMES AND REINFORCING ANGLES -INSPECTION, REPAIR AND MODIFICATION SERVICEBULLETIN


737-52A1079 R7 DOORS - AFT CARGO - FRAME AND BEAM INSPECTION,REPAIR AND MODIFICATION SERVICE BULLETIN

737-52-1154 DOORS - CARGO COMPARTMENT DOORS - AFT CARGODOOR - CROSS BEAM D INSPECTION, REPAIR ANDPREVENTIVE MODIFICATION SERVICE BULLETIN

Task Relations


Model: BOEING 737-300/400/500



737-53A1329 FUSELAGE - SKIN - FORWARD ENTRY DOORWAY - LOWERCORNERS - INSPECTION AND REPAIR SERVICE BULLETIN

2008-09-15 TO DETECT AND CORRECT CRACKING IN THE VINYLINTERLAYER OR DAMAGE TO THE STRUCTURAL INNERGLASS PANES OF THE FLIGHT DECK NO. 2, NO. 4, AND NO. 5WINDOWS

ACD (TWO WAY) TO

D-2008-202 R1 COCKPITVERGLASUNG - SEITENFENSTER NR. 2 UNDOBERFENSTER NR. 4 UND NR. 5 - INSPEKTION GERMAN AD

2008-10-09 R1 PREVENT THE POTENTIAL FOR IGNITION SOURCES INSIDEFUEL TANKS

PRIMARY TO2008-10-09 R1 PARA(G) REVISE PREVENT THE POTENTIAL FOR IGNITION SOURCES

INSIDE FUEL TANKS FAA-APPROVED MAINTENANCEPROGRAM

2008-10-09 R1 PARA(H) ACCOMPLISH PREVENT THE POTENTIAL FOR IGNITIONSOURCES INSIDE FUEL TANKS INITIAL INSPECTION ANDREPAIR (28-AWL-03)

2008-11-04 DETECT AND CORRECT CRACKING IN THE SKIN,BEARSTRAP, AND/OR FRAME OUTER CHORD IN THE HINGECUTOUT AREAS OF THE FORWARD ENTRY AND FORWARDGALLEY SERVICE DOORWAYS

ACD (TWO WAY) TO

D-2008-227 R1 RUMPFAUSSCHNITTE F¿R DIE T¿RSCHARNIERE DERVORDEREN PASSAGIERT¿R/SERVICET¿R - INSPEKTIONGERMAN AD

737-53A1200 R2 FUSELAGE - STRUCTURE AROUND OPENINGS - FORWARDENTRY AND FORWARD GALLEY SERVICE DOORWAY UPPERAND LOWER HINGE CUTOUT - INSPECTION SERVICEBULLETIN

2008-13-12 DETECT AND CORRECT FATIGUE CRACKING OF THE UPPERFRAME TO SIDE FRAME SPLICE OF THE FUSELAGE

ACD (TWO WAY) TO737-53A1261 FUSELAGE - FRAMES AND BULKHEADS - UPPER FRAME TO

SIDE FRAME SPLICE - INSPECTION, REPAIR AND / ORMODIFICATION SERVICE BULLETIN

2008-13-12 R1 DETECT AND CORRECT FATIGUE CRACKING OF THE UPPERFRAME TO SIDE FRAME SPLICE OF THE FUSELAGE

ACD (TWO WAY) TO737-53A1261 FUSELAGE - FRAMES AND BULKHEADS - UPPER FRAME TO

SIDE FRAME SPLICE - INSPECTION, REPAIR AND / ORMODIFICATION SERVICE BULLETIN

2008-13-25 PREVENT FATIGUE CRACKING IN THE WEB PANEL OF THEMAIN WHEEL WELL PRESSURE DECK

ACD (TWO WAY) TO737-57-1289 WINGS - CENTER WING BOX - MAIN WHEEL WELL

PRESSURE DECK - WEB INSPECTION SERVICE BULLETIN

Task Relations


Model: BOEING 737-300/400/500


2008-17-03 DETECT AND CORRECT CRACKS FOUND AT THE CUTOUT INTHE WEB OF BODY STATION FRAME 303.9 INBOARD OFSTRINGER 16L

ACD (TWO WAY) TO

737-53A1197 FUSELAGE - BONDED SKIN DOUBLERS (TEAR STRAPS) -DELAMINATION INSPECTION AND REPAIR SERVICEBULLETIN

737-53A1188 R2 FUSELAGE - BODY STATION 303.9 FRAME - WEB CRACKS ATHOLES FOR DOOR STOP INTERCOSTAL STRAP ATSTRINGERS 15 AND 16 LEFT - PREVENTIVE CHANGE ANDREPAIR SERVICE BULLETIN

2008-17-13 PREVENT A WATER LEAK INTO THE FLIGHT DECK CEILING ACD (TWO WAY) TO737-38A1054 R1 WATER/WASTE - PASSENGER WATER SYSTEM, LAVATORY

A STRAIGHT TO 90 DEGREE HOSE ASSEMBLYREPLACEMENT SERVICE BULLETIN

2008-23-09 ENSURE THAT INSULATION BLANKETS CONSTRUCTED OFAN-26 ARE REMOVED FROM THE FUSELAGE

ACD (TWO WAY) TO737-25-1572 SERVICE BULLETIN

2008-24-05 PREVENT FAILURE OF THE WINDSHIELD WIPERS IN WETWEATHER

ACD (TWO WAY) TO737-30A1059 R2 ICE AND RAIN PROTECTION - WINDSHIELD WIPER SYSTEM -

CHANGE THE WINDSHIELD WIPER MOTOR SERVICEBULLETIN

2009-04-15 DETECT AND CORRECT MULTIPLE ADJACENT CRACKEDSTRINGER TIE CLIPS AND DAMAGED SKIN AND FRAMES

PRIMARY TO2009-04-15 PARA (G) ACCOMPLISH DETECT AND CORRECT MULTIPLE ADJACENT

CRACKED STRINGER TIE CLIPS AND DAMAGED SKIN ANDFRAMES INSPECTION B

2009-04-15 PARA (F) ACCOMPLISH DETECT AND CORRECT MULTIPLE ADJACENTCRACKED STRINGER TIE CLIPS AND DAMAGED SKIN ANDFRAMES INSPECTION A

2009-04-15 PARA (J) ACCOMPLISH DETECT AND CORRECT MULTIPLE ADJACENTCRACKED STRINGER TIE CLIPS AND DAMAGED SKIN ANDFRAMES

2009-04-15 DETECT AND CORRECT MULTIPLE ADJACENT CRACKEDSTRINGER TIE CLIPS AND DAMAGED SKIN AND FRAMES

ACD (TWO WAY) TO737-53-1268 FUSELAGE - STRINGER TIE CLIPS - STA 360 TO STA 907,

S-10L TO S-10R, INSPECTION AND REPLACEMENT SERVICEBULLETIN

2009-07-11 PREVENT DISCREPANCIES OF THE FUSELAGE SKIN

PRIMARY TO

Task Relations


Model: BOEING 737-300/400/500


2009-07-11 PARA (F) ACCOMPLISH PREVENT DISCREPANCIES OF THEFUSELAGE SKIN A DETAILED INSPECTION FOR DISCREPANCIES (WEAR ORCRACKING) OF THE FUSELAGE SKIN UNDER THE DORSALFIN ASSEMBLY BY DOING ALL THE ACTIONS SPECIFIED INBOEING MESSAGE NUMBER 1-QXO35

2009-07-11 PARA (G) REPAIR PREVENT DISCREPANCIES OF THE FUSELAGESKIN ANY DISCREPANCY (WEAR OR CRACKING) FOUND DURINGANY INSPECTION

2009-07-11 PARA (J) ACCOMPLISH PREVENT DISCREPANCIES OF THEFUSELAGE SKIN DETAILED INSPECTION FOR ANY CHAFING (ABRASION) ORCRACK IN THE FUSELAGE SKIN OF THE DORSAL FINLANDING AND ABRASION RESISTANT COATING, DAMAGE TODORSAL FIN SEALS, ATTACH CLIP, AND SEAL RETAINERS

2009-07-11 PARA (F) ACCOMPLISH PREVENT DISCREPANCIES OF THEFUSELAGE SKIN A DETAILED INSPECTION FOR DISCREPANCIES (WEAR ORCRACKING) OF THE FUSELAGE SKIN UNDER THE DORSALFIN ASSEMBLY BY DOING ALL THE ACTIONS SPECIFIED INBOEING MESSAGE NUMBER 1-QXO35

ACD (TWO WAY) TO

737-55-1057 R1 VERTICAL STABILIZER - INSPECTION OF FUSELAGE SKINFOR WEAR AND DORSAL FIN ASSEMBLY PREVENTIVEMODIFICATION SERVICE BULLETIN

2009-07-11 PARA (J) ACCOMPLISH PREVENT DISCREPANCIES OF THEFUSELAGE SKIN DETAILED INSPECTION FOR ANY CHAFING (ABRASION) ORCRACK IN THE FUSELAGE SKIN OF THE DORSAL FINLANDING AND ABRASION RESISTANT COATING, DAMAGE TODORSAL FIN SEALS, ATTACH CLIP, AND SEAL RETAINERS

ACD (TWO WAY) TO

737-53A1266 FUSELAGE - SKIN - CROWN SKIN INSPECTION AND REPAIR(BS857 TO BS1006) AND DORSAL FIN NOSE CAPMODIFICATION (BS 860 TO BS 887) SERVICE BULLETIN

2009-09-06 DETECT AND CORRECT FATIGUE CRACKING OF THEBACKUP INTERCOSTALS AND UPPER SILL WEB OF THEFORWARD AIRSTAIR DOORWAY

ACD (TWO WAY) TO

737-53A1269 FUSELAGE - STRUCTURE AROUND OPENINGS - FORWARDAIRSTAIR DOOR CUTOUT - UPPER SILL WEB ANDINTERCOSTALS INSPECTION AND MODIFICATION SERVICEBULLETIN

2009-09-07 DETECT AND CORRECT BROKEN RETRACT ACTUATORBEAMS OF THE MLG

ACD (TWO WAY) TO737-32A1355 R2 LANDING GEAR - MAIN GEAR EXTENSION AND RETRACTION

- RETRACT ACTUATOR BEAM INSPECTION AND REWORKSERVICE BULLETIN

Task Relations


Model: BOEING 737-300/400/500


2009-12-05 PREVENT LOSS OF ALL ATTITUDE INDICATIONS FROM ACD (TWO WAY) TO737-21A1156 R3 AIR CONDITIONING- EQUIPMENT COOLING SYSTEM -

ELECTRONIC FLIGHT INSTRUMENT SYSTEM COOLINGSUPPLY OFF LIGHT WIRING CHANGE SERVICE BULLETIN

737-21A1156 R2 AIR CONDITIONING- EQUIPMENT COOLING SYSTEM -ELECTRONIC FLIGHT INSTRUMENT SYSTEM COOLINGSUPPLY OFF LIGHT WIRING CHANGE (SUPERSEDED BY SB737-21A1156 R3) SERVICE BULLETIN

2009-12-06 ENSURE THAT THE FLIGHTCREW IS ABLE TO TURN OFFELECTRICAL POWER TO IFE SYSTEMS AND OTHERNON-ESSENTIAL ELECTRICAL SYSTEMS THROUGH ASWITCH IN THE FLIGHT COMPARTMENT

ACD (TWO WAY) TO

737-24-1145 ELECTRICAL POWER - ELECTRICAL LOAD DISTRIBUTION -INSTALLATION OF THE INFLIGHT ENTERTAINMENT SYSTEMCIRCUIT BREAKER, RELAYS AND WIRING SERVICEBULLETIN

2009-14-04 PREVENT CORROSION OF THE ELECTRICAL CONNECTORSOF THE WING REAR SPARS

PRIMARY TO2009-14-04 PARA (F) ACCOMPLISH PREVENT CORROSION OF THE ELECTRICAL

CONNECTORS OF THE WING REAR SPARS DEACTIVATINGOR MODIFYING THE OUTBOARD LANDING LIGHTS (737-300,-400, AND -500 SERIES)

2009-14-04 PARA (G) ACCOMPLISH PREVENT CORROSION OF THE ELECTRICALCONNECTORS OF THE WING REAR SPARS INSPECTIONAND REPLACEMENTS

2009-14-04 PREVENT CORROSION OF THE ELECTRICAL CONNECTORSOF THE WING REAR SPARS

ACD (TWO WAY) TO737-28-1241 R2 FUEL - ENGINE FUEL SHUTOFF VALVE - WIRE BUNDLE

REPLACEMENT W802 AND W804 AND INSPECTION OFGROMMETS AND FAIRLEADS IN THE ELECTRICAL JUNCTIONBOXES IN THE MAIN WHEEL WELL SERVICE BULLETIN

D-2009-213 R1 LANDING LIGHTS WIRING / FUEL SHUTOFF VALVES WIRING -INSPECTION / MODIFICATION / REPLACEMENT GERMAN AD

737-33A1140 R1 LIGHTS - OUTBOARD LANDING LIGHTS - ISOLATE OR ADDNEW WIRES SERVICE BULLETIN

2009-21-01 DETECT AND CORRECT CRACKING IN THE AFT FUSELAGESKIN ALONG THE LONGITUDINAL EDGES OF THE BONDEDSKIN DOUBLER

ACD (TWO WAY) TO

737-53-1168 R3 FUSELAGE - AFT SKIN - INSPECTION, MODIFICATION ANDREPLACEMENT SERVICE BULLETIN

737-53-1187 R2 FUSELAGE - AFT SKIN - INSPECTION, MODIFICATION ANDREPLACEMENT SERVICE BULLETIN

Task Relations


Model: BOEING 737-300/400/500


2009-23-10 DETECT AND CORRECT CORROSION OF THE CARRIAGESPINDLE(SUPERSEDED BY AD 2011-04-10)

ACD (TWO WAY) TO

737-57A1304 R1 WINGS - TRAILING EDGE FLAPS - OUTBOARD FLAP,CARRIAGE SPINDLE- INSPECTION FOR CORROSIONSERVICE BULLETIN

2009-26-03 PREVENT A STANDBY STATIC INVERTER FROMOVERHEATING

ACD (TWO WAY) TO737-24A1166 R4 ELECTRICAL POWER - STANDBY POWER GENERATION -

REMOVAL AND REPLACEMENT OF THE STATIC INVERTERMODULE SERVICE BULLETIN

2010-01-03 QUANTITY OF HEAVILY CONTAMINATED HALON 1211 (BCF)TO FIRE FIGHTING ENTERPRISES (FFE)

ACD (TWO WAY) TO2009-0251-E FIRE PROTECTION - PORTABLE FIRE EXTINGUISHERS -

IDENTIFICATION / REPLACEMENT EASA AIRWORTHINESSDIRECTIVE

2009-0262 HALON 1211 FIRE EXTINGUISHERS - IDENTIFICATION /REPLACEMENT (SUPERSEDED BY AD 2009-0262 R1) EASAAIRWORTHINESS DIRECTIVE

2010-01-09 TO DETECT AND CORRECT FATIGUE CRACKING OF THEFUSELAGE SKIN PANELS AT THE CHEM-MILLED STEPS

ACD (TWO WAY) TO737-53A1301 R2 FUSELAGE - SKIN - CRACKS AT CHEM-MILLED STEPS IN

CROWN SKINS AT SPECIFIED LOCATIONS - INSPECTIONSERVICE BULLETIN

737-53-1305 FUSELAGE - SKIN - CHEM-MILLED STEPS IN CROWN SKINSWITH 20 INCH TEAR STRAP BAYS AT SPECIFIED LOCATIONS- INSPECTION AND MODIFICATION (SUPERSEDED BY SB737-53-1305 R1) SERVICE BULLETIN

2010-05-13 TO PREVENT RAPID DECOMPRESSION OF THE AIRPLANEDUE TO FATIGUE CRACKS RESULTING FROM SCRIBE LINESON PRESSURIZED FUSELAGE STRUCTURE

PRIMARY TO

2010-05-13 PARA (V) REPORT TO PREVENT RAPID DECOMPRESSION OF THEAIRPLANE DUE TO FATIGUE CRACKS RESULTING FROMSCRIBE LINES ON PRESSURIZED FUSELAGE STRUCTURE

2010-05-13 TO PREVENT RAPID DECOMPRESSION OF THE AIRPLANEDUE TO FATIGUE CRACKS RESULTING FROM SCRIBE LINESON PRESSURIZED FUSELAGE STRUCTURE

ACD (TWO WAY) TO

737-53A1262 R3 FUSELAGE - SKIN - INSPECTIONS OF THE FUSELAGE SKINFOR SCRIBE LINES SERVICE BULLETIN

737-53A1262 R3 ZONE 1B INSPECTION FUSELAGE - SKIN - INSPECTIONS OF THEFUSELAGE SKIN FOR SCRIBE LINES SERVICE BULLETIN OFTHE FUSELAGE SKIN FOR SCRIBE LINES

Task Relations


Model: BOEING 737-300/400/500


737-53A1262 R3 ZONE 5 INSPECTION FUSELAGE - SKIN - INSPECTIONS OF THEFUSELAGE SKIN FOR SCRIBE LINES SERVICE BULLETIN OFTHE FUSELAGE SKIN FOR SCRIBE LINES



2010-14-06 TO PREVENT THE IN-LINE FLOW INDICATORS OF THEPASSENGER OXYGEN MASKS FROM FRACTURING ANDSEPARATING

PRIMARY TO

2010-14-06 PARA (G) GENERAL VISUAL INSPECTION TO PREVENT THE IN-LINEFLOW INDICATORS OF THE PASSENGER OXYGEN MASKSFROM FRACTURING AND SEPARATING TO DETERMINE THEMANUFACTURER AND MANUFACTURE DATE OF THEOXYGEN MASKS IN THE PASSENGER SERVICE UNIT ANDTHE LAVATORY AND ATTENDANT BOX ASSEMBLIES

2010-14-06 PARA (H) GENERAL VISUAL INSPECTION TO PREVENT THE IN-LINEFLOW INDICATORS OF THE PASSENGER OXYGEN MASKSFROM FRACTURING AND SEPARATING TO DETERMINE THEMANUFACTURER AND MANUFACTURE DATE OF THEOXYGEN MASKS IN THE PASSENGER SERVICE UNIT ANDTHE LAVATORY AND ATTENDANT BOX ASSEMBLIES

2010-14-06 TO PREVENT THE IN-LINE FLOW INDICATORS OF THEPASSENGER OXYGEN MASKS FROM FRACTURING ANDSEPARATING

ACD (TWO WAY) TO

737-35-1099 R1 OXYGEN - PASSENGER OXYGEN SYSTEM - OXYGEN MASKASSEMBLY INSPECTION AND MODIFICATION SERVICEBULLETIN

2010-15-08 TO DETECT AND CORRECT CRACKED, CORRODED, ORFRACTURED CARRIAGE SPINDLES

PRIMARY TO2010-15-08 PARA (O) DETAILED INSPECTION TO DETECT AND CORRECT

CRACKED, CORRODED, OR FRACTURED CARRIAGESPINDLES FOR CORROSION, PITTING, AND CRACKING OFTHE CARRIAGE SPINDLE, THE MAGNETIC PARTICLEINSPECTION FOR CRACKING OF THE CARRIAGE SPINDLE

2010-15-08 PARA (Q) REPLACE TO DETECT AND CORRECT CRACKED,CORRODED, OR FRACTURED CARRIAGE SPINDLES THECARRIAGE SPINDLE WITH A NEW OR DOCUMENTED (FORWHICH THE SERVICE LIFE, IN FLIGHT CYCLES, IS KNOWN)CARRIAGE SPINDLE

Task Relations


Model: BOEING 737-300/400/500


2010-15-08 PARA (H) PERFORM TO DETECT AND CORRECT CRACKED,CORRODED, OR FRACTURED CARRIAGE SPINDLES A GAPCHECK OF THE INBOARD AND OUTBOARD CARRIAGE OFTHE LEFT AND RIGHT OUTBOARD MID-FLAPS (2003-24-08)

2010-15-08 PARA (J) NDT AND VISUAL CHECK TO DETECT AND CORRECTCRACKED, CORRODED, OR FRACTURED CARRIAGESPINDLES FOR EACH CARRIAGE SPINDLE OF THE LEFTAND RIGHT OUTBOARD MID-FLAPS (2003-24-08)


ACD (TWO WAY) TO737-57A1277 R3 WINGS - TRAILING EDGE FLAPS - OUTBOARD FLAP

CARRIAGE SPINDLE - INSPECTION FOR CRACKING SERVICEBULLETIN

737-57A1218 R6 PARA E2

REPLACE WINGS - TRAILING EDGE FLAPS - OUTBOARDFLAP CARRIAGE SPINDLE REPAIR AND LIFE LIMITINGSERVICE BULLETIN OUTBOARD FLAP (INBOARD CARRIAGEWBL 254 AND OUTBOARD CARRIAGE WBL 355)

737-57A1218 R6 PARA E1

PERFORM WINGS - TRAILING EDGE FLAPS - OUTBOARDFLAP CARRIAGE SPINDLE REPAIR AND LIFE LIMITINGSERVICE BULLETIN INITIAL INSPECTION AND OVERHAULOF TRAILING EDGE FLAPS - OUTBOARD FLAP CARRIAGESPINDLE

737-57A1218 R6 WINGS - TRAILING EDGE FLAPS - OUTBOARD FLAPCARRIAGE SPINDLE REPAIR AND LIFE LIMITING SERVICEBULLETIN

D-2002-371 R3 M¿GLICHER VERLUST DER STEUERBARKEIT DESLUFTFAHRZEUGS BEI DER LANDUNG DURCH ASYMETRISCHAUSGEFAHRENE LANDEKLAPPEN AUFGRUNDGEBROCHENER ANTRIEBSSPINDELN. GERMAN AD

2010-16-06 TO PREVENT INADVERTENT ELECTRICAL CURRENT, WHICHCAN CAUSE THE LOW-PRESSURE FLEX-HOSES OF THECREW OXYGEN SYSTEM TO MELT OR BURN, RESULTING INOXYGEN SYSTEM LEAKAGE AND SMOKE OR FIRE

PRIMARY TO

2010-16-06 PARA (G) INSPECTION TO PREVENT INADVERTENT ELECTRICALCURRENT, WHICH CAN CAUSE THE LOW-PRESSUREFLEX-HOSES OF THE CREW OXYGEN SYSTEM TO MELT ORBURN, RESULTING IN OXYGEN SYSTEM LEAKAGE ANDSMOKE OR FIRE TO DETERMINE WHETHER ANYLOW-PRESSURE FLEX-HOSE OF THE CREW OXYGENSYSTEM INSTALLED UNDER THE OXYGEN MASK STOWAGEBOX IN THE FLIGHT DECK HAS A PART NUMBER IDENTIFIEDIN TABLE 1 OR TABLE 2

Task Relations


Model: BOEING 737-300/400/500


2010-16-06 PARA (H) DO NOT INSTALL TO PREVENT INADVERTENT ELECTRICALCURRENT, WHICH CAN CAUSE THE LOW-PRESSUREFLEX-HOSES OF THE CREW OXYGEN SYSTEM TO MELT ORBURN, RESULTING IN OXYGEN SYSTEM LEAKAGE ANDSMOKE OR FIRE A CREW OXYGEN HOSE WITH A PARTNUMBER IDENTIFIED IN TABLE 1 OR TABLE 2 OF THIS AD, ASAPPLICABLE, ON ANY AIRPLANE

2010-16-06 TO PREVENT INADVERTENT ELECTRICAL CURRENT, WHICHCAN CAUSE THE LOW-PRESSURE FLEX-HOSES OF THECREW OXYGEN SYSTEM TO MELT OR BURN, RESULTING INOXYGEN SYSTEM LEAKAGE AND SMOKE OR FIRE

ACD (TWO WAY) TO

D-2010-267 R1 M¿GLICHER AUSFALL DES''FLIGHTCREW/SUPERNUMERARY OXYGEN SYSTEMS''DURCH LEITUNGSSCH¿DEN AN FLEXIBLENNIEDERDRUCKSCHLAUCHLEITUNGEN AUFGRUND EINESELEKTRISCHEN KURZSCHLUSSES IM ''AUDIO SELECTPANEL'' GERMAN AD

2010-16-06 PARA (G) INSPECTION TO PREVENT INADVERTENT ELECTRICALCURRENT, WHICH CAN CAUSE THE LOW-PRESSUREFLEX-HOSES OF THE CREW OXYGEN SYSTEM TO MELT ORBURN, RESULTING IN OXYGEN SYSTEM LEAKAGE ANDSMOKE OR FIRE TO DETERMINE WHETHER ANYLOW-PRESSURE FLEX-HOSE OF THE CREW OXYGENSYSTEM INSTALLED UNDER THE OXYGEN MASK STOWAGEBOX IN THE FLIGHT DECK HAS A PART NUMBER IDENTIFIEDIN TABLE 1 OR TABLE 2

ACD (TWO WAY) TO

737-35A1053 R2 OXYGEN - CREW OXYGEN - CREW OXYGEN SYSTEM LOWPRESSURE FLEX HOSE REPLACEMENT SERVICE BULLETIN

2010-25-06 TO DETECT AND CORRECT FATIGUE CRACKING OFCERTAIN FUSELAGE FRAMES AND STUB BEAMS ANDPOSSIBLE SEVERED FRAMES

PRIMARY TO

2010-25-06 PARA(G)(1)(2)

DETAILED INSPECTION TO DETECT AND CORRECTFATIGUE CRACKING OF CERTAIN FUSELAGE FRAMES ANDSTUB BEAMS AND POSSIBLE SEVERED FRAMES OR HIGHFREQUENCY EDDY CURRENT (HFEC) INSPECTION FORCRACKING OF BODY STATION (BS) 616 AND BS 639 FRAMEWEBS, INNER CHORD, AND OUTER CHORD, AND THE STUBBEAMS FOR AIRPLANES ON WHICH NO INSPECTION HASBEEN DONE

2010-25-06 PARA (G)(3) RE-INSPECT TO DETECT AND CORRECT FATIGUECRACKING OF CERTAIN FUSELAGE FRAMES AND STUBBEAMS AND POSSIBLE SEVERED FRAMES FOR AIRPLANESON WHICH A DETAILED OR HFEC INSPECTION HAS BEENDONE

Task Relations


Model: BOEING 737-300/400/500


2010-25-06 PARA (H) DETAILED INSPECTION TO DETECT AND CORRECTFATIGUE CRACKING OF CERTAIN FUSELAGE FRAMES ANDSTUB BEAMS AND POSSIBLE SEVERED FRAMES OR HFECINSPECTION FOR CRACKING OF THE REPLACEMENT FRAMESECTION (FRAME WEBS, INNER CHORD, AND OUTERCHORD)

2010-25-06 TO DETECT AND CORRECT FATIGUE CRACKING OFCERTAIN FUSELAGE FRAMES AND STUB BEAMS ANDPOSSIBLE SEVERED FRAMES

ACD (TWO WAY) TO

737-53A1254 R2 FUSELAGE - BODY FRAME AND OVERWING STUB BEAMINSPECTION AND REPAIR - BODY STATIONS 597 TO 639SERVICE BULLETIN

D-2011-021 R1 FUSELAGE - BODY FRAME AND STUB BEAM - INSPECTION /REPAIR (BS616 AND BS639) GERMAN AD

2011-0090 OXYGEN MASK REGULATOR INFLATABLE HARNESS -IDENTIFICATION/REPLACEMENT EASA

PRIMARY TO2011-0090 PARA (1) IDENTIFY OXYGEN MASK REGULATOR INFLATABLE

HARNESS - IDENTIFICATION/REPLACEMENT EASA P/N ANDBATCH NUMBER OF THE FLIGHT CREW OXYGEN MASKREGULATOR INFLATABLE HARNES/REPLACE AS NEEDED

2011-0090 PARA (3) DO NOT INSTALL OXYGEN MASK REGULATOR INFLATABLEHARNESS - IDENTIFICATION/REPLACEMENT EASA A FLIGHTCREW OXYGEN MASK REGULATOR UNLESS IT HAS BEENDETERMINED THAT THE P/N AND BATCH NUMBER OF THEINFLATABLE HARNESS FITTED IS NOT LISTED

2011-0098 EQUIPMENT & FURNISHINGS - PASSENGER SEAT -REPLACEMENT EASA AIRWORTHINESS DIRECTIVE

PRIMARY TO2011-0098 PARA (3) PERFORM EQUIPMENT & FURNISHINGS - PASSENGER

SEAT - REPLACEMENT EASA AIRWORTHINESS DIRECTIVE DYNAMIC AND/OR STATIC TESTING ON PASSENGER SEATSFOR AEROPLANES REQUIRED TO MEET CS/JAR/FAR 25.562REQUIREMENTS (EITHER BY THEIR ORIGINALCERTIFICATION BASES OR POST TC MODIFICATIONS)

2011-0098 PARA (1) PERFORM EQUIPMENT & FURNISHINGS - PASSENGERSEAT - REPLACEMENT EASA AIRWORTHINESS DIRECTIVE ONE OF THE PARAGRAPHS (1.1), (1.2), (1.3)

2011-0098 PARA (2) PERFORM EQUIPMENT & FURNISHINGS - PASSENGERSEAT - REPLACEMENT EASA AIRWORTHINESS DIRECTIVE TESTING TO DETERMINE WHETHER THE SEAT CUSHIONSCOMPLY WITH CS/JAR/FAR 25.853(C) (I.E. APPENDIX F PARTII)

Task Relations


Model: BOEING 737-300/400/500


2011-0098 PARA (4) PERFORM EQUIPMENT & FURNISHINGS - PASSENGERSEAT - REPLACEMENT EASA AIRWORTHINESS DIRECTIVE STATIC TESTING ON PASSENGER SEATS FOR AEROPLANESNOT REQUIRED TO MEET ANY CS/JAR/FAR 25.562REQUIREMENTS (EITHER BY THEIR ORIGINALCERTIFICATION BASES OR POST TC MODIFICATIONS)

2011-01-09 PREVENT PBE UNITS FROM IGNITING PRIMARY TO2011-01-09 PARA (G) INSPECT PREVENT PBE UNITS FROM IGNITING TO

DETERMINE THE SERIAL NUMBER OF THE PBE UNITSINSTALLED IN THE AIRCRAFT

2011-01-09 PARA (H) DO NOT INSTALL PREVENT PBE UNITS FROM IGNITING APBE UNIT HAVING P/N 119003-11 WITH A SERIAL NUMBERRANGING FROM 003-50730M TO 003-51329M INCLUSIVE

2011-01-12 TO PREVENT DAMAGE OF THE FUSE PINS OF THE INBOARDAND OUTBOARD MIDSPAR FITTINGS OF THE NACELLESTRUT

PRIMARY TO

2011-01-12 PARA (G) DETAILED INSPECTION TO PREVENT DAMAGE OF THEFUSE PINS OF THE INBOARD AND OUTBOARD MIDSPARFITTINGS OF THE NACELLE STRUT FOR DISCREPANCIESOF THE FUSE PINS OF THE INBOARD AND OUTBOARDMIDSPAR FITTINGS OF THE NACELLE STRUT BY DOING ALLTHE ACTIONS, INCLUDING ALL APPLICABLE CORRECTIVEACTIONS

2011-01-12 PARA (H) REPLACE TO PREVENT DAMAGE OF THE FUSE PINS OFTHE INBOARD AND OUTBOARD MIDSPAR FITTINGS OF THENACELLE STRUT ALL MIDSPAR FUSE PINS HAVING PARTNUMBER (P/N) 311A1092-2 WITH A MIDSPAR FUSE PINHAVING P/N 311A1092-3

2011-01-12 TO PREVENT DAMAGE OF THE FUSE PINS OF THE INBOARDAND OUTBOARD MIDSPAR FITTINGS OF THE NACELLESTRUT

ACD (TWO WAY) TO

737-54A1044 R2 NACELLES/PYLONS - NACELLE STRUT - MIDSPAR FUSE PIN -INSPECTION, REPAIR AND REPLACEMENT SERVICEBULLETIN

2011-03-14 TO PREVENT FAILURE OF THE FLIGHTCREW TORECOGNIZE AND REACT PROPERLY TO A VALID CABINALTITUDE WARNING HORN

PRIMARY TO

2011-03-14 PARA (G) INSTALL TO PREVENT FAILURE OF THE FLIGHTCREW TORECOGNIZE AND REACT PROPERLY TO A VALID CABINALTITUDE WARNING HORN TWO WARNING LEVELINDICATOR LIGHTS ON THE P2-2 CENTER INSTRUMENTPANEL IN THE FLIGHT COMPARTMENT

Task Relations


Model: BOEING 737-300/400/500


2011-03-14 PARA (H) ACCOMPLISH TO PREVENT FAILURE OF THE FLIGHTCREWTO RECOGNIZE AND REACT PROPERLY TO A VALID CABINALTITUDE WARNING HORN ACTIVATE THE CABIN ALTITUDEWARNING AND TAKEOFF CONFIGURATION WARNINGLIGHTS

2011-03-14 TO PREVENT FAILURE OF THE FLIGHTCREW TORECOGNIZE AND REACT PROPERLY TO A VALID CABINALTITUDE WARNING HORN

ACD (TWO WAY) TO

737-31A1325 R1 INDICATING / RECORDING SYSTEMS - AURAL WARNINGSYSTEM - INSTALLATION OF THE CABIN ALTITUDEWARNING SYSTEM AND TAKEOFF CONFIGURATIONWARNING SYSTEM LIGHTS SERVICE BULLETIN

2011-03R2 SECURITY CONCERNS WITH THE CHEMICAL OXYGENGENERATORS INSTALLED IN THE LAVATORIES CANADIANAIRWORTHINESS DIRECTIVE

PRIMARY TO

2011-03R2 PART I B SECURITY CONCERNS WITH THE CHEMICAL OXYGENGENERATORS INSTALLED IN THE LAVATORIES CANADIANAIRWORTHINESS DIRECTIVE MODIFY THE AEROPLANEDISPATCH RELEASE PROCEDURES TO NOTIFY THE FLIGHTAND CABIN CREW THAT THE OXYGEN SUPPLY IN THELAVATORIES IS INOPERATIVE

2011-03R2 PART I A 2 A SECURITY CONCERNS WITH THE CHEMICAL OXYGENGENERATORS INSTALLED IN THE LAVATORIES CANADIANAIRWORTHINESS DIRECTIVE REMOVE THE OXYGENMASK(S), CLOSE THE MASK DISPENSER DOORS ANDPLACARD THEM INOPERATIVE

2011-03R2 PART I A 1 SECURITY CONCERNS WITH THE CHEMICAL OXYGENGENERATORS INSTALLED IN THE LAVATORIES CANADIANAIRWORTHINESS DIRECTIVE DISABLE OR REMOVE THECHEMICAL OXYGEN GENERATOR IN ALL LAVATORIES ONBOARD THE AEROPLANE

2011-03R2 PART I A 2 B SECURITY CONCERNS WITH THE CHEMICAL OXYGENGENERATORS INSTALLED IN THE LAVATORIES CANADIANAIRWORTHINESS DIRECTIVE REMOVE RESTOWED MASKSFROM THE DISPENSER

2011-03R2 PART II SECURITY CONCERNS WITH THE CHEMICAL OXYGENGENERATORS INSTALLED IN THE LAVATORIES CANADIANAIRWORTHINESS DIRECTIVE INSTALL A SUPPLEMENTALOXYGEN SYSTEM IN EACH LAVATORY FOR ALL TRANSPORTCATEGORY AEROPLANES

2011-04-10 TO DETECT AND CORRECT CORROSION OF THE CARRIAGESPINDLE (SUPERSEDED BY FAA AD 2012-13-07)

PRIMARY TO

Task Relations


Model: BOEING 737-300/400/500


2011-04-10 PARA (J) REPLACE TO DETECT AND CORRECT CORROSION OF THECARRIAGE SPINDLE (SUPERSEDED BY FAA AD 2012-13-07) ANY HVOF-COATED CARRIAGE SPINDLE HAVING A SERIALNUMBER IDENTIFIED IN TABLE 2 OR TABLE 3 OF APPENDIXA OF BOEING SERVICE BULLETIN 737-57A1304, REVISION 1

2011-04-10 PARA (I) DETAILED INSPECTION TO DETECT AND CORRECTCORROSION OF THE CARRIAGE SPINDLE (SUPERSEDED BYFAA AD 2012-13-07) OF THE SPINDLE FOR CORROSION ANDPOTENTIAL INDICATIONS OF CORROSION OF THECARRIAGE SPINDLE FOR AIRPLANES ON WHICH ACARRIAGE SPINDLE HAVING A SERIAL NUMBER IDENTIFIEDIN TABLE 3 OF APPENDIX A OF BOEING SERVICE BULLETIN737-57A1304, REVISION 1

2011-04-10 PARA (H) DETAILED INSPECTION TO DETECT AND CORRECTCORROSION OF THE CARRIAGE SPINDLE (SUPERSEDED BYFAA AD 2012-13-07) OF THE SPINDLE FOR CORROSION ANDPOTENTIAL INDICATIONS OF CORROSION OF THECARRIAGE SPINDLE, AND DO ALL APPLICABLE RELATEDINVESTIGATIVE AND CORRECTIVE ACTIONS FORAIRPLANES ON WHICH ANY AFFECTED CARRIAGE SPINDLEWAS DETERMINED TO BE INSTALLED

2011-04-10 PARA (G) INSPECT TO DETECT AND CORRECT CORROSION OF THECARRIAGE SPINDLE (SUPERSEDED BY FAA AD 2012-13-07) THE CARRIAGE SUB-ASSEMBLY TO DETERMINE WHETHERAN AFFECTED CARRIAGE SPINDLE WITH A HIGH VELOCITYOXY-FUEL (HVOF) THERMAL COATING IS INSTALLED

2011-04-10 TO DETECT AND CORRECT CORROSION OF THE CARRIAGESPINDLE (SUPERSEDED BY FAA AD 2012-13-07)

ACD (TWO WAY) TO737-57A1304 R1 WINGS - TRAILING EDGE FLAPS - OUTBOARD FLAP,

CARRIAGE SPINDLE- INSPECTION FOR CORROSIONSERVICE BULLETIN

2011-08-51 TO DETECT AND CORRECT CRACKING IN THE LOWER SKINAT THE LOWER ROW OF FASTENERS OF THE LAP JOINT ATSTRINGER S-4L BETWEEN BODY STATION (BS) 664 AND BS727

ACD (TWO WAY) TO

737-53A1319 R1 FUSELAGE - SKIN - CROWN SKIN LAP JOINT - INSPECTIONFOR LOWER ROW CRACKING AT STRINGER S-4, BETWEENBS 360 AND BS 908 SERVICE BULLETIN

2011-08-51-E EXTERNAL EDDY CURRENT INSPECTIONS OF THE LAPJOINT AT STRINGERS S-4R AND S-4L, ALONG THE ENTIRELENGTH FROM BODY STATION (BS) 360 TO BS 908

ACD (TWO WAY) TO

737-53A1319 R1 FUSELAGE - SKIN - CROWN SKIN LAP JOINT - INSPECTIONFOR LOWER ROW CRACKING AT STRINGER S-4, BETWEENBS 360 AND BS 908 SERVICE BULLETIN

2011-12-01 PREVENT ACCELERATED FIRES AND INJURIES TO THEFLIGHTCREW AND PASSENGERS

PRIMARY TO

Task Relations


Model: BOEING 737-300/400/500


2011-12-01 PARA (H) (2) REMOVE PREVENT ACCELERATED FIRES AND INJURIES TOTHE FLIGHTCREW AND PASSENGERS ANY SEATINGSYSTEMS ARE NOT SHOWN TO BE COMPLIANT WITH THEREGULATIONS SPECIFIED IN PARAGRAPH (G)(2)(I) OF THISAD,:14 CFR 25.561(B)(3)(II) AND 14 CFR 25.561(B)(3)(III).

2011-12-01 PARA (H) (1) REMOVE PREVENT ACCELERATED FIRES AND INJURIES TOTHE FLIGHTCREW AND PASSENGERS THENON-COMPLIANT SEATING SYSTEMS FOR PARA (G) (2): 14CFR 25.562(B)(2), AND 14 CFR 25.562(C)(7)

2011-12-01 PARA (G) (4) DETERMINE PREVENT ACCELERATED FIRES AND INJURIESTO THE FLIGHTCREW AND PASSENGERS IF THE SEATBOTTOM CUSHION ASSEMBLY AND SEAT BACK CUSHIONASSEMBLY ARE SHOWN TO BE COMPLIANT WITH 14 CFR25.853(C) FOR KOITO INDUSTRIES, LTD., SEATS APPROVEDUNDER TSO-C39B OR TSO-C39C AND COMPONENTS OFSEATING SYSTEMS APPROVED UNDER TSO-C127A REMOVEAS NEEDED

2011-12-01 PARA (G) (2) DETERMINE PREVENT ACCELERATED FIRES AND INJURIESTO THE FLIGHTCREW AND PASSENGERS IF THE SEATINGSYSTEMS ARE COMPLIANT FOR KOITO INDUSTRIES, LTD.,SEATING SYSTEMS APPROVED UNDER TSO-C127A

2011-12-01 PARA (G) (1) DETERMINE PREVENT ACCELERATED FIRES AND INJURIESTO THE FLIGHTCREW AND PASSENGERS IF THE SEATSARE COMPLIANT WITH 14 CFR 25.561(B)(3)(II) AND 14 CFR25.561(B)(3)(III) FOR KOITO INDUSTRIES, LTD., SEATSAPPROVED UNDER TSO-C39B OR TSO-C39C.

2011-12-01 PARA (G) (3) DETERMINE PREVENT ACCELERATED FIRES AND INJURIESTO THE FLIGHTCREW AND PASSENGERS IF THE SEATINGSYSTEMS ARE COMPLIANT WITH 14 CFR 25.561(B)(3)(II) AND14 CFR 25.561(B)(3)(III) FOR KOITO INDUSTRIES, LTD.,SEATING SYSTEMS APPROVED UNDER TSO-C127A

2011-12-01 PREVENT ACCELERATED FIRES AND INJURIES TO THEFLIGHTCREW AND PASSENGERS

ACD (TWO WAY) TO2011-0098 PARA (4) PERFORM EQUIPMENT & FURNISHINGS - PASSENGER

SEAT - REPLACEMENT EASA AIRWORTHINESS DIRECTIVE STATIC TESTING ON PASSENGER SEATS FOR AEROPLANESNOT REQUIRED TO MEET ANY CS/JAR/FAR 25.562REQUIREMENTS (EITHER BY THEIR ORIGINALCERTIFICATION BASES OR POST TC MODIFICATIONS)

2011-0098 PARA (2) PERFORM EQUIPMENT & FURNISHINGS - PASSENGERSEAT - REPLACEMENT EASA AIRWORTHINESS DIRECTIVE TESTING TO DETERMINE WHETHER THE SEAT CUSHIONSCOMPLY WITH CS/JAR/FAR 25.853(C) (I.E. APPENDIX F PARTII)

Task Relations


Model: BOEING 737-300/400/500


2011-0098 PARA (1) PERFORM EQUIPMENT & FURNISHINGS - PASSENGERSEAT - REPLACEMENT EASA AIRWORTHINESS DIRECTIVE ONE OF THE PARAGRAPHS (1.1), (1.2), (1.3)

2011-0098 EQUIPMENT & FURNISHINGS - PASSENGER SEAT -REPLACEMENT EASA AIRWORTHINESS DIRECTIVE

2011-0098 PARA (3) PERFORM EQUIPMENT & FURNISHINGS - PASSENGERSEAT - REPLACEMENT EASA AIRWORTHINESS DIRECTIVE DYNAMIC AND/OR STATIC TESTING ON PASSENGER SEATSFOR AEROPLANES REQUIRED TO MEET CS/JAR/FAR 25.562REQUIREMENTS (EITHER BY THEIR ORIGINALCERTIFICATION BASES OR POST TC MODIFICATIONS)

2011-12-09 TO PREVENT DAMAGE TO THE FUEL PUMPS CAUSED BYELECTRICAL ARCING

PRIMARY TO2011-12-09 PARA (H) PERFORM TO PREVENT DAMAGE TO THE FUEL PUMPS

CAUSED BY ELECTRICAL ARCING WIRING CHANGES ANDCERTAIN BONDING MEASUREMENTS FOR AIRPLANES ONWHICH BOEING ALERT SERVICE BULLETIN 737-28A1212,DATED JULY 23, 2009, HAS BEEN INCORPORATED AS OFTHE EFFECTIVE DATE OF THIS AD, AND ON WHICH THEM181, M182, AND M183 SUPPLIER RELAY MODULES ARENOT INSTALLED

2011-12-09 PARA (L) REVISE TO PREVENT DAMAGE TO THE FUEL PUMPSCAUSED BY ELECTRICAL ARCING THE MAINTENANCEPROGRAM

2011-12-09 PARA (I) PERFORM TO PREVENT DAMAGE TO THE FUEL PUMPSCAUSED BY ELECTRICAL ARCING CERTAIN BONDINGMEASUREMENTS FOR AIRPLANES ON WHICH BOEINGALERT SERVICE BULLETIN 737-28A1212, DATED JULY 23,2009, HAS BEEN INCORPORATED AS OF THE EFFECTIVEDATE OF THIS AD, AND ON WHICH THE M181, M182, ANDM183 SUPPLIER RELAY MODULES ARE INSTALLED

2011-12-09 PARA (G)(2) MODIFY TO PREVENT DAMAGE TO THE FUEL PUMPSCAUSED BY ELECTRICAL ARCING THE M181, M182, ANDM183 RELAY MODULE ASSEMBLIES, AND DO CERTAINBONDING RESISTANCE MEASUREMENTS TO VERIFY THATCERTAIN BONDING REQUIREMENTS ARE MET FORAIRPLANES WITH THE M181, M182, AND M183 SUPPLIERRELAY MODULES INSTALLED AND ON WHICH BOEINGALERT SERVICE BULLETIN 737-28A1212, DATED JULY 23,2009, HAS NOT BEEN INCORPORATED AS OF THEEFFECTIVE DATE OF THIS AD

Task Relations


Model: BOEING 737-300/400/500


2011-12-09 PARA (G)(1) PERFORM TO PREVENT DAMAGE TO THE FUEL PUMPSCAUSED BY ELECTRICAL ARCING WIRING CHANGES;REPLACE THE FUEL PUMP POWER CONTROL RELAYS FORTHE MAIN, CENTER, AND AUXILIARY TANKS FOR AIRPLANESWITHOUT THE M181, M182, AND M183 SUPPLIER RELAYMODULES INSTALLED AND ON WHICH BOEING ALERTSERVICE BULLETIN 737-28A1212, DATED JULY 23, 2009, HASNOT BEEN INCORPORATED AS OF THE EFFECTIVE DATE OFTHIS AD

2011-12-09 TO PREVENT DAMAGE TO THE FUEL PUMPS CAUSED BYELECTRICAL ARCING

ACD (TWO WAY) TO737-28A1212 R2 FUEL - ENGINE FUEL FEED SYSTEM - FUEL PUMP CONTROL

GROUND FAULT INTERRUPTER (GFI) RELAY INSTALLATIONSERVICE BULLETIN

2011-21-08 TO PREVENT FAILURE OF THE BACKREST LINKS COULDRESULT IN INJURY TO AN OCCUPANT DURING EMERGENCYLANDING CONDITIONS

PRIMARY TO

2011-21-08 PARA (F)(1) GENERAL VISUAL INSPECTION TO PREVENT FAILURE OFTHE BACKREST LINKS COULD RESULT IN INJURY TO ANOCCUPANT DURING EMERGENCY LANDING CONDITIONS OF THE BACKREST LINKS HAVING P/NS 90-000200-104-1AND 90-000200-104-2

2011-21-08 PARA (F)(2) REPLACE TO PREVENT FAILURE OF THE BACKREST LINKSCOULD RESULT IN INJURY TO AN OCCUPANT DURINGEMERGENCY LANDING CONDITIONS BOTH BACKRESTLINKS OF THE AFFECTED SEAT WITH NEW, IMPROVEDBACKREST LINKS HAVING P/NS 90-100200-104-1 AND90-100200-104-2

2011-21-08 PARA (F)(5) REPLACE TO PREVENT FAILURE OF THE BACKREST LINKSCOULD RESULT IN INJURY TO AN OCCUPANT DURINGEMERGENCY LANDING CONDITIONS THE LINKS, P/NS90-000200-104-1 AND 90-000200-104-2, WITH NEW IMPROVEDLINKS, P/NS 90-100200-104-1 AND 90-100200-104-2

2011-23-05 TO DETECT AND CORRECT CRACKING IN THE FUSELAGEFRAMES AND FRAME REINFORCEMENTS

PRIMARY TO2011-23-05 PARA (H) PERFORM TO DETECT AND CORRECT CRACKING IN THE

FUSELAGE FRAMES AND FRAME REINFORCEMENTS ANHFEC HOLE/EDGE INSPECTION FOR CRACKING OF THE1.04-INCH NOMINAL DIAMETER WIRE PENETRATION HOLE INTHE FRAME AND FRAME REINFORCEMENT BETWEEN S-20AND S-21

Task Relations


Model: BOEING 737-300/400/500


2011-23-05 PARA (G) PERFORM TO DETECT AND CORRECT CRACKING IN THEFUSELAGE FRAMES AND FRAME REINFORCEMENTS AHIGH FREQUENCY EDDY CURRENT (HFEC) SURFACE ORHFEC HOLE/EDGE INSPECTION FOR ANY CRACKING OF THE1.04-INCH NOMINAL DIAMETER WIRE PENETRATION HOLE INTHE FORWARD CARGOBAY FRAMES AND FRAME REINFORCEMENTS BETWEENS-20 AND S-21

2011-23-05 PARA (J) ACCOMPLISH TO DETECT AND CORRECT CRACKING IN THEFUSELAGE FRAMES AND FRAME REINFORCEMENTS OPTIONAL TERMINATING ACTION SPECIFIED IN PART 5 OFTHE ACCOMPLISHMENT INSTRUCTIONS OF BOEING ALERTSERVICE BULLETIN 737-53A1279, REVISION 1,

2011-23-05 TO DETECT AND CORRECT CRACKING IN THE FUSELAGEFRAMES AND FRAME REINFORCEMENTS

ACD (TWO WAY) TO737-53A1279 R1 FUSELAGE - FRAMES AND BULKHEADS - FORWARD CARGO

BAY STRINGER 19 TO STRINGER 21 - FRAMES AND FRAMEREINFORCEMENTS - INSPECTION, REPAIR ANDPREVENTATIVE MODIFICATION AT WIRE PENETRATIONHOLE SERVICE BULLETIN


PRIMARY TO2011-24-12 PARA (G) ACCOMPLISH TO DETECT AND CORRECT FATIGUE

CRACKING OF THE FUSELAGE SKIN PANELS AT THECHEM-MILLED STEPS EXTERNAL NON-DESTRUCTIVEINSPECTION (NDI) TO DETECT CRACKS IN THE FUSELAGESKIN ALONG THE CHEM-MILL STEPS AT STRINGERS S-1AND S-2 RIGHT, BETWEEN STATION (STA) 827 AND STA 847

2011-24-12 PARA (J)(1) DETAILED INSPECTION TO DETECT AND CORRECTFATIGUE CRACKING OF THE FUSELAGE SKIN PANELS ATTHE CHEM-MILLED STEPS AND AN EXTERNALNON-DESTRUCTIVE INSPECTION (NDI) (MEDIUMFREQUENCY EDDY CURRENT INSPECTION, MAGNETOOPTICAL IMAGING INSPECTION, C-SCAN INSPECTION, ORULTRASONIC PHASED ARRAY INSPECTION) FOR CRACKINGIN THE FUSELAGE SKIN AT THE CHEM-MILL STEPS ATSTRINGERS S-1 AND S-2R BETWEEN STA 827 AND STA 847FOR GROUPS 2, 8, 10, 13 THROUGH 18, AND 21 THROUGH 25AIRPLANES

Task Relations


Model: BOEING 737-300/400/500


2011-24-12 PARA (J)(2) DETAILED INSPECTION TO DETECT AND CORRECTFATIGUE CRACKING OF THE FUSELAGE SKIN PANELS ATTHE CHEM-MILLED STEPS AND AN EXTERNAL NDI (MEDIUMFREQUENCY EDDY CURRENT INSPECTION; MAGNETOOPTICAL IMAGING INSPECTION, C-SCAN INSPECTION, ORULTRASONIC PHASED ARRAY INSPECTION) FOR CRACKINGIN THE FUSELAGE SKIN AT THE CHEM MILL STEPS AT THESPECIFIED LOCATIONS OTHER THAN AT S-1 AND S-2RBETWEEN STA 827 AND STA 847 FOR GROUPS 1 THROUGH25 AIRPLANES

2011-24-12 PARA (O) ACCOMPLISH TO DETECT AND CORRECT FATIGUECRACKING OF THE FUSELAGE SKIN PANELS AT THECHEM-MILLED STEPS APPLICABLE INSPECTIONS ANDCORRECTIVE ACTION FOR GROUP 26 AIRPLANES

2011-24-12 PARA (I) TERMINATING ACTION TO DETECT AND CORRECT FATIGUECRACKING OF THE FUSELAGE SKIN PANELS AT THECHEM-MILLED STEPS (OPTIONAL) FOR REPETITIVEINSPECTIONS IN PARAGRAPH (G)

2011-24-12 PARA (M) TERMINATING ACTION TO DETECT AND CORRECT FATIGUECRACKING OF THE FUSELAGE SKIN PANELS AT THECHEM-MILLED STEPS (OPTIONAL) FOR REPETITIVEINSPECTIONS IN PARAGRAPH (J)

2011-24-12 PARA (N) TERMINATING ACTION TO DETECT AND CORRECT FATIGUECRACKING OF THE FUSELAGE SKIN PANELS AT THECHEM-MILLED STEPS (ACCOMPLISHING A MODIFICATIONOF THE CHEM-MILLED STEPS AT ANY LOCATION) FORPARAGRAPHS (G) AND (J)


ACD (TWO WAY) TO737-53A1301 R2 FUSELAGE - SKIN - CRACKS AT CHEM-MILLED STEPS IN

CROWN SKINS AT SPECIFIED LOCATIONS - INSPECTIONSERVICE BULLETIN

737-53-1305 R1 FUSELAGE - SKIN - CHEM-MILLED STEPS IN CROWN SKINSWITH 20 INCH TEAR STRAP BAYS AT SPECIFIED LOCATIONS- INSPECTION AND MODIFICATION SERVICE BULLETIN

2011-27-03 TO PREVENT AN UNDETECTED FAILURE OF THE PRIMARYLOAD PATH FOR THE BALLSCREW IN THE DRIVEMECHANISM OF THE HSTA AND SUBSEQUENT WEAR ANDFAILURE OF THE SECONDARY LOAD PATH

PRIMARY TO

2011-27-03 PARA(G)(1)(I)(1)

DETAILED INSPECTION TO PREVENT AN UNDETECTEDFAILURE OF THE PRIMARY LOAD PATH FOR THEBALLSCREW IN THE DRIVE MECHANISM OF THE HSTA ANDSUBSEQUENT WEAR AND FAILURE OF THE SECONDARYLOAD PATH IN ACCORDANCE WITH PARAGRAPH E OFSERVICE BULLETIN 737-27A1278 R 1

Task Relations


Model: BOEING 737-300/400/500


2011-27-03 PARA(G)(1)(I)(2)

LUBRICATE TO PREVENT AN UNDETECTED FAILURE OFTHE PRIMARY LOAD PATH FOR THE BALLSCREW IN THEDRIVE MECHANISM OF THE HSTA AND SUBSEQUENT WEARAND FAILURE OF THE SECONDARY LOAD PATH INACCORDANCE WITH PARAGRAPH E OF SERVICE BULLETIN737-27A1278 R1

2011-27-03 PARA(G)(1)(I)(3)

OVERHAUL TO PREVENT AN UNDETECTED FAILURE OFTHE PRIMARY LOAD PATH FOR THE BALLSCREW IN THEDRIVE MECHANISM OF THE HSTA AND SUBSEQUENT WEARAND FAILURE OF THE SECONDARY LOAD PATH THEHORIZONTAL STABILIZER TRIM ACTUATOR INACCORDANCE PARAGRAPH E OF SERVICE BULLETIN737-27A1278 R1

2011-27-03 PARA(G)(1)(I)(4)

INCORPORATE TO PREVENT AN UNDETECTED FAILURE OFTHE PRIMARY LOAD PATH FOR THE BALLSCREW IN THEDRIVE MECHANISM OF THE HSTA AND SUBSEQUENT WEARAND FAILURE OF THE SECONDARY LOAD PATH SERVICEBULLETIN UMBRA CUSCINETTI, S.P.A. SB 07322-27-01, ORSERVICE BULLETIN LINEAR MOTION, LLC SB 7901708, ORSERVICE BULLETIN SKYTRONICS, INC. SB 93004, ASAPPLICABLE, IN ACCORDANCE WITH ACCOMPLISHMENTINSTRUCTIONS, PARAGRAPH E OF SERVICE BULLETIN737-27A1278 R1

2011-27-03 PARA(G)(1)(I)(5)

REPAIR/REPLACE TO PREVENT AN UNDETECTED FAILUREOF THE PRIMARY LOAD PATH FOR THE BALLSCREW IN THEDRIVE MECHANISM OF THE HSTA AND SUBSEQUENT WEARAND FAILURE OF THE SECONDARY LOAD PATH THEHORIZONTAL STABILIZER TRIM ACTUATOR INACCORDANCE WITH PARAGRAPH E OF THE SERVICEBULLETIN 737-27A1278 R1

2011-27-03 PARA(G)(1)(I)(6)

REMOVE TO PREVENT AN UNDETECTED FAILURE OF THEPRIMARY LOAD PATH FOR THE BALLSCREW IN THE DRIVEMECHANISM OF THE HSTA AND SUBSEQUENT WEAR ANDFAILURE OF THE SECONDARY LOAD PATH THE STABILIZERBALLSCREW ASSY 102J033-1 OR 102J033-1 (OS) ANDINSTALL STABILIZER BALLSCREW ASSY 102J033-3 OR102J033-502 IN ACCORDANCE WITH PARAGRAPH E OFSERVICE BULLETIN 737-27A1278 R1

2011-27-03 PARA(G)(1)(I)(7)

INCORPORATE TO PREVENT AN UNDETECTED FAILURE OFTHE PRIMARY LOAD PATH FOR THE BALLSCREW IN THEDRIVE MECHANISM OF THE HSTA AND SUBSEQUENT WEARAND FAILURE OF THE SECONDARY LOAD PATH BOEINGSERVICE BULLETIN 737-27-1046 REVISION 1 INACCORDANCE WITH PARAGRAPH E OF SERVICE BULLETIN737-27A1278 R1

Task Relations


Model: BOEING 737-300/400/500


2011-27-03 PARA(G)(1)(I)(8)

INCORPORATE TO PREVENT AN UNDETECTED FAILURE OFTHE PRIMARY LOAD PATH FOR THE BALLSCREW IN THEDRIVE MECHANISM OF THE HSTA AND SUBSEQUENT WEARAND FAILURE OF THE SECONDARY LOAD PATH SKYTRONICS, INC. SB 93004 IN ACCORDANCE WITHPARAGRAPH E OF SERVICE BULLETIN 737-27A1278 R1

2011-27-03 PARA(G)(1)(II)(C)

ACCOMPLISH TO PREVENT AN UNDETECTED FAILURE OFTHE PRIMARY LOAD PATH FOR THE BALLSCREW IN THEDRIVE MECHANISM OF THE HSTA AND SUBSEQUENT WEARAND FAILURE OF THE SECONDARY LOAD PATH MODIFICATION(S)

2011-27-03 PARA(G)(1)(II)(B)

ACCOMPLISH TO PREVENT AN UNDETECTED FAILURE OFTHE PRIMARY LOAD PATH FOR THE BALLSCREW IN THEDRIVE MECHANISM OF THE HSTA AND SUBSEQUENT WEARAND FAILURE OF THE SECONDARY LOAD PATH INITIALOVERHAUL

2011-27-03 PARA(G)(1)(II)(A)

ACCOMPLISH TO PREVENT AN UNDETECTED FAILURE OFTHE PRIMARY LOAD PATH FOR THE BALLSCREW IN THEDRIVE MECHANISM OF THE HSTA AND SUBSEQUENT WEARAND FAILURE OF THE SECONDARY LOAD PATH INITIALDETAILED INSPECTION AND LUBRICATION

2011-27-03 TO PREVENT AN UNDETECTED FAILURE OF THE PRIMARYLOAD PATH FOR THE BALLSCREW IN THE DRIVEMECHANISM OF THE HSTA AND SUBSEQUENT WEAR ANDFAILURE OF THE SECONDARY LOAD PATH

ACD (TWO WAY) TO

737-27A1278 R1 FLIGHT CONTROLS - HORIZONTAL STABILIZER TRIMCONTROL SYSTEM - BALLSCREW AND BALL NUTINSPECTION AND LUBRICATION SERVICE BULLETIN

2011-27-03 PARA(G)(1)(II)(A)

ACCOMPLISH TO PREVENT AN UNDETECTED FAILURE OFTHE PRIMARY LOAD PATH FOR THE BALLSCREW IN THEDRIVE MECHANISM OF THE HSTA AND SUBSEQUENT WEARAND FAILURE OF THE SECONDARY LOAD PATH INITIALDETAILED INSPECTION AND LUBRICATION

ASSOCIATED -(ONE WAY) TO

27-108-01 LUBRICATE - LUBRICATE THE STABILIZER TRIM ACTUATORAND ACTUATOR GIMBAL PINS.

27-096-01 DETAILED INSPECTION - INSPECT (DETAILED) THESTABILIZER TRIM JACKSCREW INCLUDING UPPER ANDLOWER GIMBALS

2011-27-03 PARA(G)(1)(II)(B)

ACCOMPLISH TO PREVENT AN UNDETECTED FAILURE OFTHE PRIMARY LOAD PATH FOR THE BALLSCREW IN THEDRIVE MECHANISM OF THE HSTA AND SUBSEQUENT WEARAND FAILURE OF THE SECONDARY LOAD PATH INITIALOVERHAUL


27-094-01 (001.0) STABILIZER TRIM ACTUATOR

Task Relations


Model: BOEING 737-300/400/500


2011-27-03 PARA(G)(1)(II)(C)

ACCOMPLISH TO PREVENT AN UNDETECTED FAILURE OFTHE PRIMARY LOAD PATH FOR THE BALLSCREW IN THEDRIVE MECHANISM OF THE HSTA AND SUBSEQUENT WEARAND FAILURE OF THE SECONDARY LOAD PATH MODIFICATION(S)


27-094-01 (001.0) STABILIZER TRIM ACTUATOR 2012-0037 FIRE PROTECTION – HAND OPERATED FIRE EXTINGUISHER

– MODIFICATION EASA AIRWORTHINESS DIRECTIVE PRIMARY TO

2012-0037 PARA (1) MODIFY FIRE PROTECTION – HAND OPERATED FIREEXTINGUISHER – MODIFICATION EASA AIRWORTHINESSDIRECTIVE THE FIRE EXTINGUISHER

2012-0037 PARA (2) DO NOT INSTALL FIRE PROTECTION – HAND OPERATEDFIRE EXTINGUISHER – MODIFICATION EASAAIRWORTHINESS DIRECTIVE ANY FIRE EXTINGUISHERWITHP/N MENTIONED IN THE APPLICABILITY SECTION OF THISAD ON AN AEROPLANE,UNLESS IT HAS BEEN MODIFIED IN COMPLIANCE WITH THEREQUIREMENTS OF THISAD.

2012-02-08 PREVENT TCAS UNITS FROM DROPPING TRACKS PRIMARY TO2012-02-08 PARA (G) UPGRADE PREVENT TCAS UNITS FROM DROPPING

TRACKS SOFTWARE FOR THE ACSS TCAS 2012-02-09 TO PREVENT IGNITION OF THE BMS 8-39 OR AMS 3570

POLYURETHANE FOAM INSULATION ON THE DUCTASSEMBLIES

ACD (TWO WAY) TO

737-21A1132 R3 AIR CONDITIONING - DISTRIBUTION - REPLACEMENT OFBMS 8-39 DUCT INSULATION SERVICE BULLETIN

2012-0254 OXYGEN - FLIGHT CREW OXYGEN MASK REGULATOR-IDENTIFICATION / OPERATIONAL PROCEDURE /REPLACEMENT (SUPERSEDED BY 2012-0254 R1) EASAAIRWORTHINESS DIRECTIVE

PRIMARY TO

2012-0254 (2.2) AMEND OXYGEN - FLIGHT CREW OXYGEN MASKREGULATOR -IDENTIFICATION / OPERATIONAL PROCEDURE/ REPLACEMENT (SUPERSEDED BY 2012-0254 R1) EASAAIRWORTHINESS DIRECTIVE AIRCRAFT FLIGHT MANUAL(AFM)

2012-0254 (1) INSPECT/CHECK OXYGEN - FLIGHT CREW OXYGEN MASKREGULATOR -IDENTIFICATION / OPERATIONAL PROCEDURE/ REPLACEMENT (SUPERSEDED BY 2012-0254 R1) EASAAIRWORTHINESS DIRECTIVE OXYGEN MASK REGULATORTO INDENTIFY THE P/N AND S/N

Task Relations


Model: BOEING 737-300/400/500


2012-0254 (2.1) REPLACE OXYGEN - FLIGHT CREW OXYGEN MASKREGULATOR -IDENTIFICATION / OPERATIONAL PROCEDURE/ REPLACEMENT (SUPERSEDED BY 2012-0254 R1) EASAAIRWORTHINESS DIRECTIVE AFFECTED OXYGEN MASKREGULATOR

2012-0254 (3) REPLACE OXYGEN - FLIGHT CREW OXYGEN MASKREGULATOR -IDENTIFICATION / OPERATIONAL PROCEDURE/ REPLACEMENT (SUPERSEDED BY 2012-0254 R1) EASAAIRWORTHINESS DIRECTIVE EACH AFFECTED FLIGHTCREW OXYGEN MASK REGULATOR WITH A SERVICEABLEPART

2012-0254 OXYGEN - FLIGHT CREW OXYGEN MASK REGULATOR-IDENTIFICATION / OPERATIONAL PROCEDURE /REPLACEMENT (SUPERSEDED BY 2012-0254 R1) EASAAIRWORTHINESS DIRECTIVE

ACD (TWO WAY) TO

D-2012-445 OXYGEN - FLIGHT CREW OXYGEN MASK REGULATOR -IDENTIFICATION / OPERATIONAL PROCEDURE /REPLACEMENT GERMAN AD

2012-0254 R1 OXYGEN - FLIGHT CREW OXYGEN MASK REGULATOR -IDENTIFICATION / OPERATIONAL PROCEDURE /REPLACEMENT EASA AIRWORTHINESS DIRECTIVE

PRIMARY TO

2012-0254 R1 (2.2) AMEND OXYGEN - FLIGHT CREW OXYGEN MASKREGULATOR - IDENTIFICATION / OPERATIONALPROCEDURE / REPLACEMENT EASA AIRWORTHINESSDIRECTIVE THE AIRCRAFT FLIGHT MANUAL (AFM) ANDINSTALL A PLACARD

2012-0254 R1 (2.1) REPLACE OXYGEN - FLIGHT CREW OXYGEN MASKREGULATOR - IDENTIFICATION / OPERATIONALPROCEDURE / REPLACEMENT EASA AIRWORTHINESSDIRECTIVE EACH AFFECTED FLIGHT CREW OXYGEN MASKREGULATOR WITH A SERVICEABLE PART

2012-0254 R1 (3) REPLACE OXYGEN - FLIGHT CREW OXYGEN MASKREGULATOR - IDENTIFICATION / OPERATIONALPROCEDURE / REPLACEMENT EASA AIRWORTHINESSDIRECTIVE EACH AFFECTED FLIGHT CREW OXYGEN MASKREGULATOR

2012-0254 R1 (1) INSPECT OXYGEN - FLIGHT CREW OXYGEN MASKREGULATOR - IDENTIFICATION / OPERATIONALPROCEDURE / REPLACEMENT EASA AIRWORTHINESSDIRECTIVE EACH FLIGHT CREW OXYGEN MASKREGULATOR TO IDENTIFY THE P/N AND S/N

2012-0254 R1 OXYGEN - FLIGHT CREW OXYGEN MASK REGULATOR -IDENTIFICATION / OPERATIONAL PROCEDURE /REPLACEMENT EASA AIRWORTHINESS DIRECTIVE

ACD (TWO WAY) TO

Task Relations


Model: BOEING 737-300/400/500


D-2012-445 R1 OXYGEN - FLIGHT CREW OXYGEN MASK REGULATOR -IDENTIFICATION / OPERATIONAL PROCEDURE /REPLACEMENT GERMAN AD

737-SL-35-026 CREW OXYGEN MASK REGULATORS SET INCORRECTLY BYSUPPLIER REPAIR STATION SERVICE LETTER

2012-461 OXYGEN - FLIGHT CREW OXYGEN MASK REGULATOR -IDENTIFICATION / OPERATIONAL PROCEDURE /REPLACEMENT ITALIAN CIVIL AVIATION AUTHORITY

2012-11-09 TO ELIMINATE THIS HAZARD AND ENSURE THAT ALLLAVATORIES HAVE A SUPPLEMENTAL OXYGEN SUPPLY

PRIMARY TO2012-11-09 PARA (L) INSTALL TO ELIMINATE THIS HAZARD AND ENSURE THAT

ALL LAVATORIES HAVE A SUPPLEMENTAL OXYGEN SUPPLYA SUPPLEMENTAL OXYGEN SYSTEM THAT MEETS ALLAPPLICABLE SECTIONS OF PARTS 25 AND 121 OF THEFEDERAL AVIATION REGULATIONS (14 CFR PART 25 AND 14CFR PART 121) IN EACH LAVATORY

2012-11-09 PARA (G) ACTIVATION TO ELIMINATE THIS HAZARD AND ENSURETHAT ALL LAVATORIES HAVE A SUPPLEMENTAL OXYGENSUPPLY OF ALL CHEMICAL OXYGEN GENERATORS IN THELAVATORIES UNTIL THE GENERATOR OXYGEN SUPPLY ISEXPENDED AND REMOVE OR RE-STOW THE OXYGENMASKS AND CLOSE THE MASK DISPENSER DOOR.

2012-11-09 PARA (J) DO NOT INSTALL TO ELIMINATE THIS HAZARD AND ENSURETHAT ALL LAVATORIES HAVE A SUPPLEMENTAL OXYGENSUPPLY A CHEMICAL OXYGEN GENERATOR IN ANYLAVATORY ON ANY AFFECTED AIRPLANE

2012-12-04 PERFORM PRIMARY TO2012-12-04 PARA (G) PERFORM PERFORM A DETAILED INSPECTION AND A

NONDESTRUCTIVE INSPECTION (NDI) (MEDIUM FREQUENCYEDDY CURRENT, MAGNETO OPTICAL IMAGING, C-SCAN, ORULTRASONIC PHASED ARRAY) TO DETECT CRACKS IN THEFUSELAGE SKIN ALONG THE CHEM-MILL STEPS ATSTRINGERS S-1 AND S-2R, BETWEEN STATION (STA) 400ANDSTA 460, IN ACCORDANCE WITH THE ACCOMPLISHMENTINSTRUCTIONS OF BOEING SERVICE BULLETIN737-53A1293, REVISION 2,

2012-12-04 PERFORM ACD (TWO WAY) TO737-53-1305 R1 FUSELAGE - SKIN - CHEM-MILLED STEPS IN CROWN SKINS

WITH 20 INCH TEAR STRAP BAYS AT SPECIFIED LOCATIONS- INSPECTION AND MODIFICATION SERVICE BULLETIN

Task Relations


Model: BOEING 737-300/400/500


2012-12-04 PARA (G) PERFORM PERFORM A DETAILED INSPECTION AND ANONDESTRUCTIVE INSPECTION (NDI) (MEDIUM FREQUENCYEDDY CURRENT, MAGNETO OPTICAL IMAGING, C-SCAN, ORULTRASONIC PHASED ARRAY) TO DETECT CRACKS IN THEFUSELAGE SKIN ALONG THE CHEM-MILL STEPS ATSTRINGERS S-1 AND S-2R, BETWEEN STATION (STA) 400ANDSTA 460, IN ACCORDANCE WITH THE ACCOMPLISHMENTINSTRUCTIONS OF BOEING SERVICE BULLETIN737-53A1293, REVISION 2,

ACD (TWO WAY) TO

737-53A1293 R2 FUSELAGE - SKIN - STRINGER S-1 AND STRINGER S-2R,STATION 400 TO STATION 460 INSPECTION AND REPAIRSERVICE BULLETIN

2012-12-05 TO DETECT AND CORRECT FATIGUE CRACKING OF THEINTERCOSTALS ON THE FORWARDAND AFT SIDES OF THE FORWARD ENTRY DOOR CUTOUT

PRIMARY TO

2012-12-05 PARA (Q) HFEC TO DETECT AND CORRECT FATIGUE CRACKING OFTHE INTERCOSTALS ON THE FORWARDAND AFT SIDES OF THE FORWARD ENTRY DOOR CUTOUT INSPECTIONS FOR CRACKING OF THE REINFORCEMENTANGLE AND SHEAR WEB, AND A DETAILED INSPECTIONFOR CRACKING OF THE STA 348.2 FRAME OUTER CHORD,INNER CHORD, AND REINFORCEMENT ANGLE FOR GROUPS2 AND 3 AIRPLANES IDENTIFIED IN BOEING ALERT SERVICEBULLETIN 737-53A1240, REVISION 1

2012-12-05 PARA (K) DETAILED INSPECTION TO DETECT AND CORRECTFATIGUE CRACKING OF THE INTERCOSTALS ON THEFORWARDAND AFT SIDES OF THE FORWARD ENTRY DOOR CUTOUT FOR CRACKING OF THE INTERCOSTAL WEB, ATTACHMENTCLIPS, AND STRINGER SPLICE CHANNELS; AND A HIGHFREQUENCY EDDY CURRENT (HFEC) INSPECTION FORCRACKING OF THE STRINGER SPLICE CHANNELS LOCATEDFORWARD AND AFT OF THE FORWARD ENTRY DOOR FORGROUP 1 AIRPLANES IDENTIFIED IN BOEING ALERTSERVICE BULLETIN 737-53A1204, REVISION 1

2012-12-05 PARA (L) DETAILED INSPECTION TO DETECT AND CORRECTFATIGUE CRACKING OF THE INTERCOSTALS ON THEFORWARDAND AFT SIDES OF THE FORWARD ENTRY DOOR CUTOUT FOR CRACKING OF THE INTERCOSTAL WEBS ANDATTACHMENT CLIPS LOCATED FORWARD OF THEFORWARD ENTRY DOOR FOR CARGO CONFIGURATIONAIRPLANES

Task Relations


Model: BOEING 737-300/400/500


2012-12-05 PARA (P) DETAILED INSPECTION TO DETECT AND CORRECTFATIGUE CRACKING OF THE INTERCOSTALS ON THEFORWARDAND AFT SIDES OF THE FORWARD ENTRY DOOR CUTOUT TO DETECT MISSING FASTENERS OF THE STA 348.2 FRAMEFOR GROUPS 2 AND 3 AIRPLANES IDENTIFIED IN BOEINGALERT SERVICE BULLETIN 737-53A1240, REVISION 1

2012-12-05 PARA (K) DETAILED INSPECTION TO DETECT AND CORRECTFATIGUE CRACKING OF THE INTERCOSTALS ON THEFORWARDAND AFT SIDES OF THE FORWARD ENTRY DOOR CUTOUT FOR CRACKING OF THE INTERCOSTAL WEB, ATTACHMENTCLIPS, AND STRINGER SPLICE CHANNELS; AND A HIGHFREQUENCY EDDY CURRENT (HFEC) INSPECTION FORCRACKING OF THE STRINGER SPLICE CHANNELS LOCATEDFORWARD AND AFT OF THE FORWARD ENTRY DOOR FORGROUP 1 AIRPLANES IDENTIFIED IN BOEING ALERTSERVICE BULLETIN 737-53A1204, REVISION 1

ACD (TWO WAY) TO

737-53A1204 R2 FUSELAGE - MAIN FRAME - FRAMES AND BULKHEADS -BODY STATION BS 360 - BS 348.2 AND BS 303.9 - BS 294.5STRINGERS S-7L - S-16L LEFT INTERCOSTAL INSPECTION /REPAIR / MODIFICATION SERVICE BULLETIN

2012-12-05 PARA (L) DETAILED INSPECTION TO DETECT AND CORRECTFATIGUE CRACKING OF THE INTERCOSTALS ON THEFORWARDAND AFT SIDES OF THE FORWARD ENTRY DOOR CUTOUT FOR CRACKING OF THE INTERCOSTAL WEBS ANDATTACHMENT CLIPS LOCATED FORWARD OF THEFORWARD ENTRY DOOR FOR CARGO CONFIGURATIONAIRPLANES

ACD (TWO WAY) TO


2012-12-05 PARA (P) DETAILED INSPECTION TO DETECT AND CORRECTFATIGUE CRACKING OF THE INTERCOSTALS ON THEFORWARDAND AFT SIDES OF THE FORWARD ENTRY DOOR CUTOUT TO DETECT MISSING FASTENERS OF THE STA 348.2 FRAMEFOR GROUPS 2 AND 3 AIRPLANES IDENTIFIED IN BOEINGALERT SERVICE BULLETIN 737-53A1240, REVISION 1

ACD (TWO WAY) TO

737-53A1240 R1 FUSELAGE - FRAMES AND BULKHEADS - FORWARD DOOR,INSPECTION AND REPAIR OF INNER FRAME CHORD,STRINGERS AND INTERCOSTALS SERVICE BULLETIN

Task Relations


Model: BOEING 737-300/400/500


2012-12-05 PARA (Q) HFEC TO DETECT AND CORRECT FATIGUE CRACKING OFTHE INTERCOSTALS ON THE FORWARDAND AFT SIDES OF THE FORWARD ENTRY DOOR CUTOUT INSPECTIONS FOR CRACKING OF THE REINFORCEMENTANGLE AND SHEAR WEB, AND A DETAILED INSPECTIONFOR CRACKING OF THE STA 348.2 FRAME OUTER CHORD,INNER CHORD, AND REINFORCEMENT ANGLE FOR GROUPS2 AND 3 AIRPLANES IDENTIFIED IN BOEING ALERT SERVICEBULLETIN 737-53A1240, REVISION 1

ACD (TWO WAY) TO


2012-13-07 TO DETECT AND CORRECT CORROSION OF THE CARRIAGESPINDLE

PRIMARY TO2012-13-07 PARA (H)CARRIAGE 4

DETAILED INSPECTION TO DETECT AND CORRECTCORROSION OF THE CARRIAGE SPINDLE OR BORESCOPEINSPECTION OF THE FORWARD END OF THE CARRIAGESPINDLE FOR CORROSION AND FLAKING AND MISSINGTHERMAL COATING

2012-13-07 PARA (H)CARRIAGE 1

DETAILED INSPECTION TO DETECT AND CORRECTCORROSION OF THE CARRIAGE SPINDLE ORBOROESCOPE INSPECTION OF THE FORWARD END OF THECARRIAGE SPINDLE FOR CORROSION AND FLAKING ANDMISSING THERMAL COATING

2012-13-07 PARA (J) DO NOT INSTALL TO DETECT AND CORRECT CORROSIONOF THE CARRIAGE SPINDLE A SERVICEABLEHVOF-COATED CARRIAGE ON AN AIRPLANE UNLESS THEACTIONS REQUIRED BY PARAGRAPH (H)(1) OF THIS AD AREDONE ON THAT CARRIAGE PRIOR TO INSTALLATION

2012-13-07 PARA (G) PERFORM TO DETECT AND CORRECT CORROSION OF THECARRIAGE SPINDLE AN INSPECTION OF THE PART OR ARECORDS REVIEW TO DETERMINE WHETHER A SUSPECTCARRIAGE WITH A HIGH VELOCITY OXYGENATED FUEL(HVOF) THERMAL COATING IS INSTALLED AT WING BUTTLINE WBL) 254 OR WBL 355





Task Relations


Model: BOEING 737-300/400/500


2012-13-07 PARA (G) PERFORM TO DETECT AND CORRECT CORROSION OF THECARRIAGE SPINDLE AN INSPECTION OF THE PART OR ARECORDS REVIEW TO DETERMINE WHETHER A SUSPECTCARRIAGE WITH A HIGH VELOCITY OXYGENATED FUEL(HVOF) THERMAL COATING IS INSTALLED AT WING BUTTLINE WBL) 254 OR WBL 355

ACD (TWO WAY) TO

737-57A1319 R1 WINGS - TRAILING EDGE FLAPS - OUTBOARD FLAP,CARRIAGE SPINDLE - INSPECTION FOR CORROSIONSERVICE BULLETIN



ACD (TWO WAY) TO


2012-16-07 DO AN EXTERNAL DETAILED INSPECTION; AND, ASAPPLICABLE, DO AN EXTERNAL OR INTERNAL SUBSURFACEEDDYCURRENT, MAGNETO OPTIC IMAGER, OR C-SCANINSPECTION; TO DETECT CRACKS IN THE FUSELAGE SKINAT THE CHEMMILLSTEPS; IN ACCORDANCE WITH THE ACCOMPLISHMENTINSTRUCTIONS OF BOEING SPECIAL ATTENTION SERVICEBULLETIN 737-53-1315

ACD (TWO WAY) TO

737-53-1315 FUSELAGE - SKIN - STATION 727 TO 1016 - AFT SKININSPECTION AND REPAIR SERVICE BULLETIN

2012-18-13 TO DETECT AND CORRECT FATIGUE CRACKS IN THE AFTPRESSURE BULKHEAD (SUPERSEDED BY FAA AD2012-18-13 R1)

PRIMARY TO

2012-18-13 PARA (L) PERFORM TO DETECT AND CORRECT FATIGUE CRACKS INTHE AFT PRESSURE BULKHEAD (SUPERSEDED BY FAA AD2012-18-13 R1) INSPECTIONS OF THE WEB AT THE ''Y''CHORD IN THE LOWER BULKHEAD FROMS-15L TO S-15R

2012-18-13 PARA (S) TERMINATING ACTION TO DETECT AND CORRECT FATIGUECRACKS IN THE AFT PRESSURE BULKHEAD (SUPERSEDEDBY FAA AD 2012-18-13 R1)

2012-18-13 PARA (Q) PERFORM TO DETECT AND CORRECT FATIGUE CRACKS INTHE AFT PRESSURE BULKHEAD (SUPERSEDED BY FAA AD2012-18-13 R1) A DETAILED INSPECTION OF THE BULKHEADWEB AND STIFFENERS FOR EXISTING REPAIRS

Task Relations


Model: BOEING 737-300/400/500


2012-18-13 PARA (P) PERFORM TO DETECT AND CORRECT FATIGUE CRACKS INTHE AFT PRESSURE BULKHEAD (SUPERSEDED BY FAA AD2012-18-13 R1) INSPECTION OF THE FORWARD FLANGE OFTHE ''Z'' STIFFENERS AT THE DOMECAP

2012-18-13 PARA (O) PERFORM TO DETECT AND CORRECT FATIGUE CRACKS INTHE AFT PRESSURE BULKHEAD (SUPERSEDED BY FAA AD2012-18-13 R1) INSPECTION OF THE DOME CAP AT THECENTER OF THE BULKHEAD

2012-18-13 PARA (N) PERFORM TO DETECT AND CORRECT FATIGUE CRACKS INTHE AFT PRESSURE BULKHEAD (SUPERSEDED BY FAA AD2012-18-13 R1) INSPECTION FOR OIL-CANNING

2012-18-13 PARA (M) PERFORM TO DETECT AND CORRECT FATIGUE CRACKS INTHE AFT PRESSURE BULKHEAD (SUPERSEDED BY FAA AD2012-18-13 R1) A ONE-TIME LFEC INSPECTION

2012-18-13 PARA (K) PERFORM TO DETECT AND CORRECT FATIGUE CRACKS INTHE AFT PRESSURE BULKHEAD (SUPERSEDED BY FAA AD2012-18-13 R1) INSPECTIONS OF THE WEB AT THE ''Y''CHORD UPPER BULKHEAD FROM S-15LTO S-15R

2012-18-13 PARA (J) ACCOMPLISH TO DETECT AND CORRECT FATIGUE CRACKSIN THE AFT PRESSURE BULKHEAD (SUPERSEDED BY FAAAD 2012-18-13 R1) (RETAINED) CORRECTIVE ACTIONS

2012-18-13 PARA(G)(H)(I)

ACCOMPLISH TO DETECT AND CORRECT FATIGUE CRACKSIN THE AFT PRESSURE BULKHEAD (SUPERSEDED BY FAAAD 2012-18-13 R1) (RETAINED) INITIAL AND REPETITIVEINSPECTION

2012-18-13 TO DETECT AND CORRECT FATIGUE CRACKS IN THE AFTPRESSURE BULKHEAD (SUPERSEDED BY FAA AD2012-18-13 R1)

ACD (TWO WAY) TO

737-53A1214 R4 FUSELAGE - BODY STATION 1016 AFT PRESSUREBULKHEAD WEB CRACKS - INSPECTION AND REPAIRSERVICE BULLETIN

2012-18-13 R1 TO DETECT AND CORRECT FATIGUE CRACKS IN THE AFTPRESSURE BULKHEAD

PRIMARY TO2012-18-13 R1 PARA (L) PERFORM TO DETECT AND CORRECT FATIGUE CRACKS IN

THE AFT PRESSURE BULKHEAD RETAINED INSPECTIONSOF THE WEB AT THE "'Y" CHORD IN THE LOWER BULKHEADFROM S-15L TO S-15R WITH REVISED INSPECTION ANDREPAIR CONDITIONS

2012-18-13 R1 PARA (K) PERFORM TO DETECT AND CORRECT FATIGUE CRACKS INTHE AFT PRESSURE BULKHEAD RETAINED INSPECTIONSOF THE WEB AT THE "'Y" CHORD UPPER BULKHEAD FROMS-15L TO S-15R

Task Relations


Model: BOEING 737-300/400/500


2012-18-13 R1 PARA (J) ACCOMPLISH TO DETECT AND CORRECT FATIGUE CRACKSIN THE AFT PRESSURE BULKHEAD (RETAINED)CORRECTIVE ACTIONS

2012-18-13 R1 PARA(G)(H)(I)

ACCOMPLISH TO DETECT AND CORRECT FATIGUE CRACKSIN THE AFT PRESSURE BULKHEAD (RETAINED) INITIAL ANDREPETITIVE INSPECTION

2012-18-13 R1 PARA (Q) PERFORM TO DETECT AND CORRECT FATIGUE CRACKS INTHE AFT PRESSURE BULKHEAD RETAINED INSPECTIONFOR EXISTING REPAIRS ON THE BULKHEAD

2012-18-13 R1 PARA (P) PERFORM TO DETECT AND CORRECT FATIGUE CRACKS INTHE AFT PRESSURE BULKHEAD RETAINED INSPECTION OFTHE FORWARD FLANGE OF THE "Z" STIFFENERS AT THEDOME CAP

2012-18-13 R1 PARA (O) PERFORM TO DETECT AND CORRECT FATIGUE CRACKS INTHE AFT PRESSURE BULKHEAD RETAINED INSPECTION OFTHE DOME CAP AT THE CENTER OF THE BULKHEAD

2012-18-13 R1 PARA (N) PERFORM TO DETECT AND CORRECT FATIGUE CRACKS INTHE AFT PRESSURE BULKHEAD RETAINED INSPECTIONFOR OIL-CANNING

2012-18-13 R1 PARA (M) PERFORM TO DETECT AND CORRECT FATIGUE CRACKS INTHE AFT PRESSURE BULKHEAD RETAINED ONE-TIMEINSPECTION UNDER THE TEAR STRAP

2012-18-13 R1 PARA (S) TERMINATING ACTION TO DETECT AND CORRECT FATIGUECRACKS IN THE AFT PRESSURE BULKHEAD

2012-18-13 R1 TO DETECT AND CORRECT FATIGUE CRACKS IN THE AFTPRESSURE BULKHEAD

ACD (TWO WAY) TOF-1999-193-IMP R1 REAR PRESSURE BULKHEAD (REPLACED BY FAA AD

2012-18-13) CONSIGNE DE NAVIGABILITE (DGAC) 2012-346 FUSELAGE - AFT PRESSURE BULKHEAD WEB -

INSPECTIONS/REPAIR (CANCELLED BY ENAC AD 2013-166)ITALIAN CIVIL AVIATION AUTHORITY

2013-166 FUSELAGE - AFT PRESSURE BULKHEAD WEB -INSPECTIONS/REPAIR ITALIAN CIVIL AVIATION AUTHORITY

D-1999-191 R2 FUSELAGE - AFT PRESSURE BULKHEAD WEB -INSPECTIONS / REPAIR GERMAN AD


2012-19-11 TO PREVENT THE LOSS OF CABIN ALTITUDE WARNING ACD (TWO WAY) TO737-21-1164 R2 AIR CONDITIONING - PRESSURIZATION INDICATION AND

WARNING - REDUNDANT PRESSURE SWITCH AND AURALWARNING MODULE INSTALLATION SERVICE BULLETIN

Task Relations


Model: BOEING 737-300/400/500


2012-399 AIR CONDITIONING - CABIN ALTITUDE PRESSURE SWITCH -AURAL WARNING MODULE (AWM) -INSTALLATION/REPLACEMENT ITALIAN CIVIL AVIATIONAUTHORITY

2012-23-04 TO DETECT AND CORRECT FATIGUE CRACKING OF THEOUTBOARD AND AUXILIARY CHORDS

PRIMARY TO2012-23-04 PARA (K) INSTALL TO DETECT AND CORRECT FATIGUE CRACKING

OF THE OUTBOARD AND AUXILIARY CHORDS /REPLACETHE OUTBOARD CHORD AFTER ACCOMPLISHING THETIME-LIMITED REPAIR

2012-23-04 PARA (L) INTERNAL - DETAILED TO DETECT AND CORRECT FATIGUECRACKING OF THE OUTBOARD AND AUXILIARY CHORDS AND HFEC INSPECTIONS TO DETECT CRACKS IN THEAUXILIARY CHORD RADIUS OF THE FRAME AT BS 727AUXILIARY CHORD

2012-23-04 PARA (M)(1)(I) ULTRASONIC TO DETECT AND CORRECT FATIGUECRACKING OF THE OUTBOARD AND AUXILIARY CHORDS AND SURFACE HFEC INSPECTIONS TO DETECT CRACKS INTHE FORWARD FLANGE OF THE OUTBOARD CHORD OF THEFRAME AT BS 727

2012-23-04 PARA(M)(1)(II)

OPEN TO DETECT AND CORRECT FATIGUE CRACKING OFTHE OUTBOARD AND AUXILIARY CHORDS HOLE EDDYCURRENT INSPECTION TO DETECT CRACKS IN THEFORWARD FLANGE OF THE OUTBOARD CHORD OF THEFRAME AT BS 727

2012-23-04 PARA (N)(1)(I) ULTRASONIC TO DETECT AND CORRECT FATIGUECRACKING OF THE OUTBOARD AND AUXILIARY CHORDS LOW FREQUENCY EDDY CURRENT, AND EDGE HFECINSPECTIONS TO DETECT CRACKS IN THE FORWARDFLANGE OF THE OUTBOARD CHORD OF THE FRAME AT BS727

2012-23-04 PARA(N)(1)(II)

OPEN TO DETECT AND CORRECT FATIGUE CRACKING OFTHE OUTBOARD AND AUXILIARY CHORDS HOLE EDDYCURRENT INSPECTION TO DETECT CRACKS IN THEFORWARD FLANGE OF THE OUTBOARD CHORD OF THEFRAME AT BS 727

2012-23-04 PARA (I) (J) PERFORM TO DETECT AND CORRECT FATIGUE CRACKINGOF THE OUTBOARD AND AUXILIARY CHORDS RETAINEDINITIAL AND REPETITIVE INSPECTION: BS 727 FRAMECHORD HAS NOT BEEN REPLACED OR ONLY LOWEROUTBOARD CHORD HAS BEEN REPLACED

2012-23-04 PARA (G) (H) PERFORM TO DETECT AND CORRECT FATIGUE CRACKINGOF THE OUTBOARD AND AUXILIARY CHORDS RETAINEDINITIAL OR REPETITIVE INSPECTIONS: BS 727 FRAMECHORD HAS BEEN REPLACED

Task Relations


Model: BOEING 737-300/400/500


2012-23-04 PARA (O) ACCOMPLISH TO DETECT AND CORRECT FATIGUECRACKING OF THE OUTBOARD AND AUXILIARY CHORDS ONE-TIME FOLLOW-ON OPEN HOLE EDDY CURRENTINSPECTION TO DETECT CRACKS IN THE MODIFIED CHORD

2012-23-04 PARA (R) TERMINATING TO DETECT AND CORRECT FATIGUECRACKING OF THE OUTBOARD AND AUXILIARY CHORDS ACTION FOR THE INSPECTIONS REQUIRED BYPARAGRAPHS (G) THROUGH (O) THIS AD BYACCOMPLISHING REPLACEMENT OF THE CRACKED CHORDAND INSTALLATION OF THE PREVENTATIVE MODIFICATION

2012-23-04 PARA (Q) REPLACE TO DETECT AND CORRECT FATIGUE CRACKINGOF THE OUTBOARD AND AUXILIARY CHORDS THE REPAIRFOR ANY AIRPLANE ON WHICH A TIME-LIMITED REPAIR ISINSTALLED ON THE OUTBOARD CHORD OF THE FRAME ATBODY STATION BS 727

2012-23-04 TO DETECT AND CORRECT FATIGUE CRACKING OF THEOUTBOARD AND AUXILIARY CHORDS

ACD (TWO WAY) TO737-53A1166 R2 FUSELAGE - FRAMES - BS 727 OUTBOARD CHORD AT

STRINGER 18A, INSPECTION AND MODIFICATION SERVICEBULLETIN

D-1996-162 R1 FUSELAGE - FRAME BODY STATION (BS) 727 AND STRINGER18A OUTBOARD CHORDS - INSPECTION / REPAIR GERMANAD

2012-429 FUSELAGE - FRAME BODY STATION (BS) 727 AND STRINGER18A OUTBOARD CHORDS - INSPECTION/REPAIR ITALIANCIVIL AVIATION AUTHORITY

2012-23-14 TO DETECT AND CORRECT CRACKING IN THE FUSELAGESKIN AND INTERNAL SUPPORT STRUCTURE

PRIMARY TO2012-23-14 PARA (G)(1) PERFORM TO DETECT AND CORRECT CRACKING IN THE

FUSELAGE SKIN AND INTERNAL SUPPORT STRUCTURE ALLRELATED INVESTIGATIVE ACTIONS AND REPAIR FORGROUP 1 AIRPLANES

2012-23-14 PARA (G)(2) INSPECT TO DETECT AND CORRECT CRACKING IN THEFUSELAGE SKIN AND INTERNAL SUPPORT STRUCTURE AND REPAIR FOR GROUP 2 AIRPLANES

2012-23-14 TO DETECT AND CORRECT CRACKING IN THE FUSELAGESKIN AND INTERNAL SUPPORT STRUCTURE

ACD (TWO WAY) TOD-2013-007 AFT DRAIN MAST FUSELAGE SKIN, CHANNELS, FILLERS

AND BONDING STRAP - INSPECTION / REPAIR GERMAN AD 2012-458 AFT DRAIN MAST FUSELAGE SKIN, CHANNELS, FILLERS

AND BONDING STRAP - INSPECTION/REPAIR ITALIAN CIVILAVIATION AUTHORITY

Task Relations


Model: BOEING 737-300/400/500


2012-23-14 PARA(G)(1)

PERFORM TO DETECT AND CORRECT CRACKING IN THEFUSELAGE SKIN AND INTERNAL SUPPORT STRUCTURE ALLRELATED INVESTIGATIVE ACTIONS AND REPAIR FORGROUP 1 AIRPLANES

ACD (TWO WAY) TO

737-53A1318 FUSELAGE - SKIN - SKIN CRACKING AT THE AFT WASTEWATER DRAIN MAST - INSPECTION AND REPAIR SERVICEBULLETIN

2012-23-14 PARA(G)(2)

INSPECT TO DETECT AND CORRECT CRACKING IN THEFUSELAGE SKIN AND INTERNAL SUPPORT STRUCTURE AND REPAIR FOR GROUP 2 AIRPLANES

ACD (TWO WAY) TO

737-53A1318 FUSELAGE - SKIN - SKIN CRACKING AT THE AFT WASTEWATER DRAIN MAST - INSPECTION AND REPAIR SERVICEBULLETIN

2012-26-02 TO DETECT AND CORRECT FATIGUE CRACKING OF THEFUSELAGE SKIN

PRIMARY TO2012-26-02 PARA (J) PERFORM TO DETECT AND CORRECT FATIGUE CRACKING

OF THE FUSELAGE SKIN REPAIR 2012-26-02 PARA (K) TO DETECT AND CORRECT FATIGUE CRACKING OF THE

FUSELAGE SKIN REPORTING NOT REQUIRED 2012-26-02 PARA (L) TO DETECT AND CORRECT FATIGUE CRACKING OF THE

FUSELAGE SKIN RETAINED CREDIT FOR PREVIOUSACTIONS

2012-26-02 PARA (M) PERFORM TO DETECT AND CORRECT FATIGUE CRACKINGOF THE FUSELAGE SKIN A NON-DESTRUCTIVE INSPECTION(NDI) (MEDIUM FREQUENCY EDDY CURRENT,MAGNETO OPTICAL IMAGING, C-SCAN, OR ULTRASONICPHASED ARRAY) FOR HORIZONTAL CHEM-MILL CRACKINGABOVE THE S-4 AND S-10 LAP JOINTS

2012-26-02 PARA(N)(1)(2)(I)

PERFORM TO DETECT AND CORRECT FATIGUE CRACKINGOF THE FUSELAGE SKIN PERMANENT OR TIME-LIMITEDREPAIR FOR CRACKING FOUND DURING INSPECTIONS,INCLUDING RELATED INVESTIGATIVE ACTIONS ANDAPPLICABLE CORRECTIVE ACTIONS

2012-26-02 PARA(N)(2)(II)

PERFORM TO DETECT AND CORRECT FATIGUE CRACKINGOF THE FUSELAGE SKIN A DETAILED INSPECTION FORLOOSE FASTENERS, AFTER THE TIME-LIMITED REPAIR WASINSTALLED

2012-26-02 PARA(N)(2)(III)

DO TO DETECT AND CORRECT FATIGUE CRACKING OF THEFUSELAGE SKIN THE PERMANENT REPAIR, AFTER THETIME-LIMITED REPAIR WAS INSTALLED

2012-26-02 PARA (O) PERFORM TO DETECT AND CORRECT FATIGUE CRACKINGOF THE FUSELAGE SKIN AN NDI (MEDIUM FREQUENCYEDDY CURRENT, MAGNETO OPTICAL IMAGING, C-SCAN, ORULTRASONIC PHASED ARRAY) FOR HORIZONTALCHEM-MILL CRACKING IN THE SHEAR WRINKLE AREAS

Task Relations


Model: BOEING 737-300/400/500


2012-26-02 PARA (P) PERFORM TO DETECT AND CORRECT FATIGUE CRACKINGOF THE FUSELAGE SKIN AN NDI (MEDIUM FREQUENCYEDDY CURRENT, MAGNETO OPTICAL IMAGING, C-SCAN, ORULTRASONIC PHASED ARRAY) FOR VERTICAL CHEM-MILLCRACKING AT LOCATIONS SPECIFIED IN

2012-26-02 PARA (Q) PERFORM TO DETECT AND CORRECT FATIGUE CRACKINGOF THE FUSELAGE SKIN AN NDI (MEDIUM FREQUENCYEDDY CURRENT, MAGNETO OPTICAL IMAGING, CSCAN, ORULTRASONIC PHASED ARRAY) FOR HORIZONTALCHEM-MILL CRACKING IN GENERAL POCKET-TO-POCKETAREAS AT SPECIFIED LOCATIONS

2012-26-02 PARA (R) TO DETECT AND CORRECT FATIGUE CRACKING OF THEFUSELAGE SKIN NEW INSPECTION EXCEPTION

2012-26-02 PARA (S) REPAIR TO DETECT AND CORRECT FATIGUE CRACKING OFTHE FUSELAGE SKIN THE CRACK USING A METHODAPPROVED IN ACCORDANCE WITH THE PROCEDURES

2012-26-02 PARA (T)(1) INSTALL TO DETECT AND CORRECT FATIGUE CRACKINGOF THE FUSELAGE SKIN INTERNAL TEAR STRAPDOUBLERS (FOR AIRPLANES ON WHICH PERMANENTREPAIRS HAVE BEEN DONE)

2012-26-02 PARA (T)(2) PERFORM TO DETECT AND CORRECT FATIGUE CRACKINGOF THE FUSELAGE SKIN A DETAILED INSPECTION FORLOOSE FASTENERS (FOR AIRPLANES ON WHICHTIME-LIMITED REPAIRS HAVE BEEN INSTALLED)

2012-26-02 PARA (T)(3) ACCOMPLISH TO DETECT AND CORRECT FATIGUECRACKING OF THE FUSELAGE SKIN THE REPAIRPERMANENT BY REPLACING THE BLIND FASTENERS IN THETIME-LIMITED REPAIR WITH SOLID RIVETS, AND INSTALLINTERNAL TEAR STRAP DOUBLERS

2012-26-02 PARA (U) REPAIR TO DETECT AND CORRECT FATIGUE CRACKING OFTHE FUSELAGE SKIN THE CRACK USING A METHODAPPROVED IN ACCORDANCE WITH THE PROCEDURES

2012-26-02 PARA (W) TO DETECT AND CORRECT FATIGUE CRACKING OF THEFUSELAGE SKIN POST - REPAIR INSPECTIONS NOTREQUIRED

2012-26-02 PARA (V) ACCOMPLISH TO DETECT AND CORRECT FATIGUECRACKING OF THE FUSELAGE SKIN EXCEPTIONS TOBOEING ALERT SERVICE BULLETIN 737 53A1234 REVISION 2DATED NOV 24,2010

2012-26-02 PARA (G)(H) PERFORM TO DETECT AND CORRECT FATIGUE CRACKINGOF THE FUSELAGE SKIN DETAILED AND EDDY CURRENTINSPECTIONS FOR CRACKING OF THE CROWN AREA OFTHE FUSELAGE SKIN

Task Relations


Model: BOEING 737-300/400/500


2012-26-02 PARA (I) PERFORM TO DETECT AND CORRECT FATIGUE CRACKINGOF THE FUSELAGE SKIN A PERMANENT OR TIME - LIMITEDREPAIR ((INCLUDING RELATED INVESTIGATIVE ACTIONSAND APPLICABLE CORRECTIVE ACTIONS)


ASSOCIATED -(ONE WAY) TO737-53A1234-AMOC-01 ALTERNATIVE METHOD OF COMPLIANCE (AMOC) TO

PARAGRAPHS (G), (H), (I)(1), (M), (N)(1), (O), (P) AND (Q) OFFAA AIRWORTHINESS DIRECTIVE (AD) 2012-26-02 SERVICEBULLETIN


ACD (TWO WAY) TO2013-33 FUSELAGE - SKIN CROWN AREA FATIGUE CRACKING -

INSPECTION/REPAIR ITALIAN CIVIL AVIATION AUTHORITY 737-53A1234 R2 FUSELAGE - SKIN - CRACKS AT CHEM-MILLED STEPS -

INSPECTION AND REPAIR SERVICE BULLETIN 737-53-1234 R1 FUSELAGE - SKIN - CRACKS AT CHEM-MILLED STEPS -

INSPECTION AND REPAIR SERVICE BULLETIN D-2005-309 R1 FUSELAGE - SKIN CROWN AREA FATIGUE CRACKING -

INSPECTION / REPAIR GERMAN AD 2013-0020 R2 EQUIPMENT & FURNISHINGS - SAFETY BELTS / TORSO

RESTRAINT SYSTEMS - INSPECTION / REPLACEMENT EASAAIRWORTHINESS DIRECTIVE

PRIMARY TO

2013-0020 R2 (2) EQUIPMENT & FURNISHINGS - SAFETY BELTS / TORSORESTRAINT SYSTEMS - INSPECTION / REPLACEMENT EASAAIRWORTHINESS DIRECTIVE VERIFY IF THEORGANISATION IS LISTED AMONG THE AUTHORIZEDMAINTENANCE OR REPAIR ORGANISATION REFERENCEDOCUMENTS QUOTED IN THE REF. PUBLICATIONS SECTIONOF THIS AD

2013-0020 R2 (1) EQUIPMENT & FURNISHINGS - SAFETY BELTS / TORSORESTRAINT SYSTEMS - INSPECTION / REPLACEMENT EASAAIRWORTHINESS DIRECTIVE INSPECT THE MARKINGS OFSAFETY BELTS AND/OR TORSO RESTRAINT SYSTEMS, TODETERMINE IF THEY HAVE BEEN MAINTAINED ORREPAIRED BY ORGANISATIONS OTHER THAN THE DESIGNAPPROVAL HOLDER

2013-0020 R2 (3) EQUIPMENT & FURNISHINGS - SAFETY BELTS / TORSORESTRAINT SYSTEMS - INSPECTION / REPLACEMENT EASAAIRWORTHINESS DIRECTIVE REMOVE AND REPLACEBELTS NOT MEETING THE CERTIFICATION REQUIREMENTSOR MAKE RELEVANT SEAT INOPERATIVE

Task Relations


Model: BOEING 737-300/400/500


2013-0020 R2 (4) EQUIPMENT & FURNISHINGS - SAFETY BELTS / TORSORESTRAINT SYSTEMS - INSPECTION / REPLACEMENT EASAAIRWORTHINESS DIRECTIVE AFTER 14 FEBRUARY 2013[THE EFFECTIVE DATE OF THE ORIGINAL ISSUE OF THISAD], DO NOT INSTALL SAFETY BELTS OR TORSORESTRAINT SYSTEMS ON ANY AIRCRAFT, UNLESSINSPECTED AND CORRECTED IN COMPLIANCE WITH THEREQUIREMENTS OF THIS AD

2013-0020 R2 (1) EQUIPMENT & FURNISHINGS - SAFETY BELTS / TORSORESTRAINT SYSTEMS - INSPECTION / REPLACEMENT EASAAIRWORTHINESS DIRECTIVE INSPECT THE MARKINGS OFSAFETY BELTS AND/OR TORSO RESTRAINT SYSTEMS, TODETERMINE IF THEY HAVE BEEN MAINTAINED ORREPAIRED BY ORGANISATIONS OTHER THAN THE DESIGNAPPROVAL HOLDER


2013-223 EQUIPMENT & FURNISHINGS - SAFETY BELTS / TORSORESTRAINT SYSTEMS- INSPECTION/REPLACEMENT ITALIAN CIVIL AVIATIONAUTHORITY

2013-01-03 TO PREVENT POWER FROM BEING SUPPLIED TOPASSENGER SEATS WHEN THE ENTERTAINMENT CONTROLSWITCH IS IN THE OFF POSITION

ACD (TWO WAY) TO

2013-19 COMMUNICATIONS - SEAT ELECTRONIC BOXES (SEBS) -MODIFICATION ITALIAN CIVIL AVIATION AUTHORITY

D-2013-047 COMMUNICATIONS - SEAT ELECTRONIC BOXES (SEBS) -MODIFICATION GERMAN AD

737-23-1302 COMMUNICATIONS - PASSENGER ENTERTAINMENTSYSTEM - AUDIO ENTERTAINMENT MULTIPLEXER POWERRELAY WIRING CHANGE SERVICE BULLETIN

2013-04-05 TO DETECT AND CORRECT CRACKS AND CORROSION OFTHE SKIN AND SURROUNDING STRUCTURE UNDER THENUMBER 3 VHF ANTENNA

PRIMARY TO

2013-04-05 PARA (H) REPAIR TO DETECT AND CORRECT CRACKS ANDCORROSION OF THE SKIN AND SURROUNDING STRUCTUREUNDER THE NUMBER 3 VHF ANTENNA IF ANY CRACK ORCORROSION IS FOUND DURING ANY INSPECTIONREQUIRED BY PARAGRAPH (G) OF THIS AD

2013-04-05 PARA (G) DO TO DETECT AND CORRECT CRACKS AND CORROSIONOF THE SKIN AND SURROUNDING STRUCTURE UNDER THENUMBER 3 VHF ANTENNA THE APPLICABLE INSPECTIONS(EXTERNAL DETAILED; EXTERNAL HIGH FREQUENCY EDDYCURRENT (HFEC); AND INTERNAL DETAILED AND HFEC)FOR CRACKS ANDCORROSION IN THE SKIN, SUPPORT, FRAMES, STRINGERS,OR ANTENNA, AS APPLICABLE

Task Relations


Model: BOEING 737-300/400/500


2013-04-05 PARA (K) TERMINATING ACTION TO DETECT AND CORRECT CRACKSAND CORROSION OF THE SKIN AND SURROUNDINGSTRUCTURE UNDER THE NUMBER 3 VHF ANTENNA FORTHE REPETITIVE INSPECTION REQUIREMENTS OFPARAGRAPH (G) OF THIS AD FOR GROUPS 1, 2, 3, 4, 6, AND7 AIRPLANES, EXCEPT AS PROVIDED BY PARAGRAPHS(J)(2) AND (J)(3) OF THIS AD

2013-04-05 PARA (G)(4) REMOVE TO DETECT AND CORRECT CRACKS ANDCORROSION OF THE SKIN AND SURROUNDING STRUCTUREUNDER THE NUMBER 3 VHF ANTENNA THE ANTENNA ORCOVER PLATE AND DO AN EXTERNAL DETAILED AND HFECINSPECTION FOR ANY CRACK OR CORROSION IN THE SKIN AND DO AN INTERNAL DETAILED AND HFEC INSPECTIONFOR ANY CRACK OR CORROSION IN THE SKIN

2013-04-05 PARA (G)(3) DO TO DETECT AND CORRECT CRACKS AND CORROSIONOF THE SKIN AND SURROUNDING STRUCTURE UNDER THENUMBER 3 VHF ANTENNA AN INTERNAL DETAILED ANDHFEC INSPECTION FOR ANY CRACK OR CORROSION IN THESKIN, ANTENNA SUPPORT STRUCTURE, SURROUNDINGFRAMES AND STRINGERS

2013-04-05 PARA (G)(2) DO TO DETECT AND CORRECT CRACKS AND CORROSIONOF THE SKIN AND SURROUNDING STRUCTURE UNDER THENUMBER 3 VHF ANTENNA AN EXTERNAL HIGH FREQUENCYEDDY CURRENT (HFEC) INSPECTION FOR ANY CRACK INTHE SKIN

2013-04-05 PARA (G)(1) DO TO DETECT AND CORRECT CRACKS AND CORROSIONOF THE SKIN AND SURROUNDING STRUCTURE UNDER THENUMBER 3 VHF ANTENNA AN EXTERNAL DETAILEDINSPECTION FOR ANY CRACK IN THE SKIN

2013-04-05 PARA (L) REPLACEMENT TO DETECT AND CORRECT CRACKS ANDCORROSION OF THE SKIN AND SURROUNDING STRUCTUREUNDER THE NUMBER 3 VHF ANTENNA OF THE BONDEDSKIN PANELS WITH SOLID SKIN PANELS

2013-04-05 TO DETECT AND CORRECT CRACKS AND CORROSION OFTHE SKIN AND SURROUNDING STRUCTURE UNDER THENUMBER 3 VHF ANTENNA

ACD (TWO WAY) TO

D-2013-098 FUSELAGE - SKIN AND SURROUNDING STRUCTURE 3 VERYHIGH FREQUENCY (VHF) ANTENNA - INSPECTIONS / REPAIRGERMAN AD

737-53A1042 R9 FUSELAGE - LOWER LOBE HOT-BONDED SKIN PANELINSPECTION, REPAIR, AND PANEL REPLACEMENT SERVICEBULLETIN

2013-61 FUSELAGE - SKIN AND SURROUNDING STRUCTURE 3 VERYHIGH FREQUENCY (VHF) ANTENNA - INSPECTIONS/REPAIRITALIAN CIVIL AVIATION AUTHORITY

Task Relations


Model: BOEING 737-300/400/500


1990-06-02 PREVENT STRUCTURAL FAILURE 737-53-1287 R1 FUSELAGE - SKIN - SKIN CRACKING UNDER THE NUMBER 3

VHF ANTENNA - INSPECTION, REPAIR AND PREVENTIVEMODIFICATION SERVICE BULLETIN

2013-09-01 DETECT AND CORRECT CRACKING OF THE FUSELAGE LAPJOINTS

PRIMARY TO2013-09-01 PARA (G) PERFORM DETECT AND CORRECT CRACKING OF THE

FUSELAGE LAP JOINTS EXTERNAL EDDY CURRENTINSPECTION FOR CRACKING IN THE CROWN LAP JOINTS,EXCEPT AS PROVIDED BY PARAGRAPHS (H) AND (J) OFTHIS AD

2013-09-01 PARA (K) ACCOMPLISHMENT DETECT AND CORRECT CRACKING OFTHE FUSELAGE LAP JOINTS OF A REPAIR/MODIFICATIONOF A CROWN LAP JOINT, TERMINATES THE INSPECTIONSREQUIRED BY PARAGRAPHS (G) AND (I) OF THIS AD FORTHE REPAIRED & MODIFIED AREA ONLY

2013-09-01 PARA (J) PERFORM DETECT AND CORRECT CRACKING OF THEFUSELAGE LAP JOINTS AN OPEN-HOLE INSPECTION FORCRACKING AT THE TEAR STRAP LOCATIONS, AS AN OPTIONTO CONFIRM CRACKS FOUND AT TEAR STRAP LOCATIONSWHILE DOING THE INSPECTIONS REQUIRED BYPARAGRAPH (G) OR (I) OF THIS AD

2013-09-01 PARA (I) PERFORM DETECT AND CORRECT CRACKING OF THEFUSELAGE LAP JOINTS AN INTERNAL MFEC, LOWFREQUENCY EDDY CURRENT (LFEC), AND DETAILEDINSPECTION FOR CRACKING IN THE CROWN LAP JOINTSAND STRINGER CLIPS, EXCEPT AS PROVIDED BYPARAGRAPH (J) OF THIS AD

2013-09-01 PARA (H) PERFORM DETECT AND CORRECT CRACKING OF THEFUSELAGE LAP JOINTS AN INTERNAL MID-FREQUENCYEDDY CURRENT (MFEC) INSPECTION FOR CRACKING INTHE LAP JOINT FASTENER ROW BETWEEN TEAR STRAPSOF THE CROWN LAP AND DO A DETAILED INSPECTION OFTHE LAP JOINT LOWER FASTENER ROW FOR CRACKING, ASAN OPTION TO CONFIRM CRACKS FOUND BETWEEN TEARSTRAPS DURING THE INSPECTIONS REQUIRED BYPARAGRAPH (G) OF THIS AD

2013-09-01 DETECT AND CORRECT CRACKING OF THE FUSELAGE LAPJOINTS

ACD (TWO WAY) TO737-53A1255 R2 FUSELAGE - SKIN - CROWN SKIN LAP JOINT - INSPECTION

FOR LOWER ROW CRACKING AT STRINGERS S-4, S-10, S-14BETWEEN STA 360 AND STA 908 SERVICE BULLETIN

2013-167 FUSELAGE - STRINGER S-4L AND S-4R LAP JOINTS ANDSTRINGER CLIPS BETWEEN BODY STATION(BS) 540 AND BS727 - INSPECTIONS/ REPAIR ITALIAN CIVIL AVIATIONAUTHORITY

Task Relations


Model: BOEING 737-300/400/500


737-53A1177 R6 FUSELAGE - SKIN - REPAIR METHODS FOR CRACKS INLOWER SKINS AT LAP JOINTS (SUPERSEDED BY SB737-53A1177 R7) SERVICE BULLETIN

2002-07-08 FIND AND FIX CRACKING OF CERTAIN FUSELAGE LAPJOINTS


D-2003-172 R2 FUSELAGE - SKIN - CROWN LAP JOINTS AND STRINGERCLIPS - INSPECTIONS FOR LOWER ROW CRACKING /REPAIR GERMAN AD

F-2003-184 IMP R1 (B) FUSELAGE - CRIQUES JOINTS DE RECOUVREMENT(REPLACED BY FAA AD 2013-09-01) CONSIGNE DENAVIGABILITE (DGAC)

AD/B737/213 FUSELAGE LAP JOINTS (SUPERSEDED BY FAA AD2013-09-01) CIVIL AVIATION SAFETY AUTHORITY -AUSTRALIA

2013-09-02 DETECT AND CORRECT CRACKING AND DAMAGE IN THEFLAP TRACK

PRIMARY TO2013-09-02 PARA (R) - DETECT AND CORRECT CRACKING AND DAMAGE IN THE

FLAP TRACK NEW REPLACEMENT - REPLACE THE FLAPTRACK ASSEMBLY HAVING P/N 65-46428-31 OR 65-46428-33,WITH A NEW OR SERVICEABLE FLAP TRACK ASSEMBLY

2013-09-02 PARA (W) DO NOT INSTALL DETECT AND CORRECT CRACKING ANDDAMAGE IN THE FLAP TRACK A FLAP TRACK ASSEMBLY,P/N 65-46428-31 OR 65-46428-33, ON ANY AIRPLANE

2013-09-02 PARA (S) - DETECT AND CORRECT CRACKING AND DAMAGE IN THEFLAP TRACK NEW - INSPECTIONS OF FLAP-TO-WINGATTACHMENT IF REPAIRS ARE DONE OR IF NO DAMAGE ISFOUND IN FLAP TRACK WEB AND FLANGES - DO THEINSPECTIONS SPECIFIED IN PARAGRAPHS (S)(1) THROUGH(S)(4) OF THIS AD, AND DO ALL APPLICABLE RELATEDINVESTIGATIVE AND CORRECTIVE ACTIONS

2013-09-02 PARA (T) - DETECT AND CORRECT CRACKING AND DAMAGE IN THEFLAP TRACK NEW OVERHAUL - DO AN OVERHAUL OF THEFLAP TRACK

2013-09-02 PARA (P) &(Q)

- DETECT AND CORRECT CRACKING AND DAMAGE IN THEFLAP TRACK NEW INSPECTION OF FLAP TRACK WEB ANDFLANGES - DO THE INSPECTIONS SPECIFIED INPARAGRAPHS (P)(1), (P)(2), (P)(3), AND (P)(4) OF THIS AD,AND DO ALL APPLICABLE CORRECTIVE ACTIONS.PERFORMING THESE INSPECTIONS TERMINATES THEREQUIREMENTS OF PARAGRAPHS (G), (J), (L), (M), AND (N)OF THIS AD.

Task Relations


Model: BOEING 737-300/400/500


2013-09-02 PARA (O) - DETECT AND CORRECT CRACKING AND DAMAGE IN THEFLAP TRACK RETAINED REPAIR - CONTACT BOEING FORAPPROPRIATE ACTION, IF ANY DISCREPANCY IS FOUNDDURING ANY ACTION REQUIRED BY PARAGRAPH (J), (L), OR(M) OF THIS AD & REPAIR ACCORDING TO A METHODAPPROVED BY THE MANAGER, SEATTLE ACO, FAA; ORACCORDING TO DATA MEETING THE TYPE CERTIFICATIONBASIS OF THE AIRPLANE APPROVED BY A BOEING DER ORBOEING COMPANY ODA, IF ANY DISCREPANCY IS FOUNDDURING INSPECTIONS ACCORDING TO PARAGRAPH (N) OFTHIS AD

2013-09-02 PARA (N) - DETECT AND CORRECT CRACKING AND DAMAGE IN THEFLAP TRACK RETAINED REPETITIVE INSPECTIONS -DETAILED VISUAL, HFEC, AND ULTRASONIC INSPECTIONSFOR CRACKING IN THE UPPER FLANGE OF THE INBOARDTRACK OF EACH OUTBOARD FLAP AT THE REAR SPARATTACHMENTS

2013-09-02 PARA (M) - DETECT AND CORRECT CRACKING AND DAMAGE IN THEFLAP TRACK RETAINED REWORK - REWORK OF THE FLAPTRACK ASSEMBLY AND AFT FLAP TRACK ATTACHMENTS &REPLACEMENT OF THE FLAP TRACKS, AS APPLICABLE

2013-09-02 PARA (J) (1) &(L)

PERFORM DETECT AND CORRECT CRACKING ANDDAMAGE IN THE FLAP TRACK A DETAILED VISUALINSPECTION FOR DISCREPANCIES (E.G., CORROSION, ORMISSING, DAMAGED, OR MIGRATED ANTI-FRET STRIPS ANDTAPERED SHIMS) OF THE REAR SPAR ATTACHMENTS OFTHE FLAP TRACKS

2013-09-02 PARA (U) - DETECT AND CORRECT CRACKING AND DAMAGE IN THEFLAP TRACK NEW POST-OVERHAUL INSPECTIONS - DOTHE INSPECTIONS SPECIFIED IN PARAGRAPH (P) OF THISAD.

2013-09-02 PARA (J) (2) &(L)

PERFORM DETECT AND CORRECT CRACKING ANDDAMAGE IN THE FLAP TRACK DETAILED VISUAL, HIGHFREQUENCY EDDY CURRENT (HFEC), AND ULTRASONICINSPECTIONS FOR CRACKING IN THE UPPER FLANGE OFTHE INBOARD TRACK OF EACH OUTBOARD FLAP AT THEREAR SPAR ATTACHMENTS

2013-09-02 DETECT AND CORRECT CRACKING AND DAMAGE IN THEFLAP TRACK

ACD (TWO WAY) TO2013-187 CANCELLATION NOTICE - ENAC 2002-203 IS CANCELLED &

REPLACED BY ENAC 2013-186 ITALIAN CIVIL AVIATIONAUTHORITY

F-2002-195-IMP R1 TRAILING EDGE FLAPS (VOLETS DE BORD DE FUITE)(REPLACED BY FAA AD 2013-09-02) CONSIGNE DENAVIGABILITE (DGAC)

Task Relations


Model: BOEING 737-300/400/500


F-2001-025-IMP R1 FIXING TRAILING EDGE FLAPS (FIXATION VOLETS DE BORDDE FUITE) (REPLACED BY FAA 2013-09-02) CONSIGNE DENAVIGABILITE (DGAC)

D-2003-053 R1 WINGS - OUTBOARD FLAP INBOARD TRACKS - INSPECTIONS/ REPAIR / OVERHAUL / REPLACEMENT GERMAN AD

737-57-1203 WINGS - TRAILING EDGE FLAPS - FLAP TRACKREPLACEMENT SERVICE BULLETIN

737-57A1249 R2 WING - OUTBOARD FLAP TRACKS - INSPECTION ANDMODIFICATION OF THE REAR SPAR ATTACHMENTS AT WBL254 (REPLACED BY SB 737-57A1271 R3) SERVICE BULLETIN


AD/B737/181 AMDT 1 FLAP TRACK ASSEMBLY AND REAR SPAR ATTACHMENTS(SUPERSEDED BY FAA AD 2013-09-02) CIVIL AVIATIONSAFETY AUTHORITY - AUSTRALIA

AD/B737/262 AMDT 1 WING OUTBOARD FLAP INBOARD FLAP TRACK(SUPERSEDED BY FAA AD 2013-09-02) CIVIL AVIATIONSAFETY AUTHORITY - AUSTRALIA

2013-186 WINGS - FLAP TRACKS - INSPECTIONS/REPAIR ITALIANCIVIL AVIATION AUTHORITY

2013-09-08 REPETITIVE OPERATIONAL TESTS OF THE ENGINE FUELSUCTION FEED OF THE FUEL SYSTEM, AND CORRECTIVEACTIONS

ACD (TWO WAY) TO

D-2013-165 [CORRECTION] FUEL SYSTEM - ENGINE FUEL SUCTIONFEED - OPERATIONAL TESTS GERMAN AD

2013-195 FUEL SYSTEM - ENGINE FUEL SUCTION FEED -OPERATIONAL TESTS ITALIAN CIVIL AVIATION AUTHORITY

737-28A1307 FUEL - ENGINE FUEL FEED SYSTEM - ENGINE FUELSUCTION FEED OPERATIONAL TEST SERVICE BULLETIN

2013-09-10 TO PREVENT FATIGUE CRACKING OF THE LOWERCORNERS OF THE DOOR FRAME AND NUMBER 5 CROSSBEAM OF THE FORWARD CARGO DOOR

PRIMARY TO

2013-09-10 PARA (J) INSTALL TO PREVENT FATIGUE CRACKING OF THE LOWERCORNERS OF THE DOOR FRAME AND NUMBER 5 CROSSBEAM OF THE FORWARD CARGO DOOR THEREINFORCEMENT MODIFICATION OF THE AFT CORNER OFTHE DOOR FRAME OF THE FORWARD CARGO DOOR

Task Relations


Model: BOEING 737-300/400/500


2013-09-10 PARA (K)(1) PERFORM TO PREVENT FATIGUE CRACKING OF THELOWER CORNERS OF THE DOOR FRAME AND NUMBER 5CROSS BEAM OF THE FORWARD CARGO DOOR AONE-TIME HFEC INSPECTION OF THE APPLICABLELOCATION FOR CRACKS

2013-09-10 PARA (G)(2) REPAIR/REPLACE TO PREVENT FATIGUE CRACKING OFTHE LOWER CORNERS OF THE DOOR FRAME AND NUMBER5 CROSS BEAM OF THE FORWARD CARGO DOOR /MODIFYTHE DOOR FRAME OF THE FORWARD CARGO DOOR, IF ANYCRACKING IS DETECTED DURING ANY INSPECTIONREQUIRED BY PARAGRAPH (G) OF THIS AD

2013-09-10 PARA (H)(2) REPAIR TO PREVENT FATIGUE CRACKING OF THE LOWERCORNERS OF THE DOOR FRAME AND NUMBER 5 CROSSBEAM OF THE FORWARD CARGO DOOR IN ACCORDANCEWITH A APPROVED METHOD, IF ANY CRACKING ISDETECTED ON THE LOWER CHORD SECTION OF THECROSS BEAM DURING ANY INSPECTION REQUIRED BYPARAGRAPH (H) OF THIS AD

2013-09-10 PARA (H)(3) INSTALL TO PREVENT FATIGUE CRACKING OF THE LOWERCORNERS OF THE DOOR FRAME AND NUMBER 5 CROSSBEAM OF THE FORWARD CARGO DOOR A CROSS BEAMREPAIR AND PREVENTATIVE MODIFICATION OF THEOUTBOARD RADIUS OF THE LOWER CORNERS (FORWARDAND AFT) OF THE DOOR FRAME, IF ANY CRACKING ISDETECTED ON ANY AREA EXCLUDING THE LOWER CHORDSECTION OF THE CROSS BEAM (I.E., UPPER CHORD ANDWEB SECTION) DURING ANY INSPECTION REQUIRED BYPARAGRAPH (H) OF THIS AD

2013-09-10 PARA (K)(2) PERFORM TO PREVENT FATIGUE CRACKING OF THELOWER CORNERS OF THE DOOR FRAME AND NUMBER 5CROSS BEAM OF THE FORWARD CARGO DOOR AONE-TIME GENERAL VISUAL INSPECTION OF THEREINFORCEMENT ANGLE FOR EXCESSIVE SHIMMING ORFASTENER PULL-UP

2013-09-10 PARA (H) PERFORM TO PREVENT FATIGUE CRACKING OF THELOWER CORNERS OF THE DOOR FRAME AND NUMBER 5CROSS BEAM OF THE FORWARD CARGO DOOR ADETAILED INSPECTION TO DETECT CRACKING OF THECROSS BEAM (I.E., UPPER AND LOWER CHORD AND WEBSECTIONS) OF THE FORWARD CARGO DOOR

2013-09-10 PARA (G) PERFORM TO PREVENT FATIGUE CRACKING OF THELOWER CORNERS OF THE DOOR FRAME AND NUMBER 5CROSS BEAM OF THE FORWARD CARGO DOOR AN HFECINSPECTION TO DETECT CRACKING OF THE LOWERCORNERS (FORWARD AND AFT) OF THE DOOR FRAME OFTHE FORWARD CARGO DOOR

Task Relations


Model: BOEING 737-300/400/500


2013-09-10 PARA (I) INSTALL TO PREVENT FATIGUE CRACKING OF THE LOWERCORNERS OF THE DOOR FRAME AND NUMBER 5 CROSSBEAM OF THE FORWARD CARGO DOOR THEPREVENTATIVE MODIFICATION OF THE OUTBOARD RADIUSOF THE LOWER CORNERS (FORWARD AND AFT) OF THEDOOR FRAME AND THE REINFORCEMENT MODIFICATIONOF THE CROSS BEAM OF THE FORWARD CARGO DOOR.ACCOMPLISHMENT OF PARAGRAPH (I)(1) OR (I)(2) OF THISAD, AS APPLICABLE, CONSTITUTES TERMINATING ACTIONFOR THE REPETITIVE INSPECTIONS REQUIRED BYPARAGRAPHS (G)(1) AND (H)(1) OF THIS AD.

2013-09-10 TO PREVENT FATIGUE CRACKING OF THE LOWERCORNERS OF THE DOOR FRAME AND NUMBER 5 CROSSBEAM OF THE FORWARD CARGO DOOR

ACD (TWO WAY) TO

2013-185 DOORS - FORWARD CARGO DOOR -INSPECTIONS/REPAIR/INSTALLATION ITALIAN CIVILAVIATION AUTHORITY

F-2000-196-IMP R1 FORWARD CARGO DOOR (PORTE DE SOUTE AVANT)(REPLACED BY FAA AD 2013-09-10) CONSIGNE DENAVIGABILITE (DGAC)

D-2000-161 R1 DOORS - FORWARD CARGO DOOR - LOWER CORNERS ANDCROSS BEAMS - INSPECTIONS / REPAIR / MODIFICATIONGERMAN AD

737-52-1100 R4 DOORS - FORWARD CARGO - LOWER FORWARD AND AFTCORNER INSPECTION MODIFICATION, AND REPLACEMENTSERVICE BULLETIN

737-52-1149 DOORS - FORWARD CARGO DOOR - NUMBER 4 CROSSBEAM INSPECTION, REPAIR AND PREVENTATIVEMODIFICATION SERVICE BULLETIN


2013-13-12 PREVENT FATIGUE CRACKING OF THE CORNERS OF THEDOOR FRAME AND THE CROSS BEAMS OF THE AFT CARGODOOR

PRIMARY TO

2013-13-12 PARA (T) ACCOMPLISH PREVENT FATIGUE CRACKING OF THECORNERS OF THE DOOR FRAME AND THE CROSS BEAMSOF THE AFT CARGO DOOR A ONE-TIME INSPECTION OFTHE FRAME AND A DETAILED INSPECTION OF THEREINFORCING ANGLE FOR CRACKS OF THE FORWARD ANDAFT ENDS OF CROSS BEAM E / APPLICABLE INVESTIGATIVEAND CORRECTIVE ACTIONS (IF A DOOR IS DETERMINED TOBE FROM AN AIRPLANE HAVING LINE NUMBERS 874 ANDSUBSEQUENT)

Task Relations


Model: BOEING 737-300/400/500


2013-13-12 PARA (L) MODIFY PREVENT FATIGUE CRACKING OF THE CORNERSOF THE DOOR FRAME AND THE CROSS BEAMS OF THE AFTCARGO DOOR THE FOUR CORNERS OF THE DOOR FRAMEAND THE CROSS BEAMS OF THE AFT CARGO DOOR FORAIRPLANES IDENTIFIED INPARAGRAPH (G) OF THIS AD. MODIFICATION CONSTITUTESTERMINATING ACTION FOR THE REPETITIVE INSPECTIONREQUIREMENTS OF PARAGRAPH (H) AND (K) (FORAIRPLANES IDENTIFIED IN PARAGRAPH (G))

2013-13-12 PARA (H)(3) REPAIR PREVENT FATIGUE CRACKING OF THE CORNERSOF THE DOOR FRAME AND THE CROSS BEAMS OF THE AFTCARGO DOOR THE FRAME AND MODIFY THE CORNERS OFTHE DOOR FRAME OF THE AFT CARGO DOOR, IF ANYCRACKING IS DETECTED IN THE FORWARD OR AFT UPPERDOOR FRAME

2013-13-12 PARA (H)(2) MODIFY PREVENT FATIGUE CRACKING OF THE CORNERSOF THE DOOR FRAME AND THE CROSS BEAMS OF THE AFTCARGO DOOR THE CRACKED BEAM, IF ANY CRACKING ISDETECTED IN THE UPPER OR LOWER CROSS BEAMS

2013-13-12 PARA (S) ACCOMPLISH PREVENT FATIGUE CRACKING OF THECORNERS OF THE DOOR FRAME AND THE CROSS BEAMSOF THE AFT CARGO DOOR HIGH FREQUENCY ANDDETAILED INSPECTION FOR CRACKS IN THE FORWARD ANDAFT ENDS OF CROSS BEAM E / APPLICABLE INVESTIGATIVE& CORRECTIVE ACTIONS / ACCOMPLISH MODIFICATION (IFA DOOR IS DETERMINED TO BE FROM AN AIRPLANE HAVINGLINE NUMBERS 874 AND SUBSEQUENT)

2013-13-12 PARA (H)(1) PERFORM PREVENT FATIGUE CRACKING OF THECORNERS OF THE DOOR FRAME AND THE CROSS BEAMSOF THE AFT CARGO DOOR AN INTERNAL DETAILED VISUALINSPECTION TO DETECT CRACKING OF THE CORNERS OFTHE DOOR FRAME AND THE CROSS BEAMS OF THE AFTCARGO DOOR

2013-13-12 PARA (J) ACCOMPLISH PREVENT FATIGUE CRACKING OF THECORNERS OF THE DOOR FRAME AND THE CROSS BEAMSOF THE AFT CARGO DOOR REPAIR, IF ANY CRACKING OFTHE OUTER CHORD OF THE UPPER OR LOWER CROSSBEAMS OF THE AFT CARGO DOOR IS DETECTED DURINGANY INSPECTION REQUIRED BY PARAGRAPH (H)

2013-13-12 PARA (K) PERFORM PREVENT FATIGUE CRACKING OF THECORNERS OF THE DOOR FRAME AND THE CROSS BEAMSOF THE AFT CARGO DOOR A HIGH FREQUENCY EDDYCURRENT INSPECTION (HFEC) TO DETECT CRACKING OFTHE FOUR CORNERS OF THE DOOR FRAME OF THE AFTCARGO DOOR / REPLACE THE DAMAGED FRAME ANDMODIFY THE FOUR CORNERS (FOR AIRPLANES IDENTIFIEDIN PARAGRAPH (G))

Task Relations


Model: BOEING 737-300/400/500


2013-13-12 PARA (H)(4) REPLACE PREVENT FATIGUE CRACKING OF THE CORNERSOF THE DOOR FRAME AND THE CROSS BEAMS OF THE AFTCARGO DOOR THE DAMAGED FRAME WITH A NEW FRAME,AND MODIFY THE CORNERS OF THE DOOR FRAME OF THEAFT CARGO DOOR, IF ANY CRACKING IS DETECTED IN THEFORWARD OR AFT LOWER DOOR FRAME

2013-13-12 PARA (O) INSPECT PREVENT FATIGUE CRACKING OF THE CORNERSOF THE DOOR FRAME AND THE CROSS BEAMS OF THE AFTCARGO DOOR TO DETERMINE THE CONFIGURATION OFTHE AFT CARGO DOOR

2013-13-12 PARA (P) ACCOMPLISH PREVENT FATIGUE CRACKING OF THECORNERS OF THE DOOR FRAME AND THE CROSS BEAMSOF THE AFT CARGO DOOR A ONE-TIME HFEC AND AONE-TIME ULTRASONIC INSPECTION FOR CRACKING OFTHE UPPER AND LOWER CORNER FRAMES AND THE UPPERAND LOWER CROSS BEAMS AND ACCOMPLISH ALLAPPLICABLE RELATED INVESTIGATIVE AND CORRECTIVEACTIONS (IF ANY DOOR IS DETERMINED TO BE FROM ANYAIRPLANE HAVING LINE NUMBERS 6 THROUGH 873INCLUSIVE, AND NEITHER MODIFICATION NOR REPAIRSPECIFIED HAS BEEN DONE)

2013-13-12 PARA (Q) INSPECT PREVENT FATIGUE CRACKING OF THE CORNERSOF THE DOOR FRAME AND THE CROSS BEAMS OF THE AFTCARGO DOOR THE LOWER CORNERS FRAMES TODETERMINE IF THE DOOR HAS REINFORCEMENT ANGLES,P/N 65C25180-9, -43, -10, -11, OR -12 THAT WERE INSTALLEDAS SPECIFIED IN ANY SB / ACCOMPLISH ONE TIME DVI FOREDGE MARGIN AND ACCOMPLISH A DETAILED INSPECTIONFOR CRACKS (IF ANY DOOR IS DETERMINED TO BE FROMANY AIRPLANE HAVING LINE NUMBERS 6 THROUGH 873INCLUSIVE)

2013-13-12 PARA (R) REPLACE PREVENT FATIGUE CRACKING OF THE CORNERSOF THE DOOR FRAME AND THE CROSS BEAMS OF THE AFTCARGO DOOR THE CORNER REINFORCEMENT ANGLE /ONE-TIME DETAILED INSPECTION OR HFEC INSPECTIONFOR CRACKING AT THE FORWARD AND AFT ENDS OFCROSS BEAM D / APPLICABLE REPAIRS / ONE-TIMEDETAILED INSPECTION OR ULTRASONIC INSPECTION FORCRACKING ON THE FRAMES / REPLACE THE FRAME (IF ANYCRACK FOUND DURING ANY INSPECTION REQUIRED BYPARAGRAPH (Q), OR IF ANY EDGE MARGIN DOES NOT MEETTHE SPECIFICATION)

2013-13-12 PREVENT FATIGUE CRACKING OF THE CORNERS OF THEDOOR FRAME AND THE CROSS BEAMS OF THE AFT CARGODOOR

ACD (TWO WAY) TO

AD/B737/124 AMDT 2 AFT CARGO DOOR FRAME AND CROSS BEAMS(SUPERSEDED BY FAA AD 2013-13-12) CIVIL AVIATIONSAFETY AUTHORITY - AUSTRALIA

Task Relations


Model: BOEING 737-300/400/500




737-52-1154 R1 DOORS - CARGO COMPARTMENT DOORS - AFT CARGODOOR - CROSS BEAM D INSPECTION, REPAIR ANDPREVENTIVE MODIFICATION SERVICE BULLETIN

2013-13-15 PREVENT FOREIGN OBJECT PENETRATION OF THE WINGTANK

PRIMARY TO2013-13-15 PARA (G) GENERAL VISUAL INSPECTION PREVENT FOREIGN OBJECT

PENETRATION OF THE WING TANK OF THE LEFT-WING ANDRIGHT-WING FUEL TANK ACCESS DOORS TO DETERMINETHAT IMPACT-RESISTANT ACCESS DOORS ARE INSTALLEDIN THE CORRECT LOCATIONS, AND AN INSPECTION FORPROPER APPLICATION OF STENCILS AND INDEX MARKERSOF IMPACT-RESISTANT ACCESS DOORS, AND ACCOMPLISHALL APPLICABLE CORRECTIVE ACTIONS

2013-13-15 PARA (H) REVISE PREVENT FOREIGN OBJECT PENETRATION OF THEWING TANK THE MAINTENANCE PROGRAM TOINCORPORATE AIRWORTHINESS LIMITATION (AWL)57-AWL-01, IMPACT-RESISTANT FUEL ACCESS DOORS

2013-13-15 PREVENT FOREIGN OBJECT PENETRATION OF THE WINGTANK

ACD (TWO WAY) TOD-1987-096 R1 FUEL - LEFT WING AND RIGHT - WINGFUEL TANK ACCESS

DOORS - INSPECTION / REPLACEMENT GERMAN AD 2013-250 FUEL - LEFT WING AND RIGHT WING FUEL TANK ACCESS

DOORS - INSPECTION/REPLACEMENT ITALIAN CIVILAVIATION AUTHORITY

737-28-1286 FUEL - INTEGRAL FUEL TANKS - ACCESS DOORINSPECTION/REPLACEMENT SERVICE BULLETIN

2013-15-14 TO PREVENT LOOSE OR MISSING PARTS IN THE MAIN SLATTRACK DOWNSTOP ASSEMBLIES

PRIMARY TO2013-15-14 PARA (G) DETAILED INSPECTION TO PREVENT LOOSE OR MISSING

PARTS IN THE MAIN SLAT TRACK DOWNSTOP ASSEMBLIES OR BORESCOPE INSPECTION OF THE DOWNSTOPASSEMBLIES ON THE MAIN TRACKS OF THE NO. 2, 3, 4, AND5 SLATS AND THE INBOARD TRACK OF THE NO. 1 AND 6SLATS TO VERIFY IF ANY PARTS ARE MISSING, DAMAGED,OR INSTALLED IN THE WRONG ORDER AND DO ALL THEOTHER SPECIFIED, RELATED INVESTIGATIVE, ANDCORRECTIVE ACTIONS

Task Relations


Model: BOEING 737-300/400/500


2013-15-14 PARA (H) PERFORM TO PREVENT LOOSE OR MISSING PARTS IN THEMAIN SLAT TRACK DOWNSTOP ASSEMBLIES ONE-TIMEDETAILED INSPECTION OF THE SLAT CAN INTERIOR TODETECT FOREIGN OBJECT DEBRIS (FOD) & REMOVE THEDETECTED FOD

2013-15-14 PARA (I) MODIFY TO PREVENT LOOSE OR MISSING PARTS IN THEMAIN SLAT TRACK DOWNSTOP ASSEMBLIES THE SLATTRACK HARDWARE BY INSTALLING NEW DOWNSTOPASSEMBLY HARDWARE, AND DO A DETAILED INSPECTIONFOR FOD AND A ONE-TIME INSPECTION FOR DAMAGE TOTHE INTERIOR SURFACE OF THE SLAT CAN FOR THEINBOARD AND OUTBOARD TRACKS OF SLATS 2 THROUGH5, AND THE INBOARD SLATS OF TRACKS 1 AND 6 AND DOALL APPLICABLE RELATED INVESTIGATIVE ANDCORRECTIVE ACTIONS

2013-15-14 TO PREVENT LOOSE OR MISSING PARTS IN THE MAIN SLATTRACK DOWNSTOP ASSEMBLIES

ACD (TWO WAY) TO737-57A1301 R3 WINGS - FLIGHT SURFACES - LEADING EDGE SLATS - MAIN

TRACK DOWNSTOP ASSEMBLY INSPECTION ANDMODIFICATION SERVICE BULLETIN

AD/B737/318 MAIN SLAT TRACK DOWNSTOP ASSEMBLIES (SUPERSEDEDBY FAA AD 2013-15-14) CIVIL AVIATION SAFETY AUTHORITY -AUSTRALIA

21-018-01 (001.0) LEFT PRIMARY HEAT EXCHANGER PRIMARY TO21-018-01 (001.1) RESTORE LEFT PRIMARY HEAT EXCHANGER

21-018-01 (002.0) RIGHT PRIMARY HEAT EXCHANGER PRIMARY TO21-018-01 (002.1) RESTORE RIGHT PRIMARY HEAT EXCHANGER

21-018-01 (003.0) LEFT SECONDARY HEAT EXCHANGER PRIMARY TO21-018-01 (003.1) RESTORE LEFT SECONDARY HEAT EXCHANGER

21-018-01 (004.0) RIGHT SECONDARY HEAT EXCHANGER PRIMARY TO21-018-01 (004.1) RESTORE RIGHT SECONDARY HEAT EXCHANGER

23-003-01 (001.0) AUTOMATIC/FIXED TYPE EMERGENCY LOCATORTRANSMITER

PRIMARY TO23-003-01 (001.1) DISCARD AUTOMATIC/FIXED TYPE EMERGENCY LOCATOR

TRANSMITER BATTERY 23-012-01 (001.0) (CVR) UNDERWATER LOCATOR BEACON (ULB)

BATTERY PRIMARY TO

23-012-01 (001.1) DISCARD (CVR) UNDERWATER LOCATOR BEACON (ULB) BATTERY

23-CVR-01 (001.0) CVR - COCKPIT VOICE RECORDER PRIMARY TO31-CVR-01 (001.1) FUNCTIONAL CHECK CVR - COCKPIT VOICE RECORDER .

MAKE A RECORDING TO BE EVALUATED FOR ACCEPTABLEPERFORMANCE.

24-014-01 (001.0) NO.1 ENGINE GENERATOR CONTROL UNIT PRIMARY TO

Task Relations


Model: BOEING 737-300/400/500



24-014-01 (002.0) NO.2 ENGINE GENERATOR CONTROL UNIT PRIMARY TO24-014-01 (002.1) FUNCTIONALLY CHECK NO.2 ENGINE GENERATOR

CONTROL UNIT (OFF-AIRCRAFT) PER MANUFACTURER'SCOMPONENT MAINTENANCE MANUAL

24-014-01 (003.0) APU GENERATOR CONTROL UNIT PRIMARY TO24-014-01 (003.1) FUNCTIONALLY CHECK APU GENERATOR CONTROL UNIT

(OFF-AIRCRAFT) PER MANUFACTURER'S COMPONENTMAINTENANCE MANUAL

24-026-01 (001.0) STANDBY POWER STORAGE BATTERY PRIMARY TO24-026-01 (001.1) RESTORE STANDBY POWER STORAGE BATTERY

25-040-01 (001.0) LEFT FORWARD EMERGENCY ESCAPE SLIDE PRIMARY TO25-040-01 (001.1) RESTORE LEFT FORWARD EMERGENCY ESCAPE SLIDE

25-040-01 (001.0) LEFT FORWARD EMERGENCY ESCAPE SLIDE ACD (TWO WAY) TO25-048-01 (001.0) LEFT FORWARD EMERGENCY ESCAPE EMERGENCY

ESCAPE SLIDE LIGHTING SYSTEM BATTERY 8-25-02 (001.0) FORWARD LEFT - ESCAPE SLIDE AIR BOTTLE

25-040-01 (002.0) RIGHT FORWARD EMERGENCY ESCAPE SLIDE PRIMARY TO25-040-01 (002.1) RESTORE RIGHT FORWARD EMERGENCY ESCAPE SLIDE

25-040-01 (002.0) RIGHT FORWARD EMERGENCY ESCAPE SLIDE ACD (TWO WAY) TO8-25-02 (002.0) FORWARD RIGHT - ESCAPE SLIDE AIR BOTTLE 25-048-01 (002.0) RIGHT FORWARD EMERGENCY ESCAPE EMERGENCY

ESCAPE SLIDE LIGHTING SYSTEM BATTERY 25-040-01 (003.0) LEFT AFT EMERGENCY ESCAPE SLIDE PRIMARY TO

25-040-01 (003.1) RESTORE LEFT AFT EMERGENCY ESCAPE SLIDE 25-040-01 (003.0) LEFT AFT EMERGENCY ESCAPE SLIDE ACD (TWO WAY) TO

8-25-02 (003.0) AFT LEFT - ESCAPE SLIDE AIR BOTTLE 25-048-01 (003.0) LEFT AFT EMERGENCY ESCAPE EMERGENCY ESCAPE

SLIDE LIGHTING SYSTEM BATTERY 25-040-01 (004.0) RIGHT AFT EMERGENCY ESCAPE SLIDE PRIMARY TO

25-040-01 (004.1) RESTORE RIGHT AFT EMERGENCY ESCAPE SLIDE 25-040-01 (004.0) RIGHT AFT EMERGENCY ESCAPE SLIDE ACD (TWO WAY) TO

8-25-02 (004.0) AFT RIGHT - ESCAPE SLIDE AIR BOTTLE 25-048-01 (004.0) RIGHT AFT EMERGENCY ESCAPE EMERGENCY ESCAPE

SLIDE LIGHTING SYSTEM BATTERY 25-048-01 (001.0) LEFT FORWARD EMERGENCY ESCAPE EMERGENCY

ESCAPE SLIDE LIGHTING SYSTEM BATTERY PRIMARY TO

25-048-01 (001.1) DISCARD LEFT FORWARD EMERGENCY ESCAPEEMERGENCY ESCAPE SLIDE LIGHTING SYSTEM BATTERY

Task Relations


Model: BOEING 737-300/400/500


25-048-01 (002.0) RIGHT FORWARD EMERGENCY ESCAPE EMERGENCYESCAPE SLIDE LIGHTING SYSTEM BATTERY

PRIMARY TO25-048-01 (002.1) DISCARD RIGHT FORWARD EMERGENCY ESCAPE

EMERGENCY ESCAPE SLIDE LIGHTING SYSTEM BATTERY 25-048-01 (003.0) LEFT AFT EMERGENCY ESCAPE EMERGENCY ESCAPE

SLIDE LIGHTING SYSTEM BATTERY PRIMARY TO

25-048-01 (003.1) DISCARD LEFT AFT EMERGENCY ESCAPE EMERGENCYESCAPE SLIDE LIGHTING SYSTEM BATTERY

25-048-01 (004.0) RIGHT AFT EMERGENCY ESCAPE EMERGENCY ESCAPESLIDE LIGHTING SYSTEM BATTERY

PRIMARY TO25-048-01 (004.1) DISCARD RIGHT AFT EMERGENCY ESCAPE EMERGENCY

ESCAPE SLIDE LIGHTING SYSTEM BATTERY 25-050-01 (001.0) LIFE VESTS PRIMARY TO

25-050-01 (001.1) RESTORE LIFE JACKET 25-052-01 (001.0) NO.1 LIFE RAFT PRIMARY TO

25-052-01 (001.1) RESTORE NO.1 LIFE RAFT 25-062-01 (001.0) FWD MEGAPHONE PRIMARY TO

25-062-01 (001.1) DISCARD FWD MEGAPHONE BATTERY 25-062-01 (002.0) AFT MEGAPHONE PRIMARY TO

25-062-01 (002.1) DISCARD NO.2 MEGAPHONE BATTERY 25-072-01 (001.0) NO.1 EMERGENCY FLASHLIGHT PRIMARY TO

25-072-01 (001.1) DISCARD NO.1 EMERGENCY FLASHLIGHT BATTERY 25-076-01 (001.0) NO.1 SMOKE HOOD PRIMARY TO

25-076-01 (001.1) RESTORE NO.1 SMOKE HOOD 25-076-01 (002.0) NO.2 SMOKE HOOD PRIMARY TO




25-076-01 (005.1) RESTORE NO.5 SMOKE HOOD 25-078-01 (001.0) NO.1 FIRST AID KIT PRIMARY TO

25-078-01 (001.1) RESTORE NO.1 FIRST AID KIT 25-078-01 (002.0) NO.2 FIRST AID KIT PRIMARY TO

25-078-01 (002.1) RESTORE NO.2 FIRST AID KIT 25-080-01 (001.0) DOCTORS FIRST AID KIT PRIMARY TO

25-080-01 (001.1) RESTORE DOCTOR MEDICAL KIT 26-012-01 (001.0) NO. 1 ENGINE FIRE EXTINGUISHING BOTTLE PRIMARY TO

26-012-01 (001.1) RESTORE NO. 1 ENGINE FIRE EXTINGUISHING BOTTLE (OFF-AIRCRAFT) BY HYDROSTATIC TEST

Task Relations


Model: BOEING 737-300/400/500


26-016-01 (001.1) FUNCTION CHECK NO. 1 ENGINE FIRE EXTINGUISHINGBOTTLE

26-012-01 (002.0) NO. 2 ENGINE FIRE EXTINGUISHING BOTTLE PRIMARY TO26-016-01 (002.1) FUNCTION CHECK NO. 2 ENGINE FIRE EXTINGUISHING

BOTTLE 26-012-01 (002.1) RESTORE NO. 2 ENGINE FIRE EXTINGUISHING BOTTLE

(OFF-AIRCRAFT) BY HYDROSTATIC TEST

26-014-01 (001.0) NO. 1 ENGINE LH1 FIRE EXTINGUISHER BOTTLE SQUIB PRIMARY TO26-014-01 (001.1) DISCARD NO. 1 ENGINE LH1 FIRE EXTINGUISHER BOTTLE

SQUIB 26-014-01 (002.0) NO. 1 ENGINE LH2 FIRE EXTINGUISHER BOTTLE SQUIB PRIMARY TO

26-014-01 (002.1) DISCARD NO. 1 ENGINE LH2 FIRE EXTINGUISHER BOTTLESQUIB

26-014-01 (003.0) NO. 2 ENGINE RH1 FIRE EXTINGUISHER BOTTLE SQUIB PRIMARY TO26-014-01 (003.1) DISCARD NO. 2 ENGINE RH1 FIRE EXTINGUISHER BOTTLE

SQUIB 26-014-01 (004.0) NO. 2 ENGINE RH2 FIRE EXTINGUISHER BOTTLE SQUIB PRIMARY TO

26-014-01 (004.1) DISCARD NO. 2 ENGINE FIRE EXTINGUISHER BOTTLE (RH) SQUIB

26-032-01 (001.0) APU FIRE BOTTLE PRIMARY TO26-032-01 (001.1) RESTORE APU FIRE BOTTLE (OFF -AIRCRAFT) BY

HYDROSTATIC TEST 26-044-01 (001.1) FUNCTION CHECK APU FIRE BOTTLE

26-034-01 (001.0) APU FIRE BOTTLE SQUIB PRIMARY TO26-034-01 (001.1) DISCARD APU FIRE BOTTLE SQUIB

26-052-01 (001.0) NO.1 LOWER LOBE CARGO CARTRIDGE (SQUIB)

PRIMARY TO26-052-01 (001.1) DISCARD NO.1 LOWER LOBE CARGO CARTRIDGE (SQUIB)

26-052-01 (002.0) NO. 1 CARGO FIRE EXTINGUISHER (RH) SQUIB PRIMARY TO26-052-01 (002.1) DISCARD NO. 1 CARGO FIRE EXTINGUISHER (RH) SQUIB

26-056-01 (001.0) CARGO COMPARTMENT FIRE BOTTLE PRIMARY TO26-058-01 (001.1) FUNCTIONAL CHECK CARGO COMPARTMENT FIRE BOTTLE 26-056-01 (001.1) RESTORE CARGO COMPARTMENT FIRE BOTTLE

(OFF-AIRCRAFT) BY HYDROSTATIC TEST 26-076-01 (001.0) COCKPIT PORTABLE HALON FIRE EXTINGUISHER PRIMARY TO

26-076-01 (001.1) RESTORE COCKPIT PORTABLE HALON FIRE EXTINGUISHER(OFF-AIRCRAFT) BY HYDROSTATIC TEST

26-076-01 (002.0) PASS CABIN FWD PORTABLE HALON FIRE EXTINGUISHER PRIMARY TO26-076-01 (002.1) RESTORE PASS CABIN FWD PORTABLE HALON FIRE

EXTINGUISHER (OFF-AIRCRAFT) BY HYDROSTATIC TEST

Task Relations


Model: BOEING 737-300/400/500


26-076-01 (003.0) PASS CABIN AFT PORTABLE HALON FIRE EXTINGUISHER PRIMARY TO26-076-01 (003.1) RESTORE PASS CABIN AFT PORTABLE HALON FIRE

EXTINGUISHER (OFF-AIRCRAFT) BY HYDROSTATIC TEST 26-088-01 (001.0) NO.1 PORTABLE WATER FIRE EXTINGUISHER PRIMARY TO

26-088-01 (001.1) RESTORE NO.1 PORTABLE WATER FIRE EXTINGUISHER 26-088-01 (002.0) NO.2 PORTABLE WATER FIRE EXTINGUISHER PRIMARY TO

26-088-01 (002.1) RESTORE NO.2 PORTABLE WATER FIRE EXTINGUISHER 27-094-01 (001.0) STABILIZER TRIM ACTUATOR PRIMARY TO

27-094-01 (001.1) RESTORE STABILIZER TRIM ACTUATOR PER THEMANUFACTURER'S COMPONENT MAINTENANCE MANUAL(DISCONNECT CLUTCH)

27-116-01 (001.1) RESTORE STABILIZER TRIM ACTUATOR PER THECOMPONENT MAINTENANCE MANUAL (PRIMARY BRAKEAND JACKSCREW INNER LOAD PATH)

27-51-23 (001.0) LEFT WING OUTBOARD FLAP OUTBOARD CARRIAGE ACD (TWO WAY) TO2012-13-07 PARA (J) DO NOT INSTALL TO DETECT AND CORRECT CORROSION

OF THE CARRIAGE SPINDLE A SERVICEABLEHVOF-COATED CARRIAGE ON AN AIRPLANE UNLESS THEACTIONS REQUIRED BY PARAGRAPH (H)(1) OF THIS AD AREDONE ON THAT CARRIAGE PRIOR TO INSTALLATION




27-51-23 (002.0) LEFT WING OUTBOARD FLAP INBOARD CARRIAGE ACD (TWO WAY) TO2012-13-07 PARA (H)CARRIAGE 2




27-51-23 (003.0) RIGHT WING OUTBOARD FLAP INBOARD CARRIAGE ACD (TWO WAY) TO

Task Relations


Model: BOEING 737-300/400/500






27-51-23 (004.0) RIGHT WING OUTBOARD FLAP OUTBOARD CARRIAGE ACD (TWO WAY) TO2010-15-08 TO DETECT AND CORRECT CRACKED, CORRODED, OR

FRACTURED CARRIAGE SPINDLES 2012-13-07 PARA (H)CARRIAGE 4



27-CMR-01 FUNCTIONALLY CHECK RUDDER MAIN PCU INTERNALLEAKAGE IN A LOADED CONDITION.

ACD (TWO WAY) TO27-036-01 FUNCTION CHECK - FUNCTIONALLY CHECK THE RUDDER

POWER CONTROL UNIT INTERNAL LEAKAGE TO INCLUDETHE POWER CONTROL UNIT IN A LOADED CONDITION.

28-AWL-01 DETAILED INSPECTION OF THE WIRE BUNDLES ROUTEDON MAIN DECK OVER THE CENTER FUEL TANK AND UNDERTHE MAIN DECK FLOOR BOARDS PER AMM 28-11-00

ACD (TWO WAY) TO

28-011-00 PERFORM A DETAILED INSPECTION OF THE WIREBUNDLES ROUTED ON THE MAIN DECK OVER THE CENTERFUEL TANK AND UNDER THE MAIN DECK FLOOR BOARDS

28-AWL-22 OPERATIONAL CHECK BOOST PUMP GROUND FAULTINTERRUPTER (GFI)

ACD (TWO WAY) TO28-028-22 ACCOMPLISH BOOST PUMP GROUND FAULT INTERRUPTER

(GFI) 28-AWL-23 VERIFY CONTINUED FUNCTIONALITY OF THE CENTER

TANK FUEL BOOST PUMP POWER FAILED ON PROTECTIONSYSTEM PER AMM 28-22-00.

ACD (TWO WAY) TO

Task Relations


Model: BOEING 737-300/400/500


28-028-23 VERIFY CONTINUED FUNCTIONALITY OF THE CENTERTANK FUEL BOOST PUMP POWER FAILED ON PROTECTIONSYSTEM

31-020-01 (001.0) FDR UNDERWATER LOCATOR (ULB) BEACON BATTERY PRIMARY TO31-020-01 (001.1) DISCARD FDR UNDERWATER LOCATOR (ULB) BEACON

BATTERY 31-020-01 (001.0) FDR UNDERWATER LOCATOR (ULB) BEACON BATTERY ACD (TWO WAY) TO

31-018-01 OPERATIONAL CHECK - OPERATIONALLY CHECK THEUNDERWATER LOCATOR BEACON FOR THE FLIGHT DATARECORDER AT BATTERY REPLACEMENT.

31-FDR-01 (001.0) FDR - FLIGHT DATA RECORDER PRIMARY TO31-FDR-01 (001.1) FUNCTIONAL CHECK FDR - FLIGHT DATA RECORDER . THE

FDR READOUT FROM A FLIGHT MUST BE EVALUATED TOENSURE CORRECT FUNCTIONING.

32-008-01 (001.0) LEFT MAIN LANDING GEAR ASSEMBLY PRIMARY TO32-306-01 (001.1) GENERAL VISUAL INSPECTION LEFT MAIN LANDING GEAR

ASSEMBLY - EXTERNAL-GENERAL VISUAL INSPECTION:INSPECT THE MAIN GEAR BEAM INBOARD LUG AND B.S. 706FRAME LUG

32-304-01 (001.1) GENERAL VISUAL INSPECTION LEFT MAIN LANDING GEARASSEMBLY - INTERNAL-GENERAL VISUAL INSPECTION:INSPECT THE MAIN LANDING GEAR TRUNNION BEARINGHOUSING ON LANDING GEAR BEAM AND WING REAR SPAR

32-302-01 (001.1) GENERAL VISUAL INSPECTION LEFT MAIN LANDING GEARASSEMBLY

32-008-01 (001.1) RESTORE LEFT MAIN LANDING GEAR ASSEMBLY 32-008-01 (001.0) LEFT MAIN LANDING GEAR ASSEMBLY ACD (TWO WAY) TO

32-010-01(1.15) LEFT MAIN LANDING GEAR UPPER DRAG STRUT FUSE BOLT32-010-01(5) LEFT MAIN LANDING GEAR UPLOCK ASSEMBLY 32-010-01(1.1.3) LEFT MAIN LANDING GEAR ORFICE SUPPORT TUBE

ASSEMBLY 32-010-01(15) LEFT MAIN LANDING GEAR AFT TRUNNION NUT 32-010-01(14) LEFT MAIN LANDING GEAR FORWARD TRUNNION BEARING

ASSEMBLY 32-010-01(1.1) LEFT MAIN LANDING GEAR SHOCK STRUT ASSEMBLY 32-010-01(1.1.1) LEFT MAIN LANDING GEAR OUTER CYLINDER ASSEMBLY 32-010-01(1.1.2) LEFT MAIN LANDING GEAR INNER CYLINDER ASSEMBLY 32-010-01(1.1.4) LEFT MAIN LANDING GEAR METERING PIN 32-010-01(1.2) LEFT MAIN LANDING GEAR LOWER TORSION LINK

ASSEMBLY

Task Relations


Model: BOEING 737-300/400/500


32-010-01(1.3) LEFT MAIN LANDING GEAR UPPER TORSION LINKASSEMBLY

32-010-01(1.4) LEFT MAIN LANDING GEAR UPPER DRAG STRUT ASSEMBLY 32-010-01(1.5) LEFT MAIN LANDING GEAR LOWER DRAG STRUT ASSEMBLY32-010-01(1.6) LEFT MAIN LANDING GEAR LOWER SIDE STRUT UNIVERSAL

ASSEMBLY 32-010-01(1.7) LEFT MAIN LANDING GEAR BEAM ARM ACTUATOR

ASSEMBLY 32-010-01(1.8) LEFT MAIN LANDING GEAR TRUNNION PIN ASSEMBLY 32-010-01(1.9) LEFT MAIN LANDING GEAR DRAG STRUT TEE BOLT

ASSEMBLY 32-010-01(1.10) LEFT MAIN LANDING GEAR TRUNNION LINK ASSEMBLY 32-010-01(1.11) LEFT MAIN LANDING GEAR LOWER TORSION LINK PIN 32-010-01(1.12) LEFT MAIN LANDING GEAR UPPER TORSION LINK PIN 32-010-01(1.13) LEFT MAIN LANDING GEAR TEE FITTING ATTACHMENT BOLT32-010-01(1.14) LEFT MAIN LANDING GEAR LOWER DRAG STRUT BOLT

ASSEMBLY 32-010-01(1.16) LEFT MAIN LANDING GEAR TRUNNION PIN NUT 32-010-01(2.2) LEFT MAIN LANDING GEAR REACTION LINK UNIVERSAL

ASSEMBLY 32-010-01(2.3) LEFT MAIN LANDING GEAR UPPER SIDE STRUT ASSEMBLY 32-010-01(2.4) LEFT MAIN LANDING GEAR LOWER SIDE STRUT ASSEMBLY 32-010-01(2.5) LEFT MAIN LANDING GEAR REACTION LINK ASSEMBLY 32-010-01(2.6) LEFT MAIN LANDING GEAR UPPER DOWNLOCK LINK

ASSEMBLY 32-010-01(2.7) LEFT MAIN LANDING GEAR LOWER DOWNLOCK LINK

ASSEMBLY 32-010-01(2.8) LEFT MAIN LANDING GEAR SPRING SUPPORT SHAFT 32-010-01(2.9) LEFT MAIN LANDING GEAR REACTION LINK BOLT ASSEMBLY32-010-01(2.10) LEFT MAIN LANDING GEAR UPPER SIDE STRUT BOLT

ASSEMBLY 32-010-01(2.11) LEFT MAIN LANDING GEAR SIDE STRUT BOLT ASSEMBLY 32-010-01(2.12) LEFT MAIN LANDING GEAR DOWNLOCK LINK PIVOT BOLT 32-010-01(2.14) LEFT MAIN LANDING GEAR UPPER DOWNLOCK BOLT

ASSEMBLY 32-010-01(3) LEFT MAIN LANDING GEAR ACTUATOR BEAM ASSEMBLY 32-010-01(4) LEFT MAIN LANDING GEAR LINK ASSY SUPPORT

Task Relations


Model: BOEING 737-300/400/500


32-010-01(5.2) LEFT MAIN LANDING GEAR BELLCRANK ASSEMBLY 32-010-01(6) LEFT MAIN LANDING GEAR UPLOCK SUPPORT SHAFT 32-010-01(7) LEFT MAIN LANDING GEAR REACTION LINK/UPLOCK BOLT 32-010-01(8) LEFT MAIN LANDING GEAR OUTBOARD ACTUATOR BEAM

BOLT 32-010-01(9) LEFT MAIN LANDING GEAR LOWER SIDE STRUT BOLT

ASSEMBLY 32-010-01(12) LEFT MAIN LANDING GEAR FORWARD TRUNNION BEARING

FUSE BOLT 32-010-01(13.1) LEFT MAIN LANDING GEAR INBD ACTUATOR BEAM BOLT 32-010-01(13.2) LEFT MAIN LANDING GEAR ACTUATOR ROD END BOLT

32-008-01 (001.1) RESTORE LEFT MAIN LANDING GEAR ASSEMBLY ASSOCIATED -(ONE WAY) TO737-32-1191 R4 LANDING GEAR - MAIN GEAR AND NOSE GEAR - INNER

CYLINDER AXLE INSPECTION AND REPAIR SERVICEBULLETIN

32-008-01 (002.0) RIGHT MAIN LANDING GEAR ASSEMBLY PRIMARY TO32-008-01 (002.1) RESTORE RIGHT MAIN LANDING GEAR ASSEMBLY 32-302-01 (002.1) GENERAL VISUAL INSPECTION RIGHT MAIN LANDING GEAR

ASSEMBLY 32-304-01 (002.1) GENERAL VISUAL INSPECTION RIGHT MAIN LANDING GEAR

ASSEMBLY - INTERNAL-GENERAL VISUAL INSPECTION:INSPECT THE MAIN LANDING GEAR TRUNNION BEARINGHOUSING ON LANDING GEAR BEAM AND WING REAR SPAR

32-306-01 (002.1) GENERAL VISUAL INSPECTION RIGHT MAIN LANDING GEARASSEMBLY - EXTERNAL-GENERAL VISUAL INSPECTION:INSPECT THE MAIN GEAR BEAM INBOARD LUG AND B.S. 706FRAME LUG

32-008-01 (002.0) RIGHT MAIN LANDING GEAR ASSEMBLY ACD (TWO WAY) TO32-010-01(1.10) RIGHT MAIN LANDING GEAR TRUNNION LINK ASSEMBLY 32-010-01(1.11) RIGHT MAIN LANDING GEAR LOWER TORSION LINK PIN 32-010-01(1.12) RIGHT MAIN LANDING GEAR UPPER TORSION LINK PIN 32-010-01(1.13) RIGHT MAIN LANDING GEAR TEE FITTING ATTACHMENT

BOLT 32-010-01(1.14) RIGHT MAIN LANDING GEAR LOWER DRAG STRUT BOLT

ASSEMBLY 32-010-01(1.15) RIGHT MAIN LANDING GEAR UPPER DRAG STRUT FUSE

BOLT 32-010-01(1.16) RIGHT MAIN LANDING GEAR TRUNNION PIN NUT 32-010-01(2.2) RIGHT MAIN LANDING GEAR REACTION LINK UNIVERSAL

ASSEMBLY

Task Relations


Model: BOEING 737-300/400/500


32-010-01(2.3) RIGHT MAIN LANDING GEAR UPPER SIDE STRUT ASSEMBLY32-010-01(2.4) RIGHT MAIN LANDING GEAR LOWER SIDE STRUT ASSEMBLY32-010-01(2.5) RIGHT MAIN LANDING GEAR REACTION LINK ASSEMBLY 32-010-01(2.6) RIGHT MAIN LANDING GEAR UPPER DOWNLOCK LINK

ASSEMBLY 32-010-01(2.7) RIGHT MAIN LANDING GEAR LOWER DOWNLOCK LINK

ASSEMBLY 32-010-01(2.8) RIGHT MAIN LANDING GEAR SPRING SUPPORT SHAFT 32-010-01(2.9) RIGHT MAIN LANDING GEAR REACTION LINK BOLT

ASSEMBLY 32-010-01(2.10) RIGHT MAIN LANDING GEAR UPPER SIDE STRUT BOLT

ASSEMBLY 32-010-01(2.11) RIGHT MAIN LANDING GEAR SIDE STRUT BOLT ASSEMBLY 32-010-01(2.12) RIGHT MAIN LANDING GEAR DOWNLOCK LINK PIVOT BOLT 32-010-01(2.14) RIGHT MAIN LANDING GEAR UPPER DOWNLOCK BOLT

ASSEMBLY 32-010-01(3) RIGHT MAIN LANDING GEAR ACTUATOR BEAM ASSEMBLY 32-010-01(4) RIGHT MAIN LANDING GEAR LINK ASSY SUPPORT 32-010-01(5.2) RIGHT MAIN LANDING GEAR BELLCRANK ASSEMBLY 32-010-01(6) RIGHT MAIN LANDING GEAR UPLOCK SUPPORT SHAFT 32-010-01(7) RIGHT MAIN LANDING GEAR REACTION LINK/UPLOCK BOLT 32-010-01(8) RIGHT MAIN LANDING GEAR OUTBOARD ACTUATOR BEAM

BOLT 32-010-01(9) RIGHT MAIN LANDING GEAR LOWER SIDE STRUT BOLT

ASSEMBLY 32-010-01(12) RIGHT MAIN LANDING GEAR FORWARD TRUNNION BEARING

FUSE BOLT

32-010-01(13.1) RIGHT MAIN LANDING GEAR INBD ACTUATOR BEAM BOLT

32-010-01(13.2) RIGHT MAIN LANDING GEAR ACTUATOR ROD END BOLT 32-010-01(14) RIGHT MAIN LANDING GEAR FORWARD TRUNNION BEARING

ASSEMBLY 32-010-01(15) RIGHT MAIN LANDING GEAR AFT TRUNNION NUT 32-010-01(1.1.3) RIGHT MAIN LANDING GEAR ORFICE SUPPORT TUBE

ASSEMBLY 32-010-01(5) RIGHT MAIN LANDING GEAR UPLOCK ASSEMBLY 32-010-01(1.1) RIGHT MAIN LANDING GEAR SHOCK STRUT ASSEMBLY

Task Relations


Model: BOEING 737-300/400/500


32-010-01(1.1.1) RIGHT MAIN LANDING GEAR OUTER CYLINDER ASSEMBLY 32-010-01(1.1.2) RIGHT MAIN LANDING GEAR INNER CYLINDER ASSEMBLY 32-010-01(1.1.4) RIGHT MAIN LANDING GEAR METERING PIN 32-010-01(1.2) RIGHT MAIN LANDING GEAR LOWER TORSION LINK

ASSEMBLY 32-010-01(1.3) RIGHT MAIN LANDING GEAR UPPER TORSION LINK

ASSEMBLY 32-010-01(1.4) RIGHT MAIN LANDING GEAR UPPER DRAG STRUT

ASSEMBLY 32-010-01(1.5) RIGHT MAIN LANDING GEAR LOWER DRAG STRUT

ASSEMBLY 32-010-01(1.6) RIGHT MAIN LANDING GEAR LOWER SIDE STRUT

UNIVERSAL ASSEMBLY 32-010-01(1.7) RIGHT MAIN LANDING GEAR BEAM ARM

ACTUATOR ASSEMBLY 32-010-01(1.8) RIGHT MAIN LANDING GEAR TRUNNION PIN ASSEMBLY 32-010-01(1.9) RIGHT MAIN LANDING GEAR DRAG STRUT TEE BOLT

ASSEMBLY 32-008-01 (002.1) RESTORE RIGHT MAIN LANDING GEAR ASSEMBLY ASSOCIATED -(ONE WAY) TO

737-32-1191 R4 LANDING GEAR - MAIN GEAR AND NOSE GEAR - INNERCYLINDER AXLE INSPECTION AND REPAIR SERVICEBULLETIN

32-018-01 (001.0) NOSE LANDING GEAR ASSEMBLY PRIMARY TO32-018-01 (001.1) RESTORE NOSE LANDING GEAR ASSEMBLY 32-300-01 (000.1) GENERAL VISUAL INSPECTION NOSE LANDING GEAR

ASSEMBLY 32-018-01 (001.0) NOSE LANDING GEAR ASSEMBLY ACD (TWO WAY) TO

32-020-01(1.1.1.5) NOSE LANDING GEAR LOWER STEERING (DRILLED) PLATE 32-020-01(1.1.1.3) NOSE LANDING GEAR UPPER STEERING (DRILLED) PLATE 32-020-01(7.6) NOSE LANDING GEAR CENTER LOCK MECHANISM SHAFT 32-020-01(14.1) NOSE LANDING GEAR LEFT HAND TRUNNION PIN 32-020-01(14.2) NOSE LANDING GEAR RIGHT HAND TRUNNION PIN 32-020-01(7.5) NOSE LANDING GEAR AFT LOCK MECHANISM SHAFT 32-020-01(7.2) NOSE LANDING GEAR FORWARD LOCK LINK ASSEMBLY 32-020-01(7.1) NOSE LANDING GEAR AFT LOCK BRACE ASSEMBLY 32-020-01(6) NOSE LANDING GEAR LOWER DRAG BRACE BOLT 32-020-01(5) NOSE LANDING GEAR RIGHT UPPER DRAG BRACE PIN 32-020-01(1.1) NOSE LANDING GEAR SHOCK STRUT ASSEMBLY

Task Relations


Model: BOEING 737-300/400/500


32-020-01(1.1.1.1) NOSE LANDING GEAR OUTER CYLINDER 32-020-01(1.1.2) NOSE LANDING GEAR INNER CYLINDER ASSEMBLY 32-020-01(1.1.3.1) NOSE LANDING GEAR METERING PIN 32-020-01(1.1.10.1) NOSE LANDING GEAR UPPER ORIFICE SUPPORT TUBE 32-020-01(1.1.10.2) NOSE LANDING GEAR ORIFICE SUPPORT STEM 32-020-01(1.1.11) NOSE LANDING GEAR GLAND NUT ASSEMBLY 32-020-01(1.1.13) NOSE LANDING GEAR UPPER ORIFICE PLATE 32-020-01(1.2) NOSE LANDING GEAR UPPER TORSION LINK ASSEMBLY 32-020-01(1.3) NOSE LANDING GEAR LOWER TORSION LINK ASSEMBLY 32-020-01(1.4) NOSE LANDING GEAR STEERING COLLAR ASSY 32-020-01(1.6) NOSE LANDING GEAR LEFT STEERING COLLAR BOLT 32-020-01(1.6) NOSE LANDING GEAR RIGHT STEERING COLLAR BOLT 32-020-01(1.7) NOSE LANDING GEAR UPPER TORSION LINK PIN 32-020-01(1.8) NOSE LANDING GEAR LOWER TORSION LINK PIN 32-020-01(1.9) NOSE LANDING GEAR TORSION LINK APEX BOLT 32-020-01(2) NOSE LANDING GEAR LOWER DRAG BRACE ASSEMBLY 32-020-01(3) NOSE LANDING GEAR UPPER DRAG BRACE ASSEMBLY 32-020-01(4) NOSE LANDING GEAR DRAG BRACE CENTER PIN 32-020-01(5) NOSE LANDING GEAR LEFT UPPER DRAG BRACE PIN

32-052-01 (001.0) LEFT NOSE LANDING GEAR WHEEL ASSEMBLY PRIMARY TO32-052-01 (001.1) RESTORE LEFT NOSE LANDING GEAR WHEEL ASSEMBLY -

RESTORE THE NOSE AND MAIN LANDING GEAR WHEELASSEMBLIES

32-052-01 (002.0) RIGHT NOSE LANDING GEAR WHEEL ASSEMBLY PRIMARY TO32-052-01 (002.1) RESTORE RIGHT NOSE LANDING GEAR WHEEL ASSEMBLY -

RESTORE THE NOSE AND MAIN LANDING GEAR WHEELASSEMBLIES

32-052-01 (003.0) NO. 1 LEFT MAIN LANDING GEAR WHEEL ASSEMBLY PRIMARY TO32-052-01 (003.1) RESTORE NO. 1 LEFT MAIN LANDING GEAR WHEEL

ASSEMBLY - RESTORE THE NOSE AND MAIN LANDINGGEAR WHEEL ASSEMBLIES

32-052-01 (004.0) NO. 2 LEFT MAIN LANDING GEAR WHEEL ASSEMBLY PRIMARY TO32-052-01 (004.1) RESTORE NO. 2 LEFT MAIN LANDING GEAR WHEEL


32-052-01 (005.0) NO. 1 RIGHT MAIN LANDING GEAR WHEEL ASSEMBLY PRIMARY TO32-052-01 (005.1) RESTORE NO. 1 RIGHT MAIN LANDING GEAR WHEEL


Task Relations


Model: BOEING 737-300/400/500


32-052-01 (006.0) NO. 2 RIGHT MAIN LANDING GEAR WHEEL ASSEMBLY PRIMARY TO32-052-01 (006.1) RESTORE NO. 2 RIGHT MAIN LANDING GEAR WHEEL


34-008-01 (001.0) NO.1 AIR TRAFFIC CONTROL (ATC) TRANSPONDER PRIMARY TO34-008-01 (001.1) FUNCTIONALLY CHECK NO.1 AIR TRAFFIC CONTROL (ATC)

TRANSPONDER 34-008-01 (002.0) NO.2 AIR TRAFFIC CONTROL (ATC) TRANSPONDER PRIMARY TO

34-008-01 (002.1) FUNCTIONALLY CHECK NO.2 AIR TRAFFIC CONTROL (ATC)TRANSPONDER

35-002-01 (001.0) CREW OXYGEN CYLINDER PRIMARY TO35-002-01 (001.1) RESTORE CREW OXYGEN CYLINDER (OFF-AIRCRAFT) BY

HYDROSTATIC TEST 35-004-01 (001.1) DISCARD CREW OXYGEN CYLINDER

35-014-01 (001.0) CAPT OXYGEN REGULATOR/MASK PRIMARY TO35-014-01 (001.1) FUNCTIONAL CHECK CAPT OXYGEN REGULATOR/MASK

PER MANUFACTURER'S MANUAL (OFF AIRPLANE) 35-014-01 (001.0) CAPT OXYGEN REGULATOR/MASK ASSOCIATED -(ONE WAY) TO


35-014-01 (002.0) F/O OXYGEN REGULATOR/MASK PRIMARY TO35-014-01 (002.1) FUNCTIONAL CHECK F/O OXYGEN REGULATOR/MASK PER

MANUFACTURER'S MANUAL (OFF AIRPLANE) 35-014-01 (002.0) F/O OXYGEN REGULATOR/MASK ASSOCIATED -(ONE WAY) TO


35-014-01 (003.0) 1ST OBS OXYGEN REGULATOR/MASK PRIMARY TO35-014-01 (003.1) FUNCTIONAL CHECK 1ST OBS OXYGEN REGULATOR/MASK

PER MANUFACTURER'S MANUAL (OFF AIRPLANE) 35-014-01 (003.0) 1ST OBS OXYGEN REGULATOR/MASK ASSOCIATED -(ONE WAY) TO


35-014-01 (004.0) 2ND OBS OXYGEN REGULATOR/MASK PRIMARY TO

Task Relations


Model: BOEING 737-300/400/500


35-014-01 (004.1) FUNCTIONAL CHECK 2ND OBS OXYGEN REGULATOR/MASKPER MANUFACTURER'S MANUAL (OFF AIRPLANE)

35-014-01 (004.0) 2ND OBS OXYGEN REGULATOR/MASK ASSOCIATED -(ONE WAY) TO2011-0090 PARA (3) DO NOT INSTALL OXYGEN MASK REGULATOR INFLATABLE

HARNESS - IDENTIFICATION/REPLACEMENT EASA A FLIGHTCREW OXYGEN MASK REGULATOR UNLESS IT HAS BEENDETERMINED THAT THE P/N AND BATCH NUMBER OF THEINFLATABLE HARNESS FITTED IS NOT LISTED

35-044-01 (001.0) FWD LAV OXYGEN GENERATOR

PRIMARY TO35-044-01 (001.1) DISCARD NO.1 CHEMICAL OXYGEN GENERATOR

35-044-01 (002.0) FWD ATT OXYGEN GENERATOR PRIMARY TO35-044-01 (002.1) DISCARD FWD ATT OXYGEN GENERATOR

35-044-01 (003.0) L1 OXYGEN GENERATOR PRIMARY TO35-044-01 (003.1) DISCARD L1 OXYGEN GENERATOR













35-044-01 (016.0) L14 OXYGEN GENERATOR PRIMARY TO

Task Relations


Model: BOEING 737-300/400/500


35-044-01 (016.1) DISCARD L14 OXYGEN GENERATOR 35-044-01 (017.0) R1 OXYGEN GENERATOR PRIMARY TO

35-044-01 (017.1) DISCARD R1 OXYGEN GENERATOR 35-044-01 (018.0) R2 OXYGEN GENERATOR PRIMARY TO














35-044-01 (031.1) DISCARD R15 OXYGEN GENERATOR 35-044-01 (032.0) AFT LAV OXYGEN GENERATOR PRIMARY TO

35-044-01 (032.1) DISCARD AFT LAV OXYGEN GENERATOR 35-044-01 (033.0) AFT ATT OXYGEN GENERATOR PRIMARY TO

35-044-01 (033.1) DISCARD AFT ATT OXYGEN GENERATOR 35-054-01 (001.0) NO.1 PORTABLE OXYGEN CYLINDER PRIMARY TO

35-054-01 (001.1) RESTORE NO.1 PORTABLE OXYGEN CYLINDER BYHYDROSTATIC TEST

35-056-01 (001.1) DISCARD NO.1 PORTABLE OXYGEN CYLINDER

Task Relations


Model: BOEING 737-300/400/500


35-054-01 (002.0) NO.2 PORTABLE OXYGEN CYLINDER PRIMARY TO35-056-01 (002.1) DISCARD NO.2 PORTABLE OXYGEN CYLINDER 35-054-01 (002.1) RESTORE NO.2 PORTABLE OXYGEN CYLINDER BY

HYDROSTATIC TEST 35-054-01 (003.0) NO.3 PORTABLE OXYGEN CYLINDER PRIMARY TO

35-056-01 (003.1) DISCARD NO.3 PORTABLE OXYGEN CYLINDER 35-054-01 (003.1) RESTORE NO.3 PORTABLE OXYGEN CYLINDER BY

HYDROSTATIC TEST 35-054-01 (004.0) NO.4 PORTABLE OXYGEN CYLINDER PRIMARY TO

35-054-01 (004.1) RESTORE NO.4 PORTABLE OXYGEN CYLINDER BYHYDROSTATIC TEST

35-056-01 (004.1) DISCARD NO.4 PORTABLE OXYGEN CYLINDER 49APU1 APU ACD (TWO WAY) TO

49-119-01 GENERAL VISUAL INSPECTION - INSPECT (GENERALVISUAL) THE VISIBLE PORTION OF THE APU COOLING AIRDUCT.

49-100-01 GENERAL VISUAL INSPECTION - INSPECT (GENERALVISUAL) THE APU AIR INLET DUCT ASSEMBLY.

72-012-01 DISCARD THE LEFT ENGINE FAN DISK. (REFER TO NO.1ENGINE STATUS REPORT)

ACD (TWO WAY) TO05-11-01 (1) NO. 1 ENGINE - FAN ROTOR - FAN DISK

72-012-02 DISCARD THE RIGHT ENGINE FAN DISK. (REFER TO NO.2ENGINE STATUS REPORT)

ACD (TWO WAY) TO05-11-01 (1) NO. 2 ENGINE - FAN ROTOR - FAN DISK

72-016-01 DISCARD THE LEFT ENGINE BOOSTER SPOOL. (REFER TONO.1 ENGINE STATUS REPORT)

ACD (TWO WAY) TO05-11-01 (2) NO. 1 ENGINE - FAN ROTOR - BOOSTER SPOOL

72-016-02 DISCARD THE RIGHT ENGINE BOOSTER SPOOL. (REFER TONO.2 ENGINE STATUS REPORT)

ACD (TWO WAY) TO05-11-01 (2) NO. 1 ENGINE - FAN ROTOR - BOOSTER SPOOL

72-022-01 DISCARD THE LEFT ENGINE FAN SHAFT. (REFER TO NO.1ENGINE STATUS REPORT)

ACD (TWO WAY) TO05-11-01 (3) NO. 1 ENGINE - FAN ROTOR - FAN SHAFT

72-022-02 DISCARD THE RIGHT ENGINE FAN SHAFT. (REFER TO NO.2ENGINE STATUS REPORT)

ACD (TWO WAY) TO05-11-01 (3) NO. 2 ENGINE - FAN ROTOR - FAN SHAFT

72-028-01 DISCARD THE LEFT ENGINE HPC DISKS, SPOOLS, SHAFTS,AND CDP SEAL. (REFER TO NO.1 ENGINE STATUS REPORT)

ACD (TWO WAY) TO05-11-02 (3) NO. 1 ENGINE - HIGH PRESSURE COMPRESSOR ROTOR -

STAGE 3 DISK 05-11-02 (1) NO. 1 ENGINE - HIGH PRESSURE COMPRESSOR ROTOR -

FRONT SHAFT

Task Relations


Model: BOEING 737-300/400/500


05-11-02 (4) NO. 1 ENGINE - HIGH PRESSURE COMPRESSOR ROTOR -STAGE 4 - 9 SPOOL

05-11-02 (5) NO. 1 ENGINE - HIGH PRESSURE COMPRESSOR ROTOR -COMPRESSOR REAR AIR (CDP) SEAL

05-11-02 (2) NO. 1 ENGINE - HIGH PRESSURE COMPRESSOR ROTOR -STAGE 1-2 SPOOL

72-028-02 DISCARD THE RIGHT ENGINE HPC DISKS, SPOOLS,SHAFTS, AND CDP SEAL. (REFER TO NO.2 ENGINE STATUSREPORT)

ACD (TWO WAY) TO

05-11-02 (3) NO. 2 ENGINE - HIGH PRESSURE COMPRESSOR ROTOR -STAGE 3 DISK

05-11-02 (2) NO. 2 ENGINE - HIGH PRESSURE COMPRESSOR ROTOR -STAGE 1-2 SPOOL

05-11-02 (4) NO. 2 ENGINE - HIGH PRESSURE COMPRESSOR ROTOR -STAGE 4 - 9 SPOOL

05-11-02 (5) NO. 2 ENGINE - HIGH PRESSURE COMPRESSOR ROTOR -COMPRESSOR REAR AIR (CDP) SEAL

05-11-02 (1) NO. 2 ENGINE - HIGH PRESSURE COMPRESSOR ROTOR -FRONT SHAFT

72-052-01 DISCARD THE LEFT ENGINE HPT REAR SHAFT. (REFER TONO.1 ENGINE STATUS REPORT)

ACD (TWO WAY) TO05-11-03 (4) NO. 1 ENGINE - REAR HIGH PRESSURE TURBINE - REAR

SHAFT 72-052-02 DISCARD THE RIGHT ENGINE HPT REAR SHAFT. (REFER

TO NO.2 ENGINE STATUS REPORT) ACD (TWO WAY) TO

05-11-03 (4) NO. 2 ENGINE - REAR HIGH PRESSURE TURBINE - REARSHAFT

72-054-01 DISCARD THE LEFT ENGINE HPT FRONT SHAFT. (REFERTO NO.1 ENGINE STATUS REPORT)

ACD (TWO WAY) TO05-11-03 (1) NO. 1 ENGINE - HIGH PRESSURE TURBINE ROTOR - FRONT

SHAFT 72-054-02 DISCARD THE RIGHT ENGINE HPT FRONT SHAFT. (REFER

TO NO.2 ENGINE STATUS REPORT) ACD (TWO WAY) TO

05-11-03 (1) NO. 2 ENGINE - HIGH PRESSURE TURBINE ROTOR - FRONTSHAFT

72-056-01 DISCARD THE LEFT ENGINE HPT FRONT ROTATING AIRSEAL. (REFER TO NO.1 ENGINE STATUS REPORT)

ACD (TWO WAY) TO05-11-03 (2) NO. 1 ENGINE - HIGH PRESSURE TURBINE ROTOR - FRONT

AIR SEAL 72-056-02 DISCARD THE RIGHT ENGINE HPT FRONT ROTATING AIR

SEAL. (REFER TO NO.2 ENGINE STATUS REPORT) ACD (TWO WAY) TO

Task Relations


Model: BOEING 737-300/400/500


05-11-03 (2) NO. 2 ENGINE - HIGH PRESSURE TURBINE ROTOR - FRONTAIR SEAL

72-058-01 DISCARD THE LEFT ENGINE HPT DISK. (REFER TO NO.1ENGINE STATUS REPORT)

ACD (TWO WAY) TO05-11-03 (3) NO. 1 ENGINE - HIGH PRESSURE TURBINE ROTOR - DISC

72-058-02 DISCARD THE RIGHT ENGINE HPT DISK. (REFER TO NO.2ENGINE STATUS REPORT)

ACD (TWO WAY) TO05-11-03 (3) NO. 2 ENGINE - HIGH PRESSURE TURBINE ROTOR - DISC

72-060-01 DISCARD THE LEFT ENGINE CONICAL SUPPORT (DRIVINGCONE). (REFER TO NO.1 ENGINE STATUS REPORT)

ACD (TWO WAY) TO05-11-04 (7) NO. 1 ENGINE - LOW PRESSURE TURBINE ROTOR - CONICAL

SUPPORT 72-060-02 DISCARD THE RIGHT ENGINE CONICAL SUPPORT (DRIVING

CONE). (REFER TO NO.2 ENGINE STATUS REPORT) ACD (TWO WAY) TO

05-11-04 (7) NO. 2 ENGINE - LOW PRESSURE TURBINE ROTOR - CONICALSUPPORT

72-062-01 DISCARD THE LEFT ENGINE LPT SHAFT. (REFER TO NO.1ENGINE STATUS REPORT)

ACD (TWO WAY) TO05-11-04 (5) NO. 1 ENGINE - LOW PRESSURE TURBINE ROTOR - LPT

SHAFT 72-062-02 DISCARD THE RIGHT ENGINE LPT SHAFT. (REFER TO NO.2

ENGINE STATUS REPORT) ACD (TWO WAY) TO

05-11-04 (5) NO. 2 ENGINE - LOW PRESSURE TURBINE ROTOR - LPTSHAFT

72-064-01 DISCARD THE LEFT ENGINE STUB SHAFT. (REFER TO NO.1ENGINE STATUS REPORT)

ACD (TWO WAY) TO05-11-04 (6) NO. 1 ENGINE - LOW PRESSURE TURBINE ROTOR - LPT

STUB SHAFT 72-064-02 DISCARD THE RIGHT ENGINE STUB SHAFT. (REFER TO

NO.2 ENGINE STATUS REPORT) ACD (TWO WAY) TO

05-11-04 (6) NO. 2 ENGINE - LOW PRESSURE TURBINE ROTOR - LPTSTUB SHAFT

72-066-01 DISCARD THE LEFT ENGINE LPT DISKS. (REFER TO NO.1ENGINE STATUS REPORT)

ACD (TWO WAY) TO05-11-04 (3) NO. 1 ENGINE - LOW PRESSURE TURBINE ROTOR - STAGE 3

DISK 05-11-04 (1) NO. 1 ENGINE - LOW PRESSURE TURBINE ROTOR - STAGE 1



DISK

Task Relations


Model: BOEING 737-300/400/500


72-066-02 DISCARD THE RIGHT ENGINE LPT DISKS. (REFER TO NO.2ENGINE STATUS REPORT)

ACD (TWO WAY) TO05-11-04 (2) NO. 2 ENGINE - LOW PRESSURE TURBINE ROTOR - STAGE 2




DISK 737-27-1255 R4 FLIGHT CONTROLS - RUDDER AND RUDDER TRIM CONTROL

SYSTEM - INSTALLATION OF AN ENHANCED RUDDERCONTROL SYSTEM (RSEP) SERVICE BULLETIN

PRIMARY TO

737-27-1255 R4 TABLE1.2

REPLACE FLIGHT CONTROLS - RUDDER AND RUDDER TRIMCONTROL SYSTEM - INSTALLATION OF AN ENHANCEDRUDDER CONTROL SYSTEM (RSEP) SERVICE BULLETIN MAIN RUDDER PCU CONTROL RODS AS GIVEN INACCOMPLISHMENT INSTRUCTIONS, PART 2 FOR ALLGROUPS, CONFIGURATION 3

737-27-1255 R4 TABLE1.1

INSTALL FLIGHT CONTROLS - RUDDER AND RUDDER TRIMCONTROL SYSTEM - INSTALLATION OF AN ENHANCEDRUDDER CONTROL SYSTEM (RSEP) SERVICE BULLETIN INSTALL AN ENHANCED RUDDER CONTROL SYSTEM (RSEP)AS GIVEN IN ACCOMPLISHMENT INSTRUCTIONS PART 1FOR ALL GROUPS, CONFIGURATIONS 1 AND 2

737-27A1278 R1 FLIGHT CONTROLS - HORIZONTAL STABILIZER TRIMCONTROL SYSTEM - BALLSCREW AND BALL NUTINSPECTION AND LUBRICATION SERVICE BULLETIN

PRIMARY TO

737-27A1278 R1 PARA E(OVH)

OVERHAUL FLIGHT CONTROLS - HORIZONTAL STABILIZERTRIM CONTROL SYSTEM - BALLSCREW AND BALL NUTINSPECTION AND LUBRICATION SERVICE BULLETIN THEHORIZONTAL STABILIZER TRIM ACTUATOR

737-27A1278 R1 PARA E(LUB)

LUBRICATE FLIGHT CONTROLS - HORIZONTAL STABILIZERTRIM CONTROL SYSTEM - BALLSCREW AND BALL NUTINSPECTION AND LUBRICATION SERVICE BULLETIN THEHORIZONTAL STABILIZER TRIM ACTUATOR

737-27A1278 R1 PARA E(INSP)

DETAILED INSPECTION FLIGHT CONTROLS - HORIZONTALSTABILIZER TRIM CONTROL SYSTEM - BALLSCREW ANDBALL NUT INSPECTION AND LUBRICATION SERVICEBULLETIN OF THE HORIZONTAL STABILIZER TRIMACTUATOR

Task Relations


Model: BOEING 737-300/400/500


737-27A1281 RUDDER - RUDDER AND RUDDER TRIM CONTROL SYSTEM -STANDBY RUDDER ACTUATOR SHUTOFF VALVE TEST ANDRUDDER MAIN POWER CONTROL UNIT FORCE FIGHTMONITOR TEST - TEST FREQUENCY CHANGE SERVICEBULLETIN

PRIMARY TO

737-27A1281 TABLE 1.1 ACCOMPLISH RUDDER - RUDDER AND RUDDER TRIMCONTROL SYSTEM - STANDBY RUDDER ACTUATORSHUTOFF VALVE TEST AND RUDDER MAIN POWERCONTROL UNIT FORCE FIGHT MONITOR TEST - TESTFREQUENCY CHANGE SERVICE BULLETIN THE RUDDERMAIN PCU FORCE FIGHT MONITOR TEST

737-27A1281 TABLE 2 ACCOMPLISH RUDDER - RUDDER AND RUDDER TRIMCONTROL SYSTEM - STANDBY RUDDER ACTUATORSHUTOFF VALVE TEST AND RUDDER MAIN POWERCONTROL UNIT FORCE FIGHT MONITOR TEST - TESTFREQUENCY CHANGE SERVICE BULLETIN THE STANDBYRUDDER ACTUATOR SHUTOFF VALVE TEST

737-27A1281 TABLE 1.2 ACCOMPLISH RUDDER - RUDDER AND RUDDER TRIMCONTROL SYSTEM - STANDBY RUDDER ACTUATORSHUTOFF VALVE TEST AND RUDDER MAIN POWERCONTROL UNIT FORCE FIGHT MONITOR TEST - TESTFREQUENCY CHANGE SERVICE BULLETIN THE RUDDERMAIN PCU FORCE FIGHT MONITOR

737-28A1212 R2 FUEL - ENGINE FUEL FEED SYSTEM - FUEL PUMP CONTROLGROUND FAULT INTERRUPTER (GFI) RELAY INSTALLATIONSERVICE BULLETIN

PRIMARY TO

737-28A1212 R2 PARA(E) (1)

ACCOMPLISH FUEL - ENGINE FUEL FEED SYSTEM - FUELPUMP CONTROL GROUND FAULT INTERRUPTER (GFI)RELAY INSTALLATION SERVICE BULLETIN FOR GROUP 1, 8AIRPLANES

737-28A1212 R2 PARA(E) (2)

ACCOMPLISH FUEL - ENGINE FUEL FEED SYSTEM - FUELPUMP CONTROL GROUND FAULT INTERRUPTER (GFI)RELAY INSTALLATION SERVICE BULLETIN FOR GROUP 2-7,9-13 AIRPLANES

737-28A1263 R2 FUEL - ENGINE FUEL FEED SYSTEM - FUEL BOOST PUMPELECTRICAL WIRE AND SLEEVE IN FUEL TANK CONDUIT(INSPECTION / REPLACEMENT) SERVICE BULLETIN

ACD (TWO WAY) TO

737-28A1120 R4 FUEL TANK BOOST PUMP - INSPECTION OF THE WIRING INTHE FUEL TANKS (SUPERSEDED BY 737-28A1263) SERVICEBULLETIN

737-28A1307 FUEL - ENGINE FUEL FEED SYSTEM - ENGINE FUELSUCTION FEED OPERATIONAL TEST SERVICE BULLETIN

PRIMARY TO737-28A1307 TABLE (2) PERFORM FUEL - ENGINE FUEL FEED SYSTEM - ENGINE

FUEL SUCTION FEED OPERATIONAL TEST SERVICEBULLETIN THE ENGINE NO. 2 FUEL SUCTION FEED -OPERATIONAL TEST FOR GROUP 1

Task Relations


Model: BOEING 737-300/400/500


737-28A1307 TABLE (1) PERFORM FUEL - ENGINE FUEL FEED SYSTEM - ENGINEFUEL SUCTION FEED OPERATIONAL TEST SERVICEBULLETIN THE ENGINE NO. 1 FUEL SUCTION FEED -OPERATIONAL TEST FOR GROUP 1

737-29-1115 R1 HYDRAULIC POWER - MAIN - HYDRAULIC SYSTEM(S)PRESSURE MODULE CHECK VALVE INSPECTION ANDREPLACEMENT SERVICE BULLETIN

PRIMARY TO

737-29-1115 R1 1.E(1.4.2)

REPLACE HYDRAULIC POWER - MAIN - HYDRAULICSYSTEM(S) PRESSURE MODULE CHECK VALVE INSPECTIONAND REPLACEMENT SERVICE BULLETIN THE CHECK VALVEWITH CRISSAIR CHECK VALVE P/N 1C4196

737-29-1115 R1 1.E(1.4.1)

REPLACE HYDRAULIC POWER - MAIN - HYDRAULICSYSTEM(S) PRESSURE MODULE CHECK VALVE INSPECTIONAND REPLACEMENT SERVICE BULLETIN THE CHECK VALVEWITH PARKER CHECK VALVE P/N H61C0552M1, S/N21295 OR AFTER

737-29-1115 R1 1.E (1.2) DO HYDRAULIC POWER - MAIN - HYDRAULIC SYSTEM(S)PRESSURE MODULE CHECK VALVE INSPECTION ANDREPLACEMENT SERVICE BULLETIN AN INSPECTION OF THEHYDRAULIC SYSTEMS A AND B CHECK VALVES TO IDENTIFYTHE PART NUMBER AND SERIAL NUMBER INSTALLED (FORGROUP 2 AIRPLANES)

737-29-1115 R1 1.E (1.1) DO HYDRAULIC POWER - MAIN - HYDRAULIC SYSTEM(S)PRESSURE MODULE CHECK VALVE INSPECTION ANDREPLACEMENT SERVICE BULLETIN AN INSPECTION OF THEHYDRAULIC SYSTEM A CHECK VALVES TO IDENTIFY THEPART NUMBER AND SERIAL NUMBER INSTALLED (FORGROUP 1 AIRPLANES)

737-29-1115 R1 HYDRAULIC POWER - MAIN - HYDRAULIC SYSTEM(S)PRESSURE MODULE CHECK VALVE INSPECTION ANDREPLACEMENT SERVICE BULLETIN

ACD (TWO WAY) TO

737-SL-29-108 REV. E POTENTIAL PERSONAL HAZARD - HYDRAULIC PRESSUREMODULE CARTRIDGE CHECK VALVE FRACTURES SERVICELETTER

737-30A1059 R2 ICE AND RAIN PROTECTION - WINDSHIELD WIPER SYSTEM -CHANGE THE WINDSHIELD WIPER MOTOR SERVICEBULLETIN

PRIMARY TO

737-30A1059 R2 TABLE 1(001.2)

VERIFY ICE AND RAIN PROTECTION - WINDSHIELD WIPERSYSTEM - CHANGE THE WINDSHIELD WIPER MOTORSERVICE BULLETIN THE RH WINDSHEILD WIPER MOTORPART NUMBER AND REPLACE OR CHNAGE PART NUMBERAS NEEDED

Task Relations


Model: BOEING 737-300/400/500


737-30A1059 R2 TABLE 1(001.1)

VERIFY ICE AND RAIN PROTECTION - WINDSHIELD WIPERSYSTEM - CHANGE THE WINDSHIELD WIPER MOTORSERVICE BULLETIN THE LH WINDSHIELD WIPER MOTORPART NUMBER AND REPLACE OR CHNAGE PART NUMBERAS NEEDED

737-30A1059 R2TABLE 1 (001.1)

VERIFY ICE AND RAIN PROTECTION - WINDSHIELD WIPERSYSTEM - CHANGE THE WINDSHIELD WIPER MOTORSERVICE BULLETIN THE LH WINDSHIELD WIPER MOTORPART NUMBER AND REPLACE OR CHNAGE PART NUMBERAS NEEDED


8-30-08 (1) WINDSHIELD WIPER MOTOR (DRIVE) CONVERTER 737-30A1059 R2TABLE 1 (001.2)

VERIFY ICE AND RAIN PROTECTION - WINDSHIELD WIPERSYSTEM - CHANGE THE WINDSHIELD WIPER MOTORSERVICE BULLETIN THE RH WINDSHEILD WIPER MOTORPART NUMBER AND REPLACE OR CHNAGE PART NUMBERAS NEEDED


8-30-08 (2) WINDSHIELD WIPER MOTOR (DRIVE) CONVERTER 737-32-1191 R4 LANDING GEAR - MAIN GEAR AND NOSE GEAR - INNER

CYLINDER AXLE INSPECTION AND REPAIR SERVICEBULLETIN

ACD (TWO WAY) TO

737-32-1191 R5 LANDING GEAR - MAIN GEAR AND NOSE GEAR - INNERCYLINDER AXLE INSPECTION AND REPAIR SERVICEBULLETIN

737-32A1314 R1 LANDING GEAR - MAIN GEAR AND DOORS - ACTUATORBEAM ARM INSPECTION, OVERHAUL, REWORK ANDREPLACEMENT SERVICE BULLETIN

PRIMARY TO

737-32A1314 R1 PARA E2

DETAILED INSPECTION LANDING GEAR - MAIN GEAR ANDDOORS - ACTUATOR BEAM ARM INSPECTION, OVERHAUL,REWORK AND REPLACEMENT SERVICE BULLETIN ANDULTRASONIC INSPECTION OF THE ACTUATOR BEAM ARM

737-32A1314 R1 PARA E1

DETAILED INSPECTION LANDING GEAR - MAIN GEAR ANDDOORS - ACTUATOR BEAM ARM INSPECTION, OVERHAUL,REWORK AND REPLACEMENT SERVICE BULLETIN ANDULTRASONIC INSPECTION OF THE ACTUATOR BEAM ARM

737-32A1314 R1 PARA E4

OVERHAUL LANDING GEAR - MAIN GEAR AND DOORS -ACTUATOR BEAM ARM INSPECTION, OVERHAUL, REWORKAND REPLACEMENT SERVICE BULLETIN THE ACTUATORBEAM ARM

737-47-1005 NITROGEN GENERATION SYSTEM - INSTALLATION OFWIRING AND THE NITROGEN GENERATION SYSTEMCOMPONENTS SERVICE BULLETIN

PRIMARY TO

737-47-1005 TABLE 1.1 DEATILED INSPECTION NITROGEN GENERATION SYSTEM -INSTALLATION OF WIRING AND THE NITROGENGENERATION SYSTEM COMPONENTS SERVICE BULLETIN

Task Relations


Model: BOEING 737-300/400/500


737-47-1005 TABLE 1.2 EDDY CURRENT NITROGEN GENERATION SYSTEM -INSTALLATION OF WIRING AND THE NITROGENGENERATION SYSTEM COMPONENTS SERVICE BULLETIN (MID FREQUENCY) INSPECTION

737-47-1005 TABLE 1.3 LFEC NITROGEN GENERATION SYSTEM - INSTALLATION OFWIRING AND THE NITROGEN GENERATION SYSTEMCOMPONENTS SERVICE BULLETIN INSPECTION

737-47-1008 INERT GAS SYSTEM - INSTALLATION OF THE NITROGENGENERATION SYSTEM SERVICE BULLETIN

PRIMARY TO737-47-1008 TABLE 1.1 DETAILED INSPECTION INERT GAS SYSTEM -

INSTALLATION OF THE NITROGEN GENERATION SYSTEMSERVICE BULLETIN OF THE FUSELAGE SKIN AT THE65C38767 EXTERNAL DOUBLER FOR ALL AIRPLANES

737-47-1008 TABLE 1.2 PERFORM INERT GAS SYSTEM - INSTALLATION OF THENITROGEN GENERATION SYSTEM SERVICE BULLETIN MIDFREQUENCY EDDY CURRENT (MFEC) INSPECTION OFFUSELAGE SKIN AT THE 65C38767 EXTERNAL DOUBLERFOR ALL AIRPLANES

737-47-1008 TABLE 1.3 LFEC INERT GAS SYSTEM - INSTALLATION OF THENITROGEN GENERATION SYSTEM SERVICE BULLETIN INSPECTION FOR FUSELAGE SKIN 65C38767 EXTERNALDOUBLER FOR ALL AIRPLANES


PRIMARY TO

737-52-1154 TABLE(1)(2)(3)

INSPECTION DOORS - CARGO COMPARTMENT DOORS -AFT CARGO DOOR - CROSS BEAM D INSPECTION, REPAIRAND PREVENTIVE MODIFICATION SERVICE BULLETIN ANDREPAIR OF THE FORWARD AND AFT CARGO DOOR CROSSBEAM D AND DOOR FRAME FOR ALL GROUP 1, 2,CONFIGURATION 1, 2 AIRPLANES

737-52-1154 TABLE (4.2) ACCOMPLISH DOORS - CARGO COMPARTMENT DOORS -AFT CARGO DOOR - CROSS BEAM D INSPECTION, REPAIRAND PREVENTIVE MODIFICATION SERVICE BULLETIN ONE-TIME DETAILED AND ULTRASONIC INSPECTIONS OFTHE FRAMES FOR CRACKS IN ACCORDANCE WITH PART 29AND 30 OF THE WORK INSTRUCTIONS FOR GROUP 3AIRPLANES

737-52-1154 TABLE (5) SUPPLEMENTAL INSPECTION DOORS - CARGOCOMPARTMENT DOORS - AFT CARGO DOOR - CROSS BEAMD INSPECTION, REPAIR AND PREVENTIVE MODIFICATIONSERVICE BULLETIN FOR AIRPLANES WITH A REPAIR OR APREVENTIVE MODIFICATION INSTALLED AT THE FORWARDOR AFT CARGO DOOR CROSS BEAM D

Task Relations


Model: BOEING 737-300/400/500


737-52-1154 TABLE (4.1) ACCOMPLISH DOORS - CARGO COMPARTMENT DOORS -AFT CARGO DOOR - CROSS BEAM D INSPECTION, REPAIRAND PREVENTIVE MODIFICATION SERVICE BULLETIN ONE-TIME DETAILED AND HFEC INSPECTIONS FOR CRACKSAT THE FORWARD AND AFT ENDS OF CROSS BEAM D INACCORDANCE WITH PART 28 OF THE WORK INSTRUCTIONSFOR GROUP 3 AIRPLANES

737-52-1154 TABLE(1)(2)(3)

INSPECTION DOORS - CARGO COMPARTMENT DOORS -AFT CARGO DOOR - CROSS BEAM D INSPECTION, REPAIRAND PREVENTIVE MODIFICATION SERVICE BULLETIN ANDREPAIR OF THE FORWARD AND AFT CARGO DOOR CROSSBEAM D AND DOOR FRAME FOR ALL GROUP 1, 2,CONFIGURATION 1, 2 AIRPLANES

ACD (TWO WAY) TO


737-52-1154 TABLE(4.1)

ACCOMPLISH DOORS - CARGO COMPARTMENT DOORS -AFT CARGO DOOR - CROSS BEAM D INSPECTION, REPAIRAND PREVENTIVE MODIFICATION SERVICE BULLETIN ONE-TIME DETAILED AND HFEC INSPECTIONS FOR CRACKSAT THE FORWARD AND AFT ENDS OF CROSS BEAM D INACCORDANCE WITH PART 28 OF THE WORK INSTRUCTIONSFOR GROUP 3 AIRPLANES

ACD (TWO WAY) TO


737-52-1154 TABLE(4.2)

ACCOMPLISH DOORS - CARGO COMPARTMENT DOORS -AFT CARGO DOOR - CROSS BEAM D INSPECTION, REPAIRAND PREVENTIVE MODIFICATION SERVICE BULLETIN ONE-TIME DETAILED AND ULTRASONIC INSPECTIONS OFTHE FRAMES FOR CRACKS IN ACCORDANCE WITH PART 29AND 30 OF THE WORK INSTRUCTIONS FOR GROUP 3AIRPLANES

ACD (TWO WAY) TO


737-52-1154 TABLE(5)

SUPPLEMENTAL INSPECTION DOORS - CARGOCOMPARTMENT DOORS - AFT CARGO DOOR - CROSS BEAMD INSPECTION, REPAIR AND PREVENTIVE MODIFICATIONSERVICE BULLETIN FOR AIRPLANES WITH A REPAIR OR APREVENTIVE MODIFICATION INSTALLED AT THE FORWARDOR AFT CARGO DOOR CROSS BEAM D

ACD (TWO WAY) TO



PRIMARY TO

Task Relations


Model: BOEING 737-300/400/500


737-52A1100 R5 TABLE4.6

PERFORM DOORS - FORWARD CARGO - LOWER FORWARDAND AFT CORNER INSPECTION, MODIFICATION ANDREPLACEMENT SERVICE BULLETIN DETAILED INSPECTIONAND A LFEC INSPECTION OF THE LOWER CROSS BEAM FORCRACKS IN ACCORDANCE WITH WORK INSTRUCTIONS,PART V - SUPPLEMENTAL STRUCTURAL INSPECTIONS FORAIRPLANES WITH A LOWER BEAM OUTER "T" CHORDREPAIR INSTALLED ON THE FORWARD END OF THE LOWERCROSS BEAM IN ACCORDANCE WITH THIS SERVICEBULLETIN AND THE DOOR FLIGHT CYCLES ARE NOTKNOWN

737-52A1100 R5 TABLE4.7

PERFORM DOORS - FORWARD CARGO - LOWER FORWARDAND AFT CORNER INSPECTION, MODIFICATION ANDREPLACEMENT SERVICE BULLETIN DETAILED INSPECTIONAND A LFEC INSPECTION OF THE LOWER CROSS BEAM FORCRACKS IN ACCORDANCE WITH WORK INSTRUCTIONS,PART V - SUPPLEMENTAL STRUCTURAL INSPECTIONS FORAIRPLANES WITH A LOWER BEAM OUTER "T" CHORDREPAIR INSTALLED ON THE AFT END OF THE LOWERCROSS BEAM IN ACCORDANCE WITH THIS SERVICEBULLETIN AND THE DOOR FLIGHT CYCLES ARE KNOWN.

737-52A1100 R5 TABLE4.5

PERFORM DOORS - FORWARD CARGO - LOWER FORWARDAND AFT CORNER INSPECTION, MODIFICATION ANDREPLACEMENT SERVICE BULLETIN DETAILED INSPECTIONAND A LFEC INSPECTION OF THE LOWER CROSS BEAM FORCRACKS IN ACCORDANCE WITH WORK INSTRUCTIONS,PART V - SUPPLEMENTAL STRUCTURAL INSPECTIONS FORAIRPLANES WITH A LOWER BEAM OUTER "T" CHORDREPAIR INSTALLED ON THE FORWARD END OF THE LOWERCROSS BEAM IN ACCORDANCE WITH THIS SERVICEBULLETIN AND THE DOOR FLIGHT CYCLES ARE KNOWN

737-52A1100 R5 TABLE4.4

PERFORM DOORS - FORWARD CARGO - LOWER FORWARDAND AFT CORNER INSPECTION, MODIFICATION ANDREPLACEMENT SERVICE BULLETIN DETAILED INSPECTIONAND A LFEC INSPECTION OF THE LOWER CROSS BEAM FORCRACKS IN ACCORDANCE WITH WORK INSTRUCTIONS,PART V - SUPPLEMENTAL STRUCTURAL INSPECTIONS FORAIRPLANES WITH A PREVENTIVE MODIFICATION INSTALLEDON THE AFT END OF THE LOWER CROSS BEAM INACCORDANCE WITH THIS SERVICE BULLETIN AND THEDOOR FLIGHT CYCLES ARE NOT KNOWN.

Task Relations


Model: BOEING 737-300/400/500


737-52A1100 R5 TABLE4.3

PERFORM DOORS - FORWARD CARGO - LOWER FORWARDAND AFT CORNER INSPECTION, MODIFICATION ANDREPLACEMENT SERVICE BULLETIN DETAILED INSPECTIONAND A LFEC INSPECTION OF THE LOWER CROSS BEAM FORCRACKS IN ACCORDANCE WITH WORK INSTRUCTIONS,PART V - SUPPLEMENTAL STRUCTURAL INSPECTIONS FORAIRPLANES WITH A PREVENTIVE MODIFICATION INSTALLEDON THE AFT END OF THE LOWER CROSS BEAM INACCORDANCE WITH THIS SERVICE BULLETIN AND THEDOOR FLIGHT CYCLES ARE KNOWN

737-52A1100 R5 TABLE4.2

PERFORM DOORS - FORWARD CARGO - LOWER FORWARDAND AFT CORNER INSPECTION, MODIFICATION ANDREPLACEMENT SERVICE BULLETIN DETAILED INSPECTIONAND A LFEC INSPECTION OF THE LOWER CROSS BEAM FORCRACKS IN ACCORDANCE WITH WORK INSTRUCTIONS,PART V - SUPPLEMENTAL STRUCTURAL INSPECTIONS FORAIRPLANES WITH A PREVENTIVE MODIFICATION INSTALLEDON THE FORWARD END OF THE LOWER CROSS BEAM INACCORDANCE WITH THIS SERVICE BULLETIN AND THEDOOR FLIGHT CYCLES ARE NOT KNOWN

737-52A1100 R5 TABLE4.1

PERFORM DOORS - FORWARD CARGO - LOWER FORWARDAND AFT CORNER INSPECTION, MODIFICATION ANDREPLACEMENT SERVICE BULLETIN DETAILED INSPECTIONAND A LFEC INSPECTION OF THE LOWER CROSS BEAM FORCRACKS IN ACCORDANCE WITH WORK INSTRUCTIONS,PART V - SUPPLEMENTAL STRUCTURAL INSPECTIONS FORAIRPLANES WITH A PREVENTIVE MODIFICATION INSTALLEDON THE FORWARD END OF THE LOWER CROSS BEAM INACCORDANCE WITH THIS SERVICE BULLETIN AND THEDOOR FLIGHT CYCLES ARE KNOWN

737-52A1100 R5 TABLE 3 PERFORM DOORS - FORWARD CARGO - LOWER FORWARDAND AFT CORNER INSPECTION, MODIFICATION ANDREPLACEMENT SERVICE BULLETIN ONE-TIME GENERALVISUAL INSPECTION OF THE REINFORCEMENT ANGLE FOREXCESSIVE SHIMMING OR FASTENER PULL-UP INACCORDANCE WITH WORK INSTRUCTIONS, "PART III". FORAIRPLANES WITH REINFORCEMENT ANGLE 65C27804-4INSTALLED IN ACCORDANCE WITH REVISION 2 OR 3 OFTHIS SERVICE BULLETIN

Task Relations


Model: BOEING 737-300/400/500


737-52A1100 R5 TABLE4.8

PERFORM DOORS - FORWARD CARGO - LOWER FORWARDAND AFT CORNER INSPECTION, MODIFICATION ANDREPLACEMENT SERVICE BULLETIN DETAILED INSPECTIONAND A LFEC INSPECTION OF THE LOWER CROSS BEAM FORCRACKS IN ACCORDANCE WITH WORK INSTRUCTIONS,PART V - SUPPLEMENTAL STRUCTURAL INSPECTIONS FORAIRPLANES WITH A LOWER BEAM OUTER "T" CHORDREPAIR INSTALLED ON THE AFT END OF THE LOWERCROSS BEAM IN ACCORDANCE WITH THIS SERVICEBULLETIN AND THE DOOR FLIGHT CYCLES ARE NOTKNOWN.

737-52A1100 R5 TABLE 1 PERFORM DOORS - FORWARD CARGO - LOWER FORWARDAND AFT CORNER INSPECTION, MODIFICATION ANDREPLACEMENT SERVICE BULLETIN ONE-TIME HFECINSPECTION OF THE LOWER CORNER FRAME AND THENUMBER 5CROSS-BEAM FOR CRACKS IN ACCORDANCE WITH WORKINSTRUCTIONS, "PART I." FOR AIRPLANES NOT REPAIREDAND NOT MODIFIED IN ACCORDANCE WITH THE INITIALRELEASE, REVISION 1, 2, 3, OR 4 OF THIS SERVICEBULLETIN

737-52A1100 R5 TABLE 2 PERFORM DOORS - FORWARD CARGO - LOWER FORWARDAND AFT CORNER INSPECTION, MODIFICATION ANDREPLACEMENT SERVICE BULLETIN ONE-TIME HFECINSPECTION OF THE LOWER CORNER FRAME FOR CRACKS,IN ACCORDANCE WITH WORK INSTRUCTIONS, "PART I". FORAIRPLANES MODIFIED OR REPAIRED IN ACCORDANCE WITHTHE INITIAL RELEASE, REVISION 1 OR 2 OF THIS SERVICEBULLETIN AND THE FRAME MODIFICATION ANGLE WAS NOTINSTALLED


PRIMARY TO

737-52A1153 TABLE 2.5 INSTALL DOORS - AFT CARGO - CROSS BEAM E, ADJACENTLOWER CORNER FRAMES AND REINFORCING ANGLES -INSPECTION, REPAIR AND MODIFICATION SERVICEBULLETIN A PREVENTATIVE MODIFICATION IF NO CRACK(S)FOUND IN THE BEAM WEB AND THE T-CHORD

737-52A1153 TABLE 3.1 &3.2

PERFORM DOORS - AFT CARGO - CROSS BEAM E,ADJACENT LOWER CORNER FRAMES AND REINFORCINGANGLES - INSPECTION, REPAIR AND MODIFICATIONSERVICE BULLETIN ONE TIME ULTRASONIC AND DETAILINITIAL INSPECTIONS FOR GROUP 1 CONFIGURATION 1,GROUP 2 CONFIGURATION 1, GROUP 3 AND GROUP 4, ANDGROUP 5 CONFIGURATION 1 AIRPLANES

Task Relations


Model: BOEING 737-300/400/500


737-52A1153 TABLE 3.3 PERFORM DOORS - AFT CARGO - CROSS BEAM E,ADJACENT LOWER CORNER FRAMES AND REINFORCINGANGLES - INSPECTION, REPAIR AND MODIFICATIONSERVICE BULLETIN ONE TIME HFEC AND ULTRASONICTERMINATING INSPECTION FOR GROUP 1 CONFIGURATION1, GROUP 2 CONFIGURATION 1, GROUP 3 AND GROUP 4,AND GROUP 5 CONFIGURATION 1 AIRPLANES WITH NOCRACK(S) FOUND FROM THE INITIAL INSPECTION

737-52A1153 TABLE 4.1 &4.2

PERFORM DOORS - AFT CARGO - CROSS BEAM E,ADJACENT LOWER CORNER FRAMES AND REINFORCINGANGLES - INSPECTION, REPAIR AND MODIFICATIONSERVICE BULLETIN ONE TIME ULTRASONIC AND DETAILINITIAL INSPECTIONS GROUP 1 CONFIGURATION 1, GROUP2 CONFIGURATION 1, GROUP 3 AND GROUP 4, AND GROUP5 CONFIGURATION 1 AIRPLANES

737-52A1153 TABLE 4.3 PERFORM DOORS - AFT CARGO - CROSS BEAM E,ADJACENT LOWER CORNER FRAMES AND REINFORCINGANGLES - INSPECTION, REPAIR AND MODIFICATIONSERVICE BULLETIN ONE TIME HFEC AND ULTRASONICTERMINATING INSPECTIONS FOR GROUP 1CONFIGURATION 1, GROUP 2 CONFIGURATION 1, GROUP 3AND GROUP 4, AND GROUP 5 CONFIGURATION 1AIRPLANES WITH NO CRACK(S) FOUND FROM THE INITIALINSPECTIONS

737-52A1153 TABLE 5.1 &5.3

PERFORM DOORS - AFT CARGO - CROSS BEAM E,ADJACENT LOWER CORNER FRAMES AND REINFORCINGANGLES - INSPECTION, REPAIR AND MODIFICATIONSERVICE BULLETIN A DETAILED INSPECTION AND A LFECINSPECTION OF THE CROSS BEAM FOR CRACKS FORAIRPLANES WITH A PREVENTATIVE MODIFICATIONINSTALLED ON THE FORWARD END OF CROSS BEAM E

737-52A1153 TABLE 5.5 &5.7

PERFORM DOORS - AFT CARGO - CROSS BEAM E,ADJACENT LOWER CORNER FRAMES AND REINFORCINGANGLES - INSPECTION, REPAIR AND MODIFICATIONSERVICE BULLETIN A DETAILED INSPECTION AND A LFECINSPECTION OF THE CROSS BEAM FOR CRACKS FORAIRPLANES WITH A REPAIR INSTALLED ON THE FORWARDEND OF CROSSBEAM E

737-52A1153 TABLE 6.1 &6.3

PERFORM DOORS - AFT CARGO - CROSS BEAM E,ADJACENT LOWER CORNER FRAMES AND REINFORCINGANGLES - INSPECTION, REPAIR AND MODIFICATIONSERVICE BULLETIN A DETAILED INSPECTION AND A LFECINSPECTION OF THE CROSS BEAM FOR CRACKS FORAIRPLANES WITH A PREVENTATIVE MODIFICATIONINSTALLED ON THE AFT END OF CROSS BEAM E

Task Relations


Model: BOEING 737-300/400/500


737-52A1153 TABLE 6.5 &6.7

PERFORM DOORS - AFT CARGO - CROSS BEAM E,ADJACENT LOWER CORNER FRAMES AND REINFORCINGANGLES - INSPECTION, REPAIR AND MODIFICATIONSERVICE BULLETIN A DETAILED INSPECTION AND A LFECINSPECTION OF THE CROSS BEAM FOR CRACKS FORAIRPLANES WITH A REPAIR INSTALLED ON THE AFT END OFCROSS BEAM E

737-52A1153 TABLE 1.6 INSTALL DOORS - AFT CARGO - CROSS BEAM E, ADJACENTLOWER CORNER FRAMES AND REINFORCING ANGLES -INSPECTION, REPAIR AND MODIFICATION SERVICEBULLETIN THE REPAIR FOR CRACK(S) FOUND IN THE BEAMWEB OR THE T-CHORD AND ACCOMPLISH ACTIONS INACCORDANCE WITH TABLES 1 THROUGH 4 OF SERVICEBULLETIN 737-52-1154, ORIGINAL ISSUE, PARAGRAPH 1.E.,COMPLIANCE

737-52A1153 TABLE 2.3 &2.4

INSTALL DOORS - AFT CARGO - CROSS BEAM E, ADJACENTLOWER CORNER FRAMES AND REINFORCING ANGLES -INSPECTION, REPAIR AND MODIFICATION SERVICEBULLETIN THE REPAIR FOR CRACK(S) FOUND IN THE BEAMWEB OR THE T-CHORD AND ACCOMPLISH ACTIONS INACCORDANCE WITH TABLES 1 THROUGH 4 OF SERVICEBULLETIN 737-52-1154, ORIGINAL ISSUE

737-52A1153 TABLE 3.4 ACCOMPLISH DOORS - AFT CARGO - CROSS BEAM E,ADJACENT LOWER CORNER FRAMES AND REINFORCINGANGLES - INSPECTION, REPAIR AND MODIFICATIONSERVICE BULLETIN REPLACE THE FRAME ANDREINFORCING ANGLE / INSTALL THE REPAIR ORPREVENTATIVE MODIFICATION TO BOTH ENDS OF CROSSBEAM E, / ACCOMPLISH ACTIONS IN ACCORDANCE WITHTABLES 1 THROUGH 4 OF SERVICE BULLETIN 737-52-1154(IF CRACK(S) FOUND)

737-52A1153 TABLE 4.4 ACCOMPLISH DOORS - AFT CARGO - CROSS BEAM E,ADJACENT LOWER CORNER FRAMES AND REINFORCINGANGLES - INSPECTION, REPAIR AND MODIFICATIONSERVICE BULLETIN REPLACE THE FRAME ANDREINFORCING ANGLE / INSTALL THE REPAIR ORPREVENTATIVE MODIFICATION TO BOTH ENDS OF CROSSBEAM E / ACCOMPLISH ACTIONS IN ACCORDANCE WITHTABLES 1 THROUGH 4 OF SERVICE BULLETIN 737-52-1154,ORIGINAL ISSUE (CRACK(S) FOUND)

737-52A1153 TABLE 5.2 &5.4

CONTACT DOORS - AFT CARGO - CROSS BEAM E,ADJACENT LOWER CORNER FRAMES AND REINFORCINGANGLES - INSPECTION, REPAIR AND MODIFICATIONSERVICE BULLETIN BOEING FOR REPAIR INSTRUCTIONSAND DO THE REPAIR / ACCOMPLISH ACTIONS INACCORDANCE WITH TABLES 1 THROUGH 4 OF SERVICEBULLETIN 737-52-1154, ORIGINALISSUE

Task Relations


Model: BOEING 737-300/400/500


737-52A1153 TABLE 6.6 &6.8

CONTACT DOORS - AFT CARGO - CROSS BEAM E,ADJACENT LOWER CORNER FRAMES AND REINFORCINGANGLES - INSPECTION, REPAIR AND MODIFICATIONSERVICE BULLETIN BOEING FOR REPAIR INSTRUCTIONSAND DO THE REPAIR / ACCOMPLISH ACTIONS INACCORDANCE WITH TABLES 1 THROUGH 4 OF SERVICEBULLETIN 737-52-1154, ORIGINAL ISSUE, PARAGRAPH 1.E.,COMPLIANCE

737-52A1153 TABLE 6.2 &6.4

CONTACT DOORS - AFT CARGO - CROSS BEAM E,ADJACENT LOWER CORNER FRAMES AND REINFORCINGANGLES - INSPECTION, REPAIR AND MODIFICATIONSERVICE BULLETIN BOEING FOR REPAIR INSTRUCTIONSAND DO THE REPAIR / ACCOMPLISH ACTIONS INACCORDANCE WITH TABLES 1 THROUGH 4 OF SERVICEBULLETIN 737-52-1154, ORIGINAL ISSUE (CRACK(S) FOUND)

737-52A1153 TABLE 5.6 &5.8


737-52A1153 TABLE 1.1 &1.2

PERFORM DOORS - AFT CARGO - CROSS BEAM E,ADJACENT LOWER CORNER FRAMES AND REINFORCINGANGLES - INSPECTION, REPAIR AND MODIFICATIONSERVICE BULLETIN AN INSPECTION OF THE DOOR INACCORDANCE WITH PARAGRAPH 3.B.1., WORKINSTRUCTIONS OF THIS SERVICE BULLETIN TO DETERMINEIF THE DOOR WAS ORIGINALLY FROM A GROUP 1CONFIGURATION 2, GROUP 2 CONFIGURATION 2 OR GROUP5 CONFIGURATION 2 AIRPLANE FOR ALL AIRPLANES IN ALLGROUPS

737-52A1153 TABLE 1.3 PERFORM DOORS - AFT CARGO - CROSS BEAM E,ADJACENT LOWER CORNER FRAMES AND REINFORCINGANGLES - INSPECTION, REPAIR AND MODIFICATIONSERVICE BULLETIN ONE-TIME HFEC AND ULTRASONICINSPECTIONS OF THE UPPER AND LOWER CORNERFRAMES AND THE UPPER AND LOWER CROSS BEAMS FORCRACKS IN ACCORDANCE WITH WORK INSTRUCTIONS,PART I - ACCESS AND PART II - INSPECTION OF SERVICEBULLETIN 737-52A1079 REVISION 7

Task Relations


Model: BOEING 737-300/400/500


737-52A1153 TABLE 1.4 &1.5

PERFORM DOORS - AFT CARGO - CROSS BEAM E,ADJACENT LOWER CORNER FRAMES AND REINFORCINGANGLES - INSPECTION, REPAIR AND MODIFICATIONSERVICE BULLETIN HIGH FREQUENCY EDDY CURRENT(HFEC) AND DETAIL INSPECTIONS FOR GROUP 1CONFIGURATION 1, GROUP 2 CONFIGURATION 1, GROUP 3AND GROUP 4, AND GROUP 5 CONFIGURATION 1AIRPLANES

737-52A1153 TABLE 1.7 INSTALL DOORS - AFT CARGO - CROSS BEAM E, ADJACENTLOWER CORNER FRAMES AND REINFORCING ANGLES -INSPECTION, REPAIR AND MODIFICATION SERVICEBULLETIN A PREVENTATIVE MODIFICATION IF NO CRACK(S)FOUND IN THE BEAM WEB AND THE TCHORD

737-52A1153 TABLE 2.1 &2.2

PERFORM DOORS - AFT CARGO - CROSS BEAM E,ADJACENT LOWER CORNER FRAMES AND REINFORCINGANGLES - INSPECTION, REPAIR AND MODIFICATIONSERVICE BULLETIN HIGH FREQUENCY EDDY CURRENT(HFEC) AND DETAIL INSPECTIONS FOR GROUP 1CONFIGURATION 1, GROUP 2 CONFIGURATION 1, GROUP 3AND GROUP 4, AND GROUP 5 CONFIGURATION 1AIRPLANES

737-52A1153 TABLE1.3

PERFORM DOORS - AFT CARGO - CROSS BEAM E,ADJACENT LOWER CORNER FRAMES AND REINFORCINGANGLES - INSPECTION, REPAIR AND MODIFICATIONSERVICE BULLETIN ONE-TIME HFEC AND ULTRASONICINSPECTIONS OF THE UPPER AND LOWER CORNERFRAMES AND THE UPPER AND LOWER CROSS BEAMS FORCRACKS IN ACCORDANCE WITH WORK INSTRUCTIONS,PART I - ACCESS AND PART II - INSPECTION OF SERVICEBULLETIN 737-52A1079 REVISION 7

ACD (TWO WAY) TO


737-52A1153 TABLE1.6

INSTALL DOORS - AFT CARGO - CROSS BEAM E, ADJACENTLOWER CORNER FRAMES AND REINFORCING ANGLES -INSPECTION, REPAIR AND MODIFICATION SERVICEBULLETIN THE REPAIR FOR CRACK(S) FOUND IN THE BEAMWEB OR THE T-CHORD AND ACCOMPLISH ACTIONS INACCORDANCE WITH TABLES 1 THROUGH 4 OF SERVICEBULLETIN 737-52-1154, ORIGINAL ISSUE, PARAGRAPH 1.E.,COMPLIANCE

ACD (TWO WAY) TO


Task Relations


Model: BOEING 737-300/400/500


737-52A1153 TABLE2.3 & 2.4

INSTALL DOORS - AFT CARGO - CROSS BEAM E, ADJACENTLOWER CORNER FRAMES AND REINFORCING ANGLES -INSPECTION, REPAIR AND MODIFICATION SERVICEBULLETIN THE REPAIR FOR CRACK(S) FOUND IN THE BEAMWEB OR THE T-CHORD AND ACCOMPLISH ACTIONS INACCORDANCE WITH TABLES 1 THROUGH 4 OF SERVICEBULLETIN 737-52-1154, ORIGINAL ISSUE

ACD (TWO WAY) TO


737-52A1153 TABLE3.4

ACCOMPLISH DOORS - AFT CARGO - CROSS BEAM E,ADJACENT LOWER CORNER FRAMES AND REINFORCINGANGLES - INSPECTION, REPAIR AND MODIFICATIONSERVICE BULLETIN REPLACE THE FRAME ANDREINFORCING ANGLE / INSTALL THE REPAIR ORPREVENTATIVE MODIFICATION TO BOTH ENDS OF CROSSBEAM E, / ACCOMPLISH ACTIONS IN ACCORDANCE WITHTABLES 1 THROUGH 4 OF SERVICE BULLETIN 737-52-1154(IF CRACK(S) FOUND)

ACD (TWO WAY) TO


737-52A1153 TABLE4.4

ACCOMPLISH DOORS - AFT CARGO - CROSS BEAM E,ADJACENT LOWER CORNER FRAMES AND REINFORCINGANGLES - INSPECTION, REPAIR AND MODIFICATIONSERVICE BULLETIN REPLACE THE FRAME ANDREINFORCING ANGLE / INSTALL THE REPAIR ORPREVENTATIVE MODIFICATION TO BOTH ENDS OF CROSSBEAM E / ACCOMPLISH ACTIONS IN ACCORDANCE WITHTABLES 1 THROUGH 4 OF SERVICE BULLETIN 737-52-1154,ORIGINAL ISSUE (CRACK(S) FOUND)

ACD (TWO WAY) TO


737-52A1153 TABLE5.2 & 5.4

CONTACT DOORS - AFT CARGO - CROSS BEAM E,ADJACENT LOWER CORNER FRAMES AND REINFORCINGANGLES - INSPECTION, REPAIR AND MODIFICATIONSERVICE BULLETIN BOEING FOR REPAIR INSTRUCTIONSAND DO THE REPAIR / ACCOMPLISH ACTIONS INACCORDANCE WITH TABLES 1 THROUGH 4 OF SERVICEBULLETIN 737-52-1154, ORIGINALISSUE

ACD (TWO WAY) TO


Task Relations


Model: BOEING 737-300/400/500


737-52A1153 TABLE5.6 & 5.8


ACD (TWO WAY) TO


737-52A1153 TABLE6.2 & 6.4


ACD (TWO WAY) TO


737-52A1153 TABLE6.6 & 6.8

CONTACT DOORS - AFT CARGO - CROSS BEAM E,ADJACENT LOWER CORNER FRAMES AND REINFORCINGANGLES - INSPECTION, REPAIR AND MODIFICATIONSERVICE BULLETIN BOEING FOR REPAIR INSTRUCTIONSAND DO THE REPAIR / ACCOMPLISH ACTIONS INACCORDANCE WITH TABLES 1 THROUGH 4 OF SERVICEBULLETIN 737-52-1154, ORIGINAL ISSUE, PARAGRAPH 1.E.,COMPLIANCE

ACD (TWO WAY) TO


737-53-1305 FUSELAGE - SKIN - CHEM-MILLED STEPS IN CROWN SKINSWITH 20 INCH TEAR STRAP BAYS AT SPECIFIED LOCATIONS- INSPECTION AND MODIFICATION (SUPERSEDED BY SB737-53-1305 R1) SERVICE BULLETIN

PRIMARY TO

737-53-1305 TABLE 2 INSPECT FUSELAGE - SKIN - CHEM-MILLED STEPS INCROWN SKINS WITH 20 INCH TEAR STRAP BAYS ATSPECIFIED LOCATIONS - INSPECTION AND MODIFICATION(SUPERSEDED BY SB 737-53-1305 R1) SERVICE BULLETIN FOR CRACKING IN THE FUSELAGE SKIN AT THECHEM-MILLED STEPS AT THE SPECIFIED LOCATIONS FORALL INTERNAL MODIFICATIONS INSTALLED INACCORDANCE WITH THIS SERVICE BULLETIN

737-53-1305 SECTION 3 ACCOMPLISH FUSELAGE - SKIN - CHEM-MILLED STEPS INCROWN SKINS WITH 20 INCH TEAR STRAP BAYS ATSPECIFIED LOCATIONS - INSPECTION AND MODIFICATION(SUPERSEDED BY SB 737-53-1305 R1) SERVICE BULLETIN MODIFICATIONS

Task Relations


Model: BOEING 737-300/400/500


737-53-1305 TABLE 1.2 INSPECT FUSELAGE - SKIN - CHEM-MILLED STEPS INCROWN SKINS WITH 20 INCH TEAR STRAP BAYS ATSPECIFIED LOCATIONS - INSPECTION AND MODIFICATION(SUPERSEDED BY SB 737-53-1305 R1) SERVICE BULLETIN FOR CRACKING IN THE FUSELAGE SKIN AT THE OUTERROW OF FASTENERS COMMONTO THE MODIFICATION DOUBLERS FOR ALL INTERNALMODIFICATIONS INSTALLED IN ACCORDANCE WITH THISSERVICE BULLETIN

737-53-1305 TABLE 1.1 INSPECT FUSELAGE - SKIN - CHEM-MILLED STEPS INCROWN SKINS WITH 20 INCH TEAR STRAP BAYS ATSPECIFIED LOCATIONS - INSPECTION AND MODIFICATION(SUPERSEDED BY SB 737-53-1305 R1) SERVICE BULLETIN FOR CRACKING IN THE FUSELAGE SKIN AT THE OUTERROW OF FASTENERS COMMONTO THE MODIFICATION DOUBLERS FOR ALL EXTERNALMODIFICATIONS INSTALLED IN ACCORDANCE WITH THISSERVICE BULLETIN

737-53-1305 R1 FUSELAGE - SKIN - CHEM-MILLED STEPS IN CROWN SKINSWITH 20 INCH TEAR STRAP BAYS AT SPECIFIED LOCATIONS- INSPECTION AND MODIFICATION SERVICE BULLETIN

PRIMARY TO

737-53-1305 R1 TABLE1.1

INSPECT FUSELAGE - SKIN - CHEM-MILLED STEPS INCROWN SKINS WITH 20 INCH TEAR STRAP BAYS ATSPECIFIED LOCATIONS - INSPECTION AND MODIFICATIONSERVICE BULLETIN FOR CRACKING IN THE FUSELAGE SKINAT THE OUTER ROW OF FASTENERS COMMON TO THEMODIFICATION DOUBLERS FOR ALL EXTERNALMODIFICATIONS INSTALLED

737-53-1305 R1 PARA(E)(1)

ACCOMPLISH FUSELAGE - SKIN - CHEM-MILLED STEPS INCROWN SKINS WITH 20 INCH TEAR STRAP BAYS ATSPECIFIED LOCATIONS - INSPECTION AND MODIFICATIONSERVICE BULLETIN MODIFICATIONS

737-53-1305 R1 TABLE1.2

INSPECT FUSELAGE - SKIN - CHEM-MILLED STEPS INCROWN SKINS WITH 20 INCH TEAR STRAP BAYS ATSPECIFIED LOCATIONS - INSPECTION AND MODIFICATIONSERVICE BULLETIN FOR CRACKING IN THE FUSELAGE SKINAT THE OUTER ROW OF FASTENERS COMMONTO THE MODIFICATION DOUBLERS FOR ALL INTERNALMODIFICATIONS INSTALLED

737-53-1305 R1 TABLE 2 INSPECT FUSELAGE - SKIN - CHEM-MILLED STEPS INCROWN SKINS WITH 20 INCH TEAR STRAP BAYS ATSPECIFIED LOCATIONS - INSPECTION AND MODIFICATIONSERVICE BULLETIN FOR CRACKING IN THE FUSELAGE SKINAT THE CHEM-MILLED STEPS AT THE SPECIFIEDLOCATIONS FOR ALL INTERNAL MODIFICATIONS INSTALLED

737-53-1315 FUSELAGE - SKIN - STATION 727 TO 1016 - AFT SKININSPECTION AND REPAIR SERVICE BULLETIN

PRIMARY TO

Task Relations


Model: BOEING 737-300/400/500


737-53-1315 TABLE 1.3.2 PERFORM FUSELAGE - SKIN - STATION 727 TO 1016 - AFTSKIN INSPECTION AND REPAIR SERVICE BULLETIN ANINTERNAL DETAILED INSPECTION AND HIGH FREQUENCYEDDY CURRENT INSPECTION OF THE BONDED DOUBLERFOR DISBONDING AND CRACKS FOR AIRPLANES WITH TIMELIMITED REPAIRS

737-53-1315 TABLE 2.1.1 PERFORM FUSELAGE - SKIN - STATION 727 TO 1016 - AFTSKIN INSPECTION AND REPAIR SERVICE BULLETIN ANEXTERNAL DETAILED INSPECTION TO INSPECT FORCRACKS IN THE FUSELAGE SKIN AT THE CHEM-MILL STEPSFOR ZONE 2 FOR ALL AIRPLANES

737-53-1315 TABLE 2.1.2 PERFORM FUSELAGE - SKIN - STATION 727 TO 1016 - AFTSKIN INSPECTION AND REPAIR SERVICE BULLETIN ANEXTERNAL DETAILED INSPECTION AND AN EXTERNALSUBSURFACE EDDY CURRENT, MAGNETO OPTIC IMAGER(MOI) OR C-SCAN INSPECTION FOR CRACKS IN THEFUSELAGE SKIN AT THE CHEM-MILL STEPS IN ZONE 3 FORALL AIRPLANES

737-53-1315 TABLE 2.3.1 PERFORM FUSELAGE - SKIN - STATION 727 TO 1016 - AFTSKIN INSPECTION AND REPAIR SERVICE BULLETIN AGENERAL VISUAL INSPECTION FOR LOOSE OR MISSINGFASTENERS FOR AIRPLANES WITH TIME LIMITED REPAIRS

737-53-1315 TABLE 2.3.2 PERFORM FUSELAGE - SKIN - STATION 727 TO 1016 - AFTSKIN INSPECTION AND REPAIR SERVICE BULLETIN ANINTERNAL DETAILED INSPECTION AND HIGH FREQUENCYEDDY CURRENT INSPECTION OF THE BONDED DOUBLERFOR DISBONDING AND CRACKS FOR AIRPLANES WITH TIMELIMITED REPAIRS

737-53-1315 TABLE 2.3.3 MAKE FUSELAGE - SKIN - STATION 727 TO 1016 - AFT SKININSPECTION AND REPAIR SERVICE BULLETIN THE TIMELIMITED REPAIR PERMANENT FOR AIRPLANES WITH TIMELIMITED REPAIRS

737-53-1315 TABLE 1.3.1 PERFORM FUSELAGE - SKIN - STATION 727 TO 1016 - AFTSKIN INSPECTION AND REPAIR SERVICE BULLETIN AGENERAL VISUAL INSPECTION FOR LOOSE OR MISSINGFASTENERS FOR AIRPLANES WITH TIME LIMITED REPAIRS

737-53-1315 TABLE 1.1.3 PERFORM FUSELAGE - SKIN - STATION 727 TO 1016 - AFTSKIN INSPECTION AND REPAIR SERVICE BULLETIN ANEXTERNAL DETAILED INSPECTION AND AN EXTERNALSUBSURFACE EDDY CURRENT, MOI OR C-SCANINSPECTION FOR CRACKS IN THE FUSELAGE SKIN AT THECHEM-MILL STEPS FOR ZONE 3 FOR ALL AIRPLANES

Task Relations


Model: BOEING 737-300/400/500


737-53-1315 TABLE 1.1.2 PERFORM FUSELAGE - SKIN - STATION 727 TO 1016 - AFTSKIN INSPECTION AND REPAIR SERVICE BULLETIN ANEXTERNAL DETAILED INSPECTION TO INSPECT FORCRACKS IN THE FUSELAGE SKIN AT THE CHEM-MILL STEPSFOR ZONE 2 FOR ALL AIRPLANES

737-53-1315 TABLE 1.1.1 PERFORM FUSELAGE - SKIN - STATION 727 TO 1016 - AFTSKIN INSPECTION AND REPAIR SERVICE BULLETIN ANEXTERNAL DETAILED INSPECTION AND AN EXTERNALSUBSURFACE EDDY CURRENT, MAGNETO OPTIC IMAGER(MOI) OR C-SCAN INSPECTION FOR CRACKS IN THEFUSELAGE SKIN AT THE CHEM-MILL STEPS FOR ZONE 1FOR ALL AIRPLANES

737-53-1315 TABLE 1.3.3 MAKE FUSELAGE - SKIN - STATION 727 TO 1016 - AFT SKININSPECTION AND REPAIR SERVICE BULLETIN THE TIMELIMITED REPAIR PERMANENT FOR AIRPLANES WITH TIMELIMITED REPAIRS

737-53-1327 FUSELAGE - CARGO COMPARTMENT SIDEWALL LININGS -INSPECTION AND REPAIR SERVICE BULLETIN

PRIMARY TO737-53-1327 TABLE 1.2 REMOVE AND REPLACE FUSELAGE - CARGO

COMPARTMENT SIDEWALL LININGS - INSPECTION ANDREPAIR SERVICE BULLETIN ALUMINUM SIDEWALL LININGSWITH PRODUCTION TYPE FIBERGLASS SIDEWALL LININGS

737-53-1327 TABLE 1.3 CONTACT FUSELAGE - CARGO COMPARTMENT SIDEWALLLININGS - INSPECTION AND REPAIR SERVICE BULLETIN BOEING FOR SUB-STRUCTURE INSPECTIONS AND REPAIRINSTRUCTIONS AND DO THE WORK INSTRUCTED BYBOEING

737-53-1327 TABLE 1.1 INSPECTION FUSELAGE - CARGO COMPARTMENTSIDEWALL LININGS - INSPECTION AND REPAIR SERVICEBULLETIN OF THE FORWARD AND AFT CARGOCOMPARTMENTS SIDEWALL FOR ALL AIRPLANES


PRIMARY TO

737-53A1177 R7 TBL08.1.2

PERFORM FUSELAGE - SKIN - REPAIR METHODS FORCRACKS IN LOWER SKINS AT LAP JOINTS AND WINDOWCORNERS SERVICE BULLETIN THE PREVENTATIVEMODIFICATION PER THE SERVICE BULLETINACCOMPLISHMENT INSTRUCTIONS 3.B.5. (C) FORAIRPLANES WITH LESS THAN 50,000 TOTAL FLIGHT CYCLESAT THE REVISION 7 DATE OF THIS SERVICE BULLETIN (FORGROUP 2-17, 23-27)

Task Relations


Model: BOEING 737-300/400/500


737-53A1177 R7 TBL08.2.1

PERFORM FUSELAGE - SKIN - REPAIR METHODS FORCRACKS IN LOWER SKINS AT LAP JOINTS AND WINDOWCORNERS SERVICE BULLETIN A SURFACE HFECINSPECTION AT THE APPLICABLE FASTENER HOLES PERTHESERVICE BULLETIN ACCOMPLISHMENT INSTRUCTIONS3.B.5. (B) (C) FOR AIRPLANES WITH 50,000 OR MORE TOTALFLIGHT CYCLES AND HAVE DONE THE PREVENTATIVEMODIFICATION (FASTENER HOLE INSPECTION ANDINSTALLATION OF OVERSIZE FASTENER) PER REVISION 5OR REVISION 6 OF THIS SERVICE BULLETIN (FOR GROUP2-17, 23-27)

737-53A1177 R7 TBL08.2.2

PERFORM FUSELAGE - SKIN - REPAIR METHODS FORCRACKS IN LOWER SKINS AT LAP JOINTS AND WINDOWCORNERS SERVICE BULLETIN THE PREVENTATIVEMODIFICATION PER THE SERVICE BULLETINACCOMPLISHMENTINSTRUCTIONS 3.B.5. (C) FOR AIRPLANES WITH 50,000 ORMORE TOTAL FLIGHT CYCLESAND HAVE DONE THE PREVENTATIVE MODIFICATION(FASTENER HOLE INSPECTIONAND INSTALLATION OF OVERSIZE FASTENER) PERREVISION 5 OR REVISION 6 OF THIS SERVICE BULLETIN (FOR GROUP 2-17, 23-27)

737-53A1177 R7 TBL08.3.1

PERFORM FUSELAGE - SKIN - REPAIR METHODS FORCRACKS IN LOWER SKINS AT LAP JOINTS AND WINDOWCORNERS SERVICE BULLETIN A SURFACE HFECINSPECTION AT THE APPLICABLE FASTENER HOLES PERTHE SERVICE BULLETIN ACCOMPLISHMENT INSTRUCTIONS3.B.5. (A) (B) (C) FOR AIRPLANES WITH 50,000 OR MORETOTAL FLIGHT CYCLES AND HAVE NOT DONE THEPREVENTATIVE MODIFICATION (FASTENER HOLEINSPECTION AND INSTALLATION OF OVERSIZE FASTENER)PER REVISION 5 OR REVISION 6 OF THIS SERVICE BULLETIN(FOR GROUP 2-17, 23-27)

737-53A1177 R7 TBL08.3.2

PERFORM FUSELAGE - SKIN - REPAIR METHODS FORCRACKS IN LOWER SKINS AT LAP JOINTS AND WINDOWCORNERS SERVICE BULLETIN THE PREVENTATIVEMODIFICATION PER THE SERVICE BULLETINACCOMPLISHMENT INSTRUCTIONS 3.B.5. (C) FORAIRPLANES WITH 50,000 OR MORE TOTAL FLIGHT CYCLESAND HAVE NOT DONE THE PREVENTATIVE MODIFICATION(FASTENER HOLE INSPECTION AND INSTALLATION OFOVERSIZE FASTENER) PER REVISION 5 OR REVISION 6 OFTHIS SERVICE BULLETIN (FOR GROUP 2-17, 23-27)

Task Relations


Model: BOEING 737-300/400/500


737-53A1177 R7 TBL 08.4 REPAIR FUSELAGE - SKIN - REPAIR METHODS FOR CRACKSIN LOWER SKINS AT LAP JOINTS AND WINDOW CORNERSSERVICE BULLETIN PER THE SERVICE BULLETINACCOMPLISHMENT INSTRUCTIONS 3.B.5. FOR ANYFASTENER HOLE CRACK FOUND (FOR GROUP 2-17, 23-27)

737-53A1177 R7 TBL09.1.1

PERFORM FUSELAGE - SKIN - REPAIR METHODS FORCRACKS IN LOWER SKINS AT LAP JOINTS AND WINDOWCORNERS SERVICE BULLETIN A SURFACE HFECINSPECTION AT THE APPLICABLE FASTENER HOLES PERTHE SERVICE BULLETIN ACCOMPLISHMENT INSTRUCTIONS3.B.5. (A) (B) FOR AIRPLANES WITH LESS THAN 50,000TOTAL FLIGHT CYCLES AS OF THE RELEASE DATE OFREVISION 7 OF THIS SERVICE BULLETIN (GROUP 18-22, 28)

737-53A1177 R7 TBL09.1.2

PERFORM FUSELAGE - SKIN - REPAIR METHODS FORCRACKS IN LOWER SKINS AT LAP JOINTS AND WINDOWCORNERS SERVICE BULLETIN THE PREVENTATIVEMODIFICATION PER THE SERVICE BULLETINACCOMPLISHMENT INSTRUCTIONS 3.B.5 FOR AIRPLANESWITH LESS THAN 50,000 TOTAL FLIGHT CYCLES AS OF THERELEASE DATE OF REVISION 7 OF THIS SERVICE BULLETIN(GROUP 18-22, 28)

737-53A1177 R7 TBL09.2.1

PERFORM FUSELAGE - SKIN - REPAIR METHODS FORCRACKS IN LOWER SKINS AT LAP JOINTS AND WINDOWCORNERS SERVICE BULLETIN A SURFACE HFECINSPECTION AT THE APPLICABLE FASTENER HOLES PERTHE SERVICE BULLETIN ACCOMPLISHMENT INSTRUCTIONS3.B.5. (B) FOR AIRPLANES WITH 50,000 OR MORE TOTALFLIGHT CYCLES AND HAVE DONE THE PREVENTATIVEMODIFICATION (FASTENER HOLE INSPECTION ANDINSTALLATION OF OVERSIZE FASTENER) PER REVISION 5OR REVISION 6 OF THIS SERVICE BULLETIN (GROUP 18-22,28)

737-53A1177 R7 TBL09.2.2

PERFORM FUSELAGE - SKIN - REPAIR METHODS FORCRACKS IN LOWER SKINS AT LAP JOINTS AND WINDOWCORNERS SERVICE BULLETIN THE PREVENTATIVEMODIFICATION PER THE SERVICE BULLETINACCOMPLISHMENT INSTRUCTIONS 3.B.5. FOR AIRPLANESWITH 50,000 OR MORE TOTAL FLIGHT CYCLES AND HAVEDONE THE PREVENTATIVE MODIFICATION (FASTENER HOLEINSPECTION AND INSTALLATION OF OVERSIZE FASTENER)PER REVISION 5 OR REVISION 6 OF THIS SERVICE BULLETIN(GROUP 18-22, 28)

Task Relations


Model: BOEING 737-300/400/500


737-53A1177 R7 TBL09.3.1

PERFORM FUSELAGE - SKIN - REPAIR METHODS FORCRACKS IN LOWER SKINS AT LAP JOINTS AND WINDOWCORNERS SERVICE BULLETIN A SURFACE HFECINSPECTION AT THE APPLICABLE FASTENER HOLES PERTHE SERVICE BULLETIN ACCOMPLISHMENT INSTRUCTIONS3.B.5. (B) FOR AIRPLANES WITH 50,000 OR MORE TOTALFLIGHT CYCLES AND HAVE NOT DONE THE PREVENTATIVEMODIFICATION (FASTENER HOLE INSPECTION ANDINSTALLATION OF OVERSIZE FASTENER) PER REVISION 5OR REVISION 6 OF THIS SERVICE BULLETIN (GROUP 18-22,28)

737-53A1177 R7 TBL09.3.2

PERFORM FUSELAGE - SKIN - REPAIR METHODS FORCRACKS IN LOWER SKINS AT LAP JOINTS AND WINDOWCORNERS SERVICE BULLETIN THE PREVENTATIVEMODIFICATION PER THE SERVICE BULLETINACCOMPLISHMENT INSTRUCTIONS 3.B.5 FOR AIRPLANESWITH 50,000 OR MORE TOTAL FLIGHT CYCLES AND HAVENOT DONE THE PREVENTATIVE MODIFICATION (FASTENERHOLE INSPECTION AND INSTALLATION OF OVERSIZEFASTENER) PER REVISION 5 OR REVISION 6 OF THISSERVICE BULLETIN (GROUP 18-22, 28)

737-53A1177 R7 TBL 09.4 CONTACT FUSELAGE - SKIN - REPAIR METHODS FORCRACKS IN LOWER SKINS AT LAP JOINTS AND WINDOWCORNERS SERVICE BULLETIN BOEING FOR REPAIRINSTRUCTIONS AND DO THE WORK INSTRUCTED BYBOEING IF ANY FASTENER HOLE CRACK FOUND

737-53A1177 R7 TBL 10.1 PERFORM FUSELAGE - SKIN - REPAIR METHODS FORCRACKS IN LOWER SKINS AT LAP JOINTS AND WINDOWCORNERS SERVICE BULLETIN A SURFACE HFECINSPECTION AT THE APPLICABLE FASTENER HOLES PERTHE SERVICE BULLETIN ACCOMPLISHMENT INSTRUCTIONS3.B.5 FOR ALL AIRPLANES (GROUP 2-28)


737-53A1177 R7 TBL 11.1 PERFORM FUSELAGE - SKIN - REPAIR METHODS FORCRACKS IN LOWER SKINS AT LAP JOINTS AND WINDOWCORNERS SERVICE BULLETIN A SURFACE HFECINSPECTION AT THE APPLICABLE FASTENER HOLES PERTHESERVICE BULLETIN ACCOMPLISHMENT INSTRUCTIONS3.B.5. FOR ALL AIRPLANES (GROUP 2-28)

Task Relations


Model: BOEING 737-300/400/500



737-53A1177 R7 TBL 12.1 PERFORM FUSELAGE - SKIN - REPAIR METHODS FORCRACKS IN LOWER SKINS AT LAP JOINTS AND WINDOWCORNERS SERVICE BULLETIN AN INTERNAL HFECINSPECTION OF THE WINDOW FORGING FOR CRACKS INACCORDANCE WITH ACCOMPLISHMENT INSTRUCTIONS,3.B.1, STEP D.(2)(A). FOR WINDOW FORGINGS WITH GROUP1 FASTENER AND MINIMUM EDGE MARGIN OF 1.2D (A)(GROUP 2-28)

737-53A1177 R7 TBL 12.2 PERFORM FUSELAGE - SKIN - REPAIR METHODS FORCRACKS IN LOWER SKINS AT LAP JOINTS AND WINDOWCORNERS SERVICE BULLETIN AN INTERNAL HFECINSPECTION OF THE WINDOW FORGING FOR CRACKS INACCORDANCE WITH ACCOMPLISHMENT INSTRUCTIONS,3.B.1, STEP D.(2)(A). FOR WINDOW FORGINGS WITH GROUP2 FASTENER AND MINIMUM EDGE MARGIN OF 1.35D (A)(GROUP 2-28)

737-53A1177 R7 TBL 12.3 CONTACT FUSELAGE - SKIN - REPAIR METHODS FORCRACKS IN LOWER SKINS AT LAP JOINTS AND WINDOWCORNERS SERVICE BULLETIN BOEING FOR REPAIRINSTRUCTIONS AND DO THE REPAIR IF ANY CRACK FOUND

737-53A1177 R7 TBL 13.1 PERFORM FUSELAGE - SKIN - REPAIR METHODS FORCRACKS IN LOWER SKINS AT LAP JOINTS AND WINDOWCORNERS SERVICE BULLETIN AN EXTERNAL SURFACEINSPECTION FOR CRACKS IN THE PRODUCTION SKINAROUND THE THREE CORNER FASTENERS INACCORDANCE WITH ACCOMPLISHMENTINSTRUCTIONS, 3.B.1, STEP D.(2)(B). FOR BS 360 TO BS 540,UPPERFORWARD AND LOWER AFT WINDOW CORNERS AND BS 727TO BS 908 LOWER FORWARD AND UPPER AFT WINDOWCORNERS, PREVENTIVE MODIFICATIONACCOMPLISHED FOR 12 FASTENERS (GROUP 2-28)

737-53A1177 R7 TBL 13.2 PERFORM FUSELAGE - SKIN - REPAIR METHODS FORCRACKS IN LOWER SKINS AT LAP JOINTS AND WINDOWCORNERS SERVICE BULLETIN A SURFACE INSPECTIONFOR CRACKS OF THE REPAIR STRUCTURE AROUND THETHREE CORNER FASTENERS IN ACCORDANCE WITHACCOMPLISHMENT INSTRUCTIONS, 3.B.1,STEP D.(2)(B). FOR BS 360 TO BS 540, UPPER FORWARDAND LOWER AFT WINDOW CORNERS AND BS 727 TO BS 908LOWER FORWARD AND UPPER AFT WINDOW CORNERS,REPAIR ACCOMPLISHED PER FIGURES 15, 21, 24, 25,26, 27, 28, DRAWINGS 65C38451 OR 65C38452 (GROUP 2-28)

Task Relations


Model: BOEING 737-300/400/500


737-53A1177 R7 TBL 13.3 CONTACT FUSELAGE - SKIN - REPAIR METHODS FORCRACKS IN LOWER SKINS AT LAP JOINTS AND WINDOWCORNERS SERVICE BULLETIN BOEING FOR REPAIRINSTRUCTIONS AND DO THE REPAIR IF ANY CRACK FOUND

737-53A1177 R7 TBL 14.1 PERFORM FUSELAGE - SKIN - REPAIR METHODS FORCRACKS IN LOWER SKINS AT LAP JOINTS AND WINDOWCORNERS SERVICE BULLETIN AN INTERNAL SURFACEHFEC INSPECTION OF THE LOWER SKIN AROUND ALL S- 20LLAP JOINT LOWER FASTENER ROWS COMMON TO THEREPAIR OR MODIFICATION PER THE SERVICE BULLETINACCOMPLISHMENT INSTRUCTIONS 3.B.1.F FOR AIRPLANESWITH LESS THAN 58,000 FLIGHT CYCLES AT THE TIME OFRELEASE OF SERVICE BULLETIN 737-53A1177 REVISION 7THAT HAVE DONE THE SERVICE BULLETIN 737-53-1077MODIFICATION OR REPAIR (GROUP 2, 4-5, 7CONFIGURATION 2)

737-53A1177 R7 TBL 14.2 PERFORM FUSELAGE - SKIN - REPAIR METHODS FORCRACKS IN LOWER SKINS AT LAP JOINTS AND WINDOWCORNERS SERVICE BULLETIN AN INTERNAL SURFACEHFEC INSPECTION OF THE LOWER SKIN AROUND ALL S-20LLAP JOINT LOWER FASTENER ROWS COMMON TO THEREPAIR OR MODIFICATION PER THE SERVICE BULLETINACCOMPLISHMENT INSTRUCTIONS 3.B.1.F FOR AIRPLANESWITH 58,000 FLIGHT CYCLES OR HIGHER AT THE RELEASEOF SERVICE BULLETIN 737-53A1177 REVISION 7 THAT HAVEDONE THE SERVICE BULLETIN 737-53-1077 MODIFICATIONOR REPAIR (GROUP 2, 4-5, 7, CONFIGURATION 2)

737-53A1177 R7 TBL 14.3 CONTACT FUSELAGE - SKIN - REPAIR METHODS FORCRACKS IN LOWER SKINS AT LAP JOINTS AND WINDOWCORNERS SERVICE BULLETIN BOEING FOR REPAIR INSTRUCTIONS AND DO THE WORK INSTRUCTED BY BOEING.IF ANY FASTENER HOLE CRACK FOUND

737-53A1177 R7 TBL 15.1 PERFORM FUSELAGE - SKIN - REPAIR METHODS FORCRACKS IN LOWER SKINS AT LAP JOINTS AND WINDOWCORNERS SERVICE BULLETIN AN INTERNAL SURFACEHFEC INSPECTION OF THE LOWER SKIN AROUND ALL S-20LLAP JOINT LOWER FASTENER ROWS COMMON TO THEREPAIR OR MODIFICATIONPER THE SERVICE BULLETIN ACCOMPLISHMENTINSTRUCTIONS 3.B.1.F FOR AIRPLANES WITH LESS THAN58,000 FLIGHT CYCLES WHEN A SERVICE BULLETIN737-53-1077 MODIFICATION OR REPAIR IS INSTALLED,FOLLOWING RELEASE OF SERVICE BULLETIN 737-53A1177REVISION 7 (GROUP 2, 4-5, 7, CONFIGURATION 2)

Task Relations


Model: BOEING 737-300/400/500


737-53A1177 R7 TBL 15.2 PERFORM FUSELAGE - SKIN - REPAIR METHODS FORCRACKS IN LOWER SKINS AT LAP JOINTS AND WINDOWCORNERS SERVICE BULLETIN AN INTERNAL SURFACEHFEC INSPECTION OF THE LOWER SKIN AROUND ALL S-20LLAP JOINT LOWER FASTENER ROWS COMMON TO THEREPAIR OR MODIFICATIONPER THE SERVICE BULLETIN ACCOMPLISHMENTINSTRUCTIONS 3.B.1.F FOR AIRPLANES WITH 58,000 FLIGHTCYCLES OR HIGHER WHEN A SERVICE BULLETIN737-53-1077 MODIFICATION OR REPAIR IS INSTALLED,FOLLOWING RELEASE OF SERVICE BULLETIN 737-53A1177REVISION 7 (GROUP 2, 4-5, 7, CONFIGURATION 2)

737-53A1177 R7 TBL 15.3 CONTACT FUSELAGE - SKIN - REPAIR METHODS FORCRACKS IN LOWER SKINS AT LAP JOINTS AND WINDOWCORNERS SERVICE BULLETIN BOEING FOR REPAIR INSTRUCTIONS AND DO THE WORK INSTRUCTED BY BOEING.IF ANY FASTENER HOLE CRACK FOUND

737-53A1177 R7 TBL 16.1 PERFORM FUSELAGE - SKIN - REPAIR METHODS FORCRACKS IN LOWER SKINS AT LAP JOINTS AND WINDOWCORNERS SERVICE BULLETIN AN INTERNAL SURFACEHFEC AND DETAILED INSPECTION OF THE BUTT SPLICESTRAPAND AROUND FASTENERS FOR CRACKS PER SERVICEBULLETIN ACCOMPLISHMENTINSTRUCTIONS 3.B.10. FOR ALL AIRPLANES (GROUP 2-17,19-21, 23-27)


737-53A1177 R7 TBL 16.3 CONTACT FUSELAGE - SKIN - REPAIR METHODS FORCRACKS IN LOWER SKINS AT LAP JOINTS AND WINDOWCORNERS SERVICE BULLETIN BOEING FOR REPAIRINSTRUCTIONS AND DO THE REPAIR. IF ANY CRACK FOUND


Task Relations


Model: BOEING 737-300/400/500




737-53A1177 R7 TBL 18.1 PERFORM FUSELAGE - SKIN - REPAIR METHODS FORCRACKS IN LOWER SKINS AT LAP JOINTS AND WINDOWCORNERS SERVICE BULLETIN AN INTERNAL SURFACEHFEC AND DETAILED INSPECTION OF THE BUTT SPLICESTRAPAND AROUND FASTENERS FOR CRACKS PER SERVICEBULLETIN ACCOMPLISHMENTINSTRUCTIONS 3.B.10. FOR ALL AIRPLANES (GROUP 9-17,23-27)

737-53A1177 R7 TBL 18.2 PERFORM FUSELAGE - SKIN - REPAIR METHODS FORCRACKS IN LOWER SKINS AT LAP JOINTS AND WINDOWCORNERS SERVICE BULLETIN AN INTERNAL SURFACEHFEC AND DETAILED INSPECTION OF THE BUTT SPLICESTRAPAND AROUND FASTENERS FOR CRACKS PER SERVICEBULLETIN ACCOMPLISHMENTINSTRUCTIONS 3.B.10. FOR ALL AIRPLANES (GROUP 9-17,23-27)


737-53A1177 R7 TBL 01.1 ACCOMPLISH FUSELAGE - SKIN - REPAIR METHODS FORCRACKS IN LOWER SKINS AT LAP JOINTS AND WINDOWCORNERS SERVICE BULLETIN THE LAP JOINTMODIFICATION (REPAIR) TO THE CROWN LAP JOINTS FORALL AIRPLANES

737-53A1177 R7 TBL 02.1 PERFORM FUSELAGE - SKIN - REPAIR METHODS FORCRACKS IN LOWER SKINS AT LAP JOINTS AND WINDOWCORNERS SERVICE BULLETIN AN EXTERNAL EDDYCURRENT AND GENERAL VISUAL INSPECTION OF THE LAPJOINTS OUTSIDE THE CROWN AREA FOR CRACKS FOR ALLAIRPLANES

Task Relations


Model: BOEING 737-300/400/500


737-53A1177 R7 TBL 03 REPLACEMENT FUSELAGE - SKIN - REPAIR METHODS FORCRACKS IN LOWER SKINS AT LAP JOINTS AND WINDOWCORNERS SERVICE BULLETIN OF LOCAL LAP JOINT SRMREPAIRS

737-53A1177 R7 TBL 04.1 ACCOMPLISH FUSELAGE - SKIN - REPAIR METHODS FORCRACKS IN LOWER SKINS AT LAP JOINTS AND WINDOWCORNERS SERVICE BULLETIN INSPECTIONS (SSI F-38CAND F-38D. PRODUCTION FUSELAGE CIRCUMFERENTIALBUTT SPLICE STRUCTURE AT BS 540 AND BS 727 COMMONTO THE STRINGERS S-4 AND S-10 LAP JOINT MODIFICATION(REPAIR)) FOR GROUP 2-5 AIRPLANES

737-53A1177 R7 TBL 04.2 ACCOMPLISH FUSELAGE - SKIN - REPAIR METHODS FORCRACKS IN LOWER SKINS AT LAP JOINTS AND WINDOWCORNERS SERVICE BULLETIN INSPECTIONS (SSI F-38BAND F-38E. PRODUCTION FUSELAGE CIRCUMFERENTIALBUTT SPLICE STRUCTURE AT BS 360 AND BS 908 COMMONTO THE STRINGERS S-4 OR S-10 LAP JOINT MODIFICATION(REPAIR)) FOR GROUP 2-5 AIRPLANES

737-53A1177 R7 TBL 04.3 ACCOMPLISH FUSELAGE - SKIN - REPAIR METHODS FORCRACKS IN LOWER SKINS AT LAP JOINTS AND WINDOWCORNERS SERVICE BULLETIN INSPECTIONS (SSI F-39A,F-39B, AND F-39C. PRODUCTION FUSELAGE CROWNSTRINGERS S-4 AND S-10 COMMON TO THE LAP JOINTMODIFICATION (REPAIR)) FOR GROUP 2-5 AIRPLANES

737-53A1177 R7 TBL 04.4 ACCOMPLISH FUSELAGE - SKIN - REPAIR METHODS FORCRACKS IN LOWER SKINS AT LAP JOINTS AND WINDOWCORNERS SERVICE BULLETIN INSPECTIONS (SSI F-39F,F-39G, AND F-39H. LAP JOINT MODIFICATION(REPAIR) DOUBLER AND TRIPLER) FOR GROUP 2-5AIRPLANES

737-53A1177 R7 TBL 04.5 ACCOMPLISH FUSELAGE - SKIN - REPAIR METHODS FORCRACKS IN LOWER SKINS AT LAP JOINTS AND WINDOWCORNERS SERVICE BULLETIN INSPECTIONS (SSI F-48A.FUSELAGE SKIN LONGITUDINAL LAP SPLICES) FOR GROUP2-5 AIRPLANES

737-53A1177 R7 TBL 02.2 REPAIR FUSELAGE - SKIN - REPAIR METHODS FOR CRACKSIN LOWER SKINS AT LAP JOINTS AND WINDOW CORNERSSERVICE BULLETIN IF ANY CRACK FOUND

737-53A1177 R7 TBL 05.1 ACCOMPLISH FUSELAGE - SKIN - REPAIR METHODS FORCRACKS IN LOWER SKINS AT LAP JOINTS AND WINDOWCORNERS SERVICE BULLETIN INSPECTIONS( SSI F-38CAND F-38D. PRODUCTION FUSELAGE CIRCUMFERENTIALBUTT SPLICE STRUCTURE AT BS 540 AND BS 727 COMMONTO THE STRINGERS S-4 AND S-10 LAP JOINT MODIFICATION(REPAIR)) FOR GROUP 6-8 AIRPLANES

Task Relations


Model: BOEING 737-300/400/500


737-53A1177 R7 TBL 05.2 ACCOMPLISH FUSELAGE - SKIN - REPAIR METHODS FORCRACKS IN LOWER SKINS AT LAP JOINTS AND WINDOWCORNERS SERVICE BULLETIN INSPECTIONS (SSI F-38BAND F-38E. PRODUCTION FUSELAGE CIRCUMFERENTIALBUTT SPLICE STRUCTURE AT BS 360 AND BS 908 COMMONTO THE STRINGERS S-4 AND S-10 LAP JOINT MODIFICATION(REPAIR)) FOR GROUP 6-8 AIRPLANES

737-53A1177 R7 TBL 05.3 ACCOMPLISH FUSELAGE - SKIN - REPAIR METHODS FORCRACKS IN LOWER SKINS AT LAP JOINTS AND WINDOWCORNERS SERVICE BULLETIN INSPECTIONS (SSI F-39A,F-39B AND F-39C. PRODUCTION FUSELAGECROWN STRINGERS S-4 AND S-10 COMMON TO THE LAPJOINT MODIFICATION (REPAIR)) FOR GROUP 6-8 AIRPLANES

737-53A1177 R7 TBL 05.4 ACCOMPLISH FUSELAGE - SKIN - REPAIR METHODS FORCRACKS IN LOWER SKINS AT LAP JOINTS AND WINDOWCORNERS SERVICE BULLETIN INSPECTIONS (SSI F-39F,F-39G, AND F-39H. LAP JOINT MODIFICATION(REPAIR) DOUBLER AND TRIPLER) FOR GROUP 6-8AIRPLANES

737-53A1177 R7 TBL 05.5 ACCOMPLISH FUSELAGE - SKIN - REPAIR METHODS FORCRACKS IN LOWER SKINS AT LAP JOINTS AND WINDOWCORNERS SERVICE BULLETIN INSPECTIONS (SSI F-48A.FUSELAGE SKIN LONGITUDINAL LAP SPLICES) FOR GROUP6-8 AIRPLANES

737-53A1177 R7 TBL 06.1 ACCOMPLISH FUSELAGE - SKIN - REPAIR METHODS FORCRACKS IN LOWER SKINS AT LAP JOINTS AND WINDOWCORNERS SERVICE BULLETIN INSPECTIONS (SSI F-38BAND F-38C. PRODUCTION FUSELAGE CIRCUMFERENTIALBUTT SPLICE STRUCTURE AT BS 540 AND BS 727 COMMONTO THE STRINGERS S-4 AND S-10 LAP JOINT MODIFICATION(REPAIR)) FOR GROUP 9-17, 19-21, 23-27 AIRPLANES

737-53A1177 R7 TBL 06.2 ACCOMPLISH FUSELAGE - SKIN - REPAIR METHODS FORCRACKS IN LOWER SKINS AT LAP JOINTS AND WINDOWCORNERS SERVICE BULLETIN INSPECTIONS (SSI F-38AAND F-38D. PRODUCTION FUSELAGE CIRCUMFERENTIALBUTT SPLICE STRUCTURE AT BS 360 AND BS 908 COMMONTO THE STRINGERS S-4 OR S-10 LAP JOINT MODIFICATION(REPAIR)) FOR GROUP 9-17, 19-21, 23-27 AIRPLANES

737-53A1177 R7 TBL 06.3 ACCOMPLISH FUSELAGE - SKIN - REPAIR METHODS FORCRACKS IN LOWER SKINS AT LAP JOINTS AND WINDOWCORNERS SERVICE BULLETIN INSPECTIONS (SSI F-38GAND F-38H. PRODUCTION FUSELAGE CIRCUMFERENTIALBUTT SPLICE STRUCTURE AT BS 500C AND BS 727GCOMMON TO THE LAP JOINT MODIFICATION (REPAIR)(737-400 ONLY)) FOR GROUP 9-17, 19-21, 23-27 AIRPLANES

Task Relations


Model: BOEING 737-300/400/500


737-53A1177 R7 TBL 06.4 ACCOMPLISH FUSELAGE - SKIN - REPAIR METHODS FORCRACKS IN LOWER SKINS AT LAP JOINTS AND WINDOWCORNERS SERVICE BULLETIN INSPECTIONS (SSI F-39AAND F-39E. PRODUCTION FUSELAGECROWN STRINGERS S-4 AND S-10 COMMON TO THE LAPJOINT MODIFICATION (REPAIR)) FOR GROUP 9-17, 19-21,23-27 AIRPLANES

737-53A1177 R7 TBL 06.5 ACCOMPLISH FUSELAGE - SKIN - REPAIR METHODS FORCRACKS IN LOWER SKINS AT LAP JOINTS AND WINDOWCORNERS SERVICE BULLETIN INSPECTIONS (SSI F-39BAND F-39F. LAP JOINT MODIFICATION (REPAIR)DOUBLER AND TRIPLER) FOR GROUP 9-17, 19-21, 23-27AIRPLANES

737-53A1177 R7 TBL 06.6 ACCOMPLISH FUSELAGE - SKIN - REPAIR METHODS FORCRACKS IN LOWER SKINS AT LAP JOINTS AND WINDOWCORNERS SERVICE BULLETIN INSPECTIONS (SSI F-48B.FUSELAGE SKIN LONGITUDINAL LAP SPLICES,LOWER ROW) FOR GROUP 9-17.9-21, 23-27 AIRPLANES

737-53A1177 R7 TBL 07.1 ACCOMPLISH FUSELAGE - SKIN - REPAIR METHODS FORCRACKS IN LOWER SKINS AT LAP JOINTS AND WINDOWCORNERS SERVICE BULLETIN INSPECTIONS (SSI F-38BAND F-38C. PRODUCTION FUSELAGE CIRCUMFERENTIALBUTT SPLICE STRUCTURE AT BS 540 AND BS 727 COMMONTO THE STRINGER S-4 LAP JOINT MODIFICATION (REPAIR)(A)) FOR GROUP 9-17, 23-27 AIRPLANES

737-53A1177 R7 TBL 07.2 ACCOMPLISH FUSELAGE - SKIN - REPAIR METHODS FORCRACKS IN LOWER SKINS AT LAP JOINTS AND WINDOWCORNERS SERVICE BULLETIN INSPECTIONS (SSI F-38BAND F-38C. PRODUCTION FUSELAGE CIRCUMFERENTIALBUTT SPLICE STRUCTURE AT BS 540 AND BS 727 COMMONTO THE WINDOW BELT REPLACEMENT ABOVE STRINGERS-10) FOR GROUP 9-17, 23-27 AIRPLANES

737-53A1177 R7 TBL 07.3 ACCOMPLISH FUSELAGE - SKIN - REPAIR METHODS FORCRACKS IN LOWER SKINS AT LAP JOINTS AND WINDOWCORNERS SERVICE BULLETIN INSPECTIONS (SSI F-38AAND F-38D. PRODUCTION FUSELAGE CIRCUMFERENTIALBUTT SPLICE STRUCTURE AT BS 360 AND BS 908 COMMONTO THE LAP JOINT MODIFICATION (REPAIR) AT STRINGERS-4 AND COMMON TO THE WINDOW BELT SKIN PANELREPLACEMENT FROM ABOVE STRINGER S-9 TO BELOWS-10 (A)) FOR GROUP 9-17, 23-27 AIRPLANES

Task Relations


Model: BOEING 737-300/400/500


737-53A1177 R7 TBL 07.4 ACCOMPLISH FUSELAGE - SKIN - REPAIR METHODS FORCRACKS IN LOWER SKINS AT LAP JOINTS AND WINDOWCORNERS SERVICE BULLETIN INSPECTIONS (SSI F-39A.PRODUCTION FUSELAGE CROWN STRINGERSS-4 COMMON TO THE LAP JOINT MODIFICATION (REPAIR)AND STRINGERS S-9 AND S- 10 COMMON TO THE WINDOWBELT REPLACEMENT (A)) FOR GROUP 9-17, 23-27AIRPLANES

737-53A1177 R7 TBL 07.5 ACCOMPLISH FUSELAGE - SKIN - REPAIR METHODS FORCRACKS IN LOWER SKINS AT LAP JOINTS AND WINDOWCORNERS SERVICE BULLETIN INSPECTIONS (SSI F-39B.LAP JOINT MODIFICATION (REPAIR) DOUBLERAND TRIPLER AT STRINGER S-4 AND WINDOW BELTREPLACEMENT DOUBLER, TRIPLER AND NEW SOLID SKINABOVE S-10 (A)) FOR GROUP 9-17, 23-27 AIRPLANES

737-53A1177 R7 TBL 07.6 ACCOMPLISH FUSELAGE - SKIN - REPAIR METHODS FORCRACKS IN LOWER SKINS AT LAP JOINTS AND WINDOWCORNERS SERVICE BULLETIN INSPECTIONS (SSI F-48B.FUSELAGE SKIN LONGITUDINAL LAP SPLICES,LOWER ROW) FOR GROUP 9-17, 23-27 AIRPLANES

737-53A1177 R7 TBL08.1.1

PERFORM FUSELAGE - SKIN - REPAIR METHODS FORCRACKS IN LOWER SKINS AT LAP JOINTS AND WINDOWCORNERS SERVICE BULLETIN A SURFACE HFECINSPECTION AT THE APPLICABLE FASTENER HOLES PERTHESERVICE BULLETIN FOR AIRPLANES WITH LESS THAN50,000 TOTAL FLIGHT CYCLES AT THE REVISION 7 DATE OFTHIS SERVICE BULLETIN (FOR GROUP 2-17, 23-27)


ACD (TWO WAY) TO

737-53-1077 R2 FUSELAGE SKIN INSPECTION, REPAIR AND PREVENTIVEMODIFICATION AFT OF BS 727 BETWEEN S-18 AND S-21SERVICE BULLETIN

737-53A1322 FUSELAGE - STRINGERS AND OTHER LONGITUDINALMEMBERS - STRINGER SPLICES AND BUTT STRAPS ATBODY STATION 360 AND BODY STATION 908, STRINGERS-10L TO S-10R - INSPECTION AND REPLACEMENT SERVICEBULLETIN

737-53A1135 R2 FUSELAGE-LONGITUDINAL LAP JOINT LOWER SKIN AT LEFTAND RIGHT STRINGER 14 SERVICE BULLETIN

737-53A1042 R9 FUSELAGE - LOWER LOBE HOT-BONDED SKIN PANELINSPECTION, REPAIR, AND PANEL REPLACEMENT SERVICEBULLETIN

Task Relations


Model: BOEING 737-300/400/500


737-53A1200 R1 FUSELAGE - STRUCTURE AROUND OPENINGS - FORWARDENTRY AND FORWARD GALLEY SERVICE DOORWAY UPPERAND LOWER HINGE CUTOUT - INSPECTION (SUPERSEDEDBY SB 737-53A1200 R2) SERVICE BULLETIN

PRIMARY TO

737-53A1200 R1 PARA E.(1)

INSPECTION FUSELAGE - STRUCTURE AROUND OPENINGS- FORWARD ENTRY AND FORWARD GALLEY SERVICEDOORWAY UPPER AND LOWER HINGE CUTOUT -INSPECTION (SUPERSEDED BY SB 737-53A1200 R2)SERVICE BULLETIN OF FORWARD ENTRY DOORWAY -UPPER HINGE CUTOUT

737-53A1200 R1 PARA E.(2)

INSPECTION FUSELAGE - STRUCTURE AROUND OPENINGS- FORWARD ENTRY AND FORWARD GALLEY SERVICEDOORWAY UPPER AND LOWER HINGE CUTOUT -INSPECTION (SUPERSEDED BY SB 737-53A1200 R2)SERVICE BULLETIN OF FORWARD ENTRY DOORWAY -LOWER HINGE CUTOUT

737-53A1200 R1 PARA E.(3)

INSPECTION FUSELAGE - STRUCTURE AROUND OPENINGS- FORWARD ENTRY AND FORWARD GALLEY SERVICEDOORWAY UPPER AND LOWER HINGE CUTOUT -INSPECTION (SUPERSEDED BY SB 737-53A1200 R2)SERVICE BULLETIN OF FORWARD GALLEY SERVICEDOORWAY - UPPER HINGE CUTOUT

737-53A1200 R1 PARA E.(4)

INSPECTION FUSELAGE - STRUCTURE AROUND OPENINGS- FORWARD ENTRY AND FORWARD GALLEY SERVICEDOORWAY UPPER AND LOWER HINGE CUTOUT -INSPECTION (SUPERSEDED BY SB 737-53A1200 R2)SERVICE BULLETIN OF FORWARD GALLEY SERVICEDOORWAY - LOWER HINGE CUTOUT

737-53A1200 R2 FUSELAGE - STRUCTURE AROUND OPENINGS - FORWARDENTRY AND FORWARD GALLEY SERVICE DOORWAY UPPERAND LOWER HINGE CUTOUT - INSPECTION SERVICEBULLETIN

PRIMARY TO

737-53A1200 R2 PARA E.(1.3)

ACCOMPLISH FUSELAGE - STRUCTURE AROUNDOPENINGS - FORWARD ENTRY AND FORWARD GALLEYSERVICE DOORWAY UPPER AND LOWER HINGE CUTOUT -INSPECTION SERVICE BULLETIN OPTION B (2) ONFORWARD ENTRY DOORWAY- UPPER HINGE CUTOUT

737-53A1200 R2 PARA E.(1.4)

ACCOMPLISH FUSELAGE - STRUCTURE AROUNDOPENINGS - FORWARD ENTRY AND FORWARD GALLEYSERVICE DOORWAY UPPER AND LOWER HINGE CUTOUT -INSPECTION SERVICE BULLETIN INSPECTIONS FORAIRPLANES WITH SRM REPAIRS

737-53A1200 R2 PARA E.(1.5)

CONTACT FUSELAGE - STRUCTURE AROUND OPENINGS -FORWARD ENTRY AND FORWARD GALLEY SERVICEDOORWAY UPPER AND LOWER HINGE CUTOUT -INSPECTION SERVICE BULLETIN BOEING

Task Relations


Model: BOEING 737-300/400/500


737-53A1200 R2 PARA E.(2.2)

ACCOMPLISH FUSELAGE - STRUCTURE AROUNDOPENINGS - FORWARD ENTRY AND FORWARD GALLEYSERVICE DOORWAY UPPER AND LOWER HINGE CUTOUT -INSPECTION SERVICE BULLETIN OPTION B (1) ONFORWARD ENTRY DOORWAY - LOWER HINGE CUTOUT

737-53A1200 R2 PARA E.(2.3)

ACCOMPLISH FUSELAGE - STRUCTURE AROUNDOPENINGS - FORWARD ENTRY AND FORWARD GALLEYSERVICE DOORWAY UPPER AND LOWER HINGE CUTOUT -INSPECTION SERVICE BULLETIN OPTION B (2) ONFORWARD ENTRY DOORWAY - LOWER HINGE CUTOUT

737-53A1200 R2 PARA E.(2.4)


737-53A1200 R2 PARA E.(2.5)


737-53A1200 R2 PARA E.(3.2)

ACCOMPLISH FUSELAGE - STRUCTURE AROUNDOPENINGS - FORWARD ENTRY AND FORWARD GALLEYSERVICE DOORWAY UPPER AND LOWER HINGE CUTOUT -INSPECTION SERVICE BULLETIN OPTION B (1) ONFORWARD GALLEY SERVICE DOORWAY - UPPER HINGECUTOUT

737-53A1200 R2 PARA E.(3.3)

ACCOMPLISH FUSELAGE - STRUCTURE AROUNDOPENINGS - FORWARD ENTRY AND FORWARD GALLEYSERVICE DOORWAY UPPER AND LOWER HINGE CUTOUT -INSPECTION SERVICE BULLETIN OPTION B (2) ONFORWARD GALLEY SERVICE DOORWAY - UPPER HINGECUTOUT

737-53A1200 R2 PARA E.(3.4)


737-53A1200 R2 PARA E.(3.5)


737-53A1200 R2 PARA E.(4.2)

ACCOMPLISH FUSELAGE - STRUCTURE AROUNDOPENINGS - FORWARD ENTRY AND FORWARD GALLEYSERVICE DOORWAY UPPER AND LOWER HINGE CUTOUT -INSPECTION SERVICE BULLETIN OPTION B (1) ONFORWARD GALLEY SERVICE DOORWAY - LOWER HINGECUTOUT

Task Relations


Model: BOEING 737-300/400/500


737-53A1200 R2 PARA E.(4.3)

ACCOMPLISH FUSELAGE - STRUCTURE AROUNDOPENINGS - FORWARD ENTRY AND FORWARD GALLEYSERVICE DOORWAY UPPER AND LOWER HINGE CUTOUT -INSPECTION SERVICE BULLETIN OPTION B (2) ONFORWARD GALLEY SERVICE DOORWAY - LOWER HINGECUTOUT

737-53A1200 R2 PARA E.(4.4)


737-53A1200 R2 PARA E.(4.5)


737-53A1200 R2 PARA E.(1.2)

ACCOMPLISH FUSELAGE - STRUCTURE AROUNDOPENINGS - FORWARD ENTRY AND FORWARD GALLEYSERVICE DOORWAY UPPER AND LOWER HINGE CUTOUT -INSPECTION SERVICE BULLETIN OPTION B (1) ONFORWARD ENTRY DOORWAY - UPPER HINGE CUTOUT

737-53A1200 R2 PARA E.(4.1)

ACCOMPLISH FUSELAGE - STRUCTURE AROUNDOPENINGS - FORWARD ENTRY AND FORWARD GALLEYSERVICE DOORWAY UPPER AND LOWER HINGE CUTOUT -INSPECTION SERVICE BULLETIN OPTION A ON FORWARDGALLEY SERVICE DOORWAY - LOWER HINGE CUTOUT

737-53A1200 R2 PARA E.(3.1)

ACCOMPLISH FUSELAGE - STRUCTURE AROUNDOPENINGS - FORWARD ENTRY AND FORWARD GALLEYSERVICE DOORWAY UPPER AND LOWER HINGE CUTOUT -INSPECTION SERVICE BULLETIN OPTION A ON FORWARDGALLEY SERVICE DOORWAY - UPPER HINGE CUTOUT

737-53A1200 R2 PARA E.(1.1)

ACCOMPLISH FUSELAGE - STRUCTURE AROUNDOPENINGS - FORWARD ENTRY AND FORWARD GALLEYSERVICE DOORWAY UPPER AND LOWER HINGE CUTOUT -INSPECTION SERVICE BULLETIN OPTION A ON FORWARDENTRY DOORWAY - UPPER HINGE CUTOUT

737-53A1200 R2 PARA E.(2.1)

ACCOMPLISH FUSELAGE - STRUCTURE AROUNDOPENINGS - FORWARD ENTRY AND FORWARD GALLEYSERVICE DOORWAY UPPER AND LOWER HINGE CUTOUT -INSPECTION SERVICE BULLETIN OPTION A ON FORWARDENTRY DOORWAY - LOWER HINGE CUTOUT


PRIMARY TO

Task Relations


Model: BOEING 737-300/400/500


737-53A1204 R2 TABLE 4 DETAILED INSPECTION FUSELAGE - MAIN FRAME - FRAMESAND BULKHEADS - BODY STATION BS 360 - BS 348.2 AND BS303.9 - BS 294.5 STRINGERS S-7L - S-16L LEFTINTERCOSTAL INSPECTION / REPAIR / MODIFICATIONSERVICE BULLETIN AND HIGH FREQUENCY EDDYCURRENT (HFEC) INSPECTION FOR CRACKS INACCORDANCE WITH ACCOMPLISHMENT INSTRUCTIONS 3.BPART 4. AT INTERCOSTAL LOCATION S-16L FROM BS 348.2TO BS 360, GROUP 4

737-53A1204 R2 TABLE 5 DETAILED INSPECTION FUSELAGE - MAIN FRAME - FRAMESAND BULKHEADS - BODY STATION BS 360 - BS 348.2 AND BS303.9 - BS 294.5 STRINGERS S-7L - S-16L LEFTINTERCOSTAL INSPECTION / REPAIR / MODIFICATIONSERVICE BULLETIN AND HIGH FREQUENCY EDDYCURRENT (HFEC) INSPECTION FOR CRACKS INACCORDANCE WITH ACCOMPLISHMENT INSTRUCTIONS 3.BPART 5. AT INTERCOSTAL LOCATIONS S-7L TO S-15L FROMBS 348.2 TO BS 360 AND S-7L TO S-16L FROM BS 294.5 TOBS 303.9 GROUP 4

737-53A1204 R2 TABLE 3 DETAILED INSPECTION FUSELAGE - MAIN FRAME - FRAMESAND BULKHEADS - BODY STATION BS 360 - BS 348.2 AND BS303.9 - BS 294.5 STRINGERS S-7L - S-16L LEFTINTERCOSTAL INSPECTION / REPAIR / MODIFICATIONSERVICE BULLETIN IN ACCORDANCE WITHACCOMPLISHMENT INSTRUCTIONS 3.B PART 3. ATINTERCOSTAL LOCATIONS S-7L TO S-16L FROM BS 294.5 TOBS 303.9, AND AT INTERCOSTAL LOCATIONS S-8L, S-10L,S-12L, S-14L,S-15L AND S-16L FROM BS 348.2 TO BS 360 GROUP 2

737-53A1204 R2 TABLE 1 DETAILED INSPECTION FUSELAGE - MAIN FRAME - FRAMESAND BULKHEADS - BODY STATION BS 360 - BS 348.2 AND BS303.9 - BS 294.5 STRINGERS S-7L - S-16L LEFTINTERCOSTAL INSPECTION / REPAIR / MODIFICATIONSERVICE BULLETIN AND HIGH FREQUENCY EDDYCURRENT (HFEC) INSPECTION FOR CRACKS INACCORDANCE WITH ACCOMPLISHMENT INSTRUCTIONS 3.B.PART 1. AT INTERCOSTAL LOCATION S-16L FROM BS 348.2TO BS 360, GROUP 1,3

737-53A1204 R2 TABLE 2 DETAILED INSPECTION FUSELAGE - MAIN FRAME - FRAMESAND BULKHEADS - BODY STATION BS 360 - BS 348.2 AND BS303.9 - BS 294.5 STRINGERS S-7L - S-16L LEFTINTERCOSTAL INSPECTION / REPAIR / MODIFICATIONSERVICE BULLETIN AND HIGH FREQUENCY EDDYCURRENT (HFEC) INSPECTION FOR CRACKS INACCORDANCE WITH ACCOMPLISHMENT INSTRUCTIONS 3.BPART 2. AT INTERCOSTAL LOCATIONS S-7L TO S-15L FROMBS 348.2 TO BS 360 AND S-7L TO S-16L FROM BS 294.5 TOBS 303.9, GROUP 1,3

Task Relations


Model: BOEING 737-300/400/500


737-53A1214 R3 FUSELAGE - BODY STATION 1016 AFT PRESSUREBULKHEAD WEB CRACKS - INSPECTION AND REPAIR(SUPERSEDED BY SB 737-53A1214 R4) SERVICE BULLETIN

PRIMARY TO

737-53A1214 R3 TABLE8.1

HFEC FUSELAGE - BODY STATION 1016 AFT PRESSUREBULKHEAD WEB CRACKS - INSPECTION AND REPAIR(SUPERSEDED BY SB 737-53A1214 R4) SERVICE BULLETIN INSPECTION OF THE WEB AT FASTENER LOCATIONS TO ATEAR STRAP IN ACCORDANCE WITH APPENDIX A (OR) ATTHE OPERATORS OPTION, DO A LFEC INSPECTION OF THEWEB

737-53A1214 R3 TABLE1.2

EDDY CURRENT INSPECTION FUSELAGE - BODY STATION1016 AFT PRESSURE BULKHEAD WEB CRACKS -INSPECTION AND REPAIR (SUPERSEDED BY SB 737-53A1214R4) SERVICE BULLETIN AND DETAILED INSPECTION FORANY CRACKING AND ANY INCORRECTLY DRILLED ORELONGATED FASTENER HOLE(S) - NDT INSPECTION OFWEB AT "Y" CHORD IN THE UPPER BULKHEAD FROM S-15LTO S-15R

737-53A1214 R3 TABLE 7 DETAIL INSPECTION FUSELAGE - BODY STATION 1016 AFTPRESSURE BULKHEAD WEB CRACKS - INSPECTION ANDREPAIR (SUPERSEDED BY SB 737-53A1214 R4) SERVICEBULLETIN OF THE BULKHEAD WEB AND STIFFENERS TOFIND EXISTING REPAIRS ON THE BULKHEAD FOR ALLAIRPLANES

737-53A1214 R3 TABLE8.5

REMOVE AND REPLACE FUSELAGE - BODY STATION 1016AFT PRESSURE BULKHEAD WEB CRACKS - INSPECTIONAND REPAIR (SUPERSEDED BY SB 737-53A1214 R4)SERVICE BULLETIN THE EXISTING REPAIR INACCORDANCE WITH 737-100/200 SRM 53-10-4, FIGURE 3AREPAIR, OR 737-300 SRM 53-80-08 REPAIR 11 OR 737-400SRM 53-10-4 REPAIR 11 OR 737-500 SRM 53-80-08 REPAIR 11AS APPLICABLE.

737-53A1214 R3 TABLE 6 HFEC FUSELAGE - BODY STATION 1016 AFT PRESSUREBULKHEAD WEB CRACKS - INSPECTION AND REPAIR(SUPERSEDED BY SB 737-53A1214 R4) SERVICE BULLETIN -NDT INSPECTION OF THE FORWARD FLANGE OF THE "Z"STIFFENERS AT THE DOME CAP

737-53A1214 R3 TABLE 5 EDDY CURRENT INSPECTION FUSELAGE - BODY STATION1016 AFT PRESSURE BULKHEAD WEB CRACKS -INSPECTION AND REPAIR (SUPERSEDED BY SB 737-53A1214R4) SERVICE BULLETIN - NDT INSPECTION OF THE DOMECAP AT THE CENTER OF THE BULKHEAD

737-53A1214 R3 TABLE4.3.2

INSTALL FUSELAGE - BODY STATION 1016 AFT PRESSUREBULKHEAD WEB CRACKS - INSPECTION AND REPAIR(SUPERSEDED BY SB 737-53A1214 R4) SERVICE BULLETIN THE REPAIR FOR OIL-CANS FOUND WITHIN LIMITS DEFINEDIN SRM WHEN THE REPAIRS CAN BE DEFERRED (OPTION 1)

Task Relations


Model: BOEING 737-300/400/500


737-53A1214 R3 TABLE4.3.1

DETAIL INSPECTION FUSELAGE - BODY STATION 1016 AFTPRESSURE BULKHEAD WEB CRACKS - INSPECTION ANDREPAIR (SUPERSEDED BY SB 737-53A1214 R4) SERVICEBULLETIN AND NDT INSPECTION FOR OIL-CANS FOUNDWITHIN LIMITS DEFINED IN SRM WHEN THE REPAIRS CANBE DEFERRED (OPTION 1)

737-53A1214 R3 TABLE4.2

DETAILED INSPECTION FUSELAGE - BODY STATION 1016AFT PRESSURE BULKHEAD WEB CRACKS - INSPECTIONAND REPAIR (SUPERSEDED BY SB 737-53A1214 R4)SERVICE BULLETIN FOR NO OIL-CANS ON - INITIALINSPECTION OR REPEAT INSPECTIONS

737-53A1214 R3 TABLE4.1

INITIAL FUSELAGE - BODY STATION 1016 AFT PRESSUREBULKHEAD WEB CRACKS - INSPECTION AND REPAIR(SUPERSEDED BY SB 737-53A1214 R4) SERVICE BULLETIN DETAILED INSPECTION FOR OIL-CANS

737-53A1214 R3 TABLE 3 EDDY CURRENT INSPECTION FUSELAGE - BODY STATION1016 AFT PRESSURE BULKHEAD WEB CRACKS -INSPECTION AND REPAIR (SUPERSEDED BY SB 737-53A1214R4) SERVICE BULLETIN FOR ANY CRACKING - NDTINSPECTION UNDER TEAR STRAP

737-53A1214 R3 TABLE 2 EDDY CURRENT INSPECTION FUSELAGE - BODY STATION1016 AFT PRESSURE BULKHEAD WEB CRACKS -INSPECTION AND REPAIR (SUPERSEDED BY SB 737-53A1214R4) SERVICE BULLETIN AND DETAILED INSPECTION FORANY CRACKING AND FOR ANY INCORRECTLY DRILLED ORELONGATED FASTENER HOLE(S) OR CORROSION - NDTINSPECTION OF WEB AT "Y" CHORD IN THE LOWERBULKHEAD FROM S-15L TO S-15R

737-53A1214 R3 TABLE1.1

EDDY CURRENT INSPECTION FUSELAGE - BODY STATION1016 AFT PRESSURE BULKHEAD WEB CRACKS -INSPECTION AND REPAIR (SUPERSEDED BY SB 737-53A1214R4) SERVICE BULLETIN AND DETAILED INSPECTION FORANY CRACKING AND ANY INCORRECTLY DRILLED ORELONGATED FASTENER HOLE(S) - NDT INSPECTION OFWEB AT "Y" CHORD IN THE UPPER BULKHEAD FROM S-15LTO S-15R


PRIMARY TO

737-53A1214 R4 TABLE3.2

EDDY-CURRENT INSPECTION FUSELAGE - BODY STATION1016 AFT PRESSURE BULKHEAD WEB CRACKS -INSPECTION AND REPAIR SERVICE BULLETIN FOR ANYCRACKING - NDT INSPECTION UNDER TEAR STRAP (15,000TOTAL FLIGHT CYCLES OR MORE)

Task Relations


Model: BOEING 737-300/400/500


737-53A1214 R4 TABLE 7 DETAILED INSPECTION FUSELAGE - BODY STATION 1016AFT PRESSURE BULKHEAD WEB CRACKS - INSPECTIONAND REPAIR SERVICE BULLETIN OF THE BULKHEAD WEBAND STIFFENERS TO FIND EXISTING REPAIRS ON THEBULKHEAD FOR ALL AIRPLANES

737-53A1214 R4 TABLE 5 EDDY-CURRENT INSPECTION FUSELAGE - BODY STATION1016 AFT PRESSURE BULKHEAD WEB CRACKS -INSPECTION AND REPAIR SERVICE BULLETIN - NDTINSPECTION OF THE DOME CAP AT THE CENTER OF THEBULKHEAD

737-53A1214 R4 TABLE 6 HFEC FUSELAGE - BODY STATION 1016 AFT PRESSUREBULKHEAD WEB CRACKS - INSPECTION AND REPAIRSERVICE BULLETIN - NDT INSPECTION OF THE FORWARDFLANGE OF THE "Z" STIFFENERS AT THE DOME CAP

737-53A1214 R4 TABLE4.1

DETAILED INSPECTION FUSELAGE - BODY STATION 1016AFT PRESSURE BULKHEAD WEB CRACKS - INSPECTIONAND REPAIR SERVICE BULLETIN (INITIAL) FOR OIL-CANS

737-53A1214 R4 TABLE4.3

DETAILED INSPECTION FUSELAGE - BODY STATION 1016AFT PRESSURE BULKHEAD WEB CRACKS - INSPECTIONAND REPAIR SERVICE BULLETIN FOR NO OIL-CANS ON -INITIAL INSPECTION OR REPEAT INSPECTIONS

737-53A1214 R4 TABLE4.5.1

DETAILED INSPECTION FUSELAGE - BODY STATION 1016AFT PRESSURE BULKHEAD WEB CRACKS - INSPECTIONAND REPAIR SERVICE BULLETIN AND NDT INSPECTIONFOR OIL-CANS FOUND WITHIN LIMITS DEFINED IN SRMWHEN THE REPAIRS CAN BE DEFERRED (OPTION 1)

737-53A1214 R4 TABLE1.2

EDDY-CURRENT INSPECTION FUSELAGE - BODY STATION1016 AFT PRESSURE BULKHEAD WEB CRACKS -INSPECTION AND REPAIR SERVICE BULLETIN ANDDETAILED INSPECTION FOR ANY CRACKING AND ANYINCORRECTLY DRILLED OR ELONGATED FASTENERHOLE(S) OF WEB AT "Y" CHORD IN THE UPPER BULKHEADFROM S-15L TO S-15R EXCEPT S-5L TO S-7L AND S-5R TOS-9R (25000 TOTAL FLIGHT CYCLES OR MORE)

737-53A1214 R4 TABLE1.1

EDDY-CURRENT INSPECTION FUSELAGE - BODY STATION1016 AFT PRESSURE BULKHEAD WEB CRACKS -INSPECTION AND REPAIR SERVICE BULLETIN ANDDETAILED INSPECTION FOR ANY CRACKING AND ANYINCORRECTLY DRILLED OR ELONGATED FASTENERHOLE(S) OF WEB AT "Y" CHORD IN THE UPPERBULKHEAD FROM S-5L TO S-7L AND S-5R TO S9R (25,000TOTALFLIGHT CYCLES OR MORE)

Task Relations


Model: BOEING 737-300/400/500


737-53A1214 R4 TABLE2.1

EDDY-CURRENT INSPECTION FUSELAGE - BODY STATION1016 AFT PRESSURE BULKHEAD WEB CRACKS -INSPECTION AND REPAIR SERVICE BULLETIN ANDDETAILED INSPECTION FOR ANY CRACKING AND FOR ANYINCORRECTLY DRILLED OR ELONGATED FASTENERHOLE(S) OR CORROSION OF WEB AT "Y" CHORD IN THELOWER BULKHEAD FROM S-15L TO S-15R (LESS THAN 24000TOTAL FLIGHT CYCLES)

737-53A1214 R4 TABLE2.2

EDDY-CURRENT INSPECTION FUSELAGE - BODY STATION1016 AFT PRESSURE BULKHEAD WEB CRACKS -INSPECTION AND REPAIR SERVICE BULLETIN ANDDETAILED INSPECTION FOR ANY CRACKING AND FOR ANYINCORRECTLY DRILLED OR ELONGATED FASTENERHOLE(S) OR CORROSION OF WEB AT "Y" CHORD IN THELOWER BULKHEAD FROM S-15L TO S-15R (24,000 TOTALFLIGHT CYCLES OR MORE)

737-53A1214 R4 TABLE3.1

EDDY-CURRENT INSPECTION FUSELAGE - BODY STATION1016 AFT PRESSURE BULKHEAD WEB CRACKS -INSPECTION AND REPAIR SERVICE BULLETIN OR ANYCRACKING - NDT INSPECTION UNDER TEAR STRAP (LESSTHAN 15,000TOTAL FLIGHT CYCLES)

737-53A1214 R4 TABLE8.5

REMOVE FUSELAGE - BODY STATION 1016 AFT PRESSUREBULKHEAD WEB CRACKS - INSPECTION AND REPAIRSERVICE BULLETIN THE EXISTING REPAIR AND REPLACETHE EXISTING REPAIR AND REPLACE IN ACCORDANCEWITH 737-100/200 SRM 53-10-4, FIGURE 3A REPAIR, OR737-300 SRM 53-80-08, REPAIR 11 OR 737-400 SRM 53-80-08 ,REPAIR 11 OR 737-500 SRM 53-80-08, REPAIR 11 ASAPPLICABLE

737-53A1214 R4 TABLE8.1

HFEC FUSELAGE - BODY STATION 1016 AFT PRESSUREBULKHEAD WEB CRACKS - INSPECTION AND REPAIRSERVICE BULLETIN INSPECTION OF THE WEB ATFASTENER LOCATIONS TO A TEAR STRAP (OR) AT THEOPERATORS OPTION, DO A LFEC INSPECTION OF THE WEB

737-53A1214 R4 TABLE4.5.2

INSTALL FUSELAGE - BODY STATION 1016 AFT PRESSUREBULKHEAD WEB CRACKS - INSPECTION AND REPAIRSERVICE BULLETIN THE REPAIR OIL-CANS FOUND WITHINLIMITS DEFINED IN SRM WHEN THE REPAIRS CAN BEDEFERRED (OPTION 1)

737-53A1240 R1 FUSELAGE - FRAMES AND BULKHEADS - FORWARD DOOR,INSPECTION AND REPAIR OF INNER FRAME CHORD,STRINGERS AND INTERCOSTALS SERVICE BULLETIN

PRIMARY TO

Task Relations


Model: BOEING 737-300/400/500


737-53A1240 R1 TABLE3.2

EDDY CURRENT INSPECTION FUSELAGE - FRAMES ANDBULKHEADS - FORWARD DOOR, INSPECTION AND REPAIROF INNER FRAME CHORD, STRINGERS AND INTERCOSTALSSERVICE BULLETIN FOR CRACKING OF THE FRAME,REINFORCEMENT ANGLE, AND SHEAR WEB INACCORDANCE WITH PARAGRAPH 3.B., WORKINSTRUCTIONS, STEP 3.B.3.B. DO A DETAILED INSPECTIONFOR CRACKING OF THE STA 348.2 FRAME OUTER CHORD,INNER CHORD AND REINFORCEMENT ANGLE INACCORDANCE WITH PARAGRAPH 3.B., WORKINSTRUCTIONS, STEP 3.B.3.B (GROUP 3)

737-53A1240 R1 TABLE2.2

EDDY CURRENT INSPECTION FUSELAGE - FRAMES ANDBULKHEADS - FORWARD DOOR, INSPECTION AND REPAIROF INNER FRAME CHORD, STRINGERS AND INTERCOSTALSSERVICE BULLETIN FOR CRACKING OF THE FRAME,REINFORCEMENT ANGLE, AND SHEAR WEB INACCORDANCE WITH PARAGRAPH 3.B., WORKINSTRUCTIONS, STEP 3.B.3.B. DO A DETAILED INSPECTIONFOR CRACKING OF THE STA 348.2 FRAME OUTER CHORD,INNER CHORD AND REINFORCEMENT ANGLE INACCORDANCE WITH PARAGRAPH 3.B., WORKINSTRUCTIONS, STEP 3.B.3.B. (GROUP 2)

737-53A1240 R1 TABLE2.1

INSPECT FUSELAGE - FRAMES AND BULKHEADS -FORWARD DOOR, INSPECTION AND REPAIR OF INNERFRAME CHORD, STRINGERS AND INTERCOSTALS SERVICEBULLETIN FOR MISSING FASTENERS IN ACCORDANCEWITH PARAGRAPH 3.B., WORK INSTRUCTIONS, STEP3.B.3.A. (GROUPS 2)

737-53A1240 R1 TABLE3.1

INSPECT FUSELAGE - FRAMES AND BULKHEADS -FORWARD DOOR, INSPECTION AND REPAIR OF INNERFRAME CHORD, STRINGERS AND INTERCOSTALS SERVICEBULLETIN FOR MISSING FASTENERS IN ACCORDANCEWITH PARAGRAPH 3.B., WORK INSTRUCTIONS, STEP 3.B.3.A(GROUP 3)

737-53A1240 R1 TABLE 1 EDDY CURRENT INSPECTION FUSELAGE - FRAMES ANDBULKHEADS - FORWARD DOOR, INSPECTION AND REPAIROF INNER FRAME CHORD, STRINGERS AND INTERCOSTALSSERVICE BULLETIN FOR CRACKING OF THE FRAME INACCORDANCE WITH PARAGRAPH 3.B., WORKINSTRUCTIONS, PART 1. DO A DETAILED INSPECTION FORCRACKING OF THE FRAME INNER CHORD AND OUTERCHORD IN ACCORDANCE WITH PARAGRAPH 3.B., WORKINSTRUCTIONS, PART 1. (GROUP 1)

737-53A1241 R1 FUSELAGE - FRAMES AND BULKHEADS - STA 277 TO STA328 FRAME INSPECTIONS, STRINGER 7R TO 17R -FORWARD GALLEY DOOR CUTOUT SERVICE BULLETIN

PRIMARY TO

Task Relations


Model: BOEING 737-300/400/500


737-53A1241 R1 GRP 2TBL1.05

CONTACT FUSELAGE - FRAMES AND BULKHEADS - STA 277TO STA 328 FRAME INSPECTIONS, STRINGER 7R TO 17R -FORWARD GALLEY DOOR CUTOUT SERVICE BULLETIN BOEING TO GET INSTRUCTIONS FOR REPAIR AND DO THEWORK INSTRUCTED (IF ANY CRACK IS FOUND IN THE STA291.5 FRAME WEB BETWEEN S-8R TO S-15R)

737-53A1241 R1 GRP 2TBL1.06

REMOVE AND INSTALL FUSELAGE - FRAMES ANDBULKHEADS - STA 277 TO STA 328 FRAME INSPECTIONS,STRINGER 7R TO 17R - FORWARD GALLEY DOOR CUTOUTSERVICE BULLETIN NEW PART(S) (IF ANY CRACK IS FOUNDIN THE INTERCOSTAL(S))

737-53A1241 R1 GRP 2TBL1.07

REMOVE AND INSTALL FUSELAGE - FRAMES ANDBULKHEADS - STA 277 TO STA 328 FRAME INSPECTIONS,STRINGER 7R TO 17R - FORWARD GALLEY DOOR CUTOUTSERVICE BULLETIN NEW PART(S) (IF ANY CRACK IS FOUNDIN THE INNER CHORD OF THE DOOR HINGEINTERCOSTAL(S))

737-53A1241 R1 GRP 2TBL1.08

REMOVE AND INSTALL FUSELAGE - FRAMES ANDBULKHEADS - STA 277 TO STA 328 FRAME INSPECTIONS,STRINGER 7R TO 17R - FORWARD GALLEY DOOR CUTOUTSERVICE BULLETIN NEW PART(S) (IF ANY CRACK IS FOUNDIN THE FORWARD INNER RADIUS TRIMOUT OF THEINTERCOSTAL AT STRINGER 14R)

737-53A1241 R1 GRP 2TBL1.09

REPAIR FUSELAGE - FRAMES AND BULKHEADS - STA 277TO STA 328 FRAME INSPECTIONS, STRINGER 7R TO 17R -FORWARD GALLEY DOOR CUTOUT SERVICE BULLETIN THEFRAME (IF ANY CRACK IS FOUND AT THE STA 277 FRAMEWEB AROUND THE CUTOUT FOR STRINGER 16R)

737-53A1241 R1 GRP 2TBL1.10

REPAIR FUSELAGE - FRAMES AND BULKHEADS - STA 277TO STA 328 FRAME INSPECTIONS, STRINGER 7R TO 17R -FORWARD GALLEY DOOR CUTOUT SERVICE BULLETIN THEFRAME (IF ANY CRACK IS FOUND AT THE STA 277 Z FRAMEBETWEEN STRINGER 7R AND 13R)

737-53A1241 R1 GRP 2TBL1.11

REMOVE AND INSTALL FUSELAGE - FRAMES ANDBULKHEADS - STA 277 TO STA 328 FRAME INSPECTIONS,STRINGER 7R TO 17R - FORWARD GALLEY DOOR CUTOUTSERVICE BULLETIN NEW PART(S) (IF ANY OTHER CRACK ISFOUND AT THE STA 277 FRAME, FRAME SHEAR TIES ANDSTRINGER CLIPS FROM STRINGER 7R TO STRINGER 17R)

737-53A1241 R1 GRP 2TBL1.12

CONTACT FUSELAGE - FRAMES AND BULKHEADS - STA 277TO STA 328 FRAME INSPECTIONS, STRINGER 7R TO 17R -FORWARD GALLEY DOOR CUTOUT SERVICE BULLETIN BOEING TO GET INSTRUCTIONS FOR REPAIR AND DO THEWORK INSTRUCTED (IF ANY CRACK IS FOUND IN THE STA291.5 FRAME OUTER CHORD)

Task Relations


Model: BOEING 737-300/400/500


737-53A1241 R1 GRP 3TBL2.01

DETAILED FUSELAGE - FRAMES AND BULKHEADS - STA 277TO STA 328 FRAME INSPECTIONS, STRINGER 7R TO 17R -FORWARD GALLEY DOOR CUTOUT SERVICE BULLETIN ANDA SURFACE HFEC INSPECTION OF THE STA 291.5 FRAMEWEB AROUND THE STRINGER 16R INTERCOSTAL STRAPCUTOUT FOR ANY CRACK (AIRPLANES WITH LESS THAN OREQUAL TO 35,500 FLIGHT CYCLES ON THE EFFECTIVE DATEOF AD 2005-07-12 AND HAVE NOT STARTED INSPECTIONS INACCORDANCE WITH THE ORIGINAL ISSUE OF THIS SERVICEBULLETIN)

737-53A1241 R1 GRP 3TBL2.02

DETAILED FUSELAGE - FRAMES AND BULKHEADS - STA 277TO STA 328 FRAME INSPECTIONS, STRINGER 7R TO 17R -FORWARD GALLEY DOOR CUTOUT SERVICE BULLETIN ANDA SURFACE HFEC INSPECTION OF THE STA 291.5 FRAMEWEB AROUND THE STRINGER 16R INTERCOSTAL STRAPCUTOUT FOR ANY CRACK (AIRPLANES WITH MORE THAN35,500 FLIGHT CYCLES ON THE EFFECTIVE DATE OF AD2005-07-12 AND HAVE NOT STARTED INSPECTIONS INACCORDANCE WITH ORIGINAL ISSUE OF THIS SERVICEBULLETIN)

737-53A1241 R1 GRP 3TBL2.03

DETAILED FUSELAGE - FRAMES AND BULKHEADS - STA 277TO STA 328 FRAME INSPECTIONS, STRINGER 7R TO 17R -FORWARD GALLEY DOOR CUTOUT SERVICE BULLETIN ANDA SURFACE HFEC INSPECTION OF THE STA 291.5 FRAMEWEB AROUND THE STRINGER 16R INTERCOSTAL STRAPCUTOUT FOR ANY CRACK (AIRPLANES THAT HAVESTARTED INSPECTIONS IN ACCORDANCE WITH ORIGINALISSUE OF THIS SERVICE BULLETIN)

737-53A1241 R1 GRP 3TBL2.04

REPAIR FUSELAGE - FRAMES AND BULKHEADS - STA 277TO STA 328 FRAME INSPECTIONS, STRINGER 7R TO 17R -FORWARD GALLEY DOOR CUTOUT SERVICE BULLETIN THEFRAME WEB (IF ANY CRACK IS FOUND IN THE STA 291.5FRAME WEB AT S-16R)

737-53A1241 R1 GRP 3TBL2.05.1

DETAILED INSPECTION FUSELAGE - FRAMES ANDBULKHEADS - STA 277 TO STA 328 FRAME INSPECTIONS,STRINGER 7R TO 17R - FORWARD GALLEY DOOR CUTOUTSERVICE BULLETIN OF THE STA 291.5 FRAME WEB FROMSTRINGER 8R TO 15R AND A SURFACE HFEC INSPECTIONOF THE STA 291.5 FRAME OUTER CHORD WHERE THEFRAME WEB IS NOT VISIBLE FOR ANY CRACK (ALLAIRPLANES)

737-53A1241 R1 GRP 3TBL2.05.2

DETAILED INSPECTION FUSELAGE - FRAMES ANDBULKHEADS - STA 277 TO STA 328 FRAME INSPECTIONS,STRINGER 7R TO 17R - FORWARD GALLEY DOOR CUTOUTSERVICE BULLETIN OF THE INTERCOSTALS FROMSTRINGERS 8R TO 16R FOR ANY CRACK (ALL AIRPLANES)

Task Relations


Model: BOEING 737-300/400/500


737-53A1241 R1 GRP 3TBL2.05.3

SURFACE FUSELAGE - FRAMES AND BULKHEADS - STA 277TO STA 328 FRAME INSPECTIONS, STRINGER 7R TO 17R -FORWARD GALLEY DOOR CUTOUT SERVICE BULLETIN HFEC INSPECTION OF THE INNER CHORD OF THE DOORHINGE INTERCOSTALS FOR ANY CRACK (ALL AIRPLANES)

737-53A1241 R1 GRP 3TBL2.05.4

SURFACE FUSELAGE - FRAMES AND BULKHEADS - STA 277TO STA 328 FRAME INSPECTIONS, STRINGER 7R TO 17R -FORWARD GALLEY DOOR CUTOUT SERVICE BULLETIN HFEC INSPECTION OF THE FORWARD INNER RADIUSTRIMOUT OF THE INTERCOSTAL AT STRINGER 14R FORANY CRACK (ALL AIRPLANES)

737-53A1241 R1 GRP 3TBL2.05.5

DETAILED INSPECTION FUSELAGE - FRAMES ANDBULKHEADS - STA 277 TO STA 328 FRAME INSPECTIONS,STRINGER 7R TO 17R - FORWARD GALLEY DOOR CUTOUTSERVICE BULLETIN OF THE STA 277 FRAME, FRAME SHEARTIES AND STRINGER CLIPS FROM STRINGER 7R TOSTRINGER 17R FOR ANY CRACK (ALL AIRPLANES)

737-53A1241 R1 GRP 3TBL2.06

CONTACT FUSELAGE - FRAMES AND BULKHEADS - STA 277TO STA 328 FRAME INSPECTIONS, STRINGER 7R TO 17R -FORWARD GALLEY DOOR CUTOUT SERVICE BULLETIN BOEING TO GET INSTRUCTIONS FOR REPAIR AND DO THEWORK INSTRUCTIONS (IF ANY CRACK IS FOUND IN THE STA291.5 FRAME WEB BETWEEN S-8R AND S-15R)

737-53A1241 R1 GRP 3TBL2.07

REMOVE AND INSTALL FUSELAGE - FRAMES ANDBULKHEADS - STA 277 TO STA 328 FRAME INSPECTIONS,STRINGER 7R TO 17R - FORWARD GALLEY DOOR CUTOUTSERVICE BULLETIN NEW PART(S) (IF ANY CRACK IS FOUNDIN THE INTERCOSTAL(S))

737-53A1241 R1 GRP 3TBL2.08

REMOVE AND INSTALL FUSELAGE - FRAMES ANDBULKHEADS - STA 277 TO STA 328 FRAME INSPECTIONS,STRINGER 7R TO 17R - FORWARD GALLEY DOOR CUTOUTSERVICE BULLETIN NEW PART(S) (IF ANY CRACK IS FOUNDIN THE INNER CHORD OF THE DOOR HINGEINTERCOSTAL(S))

737-53A1241 R1 GRP 3TBL2.09

REMOVE AND INSTALL FUSELAGE - FRAMES ANDBULKHEADS - STA 277 TO STA 328 FRAME INSPECTIONS,STRINGER 7R TO 17R - FORWARD GALLEY DOOR CUTOUTSERVICE BULLETIN NEW PART(S) (IF ANY CRACK IS FOUNDIN THE INTERCOSTAL(S) FORWARD INNER RADIUSTRIMOUT OF THE INTERCOSTAL AT STRINGER 14R)

737-53A1241 R1 GRP 3TBL2.10

REPAIR FUSELAGE - FRAMES AND BULKHEADS - STA 277TO STA 328 FRAME INSPECTIONS, STRINGER 7R TO 17R -FORWARD GALLEY DOOR CUTOUT SERVICE BULLETIN THEFRAME (IF ANY CRACK IS FOUND AT THE STA 277 FRAMEWEB AROUND THE CUTOUT FOR STRINGER 16R)

Task Relations


Model: BOEING 737-300/400/500


737-53A1241 R1 GRP 3TBL2.11

REPAIR FUSELAGE - FRAMES AND BULKHEADS - STA 277TO STA 328 FRAME INSPECTIONS, STRINGER 7R TO 17R -FORWARD GALLEY DOOR CUTOUT SERVICE BULLETIN THEFRAME (IF ANY CRACK IS FOUND AT THE STA 277 Z FRAMEBETWEEN STRINGER 7R AND 13R)

737-53A1241 R1 GRP 3TBL2.12

REMOVE AND INSTALL FUSELAGE - FRAMES ANDBULKHEADS - STA 277 TO STA 328 FRAME INSPECTIONS,STRINGER 7R TO 17R - FORWARD GALLEY DOOR CUTOUTSERVICE BULLETIN NEW PART(S) (IF ANY OTHER CRACK ISFOUND AT THE STA 277 FRAME, FRAME SHEAR TIES ANDSTRINGER CLIPS FROM STRINGER 7R TO STRINGER 17R)

737-53A1241 R1 GRP 2-3TBL3.1

DETAILED INSPECTION FUSELAGE - FRAMES ANDBULKHEADS - STA 277 TO STA 328 FRAME INSPECTIONS,STRINGER 7R TO 17R - FORWARD GALLEY DOOR CUTOUTSERVICE BULLETIN OF THE STA 294.5 STUB FRAMES FROMSTRINGER 7R TO STRINGER 17R FOR ANY CRACK (ALLAIRPLANES)

737-53A1241 R1 GRP 2-3TBL3.2

REMOVE AND INSTALL FUSELAGE - FRAMES ANDBULKHEADS - STA 277 TO STA 328 FRAME INSPECTIONS,STRINGER 7R TO 17R - FORWARD GALLEY DOOR CUTOUTSERVICE BULLETIN NEW PART(S) (IF ANY CRACK ISFOUND)

737-53A1241 R1 GRP 2-3TBL3.3

DETAILED INSPECTION FUSELAGE - FRAMES ANDBULKHEADS - STA 277 TO STA 328 FRAME INSPECTIONS,STRINGER 7R TO 17R - FORWARD GALLEY DOOR CUTOUTSERVICE BULLETIN OF THE LOWER MAIN SILL STRUCTUREBETWEEN STA 285 AND STA 300 FOR ANY CRACK (ALLAIRPLANES)

737-53A1241 R1 GRP 2-3TBL3.4

REMOVE AND INSTALL FUSELAGE - FRAMES ANDBULKHEADS - STA 277 TO STA 328 FRAME INSPECTIONS,STRINGER 7R TO 17R - FORWARD GALLEY DOOR CUTOUTSERVICE BULLETIN NEW PART(S) (IF ANY CRACK ISFOUND)

737-53A1241 R1 GRP 2-3TBL3.5

DETAILED INSPECTION FUSELAGE - FRAMES ANDBULKHEADS - STA 277 TO STA 328 FRAME INSPECTIONS,STRINGER 7R TO 17R - FORWARD GALLEY DOOR CUTOUTSERVICE BULLETIN OF THE STA 294.5, STA 312 AND STA328 FRAMES ABOVE THE INTERSECTION WITH UPPER MAINSILL FOR ANY CRACK (ALL AIRPLANES)

737-53A1241 R1 GRP 2-3TBL3.6

REPAIR FUSELAGE - FRAMES AND BULKHEADS - STA 277TO STA 328 FRAME INSPECTIONS, STRINGER 7R TO 17R -FORWARD GALLEY DOOR CUTOUT SERVICE BULLETIN THEINNER CHORD (IF ANY CRACK IS FOUND)

Task Relations


Model: BOEING 737-300/400/500


737-53A1241 R1 GRP 1 CONTACT FUSELAGE - FRAMES AND BULKHEADS - STA 277TO STA 328 FRAME INSPECTIONS, STRINGER 7R TO 17R -FORWARD GALLEY DOOR CUTOUT SERVICE BULLETIN BOEING TO GET INSTRUCTIONS FOR THE INSPECTIONSAND REPAIRS AND DO THE WORK INSTRUCTED

737-53A1241 R1 GRP 2TBL1.01

DETAILED FUSELAGE - FRAMES AND BULKHEADS - STA 277TO STA 328 FRAME INSPECTIONS, STRINGER 7R TO 17R -FORWARD GALLEY DOOR CUTOUT SERVICE BULLETIN ANDA SURFACE HFEC INSPECTION OF THE STA 291.5 FRAMEWEB AROUND THE STRINGER 16R INTERCOSTAL STRAPCUTOUT FOR ANY CRACK (AIRPLANES THAT HAVE NOTSTARTED INSPECTIONS IN ACCORDANCE WITH ORIGINALISSUE OF THIS SERVICE BULLETIN)

737-53A1241 R1 GRP 2TBL1.02

DETAILED FUSELAGE - FRAMES AND BULKHEADS - STA 277TO STA 328 FRAME INSPECTIONS, STRINGER 7R TO 17R -FORWARD GALLEY DOOR CUTOUT SERVICE BULLETIN ANDA SURFACE HFEC INSPECTION OF THE STA 291.5 FRAMEWEB AROUND THE STRINGER 16R INTERCOSTAL STRAPCUTOUT FOR ANY CRACK (AIRPLANES THAT HAVESTARTED INSPECTIONS IN ACCORDANCE WITH ORIGINALISSUE OF THIS SERVICE BULLETIN)

737-53A1241 R1 GRP 2TBL1.03

REPAIR FUSELAGE - FRAMES AND BULKHEADS - STA 277TO STA 328 FRAME INSPECTIONS, STRINGER 7R TO 17R -FORWARD GALLEY DOOR CUTOUT SERVICE BULLETIN THEFRAME WEB (IF ANY CRACK IS FOUND IN THE STA 291.5FRAME WEB AT S-16R)

737-53A1241 R1 GRP 2TBL1.04.1

DETAILED INSPECTION FUSELAGE - FRAMES ANDBULKHEADS - STA 277 TO STA 328 FRAME INSPECTIONS,STRINGER 7R TO 17R - FORWARD GALLEY DOOR CUTOUTSERVICE BULLETIN OF THE STA 291.5 FRAME WEB FROMSTRINGER 8R TO 15R AND A SURFACE HFEC INSPECTIONOF THE STA 291.5 FRAME OUTER CHORD WHERE THEFRAME WEB IS NOT VISIBLE FOR ANY CRACK (ALLAIRPLANES)

737-53A1241 R1 GRP 2TBL1.04.2

DETAILED INSPECTION FUSELAGE - FRAMES ANDBULKHEADS - STA 277 TO STA 328 FRAME INSPECTIONS,STRINGER 7R TO 17R - FORWARD GALLEY DOOR CUTOUTSERVICE BULLETIN OF THE INTERCOSTALS FROMSTRINGERS 8R TO 16R FOR ANY CRACK (ALL AIRPLANES)

737-53A1241 R1 GRP 2TBL1.04.3

SURFACE FUSELAGE - FRAMES AND BULKHEADS - STA 277TO STA 328 FRAME INSPECTIONS, STRINGER 7R TO 17R -FORWARD GALLEY DOOR CUTOUT SERVICE BULLETIN HFEC INSPECTION OF THE INNER CHORD OF THE DOORHINGE INTERCOSTALS FOR ANY CRACK (ALL AIRPLANES)

Task Relations


Model: BOEING 737-300/400/500


737-53A1241 R1 GRP 2TBL1.04.4

SURFACE FUSELAGE - FRAMES AND BULKHEADS - STA 277TO STA 328 FRAME INSPECTIONS, STRINGER 7R TO 17R -FORWARD GALLEY DOOR CUTOUT SERVICE BULLETIN HFEC INSPECTION OF THE FORWARD INNER RADIUSTRIMOUT OF THE INTERCOSTAL AT STRINGER 14R FORANY CRACK (ALL AIRPLANES)

737-53A1241 R1 GRP 2TBL1.04.5

DETAILED INSPECTION FUSELAGE - FRAMES ANDBULKHEADS - STA 277 TO STA 328 FRAME INSPECTIONS,STRINGER 7R TO 17R - FORWARD GALLEY DOOR CUTOUTSERVICE BULLETIN OF THE STA 277 FRAME, FRAME SHEARTIES AND STRINGER CLIPS FROM STRINGER 7R TOSTRINGER 17R FOR ANY CRACK (ALL AIRPLANES)

737-53A1254 R2 FUSELAGE - BODY FRAME AND OVERWING STUB BEAMINSPECTION AND REPAIR - BODY STATIONS 597 TO 639SERVICE BULLETIN

PRIMARY TO

737-53A1254 R2 TABLE 5 HFEC FUSELAGE - BODY FRAME AND OVERWING STUBBEAM INSPECTION AND REPAIR - BODY STATIONS 597 TO639 SERVICE BULLETIN INSPECT THE INNER AND OUTERCHORD COMMON TO THE REPAIR SPLICE ANGLES ANDSTRAP (INNER CHORD ONLY) BETWEEN S-14 AND S-15 ATTHE HEEL AND TOE ALONG THE ENTIRE LENGTH OF THEREPAIR SPLICES FOR AIRPLANES THAT HAVEACCOMPLISHED A PARTIAL FRAME SPLICE REPAIR AT BS616 AND/OR BS 639 IN ACCORDANCE WITHACCOMPLISHMENT INSTRUCTIONS 3.B.4

737-53A1254 R2 TABLE4.2

DETAILED INSPECTION FUSELAGE - BODY FRAME ANDOVERWING STUB BEAM INSPECTION AND REPAIR - BODYSTATIONS 597 TO 639 SERVICE BULLETIN OF THE BS 597SHEAR TIE COMMON TO THE SKIN FOR CRACKS FORAIRPLANES THAT HAVE ACCUMULATED MORE THAN 55,000TOTAL FLIGHT CYCLES (GROUP 1-2)

737-53A1254 R2 TABLE4.1

DETAILED INSPECTION FUSELAGE - BODY FRAME ANDOVERWING STUB BEAM INSPECTION AND REPAIR - BODYSTATIONS 597 TO 639 SERVICE BULLETIN OF THE BS 597SHEAR TIE COMMON TO THE SKIN FOR CRACKS FORAIRPLANES THAT HAVE ACCUMULATED BETWEEN 15,000AND 55,000 TOTAL FLIGHT CYCLES (GROUP 1-2)

737-53A1254 R2 TABLE3.2

DETAILED INSPECTION FUSELAGE - BODY FRAME ANDOVERWING STUB BEAM INSPECTION AND REPAIR - BODYSTATIONS 597 TO 639 SERVICE BULLETIN (OPTION 1) ORHFEC SURFACE INSPECTION (OPTION 2) OF THE INNERCHORD COMMON TO THE LOWEST FOUR FASTENERS ATBS 601 FOR AIRPLANES THAT HAVE ACCUMULATED MORETHAN 55,000 TOTAL FLIGHT CYCLES (GROUP 3)

Task Relations


Model: BOEING 737-300/400/500


737-53A1254 R2 TABLE3.1

DETAILED INSPECTION FUSELAGE - BODY FRAME ANDOVERWING STUB BEAM INSPECTION AND REPAIR - BODYSTATIONS 597 TO 639 SERVICE BULLETIN (OPTION 1) ORHFEC INSPECTION (OPTION 2) OF THE INNER CHORDCOMMON TO THE LOWEST FOUR FASTENERS AT BS 601FOR CRACKS (GROUP 3) FOR AIRPLANES THAT HAVEACCUMULATED BETWEEN 15,000 AND 55,000 TOTAL FLIGHTCYCLES

737-53A1254 R2 TABLE2.3

DETAILED INSPECTION FUSELAGE - BODY FRAME ANDOVERWING STUB BEAM INSPECTION AND REPAIR - BODYSTATIONS 597 TO 639 SERVICE BULLETIN (OPTION 1) ORHFEC INSPECTION (OPTION 2) OF THE REPLACEMENT STUBBEAM FOR AIRPLANES THAT HAVE ACCOMPLISHED THE BS616 OR BS 639 INTEGRAL STUB BEAM REPLACEMENT

737-53A1254 R2 TABLE1.(1) (2)

DETAILED INSPECTION FUSELAGE - BODY FRAME ANDOVERWING STUB BEAM INSPECTION AND REPAIR - BODYSTATIONS 597 TO 639 SERVICE BULLETIN (OPTION 1) ORHFEC INSPECTION (OPTION 2) OF BS 616 AND BS 639FRAMES (ORIGINAL ISSUE OR REVISION 1 NOT COMPLIEDWITH)

737-53A1254 R2 TABLE2.2(1)(2)

DETAILED INSPECTION FUSELAGE - BODY FRAME ANDOVERWING STUB BEAM INSPECTION AND REPAIR - BODYSTATIONS 597 TO 639 SERVICE BULLETIN (OPTION 1) ORHFEC INSPECTION (OPTION 2) OF THE REPLACEMENTFRAME SECTION (INNER CHORD, OUTER CHORD AND WEB)FOR CRACKS FOR AIRPLANES THAT HAVE ACCOMPLISHEDA PARTIAL FRAME SPLICE REPAIR AT BS 616 OR BS 639

737-53A1254 R2 TABLE2.1(3)

LFEC FUSELAGE - BODY FRAME AND OVERWING STUBBEAM INSPECTION AND REPAIR - BODY STATIONS 597 TO639 SERVICE BULLETIN OF THE WEB AND HFECINSPECTION OF THE INNER CHORD COMMON TO THEUPPER END FASTENER ROWS OF THE WEB SPLICEDOUBLER FOR AIRPLANES THAT HAVE ACCOMPLISHED APARTIAL FRAME SPLICE REPAIR AT BS 616 OR BS 639

737-53A1254 R2 TABLE2.1(1)(2)

DETAILED INSPECTION FUSELAGE - BODY FRAME ANDOVERWING STUB BEAM INSPECTION AND REPAIR - BODYSTATIONS 597 TO 639 SERVICE BULLETIN (OPTION 1) ORHFEC INSPECTION (OPTION 2) OF THE REPLACEMENTFRAME SECTION (PARTIAL FRAME SPLICE REPAIR AT BS616 OR BS 639)

737-53A1254 R2 TABLE1.5

DETAILED INSPECTION FUSELAGE - BODY FRAME ANDOVERWING STUB BEAM INSPECTION AND REPAIR - BODYSTATIONS 597 TO 639 SERVICE BULLETIN OPTION 1) ORHFEC INSPECTION 9OPTION 2) OF THE BS 616 AND BS 639FRAMES (REVISION 1 STARTED - LAST INSPECTION OPTION2)

Task Relations


Model: BOEING 737-300/400/500


737-53A1254 R2 TABLE1.4

DETAILED INSPECTION FUSELAGE - BODY FRAME ANDOVERWING STUB BEAM INSPECTION AND REPAIR - BODYSTATIONS 597 TO 639 SERVICE BULLETIN (OPTION 1 ) ORHFEC INSPECTION (OPTION 2) OF BS 616 AND BS 639FRAMES (REVISION 1 STARTED - LAST INSPECTION OPTION1)

737-53A1254 R2 TABLE1.3

DETAILED INSPECTION FUSELAGE - BODY FRAME ANDOVERWING STUB BEAM INSPECTION AND REPAIR - BODYSTATIONS 597 TO 639 SERVICE BULLETIN (OPTION 1) ORHFEC INSPECTION (OPTION 2) OF BS 616 AND BS 639FRAMES (ORIGINAL ISSUE STARTED)

737-53A1254 R2 TABLE2.2(3)

LFEC FUSELAGE - BODY FRAME AND OVERWING STUBBEAM INSPECTION AND REPAIR - BODY STATIONS 597 TO639 SERVICE BULLETIN INSPECTION OF THE WEB ANDHFEC INSPECTION OF THE INNER CHORD COMMON TO THEUPPER END FASTENER ROWS OF THE WEB SPLICEDOUBLER FOR AIRPLANES THAT HAVE ACCOMPLISHED APARTIAL FRAME SPLICE REPAIR AT BS 616 OR BS 639

737-53A1255 R1 FUSELAGE - SKIN - CROWN SKIN LAP JOINT - INSPECTIONFOR LOWER ROW CRACKING AT STRINGERS S-4, S-10, S-14BETWEEN STA 360 AND STA 908 (SUPERSEDED BY SB737-53A1255 R2) SERVICE BULLETIN

PRIMARY TO

737-53A1255 R1 TABLE1.5.3

ACCOMPLISH FUSELAGE - SKIN - CROWN SKIN LAP JOINT -INSPECTION FOR LOWER ROW CRACKING AT STRINGERSS-4, S-10, S-14 BETWEEN STA 360 AND STA 908(SUPERSEDED BY SB 737-53A1255 R2) SERVICE BULLETIN OPTION 2 (EXTERNAL EDDY CURRENT INSPECTION OF THECROWN LAP JOINTS FOR CRACKS)

737-53A1255 R1 TABLE1.5.4

ACCOMPLISH FUSELAGE - SKIN - CROWN SKIN LAP JOINT -INSPECTION FOR LOWER ROW CRACKING AT STRINGERSS-4, S-10, S-14 BETWEEN STA 360 AND STA 908(SUPERSEDED BY SB 737-53A1255 R2) SERVICE BULLETIN OPTION 2 (INTERNAL EDDY CURRENT INSPECTION ANDDETAILED INSPECTION OF THE CROWN LAP JOINTS AND DOA DETAILED INSPECTION OF THE STRINGER CLIPS FORCRACKS)

737-53A1255 R1 TABLE1.5.5


Task Relations


Model: BOEING 737-300/400/500


737-53A1255 R1 TABLE1.6.1

PERFORM FUSELAGE - SKIN - CROWN SKIN LAP JOINT -INSPECTION FOR LOWER ROW CRACKING AT STRINGERSS-4, S-10, S-14 BETWEEN STA 360 AND STA 908(SUPERSEDED BY SB 737-53A1255 R2) SERVICE BULLETIN INTERNAL EDDY CURRENT INSPECTION AND DETAILEDINSPECTION OF THE OVER WING CROWN LAP JOINTS ANDDO A DETAILED INSPECTION OF THE STRINGER CLIPS FORCRACKS FOR AIRPLANES WITH MORE THAN 43,299 ANDLESS THAN 45,000 TOTAL FLIGHT CYCLES AT THE REVISION1 DATE OF THIS SERVICE BULLETIN

737-53A1255 R1 TABLE1.6.2

PERFORM FUSELAGE - SKIN - CROWN SKIN LAP JOINT -INSPECTION FOR LOWER ROW CRACKING AT STRINGERSS-4, S-10, S-14 BETWEEN STA 360 AND STA 908(SUPERSEDED BY SB 737-53A1255 R2) SERVICE BULLETIN INTERNAL EDDY CURRENT INSPECTION AND DETAILEDINSPECTION OF THE NON OVER WING CROWN LAP AND DOA DETAILED INSPECTION OF THE STRINGER CLIPS FORCRACKS FOR AIRPLANES WITH MORE THAN 43,299 ANDLESS THAN 45,000 TOTAL FLIGHT CYCLES AT THE REVISION1 DATE OF THIS SERVICE BULLETIN

737-53A1255 R1 TABLE1.6.3

PERFORM FUSELAGE - SKIN - CROWN SKIN LAP JOINT -INSPECTION FOR LOWER ROW CRACKING AT STRINGERSS-4, S-10, S-14 BETWEEN STA 360 AND STA 908(SUPERSEDED BY SB 737-53A1255 R2) SERVICE BULLETIN EXTERNAL EDDY CURRENT INSPECTION OF THE CROWNLAP JOINTS FOR CRACKS FOR AIRPLANES WITH MORETHAN 43,299 AND LESS THAN 45,000 TOTAL FLIGHT CYCLESAT THE REVISION 1 DATE OF THIS SERVICE BULLETIN

737-53A1255 R1 TABLE1.7


737-53A1255 R1 TABLE1.8


Task Relations


Model: BOEING 737-300/400/500


737-53A1255 R1 TABLE1.9


737-53A1255 R1 TABLE1.10

MODIFICATION FUSELAGE - SKIN - CROWN SKIN LAP JOINT- INSPECTION FOR LOWER ROW CRACKING AT STRINGERSS-4, S-10, S-14 BETWEEN STA 360 AND STA 908(SUPERSEDED BY SB 737-53A1255 R2) SERVICE BULLETIN TO THE CROWN LAP JOINTS FOR ALL AIRPLANES

737-53A1255 R1 TABLE1.1

ACCOMPLISH FUSELAGE - SKIN - CROWN SKIN LAP JOINT -INSPECTION FOR LOWER ROW CRACKING AT STRINGERSS-4, S-10, S-14 BETWEEN STA 360 AND STA 908(SUPERSEDED BY SB 737-53A1255 R2) SERVICE BULLETIN INITIAL EXTERNAL EDDY CURRENT INSPECTION OF THECROWN LAP JOINTS FOR CRACKS FOR AIRPLANES WITHLESS THAN 35,000 TOTAL FLIGHT CYCLES AT THE REVISION1 DATE OF THIS SERVICE BULLETIN

737-53A1255 R1 TABLE1.2.1


737-53A1255 R1 TABLE1.2.2


737-53A1255 R1 TABLE1.2.3


Task Relations


Model: BOEING 737-300/400/500


737-53A1255 R1 TABLE1.2.4


737-53A1255 R1 TABLE1.2.5


737-53A1255 R1 TABLE1.3.1

ACCOMPLISH FUSELAGE - SKIN - CROWN SKIN LAP JOINT -INSPECTION FOR LOWER ROW CRACKING AT STRINGERSS-4, S-10, S-14 BETWEEN STA 360 AND STA 908(SUPERSEDED BY SB 737-53A1255 R2) SERVICE BULLETIN OPTION 1 ( INITIAL EXTERNAL EDDY CURRENT INSPECTIONOF THE CROWN LAP JOINTS FOR CRACKS) FOR AIRPLANESWITH MORE THAN 34,999 AND LESS THAN 37,500 TOTALFLIGHT CYCLES AT THE REVISION 1 DATE OF THIS SERVICEBULLETIN

737-53A1255 R1 TABLE1.5.2


737-53A1255 R1 TABLE1.5.1

ACCOMPLISH FUSELAGE - SKIN - CROWN SKIN LAP JOINT -INSPECTION FOR LOWER ROW CRACKING AT STRINGERSS-4, S-10, S-14 BETWEEN STA 360 AND STA 908(SUPERSEDED BY SB 737-53A1255 R2) SERVICE BULLETIN OPTION 1 ( INTERNAL EDDY CURRENT INSPECTION ANDDETAILED INSPECTION OF THE CROWN LAP JOINTS AND DOA DETAILED INSPECTION OF THE STRINGER CLIPS FORCRACKS) FOR AIRPLANES WITH MORE THAN 39,999 ANDLESS THAN 43,300 TOTAL FLIGHT CYCLES AT THE REVISION1 DATE OF THIS SERVICE BULLETIN

737-53A1255 R1 TABLE1.4.5

ACCOMPLISH FUSELAGE - SKIN - CROWN SKIN LAP JOINT -INSPECTION FOR LOWER ROW CRACKING AT STRINGERSS-4, S-10, S-14 BETWEEN STA 360 AND STA 908(SUPERSEDED BY SB 737-53A1255 R2) SERVICE BULLETIN OPTION 2 ( EXTERNAL EDDY CURRENT INSPECTION OF THECROWN LAP JOINTS FOR CRACKS)

Task Relations


Model: BOEING 737-300/400/500


737-53A1255 R1 TABLE1.4.4

ACCOMPLISH FUSELAGE - SKIN - CROWN SKIN LAP JOINT -INSPECTION FOR LOWER ROW CRACKING AT STRINGERSS-4, S-10, S-14 BETWEEN STA 360 AND STA 908(SUPERSEDED BY SB 737-53A1255 R2) SERVICE BULLETIN OPTION 2 ( INTERNAL EDDY CURRENT INSPECTION ANDDETAILED INSPECTION OF THE CROWN LAP JOINTS AND DOA DETAILED INSPECTION OF THE STRINGER CLIPS FORCRACKS)

737-53A1255 R1 TABLE1.4.3


737-53A1255 R1 TABLE1.4.2


737-53A1255 R1 TABLE1.4.1

ACCOMPLISH FUSELAGE - SKIN - CROWN SKIN LAP JOINT -INSPECTION FOR LOWER ROW CRACKING AT STRINGERSS-4, S-10, S-14 BETWEEN STA 360 AND STA 908(SUPERSEDED BY SB 737-53A1255 R2) SERVICE BULLETIN OPTION 1 (INTERNAL EDDY CURRENT INSPECTION ANDDETAILED INSPECTION OF THE CROWN LAP JOINTS AND DOA DETAILED INSPECTION OF THE STRINGER CLIPS FORCRACKS) FOR AIRPLANES WITH MORE THAN 37,499 ANDLESS THAN 40,000 TOTAL FLIGHT CYCLES AT THE REVISION1 DATE OF THIS SERVICE BULLETIN

737-53A1255 R1 TABLE1.3.9


737-53A1255 R1 TABLE1.3.8


Task Relations


Model: BOEING 737-300/400/500


737-53A1255 R1 TABLE1.3.7


737-53A1255 R1 TABLE1.3.6

PERFORM FUSELAGE - SKIN - CROWN SKIN LAP JOINT -INSPECTION FOR LOWER ROW CRACKING AT STRINGERSS-4, S-10, S-14 BETWEEN STA 360 AND STA 908(SUPERSEDED BY SB 737-53A1255 R2) SERVICE BULLETIN OPTION 2 (INTERNAL EDDY CURRENT INSPECTION ANDDETAILED INSPECTION OF THE CROWN LAP JOINTS AND DOA DETAILED INSPECTION OF THE STRINGER CLIPS FORCRACKS)

737-53A1255 R1 TABLE1.3.5


737-53A1255 R1 TABLE1.3.2

ACCOMPLISH FUSELAGE - SKIN - CROWN SKIN LAP JOINT -INSPECTION FOR LOWER ROW CRACKING AT STRINGERSS-4, S-10, S-14 BETWEEN STA 360 AND STA 908(SUPERSEDED BY SB 737-53A1255 R2) SERVICE BULLETIN OPTION 1 (INTERNAL EDDY CURRENT INSPECTION ANDDETAILED INSPECTION OF THE CROWN LAP JOINTS AND DOA DETAILED INSPECTION OF THE STRINGER CLIPS FORCRACKS )

737-53A1255 R1 TABLE1.3.3


737-53A1255 R1 TABLE1.3.4


737-53A1255 R2 FUSELAGE - SKIN - CROWN SKIN LAP JOINT - INSPECTIONFOR LOWER ROW CRACKING AT STRINGERS S-4, S-10, S-14BETWEEN STA 360 AND STA 908 SERVICE BULLETIN

PRIMARY TO

Task Relations


Model: BOEING 737-300/400/500


737-53A1255 R2 TABLE1.8

PERFORM FUSELAGE - SKIN - CROWN SKIN LAP JOINT -INSPECTION FOR LOWER ROW CRACKING AT STRINGERSS-4, S-10, S-14 BETWEEN STA 360 AND STA 908 SERVICEBULLETIN EXTERNAL EDDY CURRENT INSPECTION OF THECROWN LAP JOINTS <46250 FC & > 47501 FC

737-53A1255 R2 TABLE1.9

PERFORM FUSELAGE - SKIN - CROWN SKIN LAP JOINT -INSPECTION FOR LOWER ROW CRACKING AT STRINGERSS-4, S-10, S-14 BETWEEN STA 360 AND STA 908 SERVICEBULLETIN EXTERNAL EDDY CURRENT INSPECTION OF THECROWN LAP JOINTS < 475000 FC & > 48751 FC

737-53A1255 R2 TABLE1.10

PERFORM FUSELAGE - SKIN - CROWN SKIN LAP JOINT -INSPECTION FOR LOWER ROW CRACKING AT STRINGERSS-4, S-10, S-14 BETWEEN STA 360 AND STA 908 SERVICEBULLETIN MODIFICATION (ALL AIRPLANES)

737-53A1255 R2 TABLE1.1

EDDY-CURRENT INSPECTION FUSELAGE - SKIN - CROWNSKIN LAP JOINT - INSPECTION FOR LOWER ROW CRACKINGAT STRINGERS S-4, S-10, S-14 BETWEEN STA 360 AND STA908 SERVICE BULLETIN (EXTERNAL) > 35000 FC

737-53A1255 R2 TABLE1.2.1

PERFORM FUSELAGE - SKIN - CROWN SKIN LAP JOINT -INSPECTION FOR LOWER ROW CRACKING AT STRINGERSS-4, S-10, S-14 BETWEEN STA 360 AND STA 908 SERVICEBULLETIN OPTION 1(INTERNAL)

737-53A1255 R2 TABLE1.2.2

PERFORM FUSELAGE - SKIN - CROWN SKIN LAP JOINT -INSPECTION FOR LOWER ROW CRACKING AT STRINGERSS-4, S-10, S-14 BETWEEN STA 360 AND STA 908 SERVICEBULLETIN (OPTION 1) (EXTERNAL)

737-53A1255 R2 TABLE1.2.3

PERFORM FUSELAGE - SKIN - CROWN SKIN LAP JOINT -INSPECTION FOR LOWER ROW CRACKING AT STRINGERSS-4, S-10, S-14 BETWEEN STA 360 AND STA 908 SERVICEBULLETIN (OPTION 2) EXTERNAL

737-53A1255 R2 TABLE1.2.4

PERFORM FUSELAGE - SKIN - CROWN SKIN LAP JOINT -INSPECTION FOR LOWER ROW CRACKING AT STRINGERSS-4, S-10, S-14 BETWEEN STA 360 AND STA 908 SERVICEBULLETIN (OPTION 2) INTERNAL

737-53A1255 R2 TABLE1.2.5


737-53A1255 R2 TABLE1.3.1

PERFORM FUSELAGE - SKIN - CROWN SKIN LAP JOINT -INSPECTION FOR LOWER ROW CRACKING AT STRINGERSS-4, S-10, S-14 BETWEEN STA 360 AND STA 908 SERVICEBULLETIN (OPTION 1) INITIAL EXTERNAL < 34999 FC > 37500FC

Task Relations


Model: BOEING 737-300/400/500


737-53A1255 R2 TABLE1.3.2

PERFORM FUSELAGE - SKIN - CROWN SKIN LAP JOINT -INSPECTION FOR LOWER ROW CRACKING AT STRINGERSS-4, S-10, S-14 BETWEEN STA 360 AND STA 908 SERVICEBULLETIN (OPTION 1) INTERNAL AND DETAILEDINSPECTION

737-53A1255 R2 TABLE1.3.3


737-53A1255 R2 TABLE1.3.4


737-53A1255 R2 TABLE1.3.5


737-53A1255 R2 TABLE1.3.6


737-53A1255 R2 TABLE1.3.7


737-53A1255 R2 TABLE1.3.8


737-53A1255 R2 TABLE1.3.9


737-53A1255 R2 TABLE1.4.1

PERFORM FUSELAGE - SKIN - CROWN SKIN LAP JOINT -INSPECTION FOR LOWER ROW CRACKING AT STRINGERSS-4, S-10, S-14 BETWEEN STA 360 AND STA 908 SERVICEBULLETIN (OPTION 1) INTERNAL AND DETAILEDINSPECTION < 37499 FC & > 40000 FC

737-53A1255 R2 TABLE1.4.2


Task Relations


Model: BOEING 737-300/400/500


737-53A1255 R2 TABLE1.4.3


737-53A1255 R2 TABLE1.4.4


737-53A1255 R2 TABLE1.4.5


737-53A1255 R2 TABLE1.5.1

PERFORM FUSELAGE - SKIN - CROWN SKIN LAP JOINT -INSPECTION FOR LOWER ROW CRACKING AT STRINGERSS-4, S-10, S-14 BETWEEN STA 360 AND STA 908 SERVICEBULLETIN (OPTION 1) INTERNAL AND DETAILEDINSPECTION < 39000 FC & > 43000 FC

737-53A1255 R2 TABLE1.5.2


737-53A1255 R2 TABLE1.5.3


737-53A1255 R2 TABLE1.5.4


737-53A1255 R2 TABLE1.5.5


737-53A1255 R2 TABLE1.6.1

PERFORM FUSELAGE - SKIN - CROWN SKIN LAP JOINT -INSPECTION FOR LOWER ROW CRACKING AT STRINGERSS-4, S-10, S-14 BETWEEN STA 360 AND STA 908 SERVICEBULLETIN INTERNAL EDDY CURRENT INSPECTION ANDDETAILED INSPECTION OF THE OVER WING CROWN LAPJOINT < 43,299 AND > 45,000 TOTAL FLIGHT CYCLES

Task Relations


Model: BOEING 737-300/400/500


737-53A1255 R2 TABLE1.6.2

PERFORM FUSELAGE - SKIN - CROWN SKIN LAP JOINT -INSPECTION FOR LOWER ROW CRACKING AT STRINGERSS-4, S-10, S-14 BETWEEN STA 360 AND STA 908 SERVICEBULLETIN INTERNAL EDDY CURRENT INSPECTION ANDDETAILED INSPECTION OF THE NON OVER WING CROWNLAP

737-53A1255 R2 TABLE1.6.3

PERFORM FUSELAGE - SKIN - CROWN SKIN LAP JOINT -INSPECTION FOR LOWER ROW CRACKING AT STRINGERSS-4, S-10, S-14 BETWEEN STA 360 AND STA 908 SERVICEBULLETIN EDDY CURRENT INSPECTION OF THE CROWNLAP JOINTS

737-53A1255 R2 TABLE1.7

PERFORM FUSELAGE - SKIN - CROWN SKIN LAP JOINT -INSPECTION FOR LOWER ROW CRACKING AT STRINGERSS-4, S-10, S-14 BETWEEN STA 360 AND STA 908 SERVICEBULLETIN EXTERNAL EDDY CURRENT INSPECTION OF THECROWN LAP JOINTS <44999 FC & > 46251 FC

737-53A1262 R3 FUSELAGE - SKIN - INSPECTIONS OF THE FUSELAGE SKINFOR SCRIBE LINES SERVICE BULLETIN

PRIMARY TO737-53A1262 R3 ZONE 1A INSPECTION FUSELAGE - SKIN - INSPECTIONS OF THE

FUSELAGE SKIN FOR SCRIBE LINES SERVICE BULLETIN OFTHE FUSELAGE SKIN FOR SCRIBE LINES

737-53A1262 R3 ZONE 1B INSPECTION FUSELAGE - SKIN - INSPECTIONS OF THEFUSELAGE SKIN FOR SCRIBE LINES SERVICE BULLETIN OFTHE FUSELAGE SKIN FOR SCRIBE LINES




737-53A1279 R1 FUSELAGE - FRAMES AND BULKHEADS - FORWARD CARGOBAY STRINGER 19 TO STRINGER 21 - FRAMES AND FRAMEREINFORCEMENTS - INSPECTION, REPAIR ANDPREVENTATIVE MODIFICATION AT WIRE PENETRATIONHOLE SERVICE BULLETIN

PRIMARY TO

Task Relations


Model: BOEING 737-300/400/500


737-53A1279 R1 TABLE2.1

PERFORM FUSELAGE - FRAMES AND BULKHEADS -FORWARD CARGO BAY STRINGER 19 TO STRINGER 21 -FRAMES AND FRAME REINFORCEMENTS - INSPECTION,REPAIR AND PREVENTATIVE MODIFICATION AT WIREPENETRATION HOLE SERVICE BULLETIN A HFECINSPECTION FOR CRACKING AT THE 1.04 INCH NOMINALDIAMETER WIRE PENETRATION HOLE IN THE FORWARDCARGO BAY FRAMES AND FRAME REINFORCEMENTSBETWEEN S-20 AND S-21 FOR ALL AIRPLANES

737-53A1279 R1 TABLE2.3

PERFORM FUSELAGE - FRAMES AND BULKHEADS -FORWARD CARGO BAY STRINGER 19 TO STRINGER 21 -FRAMES AND FRAME REINFORCEMENTS - INSPECTION,REPAIR AND PREVENTATIVE MODIFICATION AT WIREPENETRATION HOLE SERVICE BULLETIN A HFECINSPECTION FOR CRACKING AT THE 1.04 INCH NOMINALDIAMETER WIRE PENETRATION HOLE IN THE FORWARDCARGO BAY FRAMES AND FRAME REINFORCEMENTSBETWEEN S-20 AND S-21 AFTER ACCOMPLISHMENT OF THEPARAGRAPH 3.B.2. PART 2 - INITIAL INSPECTION ORPARAGRAPH 3.B.4. PART 4 - REPEAT INSPECTION AND NOCRACKING IS FOUND

737-53A1279 R1 TABLE1.4

PERFORM FUSELAGE - FRAMES AND BULKHEADS -FORWARD CARGO BAY STRINGER 19 TO STRINGER 21 -FRAMES AND FRAME REINFORCEMENTS - INSPECTION,REPAIR AND PREVENTATIVE MODIFICATION AT WIREPENETRATION HOLE SERVICE BULLETIN A HFECINSPECTION FOR CRACKING AT THE 1.04 INCH NOMINALDIAMETER WIRE PENETRATION HOLE IN THE FORWARDCARGO BAY FRAMES AND FRAME REINFORCEMENTSBETWEEN S-20 AND S-21 AFTER ACCOMPLISHMENT OF THEPARAGRAPH 3.B.2. PART 2 - INITIAL INSPECTION ORPARAGRAPH 3.B.4. PART 4 - REPEAT INSPECTION AND NOCRACKING IS FOUND

737-53A1279 R1 TABLE1.2

PERFORM FUSELAGE - FRAMES AND BULKHEADS -FORWARD CARGO BAY STRINGER 19 TO STRINGER 21 -FRAMES AND FRAME REINFORCEMENTS - INSPECTION,REPAIR AND PREVENTATIVE MODIFICATION AT WIREPENETRATION HOLE SERVICE BULLETIN A HFECINSPECTION FOR CRACKING AT THE 1.04 INCH NOMINALDIAMETER WIRE PENETRATION HOLE IN THE FORWARDCARGO BAY FRAMES AND FRAME REINFORCEMENTSBETWEEN S-20 AND S-21 FOR AIRPLANES WITH 40,000 ORMORE TOTAL FLIGHT CYCLES AT THE DATE OF REVISION 1OF THIS SERVICE BULLETIN

Task Relations


Model: BOEING 737-300/400/500


737-53A1279 R1 TABLE1.1

PERFORM FUSELAGE - FRAMES AND BULKHEADS -FORWARD CARGO BAY STRINGER 19 TO STRINGER 21 -FRAMES AND FRAME REINFORCEMENTS - INSPECTION,REPAIR AND PREVENTATIVE MODIFICATION AT WIREPENETRATION HOLE SERVICE BULLETIN A HFECINSPECTION FOR CRACKING AT THE 1.04 INCH NOMINALDIAMETER WIRE PENETRATION HOLE IN THE FORWARDCARGO BAY FRAMES AND FRAME REINFORCEMENTSBETWEEN S-20 AND S-21 FOR AIRPLANES WITH LESS THAN40,000 TOTAL FLIGHT CYCLES AT THE DATE ON REVISION 1OF THIS SERVICE BULLETIN

737-53A1293 R2 FUSELAGE - SKIN - STRINGER S-1 AND STRINGER S-2R,STATION 400 TO STATION 460 INSPECTION AND REPAIRSERVICE BULLETIN

PRIMARY TO

737-53A1293 R2 TABLE 3(02)

REPEAT FUSELAGE - SKIN - STRINGER S-1 AND STRINGERS-2R, STATION 400 TO STATION 460 INSPECTION ANDREPAIR SERVICE BULLETIN EXTERNAL DI AND NDI OF THEFUSELAGE SKIN CHEM-MILL STEPS FOR CRACKS INACCORDANCE WITH ACCOMPLISHMENT INSTRUCTIONS,PARAGRAPH 3.B., PART 1 IF NO CRACK FOUND IN THEFUSELAGE SKIN (AND) OPTION 1 (OR) OPTION 2 USED FORGROUP 1, CONFIGURATION 3, 5 AIRPLANES

737-53A1293 R2 TABLE 3(04)

PERFORM FUSELAGE - SKIN - STRINGER S-1 ANDSTRINGER S-2R, STATION 400 TO STATION 460 INSPECTIONAND REPAIR SERVICE BULLETIN OPTION 1 (OR) OPTION 2IF CRACK(S) FOUND AT OR AFTER 5,000 TOTAL FLIGHTCYCLES (AND) CRACKS(S) FOUND IN THREE OR FEWERTEAR STRAP BAYS (AND) CRACK(S) FOUND 5 INCHES ORSHORTER (AND) CRACK(S) FOUND ARE CONTAINED WITHINTHE SKIN CUT-OUT. FOR GROUP 1, CONFIGURATION 3, 5AIRPLANES

737-53A1293 R2 TABLE 2(04)

PERFORM FUSELAGE - SKIN - STRINGER S-1 ANDSTRINGER S-2R, STATION 400 TO STATION 460 INSPECTIONAND REPAIR SERVICE BULLETIN OPTION 1 OR OPTION 2 IFCRACK(S) FOUND AT OR AFTER 35,000 TOTAL FLIGHTCYCLES (AND) CRACKS(S) FOUND IN THREE OR FEWERTEAR STRAP BAYS (AND) CRACK(S) FOUND 5 INCHES ORSHORTER (AND) CRACK(S) FOUND ARE CONTAINED WITHINTHE SKIN CUT-OUT FOR GROUP 1, CONFIGURATION 2, 4AIRPLANES

737-53A1293 R2 TABLE 2(03)

PERFORM FUSELAGE - SKIN - STRINGER S-1 ANDSTRINGER S-2R, STATION 400 TO STATION 460 INSPECTIONAND REPAIR SERVICE BULLETIN OPTION 1 OR OPTION 2 IFCRACK(S) FOUND BEFORE 35,000 TOTAL FLIGHT CYCLES(OR) CRACKS FOUND IN FOUR OR MORE TEAR STRAP BAYS(OR) CRACK(S) FOUND LONGER THAN 5 INCHES (OR)CRACK(S) FOUND ARE NOT CONTAINED WITHIN THE SKINCUT-OUT FOR GROUP 1, CONFIGURATION 2, 4 AIRPLANES

Task Relations


Model: BOEING 737-300/400/500


737-53A1293 R2 TABLE 2(02)

REPEAT FUSELAGE - SKIN - STRINGER S-1 AND STRINGERS-2R, STATION 400 TO STATION 460 INSPECTION ANDREPAIR SERVICE BULLETIN EXTERNAL DI AND NDI OF THEFUSELAGE SKIN CHEM-MILL STEPS FOR CRACKS INACCORDANCE WITH ACCOMPLISHMENT INSTRUCTIONS,PARAGRAPH 3.B., PART 1 IF NO CRACK FOUND IN THEFUSELAGE SKIN (AND) OPTION 1 (OR) OPTION 2 USED FORGROUP 1, CONFIGURATION 2, 4 AIRPLANES

737-53A1293 R2 TABLE 2(01)

PERFORM FUSELAGE - SKIN - STRINGER S-1 ANDSTRINGER S-2R, STATION 400 TO STATION 460 INSPECTIONAND REPAIR SERVICE BULLETIN OPTION 1 OR OPTION 2 IFAIRPLANES INSPECTED IN ACCORDANCE WITH THEORIGINAL ISSUE OF THIS SERVICE BULLETIN AND THE LASTINSPECTION WAS DETAILED INSPECTION (DI) PROCEDURE(OR) AIRPLANES INSPECTED IN ACCORDANCE WITHBOEING MULTI-OPERATOR MESSAGEMOM-MOM-09-0807-01B (R1) AND THE LAST INSPECTIONWAS DETAILED INSPECTION (DI) PROCEDURE FOR GROUP1, CONFIGURATION 2, 4 AIRPLANES

737-53A1293 R2 TABLE 1(04)

PERFORM FUSELAGE - SKIN - STRINGER S-1 ANDSTRINGER S-2R, STATION 400 TO STATION 460 INSPECTIONAND REPAIR SERVICE BULLETIN OPTION 1 OR OPTION 2 IFCRACK(S) FOUND AT OR AFTER 35,000 TOTAL FLIGHTCYCLES (AND) CRACKS(S) FOUND IN THREE OR FEWERTEAR STRAP BAYS (AND) CRACK(S) FOUND 5 INCHES ORSHORTER AND CRACK(S) FOUND ARE CONTAINED WITHINTHE SKIN CUT-OUT FOR GROUP 1, CONFIGURATION 1AIRPLANES

737-53A1293 R2 TABLE 1(03)

PERFORM FUSELAGE - SKIN - STRINGER S-1 ANDSTRINGER S-2R, STATION 400 TO STATION 460 INSPECTIONAND REPAIR SERVICE BULLETIN OPTION 1 OR OPTION 2 IFCRACK(S) FOUND BEFORE 35,000 TOTAL FLIGHT CYCLES(OR) CRACKS FOUND IN FOUR OR MORE TEAR STRAP BAYS(OR) CRACK(S) LONGER THAN 5 INCHES OR CRACK(S)FOUND ARE NOT CONTAINED WITHIN THE SKIN CUT-OUTFOR GROUP 1, CONFIGURATION 1 AIRPLANES

737-53A1293 R2 TABLE 1(02)

PERFORM FUSELAGE - SKIN - STRINGER S-1 ANDSTRINGER S-2R, STATION 400 TO STATION 460 INSPECTIONAND REPAIR SERVICE BULLETIN EXTERNAL DI AND NDI OFTHE FUSELAGE SKIN CHEM-MILL STEPS FOR CRACKS INACCORDANCE WITH ACCOMPLISHMENT INSTRUCTIONS,PARAGRAPH 3.B., PART 1 IF NO CRACK FOUND IN THEFUSELAGE SKIN AND OPTION 1 OR OPTION 2 USED FORGROUP 1, CONFIGURATION 1 AIRPLANES

Task Relations


Model: BOEING 737-300/400/500


737-53A1293 R2 TABLE 1(01)

PERFORM FUSELAGE - SKIN - STRINGER S-1 ANDSTRINGER S-2R, STATION 400 TO STATION 460 INSPECTIONAND REPAIR SERVICE BULLETIN OPTION 1 (OR) OPTION 2IF AIRPLANES NOT INSPECTED IN ACCORDANCE WITH THEORIGINAL ISSUE OF THIS SERVICE BULLETIN FOR GROUP 1,CONFIGURATION 1 AIRPLANES

737-53A1293 R2 TABLE 3(03)

PERFORM FUSELAGE - SKIN - STRINGER S-1 ANDSTRINGER S-2R, STATION 400 TO STATION 460 INSPECTIONAND REPAIR SERVICE BULLETIN OPTION 1 (OR) OPTION 2IF CRACK(S) FOUND BEFORE 35,000 TOTAL FLIGHT CYCLES(OR) CRACK(S) FOUND IN FOUR OR MORE TEAR STRAPBAYS. (OR) CRACK S) FOUND LONGER THAN 5 INCHES (OR)CRACK(S) FOUND ARE NOT CONTAINED WITHIN THE SKINCUT-OUT FOR GROUP 1, CONFIGURATION 3, 5 AIRPLANES

737-53A1293 R2 TABLE 3(01)

PERFORM FUSELAGE - SKIN - STRINGER S-1 ANDSTRINGER S-2R, STATION 400 TO STATION 460 INSPECTIONAND REPAIR SERVICE BULLETIN OPTION 1 (OR) OPTION 2IF AIRPLANES INSPECTED IN ACCORDANCE WITH THEORIGINAL ISSUE OF THIS SERVICE BULLETIN AND THE LASTINSPECTION WAS A NON DESTRUCTIVE INSPECTION (NDI)PROCEDURE (OR) AIRPLANES INSPECTED IN ACCORDANCEWITH BOEING MULTI-OPERATOR MESSAGEMOM-MOM-09-0807-01B (R1) AND THE LAST INSPECTIONWAS A NON DESTRUCTIVE INSPECTION (NDI) PROCEDUREFOR GROUP 1, CONFIGURATION 3, 5 AIRPLANES

737-53A1293 R2 TABLE 6 NON DESTRUCTIVE FUSELAGE - SKIN - STRINGER S-1 ANDSTRINGER S-2R, STATION 400 TO STATION 460 INSPECTIONAND REPAIR SERVICE BULLETIN INSPECTION (NDI) OF THESKIN AT THE CRITICAL ROW OF FASTENERS IN THE REPAIRFOR CRACKS FOR GROUP 2 AIRPLANES WITH A REPAIRINSTALLED IN ACCORDANCE WITH THIS SERVICE BULLETIN

737-53A1293 R2 TABLE 5(04)

PERFORM FUSELAGE - SKIN - STRINGER S-1 ANDSTRINGER S-2R, STATION 400 TO STATION 460 INSPECTIONAND REPAIR SERVICE BULLETIN OPTION 1 (OR) OPTION 2IF CRACK(S) FOUND AT OR AFTER 33,000 TOTAL FLIGHTCYCLES (AND) CRACK(S) FOUND BETWEEN STA 420 ANDSTA 440 (AND) CRACK(S) FOUND 12.5 INCHES OR SHORTER(AND) CRACK(S) FOUND ARE CONTAINED WITHIN THE SKINCUT-OUT. FOR GROUP 2 AIRPLANES

737-53A1293 R2 TABLE 5(03)

PERFORM FUSELAGE - SKIN - STRINGER S-1 ANDSTRINGER S-2R, STATION 400 TO STATION 460 INSPECTIONAND REPAIR SERVICE BULLETIN OPTION 1 (OR) OPTION 2IF CRACK(S) FOUND BEFORE 33,000 TOTAL FLIGHT CYCLES(OR) CRACK(S) FOUND BETWEEN STA 400 AND STA 420 (OR)CRACK (S) FOUND BETWEEN STA 440 AND STA 460 (OR)CRACK(S) FOUND LONGER THAN 12.5 INCHES (OR)CRACK(S) FOUND ARE NOT CONTAINED WITHIN THE SKINCUT-OUT FOR GROUP 2 AIRPLANES

Task Relations


Model: BOEING 737-300/400/500


737-53A1293 R2 TABLE 5(02)

REPEAT FUSELAGE - SKIN - STRINGER S-1 AND STRINGERS-2R, STATION 400 TO STATION 460 INSPECTION ANDREPAIR SERVICE BULLETIN EXTERNAL NDI OF THEFUSELAGE SKIN CHEM-MILL STEPS FOR CRACKS INACCORDANCE WITH ACCOMPLISHMENT INSTRUCTIONS,PARAGRAPH 3.B., PART 5 IF NO CRACK FOUND IN THEFUSELAGE SKIN (AND)OPTION 1 (OR) OPTION 2 USED FORGROUP 2 AIRPLANES

737-53A1293 R2 TABLE 5(01)

PERFORM FUSELAGE - SKIN - STRINGER S-1 ANDSTRINGER S-2R, STATION 400 TO STATION 460 INSPECTIONAND REPAIR SERVICE BULLETIN OPTION 1 (OR) OPTION 2FOR ALL GROUP 2 AIRPLANES

737-53A1293 R2 TABLE 4 DETAILED INSPECTION FUSELAGE - SKIN - STRINGER S-1AND STRINGER S-2R, STATION 400 TO STATION 460INSPECTION AND REPAIR SERVICE BULLETIN (DI) OR NONDESTRUCTIVE INSPECTIONS (NDI) OF THE SKIN AT THECRITICAL ROW OF FASTENERS IN THE REPAIR FORCRACKS FOR GROUP 1 AIRPLANES WITH A REPAIRINSTALLED IN ACCORDANCE WITH THIS SERVICE BULLETIN

737-53A1301 R2 FUSELAGE - SKIN - CRACKS AT CHEM-MILLED STEPS INCROWN SKINS AT SPECIFIED LOCATIONS - INSPECTIONSERVICE BULLETIN

PRIMARY TO

737-53A1301 R2 TABLE 2 DETAILED INSPECTION FUSELAGE - SKIN - CRACKS ATCHEM-MILLED STEPS IN CROWN SKINS AT SPECIFIEDLOCATIONS - INSPECTION SERVICE BULLETIN FOR ALLAIRPLANCE (OPTION 1 OR OPTION 2) FUSELAGE SKININSPECTIONS COMMON TO AIRCRAFT WITH 10 INCH TEARSTRAP BAYS AT NEW LOCATIONS ADDED AS GIVEN INREVISION 1 (GROUP 1-12)

737-53A1322 FUSELAGE - STRINGERS AND OTHER LONGITUDINALMEMBERS - STRINGER SPLICES AND BUTT STRAPS ATBODY STATION 360 AND BODY STATION 908, STRINGERS-10L TO S-10R - INSPECTION AND REPLACEMENT SERVICEBULLETIN

PRIMARY TO

737-53A1322 TABLE 10 PERFORM FUSELAGE - STRINGERS AND OTHERLONGITUDINAL MEMBERS - STRINGER SPLICES AND BUTTSTRAPS AT BODY STATION 360 AND BODY STATION 908,STRINGER S-10L TO S-10R - INSPECTION ANDREPLACEMENT SERVICE BULLETIN INTERNAL DETAILEDINSPECTIONS, INTERNAL HFEC SURFACE INSPECTIONSAND INTERNAL LFEC INSPECTIONS (STA 908 ZONE B)9GROUP 5 CONFIGURATION 5-8 AND GROUP 6CONFIGURATION 2)

Task Relations


Model: BOEING 737-300/400/500


737-53A1322 TABLE 09 PERFORM FUSELAGE - STRINGERS AND OTHERLONGITUDINAL MEMBERS - STRINGER SPLICES AND BUTTSTRAPS AT BODY STATION 360 AND BODY STATION 908,STRINGER S-10L TO S-10R - INSPECTION ANDREPLACEMENT SERVICE BULLETIN INTERNAL DETAILEDINSPECTIONS, INTERNAL HFEC SURFACE INSPECTIONSAND INTERNAL LFEC INSPECTIONS (STA 908 ZONE A)(GROUP 5 CONFIGURATION 1-4 AND GROUP 6CONFIGURATION 1)

737-53A1322 TABLE 06.2 PERFORM FUSELAGE - STRINGERS AND OTHERLONGITUDINAL MEMBERS - STRINGER SPLICES AND BUTTSTRAPS AT BODY STATION 360 AND BODY STATION 908,STRINGER S-10L TO S-10R - INSPECTION ANDREPLACEMENT SERVICE BULLETIN INTERNAL DETAILEDINSPECTIONS, INTERNAL HFEC SURFACE INSPECTIONSAND INTERNAL LFEC INSPECTIONS ZONE B (STA 908)(GROUP 2 CONFIGURATION 5-8, GROUP 3 CONFIGURATION2 AND GROUP 4)

737-53A1322 TABLE 06.1 PERFORM FUSELAGE - STRINGERS AND OTHERLONGITUDINAL MEMBERS - STRINGER SPLICES AND BUTTSTRAPS AT BODY STATION 360 AND BODY STATION 908,STRINGER S-10L TO S-10R - INSPECTION ANDREPLACEMENT SERVICE BULLETIN INTERNAL DETAILEDINSPECTIONS, INTERNAL HFEC SURFACE INSPECTIONSAND INTERNAL LFEC INSPECTIONS ZONE B (STA 360)(GROUP 2 CONFIGURATION 5-8, GROUP 3 CONFIGURATION2 AND GROUP 4)

737-53A1322 TABLE 05.2 PERFORM FUSELAGE - STRINGERS AND OTHERLONGITUDINAL MEMBERS - STRINGER SPLICES AND BUTTSTRAPS AT BODY STATION 360 AND BODY STATION 908,STRINGER S-10L TO S-10R - INSPECTION ANDREPLACEMENT SERVICE BULLETIN INTERNAL DETAILEDINSPECTIONS, INTERNAL HFEC SURFACE INSPECTIONSAND INTERNAL LFEC INSPECTIONS ZONE B (STA 908)(GROUP 2 CONGIFURATION 1-4 AND 3 CONFIGURATION 1)

737-53A1322 TABLE 05.1 PERFORM FUSELAGE - STRINGERS AND OTHERLONGITUDINAL MEMBERS - STRINGER SPLICES AND BUTTSTRAPS AT BODY STATION 360 AND BODY STATION 908,STRINGER S-10L TO S-10R - INSPECTION ANDREPLACEMENT SERVICE BULLETIN INTERNAL DETAILEDINSPECTIONS, INTERNAL HFEC SURFACE INSPECTIONSAND INTERNAL LFEC INSPECTIONS ZONE B (STA 360)(GROUP 2 CONGIFURATION 1-4 AND 3 CONFIGURATION 1)

Task Relations


Model: BOEING 737-300/400/500


737-53A1322 TABLE 04.2 PERFORM FUSELAGE - STRINGERS AND OTHERLONGITUDINAL MEMBERS - STRINGER SPLICES AND BUTTSTRAPS AT BODY STATION 360 AND BODY STATION 908,STRINGER S-10L TO S-10R - INSPECTION ANDREPLACEMENT SERVICE BULLETIN OPTION 1 OR OPTION 2 (STA 908 ZONE A) (GROUP 4)

737-53A1322 TABLE 03.2 PERFORM FUSELAGE - STRINGERS AND OTHERLONGITUDINAL MEMBERS - STRINGER SPLICES AND BUTTSTRAPS AT BODY STATION 360 AND BODY STATION 908,STRINGER S-10L TO S-10R - INSPECTION ANDREPLACEMENT SERVICE BULLETIN OPTION 1 OR OPTION 2(STA 908 ZONE A ) (GROUP 2 CONFIGURATION 5-8 AND 3CONFIGURATION 2)


737-53A1322 TABLE 11 PERFORM FUSELAGE - STRINGERS AND OTHERLONGITUDINAL MEMBERS - STRINGER SPLICES AND BUTTSTRAPS AT BODY STATION 360 AND BODY STATION 908,STRINGER S-10L TO S-10R - INSPECTION ANDREPLACEMENT SERVICE BULLETIN INTERNAL DETAILEDINSPECTIONS (STRINGER SPLICE POST REPAIR) (GROUP2-6)

737-53A1322 TABLE 07 PERFORM FUSELAGE - STRINGERS AND OTHERLONGITUDINAL MEMBERS - STRINGER SPLICES AND BUTTSTRAPS AT BODY STATION 360 AND BODY STATION 908,STRINGER S-10L TO S-10R - INSPECTION ANDREPLACEMENT SERVICE BULLETIN OPTION 1 AND OPTION2 (STA 908 ZONE A ) (GROUP 5, CONFIGURATION 1-4;GROUP 6, CONFIGURATION 1)

737-53A1322 TABLE 08 PERFORM FUSELAGE - STRINGERS AND OTHERLONGITUDINAL MEMBERS - STRINGER SPLICES AND BUTTSTRAPS AT BODY STATION 360 AND BODY STATION 908,STRINGER S-10L TO S-10R - INSPECTION ANDREPLACEMENT SERVICE BULLETIN OPTION 1 OR OPTION 2 (STA 908 ZONE A ) (GROUP 5 CONFIGURATION 5-8 ANDGROUP 6 CONFIGURATION 2)

737-53A1322 TABLE 01 CONTACT FUSELAGE - STRINGERS AND OTHERLONGITUDINAL MEMBERS - STRINGER SPLICES AND BUTTSTRAPS AT BODY STATION 360 AND BODY STATION 908,STRINGER S-10L TO S-10R - INSPECTION ANDREPLACEMENT SERVICE BULLETIN BOEING TO GETINSTRUCTIONS (GROUP 1)

Task Relations


Model: BOEING 737-300/400/500


737-53A1322 TABLE 02.1 PERFORM FUSELAGE - STRINGERS AND OTHERLONGITUDINAL MEMBERS - STRINGER SPLICES AND BUTTSTRAPS AT BODY STATION 360 AND BODY STATION 908,STRINGER S-10L TO S-10R - INSPECTION ANDREPLACEMENT SERVICE BULLETIN OPTION 1 OR OPTION 2 (STA 360 ZONE A ) (GROUP 2 CONFIGURATION 1-4 AND 3CONFIGURATION 1)


737-53A1322 TABLE 04.1 PERFORM FUSELAGE - STRINGERS AND OTHERLONGITUDINAL MEMBERS - STRINGER SPLICES AND BUTTSTRAPS AT BODY STATION 360 AND BODY STATION 908,STRINGER S-10L TO S-10R - INSPECTION ANDREPLACEMENT SERVICE BULLETIN OPTION 1 OR OPTION 2 (STA 360 ZONE A) (GROUP 4)

737-53A1329 FUSELAGE - SKIN - FORWARD ENTRY DOORWAY - LOWERCORNERS - INSPECTION AND REPAIR SERVICE BULLETIN

PRIMARY TO737-53A1329 GRP (2) TBL(1.2)

PERFORM FUSELAGE - SKIN - FORWARD ENTRY DOORWAY- LOWER CORNERS - INSPECTION AND REPAIR SERVICEBULLETIN INTERNAL HFEC INSPECTION OF THE BEARSTRAP AND AN EXTERNAL DETAILED AND HFECINSPECTION OF THE SKIN ASSEMBLY FOR ANY CRACK (ALLAIRPLANES)

737-53A1329 GRP (2) TBL(1.1)

PERFORM FUSELAGE - SKIN - FORWARD ENTRY DOORWAY- LOWER CORNERS - INSPECTION AND REPAIR SERVICEBULLETIN INTERNAL HIGH FREQUENCY EDDY CURRENT(HFEC) INSPECTION OF THE BEAR STRAP AND ANEXTERNAL DETAILED AND HFEC INSPECTION OF THE SKINASSEMBLY FOR ANY CRACK (ALL AIRPLANES)

737-53A1329 GRP (1) CONTACT FUSELAGE - SKIN - FORWARD ENTRY DOORWAY- LOWER CORNERS - INSPECTION AND REPAIR SERVICEBULLETIN BOEING TO GET INSTRUCTIONS FOR THEINSPECTIONS AND REPAIRS AND DO THE WORKINSTRUCTED

737-53A1329 GRP (2) TBL(1.3)

CONTACT FUSELAGE - SKIN - FORWARD ENTRY DOORWAY- LOWER CORNERS - INSPECTION AND REPAIR SERVICEBULLETIN BOEING FOR REPAIR INSTRUCTIONS AND DOTHE WORK INSTRUCTED (IF ANY CRACK IS FOUND IN THESKIN ASSEMBLY OR BEAR STRAP)

Task Relations


Model: BOEING 737-300/400/500


737-53A1329 GRP (3) TBL(2.1)


737-53A1329 GRP (3) TBL(2.2)

INSTALL FUSELAGE - SKIN - FORWARD ENTRY DOORWAY -LOWER CORNERS - INSPECTION AND REPAIR SERVICEBULLETIN THE REPAIR (IF ANY CRACK IS FOUND IN THESKIN ASSEMBLY OR BEAR STRAP AT THE LOWER AFTCORNER)

737-53A1329 GRP (3) TBL(2.3)


737-53A1329 GRP (3) TBL(2.4)

CONTACT FUSELAGE - SKIN - FORWARD ENTRY DOORWAY- LOWER CORNERS - INSPECTION AND REPAIR SERVICEBULLETIN BOEING FOR REPAIR INSTRUCTIONS AND DOTHE WORK INSTRUCTED (IF ANY CRACK IS FOUND IN THESKIN ASSEMBLY OR BEAR STRAP AT THE LOWERFORWARD CORNER)

737-54A1044 R2 NACELLES/PYLONS - NACELLE STRUT - MIDSPAR FUSE PIN -INSPECTION, REPAIR AND REPLACEMENT SERVICEBULLETIN

PRIMARY TO

737-54A1044 R2 TABLE1.3

DETAILED INSPECTION NACELLES/PYLONS - NACELLESTRUT - MIDSPAR FUSE PIN - INSPECTION, REPAIR ANDREPLACEMENT SERVICE BULLETIN OF ENGINE STRUTMIDSPAR FUSE PINS WITH PART NUMBER 311A1092-2.

737-54A1044 R2 TABLE1.2

INSTALL NACELLES/PYLONS - NACELLE STRUT - MIDSPARFUSE PIN - INSPECTION, REPAIR AND REPLACEMENTSERVICE BULLETIN A NEW MIDSPAR FUSE PINS

737-55-1091 STABILIZERS - HORIZONTAL STABILIZER - INSPECTION ANDREPLACEMENT OF THRUST BEAM CORNER FITTINGSSERVICE BULLETIN

ACD (TWO WAY) TO

737-55-1091 R1 STABILIZERS - HORIZONTAL STABILIZER - INSPECTION ANDREPLACEMENT OF THRUST BEAM CORNER FITTINGSSERVICE BULLETIN

737-55A1070 R4 STABILIZERS - ELEVATOR - TAB ASSEMBLY - INSPECTIONOF ELEVATOR TAB HINGE AND ELEVATOR TAB CONTROLMECHANISM SERVICE BULLETIN

PRIMARY TO

737-55A1070 R4 TABLE3.2

ACCOMPLISH STABILIZERS - ELEVATOR - TAB ASSEMBLY -INSPECTION OF ELEVATOR TAB HINGE AND ELEVATOR TABCONTROL MECHANISM SERVICE BULLETIN ACTION PART 3

Task Relations


Model: BOEING 737-300/400/500


737-55A1070 R4 TABLE 2 ACCOMPLISH STABILIZERS - ELEVATOR - TAB ASSEMBLY -INSPECTION OF ELEVATOR TAB HINGE AND ELEVATOR TABCONTROL MECHANISM SERVICE BULLETIN ACTION PART 6FOLLOWED BY TABLE 4 FOR ALL AIRPLANES THAT HAVEELEVATOR/TAB CONFIGURATION 21OR 31 AS DETERMINEDFROM PART 4

737-55A1070 R4 TABLE3.1

ACCOMPLISH STABILIZERS - ELEVATOR - TAB ASSEMBLY -INSPECTION OF ELEVATOR TAB HINGE AND ELEVATOR TABCONTROL MECHANISM SERVICE BULLETIN ACTION PART10,FOLLOWED BY PART 1 AND PART 2

737-55A1070 R4 TABLE1.1

ACCOMPLISH STABILIZERS - ELEVATOR - TAB ASSEMBLY -INSPECTION OF ELEVATOR TAB HINGE AND ELEVATOR TABCONTROL MECHANISM SERVICE BULLETIN ACTIONS, PART4, FOLLOWED BY PART 1,PART 2,PART 3 FOLLOWED BYPART 5 FOR AIRPLANES THAT HAVE NOT BEEN INSPECTEDIN ACCORDANCE WITH SB 737-55A1070 REV. 1

737-55A1070 R4 TABLE1.2

ACCOMPLISH STABILIZERS - ELEVATOR - TAB ASSEMBLY -INSPECTION OF ELEVATOR TAB HINGE AND ELEVATOR TABCONTROL MECHANISM SERVICE BULLETIN ACTIONS PART4 FOLLOWED BY PART 1, PART 2,PART 3, FOLLOWED BYPART 5 FOR AIRPLANES THAT HAVE BEEN INSPECTED INACCORDANCE WITH SB 737-55A1070 REV. 1

737-57-1210 R3 WINGS - CENTER WING BOX - FLOOR BEAM INSPECTION,MODIFICATION AND REPAIR (SUPERSEDED BY SB737-57-1210 R4) SERVICE BULLETIN

PRIMARY TO

737-57-1210 R3 PARA (E) DETAILED INSPECTION WINGS - CENTER WING BOX -FLOOR BEAM INSPECTION, MODIFICATION AND REPAIR(SUPERSEDED BY SB 737-57-1210 R4) SERVICE BULLETIN FOR CRACKS IN THE FLOOR BEAM

737-57-1210 R4 WINGS - CENTER WING BOX - FLOOR BEAM INSPECTION,MODIFICATION AND REPAIR SERVICE BULLETIN

PRIMARY TO737-57-1210 R4 PARA (E)2

DETAILED INSPECTION WINGS - CENTER WING BOX -FLOOR BEAM INSPECTION, MODIFICATION AND REPAIRSERVICE BULLETIN FOR CRACKS IN THE FLOOR BEAM(STATION 651 TO STATION 676)

737-57-1210 R4 PARA (E)1

DETAILED INSPECTION WINGS - CENTER WING BOX -FLOOR BEAM INSPECTION, MODIFICATION AND REPAIRSERVICE BULLETIN FOR CRACKS IN THE FLOOR BEAM(STATION 698 TO STATION 717)

737-57-1296 R1 WINGS - CENTER WING BOX - LONGITUDINAL FLOOR BEAMSBETWEEN BODY STATION 656 AND BODY STATION 727 -INSPECTION, REPAIR AND PREVENTIVE MODIFICATIONSERVICE BULLETIN

PRIMARY TO

Task Relations


Model: BOEING 737-300/400/500


737-57-1296 R1 (TABLE3)-1

DETAILED INSPECTION WINGS - CENTER WING BOX -LONGITUDINAL FLOOR BEAMS BETWEEN BODY STATION656 AND BODY STATION 727 - INSPECTION, REPAIR ANDPREVENTIVE MODIFICATION SERVICE BULLETIN AT (LBL)24.82 AND RIGHT BUTTOCK LINE (RBL) 24.82, BETWEENSTATION (STA) 656 AND STA 685 (GROUP 3)

737-57-1296 R1 (TABLE1-2-4)-4

DETAILED INSPECTION WINGS - CENTER WING BOX -LONGITUDINAL FLOOR BEAMS BETWEEN BODY STATION656 AND BODY STATION 727 - INSPECTION, REPAIR ANDPREVENTIVE MODIFICATION SERVICE BULLETIN AT LBL45.57 AND RBL 45.57, STA 727B (GROUP 1,2 AND 4)

737-57-1296 R1 (TABLE1-2-4)-3

DETAILED INSPECTION WINGS - CENTER WING BOX -LONGITUDINAL FLOOR BEAMS BETWEEN BODY STATION656 AND BODY STATION 727 - INSPECTION, REPAIR ANDPREVENTIVE MODIFICATION SERVICE BULLETIN AT LBL24.82 AND RBL 24.82, STA 727B (GROUP 1,2 AND 4)

737-57-1296 R1 (TABLE1-2-4)-2

DETAILED INSPECTION WINGS - CENTER WING BOX -LONGITUDINAL FLOOR BEAMS BETWEEN BODY STATION656 AND BODY STATION 727 - INSPECTION, REPAIR ANDPREVENTIVE MODIFICATION SERVICE BULLETIN AT LBL45.57 AND RBL 45.57, BETWEEN STA 705 AND STA 715(GROUP 1,2 AND 4)

737-57-1296 R1 (TABLE1-2-4)-1

DETAILED INSPECTION WINGS - CENTER WING BOX -LONGITUDINAL FLOOR BEAMS BETWEEN BODY STATION656 AND BODY STATION 727 - INSPECTION, REPAIR ANDPREVENTIVE MODIFICATION SERVICE BULLETIN AT (LBL)24.82 AND (RBL) 24.82 BETWEEN STATION 705 AND STATION715 (GROUP 1,2 AND 4)

737-57-1296 R1 (TABLE3)-6

HIGH FREQUENCY EDDY CURRENT WINGS - CENTER WINGBOX - LONGITUDINAL FLOOR BEAMS BETWEEN BODYSTATION 656 AND BODY STATION 727 - INSPECTION,REPAIR AND PREVENTIVE MODIFICATION SERVICEBULLETIN AT LBL 24.82 AND RBL 24.82, BETWEEN STA 660AND STA 666 (GROUP 3)

737-57-1296 R1 (TABLE3)-5

DETAILED INSPECTION WINGS - CENTER WING BOX -LONGITUDINAL FLOOR BEAMS BETWEEN BODY STATION656 AND BODY STATION 727 - INSPECTION, REPAIR ANDPREVENTIVE MODIFICATION SERVICE BULLETIN AT LBL45.57 AND RBL 45.57, STA 727B (GROUP 3)

737-57-1296 R1 (TABLE3)-4

DETAILED INSPECTION WINGS - CENTER WING BOX -LONGITUDINAL FLOOR BEAMS BETWEEN BODY STATION656 AND BODY STATION 727 - INSPECTION, REPAIR ANDPREVENTIVE MODIFICATION SERVICE BULLETIN AT LBL24.82 AND RBL 24.82, STA 727B (GROUP 3)

Task Relations


Model: BOEING 737-300/400/500


737-57-1296 R1 (TABLE3)-3

DETAILED INSPECTION WINGS - CENTER WING BOX -LONGITUDINAL FLOOR BEAMS BETWEEN BODY STATION656 AND BODY STATION 727 - INSPECTION, REPAIR ANDPREVENTIVE MODIFICATION SERVICE BULLETIN AT LBL45.57 AND RBL 45.57, BETWEEN STA 705 AND STA 715(GROUP 3)

737-57-1296 R1 (TABLE3)-2

DETAILED INSPECTION WINGS - CENTER WING BOX -LONGITUDINAL FLOOR BEAMS BETWEEN BODY STATION656 AND BODY STATION 727 - INSPECTION, REPAIR ANDPREVENTIVE MODIFICATION SERVICE BULLETIN AT LBL24.82 AND RBL 24.82, BETWEEN STA 705 AND STA 715(GROUP 3)

737-57-1296 R1 (TABLE1-2-4)-5

HIGH FREQUENCY EDDY CURRENT WINGS - CENTER WINGBOX - LONGITUDINAL FLOOR BEAMS BETWEEN BODYSTATION 656 AND BODY STATION 727 - INSPECTION,REPAIR AND PREVENTIVE MODIFICATION SERVICEBULLETIN INSPECTION AT LBL 24.82 AND RBL 24.82,BETWEEN STA 660 AND STA 666 (GROUP 1,2 AND 4)

737-57-1318 WINGS - LANDING GEAR SUPPORT BEAM - REAR SPAR ANDAFT SUPPORT FITTING INSPECTION SERVICE BULLETIN

PRIMARY TO737-57-1318 TBL (1) HFEC WINGS - LANDING GEAR SUPPORT BEAM - REAR

SPAR AND AFT SUPPORT FITTING INSPECTION SERVICEBULLETIN INSPECTIONS (GROUP 1) - CONTACT BOEINGAND DO THE WORK AS INSTRUCTED

737-57-1318 TBL (3)OPTION (3)

HFEC WINGS - LANDING GEAR SUPPORT BEAM - REARSPAR AND AFT SUPPORT FITTING INSPECTION SERVICEBULLETIN ACTION 1-SURFACE INSPECTION OF THE REARSPAR UPPER CHORD AND REAR SPAR WEB & ACTION2-OPEN HOLE INSPECTION FOR CRACKING IN THE 12FASTENER HOLES, FOR GROUP 2-6, CONFIGURATION 2

737-57-1318 TBL (5)OPTION (3)

HFEC WINGS - LANDING GEAR SUPPORT BEAM - REARSPAR AND AFT SUPPORT FITTING INSPECTION SERVICEBULLETIN ACTION 1- SURFACE INSPECTION OF THE REARSPAR UPPER CHORD AND REAR SPAR WEB & ACTION 2-OPEN HOLE INSPECTION FOR CRACKING IN THE 12FASTENER HOLES, FOR GROUP 7

737-57-1318 TBL (5)OPTION (2)

HFEC WINGS - LANDING GEAR SUPPORT BEAM - REARSPAR AND AFT SUPPORT FITTING INSPECTION SERVICEBULLETIN ACTION 1- OPEN HOLE INSPECTION FORCRACKING IN THE 8 FASTENER HOLES IN THE UPPER ROWOF FASTENERS & ACTION 2- OPEN HOLE INSPECTION INTHE 12 FASTENER HOLES, FOR GROUP 7

737-57-1318 TBL (5)OPTION (1)

HFEC WINGS - LANDING GEAR SUPPORT BEAM - REARSPAR AND AFT SUPPORT FITTING INSPECTION SERVICEBULLETIN OPEN HOLE INSPECTION FOR CRACKING IN THE12 FASTENER HOLES, FOR GROUP 7

Task Relations


Model: BOEING 737-300/400/500


737-57-1318 TBL (4)OPTION (3)

HFEC WINGS - LANDING GEAR SUPPORT BEAM - REARSPAR AND AFT SUPPORT FITTING INSPECTION SERVICEBULLETIN ACTION 1- SURFACE INSPECTION OF THE REARSPAR UPPER CHORD AND REAR SPAR WEB & ACTION 2-OPEN HOLE INSPECTION FOR CRACKING IN THE 12FASTENER HOLES, FOR GROUP 2-6, CONFIGURATION 3

737-57-1318 TBL (4)OPTION (2)

HFEC WINGS - LANDING GEAR SUPPORT BEAM - REARSPAR AND AFT SUPPORT FITTING INSPECTION SERVICEBULLETIN ACTION 1-OPEN HOLE INSPECTION FORCRACKING IN THE 8 FASTENER HOLES IN THE UPPER ROWOF FASTENERS & ACTION 2-OPEN HOLE INSPECTION FORCRACKING IN THE 12 FASTENER HOLES, FOR GROUP 2-6,CONFIGURATION 3

737-57-1318 TBL (3)OPTION (2)

HFEC WINGS - LANDING GEAR SUPPORT BEAM - REARSPAR AND AFT SUPPORT FITTING INSPECTION SERVICEBULLETIN OPEN HOLE INSPECTION FOR CRACKING.ACTION 1-IN THE 8 FASTENER HOLES (LOCATIONS 1-8) &ACTION 2-IN THE 12 FASTENER HOLES (LOCATIONS 1-12),FOR GROUP 2-6, CONFIGURATION 2

737-57-1318 TBL (3)OPTION (1)

HFEC WINGS - LANDING GEAR SUPPORT BEAM - REARSPAR AND AFT SUPPORT FITTING INSPECTION SERVICEBULLETIN OPEN HOLE INSPECTION FOR CRACKING IN THE12 FASTENER HOLES , FOR GROUP 2-6, CONFIGURATION 2

737-57-1318 TBL (2)OPTION (3)

HFEC WINGS - LANDING GEAR SUPPORT BEAM - REARSPAR AND AFT SUPPORT FITTING INSPECTION SERVICEBULLETIN ACTION 1: SURFACE INSPECTION OF THE REARSPAR UPPER CHORD. ACTION 2: SURFACE INSPECTION OFTHE REAR SPAR WEB & ACTION 3: OPEN HOLE INSPECTIONFOR CRACKING IN THE 12 FASTENER HOLES , FOR GROUP2-6, CONFIGURATION 1

737-57-1318 TBL (2)OPTION (2)

HFEC WINGS - LANDING GEAR SUPPORT BEAM - REARSPAR AND AFT SUPPORT FITTING INSPECTION SERVICEBULLETIN OPEN HOLE INSPECTION FOR CRACKING.ACTION 1-AT THE 4 UPPER ROW FASTENER HOLES(LOCATIONS 3, 4, 5 AND 6) THAT WERE PREVIOUSLY HFECINSPECTED, ACTION 2-AT THE 4 UPPER ROW FASTENERHOLES (LOCATIONS 1, 2, 7 AND 8) THAT WERE NOTPREVIOUSLY HFEC INSPECTED & ACTION 3-IN THE 12FASTENER HOLES (LOCATIONS 1-12), FOR GROUP 2-6,CONFIGURATION 1

737-57-1318 TBL (2)OPTION (1)

HFEC WINGS - LANDING GEAR SUPPORT BEAM - REARSPAR AND AFT SUPPORT FITTING INSPECTION SERVICEBULLETIN OPEN HOLE INSPECTION FOR CRACKING IN THE12 FASTENER HOLES, FOR GROUP 2-6, CONFIGURATION 1

Task Relations


Model: BOEING 737-300/400/500


737-57-1318 TBL (4)OPTION (1)

HFEC WINGS - LANDING GEAR SUPPORT BEAM - REARSPAR AND AFT SUPPORT FITTING INSPECTION SERVICEBULLETIN OPEN HOLE INSPECTION FOR CRACKING IN THE12 FASTENER HOLES, FOR GROUP 2-6, CONFIGURATION 3

737-57A1218 R6 WINGS - TRAILING EDGE FLAPS - OUTBOARD FLAPCARRIAGE SPINDLE REPAIR AND LIFE LIMITING SERVICEBULLETIN

PRIMARY TO

737-57A1218 R6 PARA E2

REPLACE WINGS - TRAILING EDGE FLAPS - OUTBOARDFLAP CARRIAGE SPINDLE REPAIR AND LIFE LIMITINGSERVICE BULLETIN OUTBOARD FLAP (INBOARD CARRIAGEWBL 254 AND OUTBOARD CARRIAGE WBL 355)

737-57A1218 R6 PARA E1

PERFORM WINGS - TRAILING EDGE FLAPS - OUTBOARDFLAP CARRIAGE SPINDLE REPAIR AND LIFE LIMITINGSERVICE BULLETIN INITIAL INSPECTION AND OVERHAULOF TRAILING EDGE FLAPS - OUTBOARD FLAP CARRIAGESPINDLE


PRIMARY TO

737-57A1271 R3 PARAE(2)

PERFORM WINGS - TRAILING EDGE AND TRAILING EDGEDEVICES - TRAILING EDGE FLAPS - OUTBOARD FLAP,INBOARD TRACK INSPECTION/OVERHAUL/REPLACEMENTAT WBL 254 SERVICE BULLETIN AN INITIAL OVERHAUL OFTHE FLAP TRACK

737-57A1271 R3 PARAE(1)

PERFORM WINGS - TRAILING EDGE AND TRAILING EDGEDEVICES - TRAILING EDGE FLAPS - OUTBOARD FLAP,INBOARD TRACK INSPECTION/OVERHAUL/REPLACEMENTAT WBL 254 SERVICE BULLETIN THE INITIAL INSPECTIONOF THE FLAP TRACK

737-57A1277 R1 WINGS - TRAILING EDGE FLAPS - OUTBOARD FLAPCARRIAGE SPINDLE - INSPECTION FOR CRACKING(SUPERSEDED BY SB 737-57A1277 R2) SERVICE BULLETIN

PRIMARY TO

737-57A1277 R1 PARA E.(2)

PERFORM WINGS - TRAILING EDGE FLAPS - OUTBOARDFLAP CARRIAGE SPINDLE - INSPECTION FOR CRACKING(SUPERSEDED BY SB 737-57A1277 R2) SERVICE BULLETIN A GAP CHECK ON EACH OUTBOARD FLAP ASSEMBLY TODETECT A SEVERED SPINDLE

737-57A1277 R1 PARA E.(1)

NDT INSPECTION WINGS - TRAILING EDGE FLAPS -OUTBOARD FLAP CARRIAGE SPINDLE - INSPECTION FORCRACKING (SUPERSEDED BY SB 737-57A1277 R2) SERVICEBULLETIN OF THE SPINDLE OF EACH CARRIAGE (TWOCARRIAGES PER MIDFLAP)

737-57A1277 R2 WINGS - TRAILING EDGE FLAPS - OUTBOARD FLAPCARRIAGE SPINDLE - INSPECTION FOR CRACKING(SUPERSEDED BY SB 737-57A1277 R3) SERVICE BULLETIN

PRIMARY TO

Task Relations


Model: BOEING 737-300/400/500


737-57A1277 R2 PARA E1

NDT WINGS - TRAILING EDGE FLAPS - OUTBOARD FLAPCARRIAGE SPINDLE - INSPECTION FOR CRACKING(SUPERSEDED BY SB 737-57A1277 R3) SERVICE BULLETIN INSPECTION OF THE SPINDLE OF EACH CARRIAGE (TWOCARRIAGES PER MIDFLAP)

737-57A1277 R2 PARA E2

PERFORM WINGS - TRAILING EDGE FLAPS - OUTBOARDFLAP CARRIAGE SPINDLE - INSPECTION FOR CRACKING(SUPERSEDED BY SB 737-57A1277 R3) SERVICE BULLETIN A GAP CHECK ON EACH OUTBOARD FLAP ASSEMBLY TODETCT A SEVERED SPINDLE

737-57A1277 R3 WINGS - TRAILING EDGE FLAPS - OUTBOARD FLAPCARRIAGE SPINDLE - INSPECTION FOR CRACKING SERVICEBULLETIN

PRIMARY TO

737-57A1277 R3 PARA E(GAP)

PERFORM WINGS - TRAILING EDGE FLAPS - OUTBOARDFLAP CARRIAGE SPINDLE - INSPECTION FOR CRACKINGSERVICE BULLETIN A GAP CHECK ON EACH OUTBOARDFLAP ASSEMBLY TO DETCT A SEVERED SPINDLE

737-57A1277 R3 PARA E(NDT)

NDT INSPECTION WINGS - TRAILING EDGE FLAPS -OUTBOARD FLAP CARRIAGE SPINDLE - INSPECTION FORCRACKING SERVICE BULLETIN OF THE SPINDLE OF EACHCARRIAGE (TWO CARRIAGES PER MIDFLAP)

737-57A1301 R2 WINGS - FLIGHT SURFACES - LEADING EDGE SLATS - MAINTRACK DOWNSTOP ASSEMBLY INSPECTION ANDMODIFICATION (SUPERSEDED BY SB 737-57A1301 R3)SERVICE BULLETIN

PRIMARY TO

737-57A1301 R2 TABLE1.2

TORQUE WINGS - FLIGHT SURFACES - LEADING EDGESLATS - MAIN TRACK DOWNSTOP ASSEMBLY INSPECTIONAND MODIFICATION (SUPERSEDED BY SB 737-57A1301 R3)SERVICE BULLETIN THE NUT AND DO A DETAILEDINSPECTION TO VERIFY THAT THE BOLT CHAMFERPROTRUDES FULLY BEYOND THE NUT FOR ALL AIRPLANES

737-57A1301 R2 TABLE2.3

DETAILED INSPECTION WINGS - FLIGHT SURFACES -LEADING EDGE SLATS - MAIN TRACK DOWNSTOPASSEMBLY INSPECTION AND MODIFICATION (SUPERSEDEDBY SB 737-57A1301 R3) SERVICE BULLETIN FOR DAMAGETO THE INTERIOR SURFACE OF THE SLAT CAN AND DEBRISIN THE SLAT FOR ALL AIRPLANES

737-57A1301 R2 TABLE1.1

DETAILED INSPECTION WINGS - FLIGHT SURFACES -LEADING EDGE SLATS - MAIN TRACK DOWNSTOPASSEMBLY INSPECTION AND MODIFICATION (SUPERSEDEDBY SB 737-57A1301 R3) SERVICE BULLETIN OF SLATS 2, 3,4, AND 5 AND THE INBOARD TRACK OF THE NUMBER 1 AND6 SLATS, MAIN TRACK DOWNSTOP ASSEMBLIES. GROUP 1,CONFIGURATION 1; GROUP 2, CONFIGURATION 2

Task Relations


Model: BOEING 737-300/400/500


737-57A1301 R2 TABLE2.2

REPLACE WINGS - FLIGHT SURFACES - LEADING EDGESLATS - MAIN TRACK DOWNSTOP ASSEMBLY INSPECTIONAND MODIFICATION (SUPERSEDED BY SB 737-57A1301 R3)SERVICE BULLETIN BOLT, WASHER, NUT, AND STOPFITTING AND THEN DO A DETAILED INSPECTION OF THESLAT CAN AND SLAT MAIN TRACK DOWNSTOP ASSEMBLIES.GROUP 1, CONFIGURATION 2, GROUP 2.

737-57A1301 R2 TABLE2.1

REPLACE WINGS - FLIGHT SURFACES - LEADING EDGESLATS - MAIN TRACK DOWNSTOP ASSEMBLY INSPECTIONAND MODIFICATION (SUPERSEDED BY SB 737-57A1301 R3)SERVICE BULLETIN BOLT, WASHERS AND NUT INDOWNSTOP ASSEMBLY AND THEN DO A DETAILEDINSPECTION OF THE SLAT CAN AND SLAT MAIN TRACKDOWNSTOP ASSEMBLIES. GROUP 1, CONFIGURATION 1.

737-57A1301 R3 WINGS - FLIGHT SURFACES - LEADING EDGE SLATS - MAINTRACK DOWNSTOP ASSEMBLY INSPECTION ANDMODIFICATION SERVICE BULLETIN

PRIMARY TO

737-57A1301 R3 TABLE1.1

DETAILED INSPECTION WINGS - FLIGHT SURFACES -LEADING EDGE SLATS - MAIN TRACK DOWNSTOPASSEMBLY INSPECTION AND MODIFICATION SERVICEBULLETIN OF SLATS 2, 3, 4, AND 5 AND THE INBOARDTRACK OF THE NUMBER 1 AND 6 SLATS, MAIN TRACKDOWNSTOP ASSEMBLIES. GROUP 1, CONFIGURATION 1,CONFIGURATION 2; GROUP 2 AIRPLANES

737-57A1301 R3 TABLE2.1/.2

REPLACE WINGS - FLIGHT SURFACES - LEADING EDGESLATS - MAIN TRACK DOWNSTOP ASSEMBLY INSPECTIONAND MODIFICATION SERVICE BULLETIN BOLT, WASHERSAND NUT IN DOWNSTOP ASSEMBLY AS GIVEN INPARAGRAPH 3.B WORK INSTRUCTIONS, PART 4. THEN DO ADETAILED INSPECTION OF THE SLAT CAN AND SLAT MAINTRACK. GROUP 1, CONFIGURATION 1

737-57A1301 R3 TABLE 3 DETAILED INSPECTION WINGS - FLIGHT SURFACES -LEADING EDGE SLATS - MAIN TRACK DOWNSTOPASSEMBLY INSPECTION AND MODIFICATION SERVICEBULLETIN OF THE SLAT CAN INTERIOR TO CHECK FORFOREIGN OBJECT DEBRIS (FOD) FOR ALL AIRPLANES

737-57A1301 R3 TABLE1.9

TORQUE WINGS - FLIGHT SURFACES - LEADING EDGESLATS - MAIN TRACK DOWNSTOP ASSEMBLY INSPECTIONAND MODIFICATION SERVICE BULLETIN THE NUT AND DO ADETAILED INSPECTION TO VERIFY THAT THE BOLTCHAMFER PROTRUDES FULLY BEYOND THE NUT FOR ALLAIRPLANES

737-57A1319 WINGS - TRAILING EDGE FLAPS - OUTBOARD FLAP,CARRIAGE SPINDLE - INSPECTION FOR CORROSIONSERVICE BULLETIN

PRIMARY TO

Task Relations


Model: BOEING 737-300/400/500


737-57A1319 TABLE 1(CIC)

INSPECT WINGS - TRAILING EDGE FLAPS - OUTBOARDFLAP, CARRIAGE SPINDLE - INSPECTION FOR CORROSIONSERVICE BULLETIN THE LOWER SURFACE OF THEFORWARD END OF THE SPINDLE AT THE ROOT FOR CICCOVERAGE AND APPLY AS NECESSARY

737-57A1319 TABLE 1(REP)

REPLACE WINGS - TRAILING EDGE FLAPS - OUTBOARDFLAP, CARRIAGE SPINDLE - INSPECTION FOR CORROSIONSERVICE BULLETIN THE CARRIAGE WITH A SERVICEABLECARRIAGE IF MISSING OR FLAKED COATING OR BASEMETAL CORROSION IS FOUND.

737-57A1319 TABLE 1(INSP)

INSPECT WINGS - TRAILING EDGE FLAPS - OUTBOARDFLAP, CARRIAGE SPINDLE - INSPECTION FOR CORROSIONSERVICE BULLETIN THE LOWER SURFACE OF THEFORWARD END OF THE SPINDLE AT THE ROOT FOR ALLAIRPLANES WITH SUSPECT CARRIAGE PART NUMBERS65C27409-29 OR 65C27409-31 OR 65-47821-30 ORUNIDENTIFIABLE PART NUMBERS

737-57A1319 TABLE 1(DET)

DETERMINE WINGS - TRAILING EDGE FLAPS - OUTBOARDFLAP, CARRIAGE SPINDLE - INSPECTION FOR CORROSIONSERVICE BULLETIN IF YOU HAVE ANY SUSPECT CARRIAGEINSTALLED ON ALL AIRPLANES

737-57A1319 WINGS - TRAILING EDGE FLAPS - OUTBOARD FLAP,CARRIAGE SPINDLE - INSPECTION FOR CORROSIONSERVICE BULLETIN

ACD (TWO WAY) TO


D-2012-237 R1 FIRE PROTECTION IN LAVATORIES GERMAN AD PRIMARY TOD-2012-237 R1 (A) FIRE PROTECTION IN LAVATORIES GERMAN AD INSTALL

PLACARDS D-2012-237 R1 (B) FIRE PROTECTION IN LAVATORIES GERMAN AD

ANNOUNCMENT PROCEDURES D-2012-237 R1 (C) FIRE PROTECTION IN LAVATORIES GERMAN AD ASHTRAY

INSTALLATION D-2012-237 R1 (H) FIRE PROTECTION IN LAVATORIES GERMAN AD

OCCURRENCE REPORTS D-2012-237 R1 (E) FIRE PROTECTION IN LAVATORIES GERMAN AD

INSPECTIONS D-2012-237 R1 (F) FIRE PROTECTION IN LAVATORIES GERMAN AD FIRE

PROTECTING CHARACTERISTICS OF THE LAVATORYEQUIPMENT

D-2012-237 R1 (G) FIRE PROTECTION IN LAVATORIES GERMAN AD FIRE/SMOKE ALARM SYSTEMS OR FIRE EXTINGUISHINGSYSTEMS

Task Relations


Model: BOEING 737-300/400/500


D-2012-237 R1 (D) FIRE PROTECTION IN LAVATORIES GERMAN AD ALLOWANCES OF PARTIALLY MISSING OR INOPERATIVEASHTRAYS

ICA-REP-53-043-08 ACCOMPLISH FUSELAGE SECTION 43. BS400, S22R-S23R.SUPPLEMENTAL INSPECTIONS PER SRM 53-00-01 FIGURE210, REPAIR 32 AND SB 737-53A1228

ACD (TWO WAY) TO

737-53A1228 FUSELAGE - MAIN CARGO DOOR CUTOUT, FORWARDCARGO DOOR CUTOUT, AFT CARGO DOOR CUTOUT - SKIN,BEARSTRAP AND FRAME INSPECTIONS SERVICE BULLETIN

ICA-REP-53-046-02 INSPECT TWO CRACKS IN BS727 S18A FOUND DURING NDTPER FIG 10 AT POSITION: FWD LOWER RH BORE, BOTHCRACKS AT 3 O'CLOCK POSITION, 80% AMPLITUDE.DAMAGE SECTION WAS REMOVED BETWEEN S18 TO 24 RHAND NEW SECTION SPLICED IAW SB 737-53-1088 AND DWG65C33722. REPAIR REQUIRES A REPEAT INSPECTION

ACD (TWO WAY) TO

737-53-1088 R1 FUSELAGE - STATION NUMBER 727 BULKHEAD - OUTBOARDCHORD INSPECTION AND REPLACEMENT SERVICEBULLETIN

ICA-REP-53-046-04 INSPECT AIRCON FRAME BRACKET AT BS830 RH, 827 LH,827 RH AND 867 LH

ACD (TWO WAY) TO737-53-1216 R1 FUSELAGE - MAIN FRAME - AIR-CONDITIONING BRACKET

ATTACHMENTS, STATION 360 THROUGH STATION 907 ATSTRINGER 8L AND STRINGER 8R - INSPECTION,PREVENTIVE MODIFICATION, AND REPAIR SERVICEBULLETIN

Task Relations


Model: BOEING 737-300/400/500


Documents

5. Inspection Tasks Packages