2008 - Checklist - Learjet 35A - Ch 2

CL-102B

Copyright © 2006 by Bombardier AerospaceAll rights reserved. Printed in Canada.

&

HANDBOOK

CREW CHECKLIST

QUICK REFERENCE

CL-102BLOEP-1 April 2001

Change 2

LIST OF EFFECTIVE PAGESUse this List of Effective Pages to determine the current status of the Crew Checklist andQuick Reference Handbook. Pages affected by the current change are indicated by an aster-isk (*) immediately preceding the page number.

Dates of issue for original and changed pages are:

Reissue ................................. A .......................... September 1996Reissue ................................. B .....................................April 2001Change.................................. 1 ........................... September 2006Change.................................. 2 ......................................May 2008

Page Change Aircraft Affected

Title ................................................ 1 All*LOEP-1 thru LOEP-4 ..................... 2 All*LOR ............................................... 2 Alli and ii ............................................B All

Normal ProceduresN-1 thru N-4 ...................................B AllN-5 .................................................B Aircraft without Rosemount Pitot-

Static SystemN-5.1 ..............................................B Aircraft with Rosemount Pitot-Static

SystemN-6 thru N-8 ................................... 1 AllN-9 thru N-17 .................................B AllN-18 ............................................... 1 AllN-19 and N-20 ...............................B All

Performance DataP-1 thru P-4 ...................................B AllP-5 and P-6....................................B Aircraft without Thrust ReversersP-5.1 and P-6.1..............................B Aircraft with Aeronca Thrust

ReversersP-5.2 and P-6.2..............................B Aircraft with TR-4000 Thrust

ReversersP-7 thru P-17 .................................B AllP-18 ...............................................B Aircraft without Thrust ReversersP-18.1 ............................................B Aircraft with Aeronca Thrust

ReversersP-18.2 ............................................B Aircraft with TR-4000 Thrust

ReversersP-19 thru P-28 ...............................B AllP-29 thru P-34 ...............................B Aircraft without Rosemount Pitot-

Static SystemP-29.1 thru P-34.1 .........................B Aircraft with Rosemount Pitot-Static

SystemChange 2

CL-102B April 2001 LOEP-2Change 2

b


P-35................................................1 Aircraft without Rosemount Pitot-Static System

P-35.1.............................................1 Aircraft with Rosemount Pitot-StaticSystem

P-36 thru P-42 ............................... B Aircraft without Rosemount Pitot-Static System

P-36.1 thru P-42.1 ......................... B Aircraft with Rosemount Pitot-StaticSystem

P-43................................................1 Aircraft without Rosemount Pitot-Static System

P-43.1.............................................1 Aircraft with Rosemount Pitot-StaticSystem

P-44 thru P-51 ............................... B Aircraft without Rosemount Pitot-Static System

P-44.1 thru P-51.1 ......................... B Aircraft with Rosemount Pitot-StaticSystem

P-52 thru P-55 ............................... B AllP-56 thru P-58 ................................1 All

Emergency ProceduresE-i and E-ii ..................................... B AllE-1................................................. B AllE-2..................................................1 AllE-3 and E-4 ................................... B AllE-5..................................................1 AllE-6................................................. B Aircraft 35-001 thru 35-508, 36-001

thru 36-053, and aircraft not incorpo-rating AMK 85-1

E-6.1.............................................. B Aircraft 35-509 & on, 36-054 & on;and prior aircraft incorporatingAMK 85-1

E-7 and E-8 ................................... B Aircraft 35-001 thru 35-201 & 35-205;and 36-001 thru 36-040 not incorpo-rating AMK 78-13

E-7.1 and E-8.1 ............................. B Aircraft 35-202 thru 35-204, 35-206 &on; 36-041 & on; and prior aircraftincorporating AMK 78-13

E-9..................................................1 AllE-10 thru E-19 ............................... B AllE-20............................................... B Aircraft 35-001 thru 35-081 & 35-083

thru 35-086; and 36-001 thru 36-022not incorporating AMK 76-7

E-20.1............................................ B Aircraft 35-082, 35-087 thru 35-106 &35-108 thru 35-112; 36-023 thru36-031; and prior aircraft incorporat-ing AMK 76-7

Change 2

CL-102BLOEP-3 April 2001

Change 2


E-20.2 ............................................B Aircraft 35-107, 35-113 & on; and36-032 & on

E-21 ...............................................B AllE-22 ............................................... 1 Aircraft 35-001 thru 35-106 & 35-108

thru 35-112; and 36-001 thru 36-031E-22.1 ............................................ 1 Aircraft 35-107, 35-113 & on; and

36-032 & onE-23 ............................................... 1 Aircraft 35-001 thru 35-201 & 35-205;

and 36-001 thru 36-040 not incorpo-rating AMK 78-13

E-23.1 ............................................ 1 Aircraft 35-202 thru 35-204, 35-206 &on; 36-041 & on; and prior aircraftincorporating AMK 78-13

E-24 ............................................... 1 AllE-25 thru E-32 ...............................B AllE-33 ............................................... 1 AllE-34 ...............................................B AllE-35 ...............................................B Aircraft with Aeronca Thrust

ReversersE-35.1 ............................................B Aircraft with TR-4000 Thrust

Reversers

Abnormal ProceduresA-i ..................................................B AllA-ii.................................................. 1 AllA-1 ................................................. 1 Aircraft 35-001 thru 35-106 & 35-108

thru 35-112; and 36-001 thru 36-031A-1.1 .............................................. 1 Aircraft 35-107, 35-113 & on; and

36-032 & on*A-2 ................................................. 2 AllA-3 thru A-5 ...................................B AllA-6 thru A-9 ...................................B Aircraft 35-001 thru 35-106 & 35-108

thru 35-112; and 36-001 thru 36-031A-6.1 thru A-9.1 .............................B Aircraft 35-107, 35-113 & on; and

36-032 & onA-10 ...............................................B AllA-11................................................ 1 AllA-12 thru A-14 ...............................B AllA-15 and A-16................................B Aircraft 35-001 thru 35-106 & 35-108

thru 35-112; and 36-001 thru 36-031A-15.1 and A-16.1..........................B Aircraft 35-107, 35-113 & on; and air-

craft 36-032 & onA-17 thru A-22 ...............................B All

*A-23 ............................................... 2 AllA-24 ............................................... 1 All

Change 2

CL-102B April 2001 LOEP-4Change 2

b


A-25............................................... B Aircraft without Rosemount Pitot-Static System

A-25.1............................................ B Aircraft with Rosemount Pitot-StaticSystem

A-26 thru A-30 ............................... B All*A-31................................................2 AllA-32............................................... B AllA-33 thru A-35 ............................... B Aircraft without Thrust ReversersA-33.1 thru A-35.1 ......................... B Aircraft with Aeronca Thrust

ReversersA-33.2 thru A-35.2 ......................... B Aircraft with TR-4000 Thrust

Reversers

Supplemental DataS-1 thru S-13 ................................. B AllS-14............................................... B Aircraft without Split Essential BusesS-14.1............................................ B Aircraft with Split Essential BusesS-15 and S-16 ............................... B AllS-17............................................... B Aircraft 35-001 thru 35-106 & 35-108

thru 35-112; and aircraft 36-001 thru36-031

S-17.1............................................ B Aircraft 35-107, 35-113 & on; and air-craft 36-032 & on

S-18............................................... B Aircraft 35-001 thru 35-081 & 35-083thru 35-086; and 36-001 thru 36-022not incorporating AMK 76-7

S-18.1............................................ B Aircraft 35-082, 35-087 thru 35-106 &35-108 thru 35-112; 36-023 thru36-031; and prior aircraft incorporat-ing AMK 76-7

S-18.2............................................ B Aircraft 35-107, 35-113 & on; and36-032 & on

S-19............................................... B Aircraft without Rosemount Pitot-Static System

S-19.1............................................ B Aircraft with Rosemount Pitot-StaticSystem

S-20............................................... B AllS-21............................................... B Aircraft 35-001 thru 35-106 & 35-108

thru 35-112; and 36-001 thru 36-031S-21.1............................................ B Aircraft 35-107, 35-113 & on; and

36-032 & onS-22 and S-23 ............................... B AllS-24................................................1 All

Change 2

CL-102BApril 2001 LORChange 2

b

LOG OF REVISIONS

REVISIONNO.

DESCRIPTION INCORPORATEDBY

DATE

Reissue BApril 2001

Harmonizes with:- Change 5 of FM-019- Change 12 of FM-102- Change 20 of FM-108Reformatted to fit new size checklist.

Change 1September 2006

Harmonizes with:- Change 6 of FM-019- Change 13 of FM-102- Change 21 of FM-108

Change 2May 2008

Harmonizes with:- Change 7 of FM-019- Change 14 of FM-102- Change 22 of FM-108

IMPORTANT

TO THE OWNER OF THIS CHECKLIST

A yearly checklist revision service is available. The cost of revision servicewill be billed at current pricing levels. If you wish to receive the checklist re-vision service, please fill in the blanks below and mail to the address at thebottom of the page.

Aircraft Serial Number

Mailing Address forRevision Service:

Name

Address

Business Phone No

Fax No

E-Mail Address

Mail To: Learjet Inc.P.O. Box 7707Wichita, Kansas 67277-7707Attn: Document Control Center (MS#71)

CL-102B

35 -36 -

TECHNICAL PUBLICATION USER COMMENT SHEET

We welcome your comments, criticism, and suggestions concerning anyBombardier-Learjet publication. The action taken, as the result of your com-ments, will be noted below and a copy returned to you. This form may bereturned in any of the following formats:- E-mailed to [email protected] (preferred)- Mailed to Bombardier-Learjet Technical Publications- Faxed to (316) 946-2002

Today’s Date Aircraft Model S/N

Checklist Procedure

Page Number

Comment/Suggestion

Name

Address

Business Phone FAX

E-Mail

Action Taken

Mail To: Learjet Inc.P.O. Box 7707Wichita, Kansas 67277-7707Attn: Manager Technical Publications (MS#53)

CL-102B

3536

CL-102B April 2001 i

b

IMPORTANT NOTICEAPPLICABILITY: This checklist is applicable to all Learjet Model 35 and36 series aircraft (35-001 and on, and 36-001 and on).

NOTEThis checklist contains performance data for aircraftwith Century III wing. Aircraft without Century III wing,refer to the FAA Approved Airplane Flight Manual andPilot’s Manual for performance data.

USE OF CHECKLIST: These are suggested procedures only and in noway supersede current procedures outlined in the FAA Approved AirplaneFlight Manual and any revisions thereto. In the event of conflict, the FAAApproved Airplane Flight Manual takes precedence.

This checklist has been designed so that pages not applicable to a partic-ular aircraft may be removed from the checklist. Removing such pagesallows the operator to construct a checklist applicable to a particularaircraft.

Each text page of this checklist contains an effectivity block located at thebottom of the page. To remove pages not applicable to your aircraft, exam-ine the effectivity block to determine if the page is applicable to youraircraft. If the page is not applicable, remove the page from the checklistand discard. If the page is applicable, retain the page.

NOTEBe sure to examine each page of the checklist toensure that all pages not applicable to your aircraft areremoved.

THROUGH FLIGHT CHECKLIST PROCEDURES: Checklist itemsmarked with this symbol (◆) may be used for preflight during intermediatestops where both engines are shut down provided certain criteria are met.Refer to Section II Introduction in the FAA Approved Airplane Flight Manualfor list of criteria.

NOTEBecause this checklist is abbreviated from the AFM,some items marked as through flight appear to entailmore than the AFM itself. Only those items marked asthrough flight in the AFM need be accomplished.

Continued

CL-102Bii April 2001

BOLD PRINT CHECKLIST ITEMS IN NORMAL PROCEDURES: Check-list items emphasized by bold print such as “Spoilers ......Retracted, LightOut” are items considered important to emphasize.

MEMORY ITEMS: Procedures in this checklist emphasized by enclosurein a box such as this should be memorized for crew accomplish-ment without reference to the procedure.

CL-102B April 2001 N-1

ALLEFFECTIVITY

b

NORMAL PROCEDURES

EXTERIOR PREFLIGHT............................................................... N-2

CABIN PREFLIGHT ...................................................................... N-4

BEFORE STARTING ENGINES.................................................... N-5

STARTING ENGINES ................................................................... N-8

BEFORE TAXI

Two Engine.................................................................................... N-9One Engine ................................................................................... N-10TAXI AND BEFORE TAKEOFF

Two Engine.................................................................................... N-9One Engine ................................................................................... N-11RUNWAY LINEUP......................................................................... N-12

AFTER TAKEOFF ......................................................................... N-13

CLIMB ........................................................................................... N-13

CRUISE......................................................................................... N-14

DESCENT ..................................................................................... N-14

APPROACH .................................................................................. N-14

LANDING SPEEDS AND DISTANCES......................................... N-15BEFORE LANDING....................................................................... N-16

GO AROUND ................................................................................ N-16

AFTER LANDING/CLEARING RUNWAY...................................... N-17

SHUTDOWN ................................................................................. N-17

QUICK TURNAROUND ................................................................ N-18

ALLEFFECTIVITY CL-102B

N-2 April 2001

EXTERIOR PREFLIGHT◆ During Preflight, remove all covers, check all vents for obstruction,

check access doors, lights, antennas, and static wicks for conditionand security.

Power OFF1. Controls Lock..................................................... REMOVE & STOW

2. Pilot’s Defog Nozzle.............................................................. CLEAR

3. Left Stall Vane, Pitot-Static & Static Ports ............................ CHECK

4. Left Pitot-Static Drains .........................................DRAIN AS REQ’D

5. Nose Strut & Wheel Well ..................................................... CHECK

6. Nose Wheel & Tire............................................................... CHECK

7. Radome ............................................................................... CHECK

8. Oxygen Valve & Discharge Disc .............. CHECK, IF APPLICABLE

9. Total Temp Probe & Press Static Port.................................. CHECK

10. Right Stall Vane, Pitot-Static & Static Ports.......................... CHECK

11. Right Pitot-Static Drains.......................................DRAIN AS REQ’D

12. Copilot’s Defog Nozzle ......................................................... CLEAR

13. Lower Fuselage ................................................................... CHECK

14. Emergency Exit ................................................................. SECURE

15. Upper Fuselage ................................................................... CHECK

16. Right Engine Inlet ................................................................ CHECK

17. Fuselage Fuel Drains ............................................................DRAIN

18. Right Main Strut & Wheel Well............................................. CHECK

19. Right Main Wheels, Tires & Brakes ..................................... CHECK

(Procedure Continued)

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ALLEFFECTIVITY

b

20. Right Wing............................................................................CHECK

a. Stall Strip & Stall Fence (if installed) .............................CHECK

b. Tip Tank ........................................................................CHECK

c. Tip Tank Sump ...............................................................DRAIN

21. Right Fuel Cap................................................................... SECURE

22. Right Nav Light & Static Wicks (2)........................................CHECK

23. Right Aileron, Spoiler & Flap.................................................CHECK

24. Boundary Layer Energizers or Vortex Generators................CHECK

25. Right Engine .........................................................................CHECK

TR. Thrust Reverser...............................CHECK & STOWED (Aeronca)CHECK & PINS REMOVED (TR-4000)

26. Fuel Vent ...................................................... DRAIN COMPLETELY

27. Fuselage Fuel Drains ............................................................DRAIN

28. Tailcone Interior ....................................................................CHECK

29. Drag Chute (if installed)........................................................CHECK

30. Right Fuselage .....................................................................CHECK

31. Right Fuel Computer Drain....................................................DRAIN

32. Oxygen Discharge Disc ........................... CHECK, IF APPLICABLE

33. Tail Section & Static Wicks (8) ..............................................CHECK

34. Tailstand ............................................................................REMOVE

35. Left Fuselage........................................................................CHECK

36. Left Fuel Computer Drain ......................................................DRAIN

37. Fire Extinguisher Discs.........................................................CHECK

38. Left Engine ...........................................................................CHECK

TR. Thrust Reverser..... ..........................CHECK & STOWED (Aeronca)CHECK & PINS REMOVED (TR-4000)


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N-4 April 2001

39. Left Spoiler, Flap & Aileron .................................................. CHECK

40. Boundary Layer Energizers or Vortex Generators............... CHECK

41. Left Nav Light & Static Wicks (2) ......................................... CHECK

42. Left Fuel Cap ..................................................................... SECURE

43. Left Wing ............................................................................. CHECK

a. Tip Tank........................................................................ CHECK

b. Tip Tank Sump ...............................................................DRAIN

c. Stall Strip & Stall Fence (if installed)............................. CHECK

44. Left Main Strut & Wheel Well ............................................... CHECK

45. Left Main Wheels, Tires & Brakes ....................................... CHECK

46. Left Engine Inlet................................................................... CHECK

Power ON

47. Landing Gear Switch ...................................................................DN

48. Battery Switches..........................................................................ON

49. Fuel Quantities .................................................................... CHECK

50. Pitot-Static/Stall Vane/Temp Probe Heat.............................. CHECK

51. Exterior Lights...................................................................... CHECK

52. Battery Switches........................................................................OFF

CABIN PREFLIGHT1. Baggage ......................................................................... SECURED

2. Cabin Air Damper ............................................................ AS REQ’D

3. Emergency Exit ............................................. SECURED & CLEAR

4. Passengers....................................................................... BRIEFED

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ALLEFFECTIVITY

b

BEFORE STARTING ENGINES1. Controls Lock.................................................................... STOWED

2. Safety Belts, ShoulderHarnesses & Seats..........................................SECURE & ADJUST

3. Flight Controls ......................................................................CHECK

4. Oxygen System:

a. Pass Mask Valve............................................................. AUTO

b. Pass Oxygen Valve........................................................ NORM

c. Oxygen Pressure ..........................................................CHECK

d. Crew Masks ..................................... CHECK & SELECT 100%

5. Circuit Breakers .............................................................................IN


7. Emergency Battery(ies) ..............................................CHECK & ON

8. Panel Switches & Avionics ............................................OFF or SET

Fuel Cmptr (ON) Pitch Trim (PRI)Anti-Skid (ON) Jet Pumps (ON)ALT Static (CLOSED) Emer Press (NORM, if instl)Bleed Air (ON) Pilot’s Altimeter (NORM)

9. Batteries .....................................................................CHECK & ON

10. GPU (if desired).....................................................CONNECT & ON

11. Inverters......................................................................CHECK & ON

12. Emergency Lights (if installed) ...............................TEST & ARMED


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Without Rosemount Pitot-Static System

EFFECTIVITY

CL-102B April 2001 N-5.1

ALLEFFECTIVITY

b

BEFORE STARTING ENGINES1. Controls Lock.................................................................... STOWED

2. Safety Belts, ShoulderHarnesses & Seats..........................................SECURE & ADJUST


4. Oxygen System:

a. Pass Mask Valve............................................................. AUTO

b. Pass Oxygen Valve........................................................ NORM

c. Oxygen Pressure ..........................................................CHECK

d. Crew Masks ..................................... CHECK & SELECT 100%



7. Emergency Battery(ies) ..............................................CHECK & ON

8. Panel Switches & Avionics ............................................OFF or SET

Fuel Cmptr (ON) Pitch Trim (PRI)Anti-Skid (ON) Jet Pumps (ON)Static Source (BOTH) Emer Press (NORM, if instl)Bleed Air (ON)

9. Batteries .....................................................................CHECK & ON

10. GPU (if desired).....................................................CONNECT & ON

11. Inverters......................................................................CHECK & ON

12. Emergency Lights (if installed) ...............................TEST & ARMED


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With Rosemount Pitot-Static System

EFFECTIVITY


N-6 April 2001Change 1

13. System Pressure:

a. Hydraulic Pressure....................................................... CHECK

b. Emergency Air Pressure .............................................. CHECK

14. Parking Brake ............................................................................ SET

15. Emergency Brake Handle............................PULL FROM RECESS,THEN RETURN

(Do not push handle downward)16. Hyd Pump..................................................................................OFF

17. Annunciator Lights ...................................................................TEST

18. Warning Systems:

a. Ice Detect Lights .......................................................... CHECK

b. Gear Warning...................................................................TEST

c. Fire Detect .......................................................................TEST

Start One Engine if GPU not Utilized(See Starting Engines Checklist)

d. Cabin Altitude ..................................................................TEST

e. Stick Puller/Mach Warning ........................................... CHECK

f. Mach Trim ........................................................................TEST

g. Stall Warning System (L & R)...........................................TEST

19. Standby Gyro ..........................................UNCAGE, GYRO ERECT

20. Pressurization & Temperature Controls:

a. Pressurization Controls:

(1) L and R Bleed Air Switches.............................................ON

(2) Cabin Air .......................................................................OFF

(3) Auto-Man Switch ............................................ AS DESIRED

(4) Cabin Controller ................................... CRUISE ALTITUDE

(5) Rate Selector ................................................. AS DESIRED

(6) IN NORMAL/OUT DEFOG Knob (if installed) ....... PUSH IN

b. Cabin Temp Controls .......................................... AS DESIRED(Procedure Continued)

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Change 1

CL-102B April 2001 N-7Change 1 ALL

EFFECTIVITY

b

21. Trim Systems:

a. Secondary Pitch & Cutout.............................................CHECK

b. Primary Pitch & Cutout..................................................CHECK

c. Trim Speed (FC-530 autopilot)......................................CHECK

d. Trim Monitor (FC-530 autopilot) ....................................CHECK

e. Aileron...........................................................................CHECK

f. Rudder ..........................................................................CHECK

g. Takeoff Trim (all three axes)............................................... SET

22. Autopilot Monitor...................................................................CHECK

23. Yaw Dampers .......................................................................CHECK

24. Fuel Panel:

a. Fuel Counter ................................................................... ZERO

b. Fuel Quantities..............................................................CHECK

c. Crossflow Valve ............................................................CLOSE

d. Transfer — Fill....................................................................OFF

e. Standby Pumps.................................................CHECK & OFF

f. Fuselage Valve (if installed) ..........................................CLOSE

g. Fuel Jettison.......................................................................OFF

25. CVR.........................................................................................TEST

26. Drag Chute Handle (if installed) ....................................... STOWED

27. Takeoff Data (N1, V1, VR, V2 & T.O. Distance) .......................................COMPUTE & BUGS SET

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STARTING ENGINES1. Cabin Door ..............................................SECURED & LIGHT OUT

2. Fuel Computers ...........................................................................ON

3. Air Conditioner...........................................................................OFF

4. Aux Heat (if installed).................................................................OFF

5. Batteries ......................................................................................ON

• Lead Acid — 24 vdc minimum• Nickel-Cadmium — 23 vdc minimum

6. Inverters.......................................................................................ON

7. Parking Brake (hydraulic pressure req’d) .................................. SET

8. Hyd Pump..................................................................................OFF

9. Beacon Light................................................................................ON

10. Thrust Levers......................................................................CUTOFF

11. Engine ........................................START (ENSURE N1 ROTATION)

12. Start-Gen Switch:

• GPU Assisted Start ............................................ OFF @ IDLE

• Battery Start .......................................................GEN @ IDLE

13. Voltmeter & Ammeter .......................................................... CHECK

14. Spoileron/Spoilers................................................................ CHECK

15. Flaps................................................................................... 20° or 8°

16. Hydraulic Pressure .............................................................. CHECK

Return to and CompleteBefore Starting Engines Checklist (if required)

17. Other Engine .................................................... OPTIONAL START

If other engine is not started, refer to Before Taxi (One Engine) Checklist,page N-1018. GPU (if used)............................................................ DISCONNECT

19. Start-Gen Switches................................................................... GEN


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ALLEFFECTIVITY

b

20. Battery Charging Bus/Current Limiters.................................CHECK

21. Starter Disengagement (if required) .....................................CHECK

22. Voltmeters & Ammeters........................................................CHECK

BEFORE TAXI (TWO ENGINE)1. Avionics ..................................................................................... SET

2. Radar.......................................................................................STBY


4. Coffee/Oven (if installed) ............................................ AS DESIRED

5. Fuel Control Governor ..........................................................CHECK

6. Windshield Heat ................................................ PURGE AS REQ’D

7. Lights ........................................................................ON, AS REQ’D

8. Anti-Skid .............................................................. ON, LIGHTS OUT

9. Pax Briefing/Cabin Secured ......................................... COMPLETE

10. No Smoking Fasten Seat Belt Sign..........................................ON

11. Parking Brake...................................................................RELEASE

TAXI AND BEFORE TAKEOFF(two engine)

1. Brakes & Steering.................................................................CHECK

2. Fuel Panel ...............................................CHECKED & BALANCED

TR. Thrust Reversers (if installed).......................... CHECK & STOWED


4. Flight Instruments .................................................................CHECK

5. Takeoff Data (N1, V1, VR, V2 & T.O. Distance)............. REVIEWED & BUGS SET

6. Engine Instruments...............................................................CHECK

7. Voltmeters & Ammeters........................................................CHECK


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N-10 April 2001

8. Nav Equipment .......................................................................... SET

9. Radar .............................................................................. AS REQ’D

10. Spoilers................................................ RETRACTED, LIGHT OUT

11. Flaps ..................................... SET 20° or 8°, CHECK INDICATION

12. Trims (3).........................................................SET/PRI/LIGHT OUT

13. Pressurization.......................................................................... SET

14. Cabin Air.....................................................................................ON

15. Cabin Temp Controls ................................................................. SET

16. Anti-Ice Systems............................................ CHECK & AS REQ’D

17. Electrically-Heated Windshield (if installed).................................ON

18. Crew Takeoff Briefing.................................................... COMPLETE

BEFORE TAXI (ONE ENGINE)1. GPU (if used)............................................................ DISCONNECT

2. Start-Gen Switch....................................................................... GEN

3. Voltmeter & Ammeter .......................................................... CHECK

4. Avionics ..................................................................................... SET

5. Radar.......................................................................................STBY

6. Circuit Breakers ............................................................................ IN


8. Lights ........................................................................ON, AS REQ’D




12. Parking Brake .................................................................. RELEASE

TAKEOFF PITCH TRIM SETTINGS — DEGREES

CENTER OF GRAVITY — % MAC5 8 12 16 20 24 28 30

7.6 7.5 7.4 7.3 7.2 6.1 5.0 5.0

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CL-102B April 2001 N-11

ALLEFFECTIVITY

b

TAXI AND BEFORE TAKEOFF(ONE ENGINE)

1. Brakes & Steering.................................................................CHECK



4. Takeoff Data(N1, V1, VR, V2 & T.O. Distance)............. REVIEWED & BUGS SET


6. Radar .............................................................................. AS REQ’D

7. Spoilers ................................................RETRACTED, LIGHT OUT

8. Flaps ..................................... SET 20° or 8°, CHECK INDICATION


10. Pressurization.......................................................................... SET


TAKEOFF PITCH TRIM SETTINGS — DEGREES

CENTER OF GRAVITY — % MAC5 8 12 16 20 24 28 30

7.6 7.5 7.4 7.3 7.2 6.1 5.0 5.0

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N-12 April 2001

Ready to Start 2nd Engine:11. Air Conditioner...........................................................................OFF


13. Thrust Lever .......................................................................CUTOFF

14. Engine ...................................................................................START

15. Start-Gen Switch..........................................................GEN @ IDLE

16. Battery Charging Bus/Current Limiters................................ CHECK

17. Starter Disengagement (if required) .................................... CHECK

18. Voltmeter & Ammeters......................................................... CHECK


20. Anti-Ice Systems............................................ CHECK & AS REQ’D

21. Electrically-Heated Windshield (if installed).................................ON

22. Engine Instruments.............................................................. CHECK

TR. Thrust Reversers ............................................ CHECK & STOWED

23. Fuel Control Governor ......................................................... CHECK

24. Flight Controls ..................................................................... CHECK


26. Cabin Air.....................................................................................ON

27. Crew Takeoff Briefing.................................................... COMPLETE

RUNWAY LINEUP1. Parking Brake ................................................................RELEASED

2. Transponder ................................................................................ON

TR. Thrust Reversers (TR-4000)..................................................... ARM

3. Pitot Heat.....................................................................................ON

4. Lights (Strobe, Recognition & Landing) .......................................ON

5. Stall Warning................................................................................ON

6. Ignition .........................................................................................ON

7. Annunciator Panel .............................................................NORMAL

◆

◆

◆

◆

◆

◆

◆

◆

◆

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◆

◆

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CL-102B April 2001 N-13

ALLEFFECTIVITY

b

AFTER TAKEOFF1. Landing Gear (positive rate) ........................................................ UP

2. Yaw Damper ................................................................... ENGAGED

TR. Thrust Reversers (TR-4000)............................................... DISARM

3. Flaps............................................................................................ UP

4. Ignition .......................................................................................OFF

5. Pressurization.......................................................................CHECK

6. Landing/Taxi Lights....................................................................OFF

AP. Autopilot APPR Light (FC-200 autopilot) ...................................OUT

7. Hydraulic Pressure ...............................................................CHECK

8. Angle-of-Attack Indicators ......................................CROSS CHECK

CLIMB10,000 Ft Checks:

1. No Smoking Fasten Seat Belt Sign ................................. AS REQ’D

2. Pressurization..................................................................CHECKED

18,000 Ft (or Transition Altitude) Checks:

1. Altimeters ................................................SET 29.92'' Hg (1013 mb)

2. Recognition Light.......................................................................OFF

3. Air Conditioner............................................... OFF, IF APPLICABLE

4. Oxygen Pressure..................................................................CHECK

5. EMER PRESS Switches (if installed) ................................NORMAL

FL 350 Checks:


FL 410 Checks:

1. 35-001 thru 35-112, except 35-107; 36-001 thru 36-031:Crew & Passenger Oxygen Masks .......................................... DON


N-14 April 2001

CRUISE1. Pressurization...................................................CHECK & NORMAL

2. Fuel Management............................................................ AS REQ’D

3. Engine Instruments.............................................................. CHECK


5. Other Systems................................................................. MONITOR

DESCENT1. Windshield Heat .............................................................. AS REQ’D

2. Windshield Aux Defog (if installed) .................................. AS REQ’D

3. Cabin Controller................................................. FIELD ELEVATION

4. Anti-Ice Systems.............................................................. AS REQ’D

FL 180 (or Transition Level) Checks:

1. Altimeters......................................... SET BARO & CROSS CHECK

2. Recognition Light .........................................................................ON

3. Pressurization...................................................................... CHECK

4. No Smoking Fasten Seat Belt Sign .............................................ON


APPROACH1. Circuit Breakers ............................................................................ IN

2. Hydraulic & Emergency Air Pressure .................................. CHECK

3. Landing Data (N1, VREF, VAPP, Distance).......... COMPUTED & SET

4. Fuel ...............................................................................BALANCED

5. Approach Setup & Briefing ........................................... COMPLETE

TR. Position Indicator Lights (Aeronca)........................................... OUT

a. Bleed Valve ......................................................................TEST

CL-102B April 2001 N-15

ALLEFFECTIVITY

b

LANDING SPEEDS

These speeds & distances were determined for dry runway, zero wind,zero runway gradient, anti-ice off, & anti-skid on.

SPEEDWEIGHT — 1000 LB

10 11 12 13 14 15 15.3 16 17 18.3

VREF &LDG CLIMB 105 110 115 119 123 127 129 131 135 140

APPROACHCLIMB 111 116 121 126 130 134 136 138 142 147

LANDING DISTANCES °F 0 20 40 60 80 100°C -18 -7 4 16 27 38

WT15,300 2825 2900 2976 3051 3127 320315,000 2791 2864 2936 3009 3082 315514,000 2679 2742 2805 2868 2931 299513,000 2549 2608 2667 2726 2785 284412,000 2422 2479 2536 2594 2651 270911,000 2314 2366 2417 2469 2521 257210,000 2208 2255 2302 2348 2395 244215,300 2986 3061 3137 3212 3287 336215,000 2946 3019 3091 3163 3236 330814,000 2814 2877 2939 3002 3065 312813,000 2675 2734 2792 2851 2910 296812,000 2544 2601 2658 2715 2773 283011,000 2424 2476 2527 2578 2630 268110,000 2308 2354 2401 2447 2494 254015,300 3112 3190 3269 3348 342615,000 3067 3143 3219 3294 337014,000 2919 2984 3050 3116 3181 324713,000 2773 2834 2896 2957 3018 308012,000 2640 2699 2759 2819 2878 293811,000 2510 2564 2617 2671 2724 277810,000 2386 2434 2483 2531 2580 2628

TEMP

4000

FT

2000

FT

SEA

LEV

EL


N-16 April 2001

BEFORE LANDING1. Spoilers....................................................................... RETRACTED

2. Flaps................................................................................... 8° or 20°

3. Landing Gear.........................................................................DOWN

4. Landing/Taxi Lights .......................................................... AS REQ’D


6. Engine Sync ..............................................................................OFF


7. Flaps.............................................................. DOWN & INDICATED


9. Ignition .........................................................................................ON

10. Autopilot.......................................................................DISENGAGE

11. Yaw Damper (FC-200 autopilot) .................... OFF DURING FLARE

GO AROUND1. Autopilot.................................................................... DISENGAGED

2. Thrust Levers................................................................... AS REQ’D

3. Spoilers....................................................................... RETRACTED

4. Flaps............................................................................................20°

5. Landing Gear (positive rate) ........................................................ UP

6. Climb at Approach Climb Speed

7. Clear of Obstacles ........................................ VREF + 30, FLAPS UP

CL-102B April 2001 N-17

ALLEFFECTIVITY

b

AFTER LANDING/CLEARING RUNWAY1. Stall Warning .............................................................................OFF

2. Ignition .......................................................................................OFF

TR. Thrust Reverser (TR-4000) ................................................ DISARM

3. Cabin Air....................................................................................OFF

4. Anti-Ice Systems:

a. Pitot Heat & Alcohol ...........................................................OFF

b. Defog, Windshield, Nacelle,Stab & Wing Heat..................................................... AS REQ’D

5. Lights .......................................................................... AS DESIRED

6. One Thrust Lever (Optional)...............................................CUTOFF

7. Spoilers............................................................................ RETRACT

8. Flaps........................................................................................... UP

9. Hydraulic Pressure ...............................................................CHECK

10. Unnecessary Avionics ...............................................................OFF

11. Transponder ............................................................... STBY or OFF

SHUTDOWN1. Parking Brake/Chocks ............................................................... SET

2. Anti-Ice Systems........................................................................OFF

3. Emergency Lights (if installed) ........................................... DISARM

4. Avionics .....................................................................................OFF

5. Standby Attitude Gyro.............................................................CAGE

6. Emergency Battery(ies) .............................................................OFF

7. Coffee/Oven (if installed) ...........................................................OFF




8. Thrust Levers......................................................................CUTOFF

9. Start-Gen Switches....................................................................OFF

10. Inverters.....................................................................................OFF

11. Fuel Transfer .............................................................................OFF

12. Crossflow Valve ................................................................. CLOSED

13. Beacon Light..............................................................................OFF

14. Batteries ....................................................................................OFF

15. Controls Lock......................................................................INSTALL

QUICK TURNAROUND(ONE OR NO ENGINE SHUTDOWN)

1. Cabin Door ..................................................................... SECURED



4. Engine .................START (ENSURE N1 ROTATION) (2 RUNNING)

5. Start-Gen Switches................................................................... GEN

6. Voltmeter & Ammeters......................................................... CHECK

7. Battery Charging Bus/Current Limiters (if required)................................................ CHECK

8. Starter Disengagement (if required) .................................... CHECK

9. Circuit Breakers ............................................................................ IN

10. Avionics ..................................................................................... SET


12. Anti-Ice Systems.............................................................. AS REQ’D



Change 1

CL-102B April 2001 N-19

ALLEFFECTIVITY

b

Taxi:

1. Fuel Panel & Quantity...........................................................CHECK

2. Takeoff Data (N1, V1, VR, V2 & T.O. Distance) .......................................COMPUTE & BUGS SET


4. Radar...........................................................................................ON



7. Spoilers ................................................RETRACTED, LIGHT OUT

8. Flaps ............................................. 20° or 8°, CHECK INDICATION


10. Pressurization ......................................................................... SET

11. Cabin Air.....................................................................................ON

12. Crew Takeoff Briefing ................................................... COMPLETE

Runway Lineup:

1. Parking Brake................................................................RELEASED

2. Transponder ................................................................................ON


3. Pitot Heat.....................................................................................ON

4. Lights (Strobe, Recognition & Landing) .......................................ON

5. Stall Warning ...............................................................................ON

6. Ignition .........................................................................................ON

7. Annunciator Panel .............................................................NORMAL


N-20 April 2001

CREW NOTES

CL-102B April 2001 P-1

ALL

EFFECTIVITY

b

PERFORMANCE DATA

SPEED/TEMPERATURE CONVERSION ..................................... P-3

TAKEOFF POWER (N1) SETTING ............................................... P-5

PARTIAL POWER TAKEOFF (N1) SETTING................................ P-6

TAKEOFF WEIGHT LIMITS FLAPS — 8°..................................... P-7

TAKEOFF SPEEDS AND DISTANCES FLAPS — 8° ................... P-8

TAKEOFF WEIGHT LIMITS FLAPS — 20°................................... P-13

TAKEOFF SPEEDS AND DISTANCES FLAPS — 20° ................. P-14

MAXIMUM CONTINUOUS THRUST FOR CLIMB (N1) ................ P-18

CLIMB PERFORMANCE—TWO ENGINE.................................... P-19

LONG RANGE CRUISE—TWO ENGINE ..................................... P-29

NORMAL CRUISE ........................................................................ P-38

LONG RANGE CRUISE—ONE ENGINE...................................... P-47

MAXIMUM RANGE DESCENT—ONE ENGINE........................... P-53

DESCENT PERFORMANCE SCHEDULE.................................... P-54

HOLDING OPERATIONS.............................................................. P-55

LANDING WEIGHT LIMITS .......................................................... P-55

LANDING SPEEDS & DISTANCES .............................................. P-56

PER

FOR

MA

NC

E

CL-102B

P-2 April 2001ALL

EFFECTIVITY

CREW NOTES

PER

FOR

MA

NC

E


ALL

EFFECTIVITY

b

SPEED/TEMPERATURE CONVERSIONMACH — TRUE

.60 .62 .64 .66 .68 .70 .72 .74 .76 .78 .80 .820 OAT -18 -19 -20 -21 -23 -24 -25 -26 -28 -29 -30 -32

KTAS 374 385 397 408 419 431 442 453 464 475 486 496-5 OAT -23 -24 -25 -26 -27 -28 -30 -31 -32 -34 -35 -36

KTAS 370 381 393 404 416 427 438 449 460 470 481 492-10 OAT -27 -28 -30 -31 -32 -33 -34 -36 -37 -38 -39 -41

KTAS 367 378 389 400 412 423 434 445 455 466 477 487-15 OAT -32 -33 -34 -35 -36 -38 -39 -40 -41 -42 -44 -45

KTAS 363 374 386 397 408 418 429 440 451 462 474 483-20 OAT -37 -38 -39 -40 -41 -42 -43 -45 -46 -47 -48 -49

KTAS 359 371 382 393 404 415 425 436 447 457 468 478-25 OAT -41 -42 -43 -45 -46 -47 -48 -49 -50 -51 -53 -54

KTAS 356 367 378 389 399 410 421 432 443 453 463 473-30 OAT -46 -47 -48 -49 -50 -51 -52 -54 -55 -56 -57 -58

KTAS 352 363 374 385 396 406 417 427 438 448 458 468-35 OAT -51 -52 -53 -54 -55 -56 -57 -58 -59 -60 -62 -63

KTAS 349 359 370 381 391 402 413 423 434 444 453 463-40 OAT -55 -56 -57 -58 -59 -60 -62 -63 -64 -65 -66 -67

KTAS 345 356 366 377 387 398 408 418 429 439 449 459-45 OAT -60 -61 -62 -63 -64 -65 -66 -67 -68 -69 -70 -72

KTAS 341 352 362 373 383 394 404 414 424 434 444 453-50 OAT -65 -66 -67 -68 -69 -70 -71 -72 -73 -74 -75 -76

KTAS 338 348 358 369 379 389 399 409 419 429 439 449-55 OAT -69 -70 -71 -72 -73 -74 -75 -76 -77 -78 -79 -80

KTAS 334 344 355 365 375 385 395 405 415 425 435 444-60 OAT -74 -75 -76 -77 -78 -79 -80 -81 -82 -83 -84 -85

KTAS 330 340 350 360 370 380 390 400 410 419 429 438-65 OAT -79 -80 -80 -81 -82 -83 -84 -85 -86 -87 -88 -89

KTAS 326 336 347 357 366 376 386 396 405 415 424 434-70 OAT -83 -84 -85 -86 -87 -88 -89 -90 -91 -92 -93 -94

KTAS 323 332 342 352 362 371 381 390 400 409 419 428-75 OAT -88 -89 -90 -91 -91 -92 -93 -94 -95 -96 -97 -98

KTAS 318 328 338 347 358 367 377 386 395 405 414 423-80 OAT -93 -94 -94 -95 -96 -97 -98 -99 -100 -101 -102 -102

KTAS 314 323 334 343 353 362 371 381 390 399 408 418-85 OAT -97 -98 -99 -100 -101 -101 -102 -103 -104 -105 -106 -107

KTAS 310 320 329 339 348 358 367 376 385 394 403 412

RA

M A

IR T

EMPE

RAT

UR

E (R

AT)

° C

CL-102B

P-4 April 2001ALL

EFFECTIVITY

CREW NOTES


ALL

EFFECTIVITY

b

TAKEOFF POWER (N1) SETTINGANTI-ICE — OFF

NOTE: (xxxx) represents the maximum altitude at which the N1 power setting to the left of the (xxxx) may be used.

OAT ALTITUDE — FEET°F °C S.L. 1000 2000 3000 4000 5000 6000 7000 8000 9000 10000

125 52 89.8

120 49 90.4 90.4 (1700)

115 46 91.3 91.3 91.3 91.3

110 43 92.0 92.0 92.0 92.0 92.0 (4500)

105 41 92.7 92.7 92.7 92.7 92.7 92.7 (5500)

100 38 93.5 93.5 93.5 93.5 93.5 93.5 93.5 93.5

95 35 94.1 94.1 94.1 94.1 94.1 94.1 94.1 94.1 94.1

90 32 94.8 94.8 94.8 94.8 94.8 94.8 94.8 94.8 94.8 94.8 (9700)

85 29 95.5 95.5 95.5 95.5 95.5 95.5 95.5 95.5 95.5 95.5 95.5

80 27 96.0 96.0 96.0 96.0 96.0 96.0 96.0 96.0 96.0 96.0 96.0

75 24 96.5 96.5 96.5 96.5 96.5 96.5 96.5 96.5 96.5 96.5 96.5

70 21 97.1 97.1 97.1 97.1 97.1 97.1 97.1 97.1 97.1 97.1 97.1

65 18 96.8 97.6 97.6 97.6 97.6 97.6 97.6 97.6 97.6 97.6 97.6

60 16 96.3 97.0 97.8 97.8 97.8 97.8 97.8 97.8 97.8 97.8 97.8

55 13 95.8 96.5 97.3 98.2 98.2 98.2 98.2 98.2 98.2 98.2 98.2

50 10 95.3 96.0 96.8 97.9 98.5 98.5 98.5 98.5 98.5 98.5 98.5

45 7 94.7 95.5 96.3 97.4 98.4 98.7 98.7 98.7 98.7 98.7 98.7

40 4 94.3 95.0 95.8 96.9 97.9 98.7 98.9 98.9 98.9 98.9 98.9

35 2 93.7 94.5 95.2 96.3 97.4 98.2 99.0 99.1 99.1 99.1 99.1

30 -1 93.2 94.0 94.7 95.8 96.9 97.7 98.5 99.2 99.2 99.2 99.2

25 -4 92.7 93.5 94.2 95.3 96.4 97.2 98.0 98.8 99.4 99.4 99.4

20 -7 92.2 93.0 93.7 94.8 95.9 96.7 97.5 98.3 98.9 99.5 99.5

15 -9 91.8 92.5 93.2 94.3 95.3 96.2 97.0 97.7 98.4 99.6 99.6

10 -12 91.2 92.0 92.7 93.8 94.8 95.6 96.4 97.2 97.9 99.2 99.7

5 -15 90.7 91.5 92.2 93.3 94.3 95.1 95.9 96.7 97.3 98.7 99.8

0 -18 90.2 91.0 91.7 92.7 93.8 94.6 95.4 96.1 96.8 98.1 99.5

-10 -23 89.2 90.1 90.7 91.7 92.8 93.6 94.4 95.1 95.7 97.1 98.5

-20 -29 88.2 89.1 89.7 90.7 91.7 92.6 93.3 94.0 94.7 96.0 97.4

-30 -34 87.2 88.1 88.8 89.7 90.7 91.6 92.3 93.0 93.7 94.9 96.3

-40 -40 86.3 87.1 87.8 88.7 89.7 90.5 91.2 91.9 92.6 93.9 95.2

-50 -46 85.3 86.1 86.8 87.7 88.7 89.5 90.2 90.9 91.6 92.9 94.1

-60 -51 84.3 85.2 85.9 86.8 87.6 88.5 89.1 89.8 90.5 91.8 93.0

Without Thrust Reversers


EFFECTIVITY

TAK

EOFF

N1

CL-102B

P-6 April 2001ALL

EFFECTIVITY

PARTIAL POWER TAKEOFF N1 SETTING ANTI-ICE — OFF

PARTIAL POWER TAKEOFF DETERMINATION

1. TAKEOFF SPEEDS & DISTANCES Chart — Determine theAssumed Temperature (Highest Temperature allowed for runwaylength and takeoff weight).

2. TAKEOFF SPEEDS & DISTANCES Chart — Using the AssumedTemperature, calculate V1.

3. Partial POWER TAKEOFF N1 SETTING Chart — Using AmbientTemperature and Assumed Temperature, determine reduced N1setting.

NOTE: Thrust reduction must not exceed 7.7% N1.

ASSUMED TEMPERATURE — °F

10 20 30 40 50 60 70 80 90 100 110 120

OU

TSID

E A

IR T

EMPE

RAT

UR

E —

°F

80 (96.2) 94.3 92.2 89.9 87.5

70 (97.2) 95.4 93.4 91.3 89.1 86.7

60 (97.9) 96.3 94.5 92.5 90.5 88.3 85.9

50 (98.5) 97.0 95.3 93.6 91.7 89.7 87.5 85.0

40 (99.0) 97.5 96.0 94.4 92.7 90.8 88.9 86.6 84.1

30 (99.3) 98.0 96.6 95.1 93.5 91.7 89.9 87.9 85.7 83.3

20 (99.5) 98.3 97.0 95.6 94.2 92.7 91.0 89.1 87.1 84.9 82.5

10 (99.7) 98.6 97.3 96.0 94.6 93.2 91.7 90.0 88.2 86.2 84.0 81.6

0 98.8 97.6 96.3 95.0 93.6 92.2 90.7 89.1 87.3 85.3 83.1 80.7

-10 97.7 96.5 95.2 93.9 92.6 91.2 89.7 88.1 86.3 84.4 82.2 79.8

-20 96.6 95.4 94.2 92.9 91.6 90.2 88.7 87.1 85.3 83.4 81.2 79.0

-30 95.5 94.4 93.2 91.9 90.6 89.2 87.7 86.2 84.4 82.4 80.3 79.0

-40 94.4 93.3 92.1 90 9 89.6 88.2 86.7 85.2 83.4 81.5 79.3 79.0


Without Thrust ReversersEFFECTIVITY

TAK

EOFF

N1

CL-102B April 2001 P-5.1

ALL

EFFECTIVITY

TAK

EOFF

N1

b




125 52 87.0

120 49 87.8 87.8 (1700)

115 46 88.6 88.6 88.6 88.6

110 43 89.4 89.4 89.4 89.4 89.4 (4500)

105 41 90.2 90.2 90.2 90.2 90.2 90.2 (5500)

100 38 91.0 91.0 91.0 91.0 91.0 91.0 91.0 91.0

95 35 91.8 91.8 91.8 91.8 91.8 91.8 91.8 91.8 91.8

90 32 92.5 92.5 92.5 92.5 92.5 92.5 92.5 92.5 92.5 92.5 (9700)

85 29 93.2 93.2 93.2 93.2 93.2 93.2 93.2 93.2 93.2 93.2 93.2

80 27 94.0 94.0 94.0 94.0 94.0 94.0 94.0 94.0 94.0 94.0 94.0

75 24 94.7 94.7 94.7 94.7 94.7 94.7 94.7 94.7 94.7 94.7 94.7

70 21 95.2 95.2 95.2 95.2 95.2 95.2 95.2 95.2 95.2 95.2 95.2

65 18 95.0 95.9 95.9 95.9 95.9 95.9 95.9 95.9 95.9 95.9 95.9

60 16 94.5 95.5 96.4 96.4 96.4 96.4 96.4 96.4 96.4 96.4 96.4

55 13 93.9 95.0 96.1 96.9 96.9 96.9 96.9 96.9 96.9 96.9 96.9

50 10 93.4 94.5 95.5 96.6 97.3 97.3 97.3 97.3 97.3 97.3 97.3

45 7 92.9 94.0 95.0 96.1 97.2 97.7 97.7 97.7 97.7 97.7 97.7

40 4 92.4 93.4 94.5 95.6 96.7 97.8 98.0 98.0 98.0 98.0 98.0

35 2 91.9 92.9 94.0 95.1 96.2 97.3 98.3 98.3 98.3 98.3 98.3

30 -1 91.3 92.5 93.5 94.6 95.7 96.7 97.7 98.5 98.5 98.5 98.5

25 -4 90.8 91.9 93.0 94.0 95.1 96.2 97.2 98.1 98.7 98.7 98.7

20 -7 90.3 91.4 92.5 93.5 94.6 95.7 96.7 97.5 98.3 99.0 99.0

15 -9 89.8 90.8 91.9 93.0 94.1 95.1 96.2 97.0 97.8 99.2 99.2

10 -12 89.3 90.3 91.4 92.5 93.6 94.6 95.7 96.5 97.3 98.8 99.4

5 -15 88.8 89.8 90.9 92.0 93.0 94.1 55.1 96.0 96.7 98.2 99.5

0 -18 88.3 89.3 90.4 91.5 92.5 93.6 94.6 95.5 96.2 97.7 99.1

-10 -23 87.3 88.3 89.4 90.5 91.5 92.6 93.6 94.4 95.1 96.6 98.0

-20 -29 86.3 87.3 88.4 89.5 90.5 91.5 92.5 93.4 94.1 95.6 96.9

-30 -34 85.4 86.4 87.4 88.5 89.5 90.5 91.5 92.3 93.0 94.5 95.8

-40 -40 84.5 85.4 86.5 87.5 88.5 89.5 90.4 91.2 92.0 93.4 94.7

-50 -46 83.5 84.5 85.5 86.5 87.5 88.5 89.4 90.2 91.0 92.3 93.7

-60 -51 82.7 83.6 84.6 85.6 86.6 87.6 88.4 89.2 90.0 91.3 92.7

With Aeronca Thrust ReversersEFFECTIVITY

CL-102B

P-6.1 April 2001ALL

EFFECTIVITY

TAK

EOFF

N1

PARTIAL POWER TAKEOFF N1 SETTING ANTI-ICE OFF





NOTE: Thrust reduction must not exceed 7.7% N1.


10 20 30 40 50 60 70 80 90 100 110 120

OU

TSID

E A

IR T

EMPE

RAT

UR

E —

°F

80 (94.2) (91.9) 89.6 87.2 84.6

70 (95.3) 93.3 91.1 88.8 86.3 83.8

60 (96.3) 94.3 92.4 90.3 88.0 85.5 83.0

50 (97.2) 95.3 93.4 91.5 89.4 87.2 84.8 82.2

40 (98.0) 96.1 94.3 92.5 90.6 88.5 86.3 84.0 81.4

30 (98.5) 96.9 95.1 93.4 91.6 89.7 87.6 85.4 83.1 80.6

20 (98.9) 97.5 95.9 94.2 92.5 90.7 88.8 86.7 84.5 82.2 79.8

10 (99.2) 98.0 96.5 94.9 93.3 91.5 89.7 87.9 85.8 83.7 81.4 78.9

0 98.5 97.0 95.5 93.9 92.3 90.6 88.8 86.9 84.9 82.9 80.6 78.1

-10 97.3 95.9 94.4 92.9 91.3 89.6 87.9 86.0 84.0 81.9 79.6 77.2

-20 96.2 94.8 93.4 91.9 90.3 88.7 86.9 85.1 83.1 80.9 78.7 76.4

-30 95.1 93.7 92.3 90.8 89.2 87.6 85.9 84.1 82.1 80.0 77.8 76.0

-40 94.0 92.6 91.2 89.8 88.2 86.6 84.9 83.1 81.1 79.1 76.9 76.0


CL-102B April 2001 P-5.2

ALL

EFFECTIVITY

TAK

EOFF

N1

b




120 49 88.4 88.4 (1700)

115 46 89.4 89.4 89.4 89.4

110 43 90.4 90.4 90.4 90.4 90.4 (4500)

105 41 91.3 91.3 91.3 91.3 91.3 91.3 (5500)

100 38 92.2 92.2 92.2 92.2 92.2 92.2 92.2 92.2

95 35 93.1 93.1 93.1 93.1 93.1 93.1 93.1 93.1 93.1

90 32 94.0 94.0 94.0 94.0 94.0 94.0 94.0 94.0 94.0 94.0 (9700)

85 29 94.7 94.7 94.7 94.7 94.7 94.7 94.7 94.7 94.7 94.7 94.7

80 27 95.4 95.4 95.4 95.4 95.4 95.4 95.4 95.4 95.4 95.4 95.4

75 24 96.0 96.0 96.0 96.0 96.0 96.0 96.0 96.0 96.0 96.0 96.0

70 21 96.6 96.6 96.6 96.6 96.6 96.6 96.6 96.6 96.6 96.6 96.6

65 18 96.5 97.1 97.1 97.1 97.1 97.1 97.1 97.1 97.1 97.1 97.1

60 16 96.0 97.0 97.5 97.5 97.5 97.5 97.5 97.5 97.5 97.5 97.5

55 13 95.5 96.5 97.2 97.9 97.9 97.9 97.9 97.9 97.9 97.9 97.9

50 10 95.0 96.0 96.7 97.8 98.3 98.3 98.3 98.3 98.3 98.3 98.3

45 7 94.4 95.4 96.2 97.2 98.3 98.6 98.6 98.6 98.6 98.6 98.6

40 4 94.0 95.0 95.7 96.7 97.8 98.8 98.8 98.8 98.8 98.8 98.8

35 2 93.4 94.4 95.2 96.2 97.3 98.3 99.1 99.1 99.1 99.1 99.1

30 -1 92.9 93.9 94.6 95.7 96.8 97.8 98.6 99.4 99.4 99.4 99.4

25 -4 92.4 93.4 94.1 95.2 96.3 97.2 98.1 99.0 99.6 99.6 99.6

20 -7 91.9 92.8 93.6 94.7 95.8 96.7 97.6 98.4 99.2 99.8 99.8

15 -9 91.4 92.3 93.0 94.2 95.2 96.2 97.0 97.9 98.7 100.0 100.0

10 -12 90.8 91.8 92.6 93.6 94.7 95.7 96.5 97.4 98.2 99.7 100.0

5 -15 90.4 91.2 92.0 93.1 94.2 95.1 96.0 96.8 97.7 99.2 100.0

0 -18 89.8 90.8 91.6 92.6 93.7 94.6 95.5 96.3 97.2 98.6 100.0

-10 -23 88.9 89.8 90.5 91.6 92.6 93.6 94.4 95.2 96.1 97.6 99.2

-20 -29 87.9 88.8 89.5 90.6 91.6 92.5 93.4 94.2 95.0 96.5 98.2

-30 -34 86.9 87.8 88.6 89.6 90.6 91.5 92.4 93.1 94.0 95.4 97.1

-40 -40 86.0 86.8 87.6 88.6 89.6 90.4 91.3 92.1 92.9 94.4 96.0

-50 -46 85.0 85.8 86.6 87.6 88.5 89.4 90.3 91.0 91.8 93.3 94.9

-60 -51 84.0 84.8 85.6 86.6 87.5 88.3 89.3 90.0 90.8 92.2 93.8

With TR-4000 Thrust ReversersEFFECTIVITY

CL-102B

P-6.2 April 2001ALL

EFFECTIVITY

TAK

EOFF

N1

PARTIAL POWER TAKEOFF N1 SETTING ANTI-ICE OFF





NOTE: This table is for pressure altitudes up to 3000 feet. For altitudes greater than 3000 feet, refer to the FAA Approved Airplane Flight Manual.


10 20 30 40 50 60 70 80 90 100

OU

TSID

E A

IR T

EMPE

RAT

UR

E —

°F

80 93.2 90.8

70 94.4 92.1 89.9

60 95.6 93.5 91.3 89.0

50 96.6 94.6 92.6 90.4 88.1

40 97.4 95.8 93.7 91.8 89.6 87.2

30 97.9 96.4 94.7 92.8 90.9 88.7 86.4

20 98.3 96.9 95.3 93.8 91.8 90.0 87.9 85.6

10 98.5 97.2 95.9 94.4 92.8 90.9 89.0 86.9 84.6

0 98.8 97.6 96.3 94.9 93.4 91.8 90.0 88.1 85.9 83.6

-10 97.5 96.4 95.2 93.9 92.4 90.7 88.9 87.1 85.0 82.8

-20 96.5 95.5 94.4 92.9 91.3 89.7 87.9 86.1 84.1 82.0

-30 95.5 94.4 93.2 91.8 90.3 88.7 86.9 85.1 83.1 81.0

-40 94.5 93.4 92.2 90.9 89.3 87.7 85.9 84.1 82.1 80.0



ALL

EFFECTIVITY

b

TAKEOFF WEIGHT LIMITS FLAPS — 8°

These data were determined for dry runway, zero wind, zero runwaygradient, anti-ice off, & anti-skid on.DO NOT EXCEED MAXIMUM CERTIFIED TAKEOFF WEIGHT

PRESSUREALTITUDE

(FEET)

TEMPERATURE°F 0 20 40 60 80 100°C -18 -7 4 16 27 38

10000 18300 18300 17750 16800 14850

9000 18300 17400 15400

8000 17950 16050

7000 18300 16600

6000 17300 15050

5000 17900 15600

4000 18300 16200

3000 16800

2000 17400

1000 18100

S.L. 18300

CL-102B

P-8 April 2001ALL

EFFECTIVITY

TAKEOFF SPEEDS AND DISTANCES FLAPS — 8°

These data were determined for dry runway, zero wind, zero runwaygradient, anti-ice off, & anti-skid on.

°F 0 20 40 60 80 100°C -18 -7 4 16 27 38

WT V1 Dist V1 Dist V1 Dist V1 Dist V1 Dist V1 Dist18,300 136 4686 136 4857 136 5029 136 5201 137 5942 141 737018,000 134 4530 134 4695 134 4860 134 5025 136 5732 139 708817,000 128 4010 128 4152 128 4295 128 4437 130 5031 134 614916,000 122 3550 122 3675 122 3800 122 3925 124 4412 128 528515,000 115 3127 115 3229 115 3330 115 3431 118 3857 122 466314,000 109 2744 109 2841 109 2938 109 3035 112 3412 116 409013,000 104 2382 104 2461 104 2540 104 2619 106 2925 110 347512,000 103 2242 103 2314 103 2385 103 2456 104 2727 107 320311,000 103 2160 103 2227 103 2295 103 2362 103 2592 105 295810,000 103 2085 103 2152 103 2220 103 2287 103 2493 104 278718,300 136 4859 136 5036 136 5213 136 5544 138 652618,000 134 4697 134 4866 134 5036 134 5354 136 6287 141 820017,000 128 4154 128 4301 128 4447 128 4719 131 5488 135 700016,000 122 3676 122 3805 122 3934 123 4168 125 4769 129 591315,000 116 3230 116 3334 116 3438 116 3632 119 4187 123 515014,000 110 2842 110 2942 110 3042 110 3223 113 3689 117 442813,000 104 2462 104 2543 104 2624 104 2772 107 3150 111 375012,000 103 2314 103 2388 103 2461 103 2594 104 2922 108 346311,000 103 2228 103 2298 103 2367 103 2490 103 2742 106 317310,000 103 2153 103 2223 103 2292 103 2412 103 2613 104 293818,300 136 5033 136 5215 136 5397 137 5942 139 711018,000 134 4863 134 5038 134 5213 135 5732 137 684217,000 128 4298 128 4449 128 4600 129 5031 132 5946 136 793016,000 122 3803 122 3935 122 4068 123 4412 126 5126 131 658615,000 116 3332 116 3439 116 3546 117 3857 120 4517 124 564514,000 110 2940 110 3043 110 3145 111 3412 114 3967 118 476713,000 104 2542 104 2625 104 2708 105 2925 108 3375 112 402512,000 103 2387 103 2462 103 2537 103 2727 105 3117 109 372011,000 103 2296 103 2368 103 2439 103 2592 103 2892 107 339110,000 103 2221 103 2293 103 2364 103 2493 103 2733 105 3095

WEIGHT — LB10,000 11,000 12,000 13,000 14,000 15,000 16,000 17,000 18,000 18,300

125 125 125 125 125 130 134 138 142 143

124 124 124 124 128 133 137 141 145 146

TEMP

SEA

LEV

EL10

00 F

T20

00 F

T

VR

V2


ALL

EFFECTIVITY

b

TAKEOFF SPEEDS AND DISTANCESFLAPS — 8°


°F 0 20 40 60 80 100°C -18 -7 4 16 27 38

WT V1 Dist V1 Dist V1 Dist V1 Dist V1 Dist V1 Dist18,300 136 5254 136 5465 136 5711 137 6461 140 811018,000 134 5076 134 5278 134 5513 136 6225 139 778017,000 129 4482 129 4656 129 4850 130 5438 133 668016,000 123 3964 123 4117 123 4271 124 4729 127 5678 132 782715,000 116 3463 116 3587 116 3726 118 4150 121 4970 126 629814,000 110 3065 110 3184 110 3303 112 3659 115 4305 120 521413,000 104 2643 104 2740 104 2836 106 3125 109 3650 113 438812,000 103 2478 103 2566 103 2650 104 2900 106 3368 110 401011,000 103 2383 103 2466 103 2532 103 2725 104 3094 108 367810,000 103 2308 103 2391 103 2446 103 2600 103 2883 106 338518,300 136 5476 136 5758 136 6043 138 6981 142 934818,000 135 5289 135 5557 135 5828 136 6718 140 893517,000 129 4665 129 4887 129 5110 131 5844 135 756016,000 123 4125 123 4299 123 4474 125 5047 129 6324 134 906915,000 117 3593 117 3753 117 3914 119 4443 123 5465 128 696314,000 110 3190 110 3325 110 3460 113 3905 117 4644 122 566013,000 105 2745 105 2854 105 2964 107 3325 110 3925 114 475012,000 103 2570 103 2665 103 2760 104 3073 107 3629 112 431611,000 103 2470 103 2545 103 2618 103 2858 106 3311 110 396510,000 103 2395 103 2456 103 2514 103 2707 104 3034 108 365018,300 136 5846 136 6155 137 6509 138 771618,000 135 5640 135 5934 135 6270 137 741317,000 129 4956 129 5197 129 5475 132 6400 136 903516,000 123 4353 123 4542 123 4759 126 5472 130 731315,000 117 3802 117 3977 117 4177 120 4813 124 6028 129 783914,000 111 3367 111 3513 111 3681 114 4198 118 5029 122 616813,000 105 2888 105 3007 105 3143 108 3563 111 4238 115 516312,000 103 2695 103 2798 103 2916 104 3284 108 3890 113 467111,000 103 2567 103 2646 103 2737 103 3024 107 3559 110 429110,000 103 2474 103 2537 103 2610 103 2834 104 3265 109 3939

WEIGHT — LB10,000 11,000 12,000 13,000 14,000 15,000 16,000 17,000 18,000 18,300

125 125 125 125 125 130 134 138 142 143

124 124 124 124 128 133 137 141 145 146

TEMP

3000

FT

4000

FT

5000

FT

VR

V2

CL-102B

P-10 April 2001ALL

EFFECTIVITY



°F 0 20 40 60 80 100°C -18 -7 4 16 27 38

WT V1 Dist V1 Dist V1 Dist V1 Dist V1 Dist V1 Dist18,300 137 6218 137 6551 137 6975 140 878518,000 135 5994 135 6310 135 6713 138 841017,000 129 5247 129 5508 130 5840 133 7160 137 1058016,000 123 4581 123 4784 124 5043 127 6030 131 838415,000 117 4013 117 4201 118 4440 121 5240 125 6593 129 883114,000 111 3543 111 3701 112 3902 115 4490 119 5414 123 667613,000 105 3031 105 3160 106 3323 109 3800 112 4550 116 557512,000 103 2819 103 2930 104 3071 106 3510 109 4143 113 502711,000 103 2663 103 2748 103 2857 104 3213 108 3806 111 461810,000 103 2550 103 2618 103 2705 103 2965 106 3510 109 422818,300 137 6533 137 6878 138 7655 141 1037418,000 135 6294 135 6621 136 7355 140 990017,000 130 5494 130 5764 131 6356 134 832016,000 124 4774 124 4984 125 5440 128 6843 133 966815,000 117 4191 117 4385 119 4788 122 5780 127 728614,000 111 3693 111 3856 113 4181 116 4860 120 587613,000 105 3153 105 3285 107 3549 110 4100 113 492512,000 104 2924 104 3039 104 3271 107 3780 111 446711,000 103 2744 103 2832 103 3014 105 3450 109 410310,000 103 2615 103 2686 103 2827 104 3155 107 377318,300 137 6849 137 7205 138 867318,000 135 6593 135 6931 137 830517,000 130 5741 130 6020 132 7080 135 988016,000 124 4966 124 5184 126 5971 129 7870 134 1124515,000 118 4369 118 4570 120 5195 123 6320 128 819014,000 112 3842 112 4011 114 4459 117 5229 122 633813,000 106 3274 106 3411 108 3775 111 4400 114 530012,000 104 3029 104 3148 104 3486 108 4020 112 479011,000 103 2824 103 2916 103 3193 106 3688 110 440010,000 103 2680 103 2753 103 2951 104 3395 108 4035

WEIGHT — LB10,000 11,000 12,000 13,000 14,000 15,000 16,000 17,000 18,000 18,300

125 125 125 125 125 130 134 138 142 143

124 124 124 124 128 133 137 141 145 146

TEMP

6000

FT

7000

FT

8000

FT

VR

V2

CL-102B April 2001 P-11

ALL

EFFECTIVITY

b



°F 0 20 40 60 80 100°C -18 -7 4 16 27 38

WT V1 Dist V1 Dist V1 Dist V1 Dist V1 Dist V1 Dist18,300 137 7252 138 8248 140 1054618,000 136 6976 136 7909 139 1006317,000 130 6056 131 6778 133 8450 136 1161516,000 124 5213 125 5750 127 6928 131 936815,000 118 4596 119 5025 121 5825 125 7124 129 938114,000 112 4034 113 4343 115 4890 119 5768 123 706413,000 106 3429 107 3681 109 4125 112 4838 116 588912,000 104 3164 104 3397 106 3800 109 4391 113 529811,000 103 2928 103 3118 104 3470 107 4034 111 486710,000 103 2762 103 2899 103 3175 105 3711 109 444818,300 137 7815 139 946018,000 136 7505 138 904017,000 130 6470 132 7640 135 1027016,000 124 5524 127 6383 129 8127 133 1113515,000 118 4852 120 5510 123 6455 126 812614,000 112 4225 114 4675 117 5322 120 6307 124 771513,000 106 3585 108 3950 110 4475 113 5275 117 647912,000 104 3305 105 3653 107 4080 111 4768 114 580711,000 103 3042 104 3331 106 3747 108 4380 112 533310,000 103 2846 103 3048 104 3455 107 4018 110 4860

WEIGHT — LB10,000 11,000 12,000 13,000 14,000 15,000 16,000 17,000 18,000 18,300

125 125 125 125 125 130 134 138 142 143

124 124 124 124 128 133 137 141 145 146

TEMP

9000

FT

1000

0 FT

VR

V2

CL-102B

P-12 April 2001ALL

EFFECTIVITY

CREW NOTES

CL-102B April 2001 P-13

ALL

EFFECTIVITY

b

TAKEOFF WEIGHT LIMITSFLAPS — 20°

These data were determined for dry runway, zero wind, zero runwaygradient, anti-ice off, & anti-skid on.DO NOT EXCEED MAXIMUM CERTIFIED TAKEOFF WEIGHT

PRESSUREALTITUDE

(FEET)

TEMPERATURE°F 0 20 40 60 80 100°C -18 -7 4 16 27 38

10000 18300 17850 16150 14500 12850

9000 18300 16900 15100 13350

8000 17700 15900 14050

7000 18300 16450 14600

6000 17050 15150 13200

5000 17700 15700 13700

4000 18300 16300 14200

3000 16850 14700

2000 17500 15250

1000 18100 15800

S.L. 18300 16350

TAK

EOFF

— F

LAPS

20

°

CL-102B

P-14 April 2001ALL

EFFECTIVITY



°F 0 20 40 60 80 100°C -18 -7 4 16 27 38

WT V1 Dist V1 Dist V1 Dist V1 Dist V1 Dist V1 Dist18,300 131 4509 131 4680 131 4850 131 5021 133 556018,000 129 4361 129 4528 129 4696 129 4864 131 537517,000 123 3866 123 4024 123 4182 123 4340 124 475816,000 117 3396 117 3531 117 3667 117 3802 118 4161 125 508415,000 111 2964 111 3084 111 3204 111 3324 112 3640 118 441014,000 106 2603 106 2704 106 2805 106 2907 107 3175 111 382613,000 104 2431 104 2521 104 2612 104 2702 105 2942 110 352312,000 103 2288 103 2370 103 2452 103 2534 104 2750 108 327511,000 103 2218 103 2289 103 2361 103 2432 103 2621 106 308010,000 103 2115 103 2185 103 2255 103 2325 103 2511 104 291818,300 131 4676 131 4853 131 5029 131 530518,000 129 4525 129 4698 129 4871 129 5136 133 590617,000 123 4021 123 4184 123 4347 123 4573 126 520116,000 117 3529 117 3669 117 3808 117 4002 120 451315,000 111 3082 111 3205 111 3329 111 3500 114 3952 120 483114,000 106 2702 106 2807 106 2911 106 3056 108 3439 113 418313,000 104 2520 104 2613 104 2706 104 2836 106 3177 111 384112,000 103 2369 103 2453 103 2537 103 2654 105 2963 109 356311,000 103 2288 103 2362 103 2435 103 2537 103 2807 107 333110,000 103 2184 103 2256 103 2328 103 2429 103 2693 105 311318,300 131 4844 131 5026 131 5220 131 562718,000 129 4690 129 4868 129 5057 129 543817,000 123 4176 123 4344 123 4512 123 4807 128 568816,000 117 3662 117 3806 117 3950 117 4202 122 489915,000 111 3199 111 3327 111 3454 111 3677 115 4263 123 525214,000 106 2802 106 2909 106 3017 106 3206 109 3702 114 453913,000 104 2608 104 2705 104 2801 104 2969 108 3412 113 415912,000 103 2449 103 2536 103 2623 103 2775 106 3175 111 385011,000 103 2358 103 2434 103 2510 103 2643 104 2992 108 358210,000 103 2253 103 2327 103 2402 103 2532 103 2848 106 3285

WEIGHT — LB10,000 11,000 12,000 13,000 14,000 15,000 16,000 17,000 18,000 18,300

125 125 125 125 125 127 130 133 136 137

124 124 123 123 123 126 130 134 138 139

TEMP

SEA

LEV

EL10

00 F

T20

00 F

T

VR

V2

TAK

EOFF

— F

LAPS

20

°

CL-102B April 2001 P-15

ALL

EFFECTIVITY

b



°F 0 20 40 60 80 100°C -18 -7 4 16 27 38

WT V1 Dist V1 Dist V1 Dist V1 Dist V1 Dist V1 Dist18,300 131 5035 131 5255 131 5510 133 608618,000 129 4878 129 5090 129 5328 131 587517,000 123 4354 123 4538 123 4722 125 517216,000 117 3814 117 3972 117 4130 118 4492 124 536115,000 111 3334 111 3473 111 3613 112 3933 117 462914,000 106 2915 106 3034 106 3152 107 3423 111 4012 116 505813,000 104 2710 104 2815 104 2921 105 3163 109 3689 114 453512,000 103 2541 103 2636 103 2731 104 2950 107 3425 112 417511,000 103 2438 103 2521 103 2605 103 2796 105 3211 109 386610,000 103 2331 103 2413 103 2495 103 2682 104 3023 107 351518,300 131 5246 131 5523 131 5799 135 669718,000 129 5081 129 5340 129 5599 133 643817,000 123 4531 123 4731 123 4932 127 557316,000 117 3966 117 4137 117 4309 120 4806 127 589415,000 111 3468 111 3620 111 3772 114 4190 119 499514,000 106 3029 106 3158 106 3286 108 3640 112 4322 118 567513,000 104 2811 104 2926 104 3041 107 3357 111 3965 115 492512,000 103 2632 103 2736 103 2840 105 3125 109 3675 113 450011,000 103 2518 103 2609 103 2699 103 2949 107 3429 111 415010,000 103 2410 103 2499 103 2588 103 2813 105 3180 109 377518,300 131 5579 131 5889 131 627918,000 129 5393 129 5683 129 605817,000 123 4772 123 4996 123 5325 128 616016,000 117 4172 117 4365 117 4606 122 528015,000 111 3651 111 3821 111 4031 115 4565 121 558614,000 106 3184 106 3328 106 3506 109 3958 113 473713,000 104 2949 104 3078 104 3237 108 3640 112 4333 117 541012,000 103 2757 103 2873 103 3017 106 3381 110 4006 114 490411,000 103 2627 103 2729 103 2854 104 3173 108 3719 112 450810,000 103 2517 103 2616 103 2737 103 2992 106 3380 110 4098

WEIGHT — LB10,000 11,000 12,000 13,000 14,000 15,000 16,000 17,000 18,000 18,300

125 125 125 125 125 127 130 133 136 137

124 124 123 123 123 126 130 134 138 139

TEMP

3000

FT

4000

FT

5000

FT

VR

V2

CL-102B

P-16 April 2001ALL

EFFECTIVITY



°F 0 20 40 60 80 100°C -18 -7 4 16 27 38

WT V1 Dist V1 Dist V1 Dist V1 Dist V1 Dist V1 Dist18,300 131 5911 131 6253 132 696218,000 129 5704 129 6035 130 667817,000 123 5015 123 5310 123 5730 130 674716,000 117 4379 117 4594 117 4933 123 580915,000 111 3833 111 4022 112 4290 116 4940 123 656514,000 106 3338 106 3498 106 3725 110 4276 115 536613,000 104 3087 104 3230 105 3433 109 3924 113 4730 119 589412,000 103 2882 103 3010 104 3194 107 3638 111 4338 115 530811,000 103 2736 103 2848 103 3009 105 3396 109 4008 113 486710,000 103 2624 103 2732 103 2861 104 3158 107 3645 111 442118,300 131 6212 131 6716 134 769918,000 129 5998 129 6455 132 734517,000 123 5285 123 5585 126 616716,000 117 4574 117 4816 119 5286 125 642015,000 111 4006 111 4197 113 4570 118 534014,000 106 3484 106 3646 108 3962 111 4609 116 602413,000 104 3217 104 3362 106 3644 110 4221 114 515812,000 103 2999 103 3130 105 3384 108 3906 112 469411,000 103 2839 103 2953 103 3175 106 3631 110 432210,000 103 2724 103 2816 103 2994 104 3319 108 393018,300 132 6665 132 718018,000 130 6408 130 687517,000 123 5554 123 5859 128 660416,000 117 4791 117 5038 121 566915,000 112 4178 112 4373 115 4849 119 600014,000 106 3630 106 3795 109 4198 112 5058 118 682213,000 105 3347 105 3495 107 3855 111 4535 116 558512,000 104 3117 104 3250 106 3575 109 4175 113 505011,000 103 2941 103 3058 104 3342 107 3866 111 463810,000 103 2807 103 2900 103 3120 105 3515 109 4215

WEIGHT — LB10,000 11,000 12,000 13,000 14,000 15,000 16,000 17,000 18,000 18,300

125 125 125 125 125 127 130 133 136 137

124 124 123 123 123 126 130 134 138 139

TEMP

6000

FT

7000

FT

8000

FT

VR

V2

CL-102B April 2001 P-17

ALL

EFFECTIVITY

b



°F 0 20 40 60 80 100°C -18 -7 4 16 27 38

WT V1 Dist V1 Dist V1 Dist V1 Dist V1 Dist V1 Dist18,300 132 7212 134 809718,000 130 6904 133 770617,000 124 5878 126 640416,000 118 5053 120 5477 124 643915,000 112 4385 114 4721 117 5356 122 743514,000 106 3805 108 4090 110 4617 114 583313,000 105 3504 106 3758 109 4228 112 5030 118 620012,000 104 3258 105 3488 107 3913 110 4588 115 555011,000 103 3065 103 3265 105 3637 108 4228 112 508210,000 103 2906 103 3066 104 3323 106 3845 110 461518,300 133 775918,000 131 740017,000 124 6203 129 694816,000 118 5315 122 6006 126 750015,000 112 4593 116 5069 119 626114,000 107 3981 109 4384 112 5200 116 667513,000 105 3661 108 4021 110 4625 114 552512,000 104 3400 106 3725 109 4250 112 5000 116 605011,000 103 3189 104 3473 106 3932 109 4594 114 552610,000 103 3005 103 3210 104 3575 107 4175 112 5011

WEIGHT — LB10,000 11,000 12,000 13,000 14,000 15,000 16,000 17,000 18,000 18,300

125 125 125 125 125 127 130 133 136 137

124 124 123 123 123 126 130 134 138 139

TEMP

9000

FT

1000

0 FT

VR

V2

CL-102B

P-18 April 2001ALL

EFFECTIVITY

MAXIMUM CONTINUOUS THRUST FOR CLIMB (N1)ALL ENGINE

XX.X ANTI-ICE OFF or NACELLE HEAT ONLYXX.X FULL ANTI-ICE ON

SPEED SCHEDULE• 250 KIAS to 32,000 ft.• .70 MI to 45,000 ft.

RAT ALTITUDE — 1000 FEET°C S.L. 5 10 15 20 25 30 35 40 45

45 91.2 91.6 92.188.0 88.6 89.1

40 92.4 92.8 93.189.1 89.6 90.1

35 93.5 93.8 94.1 94.490.2 90.7 91.1 91.5

30 94.4 94.7 94.9 95.191.2 91.7 92.0 92.4

25 95.3 95.5 95.6 95.7 95.692.1 92.5 92.8 93.1 93.4

20 95.6 96.1 96.2 96.3 96.292.8 93.2 93.4 93.7 93.9

15 94.8 96.6 96.7 96.7 96.6 96.692.5 93.8 94.0 94.2 94.4 94.4

10 93.9 97.1 97.1 97.1 97.0 97.0 96.691.6 94.2 94.4 94.6 94.7 94.7 94.6

5 93.0 96.5 97.4 97.4 97.3 97.3 97.0 96.390.7 94.5 94.8 94.9 95.0 95.0 94.8 94.3

0 92.2 95.7 97.6 97.6 97.5 97.5 97.3 96.6 94.789.8 93.6 95.1 95.2 95.2 95.2 95.0 94.6 93.4

-5 91.3 94.7 97.8 97.8 97.7 97.7 97.5 97.0 95.2 93.189.0 92.7 95.3 95.4 95.4 95.4 95.2 94.8 93.7 92.3

-10 90.4 93.8 97.5 97.9 97.9 97.8 97.8 97.2 95.6 93.788.1 91.8 95.5 95.5 95.5 95.5 95.3 95.0 94.1 92.8

-15 89.5 93.0 96.6 98.1 98.0 98.0 97.8 97.4 96.0 94.287.2 91.0 94.5 95.6 95.6 95.6 95.5 95.2 94.3 93.1

-20 88.6 92.1 95.7 98.3 98.2 98.2 98.0 97.7 96.4 94.786.3 90.0 93.6 95.7 95.7 95.7 95.6 95.3 94.5 93.4

-25 87.8 91.2 94.7 98.6 98.5 98.5 98.3 97.9 96.7 95.185.5 89.1 92.7 95.8 95.8 95.8 95.7 95.4 94.7 93.6

-30 87.0 90.3 93.8 98.4 98.8 98.8 98.6 98.3 97.1 95.584.6 88.2 91.8 95.7 95.9 95.9 95.8 95.5 94.9 93.8

-35 86.1 89.4 92.9 97.5 99.3 99.3 99.1 98.7 97.6 95.983.8 87.4 90.9 94.8 96.1 96.1 95.9 95.7 95.0 94.0

-40 85.2 88.5 91.9 96.5 99.8 99.8 99.6 99.3 98.1 96.483.0 86.5 90.0 94.0 96.3 96.3 96.2 95.9 95.2 94.2


CL-102B

P-18.1 April 2001ALL

EFFECTIVITY


XX.X ANTI-ICE OFF or NACELLE HEAT ONLYXX.X FULL ANTI-ICE ONSPEED SCHEDULE

• 250 KIAS to 32,000 ft.• .70 MI to 45,000 ft.


45 85.9 86.4 86.482.7 83.2 83.7

40 87.4 87.7 87.784.0 84.4 84.9

35 89.0 89.3 89.3 89.985.4 85.6 86.2 86.5

30 90.5 90.9 90.9 91.386.9 87.0 87.4 87.9

25 92.0 92.4 92.4 92.588.3 88.3 88.5 89.0

20 93.2 93.4 93.4 93.4 93.689.7 89.7 89.7 90.0 90.2

15 92.5 94.3 94.3 94.3 94.5 94.589.5 90.8 90.8 90.9 91.1 91.4

10 91.6 95.1 95.1 95.1 95.1 95.1 95.188.7 91.6 91.6 91.6 91.8 91.9 91.9

5 90.7 95.1 95.7 95.7 95.5 95.5 95.6 94.7 92.187.8 92.3 92.3 92.3 92.4 92.4 92.4 91.7 90.1

0 89.8 94.2 96.3 96.3 95.9 95.9 96.1 95.4 93.087.0 91.4 92.9 92.9 92.9 92.9 92.9 92.4 90.9

-5 88.9 93.3 96.7 96.7 96.3 96.3 96.5 96.0 93.8 91.486.1 90.5 93.3 93.3 93.3 93.3 93.3 92.9 91.6 89.7

-10 88.1 92.4 96.7 97.0 96.8 96.8 96.9 96.5 94.6 92.385.3 89.6 93.6 93.6 93.6 93.6 93.6 93.4 92.3 90.6

-15 87.2 91.5 95.8 97.4 97.4 97.4 97.2 96.8 95.3 93.284.4 88.7 92.8 93.9 93.9 93.9 93.9 93.8 92.8 91.4

-20 86.3 90.6 94.8 97.8 97.9 97.9 97.6 97.2 95.8 93.983.6 87.8 91.9 94.3 94.3 94.3 94.3 94.1 93.2 92.0

-25 85.5 89.7 93.0 98.2 98.8 98.8 98.5 98.0 96.8 95.182.8 86.9 91.0 94.6 94.6 94.6 94.6 94.4 93.6 92.5

-30 84.6 88.8 93.0 98.2 98.8 98.8 98.5 98.0 96.8 95.281.9 86.0 90.1 94.5 95.0 95.0 95.0 94.6 93.9 92.9

-35 83.8 87.9 92.0 97.3 99.3 99.3 99.0 98.5 97.3 95.781.1 85.2 89.2 93.8 95.3 95.3 95.3 94.7 94.1 93.2

-40 82.9 87.0 91.1 96.4 99.7 99.7 99.4 98.9 97.7 96.280.3 84.6 88.3 93.1 95.7 95.7 95.7 95.0 94.4 93.6


CL-102B

P-18.2 April 2001ALL

EFFECTIVITY


XX.X ANTI-ICE OFF or NACELLE HEAT ONLYXX.X FULL ANTI-ICE ONSPEED SCHEDULE

• 250 KIAS to 32,000 ft.• .70 MI to 45,000 ft.


45 88.5 88.8 89.285.1 85.6 86.1

40 90.2 90.5 91.086.4 86.9 87.4

35 91.8 92.0 92.3 92.787.8 88.2 88.8 89.3

30 93.2 93.4 93.5 93.789.2 89.6 90.0 90.4

25 94.3 94.4 94.5 94.5 94.490.5 90.8 91.1 91.4 91.4

20 95.2 95.3 95.3 95.3 95.191.6 91.8 92.0 92.2 92.1

15 94.4 95.9 96.0 95.9 95.7 95.491.6 92.6 92.8 92.9 92.7 92.6

10 93.5 96.4 96.4 96.3 96.0 95.7 95.490.7 93.2 93.3 93.5 93.3 93.1 92.7

5 92.5 96.3 96.7 96.6 96.4 96.1 95.8 94.989.8 93.8 93.9 93.9 93.7 93.5 93.2 92.3

0 91.6 95.4 97.1 97.0 96.7 96.5 96.2 95.588.9 92.9 94.1 94.1 94.0 93.8 93.5 92.9

-5 90.7 94.4 97.4 97.3 97.0 96.8 96.7 96.0 93.9 91.688.0 92.0 94.3 94.3 94.1 93.9 93.7 93.2 89.8 87.7

-10 89.8 93.5 97.5 97.7 97.4 97.3 97.1 96.5 94.7 92.587.2 91.1 94.5 94.5 94.3 94.1 93.9 93.5 90.7 88.7

-15 88.9 92.6 96.5 98.1 97.9 97.7 97.5 97.0 95.3 93.486.8 90.2 93.8 94.7 94.5 94.3 94.2 93.8 91.4 89.7

-20 88.0 91.6 95.5 98.6 98.4 98.3 98.1 97.5 95.9 94.185.4 89.3 92.9 94.9 94.7 94.6 94.5 94.2 92.0 90.4

-25 87.2 90.7 94.6 99.3 99.1 99.0 98.8 98.2 96.6 94.884.6 88.4 91.9 95.3 95.1 94.9 94.9 94.5 92.5 91.1

-30 86.3 89.8 93.6 99.5 99.7 99.6 99.4 98.9 97.4 95.583.7 87.5 91.0 95.6 95.5 95.4 95.3 95.0 92.9 91.7

-35 85.5 88.9 92.7 98.5 100.0 100.0 100.0 99.4 98.1 96.382.9 86.6 90.0 94.8 96.0 95.9 95.9 95.5 93.4 92.2

-40 84.6 88.1 91.8 97.5 100.0 100.0 100.0 100.0 98.7 97.182.1 85.7 89.1 93.9 96.6 96.6 96.5 96.1 94.0 92.8


CL-102B April 2001 P-19

ALL

EFFECTIVITY

b

CLI

MB

SPE

ED

: 25

0 K

IAS

up

to 3

2,00

0 fe

et.

0.70

MI a

bove

32,

000

feet

.

WEI

GH

TIS

A -1

0°C

ISA

IS

A +

10°C

ISA

+15

°CIS

A +

20°C

18,3

00 L

BTi

me

Dis

tFu

elTi

me

Dis

tFu

elTi

me

Dis

tFu

elTi

me

Dis

tFu

elTi

me

Dis

tFu

elM

in.

N.M

.Lb

Min

.N

.M.

LbM

in.

N.M

.Lb

Min

.N

.M.

LbM

in.

N.M

.Lb

PRESSURE ALTITUDE — 1000 FEET

45 43 4116

.598

.057

0.9

23.7

146.

271

8.6

3913

.980

.851

4.5

18.0

108.

660

8.0

27.5

172.

680

7.5

3712

.270

.047

5.3

15.5

91.3

551.

121

.413

0.9

685.

526

.816

7.4

802.

936

.923

7.1

1015

.135

11.0

62.2

444.

313

.880

.051

0.1

18.5

111.

062

0.6

22.4

137.

170

9.4

28.5

177.

784

2.4

3310

.055

.641

5.5

12.4

70.5

473.

316

.395

.756

6.7

19.3

115.

363

6.7

23.6

143.

673

4.5

318.

948

.338

2.6

10.9

60.5

431.

614

.080

.050

8.2

16.3

93.9

561.

119

.311

2.7

630.

629

8.0

42.2

352.

29.

652

.239

4.5

12.3

67.9

459.

514

.178

.750

2.9

16.4

92.9

558.

627

7.2

37.0

324.

68.

645

.436

1.7

10.8

58.5

418.

312

.367

.445

5.8

14.3

78.8

503.

125

6.4

32.5

298.

57.

639

.633

1.1

9.6

50.7

381.

110

.958

.141

4.1

12.6

67.7

455.

523

5.7

28.4

273.

26.

834

.430

1.9

8.5

43.9

346.

39.

650

.237

5.4

11.1

58.3

412.

021

5.1

24.8

248.

66.

029

.827

3.7

7.5

37.9

313.

08.

543

.333

8.8

9.7

50.2

371.

119

4.5

21.5

224.

35.

325

.724

6.2

6.5

32.6

280.

97.

437

.230

3.8

8.5

43.1

332.

417

3.9

18.5

200.

54.

621

.921

9.3

5.7

27.8

249.

86.

431

.727

0.0

7.4

36.7

295.

115

3.4

15.7

176.

93.

918

.519

2.9

4.9

23.5

219.

55.

526

.823

7.2

6.4

31.0

259.

113

2.9

13.1

153.

93.

315

.416

6.9

4.1

19.5

189.

74.

722

.320

5.0

5.4

25.8

223.

911

2.4

10.8

130.

42.

812

.614

1.1

3.4

15.9

160.

43.

918

.217

3.3

4.5

21.1

189.

29

2.0

8.6

107.

32.

29.

911

5.5

2.8

12.6

131.

43.

114

.414

2.0

3.6

16.7

154.

97

1.5

6.6

84.0

1.7

7.5

90.0

2.1

9.5

102.

42.

410

.911

0.7

2.8

12.6

120.

85

1.1

4.6

60.4

1.2

5.2

64.5

1.5

6.6

73.4

1.7

7.6

79.4

1.9

8.8

86.7

30.

62.

736

.60.

73.

038

.80.

93.

844

.21.

04.

447

.81.

25.

152

.41

0.2

0.9

12.4

0.2

1.0

13.0

0.3

1.2

14.8

0.3

1.4

16.0

0.4

1.7

17.6

CLIMB PERFORMANCETWO ENGINE

CL-102B

P-20 April 2001ALL

EFFECTIVITY

CLI

MB

SP

EE

D:

250

KIA

S u

p to

32,

000

feet

.0.

70 M

I abo

ve 3

2,00

0 fe

et.

WEI

GH

TIS

A -1

0°C

ISA

IS

A +

10°C

ISA

+15

°CIS

A +

20°C

18,0

00 L

BTi

me

Dis

tFu

elTi

me

Dis

tFu

elTi

me

Dis

tFu

elTi

me

Dis

tFu

elTi

me

Dis

tFu

elM

in.

N.M

.Lb

Min

.N

.M.

LbM

in.

N.M

.Lb

Min

.N

.M.

LbM

in.

N.M

.Lb


45 4322

.013

4.2

670.

341

15.9

94.0

552.

122

.113

6.3

682.

139

13.5

78.3

500.

617

.410

4.6

588.

825

.916

2.2

768.

837

11.9

68.1

463.

415

.088

.553

5.8

20.6

125.

966

2.5

25.6

159.

477

0.3

34.4

219.

795

4.8

3510

.860

.743

3.6

13.4

77.7

496.

817

.910

7.3

601.

921

.613

1.8

685.

127

.116

9.1

807.

233

9.8

54.2

405.

812

.068

.746

1.4

15.8

92.8

550.

818

.711

1.4

617.

122

.713

7.9

708.

631

8.7

47.2

373.

910

.659

.042

1.2

13.7

77.8

494.

815

.891

.154

5.4

18.6

109.

061

1.6

297.

841

.234

4.4

9.4

50.9

385.

311

.966

.144

7.9

13.7

76.6

489.

715

.990

.154

3.0

277.

036

.231

7.5

8.4

44.3

353.

410

.557

.040

8.1

12.0

65.6

444.

213

.976

.648

9.7

256.

331

.729

2.0

7.5

38.6

323.

79.

449

.437

2.1

10.6

56.7

403.

912

.265

.944

3.7

235.

627

.826

7.4

6.6

33.6

295.

38.

342

.833

8.2

9.4

49.0

366.

410

.856

.840

1.6

215.

024

.324

3.3

5.9

29.2

267.

77.

337

.030

5.8

8.3

42.3

330.

89.

548

.936

2.0

194.

421

.021

9.7

5.1

25.1

240.

96.

431

.827

4.5

7.2

36.3

296.

78.

342

.032

4.3

173.

818

.119

6.3

4.5

21.5

214.

65.

627

.224

4.2

6.3

31.0

263.

87.

235

.828

8.0

153.

315

.417

3.3

3.9

18.2

188.

84.

822

.921

4.6

5.4

26.2

231.

76.

230

.325

2.9

132.

812

.915

0.5

3.3

15.1

163.

44.

119

.118

5.6

4.6

21.8

200.

45.

325

.221

8.6

112.

410

.612

7.8

2.7

12.3

138.

23.

415

.615

6.9

3.8

17.8

169.

44.

420

.618

4.8

91.

98.

510

5.1

2.2

9.7

113.

12.

712

.312

8.5

3.1

14.1

138.

83.

516

.315

1.4

71.

56.

482

.31.

77.

388

.22.

19.

310

0.2

2.3

10.6

108.

32.

712

.311

8.0

51.

14.

559

.21.

25.

163

.21.

56.

471

.81.

77.

477

.61.

98.

684

.73

0.6

2.7

35.9

0.7

3.0

38.1

0.9

3.8

43.3

1.0

4.3

46.8

1.1

5.0

51.2

10.

20.

912

.10.

21.

012

.80.

31.

214

.50.

31.

415

.70.

41.

617

.2


CL-102B April 2001 P-21

ALL

EFFECTIVITY

b


CLI

MB

SP

EE

D:

250

KIA

S u

p to

32,

000

feet

.0.

70 M

I abo

ve 3

2,00

0 fe

et.

WEI

GH

TIS

A -1

0°C

ISA

IS

A +

10°C

ISA

+15

°CIS

A +

20°C

17,0

00 L

BTi

me

Dis

tFu

elTi

me

Dis

tFu

elTi

me

Dis

tFu

elTi

me

Dis

tFu

elTi

me

Dis

tFu

elM

in.

N.M

.Lb

Min

.N

.M.

LbM

in.

N.M

.Lb

Min

.N

.M.

LbM

in.

N.M

.Lb


45 4317

.410

4.7

561.

541

14.1

83.1

497.

518

.711

4.2

593.

839

12.2

70.9

457.

515

.693

.053

1.5

22.0

136.

566

8.1

28.6

181.

279

9.4

3710

.962

.242

5.9

13.6

80.0

488.

618

.311

1.2

594.

022

.213

7.4

678.

228

.317

9.1

806.

435

9.9

55.7

399.

712

.270

.845

5.1

16.1

96.2

544.

919

.211

6.3

613.

223

.514

5.3

708.

133

9.0

49.9

374.

911

.062

.842

4.0

14.3

83.9

501.

616

.899

.755

7.6

20.1

121.

463

2.4

318.

143

.634

6.1

9.8

54.2

388.

312

.570

.945

3.1

14.3

82.6

497.

016

.897

.955

3.4

297.

238

.131

9.2

8.7

46.9

355.

910

.960

.541

1.5

12.5

69.8

448.

214

.481

.749

4.5

276.

533

.529

4.6

7.7

40.9

326.

99.

752

.437

5.7

11.0

60.0

407.

712

.769

.844

7.6

255.

829

.527

1.2

6.9

35.7

299.

88.

645

.534

3.1

9.8

52.0

371.

411

.260

.240

6.6

235.

225

.824

8.5

6.1

31.2

273.

77.

639

.531

2.3

8.6

45.1

337.

49.

952

.136

8.6

214.

622

.522

6.3

5.4

27.0

248.

46.

734

.228

2.7

7.6

38.9

305.

08.

744

.933

2.8

194.

119

.620

4.4

4.8

23.3

223.

75.

929

.425

4.0

6.7

33.5

273.

97.

638

.629

8.5

173.

616

.818

2.8

4.2

20.0

199.

55.

225

.122

6.2

5.8

28.6

243.

86.

633

.026

5.5

153.

114

.316

1.4

3.6

16.9

175.

64.

421

.319

8.9

5.0

24.2

214.

35.

727

.923

3.3

132.

612

.014

0.2

3.0

14.1

152.

03.

817

.717

2.1

4.2

20.2

185.

44.

923

.320

1.8

112.

29.

911

9.1

2.5

11.5

128.

63.

114

.514

5.6

3.5

16.5

156.

94.

019

.017

0.8

91.

87.

998

.02.

09.

010

5.4

2.5

11.4

119.

42.

813

.112

8.6

3.2

15.1

139.

97

1.4

6.0

76.7

1.5

6.8

82.1

1.9

8.6

93.1

2.2

9.9

100.

42.

511

.410

9.2

51.

04.

255

.21.

14.

758

.91.

46.

066

.81.

56.

972

.01.

87.

978

.43

0.6

2.5

33.5

0.6

2.8

35.5

0.8

3.5

40.2

0.9

4.0

43.4

1.0

4.6

47.4

10.

20.

811

.30.

20.

911

.90.

31.

113

.50.

31.

314

.50.

31.

515

.9

CL-102B

P-22 April 2001ALL

EFFECTIVITY


CLI

MB

SP

EED

: 25

0 K

IAS

up

to 3

2,00

0 fe

et.

0.70

MI a

bove

32,

000

feet

.

WEI

GH

TIS

A -1

0°C

ISA

IS

A +

10°C

ISA

+15

°CIS

A +

20°C

16,0

00 L

BTi

me

Dis

tFu

elTi

me

Dis

tFu

elTi

me

Dis

tFu

elTi

me

Dis

tFu

elTi

me

Dis

tFu

elM

in.

N.M

.Lb

Min

.N

.M.

LbM

in.

N.M

.Lb

Min

.N

.M.

LbM

in.

N.M

.Lb


4520

.412

4.8

589.

543

14.9

89.3

495.

521

.013

0.2

610.

541

12.6

74.3

451.

116

.499

.252

8.5

24.7

155.

768

9.9

3911

.164

.341

8.3

14.0

83.3

481.

419

.211

8.1

591.

223

.814

9.4

684.

132

.621

0.8

854.

437

10.0

56.8

391.

112

.372

.444

5.7

16.4

99.0

534.

919

.512

0.2

603.

024

.215

1.6

700.

135

9.1

51.0

367.

911

.264

.441

6.7

14.6

86.5

494.

117

.110

3.4

551.

120

.612

6.8

627.

533

8.3

45.9

345.

710

.157

.438

9.3

13.0

75.9

456.

915

.189

.550

4.7

17.9

107.

756

7.0

317.

440

.231

9.7

9.0

49.7

357.

411

.464

.641

4.6

13.0

74.8

452.

815

.288

.250

1.4

296.

735

.229

5.3

8.0

43.1

328.

210

.055

.437

7.6

11.4

63.6

409.

913

.174

.145

0.4

276.

031

.027

2.8

7.1

37.7

301.

98.

948

.034

5.4

10.1

54.9

373.

711

.663

.640

8.9

255.

427

.325

1.3

6.4

33.0

277.

17.

941

.831

5.9

8.9

47.7

341.

010

.255

.037

2.1

234.

823

.923

0.5

5.7

28.8

253.

37.

036

.428

7.9

7.9

41.4

310.

39.

147

.733

8.0

214.

320

.921

0.0

5.0

25.0

230.

06.

231

.526

0.9

7.0

35.8

280.

88.

041

.230

5.5

193.

818

.118

9.8

4.4

21.6

207.

35.

527

.223

4.6

6.2

30.9

252.

57.

035

.527

4.4

173.

315

.616

9.8

3.9

18.5

184.

94.

823

.220

9.0

5.4

26.4

224.

96.

130

.324

4.2

152.

913

.315

0.0

3.3

15.6

162.

94.

119

.718

4.0

4.6

22.3

197.

95.

325

.721

4.8

132.

511

.213

0.3

2.8

13.0

141.

13.

516

.415

9.3

3.9

18.6

171.

34.

521

.418

6.0

112.

19.

211

0.8

2.3

10.6

119.

42.

913

.413

4.9

3.3

15.2

145.

03.

717

.515

7.5

91.

77.

391

.11.

98.

497

.92.

310

.611

0.6

2.6

12.1

118.

93.

013

.912

9.1

71.

35.

671

.41.

46.

376

.31.

88.

086

.32.

09.

192

.82.

310

.510

0.8

50.

93.

951

.41.

04.

454

.71.

35.

661

.91.

46.

366

.61.

67.

372

.43

0.6

2.3

31.1

0.6

2.6

33.0

0.7

3.2

37.3

0.8

3.7

40.2

1.0

4.3

43.8

10.

20.

810

.50.

20.

811

.10.

21.

112

.50.

31.

213

.50.

31.

414

.7

CL-102B April 2001 P-23

ALL

EFFECTIVITY

b


CLI

MB

SP

EED

: 25

0 K

IAS

up

to 3

2,00

0 fe

et.

0.70

MI a

bove

32,

000

feet

.

WEI

GH

TIS

A -1

0°C

ISA

IS

A +

10°C

ISA

+15

°CIS

A +

20°C

15,0

00 L

BTi

me

Dis

tFu

elTi

me

Dis

tFu

elTi

me

Dis

tFu

elTi

me

Dis

tFu

elTi

me

Dis

tFu

elM

in.

N.M

.Lb

Min

.N

.M.

LbM

in.

N.M

.Lb

Min

.N

.M.

LbM

in.

N.M

.Lb


4516

.297

.949

6.0

4313

.278

.344

4.0

17.5

107.

952

8.2

4111

.466

.740

9.7

14.5

87.5

474.

020

.612

8.7

593.

427

.117

3.5

712.

639

10.1

58.3

382.

212

.674

.843

6.5

16.9

103.

752

7.3

20.4

127.

659

8.9

26.2

167.

071

0.2

379.

151

.835

8.5

11.2

65.6

406.

314

.788

.448

2.5

17.3

106.

053

8.8

21.0

130.

961

5.5

358.

346

.733

8.0

10.2

58.6

381.

013

.177

.844

8.0

15.3

92.2

496.

218

.211

1.5

559.

033

7.6

42.1

318.

09.

252

.435

6.7

11.8

68.7

415.

913

.680

.445

6.9

16.0

95.8

509.

431

6.9

36.9

294.

68.

245

.532

8.2

10.4

58.8

378.

811

.867

.841

2.2

13.7

79.4

454.

229

6.2

32.4

272.

47.

339

.630

1.9

9.2

50.6

345.

810

.457

.937

4.4

11.9

67.2

409.

827

5.5

28.6

251.

96.

634

.727

8.0

8.2

44.0

316.

99.

250

.134

2.0

10.5

57.9

373.

025

5.0

25.2

232.

25.

930

.425

5.5

7.3

38.4

290.

28.

243

.631

2.6

9.3

50.2

340.

123

4.5

22.1

213.

15.

226

.523

3.7

6.5

33.4

264.

77.

337

.928

4.7

8.3

43.6

309.

321

4.0

19.3

194.

34.

623

.121

2.4

5.7

29.0

240.

16.

432

.925

8.0

7.3

37.7

280.

019

3.5

16.8

175.

74.

119

.919

1.5

5.0

25.0

216.

25.

728

.423

2.1

6.4

32.5

251.

717

3.1

14.5

157.

23.

617

.117

1.0

4.4

21.4

192.

74.

924

.320

6.9

5.6

27.8

224.

215

2.7

12.3

139.

03.

114

.515

0.7

3.8

18.1

169.

74.

320

.618

2.2

4.8

23.6

197.

413

2.3

10.3

120.

82.

612

.113

0.6

3.2

15.1

147.

03.

617

.215

7.8

4.1

19.7

171.

011

1.9

8.5

102.

72.

29.

811

0.6

2.7

12.4

124.

53.

014

.013

3.7

3.4

16.1

144.

89

1.5

6.8

84.5

1.7

7.8

90.7

2.1

9.8

102.

12.

411

.110

9.7

2.8

12.8

118.

87

1.2

5.2

66.2

1.3

5.9

70.7

1.6

7.4

79.7

1.9

8.4

85.7

2.1

9.7

92.8

50.

93.

647

.70.

94.

150

.71.

25.

157

.21.

35.

961

.51

56.

766

.73

0.5

2.2

28.9

0.6

2.4

30.6

0.7

3.0

34.5

0.8

3.4

37.1

0.9

4.0

40.3

10.

20.

79.

80.

20.

810

.30.

21.

011

.60.

31.

112

.40.

31.

313

.5

CL-102B

P-24 April 2001ALL

EFFECTIVITY


CLI

MB

SP

EE

D:

250

KIA

S u

p to

32,

000

feet

.0.

70 M

I abo

ve 3

2,00

0 fe

et.

WEI

GH

TIS

A -1

0°C

ISA

IS

A +

10°C

ISA

+15

°CIS

A +

20°C

14,0

00 L

BTi

me

Dis

tFu

elTi

me

Dis

tFu

elTi

me

Dis

tFu

elTi

me

Dis

tFu

elTi

me

Dis

tFu

elM

in.

N.M

.Lb

Min

.N

.M.

LbM

in.

N.M

.Lb

Min

.N

.M.

LbM

in.

N.M

.Lb


4513

.883

.143

6.4

19.4

120.

953

3.5

4311

.769

.439

9.7

15.2

92.8

466.

623

.014

6.7

607.

041

10.3

60.0

372.

012

.977

.642

6.4

17.7

110.

152

0.9

22.0

139.

960

1.8

30.8

201.

175

5.4

399.

252

.934

8.6

11.3

67.2

395.

615

.091

.647

1.9

17.8

110.

852

9.4

22.1

139.

761

1.8

378.

347

.232

7.8

10.2

59.3

369.

713

.279

.143

5.2

15.4

93.9

482.

418

.411

4.1

544.

735

7.6

42.6

309.

59.

253

.234

7.5

11.9

70.0

405.

713

.782

.344

6.7

16.2

98.5

499.

233

7.0

38.5

291.

78.

447

.732

6.0

10.7

62.1

377.

912

.372

.341

3.3

14.3

85.5

457.

931

6.3

33.9

270.

67.

541

.630

0.6

9.4

53.4

345.

310

.761

.437

4.6

12.4

71.5

411.

029

5.7

29.8

250.

56.

736

.327

6.9

8.4

46.1

316.

09.

552

.634

1.2

10.8

60.8

372.

227

5.1

26.3

231.

86.

031

.825

5.3

7.5

40.2

290.

08.

445

.731

2.2

9.6

52.6

339.

625

4.6

23.2

213.

95.

427

.923

4.8

6.7

35.1

265.

97.

539

.828

5.7

8.5

45.7

310.

123

4.1

20.4

196.

34.

824

.421

4.9

5.9

30.6

242.

76.

734

.726

0.6

7.6

39.7

282.

421

3.7

17.8

179.

14.

321

.219

5.5

5.2

26.6

220.

45.

930

.123

6.3

6.7

34.5

255.

919

3.2

15.5

162.

03.

818

.417

6.4

4.6

23.0

198.

55.

226

.021

2.8

5.9

29.7

230.

217

2.8

13.3

145.

13.

315

.715

7.5

4.0

19.7

177.

14.

522

.318

9.8

5.1

25.5

205.

315

2.5

11.4

128.

32.

813

.313

8.9

3.5

16.7

156.

03.

918

.916

7.2

4.4

21.6

180.

813

2.1

9.5

111.

52.

411

.112

0.4

3.0

13.9

135.

33.

315

.814

4.9

3.8

18.1

156.

711

1.8

7.9

94.8

2.0

9.1

102.

02.

511

.411

4.6

2.8

12.9

122.

83.

114

.813

2.8

91.

46.

378

.11.

67.

283

.72.

09.

094

.02.

210

.210

0.8

2.5

11.7

109.

07

1.1

4.8

61.2

1.2

5.4

65.3

1.5

6.8

73.4

1.7

7.7

78.8

1.9

8.9

85.1

50.

83.

444

.10.

93.

846

.81.

14.

752

.71.

25.

456

.61.

46.

261

.23

0.5

2.0

26.7

0.5

2.2

28.3

0.6

2.8

31.8

0.7

3.2

34.2

0.8

3.6

37.0

10.

20.

79.

00.

20.

79.

50.

20.

910

.70.

21.

011

.40.

31.

212

.4

CL-102B April 2001 P-25

ALL

EFFECTIVITY

b


CLI

MB

SP

EE

D:

250

KIAS

up

to 3

2,00

0 fe

et.

0.70

MI a

bove

32,

000

feet

.

WEI

GH

TIS

A -1

0°C

ISA

IS

A +

10°C

ISA

+15

°CIS

A +

20°C

13,0

00 L

BTi

me

Dis

tFu

elTi

me

Dis

tFu

elTi

me

Dis

tFu

elTi

me

Dis

tFu

elTi

me

Dis

tFu

elM

in.

N.M

.Lb

Min

.N

.M.

LbM

in.

N.M

.Lb

Min

.N

.M.

LbM

in.

N.M

.Lb


4512

.172

.438

8.4

16.1

99.6

459.

743

10.5

61.7

360.

113

.381

.041

5.2

18.9

119.

451

7.1

25.1

162.

362

0.6

419.

354

.033

7.1

11.5

69.1

383.

515

.495

.646

0.9

18.7

117.

952

2.0

24.1

155.

061

7.8

398.

347

.831

6.9

10.2

60.4

357.

813

.381

.142

2.6

15.7

96.9

469.

819

.011

9.4

534.

437

7.6

42.8

298.

79.

253

.633

5.5

11.8

70.7

392.

013

.783

.343

1.9

16.2

100.

048

3.4

356.

938

.828

2.5

8.4

48.2

316.

010

.763

.036

6.7

12.3

73.5

401.

814

.487

.244

6.0

336.

435

.126

6.6

7.7

43.3

296.

99.

756

.134

2.5

11.1

64.9

373.

212

.876

.341

1.4

315.

730

.924

7.6

6.9

37.9

274.

38.

648

.431

3.8

9.7

55.4

339.

511

.164

.337

1.2

295.

227

.222

9.4

6.1

33.1

253.

07.

641

.928

7.7

8.6

47.7

309.

99.

855

.033

7.2

274.

724

.121

2.4

5.5

29.0

233.

56.

836

.626

4.4

7.6

41.5

284.

18.

747

.630

8.2

254.

221

.219

6.1

4.9

25.5

214.

96.

132

.024

2.6

6.8

36.2

260.

37.

741

.528

1.8

233.

818

.718

0.1

4.4

22.3

196.

85.

427

.922

1.7

6.1

31.6

237.

66.

936

.125

6.9

213.

416

.316

4.4

3.9

19.4

179.

14.

824

.320

1.4

5.4

27.4

215.

76.

131

.323

3.0

193.

014

.214

8.8

3.4

16.8

161.

74.

221

.018

1.6

4.7

23.7

194.

35.

427

.120

9.8

172.

612

.213

3.3

3.0

14.4

144.

53.

718

.016

2.1

4.1

20.3

173.

54.

723

.218

7.2

152.

310

.411

7.9

2.6

12.2

127.

53.

215

.314

2.9

3.6

17.3

152.

94.

019

.716

5.0

131.

98.

810

2.5

2.2

10.2

110.

52.

712

.712

3.9

3.0

14.4

132.

63.

416

.514

3.1

111.

67.

287

.21.

88.

393

.72.

210

.410

5.0

2.5

11.8

112.

42.

913

.512

1.3

91.

35.

871

.81.

56.

676

.91.

88.

386

.22.

09.

492

.32.

310

.799

.67

1.0

4.4

56.2

1.1

5.0

60.0

1.4

6.2

67.3

1.6

7.1

72.1

1.8

8.1

77.8

50.

73.

140

.50

83.

543

.11.

04

348

.41.

14.

951

.81.

35.

756

.03

0.4

1.8

24.6

0.5

2.0

26.0

0.6

2.5

29.2

0.7

2.9

31.3

0.7

3.3

33.9

10.

10.

68.

30.

20.

78.

70.

20.

89.

80.

20.

910

.50.

21.

111

.4

CL-102B

P-26 April 2001ALL

EFFECTIVITY


CLI

MB

SP

EE

D:

250

KIAS

up

to 3

2,00

0 fe

et.

0.70

MI a

bove

32,

000

feet

.

WEI

GH

TIS

A -1

0°C

ISA

IS

A +

10°C

ISA

+15

°CIS

A +

20°C

12,0

00 L

BTi

me

Dis

tFu

elTi

me

Dis

tFu

elTi

me

Dis

tFu

elTi

me

Dis

tFu

elTi

me

Dis

tFu

elM

in.

N.M

.Lb

Min

.N

.M.

LbM

in.

N.M

.Lb

Min

.N

.M.

LbM

in.

N.M

.Lb


4510

.663

.534

6.6

13.8

84.9

402.

920

.913

3.7

518.

9.

439.

355

.032

3.9

11.7

71.1

370.

016

.110

0.9

449.

820

.112

8.6

518.

427

.618

0.7

638.

041

8.3

48.4

304.

410

.361

.434

4.4

13.6

83.6

408.

816

.110

1.1

457.

320

.012

7.7

526.

839

7.5

43.1

287.

19.

254

.132

2.7

11.8

71.9

378.

013

.885

.141

7.3

16.5

103.

246

9.3

376.

838

.727

1.1

8.3

48.2

303.

310

.663

.135

2.2

12.2

73.8

386.

114

.387

.942

9.1

356.

335

.225

6.7

7.6

43.5

286.

29.

656

.533

0.4

11.0

65.6

360.

612

.877

.339

8.2

335.

831

.824

2.5

6.9

39.2

269.

48.

750

.430

9.3

9.9

58.2

335.

911

.568

.036

8.8

315.

228

.122

5.5

6.2

34.3

249.

27.

743

.728

4.1

8.7

49.9

306.

510

.057

.733

4.2

294.

724

.820

9.1

5.6

30.0

230.

16.

937

.926

0.9

7.7

43.1

280.

48.

849

.530

4.3

274.

321

.919

3.7

5.0

26.4

212.

56.

233

.224

0.0

6.9

37.5

257.

47.

843

.027

8.6

253.

819

.417

9.0

4.5

23.2

195.

85.

529

.022

0.4

6.2

32.8

236.

17.

037

.525

5.1

233.

417

.016

4.5

4.0

20.3

179.

44.

925

.420

1.6

5.5

28.6

215.

76.

232

.723

2.8

213.

114

.915

0.1

3.6

17.7

163.

44.

422

.118

3.3

4.9

24.9

195.

95.

528

.421

1.3

192.

713

.013

5.9

3.1

15.3

147.

53.

819

.116

5.3

4.3

21.5

176.

74.

924

.619

0.4

172.

411

.212

1.8

2.7

13.2

131.

93.

416

.414

7.6

3.8

18.5

157.

84.

221

.117

0.0

152.

19.

510

7.8

2.4

11.2

116.

42.

913

.913

0.2

3.2

15.7

139.

23.

717

.914

9.9

131.

88.

093

.82.

09.

310

1.0

2.5

11.6

113.

02.

813

.112

0.7

3.1

15.0

130.

111

1.5

6.6

79.7

1.7

7.6

85.6

2.0

9.5

95.8

2.3

10.7

102.

42.

612

.311

0.3

91.

25.

365

.71.

36.

070

.31.

77.

578

.71.

98.

584

.12.

19.

890

.67

0.9

4.0

51.5

1.0

4.5

54.9

1.3

5.7

61.5

1.4

6.5

65.7

1.6

7.4

70.8

50.

72.

837

.10.

73.

239

.40.

94.

044

.11.

04.

547

.21.

15.

150

.93

0.4

1.7

22.5

0.4

1.8

23.8

0.5

2.3

26.6

0.6

2.6

28.5

0.7

3.0

30.8

10.

10.

67.

60.

10.

68.

00.

20.

88.

90.

20.

99.

60.

21.

010

.4

CL-102B April 2001 P-27

ALL

EFFECTIVITY

b

CLI

MB

SP

EE

D:

250

KIAS

up

to 3

2,00

0 fe

et.

0.70

MI a

bove

32,

000

feet

.

WEI

GH

TIS

A -1

0°C

ISA

IS

A +

10°C

ISA

+15

°CIS

A +

20°C

11,0

00 L

BTi

me

Dis

tFu

elTi

me

Dis

tFu

elTi

me

Dis

tFu

elTi

me

Dis

tFu

elTi

me

Dis

tFu

elM

in.

N.M

.Lb

Min

.N

.M.

LbM

in.

N.M

.Lb

Min

.N

.M.

LbM

in.

N.M

.Lb


459.

455

.930

8.9

11.9

73.2

354.

917

.010

7.8

439.

022

.514

5.9

522.

643

8.3

48.9

290.

310

.362

.532

9.3

13.9

86.5

394.

016

.810

6.8

445.

021

.413

8.7

520.

741

7.5

43.3

273.

89.

154

.630

8.2

11.9

73.2

362.

414

.087

.440

1.8

17.0

107.

745

5.5

396.

838

.725

8.7

8.2

48.3

289.

710

.563

.633

7.1

12.2

74.7

370.

214

.489

.641

2.9

376.

234

.924

4.8

7.4

43.2

273.

09.

456

.231

5.4

10.8

65.4

344.

312

.677

.338

0.6

355.

731

.723

2.0

6.8

39.1

258.

08.

650

.529

6.6

9.8

58.4

322.

611

.368

.435

4.7

335.

228

.821

9.4

6.3

35.3

243.

17.

845

.227

8.1

8.9

52.0

301.

310

.260

.532

9.6

314.

725

.420

4.2

5.6

31.0

225.

27.

039

.325

5.9

7.9

44.7

275.

69.

051

.629

9.6

294.

322

.418

9.5

5.0

27.1

208.

26.

234

.223

5.3

7.0

38.7

252.

57.

944

.427

3.4

273.

919

.917

5.7

4.5

23.9

192.

45.

629

.921

6.7

6.2

33.8

232.

17.

038

.625

0.7

253.

517

.616

2.4

4.1

21.0

177.

35.

026

.219

9.2

5.6

29.6

213.

16.

333

.722

9.8

233.

115

.514

9.3

3.6

18.4

162.

64.

422

.918

2.3

5.0

25.9

194.

85.

629

.420

9.9

212.

813

.513

6.3

3.2

16.1

148.

13.

920

.016

5.8

4.4

22.5

177.

15.

025

.619

0.6

192.

511

.812

3.5

2.9

13.9

133.

93.

517

.314

9.7

3.9

19.5

159.

84.

422

.217

1.9

172.

210

.211

0.7

2.5

11.9

119.

73.

014

.813

3.7

3.4

16.7

142.

73.

819

.015

3.6

151.

98.

798

.02.

210

.110

5.7

2.6

12.6

118.

02.

914

.212

6.0

3.3

16.2

135.

513

1.6

7.3

85.2

1.8

8.5

91.7

2.2

10.5

102.

42.

511

.910

9.3

2.8

13.5

117.

611

1.3

6.0

72.5

1.5

6.9

77.8

1.9

8.6

86.9

2.1

9.7

92.7

2.4

11.1

99.8

91.

14.

859

.71.

25.

563

.81.

56.

871

.31.

77.

776

.21.

98.

882

.07

0.8

3.7

46.8

0.9

4.1

49.9

1.2

5.2

55.8

1.3

5.9

59.6

1.5

6.7

64.1

50.

62.

633

.70.

72.

935

.80.

83.

640

.10.

94.

142

.81.

04.

746

.13

0.4

1.5

20.5

0.4

1.7

21.6

0.5

2.1

24.2

0.5

2.4

25.9

0.6

2.7

27.9

10.

10.

56.

90.

10.

57.

30.

20.

78.

10.

20.

88.

70.

20.

99.

4


CL-102B

P-28 April 2001ALL

EFFECTIVITY

CLI

MB

SP

EE

D:

250

KIA

S u

p to

32,

000

feet

.0.

70 M

I abo

ve 3

2,00

0 fe

et.

WEI

GH

TIS

A -1

0°C

ISA

IS

A +

10°C

ISA

+15

°CIS

A +

20°C

10,0

00 L

BTi

me

Dis

tFu

elTi

me

Dis

tFu

elTi

me

Dis

tFu

elTi

me

Dis

tFu

elTi

me

Dis

tFu

elM

in.

N.M

.Lb

Min

.N

.M.

LbM

in.

N.M

.Lb

Min

.N

.M.

LbM

in.

N.M

.Lb


458.

349

.027

4.3

10.4

63.4

312.

414

.290

.037

7.8

17.8

114.

443

3.3

24.4

161.

253

0.1

437.

443

.225

8.8

9.1

54.8

292.

012

.074

.634

5.2

14.3

90.3

385.

217

.511

3.0

440.

241

6.6

38.5

244.

88.

148

.227

4.4

10.4

64.0

320.

312

.275

.735

2.8

14.5

91.8

395.

639

6.0

34.6

231.

87.

342

.925

8.7

9.3

56.1

299.

410

.765

.532

7.3

12.5

77.9

362.

837

5.5

31.2

219.

66.

638

.524

4.3

8.4

49.8

281.

09.

657

.830

5.8

11.1

67.8

336.

535

5.1

28.4

208.

46.

134

.923

1.2

7.6

44.9

264.

78.

751

.728

7.2

10.0

60.4

314.

633

4.7

25.8

197.

25.

631

.621

8.1

7.0

40.3

248.

77.

946

.226

8.7

9.1

53.6

293.

131

4.3

22.9

183.

75.

027

.820

2.3

6.2

35.1

229.

27.

039

.924

6.4

8.0

45.9

267.

329

3.8

20.2

170.

64.

524

.418

7.1

5.6

30.6

211.

06.

234

.622

6.1

7.1

39.6

244.

327

3.5

17.9

158.

24.

121

.517

3.0

5.0

26.8

194.

55.

630

.320

8.0

6.3

34.5

224.

325

3.1

15.8

146.

33.

718

.915

9.6

4.5

23.5

178.

95.

026

.519

1.1

5.6

30.2

205.

823

2.8

13.9

134.

63.

316

.614

6.4

4.0

20.6

163.

84.

523

.217

4.8

5.0

26.4

188.

121

2.5

12.2

122.

92.

914

.513

3.4

3.5

17.9

149.

14.

020

.215

9.0

4.5

23.0

171.

019

2.2

10.6

111.

42.

612

.512

0.6

3.1

15.5

134.

63.

517

.514

3.5

3.9

19.9

154.

217

2.0

9.2

99.9

2.2

10.8

107.

92.

713

.312

0.3

3.1

15.0

128.

33.

417

.113

7.9

151.

77.

888

.41.

99.

195

.32.

411

.310

6.2

2.6

12.8

113.

33.

014

.512

1.7

131.

56.

676

.91.

67.

682

.72.

09.

592

.22.

210

.798

.32.

512

.210

5.7

111.

25.

465

.51.

46.

270

.21.

77.

878

.21.

98.

883

.52.

110

.089

.79

1.0

4.3

53.9

1.1

4.9

57.6

1.3

6.2

64.3

1.5

7.0

68.6

1.7

7.9

73.7

70.

83.

342

.30.

83.

745

.01.

04.

750

.31.

25.

353

.61.

36.

057

.65

0.5

2.3

30.5

0.6

2.6

32.3

0.7

3.2

36.1

0.8

3.7

38.6

0.9

4.2

41.5

30.

31.

418

.50.

41.

519

.50.

41.

921

.80.

52.

223

.30.

62.

525

.11

0.1

0.5

6.2

0.1

0.5

6.6

0.1

0.6

7.3

0.2

0.7

7.8

0.2

0.8

8.4


CL-102B April 2001

P-29Without Rosemount Pitot-Static System

EFFECTIVITY

b

LONG RANGE CRUISETWO ENGINE

NOTE: Shading denotes maximum specific range.

WEIGHT — 18,000 LB TEMPERATURE — °CISA -10 ISA ISA +10

Mach Ind

ALT

ITU

DE

— 1

000

FEET

45 KTASNM/LB

Mach Ind43 KTAS

NM/LBMach Ind .780

41 KTAS 427NM/LB .351

Mach Ind .760 .76039 KTAS 415 425

NM/LB .355 .347Mach Ind .732 .732 .732

37 KTAS 400 409 419NM/LB .353 .345 .337

Mach Ind .712 .712 .71235 KTAS 391 400 409

NM/LB .350 .341 .334

CL-102B April 2001


EFFECTIVITY




Mach IndA

LTIT

UD

E —

100

0 FE

ET

45 KTASNM/LB

Mach Ind43 KTAS

NM/LBMach Ind .774

41 KTAS 424NM/LB .362

Mach Ind .752 .75239 KTAS 412 421

NM/LB .365 .356Mach Ind .726 .726 .726

37 KTAS 397 406 416NM/LB .363 .354 .347

Mach Ind .705 .705 .70535 KTAS 388 396 406

NM/LB .359 .350 .342


Mach Ind

ALT

ITU

DE

— 1

000

FEET

45 KTASNM/LB

Mach Ind43 KTAS

NM/LBMach Ind .767

41 KTAS 420NM/LB .373

Mach Ind .742 .74239 KTAS 408 416

NM/LB .376 .365Mach Ind .719 .719 .719

37 KTAS 394 403 412NM/LB .373 .363 .355

Mach Ind .699 .699 .69935 KTAS 384 393 402

NM/LB .366 .358 .350

CL-102B April 2001


EFFECTIVITY

b




Mach Ind

ALT

ITU

DE

— 1

000

FEET

45 KTASNM/LB

Mach Ind43 KTAS

NM/LBMach Ind .760 .760

41 KTAS 417 426NM/LB .385 .374

Mach Ind .738 .738 .73839 KTAS 404 414 424

NM/LB .385 .376 .368Mach Ind .713 .713 .713

37 KTAS 390 399 410NM/LB .382 .373 .366

Mach Ind .692 .692 .69235 KTAS 381 389 400

NM/LB .378 .369 .363


Mach Ind

ALT

ITU

DE

— 1

000

FEET

45 KTASNM/LB

Mach Ind .78043 KTAS 428

NM/LB .394Mach Ind .752 .752

41 KTAS 413 423NM/LB .396 .387

Mach Ind .731 .731 .73139 KTAS 401 410 420

NM/LB .397 .387 .378Mach Ind .706 .706 .706

37 KTAS 387 396 406NM/LB .395 .384 .376

Mach Ind .685 .685 .68535 KTAS 378 386 395

NM/LB .389 .379 .371

CL-102B April 2001


EFFECTIVITY




Mach Ind

ALT

ITU

DE

— 1

000

FEET

45 KTASNM/LB


NM/LB .410Mach Ind .746 .746

41 KTAS 410 420NM/LB .410 .399

Mach Ind .724 .724 .72439 KTAS 397 406 416

NM/LB .409 .399 .391Mach Ind .700 .700 .700

37 KTAS 384 392 402NM/LB .406 .395 .387

Mach Ind .680 .680 .68035 KTAS 374 382 392

NM/LB .400 .390 .382


Mach Ind

ALT

ITU

DE

— 1

000

FEET

45 KTASNM/LB


NM/LB .423Mach Ind .738 .738 .738

41 KTAS 406 415 424NM/LB .423 .413 .402

Mach Ind .717 .717 .71739 KTAS 393 403 412

NM/LB .422 .412 .403Mach Ind .693 .693 .693

37 KTAS 380 389 399NM/LB .418 .407 .399

Mach Ind .671 .671 .67135 KTAS 371 378 389

NM/LB .410 .399 .393

CL-102B April 2001


EFFECTIVITY

b




Mach Ind

ALT

ITU

DE

— 1

000

FEET

45 KTASNM/LB

Mach Ind .754 .75443 KTAS 415 424

NM/LB .441 .428Mach Ind .732 .732 .732

41 KTAS 402 412 422NM/LB .437 .427 .417

Mach Ind .710 .710 .71039 KTAS 390 399 409

NM/LB .436 .424 .414Mach Ind .686 .686 .686

37 KTAS 376 385 395NM/LB .428 .418 .409

Mach Ind .666 .666 .66635 KTAS 368 375 385

NM/LB .422 .410 .403


Mach Ind .770

ALT

ITU

DE

— 1

000

FEET

45 KTAS 424NM/LB .453

Mach Ind .745 .74543 KTAS 411 420

NM/LB .457 .444Mach Ind .723 .723 .723

41 KTAS 398 407 417NM/LB .452 .441 .430

Mach Ind .701 .701 .70139 KTAS 385 394 404

NM/LB .449 .438 .430Mach Ind .678 .678 .678

37 KTAS 373 381 391NM/LB .444 .431 .421

Mach Ind .659 .659 .65935 KTAS 363 372 381

NM/LB .431 .421 .411

CL-102B April 2001


EFFECTIVITY




Mach Ind .761A

LTIT

UD

E —

100

0 FE

ET

45 KTAS 419NM/LB .469

Mach Ind .736 .73643 KTAS 407 415

NM/LB .472 .459Mach Ind .716 .716 .716

41 KTAS 394 404 413NM/LB .468 .458 .446

Mach Ind .694 .694 .69439 KTAS 381 390 400

NM/LB .464 .452 .442Mach Ind .671 .671 .671

37 KTAS 369 377 387NM/LB .454 .443 .435

Mach Ind .651 .651 .65135 KTAS 360 368 377

NM/LB .442 .433 .424


Mach Ind .751 .751

ALT

ITU

DE

— 1

000

FEET

45 KTAS 414 423NM/LB .487 .476

Mach Ind .729 .72943 KTAS 402 411

NM/LB .488 .476Mach Ind .706 .706 .706

41 KTAS 390 398 408NM/LB .484 .472 .461

Mach Ind .686 .686 .68639 KTAS 377 386 395

NM/LB .477 .466 .457Mach Ind .664 .664 .664

37 KTAS 365 373 382NM/LB .469 .457 .448

Mach Ind .644 .644 .64435 KTAS 356 364 373

NM/LB .456 .447 .438

CL-102B April 2001Change 1 P-35


EFFECTIVITY

b




Mach Ind .741 .741

ALT

ITU

DE

— 1

000

FEET

45 KTAS 410 418NM/LB .509 .494

Mach Ind .718 .718 .71843 KTAS 397 405 416

NM/LB .505 .492 .480Mach Ind .700 .700 .700

41 KTAS 386 395 404NM/LB .504 .491 .478

Mach Ind .677 .677 .67739 KTAS 373 381 391

NM/LB .496 .482 .471Mach Ind .655 .655 .655

37 KTAS 360 368 378NM/LB .483 .471 .462

Mach Ind .635 .635 .63535 KTAS 351 360 369

NM/LB .468 .460 .451

WEIGHT —12,000 LB TEMPERATURE — °CISA -10 ISA ISA +10

Mach Ind .732 .732

ALT

ITU

DE

— 1

000

FEET

45 KTAS 405 413NM/LB .531 .514

Mach Ind .710 .710 .71043 KTAS 392 401 411

NM/LB .524 .511 .501Mach Ind .691 .691 .691

41 KTAS 381 390 398NM/LB .522 .507 .494

Mach Ind .669 .669 .66939 KTAS 368 377 386

NM/LB .513 .501 .489Mach Ind .646 .646 .646

37 KTAS 356 364 373NM/LB .501 .489 .478

Mach Ind .628 .628 .62835 KTAS 347 356 364

NM/LB .485 .477 .466Change 1

CL-102B April 2001


EFFECTIVITY




Mach Ind .721 .721 .721A

LTIT

UD

E —

100

0 FE

ET

45 KTAS 400 408 416NM/LB .548 .533 .520

Mach Ind .700 .700 .70043 KTAS 387 395 406

NM/LB .541 .527 .517Mach Ind .681 .681 .681

41 KTAS 376 385 393NM/LB .542 .527 .512

Mach Ind .660 .660 .66039 KTAS 363 372 381

NM/LB .531 .517 .506Mach Ind .637 .637 .637

37 KTAS 351 359 369NM/LB .516 .504 .493

Mach Ind .617 .617 .61735 KTAS 342 351 359

NM/LB .501 .490 .477


Mach Ind .711 .711 .711

ALT

ITU

DE

— 1

000

FEET

45 KTAS 394 403 410NM/LB .568 .554 .539

Mach Ind .690 .690 .69043 KTAS 381 390 400

NM/LB .559 .545 .537Mach Ind .669 .669 .669

41 KTAS 371 378 388NM/LB .557 .542 .532

Mach Ind .649 .649 .64939 KTAS 358 366 375

NM/LB .547 .531 .521Mach Ind .627 .627 .627

37 KTAS 346 354 363NM/LB .536 .521 .509

Mach Ind .608 .608 .60835 KTAS 336 345 353

NM/LB .517 .504 .494

CL-102B April 2001


EFFECTIVITY

b




Mach Ind .700 .700 .700

ALT

ITU

DE

— 1

000

FEET

45 KTAS 389 397 405NM/LB .587 .571 .557

Mach Ind .680 .680 .68043 KTAS 376 385 394

NM/LB .584 .570 .557Mach Ind .660 .660 .660

41 KTAS 366 373 382NM/LB .582 .565 .551

Mach Ind .639 .639 .63939 KTAS 352 361 370

NM/LB .566 .551 .543Mach Ind .617 .617 .617

37 KTAS 341 348 358NM/LB .554 .535 .526

Mach Ind .596 .596 .59635 KTAS 331 340 347

NM/LB .535 .523 .510


Mach Ind .690 .690 .690

ALT

ITU

DE

— 1

000

FEET

45 KTAS 383 391 400NM/LB .613 .597 .584

Mach Ind .666 .666 .66643 KTAS 369 378 388

NM/LB .609 .595 .583Mach Ind .647 .647 .647

41 KTAS 359 367 375NM/LB .598 .585 .573

Mach Ind .628 .628 .62839 KTAS 346 355 363

NM/LB .584 .574 .558Mach Ind .606 .606 .606

37 KTAS 335 343 351NM/LB .573 .556 .544

Mach Ind .584 .584 .58435 KTAS 325 333 340

NM/LB .554 .540 .525

CL-102B April 2001


EFFECTIVITY

NORMAL CRUISE

WEIGHT - 18,000 LB TEMPERATURE — °CMACH - .77 MI ISA -10 ISA ISA +10 ISA +15 ISA +20

ALT

ITU

DE

— 1

000

FEET

45 KTASFUEL - LB/HR

43 KTASFUEL - LB/HR

41 KTAS 422FUEL - LB/HR 1160

39 KTAS 420 430FUEL - LB/HR 1200 1258

37 KTAS 419 429FUEL - LB/HR 1230 1281

35 KTAS 421 431 440FUEL - LB/HR 1280 1340 1400

30 KTAS 428 437 447 452FUEL - LB/HR 1465 1535 1600 1635

25 KTAS 437 446 455 458FUEL - LB/HR 1740 1820 1900 1930

CL-102B April 2001


EFFECTIVITY

b

NORMAL CRUISE


ALT

ITU

DE

— 1

000

FEET

45 KTASFUEL - LB/HR

43 KTASFUEL - LB/HR


39 KTAS 420 430FUEL - LB/HR 1175 1230

37 KTAS 419 429FUEL - LB/HR 1207 1257

35 KTAS 421 431 440FUEL - LB/HR 1258 1313 1378

30 KTAS 428 437 447 452FUEL - LB/HR 1445 1512 1575 1610

25 KTAS 437 446 455 458FUEL - LB/HR 1728 1800 1877 1917


ALT

ITU

DE

— 1

000

FEET

45 KTASFUEL - LB/HR

43 KTASFUEL - LB/HR


39 KTAS 420 430FUEL - LB/HR 1125 1204

37 KTAS 419 429 439FUEL - LB/HR 1158 1232 1292

35 KTAS 421 431 440 447FUEL - LB/HR 1212 1290 1353 1380

30 KTAS 428 437 447 452FUEL - LB/HR 1404 1490 1555 1590

25 KTAS 437 446 455 458FUEL - LB/HR 1700 1786 1860 1900

CL-102B April 2001


EFFECTIVITY

NORMAL CRUISE


ALT

ITU

DE

— 1

000

FEET

45 KTASFUEL - LB/HR


41 KTAS 422 432FUEL - LB/HR 1090 1150

39 KTAS 420 430FUEL - LB/HR 1126 1180

37 KTAS 419 429 439FUEL - LB/HR 1157 1210 1265

35 KTAS 421 431 440 447FUEL - LB/HR 1213 1270 1330 1357

30 KTAS 428 437 447 452FUEL - LB/HR 1405 1470 1530 1568

25 KTAS 437 446 455 458 464FUEL - LB/HR 1700 1770 1840 1882 1919


ALT

ITU

DE

— 1

000

FEET

45 KTASFUEL - LB/HR


41 KTAS 422 432FUEL - LB/HR 1065 1122

39 KTAS 420 430FUEL - LB/HR 1101 1155

37 KTAS 419 429 439FUEL - LB/HR 1135 1186 1240

35 KTAS 421 431 440 447FUEL - LB/HR 1194 1248 1310 1330

30 KTAS 428 437 447 452FUEL - LB/HR 1385 1450 1514 1546

25 KTAS 437 416 455 458 464FUEL - LB/HR 1680 1752 1824 1865 1900

CL-102B April 2001


EFFECTIVITY

b

NORMAL CRUISE


ALT

ITU

DE

— 1

000

FEET

45 KTASFUEL - LB/HR


41 KTAS 422 432FUEL - LB/HR 1041 1100

39 KTAS 420 430FUEL - LB/HR 1080 1130

37 KTAS 419 429 439FUEL - LB/HR 1112 1164 1220

35 KTAS 421 431 440 447FUEL - LB/HR 1174 1225 1285 1310

30 KTAS 428 437 447 452FUEL - LB/HR 1366 1432 1494 1528

25 KTAS 437 446 455 458 464FUEL - LB/HR 1665 1737 1810 1850 1884


ALT

ITU

DE

— 1

000

FEET


43 KTAS 422 FUEL - LB/HR 1001

41 KTAS 422 432FUEL - LB/HR 1020 1076

39 KTAS 420 430 440FUEL - LB/HR 1060 1107 1158

37 KTAS 419 429 439 445FUEL - LB/HR 1094 1142 1195 1221

35 KTAS 421 431 440 447FUEL - LB/HR 1155 1206 1265 1290

30 KTAS 428 437 447 452FUEL - LB/HR 1350 1415 1478 1510

25 KTAS 437 446 455 458 464FUEL - LB/HR 1650 1720 1792 1830 1867

CL-102B April 2001


EFFECTIVITY

NORMAL CRUISE


ALT

ITU

DE

— 1

000

FEET


43 KTAS 422 432FUEL - LB/HR 980 1030

41 KTAS 422 432FUEL - LB/HR 1000 1055

39 KTAS 420 430 440FUEL - LB/HR 1040 1084 1135

37 KTAS 419 429 439 445FUEL - LB/HR 1073 1122 1174 1200

35 KTAS 421 431 440 447FUEL - LB/HR 1138 1188 1246 1270

30 KTAS 428 437 447 452FUEL - LB/HR 1334 1398 1460 1490

25 KTAS 437 446 455 458 464FUEL - LB/HR 1635 1705 1776 1815 1850


ALT

ITU

DE

— 1

000

FEET


43 KTAS 422 432FUEL - LB/HR 958 1002

41 KTAS 422 432FUEL - LB/HR 976 1030

39 KTAS 420 430 440FUEL - LB/HR 1017 1061 1110

37 KTAS 419 429 439 445FUEL - LB/HR 1055 1105 1150 1180

35 KTAS 421 431 440 447 450FUEL - LB/HR 1118 1168 1225 1250 1280

30 KTAS 428 437 447 452 456FUEL - LB/HR 1318 1380 1440 1471 1500

25 KTAS 437 446 455 458 464FUEL - LB/HR 1617 1690 1760 1800 1832

CL-102B April 2001Change 1 P-43


EFFECTIVITY

b

NORMAL CRUISE


ALT

ITU

DE

— 1

000

FEET


43 KTAS 422 432FUEL - LB/HR 934 980

41 KTAS 422 432FUEL - LB/HR 960 1010

39 KTAS 420 430 440 444FUEL - LB/HR 997 1041 1090 1114

37 KTAS 419 429 439 445FUEL - LB/HR 1038 1087 1134 1160

35 KTAS 421 431 440 447 450FUEL - LB/HR 1100 1150 1208 1230 1260

30 KTAS 428 437 447 452 456FUEL - LB/HR 1300 1362 1425 1455 1484

25 KTAS 437 446 455 458 464FUEL - LB/HR 1604 1673 1745 1780 1815


ALT

ITU

DE

— 1

000

FEET


43 KTAS 422 432FUEL - LB/HR 910 954

41 KTAS 422 432 442FUEL - LB/HR 940 990 1030

39 KTAS 420 430 440 444FUEL - LB/HR 978 1020 1068 1092

37 KTAS 419 429 439 445 448FUEL - LB/HR 1020 1068 1115 1140 1164

35 KTAS 421 431 440 447 450FUEL - LB/HR 1085 1132 1189 1220 1240

30 KTAS 428 437 447 452 456FUEL - LB/HR 1287 1345 1410 1440 1466

25 KTAS 437 446 455 458 464FUEL - LB/HR 1588 1660 1730 1765 1800Change 1

CL-102B April 2001


EFFECTIVITY

NORMAL CRUISE


ALT

ITU

DE

— 1

000

FEET

45 KTAS 424 433FUEL - LB/HR 871 913

43 KTAS 422 432FUEL - LB/HR 886 930

41 KTAS 422 432 442FUEL - LB/HR 920 970 1001

39 KTAS 420 430 440 444FUEL - LB/HR 958 1000 1048 1071

37 KTAS 419 429 439 445 448FUEL - LB/HR 1002 1050 1097 1120 1145

35 KTAS 421 431 440 447 450FUEL - LB/HR 1068 1114 1170 1193 1220

30 KTAS 428 437 447 452 456FUEL - LB/HR 1270 1330 1390 421 1450

25 KTAS 437 446 455 458 464FUEL - LB/HR 1572 1640 1712 1748 1780


ALT

ITU

DE

— 1

000

FEET

45 KTAS 424 433FUEL - LB/HR 850 889

43 KTAS 422 432FUEL - LB/HR 864 907

41 KTAS 422 432 442FUEL - LB/HR 900 950 988

39 KTAS 420 430 440 444FUEL - LB/HR 940 980 1025 1050

37 KTAS 419 429 439 445 448FUEL - LB/HR 985 1030 1078 1100 1125

35 KTAS 421 431 440 447 450FUEL - LB/HR 1050 1100 1150 1175 1200

30 KTAS 428 437 447 452 456FUEL - LB/HR 1258 1314 1375 1405 1430

25 KTAS 437 446 455 458 464FUEL - LB/HR 1557 1625 1696 1730 1764

CL-102B April 2001


EFFECTIVITY

b

NORMAL CRUISE


ALT

ITU

DE

— 1

000

FEET

45 KTAS 424 433FUEL - LB/HR 825 863

43 KTAS 422 432FUEL - LB/HR 841 883

41 KTAS 422 432 442FUEL - LB/HR 883 930 967

39 KTAS 420 430 440 444FUEL - LB/HR 920 960 1005 1030

37 KTAS 419 429 439 445 448FUEL - LB/HR 970 1012 1060 1082 1106

35 KTAS 421 431 440 447 450FUEL - LB/HR 1035 1080 1134 1157 1182

30 KTAS 428 437 447 452 456FUEL - LB/HR 1242 1300 1360 1387 1415

25 KTAS 437 446 455 458 464FUEL - LB/HR 1540 1610 1680 1712 1746


ALT

ITU

DE

— 1

000

FEET

45 KTAS 424 433FUEL - LB/HR 800 840

43 KTAS 422 432 442FUEL - LB/HR 820 860 904

41 KTAS 422 432 442 446FUEL - LB/HR 867 910 947 970

39 KTAS 420 430 440 444 450FUEL - LB/HR 900 940 985 1001 1031

37 KTAS 419 429 439 445 448FUEL - LB/HR 954 995 1042 1066 1088

35 KTAS 421 431 440 447 450FUEL - LB/HR 1018 1065 1117 1140 1166

30 KTAS 428 437 447 452 456FUEL - LB/HR 1230 1284 1344 1373 1400

25 KTAS 437 446 455 458 464FUEL - LB/HR 1525 1595 1665 1695 1730

CL-102B April 2001


EFFECTIVITY

NORMAL CRUISE


ALT

ITU

DE

— 1

000

FEET

45 KTAS 424 433FUEL - LB/HR 780 815

43 KTAS 422 432 442FUEL - LB/HR 800 840 880

41 KTAS 422 432 442 446FUEL - LB/HR 850 892 928 950

39 KTAS 420 430 440 444 450FUEL - LB/HR 883 923 967 990 1010

37 KTAS 419 429 439 445 448FUEL - LB/HR 937 978 1027 1050 1068

35 KTAS 421 431 440 447 450FUEL - LB/HR 1004 1050 1100 1122 1150

30 KTAS 428 437 447 452 456FUEL - LB/HR 1216 1270 1330 1360 1384

25 KTAS 437 446 455 458 464FUEL - LB/HR 1510 1580 1650 1678 1720


ALT

ITU

DE

— 1

000

FEET

45 KTAS 424 433FUEL - LB/HR 757 794

43 KTAS 422 432 442FUEL - LB/HR 777 819 855

41 KTAS 422 432 442 446FUEL - LB/HR 830 875 910 932

39 KTAS 420 430 440 444 450FUEL - LB/HR 867 905 950 970 993

37 KTAS 419 429 439 445 448FUEL - LB/HR 923 964 1010 1030 1052

35 KTAS 421 431 440 447 450FUEL - LB/HR 988 1035 1085 1107 1132

30 KTAS 428 437 447 452 456FUEL - LB/HR 1202 1257 1315 1344 1370

25 KTAS 437 446 455 458 464FUEL - LB/HR 1495 1562 1634 1662 1694

CL-102B April 2001


EFFECTIVITY

b

LONG RANGE CRUISEONE ENGINE

WEIGHT - 18,000 LB TEMPERATURE — °CISA -10 ISA ISA +10 ISA +15 ISA +20

ALT

ITU

DE

— 1

000

FEET

Mach Ind30 KTAS

FUEL-LB/HRMach Ind .537

25 KTAS 309FUEL-LB/HR 1236

KIAS 238 23820 KTAS 309 315

FUEL-LB/HR 1210 1261KIAS 254 254 254

15 KTAS 305 311 317FUEL-LB/HR 1235 1285 1334

KIAS 267 267 26710 KTAS 296 302 308

FUEL-LB/HR 1281 1331 1380


ALT

ITU

DE

— 1

000

FEET

Mach Ind30 KTAS

FUEL-LB/HRMach Ind .534 .534

25 KTAS 308 315FUEL-LB/HR 1147 1197

KIAS 236 236 23620 KTAS 306 312 318

FUEL-LB/HR 1126 1174 1221KIAS 251 251 251

15 KTAS 301 307 312FUEL-LB/HR 1160 1207 1253

KIAS 261 261 261 26110 KTAS 290 296 301 304

FUEL-LB/HR 1201 1247 1294 1317

CL-102B April 2001


EFFECTIVITY



ALT

ITU

DE

— 1

000

FEET

Mach Ind30 KTAS

FUEL-LB/HRMach Ind .530 .530 .530

25 KTAS 306 313 265FUEL-LB/HR 1054 1100 1147

KIAS 233 233 23320 KTAS 303 309 294

FUEL-LB/HR 1048 1092 1136KIAS 247 247 247 247

15 KTAS 296 302 308 311FUEL-LB/HR 1088 1131 1175 1197

KIAS 255 255 255 25510 KTAS 283 289 294 297

FUEL-LB/HR 1125 1169 1212 1234


ALT

ITU

DE

— 1

000

FEET

Mach Ind .537 .53730 KTAS 304 311

FUEL-LB/HR 1007 1053Mach Ind .527 .527 .527 .527

25 KTAS 304 311 317 320FUEL-LB/HR 973 1015 1058 1079

KIAS 230 230 230 230 23020 KTAS 299 305 312 315 318

FUEL-LB/HR 977 1018 1059 1080 1100KIAS 243 243 243 243 243

15 KTAS 291 297 303 306 308FUEL-LB/HR 1020 1061 1102 1122 1143

KIAS 249 249 249 249 24910 KTAS 276 282 287 289 292

FUEL-LB/HR 1047 l087 1128 1148 1168

CL-102B April 2001


EFFECTIVITY

b



ALT

ITU

DE

— 1

000

FEET

Mach Ind .533 .53330 KTAS 302 308


25 KTAS 301 308 314 317FUEL-LB/HR 893 932 972 991

KIAS 228 228 228 228 22820 KTAS 296 302 308 311 314

FUEL-LB/HR 913 952 990 1009 1028KIAS 238 238 238 238 238

15 KTAS 285 291 296 299 302FUEL-LB/HR 954 992 1031 1050 1069

KIAS 241 241 241 241 24110 KTAS 268 273 278 281 283

FUEL-LB/HR 967 1005 1042 1061 1080


ALT

ITU

DE

— 1

000

FEET

Mach Ind .528 .528 .52830 KTAS 299 306 313

FUEL-LB/HR 822 859 897Mach Ind .516 .516 .516 .516 .516

25 KTAS 298 305 311 314 317FUEL-LB/HR 820 856 892 910 928

KIAS 223 223 223 223 22320 KTAS 290 296 302 305 308

FUEL-LB/HR 849 884 920 938 955KIAS 232 232 232 232 232

15 KTAS 278 284 289 292 295FUEL-LB/HR 883 919 954 972 990

KIAS 233 233 233 233 23310 KTAS 260 265 270 272 275

FUEL-LB/HR 889 923 958 975 992

CL-102B April 2001


EFFECTIVITY



ALT

ITU

DE

— 1

000

FEET

Mach Ind .524 .524 .524 .52430 KTAS 297 304 310 313

FUEL-LB/HR 741 775 808 825Mach Ind .506 .506 .506 .506 .506

25 KTAS 293 299 306 309 312FUEL-LB/HR 752 786 818 835 851

KIAS 219 219 219 219 21920 KTAS 285 291 297 299 302

FUEL-LB/HR 790 823 857 873 890KIAS 225 225 225 225 225

15 KTAS 271 276 282 284 287FUEL-LB/HR 815 848 880 897 913

KIAS 224 224 224 224 22410 KTAS 250 255 260 262 264

FUEL-LB/HR 807 838 869 885 900


ALT

ITU

DE

— 1

000

FEET

Mach Ind .518 .518 .518 .518 .51830 KTAS 293 300 307 310 313

FUEL-LB/HR 669 699 730 745 761Mach Ind .498 .498 .498 .498 .498

25 KTAS 288 294 301 304 307FUEL-LB/HR 691 722 752 767 782

KIAS 213 213 213 213 21320 KTAS 277 283 288 291 294

FUEL-LB/HR 723 754 784 799 814KIAS 217 217 217 217 217

15 KTAS 261 266 271 273 276FUEL-LB/HR 740 770 800 815 830

KIAS 214 214 214 214 21410 KTAS 239 243 248 250 252

FUEL-LB/HR 725 753 781 795 809

CL-102B April 2001


EFFECTIVITY

b



ALT

ITU

DE

— 1

000

FEET

Mach Ind .509 .509 .509 .509 .50930 KTAS 289 296 302 305 309


25 KTAS 282 288 294 297 300FUEL-LB/HR 631 659 686 700 714

KIAS 203 203 203 203 20320 KTAS 267 272 278 280 283

FUEL-LB/HR 648 676 703 716 730KIAS 206 206 206 206 206

15 KTAS 248 253 257 260 262FUEL-LB/HR 656 683 709 722 735

KIAS 201 201 201 201 20110 KTAS 225 229 234 236 238

FUEL-LB/HR 642 666 691 704 716

CL-102B April 2001


EFFECTIVITY

CREW NOTES

ALLEFFECTIVITY

CL-102B April 2001

P-29.1With Rosemount Pitot-Static System

EFFECTIVITY

b




Mach Ind

ALT

ITU

DE

— 1

000

FEET

45 KTASNM/LB

Mach Ind43 KTAS

NM/LBMach Ind .764

41 KTAS 427NM/LB .351

Mach Ind .743 .74339 KTAS 415 425

NM/LB .355 .347Mach Ind .717 .717 .717

37 KTAS 400 409 419NM/LB .353 .345 .337

Mach Ind .697 .697 .69735 KTAS 391 400 409

NM/LB .350 .341 .334

CL-102B April 2001


EFFECTIVITY




Mach IndA

LTIT

UD

E —

100

0 FE

ET

45 KTASNM/LB

Mach Ind43 KTAS

NM/LBMach Ind .759

41 KTAS 424NM/LB .362

Mach Ind .737 .73739 KTAS 412 421

NM/LB .365 .356Mach Ind .711 .711 .711

37 KTAS 397 406 416NM/LB .363 .354 .347

Mach Ind .690 .690 .69035 KTAS 388 396 406

NM/LB .359 .350 .342


Mach Ind

ALT

ITU

DE

— 1

000

FEET

45 KTASNM/LB

Mach Ind43 KTAS

NM/LBMach Ind .752

41 KTAS 420NM/LB .373

Mach Ind .728 .72839 KTAS 408 416

NM/LB .376 .365Mach Ind .706 .706 .706

37 KTAS 394 403 412NM/LB .373 .363 .355

Mach Ind .685 .685 .68535 KTAS 384 393 402

NM/LB .366 .358 .350

CL-102B April 2001


EFFECTIVITY

b




Mach Ind

ALT

ITU

DE

— 1

000

FEET

45 KTASNM/LB

Mach Ind43 KTAS

NM/LBMach Ind .745 .745

41 KTAS 417 426NM/LB .385 .374

Mach Ind .725 .725 .72539 KTAS 404 414 424

NM/LB .385 .376 .368Mach Ind .698 .698 .698

37 KTAS 390 399 410NM/LB .382 .373 .366

Mach Ind .678 .678 .67835 KTAS 381 389 400

NM/LB .378 .369 .363


Mach Ind

ALT

ITU

DE

— 1

000

FEET

45 KTASNM/LB


NM/LB .394Mach Ind .740 .740

41 KTAS 413 423NM/LB .396 .387

Mach Ind .718 .718 .71839 KTAS 401 410 420

NM/LB .397 .387 .378Mach Ind .692 .692 .692

37 KTAS 387 396 406NM/LB .395 .384 .376

Mach Ind .673 .673 .67335 KTAS 378 386 395

NM/LB .389 .379 .371

CL-102B April 2001


EFFECTIVITY




Mach IndA

LTIT

UD

E —

100

0 FE

ET

45 KTASNM/LB


NM/LB .410Mach Ind .735 .735

41 KTAS 410 420NM/LB .410 .399

Mach Ind .711 .711 .71139 KTAS 397 406 416

NM/LB .409 .399 .391Mach Ind .686 .686 .686

37 KTAS 384 392 402NM/LB .406 .395 .387

Mach Ind .666 .666 .66635 KTAS 374 382 392

NM/LB .400 .390 .382


Mach Ind

ALT

ITU

DE

— 1

000

FEET

45 KTASNM/LB


NM/LB .423Mach Ind .727 .727 .727

41 KTAS 406 415 424NM/LB .423 .413 .402

Mach Ind .706 .706 .70639 KTAS 393 403 412

NM/LB .422 .412 .403Mach Ind .680 .680 .680

37 KTAS 380 389 399NM/LB .418 .407 .399

Mach Ind .659 .659 .65935 KTAS 371 378 389

NM/LB .410 .399 .393

CL-102B April 2001


EFFECTIVITY

b




Mach Ind

ALT

ITU

DE

— 1

000

FEET

45 KTASNM/LB

Mach Ind .741 .74143 KTAS 415 424

NM/LB .441 .428Mach Ind .721 .721 .721

41 KTAS 402 412 422NM/LB .437 .427 .417

Mach Ind .698 .698 .69839 KTAS 390 399 409

NM/LB .436 .424 .414Mach Ind .672 .672 .672

37 KTAS 376 385 395NM/LB .428 .418 .409

Mach Ind .654 .654 .65435 KTAS 368 375 385

NM/LB .422 .410 .403


Mach Ind .759

ALT

ITU

DE

— 1

000

FEET

45 KTAS 424NM/LB .453

Mach Ind .735 .73543 KTAS 411 420

NM/LB .457 .444Mach Ind .713 .713 .713

41 KTAS 398 407 417NM/LB .452 .441 .430

Mach Ind .689 .689 .68939 KTAS 385 394 404

NM/LB .449 .438 .430Mach Ind .664 .664 .664

37 KTAS 373 381 391NM/LB .444 .431 .421

Mach Ind .648 .648 .64835 KTAS 363 372 381

NM/LB .431 .421 .411

CL-102B April 2001


EFFECTIVITY




Mach Ind .750A

LTIT

UD

E —

100

0 FE

ET

45 KTAS 419NM/LB .469

Mach Ind .727 .72743 KTAS 407 415

NM/LB .472 .459Mach Ind .707 .707 .707

41 KTAS 394 404 413NM/LB .468 .458 .446

Mach Ind .682 .682 .68239 KTAS 381 390 400

NM/LB .464 .452 .442Mach Ind .657 .657 .657

37 KTAS 369 377 387NM/LB .454 .443 .435

Mach Ind .641 .641 .64135 KTAS 360 368 377

NM/LB .442 .433 .424


Mach Ind .740 .740

ALT

ITU

DE

— 1

000

FEET

45 KTAS 414 423NM/LB .487 .476

Mach Ind .720 .72043 KTAS 402 411

NM/LB .488 .476Mach Ind .696 .696 .696

41 KTAS 390 398 408NM/LB .484 .472 .461

Mach Ind .674 .674 .67439 KTAS 377 386 395

NM/LB .477 .466 .457Mach Ind .649 .649 .649

37 KTAS 365 373 382NM/LB .469 .457 .448

Mach Ind .635 .635 .63535 KTAS 356 364 373

NM/LB .456 .447 .438

CL-102B April 2001Change 1 P-35.1


EFFECTIVITY

b




Mach Ind .732 .732

ALT

ITU

DE

— 1

000

FEET

45 KTAS 410 418NM/LB .509 .494

Mach Ind .709 .709 .70943 KTAS 397 405 416

NM/LB .505 .492 .480Mach Ind .691 .691 .691

41 KTAS 386 395 404NM/LB .504 .491 .478

Mach Ind .664 .664 .66439 KTAS 373 381 391

NM/LB .496 .482 .471Mach Ind .640 .640 .640

37 KTAS 360 368 378NM/LB .483 .471 .462

Mach Ind .628 .628 .62835 KTAS 351 360 369

NM/LB .468 .460 .451

WEIGHT —12,000 LB TEMPERATURE — °CISA -10 ISA ISA +10

Mach Ind .723 .723

ALT

ITU

DE

— 1

000

FEET

45 KTAS 405 413NM/LB .531 .514

Mach Ind .701 .701 .70143 KTAS 392 401 411

NM/LB .524 .511 .501Mach Ind .682 .682 .682

41 KTAS 381 390 398NM/LB .522 .507 .494

Mach Ind .657 .657 .65739 KTAS 368 377 386

NM/LB .513 .501 .489Mach Ind .633 .633 .633

37 KTAS 356 364 373NM/LB .501 .489 .478

Mach Ind .621 .621 .62135 KTAS 347 356 364

NM/LB .485 .477 .466

Change 1

CL-102B April 2001


EFFECTIVITY




Mach Ind .714 .714 .714A

LTIT

UD

E —

100

0 FE

ET

45 KTAS 400 408 416NM/LB .548 .533 .520

Mach Ind .691 .691 .69143 KTAS 387 395 406

NM/LB .541 .527 .517Mach Ind .672 .672 .672

41 KTAS 376 385 393NM/LB .542 .527 .512

Mach Ind .648 .648 .64839 KTAS 363 372 381

NM/LB .531 .517 .506Mach Ind .624 .624 .624

37 KTAS 351 359 369NM/LB .516 .504 .493

Mach Ind .612 .612 .61235 KTAS 342 351 359

NM/LB .501 .490 .477


Mach Ind .706 .706 .706

ALT

ITU

DE

— 1

000

FEET

45 KTAS 394 403 410NM/LB .568 .554 .539

Mach Ind .682 .682 .68243 KTAS 381 390 400

NM/LB .559 .545 .537Mach Ind .659 .659 .659

41 KTAS 371 378 388NM/LB .557 .542 .532

Mach Ind .636 .636 .63639 KTAS 358 366 375

NM/LB .547 .531 .521Mach Ind .614 .614 .614

37 KTAS 346 354 363NM/LB .536 .521 .509

Mach Ind .602 .602 .60235 KTAS 336 345 353

NM/LB .517 .504 .494

CL-102B April 2001


EFFECTIVITY

b




Mach Ind .694 .694 .694

ALT

ITU

DE

— 1

000

FEET

45 KTAS 389 397 405NM/LB .587 .571 .557

Mach Ind .672 .672 .67243 KTAS 376 385 394

NM/LB .584 .570 .557Mach Ind .647 .647 .647

41 KTAS 366 373 382NM/LB .582 .565 .551

Mach Ind .627 .627 .62739 KTAS 352 361 370

NM/LB .566 .551 .543Mach Ind .603 .603 .603

37 KTAS 341 348 358NM/LB .554 .535 .526

Mach Ind .593 .593 .59335 KTAS 331 340 347

NM/LB .535 .523 .510


Mach Ind .684 .684 .684

ALT

ITU

DE

— 1

000

FEET

45 KTAS 383 391 400NM/LB .613 .597 .584

Mach Ind .659 .659 .65943 KTAS 369 378 388

NM/LB .609 .595 .583Mach Ind .638 .638 .638

41 KTAS 359 367 375NM/LB .598 .585 .573

Mach Ind .616 .616 .61639 KTAS 346 355 363

NM/LB .584 .574 .558Mach Ind .601 .601 .601

37 KTAS 335 343 351NM/LB .573 .556 .544

Mach Ind .581 .581 .58135 KTAS 325 333 340

NM/LB .554 .540 .525

CL-102B April 2001


EFFECTIVITY

NORMAL CRUISE


ALT

ITU

DE

— 1

000

FEET

45 KTASFUEL - LB/HR

43 KTASFUEL - LB/HR


39 KTAS 420 430FUEL - LB/HR 1200 1258

37 KTAS 419 429FUEL - LB/HR 1230 1281

35 KTAS 421 431 440FUEL - LB/HR 1280 1340 1400

30 KTAS 428 437 447 452FUEL - LB/HR 1465 1535 1600 1635

25 KTAS 437 446 455 458FUEL - LB/HR 1740 1820 1900 1930

CL-102B April 2001


EFFECTIVITY

b

NORMAL CRUISE


ALT

ITU

DE

— 1

000

FEET

45 KTASFUEL - LB/HR

43 KTASFUEL - LB/HR


39 KTAS 420 430FUEL - LB/HR 1175 1230

37 KTAS 419 429FUEL - LB/HR 1207 1257

35 KTAS 421 431 440FUEL - LB/HR 1258 1313 1378

30 KTAS 428 437 447 452FUEL - LB/HR 1445 1512 1575 1610

25 KTAS 437 446 455 458FUEL - LB/HR 1728 1800 1877 1917


ALT

ITU

DE

— 1

000

FEET

45 KTASFUEL - LB/HR

43 KTASFUEL - LB/HR


39 KTAS 420 430FUEL - LB/HR 1125 1204

37 KTAS 419 429 439FUEL - LB/HR 1158 1232 1292

35 KTAS 421 431 440 447FUEL - LB/HR 1212 1290 1353 1380

30 KTAS 428 437 447 452FUEL - LB/HR 1404 1490 1555 1590

25 KTAS 437 446 455 458FUEL - LB/HR 1700 1786 1860 1900

CL-102B April 2001


EFFECTIVITY

NORMAL CRUISE


ALT

ITU

DE

— 1

000

FEET

45 KTASFUEL - LB/HR


41 KTAS 422 432FUEL - LB/HR 1090 1150

39 KTAS 420 430FUEL - LB/HR 1126 1180

37 KTAS 419 429 439FUEL - LB/HR 1157 1210 1265

35 KTAS 421 431 440 447FUEL - LB/HR 1213 1270 1330 1357

30 KTAS 428 437 447 452FUEL - LB/HR 1405 1470 1530 1568

25 KTAS 437 446 455 458 464FUEL - LB/HR 1700 1770 1840 1882 1919


ALT

ITU

DE

— 1

000

FEET

45 KTASFUEL - LB/HR


41 KTAS 422 432FUEL - LB/HR 1065 1122

39 KTAS 420 430FUEL - LB/HR 1101 1155

37 KTAS 419 429 439FUEL - LB/HR 1135 1186 1240

35 KTAS 421 431 440 447FUEL - LB/HR 1194 1248 1310 1330

30 KTAS 428 437 447 452FUEL - LB/HR 1385 1450 1514 1546

25 KTAS 437 446 455 458 464FUEL - LB/HR 1680 1752 1824 1865 1900

CL-102B April 2001


EFFECTIVITY

b

NORMAL CRUISE


ALT

ITU

DE

— 1

000

FEET

45 KTASFUEL - LB/HR


41 KTAS 422 432FUEL - LB/HR 1041 1100

39 KTAS 420 430FUEL - LB/HR 1080 1130

37 KTAS 419 429 439FUEL - LB/HR 1 112 1164 1220

35 KTAS 421 431 440 447FUEL - LB/HR 1174 1225 1285 1310

30 KTAS 428 437 447 452FUEL - LB/HR 1366 1432 1494 1528

25 KTAS 437 446 455 458 464FUEL - LB/HR 1665 1737 1810 1850 1884


ALT

ITU

DE

— 1

000

FEET



41 KTAS 422 432FUEL - LB/HR 1020 1076

39 KTAS 420 430 440FUEL - LB/HR 1060 1107 1158

37 KTAS 419 429 439 445FUEL - LB/HR 1094 1142 1195 1221

35 KTAS 421 431 440 447FUEL - LB/HR 1155 1206 1265 1290

30 KTAS 28 437 447 452FUEL - LB/HR 1350 1415 1478 1510

25 KTAS 437 446 455 458 464FUEL - LB/HR 1650 1720 1792 1830 1867

CL-102B April 2001


EFFECTIVITY

NORMAL CRUISE


ALT

ITU

DE

— 1

000

FEET


43 KTAS 422 432FUEL - LB/HR 980 1030

41 KTAS 422 432FUEL - LB/HR 1000 1055

39 KTAS 420 430 440FUEL - LB/HR 1040 1084 1135

37 KTAS 419 429 439 445FUEL - LB/HR 1073 1122 1174 1200

35 KTAS 421 431 440 447FUEL - LB/HR 1138 1188 1246 1270

30 KTAS 428 437 447 452FUEL - LB/HR 1334 1398 1460 1490

25 KTAS 437 446 455 458 464FUEL - LB/HR 1635 1705 1776 1815 1850


ALT

ITU

DE

— 1

000

FEET


43 KTAS 422 432FUEL - LB/HR 958 1002

41 KTAS 422 432FUEL - LB/HR 976 1030

39 KTAS 420 430 440FUEL - LB/HR 1017 1061 1110

37 KTAS 419 429 439 445FUEL - LB/HR 1055 1105 1150 1180

35 KTAS 421 431 440 447 450FUEL - LB/HR 1118 1168 1225 1250 1280

30 KTAS 428 437 447 452 456FUEL - LB/HR 1318 1380 1440 1471 1500

25 KTAS 437 446 455 458 464FUEL - LB/HR 1617 1690 1760 1800 1832

CL-102B April 2001Change 1 P-43.1


EFFECTIVITY

b

NORMAL CRUISE


ALT

ITU

DE

— 1

000

FEET


43 KTAS 422 432FUEL - LB/HR 934 980

41 KTAS 422 432FUEL - LB/HR 960 1010

39 KTAS 420 430 440 444FUEL - LB/HR 997 1041 1090 1114

37 KTAS 419 429 439 445FUEL - LB/HR 1038 1087 1134 1160

35 KTAS 421 431 440 447 450FUEL - LB/HR 1100 1150 1208 1230 1260

30 KTAS 428 437 447 452 456FUEL - LB/HR 1300 1362 1425 1455 1484

25 KTAS 437 446 455 458 464FUEL - LB/HR 1604 1673 1745 1780 1815


ALT

ITU

DE

— 1

000

FEET


43 KTAS 422 432FUEL - LB/HR 910 954

41 KTAS 422 432 442FUEL - LB/HR 940 990 1030

39 KTAS 420 430 440 444FUEL - LB/HR 978 1020 1068 1092

37 KTAS 419 429 439 445 448FUEL - LB/HR 1020 1068 1115 1140 1164

35 KTAS 421 431 440 447 450FUEL - LB/HR 1085 1132 1189 1220 1240

30 KTAS 428 437 447 452 456FUEL - LB/HR 1287 1345 1410 1440 1466

25 KTAS 437 446 455 458 464FUEL - LB/HR 1588 1660 1730 1765 1800

Change 1

CL-102B April 2001


EFFECTIVITY

NORMAL CRUISE


ALT

ITU

DE

— 1

000

FEET

45 KTAS 424 433FUEL - LB/HR 871 913

43 KTAS 422 432FUEL - LB/HR 886 930

41 KTAS 422 432 442FUEL - LB/HR 920 970 1001

39 KTAS 420 430 440 444FUEL - LB/HR 958 1000 1048 1071

37 KTAS 419 429 439 445 448FUEL - LB/HR 1002 1050 1097 1120 1145

35 KTAS 421 431 440 447 450FUEL - LB/HR 1068 1114 1170 1193 1220

30 KTAS 428 437 447 452 456FUEL - LB/HR 1270 1330 1390 1421 1450

25 KTAS 437 446 455 458 464FUEL - LB/HR 1572 1640 1712 1748 1780


ALT

ITU

DE

— 1

000

FEET

45 KTAS 424 433FUEL - LB/HR 850 889

43 KTAS 422 432FUEL - LB/HR 864 907

41 KTAS 422 432 442FUEL - LB/HR 900 950 988

39 KTAS 420 430 440 444FUEL - LB/HR 940 980 1025 1050

37 KTAS 419 429 439 445 448FUEL - LB/HR 985 1030 1078 1100 1125

35 KTAS 421 431 440 447 450FUEL - LB/HR 1050 1100 1150 1175 1200

30 KTAS 428 437 447 452 456FUEL - LB/HR 1258 1314 1375 1405 1430

25 KTAS 437 446 455 458 464FUEL - LB/HR 1557 1625 1696 1730 1764

CL-102B April 2001


EFFECTIVITY

b

NORMAL CRUISE


ALT

ITU

DE

— 1

000

FEET

45 KTAS 424 433FUEL - LB/HR 825 863

43 KTAS 422 432FUEL - LB/HR 841 883

41 KTAS 422 432 442FUEL - LB/HR 883 930 967

39 KTAS 420 430 440 444FUEL - LB/HR 920 960 1005 1030

37 KTAS 419 429 439 445 448FUEL - LB/HR 970 1012 1060 1082 1106

35 KTAS 421 431 440 447 450FUEL - LB/HR 1035 1080 1134 1157 1182

30 KTAS 428 437 447 452 456FUEL - LB/HR 1242 1300 1360 1387 1415

25 KTAS 437 446 455 458 464FUEL - LB/HR 1540 1610 1680 1712 1746


ALT

ITU

DE

— 1

000

FEET

45 KTAS 424 433FUEL - LB/HR 800 840

43 KTAS 422 432 442FUEL - LB/HR 820 860 904

41 KTAS 422 432 442 446FUEL - LB/HR 867 910 947 970

39 KTAS 420 430 440 444 450FUEL - LB/HR 900 940 985 1001 1031

37 KTAS 419 429 439 445 448FUEL - LB/HR 954 995 1042 1066 1088

35 KTAS 421 431 440 447 450FUEL - LB/HR 1018 1065 1117 1140 1166

30 KTAS 428 437 447 452 456FUEL - LB/HR 1230 1284 1344 1373 1400

25 KTAS 437 446 455 458 464FUEL - LB/HR 1525 1595 1665 1695 1730

CL-102B April 2001


EFFECTIVITY

NORMAL CRUISE


ALT

ITU

DE

— 1

000

FEET

45 KTAS 424 433FUEL - LB/HR 780 815

43 KTAS 422 432 442FUEL - LB/HR 800 840 880

41 KTAS 422 432 442 446FUEL - LB/HR 850 892 928 950

39 KTAS 420 430 440 444 450FUEL - LB/HR 883 923 967 990 1010

37 KTAS 419 429 439 445 448FUEL - LB/HR 937 978 1027 1050 1068

35 KTAS 421 431 440 447 450FUEL - LB/HR 1004 1050 1100 1122 1150

30 KTAS 428 437 447 452 456FUEL - LB/HR 1216 1270 1330 1360 1384

25 KTAS 437 446 455 458 464FUEL - LB/HR 1510 1580 1650 1678 1720


ALT

ITU

DE

— 1

000

FEET

45 KTAS 424 433FUEL - LB/HR 757 794

43 KTAS 422 432 442FUEL - LB/HR 777 819 855

41 KTAS 422 432 442 446FUEL - LB/HR 830 875 910 932

39 KTAS 420 430 440 444 450FUEL - LB/HR 867 905 950 970 993

37 KTAS 419 429 439 445 448FUEL - LB/HR 923 964 1010 1030 1052

35 KTAS 421 431 440 447 450FUEL - LB/HR 988 1035 1085 1107 1132

30 KTAS 428 437 447 452 456FUEL - LB/HR 1202 1257 1315 1344 1370

25 KTAS 437 446 455 458 464FUEL - LB/HR 1495 1562 1634 1662 1694

CL-102B April 2001


EFFECTIVITY

b



ALT

ITU

DE

— 1

000

FEET

Mach Ind30 KTAS

FUEL-LB/HRMach Ind .530

25 KTAS 309FUEL-LB/HR 1236

KIAS 235 23520 KTAS 309 315

FUEL-LB/HR 1210 1261KIAS 251 251 251

15 KTAS 305 311 317FUEL-LB/HR 1235 1285 1334

KIAS 262 262 26210 KTAS 296 302 308

FUEL-LB/HR 1281 1331 1380


ALT

ITU

DE

— 1

000

FEET

Mach Ind30 KTAS

FUEL-LB/HRMach Ind .525 .525

25 KTAS 308 315FUEL-LB/HR 1147 1197

KIAS 233 233 23320 KTAS 306 312 318

FUEL-LB/HR 1126 1174 1221KIAS 248 248 248

15 KTAS 301 307 312FUEL-LB/HR 1160 1207 1253

KIAS 257 257 257 25710 KTAS 290 296 301 304

FUEL-LB/HR 1201 1247 1294 1317

CL-102B April 2001


EFFECTIVITY



ALT

ITU

DE

— 1

000

FEET

Mach Ind30 KTAS

FUEL-LB/HRMach Ind .522 .522 .522

25 KTAS 306 313 319FUEL-LB/HR 1054 1100 1147

KIAS 230 230 23020 KTAS 303 309 316

FUEL-LB/HR 1048 1092 1136KIAS 243 243 243 243

15 KTAS 296 302 308 311FUEL-LB/HR 1088 1131 1175 1197

KIAS 251 251 251 25110 KTAS 283 289 294 297

FUEL-LB/HR 1125 1169 1212 1234


ALT

ITU

DE

— 1

000

FEET

Mach Ind .530 .53030 KTAS 304 311


25 KTAS 304 311 317 320FUEL-LB/HR 973 1015 1058 1079

KIAS 227 227 227 227 22720 KTAS 299 305 312 315 318

FUEL-LB/HR 977 1018 1059 1080 1100KIAS 239 239 239 239 239

15 KTAS 291 297 303 306 308FUEL-LB/HR 1020 1061 1102 1122 1143

KIAS 245 245 245 245 24510 KTAS 276 282 287 289 292

FUEL-LB/HR 1047 1087 1128 1148 1168

CL-102B April 2001


EFFECTIVITY

b



ALT

ITU

DE

— 1

000

FEET

Mach Ind .525 .52530 KTAS 302 308


25 KTAS 301 308 314 317FUEL-LB/HR 893 932 972 991

KIAS 225 225 225 225 22520 KTAS 296 302 308 311 314

FUEL-LB/HR 913 952 990 1009 1028KIAS 235 235 235 235 235

15 KTAS 285 291 296 299 302FUEL-LB/HR 954 992 1031 1050 1069

KIAS 237 237 237 237 23710 KTAS 268 273 278 281 283

FUEL-LB/HR 967 1005 1042 1061 1080


ALT

ITU

DE

— 1

000

FEET

Mach Ind .521 .521 .52130 KTAS 299 306 313

FUEL-LB/HR 822 859 897Mach Ind .509 .509 .509 .509 .509

25 KTAS 298 305 311 314 317FUEL-LB/HR 820 856 892 910 928

KIAS 219 219 219 219 21920 KTAS 290 296 302 305 308

FUEL-LB/HR 849 884 920 938 955KIAS 229 229 229 229 229

15 KTAS 278 284 289 292 295FUEL-LB/HR 883 919 954 972 990

KIAS 230 230 230 230 23010 KTAS 260 265 270 272 275

FUEL-LB/HR 889 923 958 975 992

CL-102B April 2001


EFFECTIVITY



ALT

ITU

DE

— 1

000

FEET

Mach Ind .518 .518 .518 .51830 KTAS 297 304 310 313

FUEL-LB/HR 741 775 808 825Mach Ind .499 .499 .499 .499 .499

25 KTAS 293 299 306 309 312FUEL-LB/HR 752 786 818 835 851

KIAS 216 216 216 216 21620 KTAS 285 291 297 299 302

FUEL-LB/HR 790 823 857 873 890KIAS 221 221 221 221 221

15 KTAS 271 276 282 284 287FUEL-LB/HR 815 848 880 897 913

KIAS 220 220 220 220 22010 KTAS 250 255 260 262 264

FUEL-LB/HR 807 838 869 885 900


ALT

ITU

DE

— 1

000

FEET

Mach Ind .511 .511 .511 .511 .51130 KTAS 293 300 307 310 313


25 KTAS 288 294 301 304 307FUEL-LB/HR 691 722 752 767 782

KIAS 210 210 210 210 21020 KTAS 277 283 288 291 294

FUEL-LB/HR 723 754 784 799 814KIAS 213 213 213 213 213

15 KTAS 261 266 271 273 276FUEL-LB/HR 740 770 800 815 830

KIAS 210 210 210 210 21010 KTAS 239 243 248 250 252

FUEL-LB/HR 725 753 781 795 809

CL-102B April 2001


EFFECTIVITY

b



ALT

ITU

DE

— 1

000

FEET

Mach Ind .504 .504 .504 .504 .50430 KTAS 289 296 302 305 309


25 KTAS 282 288 294 297 300FUEL-LB/HR 631 659 686 700 714

KIAS 201 201 201 201 20120 KTAS 267 272 278 280 283

FUEL-LB/HR 648 676 703 716 730KIAS 202 202 202 202 202

15 KTAS 248 253 257 260 262FUEL-LB/HR 656 683 709 722 735

KIAS 198 198 198 198 19810 KTAS 225 229 234 236 238

FUEL-LB/HR 642 666 691 704 716

CL-102B April 2001 P-53ALL

EFFECTIVITY

b

MAXIMUM RANGE DESCENTONE ENGINE

NOTE

This table represents the minimum sink-rate speedabove the single-engine service ceiling and approxi-mates the best rate-of-climb speed below the single-engine service ceiling.

ALTITUDE — FEET DESCENT — SPEED

45,000 to 33,500 170 KIAS

33,500 to 26,500 0.50 MI

26,500 and below 200 KIAS

CL-102BP-54 April 2001ALL

EFFECTIVITY

DESCENT PERFORMANCE SCHEDULE

MINIMUM FUEL DESCENT SPEEDS: 3,000 Ft/Min at MMO down to 31,000 feet.4,000 Ft/Min at 300 KIAS down to 10,000 feet.3,000 Ft/Min at 250 KIAS to Sea Level.

NORMAL DESCENT SPEEDS: 3,000 Ft/Min at MMO/VMO down to 10,000 feet.3,000 Ft/Min at 250 KIAS to Sea Level.

AVERAGE WEIGHT12,000 Lb

MINIMUM FUEL DESCENT NORMAL DESCENT TIMEMin.

DISTANCEN.M.

FUELLb

TIMEMin.

DISTANCEN.M.

FUELLb

ALT

ITU

DE

— 1

000

FEET

45 14.5 92 169 16.4 109 28544 14.2 89 166 16.0 106 28243 13.8 87 162 15.7 104 27842 13.5 84 158 15.3 101 27541 13.2 82 154 15.0 99 27140 12.8 79 149 14.7 96 26739 12.5 76 145 14.4 94 26238 12.2 74 140 14.0 91 25737 11.8 71 135 13.7 88 25236 11.5 69 129 13.4 86 24635 11.2 66 124 13.0 83 24134 10.9 63 118 12.7 81 23433 10.5 61 112 12.4 78 22832 10.2 59 106 12.0 75 22031 9.9 56 100 11.7 73 21430 9.7 55 96 11.3 70 20529 9.4 53 92 11.0 67 19728 9.2 51 88 10.7 65 18827 8.9 49 85 10.4 62 17826 8.7 47 81 10.0 59 16925 8.4 45 78 9.7 57 15824 8.2 43 75 9.3 54 14723 7.9 42 72 9.0 51 13722 7.6 40 70 8.7 49 12621 7.4 38 67 8.4 46 11620 7.1 36 64 8.0 44 10518 6.6 33 59 7.3 39 8616 6.1 30 54 6.7 33 6814 5.6 27 50 6.0 29 5712 5.1 24 45 5.3 25 4410 4.6 21 40 4.6 21 408 3.7 17 33 3.7 17 336 2.8 12 23 2.8 12 234 1.9 8 16 1.9 8 16

CL-102B April 2001 P-55ALL

EFFECTIVITY

b

HOLDING OPERATIONS

LANDING WEIGHT LIMITSANTI-ICE OFF

These data were determined for dry runway, zero wind, zero runwaygradient, anti-ice off, & anti-skid on.DO NOT EXCEED MAXIMUM CERTIFIED LANDING WEIGHT

HOLDINGSPEEDKIAS

ALTITUDE — 1000 FT HOLDINGSPEEDKIAS

ALT — 1000 FTWEIGHT

LB 5 10 15 20 25 30

18,000 194 1179 1171 1163 1156 214 1127 1109

17,000 187 1115 1106 1088 1069 207 1062 1043

16,000 180 1040 1031 1012 1004 200 997 978

15,000 174 975 945 937 929 194 932 913

14,000 167 911 879 862 853 187 867 848

13,000 160 847 805 786 778 180 813 793

12,000 154 782 741 721 713 174 737 717

11,000 147 729 677 657 648 167 672 652

10,000 140 675 634 603 583 160 607 587

PRESSUREALTITUDE

(FEET)

TEMPERATURE°F 0 20 40 60 80 100°C -18 -7 4 16 27 38

10000 15300 15300 15300 15150 134009000 15300 139008000 144507000 150006000 15300 136005000 141004000 146003000 151002000 153001000S.L.

FUEL-LB/HR FUEL-LB/HR

LAN

DIN

G

CL-102BP-56 April 2001

Change 1ALL

EFFECTIVITY

LANDING SPEEDS & DISTANCES


TEMP°F 0 20 40 60 80 100

°C -18 -7 4 16 27 38

WT LANDING DISTANCE (FEET)

15,300ACTUAL 2825 2900 2976 3051 3127 3203

FACTORED 4709 4834 4960 5085 5212 5339

15,000ACTUAL 2791 2864 2936 3009 3082 3155

FACTORED 4652 4774 4894 5015 5137 5259

14,000ACTUAL 2679 2742 2805 2868 2931 2995

FACTORED 4465 4570 4675 4780 4885 4992

13,000ACTUAL 2549 2608 2667 2726 2785 2844

FACTORED 4249 4347 4445 4544 4642 4740

12,000ACTUAL 2422 2479 2536 2594 2651 2709

FACTORED 4037 4132 4227 4324 4419 4515

11,000ACTUAL 2314 2366 2417 2469 2521 2572

FACTORED 3857 3944 4029 4115 4202 4287

10,000ACTUAL 2208 2255 2302 2348 2395 2442

FACTORED 3680 3759 3837 3914 3992 4070

15,300ACTUAL 2986 3061 3137 3212 3287 3362

FACTORED 4977 5102 5229 5354 5479 5604

15,000ACTUAL 2946 3019 3091 3163 3236 3308

FACTORED 4910 5032 5152 5272 5394 5514

14,000ACTUAL 2814 2877 2939 3002 3065 3128

FACTORED 4690 4795 4899 5004 5109 5214

13,000ACTUAL 2675 2734 2792 2851 2910 2968

FACTORED 4459 4557 4654 4752 4850 4947

12,000ACTUAL 2544 2601 2658 2715 2773 2830

FACTORED 4240 4335 4430 4525 4622 4717

11,000ACTUAL 2424 2476 2527 2578 2630 2681

FACTORED 4040 4127 4212 4297 4384 4469

10,000ACTUAL 2308 2354 2401 2447 2494 2540

FACTORED 3847 3924 4002 4079 4157 4234

SPEED WEIGHT — 1000 LB10 11 12 13 14 15 15.3

VREF &LDG CLIMB 105 110 115 119 123 127 129

APPROACHCLIMB 111 116 121 126 130 135 136

2000

FT

SEA

LEV

EL

Change 1

LAN

DIN

G

CL-102B April 2001 P-57Change 1

ALLEFFECTIVITY

b



TEMP°F 0 20 40 60 80 100

°C -18 -7 4 16 27 38


15,300ACTUAL 3112 3190 3269 3348 3426

FACTORED 5187 5317 5449 5580 5710

15,000ACTUAL 3067 3143 3219 3294 3370

FACTORED 5112 5239 5365 5490 5617

14,000ACTUAL 2919 2984 3050 3116 3181 3247

FACTORED 4865 4974 5084 5194 5302 5412

13,000ACTUAL 2773 2834 2896 2957 3018 3080

FACTORED 4622 4724 4827 4929 5030 5134

12,000ACTUAL 2640 2699 2759 2819 2878 2938

FACTORED 4400 4499 4599 4699 4797 4897

11,000ACTUAL 2510 2564 2617 2671 2724 2778

FACTORED 4184 4274 4362 4452 4540 4630

10,000ACTUAL 2386 2434 2483 2531 2580 2628

FACTORED 3977 4057 4139 4219 4300 4380

15,300ACTUAL 3279 3362 3445 3528 3611

FACTORED 5465 5604 5742 5880 6019

15,000ACTUAL 3228 3308 3388 3468 3548

FACTORED 5380 5514 5647 5780 5914

14,000ACTUAL 3059 3128 3197 3266 3336

FACTORED 5099 5214 5329 5444 5560

13,000ACTUAL 2904 2968 3033 3098 3163 3227

FACTORED 4840 4947 5055 5164 5272 5379

12,000ACTUAL 2767 2830 2892 2955 3018 3081

FACTORED 4612 4717 4820 4925 5030 5135

11,000ACTUAL 2624 2681 2737 2794 2850 2907

FACTORED 4374 4469 4562 4657 4750 4845

10,000ACTUAL 2489 2540 2591 2643 2694 2745

FACTORED 4149 4234 4319 4405 4490 4575

SPEED WEIGHT — 1000 LB10 11 12 13 14 15 15.3

VREF &LDG CLIMB 105 110 115 119 123 127 129

APPROACHCLIMB 111 116 121 126 130 135 136

6000

FT

4000

FT

CL-102BP-58 April 2001

Change 1ALL

EFFECTIVITY



TEMP°F 0 20 40 60 80 100

°C -18 -7 4 16 27 38


15,300ACTUAL 3456 3550 3645 3739

FACTORED 5760 5917 6075 6232

15,000ACTUAL 3398 3489 3580 3671

FACTORED 5664 5815 5967 6119

14,000ACTUAL 3206 3285 3364 3443 3522

FACTORED 5344 5475 5607 5739 5870

13,000ACTUAL 3041 3115 3189 3263 3337

FACTORED 5069 5192 5315 5439 5562

12,000ACTUAL 2901 2972 3044 3116 3187

FACTORED 4835 4954 5074 5194 5312

11,000ACTUAL 2745 2809 2873 2938 3002

FACTORED 4575 4682 4789 4897 5004

10,000ACTUAL 2598 2656 2715 2773 2831

FACTORED 4330 4427 4525 4622 4719

15,300ACTUAL 3666 3766 3867

FACTORED 6110 6277 6445

15,000ACTUAL 3600 3697 3793 3890

FACTORED 6000 6162 6322 6484

14,000ACTUAL 3381 3465 3549 3633

FACTORED 5635 5775 5915 6055

13,000ACTUAL 3205 3284 3362 3440 3519

FACTORED 5342 5474 5604 5734 5865

12,000ACTUAL 3060 3136 3212 3288 3364

FACTORED 5100 5227 5354 5480 5607

11,000ACTUAL 2888 2956 3024 3093 3161

FACTORED 4814 4927 5040 5155 5269

10,000ACTUAL 2727 2789 2851 2913 2975

FACTORED 4545 4649 4752 4855 4959

SPEED WEIGHT — 1000 LB10 11 12 13 14 15 15.3

VREF &LDG CLIMB 105 110 115 119 123 127 129

APPROACHCLIMB 111 116 121 126 130 135 136

1000

0 FT

8000

FT

CL-102B April 2001 E-i

ALL

EFFECTIVITY

EMER

GEN

CYb

EMERGENCY PROCEDURES

This section contains those operating procedures requiring the use of spe-cial systems and/or regular systems in order to protect the occupants andthe aircraft from harm during a critical situation requiring immediateresponse.

The procedures located in this section supplement Normal Procedureswhen an emergency condition exists. Use of Normal Procedures should becontinued when applicable. Sound judgement as well as thorough knowl-edge of the aircraft, its characteristics, and the flight manual proceduresare essential in the handling of any emergency situation.

In addition to the outlined items in the emergency procedures, the follow-ing steps are considered part of all emergency situations:

• Maintain Airplane Control

• Analyze the Situation

• Take Proper Action

CL-102B

E-ii

April 2001A

LLEFFEC

TIVITY

EMERGENCY

LOHYD

FUELXFLO

L LOOIL

R LOOIL

LSTALL

RSTALL

CURLIM

LOWFUEL

L FUELPRESS

R FUELPRESS

SPOILER DOOR AUGAIL

PITOTHT

FUELFILTER

PRIINV

SECINV

AUXINV

SPARESTAB

OV HTWSHLDOV HT

STEERON

BLEEDAIR L

BLEEDAIR R

ENG FIREPULL

L ENGICE

R ENGICE

L FUELCMPTR

R FUELCMPTR

L VGMON

R VGMON

MACHTRIM

NAC HTON

LGEN

RGEN

CABALT

WINGOV HT

WSHLDHT

ALCAI

BAT140

BAT160

T.O.TRIM

ENG FIREPULL

DEPLOY ARM

16 16

TR-4000 THRUSTREVERSER ANNUNCIATORS

ENGSYNC

UNLOCK DEPLOY BLEEDVALVE

16 16

AERONCA THRUSTREVERSER ANNUNCIATORS

LEFT SIDE

RIGHT SIDE

LH ENGCHIP

RH ENGCHIP

PITCHTRIM

2

1 1

5

3 3 2 2

5

99

11313

WSHLDDEFOG

L R

8 8

15 15

88

OIL PRESS

LO OIL PRESS

CL-102B April 2001 E-1ALL

EFFECTIVITY

b

EMERGENCY PROCEDURESDOORS

DOOR LIGHTELECTRICAL

AC INVERTER FAILURE — TOTALBATTERY OVERHEAT LIGHT(S) (NICAD ONLY)CURRENT LIMITER FAILUREESSENTIAL BUS FAILURE — DC POWER LOSSGENERATOR FAILURE (DUAL)

ENGINEENGINE FAILUREENGINE FIRE — SHUTDOWNAIRSTART ENVELOPESTARTER–ASSIST AIRSTART (FUEL COMPUTER ON)WINDMILLING AIRSTART (FUEL COMPUTER ON)STARTER–ASSIST AIRSTART (FUEL COMPUTER OFF)WINDMILLING AIRSTART (FUEL COMPUTER OFF)OIL PRESSURE LIGHT

ENVIRONMENTAL/DOORBLEED AIR LIGHTCABIN ALTITUDE WARNING HORN ACTIVATES OR

CABIN ALTITUDE EXCEEDS 10,000 FEET(EMERGENCY DESCENT)

FIRECABIN/COCKPIT FIRE, SMOKE, OR FUMES

FLIGHT CONTROLSCONTROL SYSTEM JAMOVERSPEED RECOVERY — OVERSPEED WARNING

HORN ACTIVATESPITCH AXIS MALFUNCTION

1

3

2

4

6

5

7

8

TAB

12

TAB

9

11

10

CL-102BE-2 April 2001

Change 1ALL

EFFECTIVITY

FLIGHT CONTROLS (CONT)ROLL OR YAW AXIS MALFUNCTION

FUELFUEL PRESS LIGHT

LANDINGSDITCHINGEMERGENCY BRAKINGEMERGENCY EVACUATIONLANDING — BOTH ENGINES INOP

STALL WARNINGSTALL WARNING ACTIVATES

TAKEOFFABORTED TAKEOFF

THRUST REVERSERSINADVERTENT THRUST REVERSER

DEPLOYMENT DURING TAKEOFFINDICATION OF THRUST REVERSER DEPLOYMENT

DURING TAKEOFF (TR-4000 THRUST REVERSERS ONLY)

13

14

TAB

TAB

15

16

Change 1


EFFECTIVITY

b

CREW NOTES

1

CL-102BE-4 April 2001ALL

EFFECTIVITY

DOOR LIGHT ILLUMINATED

If light was accompanied by evidence of door failure:

• DO NOT APPROACH DOOR

1. FASTEN SEAT BELT Switch .......................................................ON

2. Cabin Altitude .............................................UP TO MAX POSSIBLE

3. Airspeed ............................................................................REDUCE

4. Establish descent.

5. Land as soon as practical.

If light was not accompanied by evidence of door failure:

• DO NOT APPROACH DOOR

1. FASTEN SEAT BELT Switch .......................................................ON

2. Continue Flight. Probable cause is latch pin switch malfunction.

DOOR

CL-102B April 2001 E-5Change 1

ALLEFFECTIVITY

b

AC INVERTER FAILURE — TOTAL

1. Maintain aircraft control by reference to the standby attitude gyro.

2. Avoid flight in instrument conditions.

3. AC BUS TIE CB (Copilot’s Panel) ........................................... PULL

4. PRI & SEC INV CBs (Pilot’s & Copilot’s Main Power Bus)and L & R AC BUS CBs (Pilot’s & Copilot’s AC Bus) ....................IN

5. AC Load ............................................................................ REDUCE

6. Inverter Switches ......................................................OFF THEN ON

If AC power is not regained:

7. PRI & SEC INV CBs ................................................PULL & RESET

8. If AC power is not regained, the following is a partial list of equip-ment that will not be usable:

• Vertical & Directional Gyros• Autopilot• Yaw Dampers• Mach Trim System• Avionics Displays• Electrical Servoed Altimeter(s)• Engine Oil Pressure Indicators• Spoilerons • Spoilers (inoperative in flight only)• Nose Wheel Steering• Windshield Electric Defog (if installed)

9. Mach Trim will be inoperative. Do not exceed MMO (.74MI).

10. Maintaining not less than 250 KIAS until approach will improvestability.

2

PRIINV

SECINV

Change 1

1


EFFECTIVITY

BATTERY OVERHEAT LIGHT(S)(NICAD ONLY)

If BAT 140 Light Illuminates:

1. BAT TEMP Indicator ........................................................ MONITOR

2. Affected Battery .........................................................................OFF



1. BAT TEMP Indicator ........................................................ MONITOR

2. Affected Battery .........................................................................OFF

3. Land as soon as possible.

CURRENT LIMITER FAILURE

1. DC Voltmeter ....................................................................... CHECK

Both current limiters have failed if battery voltage is 25 volts or less.2. • If one current limiter failed:

a. Electrical Load .....................OBSERVE GENERATOR LIMITS

•If both current limiters failed:

a. Electrical Load ......................................REDUCE & MONITOR

b. Land as soon as practical.

3. Replace failed current limiter(s) before next flight.

BAT140

BAT160

CURLIM

35-001 thru 35-508, 36-001 thru 36-053 not incorporating AMK 85-1

EFFECTIVITY

2


EFFECTIVITY

b

ESSENTIAL BUS FAILURE — DC POWER LOSSAffected Essential Bus:

1. ESS BUS TIE CB (copilot’s panel) .......................................... PULL

2. Essential Bus Load............................................................ REDUCE

a. Autopilot Switch .................................................................OFF

b. Instrument Panel Lights (if conditions permit) ....................OFF

c. Do not operate the following at the same time:

(1) Pitch, Roll & Yaw Trims

(2) Communication Transmissions

(3) Fuel Transfer & Standby Pumps

(4) Flaps

(5) Landing Gear

3. ESS BUS CB ....................................................................... RESET

If ESS BUS CB does not hold:4. Wait at least one minute before attempting reset.

If ESS BUS CB holds after being reset:5. Add loads only as necessary. Do not reset ESS BUS TIE Circuit

Breaker.


3

35-001 thru 35-201 & 35-205; and 36-001 thru 36-040 not incorporating AMK 78-13

EFFECTIVITY

2


EFFECTIVITY

If ESS BUS CB opens again:6. Essential Bus Load............................................................REDUCE

a. Autopilot Switch .................................................................OFF

b. Both Audio Panels ................................. PH (use headphones)

c. Instrument Panel Lights .................................. OFF, AS REQ’D

d. Do not operate the following at the same time:

(1) Pitch, Roll & Yaw Trims

(2) Communication Transmissions

(3) Fuel Transfer & Standby Pumps

(4) Flaps

(5) Landing Gear

e. Pull the following circuit breakers on the failed essential bus:

(1) COMM

(2) S WARN HT

(3) PITOT HT

(4) Yaw Damper

f. Select the following primary or secondary systems for opera-tion from the remaining essential bus:

(1) Pitch Trim

(2) ATC Transponder 1 or 2

(3) COMM 1 or COMM 2

(4) Yaw Damper

g. ESS BUS TIE CB.......................................................... RESETFrequently cross-check airspeed/Mach, altitude, and angle-of-attack displays against opposite system. Use reference fromsystem on opposite essential bus if differences exist and icingconditions are present.


EFFECTIVITY

3


ALLEFFECTIVITY

b

GENERATOR FAILURE (DUAL)

1. Electrical Load................................................................... REDUCEa. Air Conditioner ...................................................................OFFb. Aux Heat (if installed).........................................................OFFc. Windshield Aux Defog (if installed) ....................................OFF

2. IGN & ST CBs (main power buses)..................... CHECK & RESET3. Start-Gen Switches.................................................................. GEN4. Generator Reset Switches........................ DEPRESS (momentarily)

If generators do not reset:5. Turbine Speed (N2).................................................. 80% or ABOVE6. Start-Gen Switches...................................................OFF, then GEN7. Generator Reset Switches........................ DEPRESS (momentarily)

If generators do not reset:8. Start-Gen Switches....................................................................OFF

9. Jet Pumps....................................................................................ON

10. Fuel Computer Switches (one at a time) ...................................OFF

a. Engine response will be much slower.

b. If an engine accelerates uncontrolled,Applicable Fuel Computer Switch ........................................ON

11. If there is fuel in fuselage tank,

• Aircraft without Fuselage Valve Switch:a. XFER-FILL Switch ...........................................................XFER

b. FUSLG PMP CB (copilot’s main bus) .............................. PULL

• Aircraft with Fuselage Valve Switch:a. Fuselage Valve ...............................................................OPEN


13. All Non-essential Equipment .......................... OFF or CBs PULLED

Fully charged batteries should power minimum equipment for night IFR for approximately 30 minutes.


LGEN

RGEN

Change 1

3


EFFECTIVITY

If ship’s batteries are depleted:

14. Power will be supplied by emergency battery.

a. Emergency Power............................................................STBY

b. For gear & flap operation, Emergency Power ......................ON

15. Secondary Emergency Power (if installed) .................................ON

16. Refer to Supplemental Data, pages S-6 and S-7 for a list of condi-tions using emergency batteries.

ENGINE FAILUREDURING TAKEOFFBelow V1 Speed:

1. Thrust Levers.......................................................................... IDLE

2. Wheel Brakes ...................................................................... APPLY

3. Spoilers............................................................................. EXTEND

4. Drag Chute or Thrust Reversers (if installed) .............................................DEPLOY, IF NECESSARY

Above V1 Speed:

1. Rudder & Ailerons .........................................................AS REQ’D

2. Accelerate to VR. Keep nose wheel on runway.

3. Rotate at VR; Climb at V2.

4. Positive Rate Of Climb Established ..............................GEAR UP

5. Clear of Obstacles ..........................................V2 + 30, FLAPS-UP

6. Fuel Jettison ................................................................................ON

Fuel Jettison .............................................OFF (prior to touchdown)

7. Refer to ENGINE SHUTDOWN IN FLIGHT procedure, Tab 5,Abnormal Checklist or ENGINE FIRE — SHUTDOWN procedure,Tab 5, this section.


4


EFFECTIVITY

b

IN FLIGHT1. Control Wheel Master Switch (MSW) .........DEPRESS & RELEASE

2. Rudder & Ailerons ........................................................... AS REQ’D

3. Thrust Lever (operative engine) .................. INCREASE, AS REQ’D

4. Engine Sync ..............................................................................OFF

5. Rudder Trim..................................................................... AS REQ’D

6. Yaw Damper ......................................................................ENGAGE

7. Autopilot...................................................................... AS DESIRED

8. Refer to ENGINE SHUTDOWN IN FLIGHT procedure, Tab 5,Abnormal Checklist.

DURING APPROACH

1. Control Wheel Master Switch (MSW)...........................DEPRESS

2. Thrust Lever (operative engine)............. INCREASE, AS REQ’D

3. Flaps ..................................................................................20° MAX

4. Airspeed .................................................................. VREF + 10 MIN




8. Refer to applicable procedure(s):

• SINGLE-ENGINE LANDING procedure, Tab 14, Abnormal Check-list.

• GO AROUND procedure, Normal Checklist.• ENGINE SHUTDOWN IN FLIGHT procedure, Tab 5, Abnormal

Checklist.5

4


EFFECTIVITY

ENGINE FIRE — SHUTDOWNAffected Engine:

1. Thrust Lever...................... IDLE, UNLESS A CRITICAL THRUSTSITUATION EXISTS

2. • If fire continues more than 15 seconds or there are otherindications of fire:a. Thrust Lever ..............................................................CUTOFFb. Engine Fire Pull Handle .................................................PULLc. ARMED Light ................................................. DEPRESS ONEd. • If fire continues:

(1) Remaining ARMED light ...................................DEPRESS(2) Land as soon as possible.(3) Go to step e.

• If fire extinguishes:(1) Land as soon as practical.(2) Go to step e.

e. Ignition ...............................................................................OFFf. Engine Sync ......................................................................OFFg. Yaw Damper OFF, retrim, then...................................ENGAGEh. Jet Pump & Standby Pump ................................................OFFi. Start-Gen Switch ................................................................OFFj. Electrical Load ......................................... REDUCE, IF REQ’Dk. Crossflow Valve....................OPEN, CROSSFLOW AS REQ’Dl. Refer to SINGLE-ENGINE LANDING procedure, Tab 14,

Abnormal Checklist.• If fire extinguishes in less than 15 seconds:

a. Leave thrust lever at IDLE, unless a critical thrust situationexists.

b. Engine Sync.......................................................................OFFc. Yaw Damper OFF, retrim, then...................................ENGAGEd. Fuel Balance .................MONITOR, CROSSFLOW AS REQ’De. Land as soon as practical.f. Refer to SINGLE-ENGINE LANDING procedure, Tab 14,

Abnormal Checklist.

ENG FIREPULL

5


EFFECTIVITY

b

AIRSTART ENVELOPE

Fuel computer ON starter assist airstarts may be made at any stabilizedN2 up to 45%, and any altitude up to 30,000 feet.

Maintaining an airspeed which will maintain a minimum 15% N2 willenhance airstart capability.

Starter-assist airstarts must be used when N2 is below 15%.

Do not attempt Fuel Computer OFF airstarts above 20,000 feet.6

0 5 10 15 20 250

5

10

15

20

25

30

TURBINE SPEED (N2) — %

AL

TIT

UD

E —

100

0 F

EE

T

WINDMILLAIRSTART

FUEL COMPUTERON ONLY

FUEL COMPUTERON OR OFF

5


EFFECTIVITY

STARTER–ASSIST AIRSTART(FUEL COMPUTER ON)

Affected Engine:

1. Assure airstart envelope.2. Thrust Lever .......................................................................CUTOFF

Wait 10 seconds for fuel to drain.3. Fuel Supply:

a. Fuel available from wing tank.b. Engine Fire Pull Handle ............................................. PUSH IN

4. Fuel Panel:a. Jet Pump or Standby Pump .................................................ONb. Crossflow Valve.............................................................CLOSEc. Transfer-Fill .......................................................................OFFd. Fuselage Valve (if installed) ..........................................CLOSE

5. Electrical Load ...................................................................REDUCE6. Nacelle Heat ..............................................................................OFF7. Bleed Air ....................................................................................OFF8. Start-Gen Switch....................................................................START9. Thrust Lever @ 10% N2 & Fan Rotation .................................. IDLE

10. Air Ignition Light & Fuel Flow............................................... CHECK11. Turbine Temp (ITT) .................................... RISE (within 5 seconds)12. If no light-off within 5 seconds,

SPR Switch................................ENERGIZE UNTIL 300° - 400° ITT13. Air Ignition & Starter Engaged Lights (if installed) .................... OUT14. Start-Gen Switch..........................................................GEN @ IDLE15. Engine Instruments............................................................NORMAL16. Bleed Air ......................................................................................ON17. Nacelle Heat .................................................................... AS REQ’D

If no light-off within 10 seconds total:

18. Thrust Lever .......................................................................CUTOFF19. Start-Gen Switch........................................................................OFF20. Repeat STARTER-ASSIST AIRSTART (FUEL COMPUTER ON)

procedure.(Procedure Continued)

6


EFFECTIVITY

b

If engine will not restart:

21. Perform WINDMILLING AIRSTART (FUEL COMPUTER ON) pro-cedure, Tab , this section.

After both engines are operating:

22. Starter Disengagement (if required) .....................................CHECK23. Current Limiters ....................................................................CHECK

WINDMILLING AIRSTART(FUEL COMPUTER ON)

Affected Engine:

1. Assure airstart envelope (15% N2 & fan rotation).2. Thrust Lever .......................................................................CUTOFF


a. Fuel available from wing tank.b. Engine Fire Pull Handle ..............................................PUSH IN

4. Fuel Panel:a. Jet Pump..............................................................................ON b. Standby Pump......................................................................ONc. Crossflow Valve ............................................................CLOSEd. Transfer-Fill .......................................................................OFFe. Fuselage Valve (if installed) ..........................................CLOSE

5. Start-Gen Switch........................................................................OFF6. Electrical Load................................................................... REDUCE7. Nacelle Heat ............................................................................. OFF8. Bleed Air ....................................................................................OFF9. Air Ignition....................................................................................ON

10. Thrust Lever ........................................ IDLE, CHECK FUEL FLOW11. Turbine Temp (ITT).................................... RISE (within 5 seconds)12. If no light-off within 5 seconds,

SPR Switch................................ENERGIZE UNTIL 300° - 400° ITT13. Air Ignition................................................................OFF @ 45% N2

14. Start-Gen Switch..........................................................GEN @ IDLE15. Engine Instruments........................................................... NORMAL


7

6


EFFECTIVITY

16. Standby Pump ...........................................................................OFF17. Bleed Air .....................................................................................ON18. Nacelle Heat .................................................................... AS REQ’D

If no light-off within 10 seconds:19. Thrust Lever ......................................................................CUTOFF20. Air Ignition..................................................................................OFF21. Perform WINDMILLING AIRSTART (FUEL COMPUTER ON) pro-

cedure or STARTER–ASSIST AIRSTART (FUEL COMPUTER ON)procedure, Tab , this section.

If engine will not restart:22. Perform ENGINE SHUTDOWN IN FLIGHT procedure, Tab 5,

Abnormal Checklist.

STARTER–ASSIST AIRSTART(FUEL COMPUTER OFF)

Affected Engine:

1. Assure airstart envelope (below 20,000 feet)2. Fuel Computer...........................................................................OFF3. Thrust Lever .......................................................................CUTOFF



5. Fuel Panel:a. Standby Pump......................................................................ONb. Jet Pump ...........................................................................OFFc. Crossflow Valve.............................................................CLOSEd. Transfer-Fill .......................................................................OFFe. Fuselage Valve (if installed) ..........................................CLOSE

6. Electrical Load ...................................................................REDUCE7. Nacelle Heat ............................................................................. OFF8. Bleed Air ....................................................................................OFF9. Start-Gen Switch....................................................................START

10. Thrust Lever @ 10% N2 & Fan Rotation .................................. IDLE


7


EFFECTIVITY

b

11. Air Ignition Light & Fuel Flow................................................CHECK12. Turbine Temp (ITT).................................. RISE (within 10 seconds)13. Start-Gen Switch:

a. @ 45% N2..........................................................................OFFb. @ Idle................................................................................ GEN

14. Air Ignition & Starter Engaged Lights (if installed) .....................OUT15. Engine Instruments ......................................................... MONITOR16. Bleed Air .....................................................................................ON17. Nacelle Heat .................................................................... AS REQ’D

If no light-off within 10 seconds:18. Thrust Lever ......................................................................CUTOFF19. Start-Gen Switch........................................................................OFF20. Repeat STARTER-ASSIST AIRSTART (FUEL COMPUTER OFF)

procedure. If engine will not restart:21. Perform WINDMILLING AIRSTART (FUEL COMPUTER OFF) pro-

cedure, next page.

After both engines are operating:22. Starter Disengagement (if required) .....................................CHECK23. Current Limiters ....................................................................CHECK

8

7


EFFECTIVITY

WINDMILLING AIRSTART(FUEL COMPUTER OFF)

Affected Engine:

1. Assure airstart envelope (15% N2, 10% N1 & below 20,000 feet)2. Fuel Computer...........................................................................OFF3. Thrust Lever .......................................................................CUTOFF



5. Fuel Panel:a. Jet Pump............................................................................OFF b. Standby Pump......................................................................ONc. Crossflow Valve.............................................................CLOSEd. Transfer-Fill .......................................................................OFFe. Fuselage Valve (if installed) ..........................................CLOSE

6. Start-Gen Switch........................................................................OFF7. Electrical Load ...................................................................REDUCE8. Nacelle Heat ............................................................................. OFF9. Bleed Air ....................................................................................OFF

10. Air Ignition....................................................................................ON 11. Thrust Lever ........................................ IDLE, CHECK FUEL FLOW12. Turbine Temp (ITT) .................................. RISE (within 10 seconds)13. Engine Instruments......................................................... MONITOR14. Air Ignition................................................................OFF @ 45% N2

15. Start-Gen Switch..........................................................GEN @ IDLE16. Bleed Air ......................................................................................ON17. Nacelle Heat .................................................................... AS REQ’D

If no light-off within 10 seconds:18. Thrust Lever .......................................................................CUTOFF19. Air Ignition..................................................................................OFF20. Perform WINDMILLING AIRSTART (FUEL COMPUTER OFF) pro-

cedure or STARTER–ASSIST AIRSTART (FUEL COMPUTEROFF) procedure, Tab 7, this section.


8


EFFECTIVITY

b

If engine will not restart:

21. Perform ENGINE SHUTDOWN IN FLIGHT procedure, Tab 5,Abnormal Checklist.

OIL PRESSURE LIGHT(S)

1. Both Oil Pressure Indicators.................................................CHECK

Affected Engine:

2. Oil Temperature Indicator .....................................................CHECK

3. •Oil pressure is less than 25 psi:

If flight conditions permit, shut down affected engine. Refer toENGINE SHUTDOWN IN FLIGHT procedure, Tab 5, AbnormalChecklist.

•Oil pressure is between 25 & 38 psi or oil temperature is high:

If flight conditions permit, reduce power to maintain oil temperature limits.

•Oil pressure & oil temperature are normal:

Continue to monitor engine operation.

9

L LOOIL

R LOOIL

OR

OILPRESS

LO OILPRESS

OR

8


EFFECTIVITY

BLEED AIR LIGHT

1. Corresponding BLEED AIR Switch ...........................................OFF

BLEEDAIR L

BLEEDAIR R

35-001 thru 35-081 & 35-083 thru 35-086; and 36-001 thru 36-022 not incorporating AMK 76-7

EFFECTIVITY

9


EFFECTIVITY

b

CABIN ALTITUDE WARNING HORN ACTIVATES OR CABIN ALTITUDE EXCEEDS 10,000 FEET (EMERGENCY DESCENT)

1. Crew Oxygen Masks.................................. DON & SELECT 100%


3. Autopilot.....................................................................DISENGAGE

4. Spoilers .............................................................................EXTEND

5. Landing Gear (Below MMO or VLE) .....................................DOWN

6. Descend at MMO/VLE, but not below minimum safe altitude.

7. PASS OXY Valve .................................................................. NORM

8. PASS MASK Valve ..................................................................MAN

If time and conditions permit:

9. OXY-MIC Switches ......................................................................ON

10. Transponder ............................................................................. 7700

11. Notify ATC.

12. Check and assist passengers.

10

9


Change 1ALL

EFFECTIVITY

CABIN/COCKPIT FIRE, SMOKE, OR FUMES1. Crew Oxygen Masks.................................. DON & SELECT 100%2. Smoke Goggles ............................................DON, IF AVAILABLE3. OXY-MIC Switches.....................................................................ON

Whether or not smoke has dissipated, if it cannot be visibly verified thatthe fire has been extinguished:

4. Cockpit Door/Curtain ..............................................................OPEN5. Land as soon as possible.6. If source is known:

a. Extinguish fire using hand held extinguisher or eliminate thesource of smoke or fumes.

b. • If fire is not extinguished:(1) Land as soon as possible.(2) This checklist is complete.

• If fire has been extinguished and can be visibly verified:(1) Land as soon as practical. At the crew’s discretion, the oxy-

gen system may be returned to normal.(2) This checklist is complete.

If smoke or fumes continue:7. CABIN AIR Switch .................................................................... MAX8. AUTO-MAN Switch ................................................................... MAN9. UP-DN Manual Control ......................................UP (max. 13,000 ft)

If time & conditions permit, isolate source of smoke and fumes:10. • If bleed air system is suspected source:

a. R BLEED AIR Switch .........................................................OFF• If smoke is reduced, continue with switch OFF.• If smoke is not reduced:

(1) R BLEED AIR Switch ....................................................ON(2) L BLEED AIR Switch...................................................OFF

If smoke is reduced, continue with switch OFF.

(Procedure Continued)Change 1

35-001 thru 35-106 & 35-108 thru 35-112; and 36-001 thru 36-031

EFFECTIVITY

10


ALLEFFECTIVITY

b

• If source is electrical:a. All Non-essential Electrical Equipment ..............................OFFb. Isolate defective systems bus as follows:

The following steps separate the pilot and copilot electricalsystems. If the electrical smoke or fume source is positivelyidentified on the pilot side, pull all BUS TIE circuit breakers onthe copilot circuit breaker panel and proceed with step (4).(1) Copilot’s Circuit Breaker Panel — Pull the following circuit

breakers:

All electrical power from the copilot’s circuit breaker panel isnow off. Allow time for smoke and fumes to dissipate.

If electrical smoke or fumes continue:(2) All BUS TIE Circuit Breakers....................LEAVE PULLED

DO NOT RESET(3) All other Copilot Circuit Breakers ........................... RESET(4) Pilot’s Circuit Breaker Panel — Pull the following circuit

breakers:

All electrical power from the pilot’s circuit breaker panel is nowoff. Allow time for smoke and fumes to dissipate.


TOP ROW 3RD ROWAC BUS TIE ESS BUS TIER AC BUS R ESS BUS

R AUX AC BUS (if installed) R STALL WARN26 VAC BUS AUX INV (if installed)

2ND ROWMAIN BUS TIE R MAIN BUS R IGN & ST

SEC INV

TOP ROW 3RD ROWL AC BUS L ESS BUS

L AUX AC BUS (if installed) L STALL WARN26 VAC BUS DOOR ACTR

ENTRY LT

2ND ROWL MAIN BUS L IGN & ST

PRI INV


EFFECTIVITY

10


Change 1ALL

EFFECTIVITY

If electrical smoke or fumes continue, the malfunctioningsystem is connected to the Emergency Power Supply(ies). Inthis event:

(5) EMER BAT or EMER PWR Switch(es) — OFF.

To restore unaffected electrical systems if necessary (determination of defective system):

11. All BUS TIE Circuit Breakers ..................................LEAVE PULLEDDO NOT RESET

12. All Circuit Breakers (on panel with power removed)................ PULL

13. One (DC) BUS Circuit Breaker ............................................. RESET

a. Circuit Breakers powered by that BUS.......................... RESET(one at a time)

• Pause after resetting each circuit breaker to determine defec-tive system.

• Whenever high electrical loads or smoke or fumes occur, pullthe last circuit breaker reset.

• Hot-wired circuit breakers (L and R STALL WARN, DOORACTR, ENTRY LT, PRI INV and SEC INV circuit breakers)should be reset in sequence with the other circuit breakers onthat bus row.

14. Repeat step 13 for each DC BUS Circuit Breaker.

15. R AC BUS or L AC BUS Circuit Breaker (as applicable) ...... RESET

a. Reset circuit breakers powered by that AC BUS. (Refer tonotes under step 13 above).

16. EMER BAT or EMER PWR Switch(es)............... ON (one at a time)

If smoke and fumes recur, set switch OFF.

17. Standby Attitude Gyro...................... CAGE, then UNCAGE to erect

11


EFFECTIVITY

b

CONTROL SYSTEM JAMRefer to PITCH AXIS MALFUNCTION procedure, Tab , this section, orROLL OR YAW AXIS MALFUNCTION procedure, Tab , this section, toclear difficulty. If problem not corrected, attempt to overpower jam. If jamcan be overpowered, make normal landing. For landing with control jam,fly long, straight-in approach and establish final configuration at a safealtitude.AILERON JAM

1. Rudder...................................AS REQ’D TO MAINTAIN CONTROL

• Yaw Damper ........................................................................ON

• Crossflow Valve ..............................................................OPEN

• Standby Pumps....................................................................ON

2. Approach Configuration................................GEAR DN, FLAPS 20°

3. Approach Speed...............................................................VREF + 10

4. Maintain power to touchdown and do not flare.

ELEVATOR JAM1. Primary Pitch Trim .................AS REQ’D TO MAINTAIN CONTROL




RUDDER JAM1. Aileron ...................................AS REQ’D TO MAINTAIN CONTROL

2. Use asymmetric power if required to minimize sideslip.

• Crossflow Valve ..............................................................OPEN

• Standby Pumps....................................................................ON




6. After landing, maintain directional control with differential braking.

11


EFFECTIVITY

OVERSPEED RECOVERY — OVERSPEEDWARNING HORN ACTIVATES


2. Autopilot.................................................................... DISENGAGE

3. Identify aircraft pitch and roll attitude.

4. Level wings.

5. Elevator and Pitch Trim............................... NOSE UP AS REQ’D

If Mach or airspeed is severe or if pitch and/or roll attitude is ex-treme or unknown:6. Landing Gear ......................... DOWN, DO NOT RETRACT GEAR

12


EFFECTIVITY

b

PITCH AXIS MALFUNCTION1. Control Wheel Master Switch (MSW)............ DEPRESS & HOLD2. Attitude Control .............................................................AS REQ’D3. Thrust Levers:

• If high-speed nose-down attitude..................................... IDLE• If near stall ............................................. INCREASE AS REQ’D

4. Both Stall Warning Switches ..................................................OFF5. Pitch Trim Switch.....................................................................OFF6. Autopilot Switch ......................................................................OFF

7. Control Wheel Master Switch ...........................................RELEASE


If conditions permit, isolate malfunction:9. Pitch Trim Switch........................................................PRI then SEC

• If malfunction recurs in PRI or SEC trim:a. Select opposite system and use for remainder of flight.

b. Malfunctioning System CB — PITCH TRIM(pilot’s ess bus) or SEC PITCH TRIM (copilot’s ess bus) PULL

c. If Mach Trim & Autopilot Inoperative ..................MMO = 0.74 MI

• If malfunction does not recur:a. Pitch Trim Switch ....................................................PRI or SEC

b. Do not engage autopilot.

• If pitch trim cannot be restored, refer to JAMMED STABILIZERLANDING procedure, Tab 14, Abnormal Checklist.

10. Stall Warning Systems (one at a time).........................................ON

• If malfunction recurs, set malfunctioning system switch OFF andrefer to STALL WARNING SYSTEM FAILURE procedure, Tab 8,Abnormal Checklist.

• If malfunction does not recur, do not engage autopilot.

11. Autopilot (if not cause of malfunction) ........................ AS DESIRED

12. Yaw Damper (PRI or SEC) ................................................ENGAGE

12


EFFECTIVITY

ROLL OR YAW AXIS MALFUNCTION1. Control Wheel Master Switch .......................................DEPRESS

2. Attitude Control .............................................................AS REQ’D

If control force continues:3. Airspeed ...........................................................................REDUCE

4. Affected Axis Trim CB — ROLL TRIM orYAW TRIM (pilot’s ess bus)...................................................PULL

5. • If malfunction isolated to yaw damper:

a. Select opposite yaw damper.

• If malfunction isolated to autopilot:

a. Do not engage autopilot.

b. Reengage yaw damper.

• If malfunction isolated to roll or yaw trim:a. Minimize mistrim by using:

• asymmetric thrust

• fuel imbalance

b. Land as soon as practical.

13


EFFECTIVITY

b

FUEL PRESS LIGHT

Affected Engine:

1. Thrust Lever .......................................................................RETARD

2. Standby Pump .............................................................................ON

3. Ignition .........................................................................................ON

4. Crossflow Valve ....................................................................CLOSE

5. Transfer-Fill ...............................................................................OFF

6. Fuselage Valve (if installed)..................................................CLOSE

7. Jet Pump .....................................................................................ON

If FUEL PRESS light does not extinguish:

8. Jet Pump ...................................................................................OFF

If FUEL PRESS light does not extinguish:

9. Descend to 25,000 feet or lower.

14

L FUELPRESS

R FUELPRESS

13


EFFECTIVITY

DITCHING1. If time permits:

a. Head toward nearest land or vessel.

b. Notify ATC.

c. Transponder...................................................................... 7700

d. ELT (if installed) ...................................................................ON

e. Life Vests..............................................................................ON

f. Passengers .................................................................... BRIEF

• Use of flotation equipment.

• Emergency Exits - Do not open lower half of cabin door.

• Secure loose items.

• Brace position for emergency landing.

• Do not release seat belts until stopped.

g. No Smoking/Fasten Seat Belt Sign......................................ON

h. Fuel Jettison........................ ON (until complete or touchdown)

2. Landing Gear............................................................................... UP

3. Flaps......................................................................................DOWN

4. Cabin Air ....................................................................................OFF

5. Emergency Power .....................................................................OFF

6. Approach ..............................................................NORMAL at VREF

• Calm Sea - Land into wind.

• Moderate Swells - Land parallel to swells.

• High Winds - Land into wind on upwind side of swell.

7. Thrust Levers........................................CUTOFF @ TOUCHDOWN

8. Engine Fire Pull Handles ......................................................... PULL

9. Batteries ....................................................................................OFF

10. Emergency Exits (after full stop).............................................OPEN

DO NOT OPEN LOWER HALF OF CABIN DOOR

14


EFFECTIVITY

b

EMERGENCY BRAKINGAnti-skid protection is not available during emergency braking.

1. Emergency Brake Handle ............................................ PULL OUT

2. Emergency Brake Handle .............................PUSH DOWNWARD

3. Rudder and/or Nose Wheel Steering............................... AS REQ’D

EMERGENCY EVACUATION1. Stop the aircraft.

2. Parking Brake .......................................................................... SET

3. Thrust Levers....................................................................CUTOFF

4. • If an engine fire is suspected:

a. Applicable Engine Fire Pull Handle..............................PULL

b. ARMED Light ................................................. DEPRESS ONE

c. Other Engine Fire Pull Handle ......................................PULL

• If engine fire is not suspected:

a. Both Engine Fire Pull Handles......................................PULL

5. Batteries ...................................................................................OFF

6. Evacuate the aircraft:

a. Cabin Entry Door ................................................OPEN & EXIT

b. Aft Cabin Emergency Exit ...................................OPEN & EXIT

15

14


EFFECTIVITY

LANDING — BOTH ENGINES INOPAirplane Best Glide Speed (gear & flaps up) is VREF + 60 KIAS.The still-air gliding distance is approximately 2 nm per 1000 feet of altitude.

1. If time permits:

a. Transponder...................................................................... 7700

b. Notify ATC.

c. Prepare passengers for emergency landing.

d. No Smoking Fasten Seat Belt Sign......................................ON

2. Fuel Jettison ................................................................................ON

Fuel Jettison .............................................OFF (prior to touchdown)

3. Auxiliary Hydraulic Pump.............................................................ON

4. Landing Gear.........................................................................DOWN

5. Flaps............................................................................FULL DOWN


7. Start-Gen Switches....................................................................OFF

8. Batteries ....................................................................................OFF

9. Emergency Power (prior to touchdown) ....................................OFF

10. Touchdown in normal landing attitude.


a. Cabin Entry Door ............................................... OPEN & EXIT

b. Aft Cabin Emergency Exit .................................. OPEN & EXIT

15


ALLEFFECTIVITY

b

STALL WARNING ACTIVATES

1. Lower the pitch attitude to reduce angle of attack.

2. Thrust Levers...................................................TAKEOFF POWER

3. Level the wings.

4. Accelerate out of the stall condition.

ABORTED TAKEOFF1. Thrust Levers.......................................................................... IDLE

2. Wheel Brakes.......................................................................APPLY

3. Spoilers .............................................................................EXTEND

4. Drag Chute or Thrust Reversers (if installed) .................. AS REQ’D

5. Refer to the AFM for further disposition.

16

L STALL

R STALL

Change 1

15


EFFECTIVITY

CREW NOTES

17

16


EFFECTIVITY

b

INADVERTENT THRUST REVERSER DEPLOYMENT DURING TAKEOFF

Below V1 Speed:



3. Spoilers .............................................................................EXTEND

To improve directional control, position both Reverser Levers toREVERSE IDLE.

Above V1 Speed:


2. Thrust Lever (affected engine) .............................................. IDLE

3. Emer Stow Switch .................................................... EMER STOW


5. Rotate at VR, Climb at V2.

6. Positive Rate Of Climb Established..............................GEAR UP

7. Clear of Obstacles ........... ACCELERATE TO V2 + 30, FLAPS UP

If UNLOCK or DEPLOY lights stay on:

8. Thrust Lever (affected engine) ...........................................CUTOFF

9. Fuel Jettison ................................................................................ON

Fuel Jettison ............................................. OFF (prior to touchdown)

10. Refer to ENGINE SHUTDOWN IN FLIGHT procedure, Tab 5,Abnormal Checklist.

DEPLOYUNLOCK

With Aeronca Thrust Reversers

EFFECTIVITY

16

CL-102BE-6.1 April 2001ALL

EFFECTIVITY

35-509 & on, 36-054 & on, and prior aircraft incorporating AMK 85-1

EFFECTIVITY

BATTERY OVERHEAT LIGHT(S)(NICAD ONLY)


1. BAT TEMP Indicator ........................................................ MONITOR2. Affected Battery .........................................................................OFF3. Land as soon as practical.


1. BAT TEMP Indicator ........................................................ MONITOR2. Affected Battery .........................................................................OFF3. Land as soon as possible.

CURRENT LIMITER FAILURE

1. DC Voltmeter ....................................................................... CHECKBoth current limiters have failed if battery voltage is 25 volts or less.

2. • If one current limiter failed:a. Electrical Load .....................OBSERVE GENERATOR LIMITS

• If both current limiters failed:a. Air Conditioner ...................................................................OFFb. Windshield Aux Defog (if installed) ...................................OFFc. Recog Light .......................................................................OFFd. Aux Heat (if installed) .........................................................OFF

3. Replace failed current limiter(s) before next flight.

BAT140

BAT160

CURLIM

2

CL-102B April 2001 E-7.1ALL

EFFECTIVITY

b

ESSENTIAL BUS FAILURE — DC POWER LOSSAffected Essential Bus:

1. ESS BUS TIE CB (copilot’s panel) .......................................... PULL

2. Essential Bus Load............................................................REDUCE

3. ESS BUS CB ....................................................................... RESET

4. Do not operate the following at the same time:

a. Pitch, Roll, & Yaw Trims

b. Fuel Transfer & Standby Pumps

c. Flaps

d. Landing Gear

If ESS BUS CB does not hold:

5. Wait at least one minute before attempting reset.

If ESS BUS CB holds after being reset:

6. Add loads only as necessary. Do not reset ESS BUS TIE CircuitBreaker.

If ESS BUS CB opens again:

7. Essential Bus Load............................................................REDUCE

8. ESS BUS CB ........................................................................ RESET

If ESS BUS CB will not stay closed and it is desired to operate a load connected to that bus only:

9. Both Affected ESS BUS Loads..........................................REDUCE

10. ESS BUS TIE CB ................................................................. RESET

11. If ESS BUS TIE CB opens, leave it open. Frequently cross-checkairspeed/Mach, altitude, and angle-of-attack displays against oppo-site system. Use reference from system on opposite essential bus ifdifferences exist and icing conditions are present.

35-202 thru 35-204, 35-206 & on; 36-041 & on; and prior aircraft incorporating AMK 78-13

EFFECTIVITY

2


EFFECTIVITY

CREW NOTES


EFFECTIVITY

3


EFFECTIVITY

BLEED AIR LIGHT

If both BLEED AIR L and BLEED AIR R warning lights illuminate, the secondary pressure regulator of one of the air modulating valves has failed.

1. R BLEED AIR Switch.................................................................OFF

• If both lights go out, continue flight in this configuration.

• If both lights do not go out, proceed to step 2.

2. R BLEED AIR Switch...................................................................ON

L BLEED AIR Switch .................................................................OFF

• If both lights go out, continue flight in this configuration.

• If both lights do not go out, proceed to step 3.

3. Reduce power alternately on each engine until both lights go out.Continue flight with the appropriate engine at reduced power.

If either BLEED AIR L or BLEED AIR R warning light illuminates, an overheat sensor has tripped the light.


BLEEDAIR L

BLEEDAIR R

35-082, 35-087 thru 35-106 & 35-108 thru 35-112; 36-023 thru 36-031; and prior aircraft incorporating

AMK 76-7

EFFECTIVITY

9


EFFECTIVITY

BLEED AIR LIGHT


BLEEDAIR L

BLEEDAIR R

35-107, 35-113 & on; and 36-032 & onEFFECTIVITY

9

CL-102BE-22.1 April 2001

Change 1ALL

EFFECTIVITY

CABIN/COCKPIT FIRE, SMOKE, OR FUMES1. Crew Oxygen Masks..................................DON & SELECT 100%2. Smoke Goggles.............................................DON, IF AVAILABLE3. OXY-MIC Switches .....................................................................ON

Whether or not smoke has dissipated, if it cannot be visibly verified thatthe fire has been extinguished:

4. Cockpit Door/Curtain ..............................................................OPEN5. Land as soon as possible.6. If source is known:

a. Extinguish fire using hand held extinguisher or eliminate thesource of smoke or fumes.

b. • If fire is not extinguished:(1) Land as soon as possible.(2) This checklist is complete.

• If fire has been extinguished and can be visibly verified:(1) Land as soon as practical. At the crew’s discretion, the

oxygen system may be returned to normal.(2) This checklist is complete.

If smoke or fumes continue:7. One or Both BLEED AIR Switches .........................................EMER8. AUTO-MAN Switch ...................................................................MAN

9. UP-DN Manual Control ......................................UP (max. 13,000 ft)If time & conditions permit, isolate source of smoke and fumes:10. • If bleed air system is suspected source:

a. R BLEED AIR Switch .........................................................OFF• If smoke is reduced, continue with switch OFF.• If smoke is not reduced:

(1) R BLEED AIR Switch ....................................................ON(2) L BLEED AIR Switch ...................................................OFF

If smoke is reduced, continue with switch OFF.



Change 1

10

CL-102B April 2001 E-23.1Change 1

ALL

EFFECTIVITY

b

• If source is electrical:a. All Non-essential Electrical Equipment ..............................OFFb. Isolate defective systems bus as follows:

The following steps separate the pilot and copilot electricalsystems. If the electrical smoke or fume source is positivelyidentified on the pilot side, pull all BUS TIE circuit breakers onthe copilot circuit breaker panel and proceed with step (4).(1) Copilot’s Circuit Breaker Panel — Pull the following circuit

breakers:

All electrical power from the copilot’s circuit breaker panel isnow off. Allow time for smoke and fumes to dissipate.

If electrical smoke or fumes continue:(2) All BUS TIE Circuit Breakers....................LEAVE PULLED

DO NOT RESET(3) All other Copilot Circuit Breakers ...........................RESET(4) Pilot’s Circuit Breaker Panel — Pull the following circuit

breakers:

All electrical power from the pilot’s circuit breaker panel is now off. Allow time for smoke and fumes to dissipate.


TOP ROW 3RD ROWAC BUS TIE ESS A BUS TIER AC BUS R ESS A BUS

R AUX AC BUS (if installed) R STALL WARN26 VAC BUS

2ND ROW BOTTOM ROWMAIN BUS TIE ESS B BUS TIER MAIN BUS R ESS B BUS

R IGN & START AUX INV (if installed)SEC INV

TOP ROW 3RD ROWL AC BUS L ESS A BUS

L AUX AC BUS (if installed) L STALL WARN26 VAC BUS DOOR ACTR

ENTRY LT

2ND ROW BOTTOM ROWL MAIN BUS L ESS B BUS

L IGN & STARTPRI INV


EFFECTIVITY

10

CL-102B April 2001 E-35.1ALL

EFFECTIVITY

b

INADVERTENT THRUST REVERSER DEPLOYMENT DURING TAKEOFF

Below V1 Speed:



3. Spoilers .............................................................................EXTEND

To improve directional control, position both Reverser Levers toREVERSE IDLE.

INDICATION OF THRUST REVERSERDEPLOYMENT DURING TAKEOFF

Above V1 Speed:


2. Thrust Lever (affected engine) .............................................. IDLE

3. Thrust Reverser Control Switches.........................................OFF


5. Rotate at VR, Climb at V2.

6. Positive Rate Of Climb Established..............................GEAR UP

7. Clear of Obstacles ........... ACCELERATE TO V2 + 30, FLAPS UP

8. If DEPLOY light stays on:Thrust Lever (affected engine) ........................................CUTOFF

9. Fuel Jettison ................................................................................ON

Fuel Jettison ............................................. OFF (prior to touchdown)

10. If engine was shut down, refer to ENGINE SHUTDOWN IN FLIGHTprocedure, Tab 5, this section.

DEPLOY ARM

DEPLOY

With TR-4000 Thrust Reversers

EFFECTIVITY

16

CL-102B April 2001 A-iALL

EFFECTIVITY

AB

NO

RM

AL

b

ABNORMAL PROCEDURES

This section contains those operating procedures requiring the use of spe-cial systems and/or alternate use of regular systems which, if followed, willmaintain an acceptable level of airworthiness or reduce operational risk re-sulting from a failure condition.

The procedures located in this section supplement Normal Procedureswhen a failure condition exists. Use of Normal Procedures should be con-tinued when applicable. Sound judgement as well as thorough knowledgeof the aircraft, its characteristics, and the flight manual procedures are es-sential in the handling of any failure condition.

In addition to the outlined items in the abnormal procedures, the followingsteps are considered part of all abnormal situations:

• Maintain Airplane Control

• Analyze the Situation

• Take Proper Action

CL-102B

A-ii

April 2001C

hange 1A

LLEFFEC

TIVITY

ABNORMAL

CURLIM

LOWFUEL

L FUELPRESS

R FUELPRESS SPOILER DOOR AUG

AILPITOT

HTFUEL

FILTER

PRIINV

SECINV

AUXINV SPARE STAB

OV HTWSHLDOV HT

STEERON

BLEEDAIR L

BLEEDAIR R

ENG FIREPULL

L ENGICE

R ENGICE

L FUELCMPTR

R FUELCMPTR

LSTALL

RSTALL

L VGMON

R VGMON

MACHTRIM

NAC HTON

LGEN

RGEN

CABALT

WINGOV HT

WSHLDHT

ALCAI

BAT140

BAT160

T.O.TRIM

ENG FIREPULL

DEPLOY ARM

16 16


ENGSYNC


16 16 16


LEFT SIDE

RIGHT SIDE

LOHYD

FUELXFLO

L LOOIL

R LOOIL

LH ENGCHIP

RH ENGCHIP

PITCHTRIM

91793

4 2 344

4 4

2

8 8 12 12 7

3 3

1 1

1

5

10

5

8

6

WSHLDDEFOG

L R

OIL PRESS

LO OIL PRESS

Change 1

CL-102B April 2001 A-1Change 1

b

ALL

EFFECTIVITY

ABNORMAL PROCEDURES

ANTI-ICINGALC AI LIGHTENGINE ICE INGESTIONENG ICE LIGHTINADVERTENT ICING ENCOUNTERPITOT HT LIGHTSTABILIZER HEAT FAILURESTAB OV HT LIGHTWING HEAT FAILUREWING OV HT LIGHTWINDSHIELD HEAT FAILUREWSHLD OV HT LIGHT

ELECTRICALGENERATOR FAILURE (SINGLE)INVERTER FAILURE — PARTIAL AC POWER LOSS

ENGINEABNORMAL ENGINE OPERATIONFUEL CMPTR LIGHTENG CHIP LIGHTENGINE OVERSPEEDENGINE SHUTDOWN IN FLIGHTSTARTER ENGAGED LIGHT

ENVIRONMENTALFAILURE TO DEPRESSURIZEOVERPRESSURIZATIONCABIN ALTITUDE EXCEEDS 8500 FEETRETURN TO AUTOMATIC PRESSURIZATION MODE

2

TAB

TAB

1

3

4

5

6

7

Change 1

35-001 thru 35-106, 35-108 thru 35-112;and 36-001 thru 36-031

CL-102B April 2001 A-1.1Change 1

b

ALL

EFFECTIVITY35-107, 35-113 & on; and 36-032 & on

ABNORMAL PROCEDURES

ANTI-ICINGALC AI LIGHTENGINE ICE INGESTIONENG ICE LIGHTINADVERTENT ICING ENCOUNTERPITOT HT LIGHTSTABILIZER HEAT FAILURESTAB OV HT LIGHTWING HEAT FAILUREWING OV HT LIGHTWINDSHIELD HEAT FAILUREWSHLD DEFOG LIGHTWSHLD OV HT LIGHT

ELECTRICALGENERATOR FAILURE (SINGLE)INVERTER FAILURE — PARTIAL AC POWER LOSS

ENGINEABNORMAL ENGINE OPERATIONFUEL CMPTR LIGHTENG CHIP LIGHTENGINE OVERSPEEDENGINE SHUTDOWN IN FLIGHTSTARTER ENGAGED LIGHT

ENVIRONMENTALFAILURE TO DEPRESSURIZEINADVERTENT ACTIVATION OF EMERGENCY AIRFLOWOVERPRESSURIZATIONCAB ALT LIGHT OR CABIN ALTITUDE EXCEEDS 8500 FEETRETURN TO NORMAL PRESSURIZATION

2

TAB

TAB

1

3

4

5

6

7

CL-102BA-2 April 2001

Change 2ALL

EFFECTIVITY

FLIGHT CONTROLSAUG AIL LIGHTMACH TRIM MALFUNCTIONPITCH TRIM LIGHT IN FLIGHTSTALL WARNING SYSTEM FAILUREYAW DAMPER FAILURE

FUELCROSSFLOW VALVE FAILS TO OPENFUEL FILTER LIGHTFUEL IMBALANCE DURING FUEL TRANSFERFUEL JETTISONFUEL TRANSFER VALVE FAILS TO CLOSEFUEL VALVE LIGHT(S)LOW FUEL LIGHTNORMAL FUEL TRANSFER SYSTEM FAILURESTANDBY PUMP FAILS TO SHUT OFFTIP TANK FAILS TO TRANSFER FUEL

HYDRAULICLO HYD LIGHT

(LOW HYDRAULIC PRESSURE)HYDRAULIC SYSTEM FAILURE/

ALTERNATE GEAR EXTENSIONINSTRUMENTS

PITOT-STATIC SYSTEM MALFUNCTIONV.G. MON LIGHT

LANDING GEARALTERNATE GEAR EXTENSION/

ELECTRICAL MALFUNCTIONANTI-SKID GEN LIGHT — ANTI-SKID OFF OPERATIONNOSE WHEEL STEERING MALFUNCTION

9

TAB

TAB

8

10

11

12

7

Change 2

CL-102B April 2001 A-3

b

ALL

EFFECTIVITY

LANDINGSGEAR UPHYDRAULIC SYSTEM FAILUREJAMMED STABILIZERONE OR BOTH SPOILERS UPPARTIAL FLAPSINGLE-ENGINESTABILIZER HEAT FAILUREWING HEAT FAILUREWING & STAB HEAT FAILUREONE THRUST REVERSER DEPLOYED

TURBULENCETURBULENT AIR PENETRATION

THRUST REVERSERSAeronca Thrust Reversers

INADVERTENT THRUST REVERSERDEPLOYMENT DURING FLIGHT

UNLOCK LIGHT IN FLIGHT(THRUST REVERSER NOT DEPLOYED)

UNLOCK LIGHT AFTER NORMAL DEPLOYFAILURE OF THRUST REVERSER TO

STOW AFTER LANDINGTR-4000 Thrust Reversers

ANNUNCIATED THRUST REVERSER MALFUNCTION (REVERSER NOT DEPLOYED)

INADVERTENT THRUST REVERSER DEPLOYMENTDURING FLIGHT

THRUST REVERSER RESTOW ENVELOPE

13

14

16

TAB

12

15

TAB

CL-102BA-4 April 2001ALL

EFFECTIVITY

ALC AI LIGHT

1. When alcohol stops flowing, WSHLD/RADOME Switch............OFF

2. After landing, assure alcohol reservoir is properly replenished.

ENGINE ICE INGESTION1. Ignition ..............................................................................BOTH ON

2. Thrust Lever Movement.................................. SLOW & CAUTIOUS

3. Engine RPM ......................................................................REDUCEMaintain Anti-ice and Pressurization RPM.

4. Avoid abrupt change in pitch, roll or yaw.

5. To determine extent of engine damage:

a. Retard Thrust Levers (one at a time) to flight idle. Then cau-tiously advance and check for any vibration or abnormal noiseon each engine.

b. If either engine flames out, perform an airstartprocedure, Tab 5, Emergency Checklist. Stay below enginespeed at which engine flamed out.

c. If ice damage has been experienced, land as soon as practicaland within limitations of operating capacity of engine. Afterlanding, inspect engine for damage.

ENG ICE LIGHT

Affected Engine:

1. NAC HT CB (main bus) .............................................. PULL/RESET

If light remains illuminated:

2. • If associated NAC HEAT switch is OFF,Engine RPM ......................................................................REDUCE

• If associated NAC HEAT switch is ON,Engine RPM ............................................................... INCREASE &

FLY OUT OF ICING CONDITIONS IF POSSIBLE

ALCAI

R ENGICE

L ENGICE


b

ALL

EFFECTIVITY

INADVERTENT ICING ENCOUNTERIf icing is inadvertently encountered:

1. Anti-Ice Systems.............................................................. ACTIVATE

If approach and landing must be made with any amount of iceon the airframe:

a. Do not extend flaps beyond 20°.

b. Refer to WING & STAB HEAT FAILURE LANDING procedure,Tab 15, this section.

If heavy ice accumulation has occurred, proceed as follows:

• If landing with ice on the wings and stabilizer:1. Refer to WING & STAB HEAT FAILURE LANDING procedure,

Tab 15, this section.

• If attempting to remove ice accumulation:1. Ignition ..............................................................................BOTH ON

2. Engine RPM ...................................................................... REDUCE

3. Nacelle Heat (one engine)...........................................................ONWait for satisfactory engine operation, then:Nacelle Heat (other engine).........................................................ON

4. Stabilizer/Wing Heat ....................................................................ON

5. Windshield Heat .............................................................. AS REQ’D

PITOT HT LIGHT

1. PITOT HEAT Switches ................................................................ON

2. L & R PITOT HT CBs (ess buses)........................................CHECK

3. Pitot-Static Systems................................................CROSS-CHECK

2

PITOTHT

1


EFFECTIVITY

STABILIZER HEAT FAILURE

1. STAB & WING HT CB (copilot’s main bus).......... CHECK & RESET

2. Engine RPM ..................................................... ADJUST AS REQ’D

3. If STAB TEMP Indicator remains in the red range:

a. Fly out of icing conditions, if possible.

b. Do not extend flaps beyond 20°.

4. If cabin altitude climbs to an unacceptable level:

a. CABIN AIR Switch ............................................................ MAX

b. Descend to an acceptable level.

Refer to STABILIZER HEAT FAILURE LANDING procedure, Tab 15, thissection.

STAB OV HT LIGHT

1. Stabilizer Temperature......................................................... CHECK

2. If stabilizer overheat condition exists:

a. Engine RPM...............................................................REDUCE

b. If overheat condition remains:

(1) STAB WING HEAT Switch ..........................................OFF

(2) Fly out of icing conditions.

Refer to WING HEAT FAILURE LANDING procedure, Tab 15, this section,if landing must be made with ice or suspected ice on the wings.

STAB

TEMP

STABOV HT


EFFECTIVITY

2

CL-102BA-6.1 April 2001ALL

EFFECTIVITY

STABILIZER HEAT FAILURE

1. STAB & WING HT CB (copilot’s main bus).......... CHECK & RESET


3. If STAB TEMP Indicator remains in the red range:

a. Fly out of icing conditions, if possible.

b. Do not extend flaps beyond 20°.

Refer to STABILIZER HEAT FAILURE LANDING procedure, Tab 15, thissection.

STAB OV HT LIGHT

1. Stabilizer Temperature......................................................... CHECK

2. If stabilizer overheat condition exists:

a. Engine RPM...............................................................REDUCE





STAB

TEMP

STABOV HT


2


b

ALL

EFFECTIVITY

WING HEAT FAILURE

1. STAB & WING HT CB (copilot’s main bus) ......... CHECK & RESET


3. If WING TEMP indicator remains in the red range and/or visual indi-cations of ice accumulation remain, fly out of icing conditions.





WING OV HT LIGHT

1. Wing Temperature ................................................................CHECK

2. If wing overheat condition exists:

a. Engine RPM............................................................... REDUCE





WING

TEMP

WINGOV HT


EFFECTIVITY

2

CL-102B April 2001 A-7.1

b

ALL

EFFECTIVITY

WING HEAT FAILURE

1. STAB & WING HT CB (copilot’s main bus) ......... CHECK & RESET


3. If WING TEMP indicator remains in the red range and/or visual indi-cations of ice accumulation remain, fly out of icing conditions.


WING OV HT LIGHT

1. Wing Temperature ................................................................CHECK

2. If wing overheat condition exists:

a. Engine RPM............................................................... REDUCE




Refer to WING HEAT FAILURE LANDING procedure, Tab 15, this section,if landing must be made with ice or suspected ice on the wings.3

WING

TEMP

WINGOV HT


2


EFFECTIVITY

WINDSHIELD HEAT FAILURE1. WSHLD HT CB (pilot’s main bus)........................ CHECK & RESET

2. Windshield Heat ..................................................................... AUTO

3. Engine RPM .................................................INCREASE AS REQ’D




If system fails to anti-ice the windshield:

5. Windshield & Radome Alcohol .................................. ON, IF REQ’D

6. Windshield & Radome Alcohol .................... OFF (when depleted orout of icing conditions)


EFFECTIVITY

3


EFFECTIVITY

WINDSHIELD HEAT FAILURE1. WSHLD HT CB (pilot’s main bus)........................ CHECK & RESET

2. Windshield Heat ..........................................................................ON

3. Engine RPM .................................................INCREASE AS REQ’D

If system fails to anti-ice the windshield:

4. Windshield & Radome Alcohol .................................. ON, IF REQ’D

5. Windshield & Radome Alcohol .................... OFF (when depleted orout of icing conditions)

WSHLD DEFOG LIGHT(IF INSTALLED)

If windshield overheat condition persists for more than 10 minutes, deactivate affected windshield:

1. L or R WSHLD DEFOG CB (ess B bus).................................. PULL

2. Affected Windshield ............................................................. CHECK

If descending with an inoperative defog system into conditions requiring defogging:

1. Windshield Heat ..........................................................................ON

2. Cockpit Shoulder & Ankle Eyeball Outlets............................CLOSE

3. AUX HT ................................................................................. CREW

4. At FL 350:

a. COOL–FAN Switch .........................................................COOL

b. AUTO–MAN Switch........................................................... MAN

c. COLD–HOT Knob .................................................... AS REQ’D

5. Leave cabin air and windshield heat on until shutdown.

WSHLDDEFOG

L R


3


b

ALL

EFFECTIVITY

WSHLD OV HT LIGHT

If airflow did not shut off when WSHLD OV HT light illuminated:

1. Windshield Heat ....................................................................... MAN

2. WSHLD HEAT ON-OFF Switch....................OFF, until airflow stops

If WSHLD OV HT light remains on:

3. Engine RPM ..................................................................... REDUCE

and/orIN NORMAL/OUT DEFOG Knob.......................................PUSH IN

GENERATOR FAILURE(SINGLE)

1. Electrical Load................................................................... REDUCE

a. Air Conditioner ...................................................................OFF

b. Other Loads .................................................. SHED AS REQ’D

2. IGN & ST CB (main power bus) .......................... CHECK & RESET


4. Generator Reset Switch ........................... DEPRESS (momentarily)

If generator does not reset:

5. Turbine Speed (N2).................................................. 80% or ABOVE

6. Start-Gen Switch....................................................... OFF then GEN



8. Start-Gen Switch........................................................................OFF

WSHLDOV HT

LGEN

RGEN


EFFECTIVITY

3

CL-102B April 2001 A-9.1

b

ALL

EFFECTIVITY

WSHLD OV HT LIGHT

If airflow did not shut off when WSHLD OV HT light illuminated:

1. Windshield Heat ........................................................................OFF

GENERATOR FAILURE(SINGLE)

1. Electrical Load................................................................... REDUCE

a. Air Conditioner ...................................................................OFF

b. Other Loads .................................................. SHED AS REQ’D

2. IGN & ST CB (main power bus) .......................... CHECK & RESET




5. Turbine Speed (N2).................................................. 80% or ABOVE

6. Start-Gen Switch....................................................... OFF then GEN




4

WSHLDOV HT

LGEN

RGEN


3


EFFECTIVITY

INVERTER FAILURE —PARTIAL AC

POWER LOSSFAILURE OF PRI OR SEC INVERTER SYSTEM

1. Affected INV (main power bus) &AC BUS (AC bus) CBs........................................ CHECK & RESET

2. Failed Inverter............................................................. OFF then ON

3. Failed INV CB..................................................... PULL then RESET

If malfunction does not clear:

4. Failed Inverter............................................................................OFF

5. Corresponding AC BUS CB..................................................... PULL

6. AC BUS TIE CB (copilot’s panel)......................... CHECK & RESET

If CB opens after resetting, leave it open.

7. Aux Inverter (if installed) ................................. FAILED BUS (L or R)

If auxiliary inverter system malfunctions:

a. Corresponding AUX AC BUS CB (AC bus)...................... PULL

b. Aux Inverter ............................................. OPPOSITE AC BUS

c. AUX INV CB (copilot’s ess bus) ................... CHECK & RESET

FAILURE OF AUXILIARY INVERTER SYSTEM (IF INSTALLED)

1. Aux Inverter ...............................................................................OFF

2. L and R AUX AC BUS CBs (AC buses) .................................. PULL

SECINV

AUXINV

PRIINV

4


b

ALL

EFFECTIVITY

ABNORMAL ENGINE OPERATIONFAN SPEED (N1) OR TURBINE SPEED (N2) DECREASING OR INAP-PROPRIATE FOR THRUST LEVER POSITION

Affected Engine:1. Thrust Lever ............................................................................. IDLE2. Fuel Computer...........................................................................OFF3. If engine characteristics appear normal, continue flight with fuel

computer in manual mode. Follow the appropriate sections of theFUEL CMPTR LIGHT procedure, this page.

FUEL CMPTR LIGHT

Affected Engine:1. FUEL COMPTR CB (ess bus) ............................. CHECK & RESET2. Fuel Computer.................................OFF then ON (50% to 60% N1)

If fuel computer does not come back on line:Fuel Computer...........................................................................OFF

3. Crossflow Valve ....................................................................CLOSE4. FUS TANK Switches as follows:

a. Transfer-Fill ........................................................................OFFb. Fus Valve (if installed) ...................................................CLOSE

5. Standby Pump .............................................................................ON6. Jet Pump ...................................................................................OFF

To crossflow or transfer fuel:7. Jet Pump ......................................................ON (Steady N1 ≥ 80%)

8. Standby Pump ...........................................................................OFF

9. Crossflow or transfer fuel as required.

10. Standby Pump .............................................................................ON

11. Jet Pump ...................................................................................OFF

L FUELCMPTR

R FUELCMPTR

Change 1

4


EFFECTIVITY

ENG CHIP LIGHT

Affected Engine:

1. Engine Instruments.......................................................... MONITOR

2. Investigate cause at earliest possible maintenance.

ENGINE OVERSPEEDAffected Engine:

1. Thrust Lever .......................................................................RETARD

Do not set affected engine Fuel Computer Switch OFF.

2. If engine does not respond to thrust lever movement, shut downengine. Refer to ENGINE SHUTDOWN IN FLIGHT procedure, thispage.

ENGINE SHUTDOWN IN FLIGHTAffected Engine:

1. Engine Sync ..............................................................................OFF

2. Thrust Lever .......................................................................CUTOFF



5. Ignition .......................................................................................OFF


7. Electrical Load ...................................................................REDUCE

8. Bleed Air ....................................................................................OFF

9. Crossflow Valve ...........................OPEN, CROSSFLOW AS REQ’D

10. Refer to AIRSTART procedure, Tab 5, Emergency Checklist orSINGLE-ENGINE LANDING procedure, Tab 14, this section.

LH ENGCHIP

RH ENGCHIP

5

CL-102B April 2001 A-13

b

ALL

EFFECTIVITY

STARTER ENGAGED LIGHTREMAINS ILLUMINATED

Ground Start:

1. Affected Start-Gen Switch ........................................................ GEN

2. Affected Engine ..........................................................SHUT DOWN

3. Electrical Power.........................................................................OFF

4. Do not dispatch until trouble has been corrected.

Starter-Assist Airstart:

1. Airstart Procedure......................................................... COMPLETE

2. Affected Start-Gen Switch ........................................................ GEN

• If light goes out:

a. Continue flight.

b. Correct trouble before next flight.

• If light remains illuminated:

a. Affected IGN & ST CB (main power bus)......................... PULL

b. Corresponding generator will be inoperative.

• If light goes out:

(1) Continue flight.

(2) Refer to GENERATOR FAILURE (SINGLE) procedure,Tab 3, this section.

(3) Correct trouble before next flight.

• If light remains illuminated:

(1) Affected IGN & ST CB............................................ RESET

(2) Land as soon as practical.

(3) Correct trouble before next flight.

OFF

S T A R T

5


EFFECTIVITY

FAILURE TO DEPRESSURIZE1. Cabin Air ....................................................................................OFF

2. Both BLEED AIR Switches ........................................................OFF

INADVERTENT ACTIVATION OFEMERGENCY AIRFLOW (IF INSTALLED)

1. Thrust Levers....................................... 90% or BELOW (if practical)

2. •Aircraft 35-107 & 35-113 thru 35-658; and 36-032 thru 36-063 notincorporating AMK 90-3:

LH MOD VAL CB (pilot’s main bus) .............................................. IN

RH MOD VAL CB (copilot’s main bus).......................................... IN

•Aircraft 35-659 & on; 36-064 & on; and prior aircraft incorporatingAMK 90-3:

L EMER PRESS CB (pilot’s main bus) ......................................... IN

R EMER PRESS CB (copilot’s main bus)..................................... IN

If Emergency Airflow Continues:

3. One BLEED AIR Switch ............................................................OFF

If emergency airflow stops, leave switch OFF.

If Emergency Airflow Continues:

4. BLEED AIR Switch ......................................................................ON

Other BLEED AIR Switch ..........................................................OFF

OVERPRESSURIZATIONIf Differential Pressure Exceeds Red Line:

1. AUTO-MAN Switch ................................................................... MAN

2. UP-DN Manual Control .............................................. UP AS REQ’D

If Unable To Regulate Overpressurization:

3. One BLEED AIR Switch ............................................................OFF

4. Adjust power on opposite engine to control pressurization.

6

CL-102B April 2001 A-15

b

ALL

EFFECTIVITY

CABIN ALTITUDE EXCEEDS 8500 FEET1. Crew Oxygen Masks ....................................DON & SELECT 100%

2. If aircraft is climbing, stop climbing and level off at (or descend to)the nearest appropriate altitude.


4. Cabin Air................................................................................ NORM

5. Bleed Air ......................................................................................ON

6. Cabin Altitude .......................................................................CHECK

7. • If cabin altitude continues to climb:

a. AUTO-MAN Switch ........................................................... MAN

b. UP-DN Manual Control (red).................................... AS REQ’D

If cabin altitude continues to climb:

c. Engine RPM............................................................. MAINTAIN

d. IN NORMAL/OUT DEFOG Knob ................................PUSH IN

e. Windshield Heat.............................................................. AUTO

f. Cabin Air ............................................................................OFF

• If cabin altitude stabilizes at a safe altitude:

a. Continue flight. Continued use of oxygen system is at thecrew’s discretion.

Refer to Supplemental Data, pages S-8, S-9 and S-10 for oxygenduration charts.

35-001 thru 35-106, 35-108 thru 35-112; and 36-001 thru 36-031

EFFECTIVITY

6

CL-102B April 2001 A-15.1

b

ALL

EFFECTIVITY

CAB ALT LIGHT OR CABIN ALTITUDE EXCEEDS 8500 FEET

1. Crew Oxygen Masks ....................................DON & SELECT 100%

2. If aircraft is climbing, stop climbing and level off at (or descend to)the nearest appropriate altitude.


4. Cabin Air......................................................................................ON

5. Bleed Air ......................................................................................ON

6. Cabin Altitude .......................................................................CHECK

7. • If cabin altitude continues to climb:

a. AUTO-MAN Switch ........................................................... MAN

b. UP-DN Manual Control (red).................................... AS REQ’D

If cabin altitude continues to climb:

c. BLEED AIR Switches......................................................EMER

• If cabin altitude stabilizes at a safe altitude:

a. Continue flight. Continued use of oxygen system is at thecrew’s discretion.

b. If cabin temperature becomes hot from the use of EMERBLEED AIR:

(1) One BLEED AIR Switch ..............................................OFF

(2) If temperature is still too high, reduce power on enginesupplying bleed air.

Refer to Supplemental Data, pages S-8, S-9 and S-10 for oxygenduration charts.

7

CABALT

35-107, 35-113 & on; and 36-032 & on

EFFECTIVITY

6


EFFECTIVITY

RETURN TO AUTOMATIC PRESSURIZATION MODE1. Cabin Controller................................................ð7500 FEET (cabin)

2. Rate Selector................................................................. FULL INCR

3. UP-DN Manual Control ....................SELECTED CABIN ALTITUDE

4. Cabin Vertical Speed .............................................................. ZERO

5. Rate Selector.................................................RESET TO NOMINAL

6. AUTO-MAN Switch ................................................................. AUTO

7. Cabin Controller............................................................... AS REQ’D

35-001 thru 35-106, 35-108 thru 35-112; and 36-001 thru 36-031

EFFECTIVITY

7


EFFECTIVITY

RETURN TO NORMAL PRESSURIZATION1. Cabin Air ......................................................................................ON

2. AUTO-MAN Switch ................................................................... MAN

3. UP-DN Manual Control ....................................<7200 FEET (cabin)

4. One BLEED AIR Switch ............................................. OFF then ON

5. Other BLEED AIR Switch ........................................... OFF then ON

6. UP-DN Manual Control .................................................... AS REQ’D

Return to Automatic Mode If Desired

7. Cabin Controller ...............................................ð7200 FEET (cabin)

8. UP-DN Manual Control ...................SELECTED CABIN ALTITUDE

9. AUTO-MAN Switch ................................................................ AUTO

35-107, 35-113 & on; and 36-032 & on

EFFECTIVITY

7

CL-102B April 2001 A-17

b

ALL

EFFECTIVITY

AUG AIL LIGHT

1. Spoiler Switch ............................................................................RET

2. Spoileron Reset Switch.................................... RESET & RELEASE

3. If AUG AIL Light illuminates again:

a. SPOILERON CB (copilot’s AC bus)................................. PULL

b. Spoilers will be inoperative in flight.

c. Spoilerons will be inoperative in flight.

d. Spoilers will function normally during ground operations.

MACH TRIM MALFUNCTION(IF APPLICABLE)

1. Airspeed .................................................................. BELOW 0.74MI

2. Check Primary Pitch Trim available:

a. Pitch Trim............................................................................ PRI

b. Primary PITCH CB (pilot’s ess bus).......................................IN

3. MACH TRIM CB (pilot’s AC bus)..........................................CHECK

• If MACH TRIM CB Open:

a. MACH TRIM CB............................................................ RESET

b. Test Selector Switch..............................................MACH TRIM

c. Test Button ..........................................DEPRESS & RELEASE

d. If MACH TRIM CB opens again ..........................LEAVE OPEN

• If MACH TRIM CB Closed:

a. Reset Mach Trim Monitor if desired:

(1) Test Selector Switch.......................................MACH TRIM

(2) Test Button ...................................DEPRESS & RELEASE

b. If MACH TRIM Light remains on, MACH TRIM CB.......... PULL

8

AUGAIL

MACHTRIM

7


EFFECTIVITY

PITCH TRIM LIGHT IN FLIGHT

1. Pitch Trim...................................................................................SEC

2. NOSE DN-OFF-NOSE UP Switch................................... AS REQ’D

STALL WARNINGSYSTEM FAILURE

If both L & R systems fail:

1. Airspeed .................................................30 KNOTS ABOVE STALLVREF may be maintained on final

2. Bank angles........................................................................30° MAX

3. If L STALL WARNING Switch OFF, stick puller is inoperative,MMO = 0.74 MI

If only one system fails:

• If L Stall fails:1. Yaw Damper ..............................................................................SEC

2. If L STALL WARNING Switch OFF, stick puller is inoperative,MMO = 0.74 MI

• If R Stall fails:1. Yaw Damper ............................................................................... PRI

PITCHTRIM

RSTALL

LSTALL

(IF APPLICABLE)

8

CL-102B April 2001 A-19

b

ALL

EFFECTIVITY

YAW DAMPER FAILURESINGLE YAW DAMPER FAILURE

1. Yaw Damper .................................. SELECT REMAINING SYSTEM

2. Avoid moderate/severe turbulence.

3. Do not initiate further flight until corrected.

DUAL YAW DAMPER FAILURE

Maintaining higher airspeed (250 KIAS or higher where applicable) will im-prove Dutch roll stability.Landing with minimum tip fuel will improve Dutch roll stability and lateralcontrol. With both yaw dampers inoperative, plan flight to land with both tiptanks empty.

1. Avoid moderate/severe turbulence.


3. Do not initiate further flight until corrected.

CROSSFLOW VALVE FAILS TO OPEN1. Maintain wing fuel balance by adjusting power setting.

2. •On aircraft without FUS VALVE switch, transferring fuselage fuelwill result in a right wing heavy condition.

•On aircraft with FUS VALVE switch, transfer fuselage fuel using thefollowing procedure:

a. Transfer-Fill ......................................................................XFER

b. Fuselage Valve ...............................................................OPEN

c. Monitor wing fuel indications to ensure fuel balance.

d. • If right wing becomes heavy during fuselage fuel transfer:(1) Fuselage Valve.......................................................CLOSE

(2) When wings are balanced, Fuselage Valve .............OPEN

• If left wing becomes heavy during fuselage fuel transfer:(1) Transfer-Fill .................................................................OFF

(2) When wings are balanced, Transfer-Fill....................XFER

9

8


EFFECTIVITY

FUEL FILTER LIGHT

1. Standby Pumps................................................. ON (when possible)

FUEL IMBALANCE DURING FUEL TRANSFER1. Transfer-Fill................................................................................OFF

2. Fuselage Valve (if installed)..................................................CLOSE

3. Standby Pump (heavy wing)........................................................ON

4. Standby Pump (light wing) .........................................................OFF

5. Crossflow Valve ......................................................................OPEN

6. Fuel Balance.................................................................... MONITOR

7. • If Fuel Load Balances:

a. Crossflow Valve.............................................................CLOSE

b. Both Standby Pump Switches............................................OFF

c. Monitor fuel balance when transferring fuselage fuel.

• If Fuel Load Does Not Balance:

a. STBY PMP CB (light wing) (ess bus)............................... PULL

b. Standby Pump (heavy wing) ................................................ON

c. Crossflow Valve...............................................................OPEN

d. Fuel Balance ............................................................ MONITOR

e. • If Fuel Load Balances:

(1) Crossflow Valve......................................................CLOSE

(2) Both Standby Pump Switches .....................................OFF

Refer to AFM for conditions that will exist.

• If Fuel Load Still Does Not Balance:

(1) Crossflow Valve......................................................CLOSE

(2) Both Standby Pump Switches .....................................OFF

Refer to AFM for conditions that will exist.

FUELFILTER

9

CL-102B April 2001 A-21

b

ALL

EFFECTIVITY

FUEL JETTISON1. Fuel Jettison Switch.....................................................................ON

2. L and R FUEL JTSN Lights ..............................................BOTH ON

If only one light illuminates, Fuel Jettison Switch ......................OFF

3. Ensure that fuel is flowing from both tip tanks.

4. When jettison is complete,Fuel Jettison Switch......................................... OFF (both lights out)

FUEL TRANSFER VALVE FAILS TO CLOSE1. Conduct crossflow operations with caution as standby pump opera-

tion will transfer some fuel back into the fuselage tank.

2. Periodically transfer fuel back into wings.

FUEL VALVE LIGHT(S) Steady illumination of any of the amber fuel valve lights (except FUELJTSN) on the fuel control panel indicates the corresponding valve is not in the position selected.

LOW FUEL LIGHT

1. Fuel Quantities .....................................................................CHECK

If fuel distribution correction is required:

a. Balance wing fuel. Refer to FUEL CROSSFLOW, AFM,Section II.

b. Transfer fuselage fuel to the wings. Refer to NORMAL FUSE-LAGE FUEL TRANSFER, AFM, Section II.

2. Replan flight if necessary.

10

LOWFUEL

9


EFFECTIVITY

NORMAL FUEL TRANSFER SYSTEM FAILUREIf fuselage fuel load in excess of maximum zero wing and tip fuel weightcannot be transferred prior to reaching a total wing fuel quantity of 2250pounds, do not exceed 325 KIAS.Aircraft with FUS VALVE Switch

1. Fuselage Valve .......................................................................OPEN

2. Prior to approach or gravity transfercomplete, Fuselage Valve.....................................................CLOSE

Aircraft without FUS VALVE Switch

• Transfer valve light remains illuminated:1. Transfer-Fill................................................................................OFF

2. Replan flight.

• Transfer valve light goes out:1. FUSLG PMP CB (Copilot’s Main Bus)..................................... PULL

2. Transfer-Fill............................................................................. XFER

3. Prior to approach or gravity transfercomplete, Transfer-Fill ...............................................................OFF

STANDBY PUMP FAILS TO SHUT OFFIf standby pump light does not extinguish when pump is selected off:

1. Corresponding STANDBY PUMP Switch ............................. CYCLE

If standby pump light does not extinguish:

2. Corresponding STBY PMP CB (ess bus) ................................ PULL

10


b

ALL

EFFECTIVITY

TIP TANK FAILS TO TRANSFER FUELMaximum demonstrated fuel imbalance for landing was approximately 600pounds (one tip tank half full and the other tip tank empty). However, forbest lateral control it is recommended that the tip fuel be jettisoned to bal-ance. This is particularly important if landing is to be made in strong gustycrosswinds or with spoilerons inoperative.• If it is decided to jettison fuel:

1. Jettison tip tank fuel. Refer to FUEL JETTISON procedure, Tab 9,this section.

2. Prior to landing, Fuel Jettison Switch ........................................OFF

3. Execute normal landing.

• If it is decided not to jettison fuel:1. Configuration ................................................ GEAR DN, FLAPS DN

2. Final Approach Speed ......................................................VREF + 10

3. Landing Distance................................................. MULTIPLY BY 1.1

11

LO HYD LIGHT (If Installed)(LOW HYDRAULIC PRESSURE)

If hydraulic pressure is not regained, landing gear, flaps, spoilers, brakes,and thrust reversers (if installed) may be affected. Landing distance withno flaps, no spoilers and no anti-skid will be greatly increased (for landingdistance increase, refer to HYDRAULIC SYSTEM FAILURE LANDINGprocedure, Tab 13, this section).


2. • If pressure is normal, continue to monitor.

• If pressure is low, refer to HYDRAULIC SYSTEM FAILURE/ALTERNATE GEAR EXTENSION procedure, next page andHYDRAULIC SYSTEM FAILURE LANDING procedure, Tab 13, thissection.

LOHYD

Change 2

10

CL-102BA-24 April 2001

Change 1ALL

EFFECTIVITY

HYDRAULIC SYSTEM FAILURE/ALTERNATE GEAR EXTENSION

1. Spoilers............................................................................ RETRACT

On Approach:

2. Airspeed VLO or less (VREF + 30 recommended)


4. GEAR CB (copilot’s ess bus)................................................... PULL

5. SPOILERON CB (copilot’s AC bus)......................................... PULL

6. Flap Switch ..................................................................................DN

7. To extend gear:

a. Emergency Gear Extension Lever(Right Side Pedestal) ...........................................FULL DOWN

b. Gear Lights...................................... CHECK 3 GREEN, 2 RED

c. After gear is down and locked,Emergency Gear Extension Lever ............................. FULL UP

(1) Lift ratchet release in hole forward of extension lever, right side of pedestal.

(2) Pull extension lever up until it latches.

d. • If all of the three green LOCKED DN lights are illuminated,refer to HYDRAULIC SYSTEM FAILURE LANDING proce-dure, Tab 13, this section.

• If any gear is not down and locked, refer to GEAR UP LAND-ING procedure, Tab 12, this section.

Change 1

11

CL-102B April 2001 A-25

b

ALL

EFFECTIVITY

PITOT-STATIC SYSTEM MALFUNCTIONIf pitot-static source malfunction is known or suspected:

1. Maintain aircraft control with safe attitude & thrust.

2. Compare pilot’s and copilot’s pitot-static data.

3. Pitot Heat:

a. Pitot Heat Switches..............................................................ON

b. L & R PITOT HEAT CBs (ess buses).....................................IN

4. Determine malfunctioning system:

a. Cross-check angle-of-attack indicators.

b. Compare indications with estimated performance for existingconditions.

c. Compare data from other available sources:

• Overspeed warning horn and stick puller are actuated byswitches in the copilot’s pitot-static system.

• FMS and SAT/TAS system (if installed) provide true airspeedfrom pilot’s side.

• DME systems and ground based radar provide a source forground speed. By applying the winds to ground speed, aircraftairspeed may be calculated.

• Pitot-static data to the autopilot/flight director is provided bythe copilot’s pitot system and shoulder static ports.

If static pressure malfunction is determined or suspected:

5. •Malfunction on copilot’s side:

a. Refer to pilot’s instruments.

•Malfunction on pilot’s side:

a. Alternate Static Source ...................................................OPEN

b. Pilot’s Altimeter ................................................................STBY

Refer to AFM for Airspeed and Altitude Position Correction Charts.

Without Rosemount Pitot-Static SystemEFFECTIVITY

11

CL-102B April 2001 A-25.1

b

ALL

EFFECTIVITY

PITOT-STATIC SYSTEM MALFUNCTIONIf pitot-static source malfunction is known or suspected:

1. Maintain aircraft control with safe attitude & thrust.

2. Compare pilot’s and copilot’s pitot-static data.

3. Pitot Heat:

a. Pitot Heat Switches..............................................................ON

b. L & R PITOT HEAT CBs (ess buses).....................................IN

4. Determine malfunctioning system:

a. Cross-check angle-of-attack indicators.

b. Compare indications with estimated performance for existingconditions.

c. Compare data from other available sources:

• Overspeed warning horn and stick puller will actuate if eitherpilot’s or copilot’s airspeed indicator needle is above the VMO/MMO “barber pole” pointer.

• FMS and SAT/TAS system (if installed) provide true airspeedfrom pilot’s side.

• DME systems and ground based radar provide a source forground speed. By applying the winds to ground speed, aircraftairspeed may be calculated.

• Pitot-static data to the autopilot/flight director is provided bythe copilot’s pitot-static system.

If static pressure malfunction is determined or suspected:

5. Autopilot.......................................................................DISENGAGE

6. STATIC SOURCE Switch ....................................................... L or R


12

With Rosemount Pitot-Static SystemEFFECTIVITY

11


EFFECTIVITY

V.G. MON LIGHT

One gyro wheel has failed. Remaining wheel is operative & gyro is reliable.Replace gyro as soon as practical.

ALTERNATE GEAR EXTENSION/ELECTRICAL MALFUNCTION

1. Airspeed VLO or less.


3. GEAR CB (copilot’s ess bus)................................................... PULL

4. To extend gear:

a. Emergency Gear Lever (right side pedestal) .......FULL DOWN

b. Gear Lights...................................... CHECK 3 GREEN, 2 RED

c. If any gear is not down and locked, refer to GEAR UP LAND-ING procedure, next page.

L VGMON

R VGMON

12

CL-102B April 2001 A-27

b

ALL

EFFECTIVITY

ANTI-SKID GEN LIGHT —ANTI-SKID OFF OPERATION

1. Anti-Skid Switch..........................................................OFF, then ON

If any ANTI-SKID GEN light(s) remain illuminated:

2. Anti-Skid Switch.........................................................................OFF

Refer to AFM, Section V for increased stopping distances for take-off and landing.

3. Brakes .........................................CAUTIOUSLY APPLY, AS REQ’D

4. Be prepared to use EMERGENCY BRAKING procedure, Tab 14,Emergency Checklist.

NOSE WHEEL STEERING MALFUNCTIONAt Normal Taxi Speed:

1. Nose Wheel Steering.............................. DISENGAGE (USE MSW)

2. Thrust Levers............................................................................ IDLE

3. Brake to a stop.

4. Taxi using differential braking and thrust.

During Takeoff:

1. Nose Wheel Steering.............................. DISENGAGE (USE MSW)

2. Continue takeoff using rudder and/or brakes for directional control.

GEAR UP LANDING1. Notify ATC.

2. Passengers.............................................................................BRIEF

a. Location and operation of emergency exits.

b. All loose items — Secure.

c. Shoulder harness and seat belts — Secure.

d. Emergency landing brace position.


L R

A N T I - S K I DA N T I - S K I D

12


EFFECTIVITY

3. No Smoking/Fasten Seat Belt Sign .............................................ON

4. Cabin Air ....................................................................................OFF

5. Flaps............................................................................................DN

6. Emergency Battery(ies) .............................................................OFF

7. • If no gear have extended, touch down slightly nose high.

• If the nose gear fails to extend:

a. Relocate passengers aft to obtain aft CG, if possible.

b. Auxiliary Hydraulic Pump .....................................................ON

c. Hold the nose off the runway as long as elevator control isavailable. If hydraulic pressure is available, normal brakingmay be available. Use rudder and/or brakes for directionalcontrol. Be prepared to use EMER BRAKE. Refer to EMER-GENCY BRAKING procedure, Tab 14, Emergency Checklist.

• If a main gear fails to extend, land on same side of the runway asthe extended gear.

a. Auxiliary Hydraulic Pump .....................................................ON

b. Anti-Skid Switch .................................................................OFF

c. Hold the applicable wing up as long as possible. Maintaindirectional control with rudder and nose wheel steering. Ifhydraulic pressure is available, braking may be available.Refer to ANTI-SKID GEN LIGHT — ANTI-SKID OFF OPERA-TION procedure, Tab 12, this section. Be prepared to useEMER BRAKE. Refer to EMERGENCY BRAKING procedure,Tab 14, Emergency Checklist.

8. Final Approach Speed ..............................................................VREF

9. Thrust Levers........................................CUTOFF @ TOUCHDOWN


After aircraft stops:

11. Batteries ....................................................................................OFF


a. Cabin Entry Door ............................................... OPEN & EXIT

b. Emergency Exit Window .................................... OPEN & EXIT

13

CL-102B April 2001 A-29

b

ALL

EFFECTIVITY

HYDRAULIC SYSTEM FAILURE LANDING1. Auxiliary Hydraulic Pump.............................................................ON2. • If auxiliary hydraulic pressure is available:

a. Flap Switch ..........................................................................DNb. When maximum flap angle is obtained:

(1) FLAP Switch ...............................NEUTRAL (if applicable)(2) Auxiliary Hydraulic Pump ............................................OFF(3) Go to step 3.

• If auxiliary hydraulic pressure is not available:a. Auxiliary Hydraulic Pump ...................................................OFFb. Go to step 3.

3. Final Approach Speed — As appropriate for flap deflection:Flaps UP...........................................................................VREF + 30Flaps 8° ............................................................................VREF + 20Flaps 20° ..........................................................................VREF + 10Flaps DN................................................................................... VREF

4. Landing Distance.................................................. MULTIPLY by 2.05. Crew Approach Briefing................................................ COMPLETE6. Emergency Brake Handle................................................PULL OUT

Just Prior to Landing:7. Auxiliary Hydraulic Pump.............................................................ON8. Yaw Damper ...................................................OFF (prior to landing)

After Touchdown:9. • If hydraulic pressure is maintained:

a. Spoilers .......................................................................EXTENDb. Brakes...................................................................... AS REQ’D

• If hydraulic pressure is not maintained:a. Emergency Brake Handle ........................PUSH DOWNWARDb. Rudder and/or Nose Wheel Steering ....................... AS REQ’DUse of drag chute or thrust reversers (if installed) recommended.

13


EFFECTIVITY

JAMMED STABILIZER LANDINGControl pressure will be heavy. Copilot assistance with this procedure isrecommended. Anticipate highest pull forces (approximately 75 pounds) atlanding flare.Elevator Pull Force:

1. Move C.G. aft if possible. Transfer fuel to fuselage if possible.


3. Configuration ................................................GEAR DN, FLAPS 20°

4. Final Approach Speed ...................................................... VREF + 20

5. Yaw Damper ...................................................OFF (prior to landing)

6. Landing Distance.................................................. MULTIPLY by 1.2

Elevator Push Force:

1. Move C.G. forward if possible. Transfer fuel to wing if possible.

2. Configuration ................................................ GEAR DN, FLAPS DN

3. Final Approach Speed ..............................................................VREF

ONE OR BOTH SPOILERS UP LANDING1. Configuration ................................................ GEAR DN, FLAPS UP




Use of drag chute or thrust reversers (if installed) recommended.

14


b

ALL

EFFECTIVITY

PARTIAL FLAP LANDING1. Hydraulic Pressure ...............................................................CHECK

• If pressure is low, refer to HYDRAULIC SYSTEM FAILURE/ALTERNATE GEAR EXTENSION procedure, Tab 11, this sectionand HYDRAULIC SYSTEM FAILURE LANDING procedure,Tab 13, this section.

• If pressure is normal, go to step 2.

2. Final Approach Configuration ...........................................GEAR DN

3. Final Approach Speed .................................. As APPROPRIATE forFLAP DEFLECTION

If actual flap deflection falls between those listed, use the finalapproach speed for the lesser flap deflection.


5. Landing Distance.........As APPROPRIATE for FLAP DEFLECTION

Use of drag chute or thrust reversers (if installed) recommended.

SINGLE-ENGINE LANDING1. Final Landing Configuration..........................GEAR DN, FLAPS 20°


3. Yaw Damper ...................................... OFF (just prior to touchdown)


15

FlapDeflection

FinalApproach Speed

Multiply LandingDistance By

UP VREF + 30 1.358° VREF + 20 1.30

20° VREF + 10 1.20

Change 2

14


EFFECTIVITY

STABILIZER HEAT FAILURE LANDINGIf buffet is encountered with full flaps:





WING HEAT FAILURE LANDINGLanding with any ice on wing leading edge:

1. Configuration ................................................ GEAR DN, FLAPS DN


3. Touchdown Speed ........................................15 knots above normal


WING & STAB HEAT FAILURE LANDINGLanding with wing and stabilizer ice:




4. Touchdown Speed ........................................25 knots above normal


15

CL-102B April 2001 A-33

b

ALL

EFFECTIVITY

TURBULENT AIR PENETRATION1. Airspeed — 250 KIAS or .73 MI whichever is less.

2. Thrust — Set & Ignition — ON

3. Attitude — Maintain wings level and desired pitch. Use attitude indi-cator as primary instrument.

4. Stabilizer — Maintain control with elevators. Do not change stabi-lizer trim after set for penetration.

5. Altitude — Allow altitude to vary.

6. Autopilot and Yaw Damper:

•Yaw Damper ................................................................... ENGAGED

•Autopilot Attitude Hold and Soft Modes.......................... ENGAGED


EFFECTIVITY

15

CL-102B April 2001 A-33.1

b

ALL

EFFECTIVITY










15

CL-102B April 2001 A-33.2

b

ALL

EFFECTIVITY

ONE THRUST REVERSER DEPLOYED LANDING1. Final Landing Configuration..........................GEAR DN, FLAPS 20°


3. Reverser Control Switch (operating engine)............................. ARM

4. Yaw Damper ...................................... OFF (just prior to touchdown)


6. Spoilers..................................................EXTEND (after touchdown)

7. Brakes ............................................................................. AS REQ’D

8. Reverser Lever (operating engine)............................IDLE/DEPLOY

9. Reverse Thrust (operating engine)............................. AS DESIRED

10. Rudder, Brakes, Steering................................................. AS REQ’D









16

With TR-4000 Thrust Reversers

EFFECTIVITY

15


EFFECTIVITY

CREW NOTES


16


EFFECTIVITY

INADVERTENT THRUSTREVERSER DEPLOYMENT

DURING FLIGHT1. Rudder & Ailerons ........................................................... AS REQ’D

2. Thrust Lever (affected engine).................................................. IDLE

3. Maintain Safe Airspeed...................................................... 200 MAX

4. Emer Stow Switch.......................................................EMER STOW

5. Bleed Air (affected engine) ........................................................OFF

If UNLOCK or DEPLOY Lights stay on:

6. Shut down affected engine. Refer to ENGINE SHUTDOWN INFLIGHT procedure, Tab 4, this section.

7. Fly single-engine approach & landing. Refer to SINGLE-ENGINELANDING procedure, Tab 12, this section.

UNLOCK LIGHT IN FLIGHT(THRUST REVERSER NOT DEPLOYED)

1. Affected Thrust Lever ............................................................... IDLE

2. Airspeed ..............................................................BELOW 200 KIAS

3. Emer Stow Switch.......................................................EMER STOW

4. Bleed Air (affected engine) ........................................................OFF

• If UNLOCK Light Extinguishes:

a. Emer Stow Switch .......................................................... NORM

b. Bleed Air (affected engine)...................................................ON

c. Affected Thrust Lever............................................... AS REQ’D

• If UNLOCK Light does not Extinguish:

a. Emer Stow Switch ...............................................EMER STOW

b. Bleed Air (affected engine)...................................................ON

c. Affected Thrust Lever............................................... AS REQ’D

DEPLOYUNLOCK

UNLOCK


16


EFFECTIVITY

ANNUNCIATED THRUST REVERSERMALFUNCTION (REVERSER NOT

DEPLOYED)Affected Engine:

1. Thrust Lever ............................................................................. IDLE2. Reverse Lever ....................................................................... STOW3. Reverser Control Switch............................................................OFF4. T/R CONTROL & T/R POWER CBs (main bus)...................... PULL5. Thrust Lever .................................................................... AS REQ’D6. If desired, continue flight using Normal Procedures.7. Do not use affected reverser on landing.

INADVERTENT THRUST REVERSER DEPLOYMENT DURING FLIGHT

Affected Engine:1. Thrust Lever ............................................................................. IDLE2. Reverser Lever ...................................................................... STOW3. Reverser Control Switch............................................................OFF4. T/R POWER CB (main bus) .................................................... PULL5. Assure Restow Envelope.6. • If DEPLOY light continues to flash or reverser remains

deployed:a. Shut down engine.b. T/R CONTROL CB (main bus)......................................... PULLc. Enroute Airspeed ............................................Above 160 KIASd. Land as soon as possible. Refer to ONE THRUST

REVERSER DEPLOYED LANDING procedure, Tab 15, thissection.

• If DEPLOY light stops flashing, ARM light goes out, and restowhas occurred:a. T/R CONTROL CB (main bus)......................................... PULLb. Continue flight using idle thrust.c. Refer to SINGLE-ENGINE LANDING procedure, Tab 12, this

section.d. Do not use affected reverser on landing.

DEPLOY

ARMDEPLOY


16

CL-102B April 2001 A-35

b

ALL

EFFECTIVITY

CREW NOTES


16

CL-102B April 2001 A-35.1

b

ALL

EFFECTIVITY

UNLOCK LIGHT AFTERNORMAL DEPLOY

Reverse thrust operation is permitted. Repair or pin affected thrustreverser before further flight.

FAILURE OF THRUST REVERSER TO STOW

AFTER LANDING

If DEPLOY & BLEED VALVE lights remain on:

1. Emer Stow Switch....................................................... EMER STOW

2. If reverser does not stow, shut down affected engine.

If DEPLOY light remains on:

1. Thrust Lever (affected engine) ................................................. IDLE

2. Emer Stow Switch....................................................... EMER STOW

If UNLOCK light remains on:

1. Shut down affected engine. Do not recycle thrust reverser.

UNLOCK

BLEEDVALVE

DEPLOY

UNLOCK


16

CL-102B April 2001 A-35.2

b

ALL

EFFECTIVITY

THRUST REVERSER RESTOW ENVELOPE

100 125 150 175 2000

5

10

15

20

INDICATED AIRSPEED — KNOTS

ALT

ITU

DE

— 1

000

FE

ET

ENGINE SHUTDOWNRESTOW ENVELOPE

ENGINE SHUTDOWNOR FLIGHT IDLE

RESTOW ENVELOPE


16

CL-102B April 2001 S-1ALL

EFFECTIVITY

b

SUPPLEMENTAL DATA

CONVERSION TABLESTEMPERATURE CONVERSIONS................................................S-2LINEAR CONVERSIONS..............................................................S-3VOLUME CONVERSIONS ...........................................................S-4WEIGHT CONVERSIONS ............................................................S-5

DUAL GENERATOR FAILURE ...............................................S-6EMER BATT CONDITIONS ..........................................................S-6

ENVIRONMENTALOXYGEN DURATION

Scott ATO Crew Masks ............................................................S-86600214 Series Crew Masks ...................................................S-9ZMR 100 Series Crew Masks ..................................................S-10

SCHEMATICSHYDRAULIC SYSTEM..................................................................S-11LANDING GEAR EXTENDED ......................................................S-12ALTERNATE LANDING GEAR .....................................................S-13DC ELECTRICAL SYSTEM ..........................................................S-14AC ELECTRICAL SYSTEM ..........................................................S-15FUEL SYSTEM .............................................................................S-16BLEED AIR SYSTEM....................................................................S-17BLEED AIR DISTRIBUTION .........................................................S-18PITOT-STATIC SYSTEM...............................................................S-19PRESSURIZATION CONTROL SYSTEM.....................................S-21

ADVISORY ANNUNCIATIONSENG SYNC ...................................................................................S-22NAC HT ON ..................................................................................S-22SPOILER.......................................................................................S-22STEER ON....................................................................................S-22T.O. TRIM......................................................................................S-23WSHLD HT ...................................................................................S-23

SUPP

LEM

ENTA

L D

ATA

CL-102BS-2 April 2001ALL

EFFECTIVITY

TEMPERATURE CONVERSION• To convert from Celsius to Fahrenheit, find, in bold face columns, the number

representing the Celsius temperature to be converted. The equivalent Fahr-enheit temperature is read in the adjacent column headed °F.

• To convert from Fahrenheit to Celsius, find, in bold face columns, the numberrepresenting the Fahrenheit temperature to be converted. The equivalentCelsius temperature is read in the adjacent column headed °C.

°F °C °F °C °F °C °F °C °F °C

-148.0 -100 -73.3 -58.0 -50 -45.6 32.0 0 -17.8 122.0 50 10.0 212.0 100 37.8-146.2 -99 -72.8 -56.2 -49 -45.0 33.8 1 -17.2 123.8 51 10.6 213.8 101 38.3-144.4 -98 -72.2 -54.4 -48 -44.4 35.6 2 -16.7 125.6 52 11.1 215.6 102 38.9-142.6 -97 -71.7 -52.6 -47 -43.9 37.4 3 -16.1 127.4 53 11.7 217.4 103 39.4-140.8 -96 -71.1 -50.8 -46 -43.3 39.2 4 -15.6 129.2 54 12.2 219.2 104 40.0-139.0 -95 -70.6 -49.0 -45 -42.8 41.0 5 -15.0 131.0 55 12.8 221.0 105 40.6-137.2 -94 -70.0 -47.2 -44 -42.2 42.8 6 -14.4 132.8 56 13.3 222.8 106 41.1-135.4 -93 -69.4 -45.4 -43 -41.7 44.6 7 -13.9 134.6 57 13.9 224.6 107 41.7-133.6 -92 -68.9 -43.6 -42 -41.1 46.4 8 -13.3 136.4 58 14.4 226.4 108 42.2-131.8 -91 -68.3 -41.8 -41 -40.6 48.2 9 -12.8 138.2 59 15.0 228.2 109 42.8-130.0 -90 -67.8 -40.0 -40 -40.0 50.0 10 -12.2 140.0 60 15.6 230.0 110 43.3-128.2 -89 -67.2 -38.2 -39 -39.4 51.8 11 -11.7 141.8 61 16.1 231.8 111 43.9-126.4 -88 -66.7 -36.4 -38 -38.9 53.6 12 -11.1 143.6 62 16.7 233.6 112 44.4-124.6 -87 -66.1 -34.6 -37 -38.3 55.4 13 -10.6 145.4 63 17.2 235.4 113 45.0-122.8 -86 -65.6 -32.8 -36 -37.8 57.2 14 -10.0 147.2 64 17.8 237.2 114 45.6-121.0 -85 -65.0 -31.0 -35 -37.2 59.0 15 -9.4 149.0 65 18.3 239.0 115 46.1-119.2 -84 -64.4 -29.2 -34 -36.7 60.8 16 -8.9 150.8 66 18.9 240.8 116 46.7-117.4 -83 -63.9 -27.4 -33 -36.1 62.6 17 -8.3 152.6 67 19.4 242.6 117 47.2-115.6 -82 -63.3 -25.6 -32 -35.6 64.4 18 -7.8 154.4 68 20.0 244.4 118 47.8-113.8 -81 -62.8 -23.8 -31 -35.0 66.2 19 -7.2 156.2 69 20.6 246.2 119 48.3-112.0 -80 -62.2 -22.0 -30 -34.4 68.0 20 -6.7 158.0 70 21.1 248.0 120 48.9-110.2 -79 -61.7 -20.2 -29 -33.9 69.8 21 -6.1 159.8 71 21.7 249.8 121 49.4-108.4 -78 -61.1 -18.4 -28 -33.3 71.6 22 -5.6 161.6 72 22.2 251.6 122 50.0-106.6 -77 -60.6 -16.6 -27 -32.8 73.4 23 -5.0 163.4 73 22.8 253.4 123 50.6-104.8 -76 -60.0 -14.8 -26 -32.2 75.2 24 -4.4 165.2 74 23.3 255.2 124 51.1-103.0 -75 -59.4 -13.0 -25 -31.7 77.0 25 -3.9 167.0 75 23.9 257.0 125 51.7-101.2 -74 -58.9 -11.2 -24 -31.1 78.8 26 -3.3 168.8 76 24.4 258.8 126 52.2-99.4 -73 -58.3 -9.4 -23 -30.6 80.6 27 -2.8 170.6 77 25.0 260.6 127 52.8-97.6 -72 -57.8 -7.6 -22 -30.0 82.4 28 -2.2 172.4 78 25.6 262.4 128 53.3-95.8 -71 -57.2 -5.8 -21 -29.4 84.2 29 -1.7 174.2 79 26.1 264.2 129 53.9-94.0 -70 -56.7 -4.0 -20 -28.9 86.0 30 -1.1 176.0 80 26.7 266.0 130 54.4-92.2 -69 -56.1 -2.2 -19 -28.3 87.8 31 -0.6 177.8 81 27.2 267.8 131 55.0-90.4 -68 -55.6 -0.4 -18 -27.8 89.6 32 0.0 179.6 82 27.8 269.6 132 55.6-88.6 -67 -55.0 1.4 -17 -27.2 91.4 33 0.6 181.4 83 28.3 271.4 133 56.1-86.8 -66 -54.4 3.2 -16 -26.7 93.2 34 1.1 183.2 84 28.9 273.2 134 56.7-85.0 -65 -53.9 5.0 -15 -26.1 95.0 35 1.7 185.0 85 29.4 275.0 135 57.2-83.2 -64 -53.3 6.8 -14 -25.6 96.8 36 2.2 186.8 86 30.0 276.8 136 57.8-81.4 -63 -52.8 8.6 -13 -25.0 98.6 37 2.8 188.6 87 30.6 278.6 137 58.3-79.6 -62 -52.2 10.4 -12 -24.4 100.4 38 3.3 190.4 88 31.1 280.4 138 58.9-77.8 -61 -51.7 12.2 -11 -23.9 102.2 39 3.9 192.2 89 31.7 282.2 139 59.4-76.0 -60 -51.1 14.0 -10 -23.3 104.0 40 4.4 194.0 90 32.2 284.0 140 60.0-74.2 -59 -50.6 15.8 -9 -22.8 105.8 41 5.0 195.8 91 32.8 285.8 141 60.6-72.4 -58 -50.0 17.6 -8 -22.2 107.6 42 5.6 197.6 92 33.3 287.6 142 61.1-70.6 -57 -49.4 19.4 -7 -21.7 109.4 43 6.1 199.4 93 33.9 289.4 143 61.7-68.8 -56 -48.9 21.2 -6 -21.1 111.2 44 6.7 201.2 94 34.4 291.2 144 62.2-67.0 -55 -48.3 23.0 -5 -20.6 113.0 45 7.2 203.0 95 35.0 293.0 145 62.8-65.2 -54 -47.8 24.8 -4 -20.0 114.8 46 7.8 204.8 96 35.6 294.8 146 63.3-63.4 -53 -47.2 26.6 -3 -19.4 116.6 47 8.3 206.6 97 36.1 296.6 147 63.9-61.6 -52 -46.7 28.4 -2 -18.9 118.4 48 8.9 208.4 98 36.7 298.4 148 64.4-59.8 -51 -46.1 30.2 -1 -18.3 120.2 49 9.4 210.2 99 37.2 300.2 149 65.0

SUPP

LEM

ENTA

L D

ATA


EFFECTIVITY

b

LINEAR CONVERSIONS• To convert from meters to feet, find, in the bold face columns, the

number of meters to be converted. The equivalent number of feet isread in the adjacent column headed FEET.

• To convert from feet to meters, find, in the bold face columns, thenumber of feet to be converted. The equivalent number of meters isread in the adjacent column headed METERS.

METERS FEET METERS FEET METERS FEET

304.8 1000 3280.8 1341.1 4400 14435.5 2377.5 7800 25590.2335.3 1100 3608.9 1371.6 4500 14763.6 2407.9 7900 25918.3365.8 1200 3937.0 1402.1 4600 15091.7 2438.4 8000 26246.4396.2 1300 4265.0 1432.6 4700 15419.8 2468.9 8100 26574.5426.7 1400 4593.1 1463.1 4800 15747.8 2499.4 8200 26902.6457.2 1500 4921.2 1493.5 4900 16075.9 2529.9 8300 27230.6487.7 1600 5249.3 1524.0 5000 16404.0 2560.4 8400 27558.7518.2 1700 5577.4 1554.5 5100 16732.1 2590.8 8500 27886.8548.6 1800 5905.4 1585.0 5200 17060.2 2621.3 8600 28214.9579.1 1900 6233.5 1615.5 5300 17388.2 2651.8 8700 28543.0609.6 2000 6561.6 1645.9 5400 17716.3 2682.3 8800 28871.0640.1 2100 6889.7 1676.4 5500 18044.4 2712.8 8900 29199.1670.6 2200 7217.8 1706.9 5600 18372.5 2743.2 9000 29527.2701.0 2300 7545.8 1737.4 5700 18700.6 2773.7 9100 29855.3731.5 2400 7873.9 1767.9 5800 19028.6 2804.2 9200 30183.4762.0 2500 8202.0 1798.3 5900 19356.7 2834.7 9300 30511.4792.5 2600 8530.1 1828.8 6000 19684.8 2865.2 9400 30839.5823.0 2700 8858.2 1859.3 6100 20012.9 2895.6 9500 31167.6853.5 2800 9186.2 1889.8 6200 20341.0 2926.1 9600 31495.7883.9 2900 9514.3 1920.3 6300 20669.0 2956.6 9700 31823.8914.4 3000 9842.4 1950.7 6400 20997.1 2987.1 9800 32151.8944.9 3100 10170.5 1981.2 6500 21325.2 3017.6 9900 32479.9975.4 3200 10498.6 2011.7 6600 21653.3 3048.0 10000 32808.0

1005.9 3300 10826.6 2042.2 6700 21981.4 3352.8 11000 36088.81036.3 3400 11154.7 2072.7 6800 22309.4 3657.6 12000 39369.61066.8 3500 11482.8 2103.1 6900 22637.5 3962.4 13000 42650.41097.3 3600 11810.9 2133.6 7000 22965.6 4267.3 14000 45931.21127.8 3700 12139.0 2164.1 7100 23293.7 4572.1 15000 49212.01158.3 3800 12467.0 2194.6 7200 23621.8 4876.9 16000 52492.81188.7 3900 12795.1 2225.1 7300 23949.8 5181.7 17000 55773.61219.2 4000 13123.2 2255.5 7400 24277.9 5486.5 18000 59054.41249.7 4100 13451.3 2286.0 7500 24606.0 5791.3 19000 62335.21280.2 4200 13779.4 2316.5 7600 24934.1 6096.1 20000 65616.01310.7 4300 14107.4 2347.0 7700 25262.2 6400.9 21000 68896.8


EFFECTIVITY

VOLUME CONVERSIONS• To convert from liters to gallons, find, in the bold face columns, the number of

liters to be converted. The equivalent number of gallons is read in the adja-cent column headed GALLONS.

• To convert from gallons to liters, find, in the bold face columns, the number ofgallons to be converted. The equivalent number of liters is read in the adja-cent column headed LITERS.

LITERS GALLONS LITERS GALLONS LITERS GALLONS

18.9 5 1.3 1476.2 390 103.0 2952.3 780 206.137.9 10 2.6 1514.0 400 105.7 2990.2 790 208.775.7 20 5.3 1551.9 410 108.3 3028.0 800 211.4

113.6 30 7.9 1589.7 420 111.0 3065.9 810 214.0151.4 40 10.6 1627.6 430 113.6 3103.7 820 216.6189.3 50 13.2 1665.4 440 116.2 3141.6 830 219.3227.1 60 15.9 1703.3 450 118.9 3179.4 840 221.9265.0 70 18.5 1741.1 460 121.5 3217.3 850 224.6302.8 80 21.1 1779.0 470 124.2 3255.1 860 227.2340.7 90 23.8 1816.8 480 126.8 3293.0 870 229.9378.5 100 26.4 1854.7 490 129.5 3330.8 880 232.5416.4 110 29.1 1892.5 500 132.1 3368.7 890 235.1454.2 120 31.7 1930.4 510 134.7 3406.5 900 237.8492.1 130 34.3 1968.2 520 137.4 3444.4 910 240.4529.9 140 37.0 2006.1 530 140.0 3482.2 920 243.1567.8 150 39.6 2043.9 540 142.7 3520.1 930 245.7605.6 160 42.3 2081.8 550 145.3 3557.9 940 248.3643.5 170 44.9 2119.6 560 148.0 3595.8 950 251.0681.3 180 47.6 2157.5 570 150.6 3633.6 960 253.6719.2 190 50.2 2195.3 580 153.2 3671.5 970 256.3757.0 200 52.8 2233.2 590 155.9 3709.3 980 258.9794.9 210 55.5 2271.0 600 158.5 3747.2 990 261.6832.7 220 58.1 2308.9 610 161.2 3785.0 1000 264.2870.6 230 60.8 2346.7 620 163.8 4163.5 1100 290.6908.4 240 63.4 2384.6 630 166.4 4542.0 1200 317.0946.3 250 66.1 2422.4 640 169.1 4920.5 1300 343.5984.1 260 68.7 2460.3 650 171.7 5299.0 1400 369.9

1022.0 270 71.3 2498.1 660 174.4 5677.5 1500 396.31059.8 280 74.0 2536.0 670 177.0 6056.0 1600 422.71097.7 290 76.6 2573.8 680 179.7 6434.5 1700 449.11135.5 300 79.3 2611.7 690 182.3 6813.0 1800 475.61173.4 310 81.9 2649.5 700 184.9 7191.5 1900 502.01211.2 320 84.5 2687.4 710 187.6 7570.0 2000 528.41249.1 330 87.2 2725.2 720 190.2 7948.5 2100 554.81286.9 340 89.8 2763.1 730 192.9 8327.0 2200 581.21324.8 350 92.5 2800.9 740 195.5 8705.5 2300 607.71362.6 360 95.1 2838.8 750 198.2 9084.0 2400 634.11400.5 370 97.8 2876.6 760 200.8 9462.5 2500 660.51438.3 380 100.4 2914.5 770 203.4 9841.0 2600 686.9


EFFECTIVITY

b

WEIGHT CONVERSIONS• To convert from kilograms to pounds, find, in the bold face columns, the num-

ber of kilograms to be converted. The equivalent number of pounds is read inthe adjacent column headed POUNDS.

• To convert from pounds to kilograms, find, in the bold face columns, the num-ber of pounds to be converted. The equivalent number of kilograms is read inthe adjacent column headed KILOGRAMS.

KILOGRAMS POUNDS KILOGRAMS POUNDS KILOGRAMS POUNDS4.5 10 22.0 208.7 460 1014.1 412.8 910 2006.29.1 20 44.1 213.2 470 1036.2 417.3 920 2028.2

13.6 30 66.1 217.7 480 1058.2 421.8 930 2050.318.1 40 88.2 222.3 490 1080.3 426.4 940 2072.322.7 50 110.2 226.8 500 1102.3 430.9 950 2094.427.2 60 132.3 231.3 510 1124.3 435.5 960 2116.431.8 70 154.3 235.9 520 1146.4 440.0 970 2138.536.3 80 176.4 240.4 530 1168.4 444.5 980 2160.540.8 90 198.4 244.9 540 1190.5 449.1 990 2182.645.4 100 220.5 249.5 550 1212.5 453.6 1000 2204.649.9 110 242.5 254.0 560 1234.6 499.0 1100 2425.154.4 120 264.6 258.6 570 1256.6 544.3 1200 2645.559.0 130 286.6 263.1 580 1278.7 589.7 1300 2866.063.5 140 308.6 267.6 590 1300.7 635.0 1400 3086.468.0 150 330.7 272.2 600 1322.8 680.4 1500 3306.972.6 160 352.7 276.7 610 1344.8 907.2 2000 4409.277.1 170 374.8 281.2 620 1366.9 1134.0 2500 5511.581.6 180 396.8 285.8 630 1388.9 1360.8 3000 6613.886.2 190 418.9 290.3 640 1410.9 1587.6 3500 7716.190.7 200 440.9 294.8 650 1433.0 1814.4 4000 8818.495.3 210 463.0 299.4 660 1455.0 2041.2 4500 9920.799.8 220 485.0 303.9 670 1477.1 2268.0 5000 11023.0

104.3 230 507.1 308.4 680 1499.1 2494.8 5500 12125.3108.9 240 529.1 313.0 690 1521.2 2721.6 6000 13227.6113.4 250 551.1 317.5 700 1543.2 2948.4 6500 14329.9117.9 260 573.2 322.1 710 1565.3 3175.2 7000 15432.2122.5 270 595.2 326.6 720 1587.3 3402.0 7500 16534.5127.0 280 617.3 331.1 730 1609.4 3628.8 8000 17636.8131.5 290 639.3 335.7 740 1631.4 3855.6 8500 18739.1136.1 300 661.4 340.2 750 1653.4 4082.4 9000 19841.4140.6 310 683.4 344.7 760 1675.5 4309.2 9500 20943.7145.2 320 705.5 349.3 770 1697.5 4536.0 10000 22046.0149.7 330 727.5 353.8 780 1719.6 4989.6 11000 24250.6154.2 340 749.6 358.3 790 1741.6 5443.2 12000 26455.2158.8 350 771.6 362.9 800 1763.7 5896.8 13000 28659.8163.3 360 793.7 367.4 810 1785.7 6350.4 14000 30864.4167.8 370 815.7 371.9 820 1807.8 6804.0 15000 33069.0172.4 380 837.7 376.5 830 1829.8 7257.6 16000 35273.6176.9 390 859.8 381.0 840 1851.9 7711.1 17000 37478.2181.4 400 881.8 385.6 850 1873.9 8164.7 18000 39682.8186.0 410 903.9 390.1 860 1896.0 8618.3 19000 41887.4190.5 420 925.9 394.6 870 1918.0195.0 430 948.0 399.2 880 1940.0199.6 440 970.0 403.7 890 1962.1204.1 450 992.1 408.2 900 1984.1


EFFECTIVITY

DUAL GENERATOR FAILURE

EMER BATT CONDITIONS

When the ship’s batteries are depleted the only electrical power availablewill be from the Emergency Power Supply.

The following conditions will exist:

EQUIPMENT AND TOTAL OPERATING TIME FOR SINGLEEMERGENCY POWER SUPPLY INSTALLATION

SWITCH POSITION

STANDBYGYRO GEAR FLAPS

OPERATING TIME

ON • • • 30 minutesSTBY • 3 hrs. 45 min.

SYSTEM CONDITIONAnti-Ice All systems inoperative. Nacelle Heat (bleed air) will be

on regardless of NAC HEAT Switch position.Anti-Skid Inoperative.Autopilot/Yaw Dmpr Inoperative.Aux Hyd Pump Inoperative.Avionics Inoperative.Engines Fuel Computer Inoperative.Engine Fire Detection Extinguishing

Inoperative.Inoperative.

Flaps Operative with EMER BAT 1 selected ON.Fuel Jet Pumps Standby Pumps System Valves

Operative.Inoperative.Will remain in their last position.

Ignition Inoperative.

LGEN

RGEN



EFFECTIVITY

b

35-107, 113 & on; and 36-032 & on

Indicators N1 N2 ITT Flap Position RAT Oil Pressure Oil Temperature Fuel Flow Fuel Counter Fuel Quantity Wing Temp Stab Temp

Inoperative.Inoperative.Inoperative.Inoperative.Inoperative.Inoperative.Inoperative.Inoperative.Inoperative.Inoperative.Inoperative.Inoperative.

Instruments ADI Airspeed/Mach Altimeter

Without RosemountWith Rosemount

HSI Standby Gyro VSI

Both Inoperative.Both Operative.

Both Operative (pilot’s reverts to STBY)Both Operative.Inoperative.Operative.Direct baro-static instruments - Operative; Electrically-servoed instruments - Inoperative.

Landing Gear Operative with EMER BAT 1 selected ON.Lighting-Cockpit Floodlights Instruments

Inoperative.Lighting for standby gyro and magnetic compass will be operative. For night operations a flashlight may be nec-essary to see certain instruments.

Lighting-Exterior Inoperative.Pressurization

Auto ModeManual Mode Emer Press Valves

Operative.Inoperative.Revert to emergency mode.

Spoilers/Spoilerons Inoperative.Trim Pitch, Roll & Yaw Mach

Inoperative.Inoperative. Do not exceed MMO (0.74 MI).

Warning System Lights Horns Stall Warning

Stick Puller

Inoperative.Inoperative.Inoperative. Maintain adequate margin above stall speed by reference to airspeed indicator.Inoperative.

SYSTEM CONDITION


EFFECTIVITY

OXYGEN DURATION — MINUTESAIRCRAFT WITH SCOTT ATO CREW MASKS

FULLY CHARGED SYSTEM

• Bold face numbers (xxx) indicate 100% oxygen.• Light face numbers (xxx) indicate Diluter Demand.• Crew and passenger oxygen masks are not approved for use above 40,000 feet cabin al-

titude. Passenger durations above 30,000 feet cabin altitude are provided for infor-mation only. Passenger masks will not provide sufficient oxygen for prolongedoperation above 34,000 feet cabin altitude. Prolonged operation above 25,000 feetcabin altitude with passengers on board is not recommended.

• Prior to overwater flights, plan oxygen requirements to provide sufficient oxygen for all oc-cupants in the event of a pressurization failure. Additional oxygen may be required to as-sure that both oxygen duration and range (fuel) requirements are satisfied.

• For cabin altitudes of 10,000 feet and above, the oxygen duration times includecabin altitude ascent time from 8000 feet to final stabilized cabin altitude.

• To calculate oxygen duration for a less than fully charged system the following for-mula may be used:

Duration = Duration from chart x (system pressure ÷ 1850)

2 Crew 2 Crew 2 Crew 2 Crew 2 Crew 2 Crew 2 Crew— 2 Pass 4 Pass 6 Pass 8 Pass 9 Pass 11 Pass

Fina

l Sta

biliz

ed C

abin

Alti

tude

— 1

000

Feet

40261 82 50 36 28 26 22

251 79 48 35 27 25 21

35192 75 47 35 28 25 22

182 71 45 33 26 24 20

30145 68 45 34 27 25 22

135 64 42 32 26 24 20

25153 70 46 34 28 25 22

105 56 39 30 25 24 20

20203 78 49 37 29 27 23

84 50 36 29 24 23 20

15261 86 53 39 32 29 25

67 45 34 28 24 23 20

10253

PASSENGER OXYGEN NOT REQUIRED

54

8153

50

7148

48


EFFECTIVITY

b

OXYGEN DURATION — MINUTESAIRCRAFT WITH 6600214 SERIES CREW MASKS


• Bold face numbers (xxx) indicate 100% oxygen.• Light face numbers (xxx) indicate Diluter Demand.• Crew and passenger oxygen masks are not approved for use above 40,000 feet cabin al-



• For cabin altitudes of 10,000 feet and above, the oxygen duration times includecabin altitude ascent time from 8000 feet to final stabilized cabin altitude.

• To calculate oxygen duration for a less than fully charged system the following for-mula may be used:



Fina

l Sta

biliz

ed C

abin

Alti

tude

— 1

000

Feet

40267 84 51 36 29 26 22

251 79 47 34 27 24 21

35195 76 48 35 28 26 22

182 71 45 33 26 24 21

30219 79 49 36 29 26 22

135 64 42 32 26 23 20

25252 83 50 37 29 26 22

105 56 39 30 25 23 20

20228 81 51 37 30 27 24

84 50 37 29 25 23 20

15192 77 50 37 31 28 24

67 45 34 28 24 23 20

10163

54

8153 PASSENGER OXYGEN NOT REQUIRED50

7148

48


EFFECTIVITY

OXYGEN DURATION — MINUTESAIRCRAFT WITH ZMR 100 SERIES CREW MASKS


• Bold face numbers (xxx) indicate 100% oxygen (100% OXY position on regulator). • Light face numbers (xxx) indicate Diluter Demand (NORMAL position on regulator). • Crew and passenger oxygen masks are not approved for use above 40,000 feet cabin al-



• For cabin altitudes of 10,000 feet and above, the oxygen duration times include cabinaltitude ascent time from 8000 feet to final stabilized cabin altitude.

• To calculate oxygen duration for a less than fully charged system the following formulamay be used:



Fina

l Sta

biliz

ed C

abin

Alti

tude

— 1

000

Feet

40 251 80 48 35 28 25 22

35 182 71 45 33 26 24 20

30 135 63 42 32 26 23 20

25 105 56 39 30 25 23 20

20175 73 47 35 29 26 23

84 51 37 29 25 23 20

15124 63 44 34 28 26 23

67 45 34 28 24 23 20

1091

54

882 PASSENGER OXYGEN NOT REQUIRED50

778

48


EFFECTIVITY

b

ENG FIREPULL

ENG FIREPULL

LO HYDPRESS

LANDING GEARDOOR

SELECTORVALVE

FLAPSYSTEM

SPOILERSYSTEM

BRAKESYSTEM

LANDINGGEAR

SELECTORVALVE

THRUSTREVERSERS

BLEED AIR

FILTER

REGULATOR

RELIEFVALVE(20 PSI)

VARIABLE-VOLUMEENGINE-DRIVEN

PUMP (2)

LEGEND

PRESSURE

SUPPLY

RETURN

AIR (NITROGEN)

BLEED AIR

REGULATED BLEED AIR

ELECTRICAL

FILTER

ACCUMULATOR

OVERBOARD

VACUUMRELIEF

GROUNDSERVICE

AUXILIARYPUMP

PRESSURESWITCH

HYDPUMP

1700PSI

*TR 4000 T/R Only

*TR 4000 T/R

HYDRAULIC SYSTEM


EFFECTIVITY

LANDING GEAR EXTENDED

GE

AR

CO

NT

RO

LV

ALV

E

DO

OR

CO

NT

RO

LV

ALV

E

EM

ER

AIR

BO

TT

LE

TO

EM

ER

GE

NC

YB

RA

KE

S

SO

L

SO

LS

OL

SO

L

EX

TE

ND

RE

TR

AC

T DO

OR

AC

TU

AT

OR

MA

ING

EA

RA

CT

UA

TO

RU

PLA

TC

H

UP

LAT

CH

MA

ING

EA

RA

CT

UA

TO

R

GE

AR

INB

OA

RD

DO

OR

NO

SE

GE

AR

AC

TU

AT

OR

UP

LAT

CH

AC

TU

AT

OR

UP

LAT

CH

AC

TU

AT

OR

UP

LAT

CH

AC

TU

AT

OR

UP

LAT

CH

TO

BR

AK

ES

YS

TE

M

OV

ER

BO

AR

D

GE

AR

ALT

ER

NA

TE

EX

TE

NS

ION

CO

NT

RO

L V

ALV

E

LE

GE

ND

SY

ST

EM

HY

DR

AU

LIC

PR

ES

SU

RE

RE

TU

RN

AIR

PR

ES

SU

RE

PR

IOR

ITY

VA

LVE


EFFECTIVITY

b

ALTERNATE LANDING GEAR

��

SO

L

SO

LS

OL

SO

L

EX

TE

ND

RE

TR

AC

T

GE

AR

CO

NT

RO

LV

ALV

E

DO

OR

CO

NT

RO

LV

ALV

E

DO

OR

AC

TU

AT

OR

MA

ING

EA

RA

CT

UA

TO

R

DO

OR

AC

TU

AT

OR

UP

LAT

CH

UP

LAT

CH

AC

TU

AT

OR

UP

LAT

CH

MA

ING

EA

RA

CT

UA

TO

R

GE

AR

DO

OR

NO

SE

GE

AR

AC

TU

AT

OR

UP

LAT

CH

AC

TU

AT

OR

EM

ER

AIR

BO

TT

LE

UP

LAT

CH

TO

BR

AK

ES

YS

TE

M

TO

EM

ER

GE

NC

YB

RA

KE

VA

LVE

PR

IOR

ITY

VA

LVE

OV

ER

BO

AR

D

GE

AR

ALT

ER

NA

TE

EX

TE

NS

ION

CO

NT

RO

L V

ALV

E

LE

GE

ND

RE

TU

RN

AIR

PR

ES

SU

RE

UP

LAT

CH

AC

TU

AT

OR


EFFECTIVITY

BATTERY CHARGING BUSR

GEN

DC VOLTS

LGEN R GEN BUS

BATTERY POWER

LEGEND

GENERATOR POWER

GROUND POWER

AMPS

L GEN BUS

BAT 1

1

1

2

1

AMPS

OFF

BAT 2

OFF

LEFTBATTERY

EX

T P

OW

ER

OV

ER

VO

LTA

GE

CU

TO

UT

RIGHTBATTERY

2

LEFT ESS BUS

LEFT MAIN BUS

RIGHT ESS BUS

RIGHT MAIN BUS

OVERLOADSENSOR

OVERLOADSENSOR

GPU

CURLIM

Failure of one or both current limiters is indicated by illumination of the CUR LIM light.

Relay is energized when either BAT 1 or BAT 2 is selected.

DC ELECTRICAL SYSTEM

Without Split Essential BusesEFFECTIVITY

CL-102BS-14.1 April 2001ALL

EFFECTIVITY

DC ELECTRICAL SYSTEM


GEN

DC VOLTS

LGEN R GEN BUS

BATTERY POWER

LEGEND

GENERATOR POWER

GROUND POWER

AMPS

L GEN BUS

BAT 1

1

1

2

1

AMPS

OFF

BAT 2

OFF

LEFTBATTERY

EX

T P

OW

ER

OV

ER

VO

LTA

GE

CU

TO

UT

RIGHTBATTERY

2

LEFT ESS B BUS

LEFT ESS A BUS

LEFT MAIN BUS

RIGHT ESS B BUS

RIGHT ESS A BUS

RIGHT MAIN BUS

OVERLOADSENSOR

OVERLOADSENSOR

GPU

CURLIM

Failure of one or both current limiters is indicated by illumination of the CUR LIM light.

Relay is energized when either BAT 1 or BAT 2 is selected.

35-001 thru 35-508; 36-001 thru 36-053 not incorporating AMK 85-135-509 & on; 36-054 & on; and prior aircraft incorporating AMK-85-1

With Split Essential BusesEFFECTIVITY


EFFECTIVITY

b

AC ELECTRICAL SYSTEM


GEN

AC VOLTS

LGEN

R GENBUS

BATTERY POWER

LEGEND

GENERATOR POWER

GROUND POWER

INVERTER POWER

L GENBUS

PRI

OFF

AIRCRAFT EQUIPPED WITH AUX INVERTER.

OV

ER

LOA

DS

EN

SO

R

ON

OFF

OV

ER

LOA

DS

EN

SO

R

SEC

OFF

OV

ER

LOA

DS

EN

SO

R

*

PARALLELING CONTROL BOX

L AC BUS

R AC BUS

26 VAC

BUS

26 V ACBUS CB

26 V ACBUS CB

PRI ACVM

SEC ACVM

AC BUS TIECB

AC BUSPRI

SEC

TRANS26 V

ACBUS

TRANS

L ACBUS CB

L AUX ACBUS CB

R AUX ACBUS CB

R ACBUS CB

L BUS

R BUS

AUX INVPRI-SEC SW

PRIMARYINVERTER

AUXINVERTER

SECONDARYINVERTER

*


EFFECTIVITY

FUEL SYSTEM

CLO

SE

D

*F

US

VA

LV

E

*W

ITH

GR

AV

ITY

-FL

OW

LIN

E

CR

OS

SF

LO

WO

PE

N

LE

GE

ND

FLO

AT

SW

ITC

H

FIL

LE

R C

AP

TR

AN

SF

ER

PU

MP

EN

GIN

E F

UE

L P

UM

P

ST

AN

DB

Y P

UM

P

JET

PU

MP

PR

ES

S R

ELIE

F V

ALV

E

FU

EL F

ILT

ER

CR

OS

SF

LO

W V

ALV

E

SH

UT

OF

F V

ALV

E

MO

TIV

E F

LO

W V

ALV

E

TR

AN

SF

ER

VA

LV

E

JET

TIS

ON

VA

LV

E

PR

ES

SU

RE

SW

ITC

H

RE

LIE

F V

ALV

E

CH

EC

K V

ALV

E

AM

BE

R P

EA

NU

T L

IGH

T

GR

EE

N P

EA

NU

T L

IGH

T

CLE

AR

PE

AN

UT

LIG

HT

HIG

H P

RE

SS

UR

E F

UE

L

LO

W P

RE

SS

UR

E F

UE

L

ELE

CT

RIC

AL

LO

WF

UE

L

FU

EL

FIL

TE

RL F

UE

LP

RE

SS

EN

G F

IRE

PU

LL L J

ET

PU

MP

JET

PU

MP

R J

ET

PU

MP

A

C

A

A

FU

EL

JTS

N

A

CLO

SE

R F

UE

LP

RE

SS

G

EN

G F

IRE

PU

LL

S

OF

F

O F F

OF

F

ON

ST

AN

DB

Y P

UM

P

L

ON

L G

EN

ST

AR

T

O F F

R G

EN

ST

AR

T

L

RR

OP

EN

OP

EN

EM

PT

Y

FU

LLO

PE

N

FIL

L

O F F

XF

R

L X

FR

VA

LV

E

AR

XF

RV

ALV

E

FU

S T

AN

K

A G C

JET

PU

MP

OF

F

OF

F

ON

ST

AN

DB

Y P

UM

P

FU

EL J

TS

N

FU

EL

JTS

NA

FU

EL

XLO

WC

RO

SS

FLO

WA

MMS

J

TT

J

S M T J


EFFECTIVITY

b

BLEED AIRSHUTOFF ANDREGULATOR(MOD) VALVE

NACELLE ANTI-ICE

STABILIZER ANDWING ANTI-ICE

BLEED AIRMANIFOLD

WINDSHIELDANTI-ICE

HYDRAULICRESERVOIR

TOCABIN

FLOWCONTROL

VALVE

DUCT TEMPSENSOR

BLEEDAIR R

BLEEDAIR L

LEGEND

HP BLEED AIR

LP BLEED AIR

REGULATED BLEED AIR

PYLON TEMPSENSOR

*FAN SPINNERANTI-ICE

HP BLEED AIR

LPBLEED

AIR **T/R AIRMOTOR

**T/R AIRMOTOR

PRESSURIZATIONJET PUMP

*NOT APPLICABLE ON AIRPLANE EQUIPPED WITH CONICAL SPINNER (AAK 79-4)

**AERONCA T/R


BLEED AIR SYSTEM


EFFECTIVITY

CL-102B April 2001 S-17.1ALL

EFFECTIVITY

b

BLEED AIR SYSTEM


NACELLE ANTI-ICE

STABILIZER ANDWING ANTI-ICE

BLEED AIRMANIFOLD

WINDSHIELDANTI-ICE

HYDRAULICRESERVOIR

CABIN DUCTEMERPRESS VALVE

TOCABIN

FLOWCONTROL

VALVE

HP BLEEDAIR MANIFOLD

DUCT TEMPSENSOR

BLEEDAIR R

BLEEDAIR L

LEGEND

HP BLEED AIR

LP BLEED AIR

REGULATED BLEED AIR

REGULATED SERVO AIR

EMER RON

OFF

L EMERON

OFFBLEED AIR

SHUTOFF ANDREGULATOR(MOD) VALVE

CABIN DUCT

PYLON TEMPSENSOR

EMER PRESSVALVE

*FAN SPINNERANTI-ICE

HP BLEED AIR

LPBLEED

AIR **T/R AIRMOTOR

**T/R AIRMOTOR

BLEED-AIR SHUTOFFAND REGULATOR VALVE

TEMP CONTROL

REGULATOR

ALCOHOL ANTI-ICE

FLOW CONTROL VALVE

PRESSURIZATIONJET PUMP

EMER PRESS VALVES

*NOT APPLICABLE ON AIRPLANE EQUIPPED WITH CONICAL SPINNER (AAK 79-4)

**AERONCA T/R



EFFECTIVITY

CABAIR

OFF

INTERNAL DEFOGOUTLETS

FOOTWARMER OUTLET

LEGENDREGULATED BLEED AIR

RAM AIR

CONDITIONED BLEED AIR

FLOW CONTROL VALVE

HOT AIR BYPASS(H-VALVE)

RAM AIR OUT

HEAT EXCHANGER

RAM AIR IN

DUCT TEMPSENSOR

RAM-AIR CHECKVALVE

DUCT TEMPLIMITER

BAGGAGE COMPARTMENTAIR DIFFUSER(35 & 35A ONLY)

CABIN AIR DIFFUSERS(TYPICAL)

CABIN TEMPSENSOR

CREW OUTLETS

CHECK VALVE

TEMP

CONT

COLD

HOT

COLD

HOT

HOT

MAN

NORM

MAXBLEED AIR(RIGHT ENGINE)

BLEED AIR(LEFT ENGINE)

MAN

RMAINBUS

CABHT

MNL

CABHT

AUTO

LMAINBUS

TEMPCONT

LMAINBUS

AUTO

BLEED AIR DISTRIBUTION

35-001 thru 35-081 & 35-083 thru 35-086; and 36-001 thru 36-022 not incorporating AMK 76-7

EFFECTIVITY


EFFECTIVITY

CABAIR

OFF


RAM AIR


FLOW CONTROL VALVE


RAM AIR OUT

HEAT EXCHANGER

RAM AIRIN

DUCT TEMPSENSOR

RAM-AIR CHECKVALVE

CABIN TEMPSENSOR

CHECK VALVE

TEMP

CONT

COLD

HOTCOLD

HOT

HOT

MAN

NORM

MAX

BLEED AIR(RIGHT ENGINE)


MAN

RMAINBUS

CABHT

MNL

CABHT

AUTO

LMAINBUS

TEMPCONT

LMAINBUS

AUTO


FOOTWARMER OUTLET

DUCT TEMPLIMITER

BAGGAGE COMPARTMENTAIR DIFFUSER(35 & 35A ONLY)


CREW OUTLETS

PRESSURE SWITCH

BLEEDAIR L

BLEEDAIR R


35-082, 35-087 thru 35-106 & 35-108 thru 35-112; 36-023 thru 36-031; and prior aircraft incorporating

AMK 76-7

EFFECTIVITY


EFFECTIVITY


CABAIR

ON

OFF


FOOTWARMER OUTLET

AUX/DEFOGCREWHEATER*


RAM AIR


SERVO AIR

EMERGENCYPRESSURIZATIONVALVE

BLEED AIR(RIGHT ENGINE)

FLOW CONTROL VALVE


HPSERVOBLEED

AIR

RAM AIR OUT

HEAT EXCHANGER

RAM AIR IN

DUCT TEMPSENSOR

RAM-AIR CHECKVALVE

HPSERVOBLEED

AIR DUCT TEMPLIMITER


BAGGAGE COMPARTMENTAIR DIFFUSER(35A ONLY)


CABIN TEMPSENSOR

CREW OUTLETS

BLOWERMOTOR

CHECK VALVE

EMER RON

OFF

L EMERON

OFF

TEMP

CONT

COLD

HOT

COLD HOT

MANAUTO

* 35-643 and on, 36-064 and on; and prior aircraft incorporating auxiliary defog system.



EFFECTIVITY

b

PITOT-STATIC SYSTEM

ALTITUDEPRESSURE

SWITCH

ALTIMETER(COPILOT)

PILOT’S PITOT

COPILOT’S PITOT

PILOT’S STATIC

COPILOT’S STATIC

ALTERNATE STATIC

SHOULDER STATIC

DRAIN VALVERH SHOULDER STATIC PORT

RH PITOT HEADAIR DATASENSOR

DRAIN VALVERH FWDSTATIC PORT

DRAIN VALVE

RH CENTERSTATIC PORT

ALTITUDEPRESSURE

SWITCH

AIRSPEED AND MACHINDICATOR (PILOT)

MACH WARNING ANDLOW OVERSPEED SWITCH

MACH TRIM AND HIGHALTITUDE OVERSPEEDSWITCH

RATE OF CLIMB(COPILOT)

NOTE: EXTERNAL STATIC PORTS ARE HEATED WHENEVER A BATTERY IS ON

AIRSPEED AND MACHINDICATOR (COPILOT)

FORWARDPRESSUREBULKHEADSTATIC PORT

INSTRUMENT ALTERNATESTATIC SOURCE VALVE

RATE OF CLIMB(PILOT)

ALTIMETER(PILOT)

ALTITUDEALERTER

STATIC DEFECTCORRECTION

MODULE

LH AFTSTATIC PORT

DRAIN VALVE

LH FWDSTATIC PORT

DRAIN VALVE

LH SHOULDER STATIC PORT

LH PITOT HEAD

LEGEND

PITOT HTL R

OFF OFF

PITOTHEAT

TAT PROBE(If Installed) R STALL

VANEL STALL

VANE

Without Rosemount Pitot-Static SystemEFFECTIVITY


EFFECTIVITY

b

PITOT-STATIC SYSTEM

With Rosemount Pitot-Static SystemEFFECTIVITY

GEAR WARNING AIRSPEED SWITCH

GEAR WARNINGALTITUDE SWITCH

OPTIONALEQUIPMENT

AIR DATA UNIT

TAT PROBE(If Installed) R STALL

VANEL STALL

VANE

RATE-OF-CLIMBINDICATOR (COPILOT)

ALTIMETER (COPILOT)

MACHSWITCH

RATE-OF-CLIMBINDICATOR (PILOT)

MACH/AIRSPEEDINDICATOR

MACH/AIRSPEEDINDICATOR

SOLENOIDVALVES

SOLENOIDVALVES

PITOT

STATIC 1

COPILOT’SPITOT-STATIC

HEAD

DRAINSDRAINS

PILOT’SPITOT-STATICHEAD

PITOT

STATIC 1

STATIC 2STATIC 2

ALTIMETER (PILOT)

LEGEND

PILOT’S PITOT

COPILOT’S PITOT

PILOT’S STATIC

COPILOT’S STATIC

PITOT HTL R

OFF OFF

PITOTHEAT

STATICSOURCE

BOTH

RL

NOTE: WHEN STATIC SOURCE SWITCH IS IN THE BOTH POSITION, ALL FOURSHUTOFF VALVES ARE DEENERGIZED OPEN.

WHEN STATIC SOURCE SWITCH IS IN THE L OR R POSITION, THE SHUTOFF VALVESFOR THE OPPOSITE STATIC PROBES ARE ENERGIZED CLOSED.


EFFECTIVITY

CREW NOTES


EFFECTIVITY

b

PRESSURIZATION CONTROL SYSTEM

DN

UP

ST

AT

IC P

OR

T(E

XT

ER

NA

L A

IRC

RA

FT

)C

AB

ALT

LIM

11,5

00 F

T _

1,5

00 F

T+

CA

BIN

PR

ES

S

OU

TF

LOW

VA

LVE

8.7

PS

ID

PR

ES

S D

IFF

RE

LIE

F 8

.9 P

SID

SO

L V

ALV

E (

N.O

.)E

NE

RG

IZE

D C

LOS

ED

IN M

AN

UA

L O

RA

BO

VE

10,

000

FT

NO

CA

BIN

ALT

LIG

HT

SO

L V

ALV

E (

NC

)E

NE

RG

IZE

D O

PE

NO

N G

ND

WIT

HC

AB

AIR

OF

F1

SO

L V

ALV

E (

NC

)E

NE

RG

IZE

D O

PE

NO

N G

ND

CO

NT

RO

L P

RE

SS

UR

E(V

AC

UU

M)

SO

UR

CE

ST

AT

IC

CA

B A

LTLI

MIT

ER

11,5

00 F

T_

1,50

0 F

T+

FIL

TE

R

VA

C

RE

G

CA

BIN

PR

ES

S

FIL

TE

R

SA

FE

TY

VA

LVE

OR

IFIC

E

ST

AT

ICP

OR

T

TA

ILC

ON

EC

AB

IN

FIL

TE

R

ST

AT

ICP

RE

SS

CA

BIN

NO

SE

ALT

ER

NA

TE

ST

AT

ICP

OR

T

LE

GE

ND

RE

GU

LAT

ED

BLE

ED

AIR

VA

CU

UM

CO

NT

RO

L P

RE

SS

UR

E

ST

AT

IC P

RE

SS

UR

E

CA

BIN

PR

ES

SU

RE

MO

DIF

IED

CO

NT

RO

L P

RE

SS

UR

E

SO

L V

ALV

E (

NO

)E

NE

RG

IZE

D C

LOS

ED

ON

GN

D

0

A I R

C R A F T A L T

X

1 0

0 0

F T

C A B I

N A

L T

X 1

0 0

0

F TS

L

4 5

10

56

47

38

2

91

RAT

E

INC

RD

EC

R

1 3

5-09

9 th

ru 3

5-10

6, 3

5-10

8 th

ru 3

5-11

2;an

d 36

-029

thru

36-

031

PR

ES

S D

IFF

RE

LIE

F9.

2 P

SID


EFFECTIVITY


EFFECTIVITY

b

PRESSURIZATION CONTROL SYSTEM

INC

R

RA

TE

DN

UP

ST

AT

IC P

OR

T(E

XT

ER

NA

L A

IRC

RA

FT

)C

AB

ALT

LIM

11,5

00 F

T _

1,5

00 F

T+

CA

BIN

PR

ES

S

OU

TF

LOW

VA

LVE

9.2

PS

ID

SO

L V

ALV

E (

N.O

.)E

NE

RG

IZE

D C

LOS

ED

IN M

AN

UA

LA

BO

VE

8,7

50 _

250

FT

OR

ON

GN

DC

AB

IN A

LT L

IGH

T

+

SO

L V

ALV

E (

NC

)E

NE

RG

IZE

D O

PE

NO

N G

ND

WIT

HC

AB

AIR

OF

F

SO

L V

ALV

E (

NC

)E

NE

RG

IZE

D O

PE

NO

N G

ND

CO

NT

RO

L P

RE

SS

UR

E(V

AC

UU

M)

SO

UR

CE

ST

AT

IC

CA

B A

LTLI

MIT

ER

11,5

00 F

T_

1,50

0 F

T+

FIL

TE

R

VA

C

RE

G

CA

BIN

PR

ES

S

FIL

TE

R

SA

FE

TY

VA

LVE

OR

IFIC

E

ST

AT

ICP

OR

T

TA

ILC

ON

EC

AB

IN

FIL

TE

R

ST

AT

ICP

RE

SS

CA

BIN

NO

SE

ALT

ER

NA

TE

ST

AT

ICP

OR

T

LE

GE

ND

RE

GU

LAT

ED

SE

RV

O A

IR

VA

CU

UM

CO

NT

RO

L P

RE

SS

UR

E

ST

AT

IC P

RE

SS

UR

E

CA

BIN

PR

ES

SU

RE

MO

DIF

IED

CO

NT

RO

L P

RE

SS

UR

E

SO

L V

ALV

E (

NO

)E

NE

RG

IZE

D C

LOS

ED

ON

GN

D

CO

NT

RO

LLE

R

CABIN

ALT-FT

ACFTx 1000

12 30

25

03

CA

BIN

PR

ES

S D

IFF

RE

LIE

F 9

.4 P

SID

PR

ES

S D

IFF

RE

LIE

F9.

2 P

SID



EFFECTIVITY

ADVISORY ANNUNCIATIONSENG SYNC

The amber ENG SYNC light will illuminate when the nose gear is extendedand the SYNC-OFF switch is in the SYNC position.Turn ENG SYNC off for takeoff, landing and during single engine opera-tion.

NAC HT ON

The green NAC HT ON light will illuminate when either nacelle heat switchis on.

SPOILER

The SPOILER light will illuminate steadily when spoilers are extended. Thelight will flash if the spoilers are extended with 13° or more of flapextension.

STEER ON

The green STEER ON light will illuminate when the nose wheel steeringsystem is engaged and responsive to rudder pedal inputs.If the steering system was engaged by the wheel master button, releasethe button when nose wheel steering is no longer needed. If engaged withthe STEER LOCK switch, no action is required.

ENGSYNC

NAC HTON

SPOILER AUTOPILOTFC-530

SPOILERFC-200

AUTOPILOT

STEERON


EFFECTIVITY

b

T.O. TRIM

The amber T. O. TRIM light will illuminate when the pitch trim indicatorpointer is outside the T. O. (Take Off) segment when the aircraft is on theground.If T. O. TRIM is illuminated, set the pitch trim within the T. O. segment.

OR

The green WSHLD HT (HEAT) light will illuminate when the windshieldanti-ice system is selected on by the pilot. It will remain illuminated until thepilot selects the system off. On aircraft incorporating AMK 91-2, when theair temperature reaches it’s maximum operating scale, airflow will shut offand the light will extinguish.

T.O.TRIM

WSHLDHEAT

WSHLDHT

CL-102B

S-24

April 2001C

hange 1A

LLEFFEC

TIVITY

RED

TRIA

NG

LES DEN

OTE EM

ERG

ENC

Y PRO

CED

UR

ES.A

MB

ER TR

IAN

GLES D

ENO

TE AB

NO

RM

AL PR

OC

EDU

RES

CURLIM

LOWFUEL

L FUELPRESS

R FUELPRESS SPOILER DOOR AUG

AILPITOT

HTFUEL

FILTER

PRIINV

SECINV

AUXINV SPARE STAB

OV HTWSHLDOV HT

STEERON

BLEEDAIR L

BLEEDAIR R

ENG FIREPULL

L ENGICE

R ENGICE

L FUELCMPTR

R FUELCMPTR

LSTALL

RSTALL

L VGMON

R VGMON

MACHTRIM

NAC HTON

LGEN

RGEN

CABALT

WINGOV HT

WSHLDHT

ALCAI

BAT140

BAT160

T.O.TRIM

ENG FIREPULL

DEPLOY ARM

16 16


ENGSYNC


16 16


LEFT SIDE

RIGHT SIDE

LH ENGCHIP

RH ENGCHIP

917113139

994 2 344

411 4 12 12 7

3 3

5

5

2

1 1

3 3

16

16 16

222 1

5

5

6

1616

PITCHTRIM

3

8

WSHLDDEFOG

L R

LOHYD

FUELXFLO

L LOOIL

R LOOIL

10

8 8

815 815

88

OIL PRESS

LO OIL PRESS

Change 1

Documents

2008 - Checklist - Learjet 35A - Ch 2