MINIMUM EQUIPMENT LIST CANADAIR CHALLENGER CL 601 T7- …

MINIMUM EQUIPMENT LIST

CANADAIR CHALLENGER CL 601

T7- GFA

CONTENTS

REVISION NO: 02 DATED 12 OCT 2016

The Golden Falcon Aviation S.r.l Minimum Equipment List (MEL) is based on;

a) the Federal Aviation Administration (FAA) Master Minimum Equipment List (MMEL) Revision 10 dated 24 February, 2016; and

b) Operational (O) and Maintenance (M) procedures are based on the Bombardier

Challenger Dispatch Deviation Guide (TC), Revision 8, dated 18 March 2015. c) This MEL is applicable to commercial air transport operations under CAR OPS 1

CAA Approval_____________________________ Republic of San Marino Golden Falcon Aviation S.r.l Via 28 Luglio 212, 47891 Republic of San Marino Tel: +965 246 101 96 Email: [email protected]

mailto:[email protected]

This Page Intentionally Left Blank

GOLDEN FALCON AVIATION T7-GFA


Airplane: CL 601

Revision No: 02 Page No: I Date: 12 Oct 16

TABLE OF CONTENTS

GENERAL

ATA NO. SYSTEM PAGE NO.

--

Cover

-

-- Table of Contents - General I -- Table of Contents II - XIV -- Log of Revisions XV -- Highlights of Change XVI List of Effective Pages XVII - XXII

-- Definitions XXIII - XXVI Abbreviations and Acronyms XXVII - XXXVI

-- Preamble XXXVII - XXXXII

21 Air Conditioning 21-1 THRU 26 22 Auto Flight 22-1 THRU 14 23 Communications 23-1 THRU 24 24 Electrical Power 24-1 THRU 10 25 Equipment / Furnishings 25-1 THRU 28 26 Fire Protection 26-1 THRU 12 27 Flight Controls 27-1 THRU 16 28 Fuel 28-1 THRU 24 29 Hydraulic Power 29-1 THRU 10 30 Ice & Rain Protection 30-1 THRU 14 31 Indicating / Recording Systems 31-1 THRU 4 32 Landing Gear 32-1 THRU 6 33 Lights 33-1 THRU 24 34 Navigation 34-1 THRU 54 35 Oxygen 35-1 THRU 6 36 Pneumatics 36-1 THRU 4 38 Water / Waste 38-1 THRU 4 49 Auxiliary Power Unit 49-1 THRU 4 52 Doors 52-1 THRU 10 71 Power Plant 71-1 THRU 2 73 Engine Fuel and Control 73-1 THRU 6 74 Ignition 74-1 THRU 4 76 Engine Controls 76-1 THRU 2 77 Engine Indicating 77-1 THRU 10 78 Exhaust 78-1 THRU 2

79 Oil 79-1 THRU 2



Airplane: CL 601

Revision No: 02 Page No: II Date: 12 Oct 16

TABLE OF CONTENTS

21 AIR CONDITIONING

20−1 Heat Exchanger Fan (Foot warmer-Demist) 21−1

30−1 Emergency Pressurization System 21−2

30−2 Cabin Altitude Warning System 1. Visual (CABIN PRESS LOW light)

21−3

30−2 Cabin Altitude Warning System 2. Aural (Horn)

21−4

30−3 Cabin Altitude Indicator 21−6

30−4 Cabin Differential Pressure Indicator 21−8

30−5 Cabin Rate of Climb Indicator 21−10

31−1 Cabin Pressurization Control System 1. Automatic and Manual Modes

21−11

31−1 Cabin Pressurization Control System 2. Automatic Mode

21−13

31−1 Cabin Pressurization Control System 4. Manual Mode

21−15

32−1 Outflow / Safety Valves 21−16

51−1 Air Conditioning Units (ACUs) 21−19

52-1 Ram Air Vent Valve 21−21

53-1 Right Foot warmer De-Mist Pressure Regulating and Shut-OFF Valve 21−23

61−1 Temperature Control System

1. Cockpit Modes (NORMAL, STANDBY, MANUAL)

21−24

61−1 Temperature Control System 2. Cabin Modes (NORMAL, STANDBY, MANUAL)

21−25

61−2 Cabin Temperature Indicating System 21−26

22. AUTO FLIGHT

10−1 Autopilot System 22−1

10−1 Autopilot Systems

1a. Roll Axis Channel

22−2

10−1 Autopilot Systems

1b. Pitch Axis Channel

22−3

10−2 Flight Directors 22−4

11−1 Autopilot Disconnect Switches (Control Wheel Buttons) 22−6

11−2 Touch Control Steering (TCS) Switches 22−9

11−4 Take−Off/Go−Around (TOGA) Switches 22−10



Airplane: CL 601

Revision No: 02 Page No: III Date: 12 Oct 16

TABLE OF CONTENTS

20−1 Mach Trim System 22−11

20−2 Yaw Damper Channels 22−12

20−3 Yaw Rate Gyros 22−13

23. COMMUNICATIONS

11−1 Communication Systems VHF 23−1

11−1 Communication Systems VHF

3. Frequency Selector Button/Knob

23−2


4. Frequency Indication

23−3


4c. Control Unit Frequency Indication

23−4

11−3 Inflight Telephone System 23−5

12−1 High Frequency (HF) Communication Systems 23−6

21−1 Selective Call (SELCAL) System 23−8

21−1 Selective Call (SELCAL) System

1. Channels

23−9

21−2 Satellite Communications (SATCOM) Systems 23−10

31−1 Passenger Address (PA) System 1. Passenger Configuration

23−11

41−1 Crewmember Interphone System 1. Flight Deck to Cabin, Cabin to Flight Deck Functions

23−12

41−1 Crewmember Interphone System 2. Flight Deck to Ground

23−13

50−1 Cockpit Speakers 23−14

50−2 Cabin Alerting System (Chime/Light) 1. Flight Deck Call Light

23−15

50−2 Cabin Alerting System (Chime/Light) 2. Flight Attendant / Cabin Call Lights

23−16

50−2 Cabin Alerting System (Chime/Light) 3. Flight Attendant Cabin Chimes

23−17

50−4 Lavatory Speakers 23−18

51−1 Headset Boom Microphones 23−19

51−2 Flight Deck Hand Held Microphones 23−20

51−4 Press−To−Talk (PTT) Switches (Control Wheel) 23−21

51−5 Headsets Earphones/Headphones

a) Active Noise Cancelling/Reduction Function

23−22

71−1 Cockpit Voice Recorder (CVR) System

1. Flight Data Recorder (FDR) Installed

23−23



Airplane: CL 601

Revision No: 02 Page No: IV Date: 12 Oct 16

TABLE OF CONTENTS

24. ELECTRICAL POWER

22−1 Auxiliary Power Unit (APU) AC Loadmeter 2. Airplane with IDG P/Ns 720845

24−1

22−2 Auxiliary Power Unit (APU) Generator System 1. Airplane with IDG P/Ns 720845

24−2

23−1 Air Driven Generator (ADG) Auto−Deployment System 24−3

30−3 APU Start Battery 24−4

30−5 Battery Ammeter 24−5

31−1 TRU Cooling Fan 24−6

32−5 Battery Temperature Monitors 24−7

41−1 AC External Power System 24−8

42−1 DC External Power System 24−9

25. FURNISHINGS/EQUIPMENT

11−1 Pilot Seats 1. Lumbar Support

25−1

11−1 Pilot Seats 2. Arm Rests

25−2

11−1 Pilot Seats 3. Height Adjustments

25−3

11−1 Pilot Seats 4. Fore/Aft Adjustments

25−4

11−1 Pilot Seats 5. Recline Adjustments

25−5

11−1 Pilot Seats 6. Thigh Supports

25−6

11−1 Pilot Seats 7. Seat Belt Inertia Reel

25−7

11−2 Cockpit Sun visors 25−8

12−1 Primary Observer Seat (including associated equipment) 25−9

20−1 Passenger Seats 25−10

20−1 Passenger Seats 1. Recline Mechanism

25−11

20−1 Passenger Seats 3. Track/Swivel Mechanism

25−12

20−4 Divan Seat Berthing Belt 25−13

20−5 Cabin Gasper Vents 25−14

29−1 Cabin Power Outlet 25−15



Airplane: CL 601

Revision No: 02 Page No: V Date: 12 Oct 16

TABLE OF CONTENTS

30−1 Overhead Storage Bin(s)/Cabin and Galley Storage Compartments/Closets

25−16

50−1 Cargo Restraint Systems 25−18

60−1 Flotation Equipment (Crew and Passenger)

1 Life Vests

2 Life Rafts

25−19

60−2 Emergency Locator Transmitter (ELT)

1. Fixed ELT

25−20

60−3 Passenger Convenience Items 25−21

60−4 Airshow Cockpit Monitor System 25−22

60−6 Flashlights / Flashlight Holders 1. Flashlights

25−23

60−6 Flashlights / Flashlight Holders 2. Holders

25−24

60−8 “FASTEN SEAT BELT WHILE SEATED” sign on placard 25−25

60−9 First Aid Kit 3. First Aid Kit Seal

25−26

70−1 Galley Waste Receptacles Access Doors/Covers 25−27

70−2 Exterior Lavatory Door Ashtray 25−28

26. FIRE PROTECTION

10−1 APU Fire Detection System . 26−1

10−2 Lavatory Smoke Detection Systems 26−3

10−3 Baggage Compartment Fire Detection / Suppression System 26−4

14−1 Main Landing Gear Bay Overheat Detection System 26−5

20−1 Lavatory Fire Extinguisher System 26−7

20−3 Baggage Compartment Smoke Detection System 26−8

20−6 APU FIREX Bottle Low Pressure Switch 26−9

25−1 Portable Fire Extinguishers 26−11

27. FLIGHT CONTROLS

05−1 Control Surface Position Indicators 2. FLT SPLR L/R, AIL L/R, ELEVATOR L/R RUDDER)

27−1

05−3 Servo Monitor System 27−4

05−4 LH/RH Flight Spoiler Indication (Glareshield) 27−8

12−1 Aileron Trim System 27−9



Airplane: CL 601

Revision No: 02 Page No: VI Date: 12 Oct 16

TABLE OF CONTENTS

40−1 Trim Indicators (Ailerons, Rudder) 27−10

50−1 Flap Power Drive Unit (PDU) Motors 27−12

52−1 Rudder Pedal Adjustment Mechanism 27−13

60−2 Flight Spoiler Lights Flashing Feature 27−15

28. FUEL

11−1 Water Drain valves 28−1

13−1 Tail Cone Fuel Tank System 28−2

13−3 Turbulator Vanes (Fuel Jettison Mast, Tail Tank Fuel Systems) 28−3

15−1 Tank Ejectors (Aux Tank) 28−4

15−2 Crossfeed Shutoff Valves

1. Left to Right, Right to Left

28−5

23−1 Fuel (Boost) Pumps 28−6

25−1 APU Fuel Pump 28−9

25−2 APU Fuel Shutoff Valves 28−10

25−3 APU Negative G Feed Check Valve 28−11

27−1 Single Point Pressure Refueling System 28−12

27−1 Single Point Pressure Refueling System

1) External Refuel/Defuel Control Panel

28−13

27−1 Single Point Pressure Refueling System

2) Internal Refuel/Defuel Control Panel

a) Fuel Quantity Display

28−14

27−2 Refuel/Defuel Shut-Off Valves 1. Left, Right, Aux

28−15

27−2 Refuel/Defuel Shut−Off Valves 2. Tail

28−16

27−3 Refuel / Defuel Adapter Cap 28−17

41−1 Fuel Quantity Indicating Systems (Cockpit)

1. Main Fuel Tanks- Left and Right

28−18


3. Aux Fuel Tank (With Tail Tank Installed)

28−22


4. Fuel Totalizer

28−23



Airplane: CL 601

Revision No: 02 Page No: VII Date: 12 Oct 16

TABLE OF CONTENTS

29. HYDRAULIC POWER

11−2 Hydraulic Accumulator Pressure Gauges (Systems 1, 2 and 3) 29−1

11−3 Hydraulic Accumulators (Systems 1, 2 and 3) 29−2

11−4 Hydraulic Heat Exchanger Cooling Fan 29−3

11−7 Return Manifold Filter – Differential Pressure Indications 29−4

12−1 Electric Pump (System 3A) (ACMP) 29−5

31−1 Hydraulic Pressure Indicators (Cockpit) 29−6

31−2 Hydraulic Reservoir Quantity Indications (Systems 1, 2 and 3) 29−7

34−1 Hydraulic Pump Low Pressure Switches 29−8

35−1 Hydraulic HI TEMP Caution Lights (Systems 1, 2 and 3) 29−9

37−1 Hydraulic Pump Low Pressure Caution Lights (light function only) (ELEC PUMP,L ENG PUMP, R ENG PUMP)

29−10

30. ICE AND RAIN PROTECTION

12−1 Wing Anti−Ice System 3. Normal Control

30−1

12−1 Wing Anti−Ice System 4. Standby Control

30−2

12−2 Wing Anti−Ice System Modulating and Shut−off Valves 30−3

12−3 Wing Anti−Ice Isolation Valve 30−4

20−1 Engine Cowl Anti−Ice Pressure Regulating and Shutoff Valves 30−5

20−2 Engine Cowl Anti−Ice Pressure Relief Blow−Off Valves 30−6

31−1 Probe Heaters 1. Pitot Probes

30−7

31−1 Probe Heaters 2. Static Probes

30−8

31−1 Probe Heaters 3. Angle of Attack Vanes

30−9

31−1 Probe Heaters 4. TAT Probe

30−10

41−1 Left & Right Windshield and Side Window Heating Systems 30−11

71−1 Drain Mast Heater 30−12

80−1 Ice Detection Systems 30−13

31. INDICATING/RECORDING SYSTEMS

31−1 Flight Data Recorder (FDR) System 31−1



Airplane: CL 601

Revision No: 02 Page No: VIII Date: 12 Oct 16

TABLE OF CONTENTS

50−1 Auto CB Fail Light (10 Channel Annunciator) 31−3

60−1 Clocks 31−4

32. LANDING GEAR

30−1 Landing Gear Selector Handle Anti−Retraction Mechanism 32−1

43−1 Brake Accumulator Pressure Gauges 32−2

43−2 Brake Pressure Indications 32−3

45−1 Parking Brake Light 32−4

50−2 Remote Nose Gear Door Release Mechanism 32−5

33. LIGHTS

12−1 Lighting Control Panels (Center Pedestal & L/R Facia Panels) 1. Floodlight Systems a. BRT/DIM Systems

33−1

12−1 Lighting Control Panels (Center Pedestal & L/R Facia Panels) 1. Floodlight Systems b. Brightening Systems

33−2

12−1 Lighting Control Panels (Center Pedestal & L/R Facia Panels) 2. Instrument Brightening Systems

33−3

12−1 Lighting Control Panels (Center Pedestal & L/R Facia Panels) 3. Floor Light Systems

33−4

12−3 PBA BRT/DIM System (10 Channel Annunciator Panel) 33−5

12−4 Overhead Instrument Panel Brightening System 33−6

13−1 Cockpit/Flight Deck/Flight Compartment and Instrument Panel Lighting Systems (Excluding EFIS)

33−7

14−1 Map Reading Lights 33−8

20−1 Cabin Interior Lights 33−9

20−2 Miscellaneous Lights

1. Boarding and Dome Lights

33−10

20−3 Lavatory Vanity / Reading Lights 33−11

23−1 Fasten Seat Belt and No Smoking Warning Signs 1. Passenger Configuration

33−12

31−1 Service Lights 33−13

40−1 Position Lights (Navigation) 1. Wing Tip Position Light Bulbs

33−14

40−1 Position Lights (Navigation) 2. Upper Aft Position Light Bulb

33−15

40−1 Position Lights (Navigation)

4. Lower Aft Position Light Bulbs

33−16

40−2 High Intensity or Strobe Light System 33−17



Airplane: CL 601

Revision No: 02 Page No: IX Date: 12 Oct 16

TABLE OF CONTENTS

40−3 Anti−Collision Beacon Light System 33−18

40−4 Landing Lights (Wing Leading Edge and Nose) 33−19

40−4 Landing Lights 3. Pulse Light Function

33−20

40−6 Logo Light System 33−21

40−7 Taxi / Recognition Lights (in leading edge) 33−22

43−1 Wing Inspection Lights 33−23

50−1 Exterior Emergency Lights 33−24

34. NAVIGATION

12−1 Standby Altimeter 34−1

13−1 True Airspeed (TAS), Static Air Temperature (SAT) Total Air Temperature (TAT) Indicating Systems

1. TAS Indication

34−2


2. SAT Indication

34−3


3. TAT Indication

34−5

13−2 Vertical Speed Indicators (VSIs) 34−6

17−1 Altitude Alerting System 34−7

17−1 Altitude Alerting System

3. Aural Alert

34−8

17−1 Altitude Alerting System

4. Visual Alert

34−9

21-1 Instrument Comparator Monitor 34−10

21−2 Non-EFIS ADI Annunciators/Displays

1. ADI - Glideslope pointers

34−11


2. ADI - Localizer pointers

34−12


3. Pitch and Roll Command Bars

34−13


4. ADI-Radio Altimeter Display

34−14


5. ADI-Rate of Turn Indicators

34−15


1. HSI Bearing pointers

34−16



Airplane: CL 601

Revision No: 02 Page No: X Date: 12 Oct 16

TABLE OF CONTENTS


2. HSI Distance Measuring Equipment (DME) Displays

34−17


3. HSI Glideslope pointers

34−18


4. Heading Displays

34−19


5. Localizer pointers

34−20

22−2 Turn and Slip Indicators 34−21

23−1 Vertical Navigation System (VNAV) 34−22

23−2 Inertial Reference Systems (IRSs) 34−23

23−4 Emergency Battery Packs for Backup COMM/NAV 34−24

23−5 IRS Backup Battery 34−25

27−1 Magnetic Compass (Standby) 34−26

28−1 Standby Attitude Indicator 34−27

40−1 Windshear Alert System 34−28

41−1 Weather Radar System 34−29

42−1 Radio Altimeter Systems 34−30

42−2 Terrain Awareness and Warning System (TAWS) / Ground Proximity Warning System (GPWS)

1. GPWS/TAWS

34−31


1. GPWS/TAWS

a. Modes 1−4

34−32


1. GPWS/TAWS

b. Test Mode

34−33


1. GPWS/TAWS

d. Advisory Callouts (Mode 6)

34−34

42−2 Terrain Awareness and Warning System (TAWS) / Ground Proximity Warning System (GPWS) Class A TAWS Equipment Required

1. GPWS/TAWS

e. Windshear Mode (Reactive)

34−35


2. Terrain System − Forward Looking Terrain Avoidance (FLTA) and Premature Descent Alert (PDA) Functions

34−36



Airplane: CL 601

Revision No: 02 Page No: XI Date: 12 Oct 16

TABLE OF CONTENTS


3. Terrain Displays

34−37

43−1 Traffic Collision Avoidance System (TCAS)

2) TCAS II

34−38


2)a) Combined Traffic Alert (TA) and Resolution Advisory (RA) Dual Displays

34−39


2)b) . RA Display System(s)

34−40


2)c). TA Display System(s)

34−41

50−1 Long Range Navigation Systems (GPS) 34−42

51−1 VHF Navigation Systems (VOR / ILS) 34−43

51−2 Marker Beacon Systems 34−44

51−3 NAV/COM System

1. Preselect Tuning

34−45

51−3 NAV/COM System

2. Memory Channels

34−46

51−4 Radio Magnetic Indicators (RMIs) 34−47

52−1 Automatic Direction Finding (ADF) Systems 34−48

53−1 Distance Measuring Equipment (DME) Systems 34−49

54−1 Air Traffic Control (ATC) Transponders and Automatic Altitude Reporting Systems

34−50

54−2 Remote Transponder Ident Buttons 34−51

60−1 Datanav System 34−52

61−1 Flight Management Systems (FMS) 34−53

61−1 Flight Management Systems (FMS)

7. Navigation Databases

34−54

35. OXYGEN

10−1 Crew Oxygen Pressure Gauge 35−1

20−1 Passenger Oxygen System 35−2

20−1 Passenger Oxygen System

1) Cabin Passenger Oxygen Drop Out panels

35−3


2) Lavatory Oxygen Drop Out System

35−4


3) Pressure Gauge

35−5



Airplane: CL 601

Revision No: 02 Page No: XII Date: 12 Oct 16

TABLE OF CONTENTS

36. PNEUMATIC

10−1 Engine Bleed Air SOVs (14th Stage) 36−1

20−1 Bleed Air Pressure Indicators (LH &RH)

2. 10th Stage

36−2

23−1 Bleed Air Overheat Sensing Loops A and B 36−4

38. WATER/WASTE

10−1 Potable Water System 38−1

10−2 Lavatory Waste Systems 38−2

10−3 Lavatory External Service Cap 38−3

49. AIRBORNE AUXILIARY POWER

02−1 APU Bleed Air SOV (Load Control Valve) 49−1

02−2 Auxiliary Power Unit (APU) 49−2

61−1 Electronic Control Unit (ECU) 49−3

70−1 APU Hour Meter 49−4

52 DOORS

02−1 Exterior Door Key Locks

1. Passenger Door Key Lock

52−1


2. Cargo/Baggage Door Key Lock

52−2


3. Aft−Equipment Compartment Door Key Lock

52−3


4. External Service Doors Key Locks

52−4

11−1 Passenger Door Manual Retract Handle 52−5

11−2 Storage Compartment Door (Main Entry Door) 52−6

12−1 Main Cabin Door Power Assist System 52−7

30−1 Baggage Door Counterbalance Systems (balance springs) 52−8

70−1 Main Cabin Door Indication System 52−9

70−4 BAG DR UNSAFE Caution Light 52−10



Airplane: CL 601

Revision No: 02 Page No: XIII Date: 12 Oct 16

TABLE OF CONTENTS

71. POWER PLANT

70−1 Ecology Tank Ejector Pumps 71−1

73. ENGINE FUEL & CONTROL

30−1 Fuel Temperature Indicating Systems 73−1

31−1 Fuel Flow Indicating Systems 73−2

31−1 Fuel Flow Indicating Systems

1. Left Vertical Scale Lamps

73−3

31−1 Fuel Flow Indicating Systems

2. Right Vertical Scale Lamps

73−4

31−4 Fuel Low Pressure Indication 73−5

74. IGNITION

11−1 Ignition Systems 1. A Systems

74−1

11−1 Ignition Systems 2. B Systems

74−2

30−1 Relight Ignition System Switch 74−3

76. ENGINE CONTROLS

02−1 Engine Speed Control Systems 76−1

10−1 Automatic Power Reserve (APR) System 76−2

77. ENGINE INDICATING

10−1 N1 Vertical Scale Indicators

1) Left

77−1


2) Right

77−2


2)a) Left

77−3


2)b) Right

77−4

20−1 ITT Indicators 77−5

20−1 ITT Indicators

1. Vertical Scale Lamps

a. Left

77−6



Airplane: CL 601

Revision No: 02 Page No: XIV Date: 12 Oct 16

TABLE OF CONTENTS

20−1 ITT Indicators


b. Right

77−7

20−2 2. DGT OFF Switch 77−8

30−1 Engine Vibration Monitor 77−9

78. EXHAUST

30−1 Thrust Reverser Systems 78−1

79. ENGINE OIL

12−1 Oil Replenishment System 79−1

30−1 Oil Low Pressure Indicator Lights 79−2



Airplane: CL 601

Revision No: 02 Page No: XV Date: 12 Oct 16

LOG OF REVISIONS

Rev No. Date Page Numbers Initials

0 17 Jan 16 Initial Issue (all pages)



Airplane: CL 601

Revision No: 02 Page No: XVI Date: 12 Oct 16

HIGHLIGHTS OF CHANGE

(Reserved)



Airplane: CL 601

Revision No: 02 Page No: XVII Date: 12 Oct 16

LIST OF EFFECTIVE PAGES

CHAPTER PAGE DATE CHAPTER PAGE DATE

Table of Contents I 12 Oct 16 21 21−1 12 Oct 16

II 12 Oct 16 21−2 12 Oct 16

III 12 Oct 16 21−3 12 Oct 16

IV 12 Oct 16 21−4 12 Oct 16

V 12 Oct 16 21−5 12 Oct 16

VI 12 Oct 16 21−6 12 Oct 16

VII 12 Oct 16 21−7 12 Oct 16

VIII 12 Oct 16 21−8 12 Oct 16

IX 12 Oct 16 21−9 12 Oct 16

X 12 Oct 16 21−10 12 Oct 16

XI 12 Oct 16 21−11 12 Oct 16

XII 12 Oct 16 21−12 12 Oct 16

XIII 12 Oct 16 21−13 12 Oct 16

XIV 12 Oct 16 21−14 12 Oct 16

Log of Revisions XV 12 Oct 16 21−15 12 Oct 16

Highlights XVI 12 Oct 16 21−16 12 Oct 16

LEP XVII 12 Oct 16 21−17 12 Oct 16

XVIII 12 Oct 16 21−18 12 Oct 16

XIX 12 Oct 16 21−19 12 Oct 16

XX 12 Oct 16 21−20 12 Oct 16

XXI 12 Oct 16 21−21 12 Oct 16

XXII 12 Oct 16 21−22 12 Oct 16

XXIII 12 Oct 16 21−23 12 Oct 16

XXIV 12 Oct 16 21−24 12 Oct 16

XXV 12 Oct 16 21−25 12 Oct 16

XXVI 12 Oct 16 21−26 12 Oct 16

XXVII 12 Oct 16

XXVIII 12 Oct 16 22 22−1 12 Oct 16

XXIX 12 Oct 16 22−2 12 Oct 16

XXX 12 Oct 16 22−3 12 Oct 16

XXXI 12 Oct 16 22−4 12 Oct 16

XXXII 12 Oct 16 22−5 12 Oct 16

XXXIII 12 Oct 16 22−6 12 Oct 16

XXXIV 12 Oct 16 22−7 12 Oct 16

XXXV 12 Oct 16 22−8 12 Oct 16

XXXVI 12 Oct 16 22−9 12 Oct 16

XXXVII 12 Oct 16 22−10 12 Oct 16

XXXVIII 12 Oct 16 22−11 12 Oct 16

XXXIX 12 Oct 16 22−12 12 Oct 16

XXXX 12 Oct 16 22−13 12 Oct 16

XXXXI 12 Oct 16 22−14 12 Oct 16

XXXXII 12 Oct 16



Airplane: CL 601

Revision No: 02 Page No: XVIII Date: 12 Oct 16


23 23−1 12 Oct 16 25−12 12 Oct 16

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23−21 12 Oct 16 26−4 12 Oct 16

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Airplane: CL 601

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28

30−8 12 Oct 16

28−1 12 Oct 16 30−9 12 Oct 16

28−2 12 Oct 16 30−10 12 Oct 16

28−3 12 Oct 16 30−11 12 Oct 16

28−4 12 Oct 16 30−12 12 Oct 16

28−5 12 Oct 16 30−13 12 Oct 16

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28−8 12 Oct 16 31 31−1 12 Oct 16

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28−13 12 Oct 16 32 32−1 12 Oct 16

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28−15 12 Oct 16 32−3 12 Oct 16

28−16 12 Oct 16 32−4 12 Oct 16

28−17 12 Oct 16 32−5 12 Oct 16

28−18 12 Oct 16 32−6 12 Oct 16

28−19 12 Oct 16

28−20 12 Oct 16 33 33−1 12 Oct 16

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28−22 12 Oct 16 33−3 12 Oct 16

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28−24 12 Oct 16 33−5 12 Oct 16

33−6 12 Oct 16

29 29−1 12 Oct 16 33−7 12 Oct 16

29−2 12 Oct 16 33−8 12 Oct 16

29−3 12 Oct 16 33−9 12 Oct 16

29−4 12 Oct 16 33−10 12 Oct 16

29−5 12 Oct 16 33−11 12 Oct 16

29−6 12 Oct 16 33−12 12 Oct 16

29−7 12 Oct 16 33−13 12 Oct 16

29−8 12 Oct 16 33−14 12 Oct 16

29−9 12 Oct 16 33−15 12 Oct 16

29−10 12 Oct 16 33−16 12 Oct 16

33−17 12 Oct 16

30 30−1 12 Oct 16 33−18 12 Oct 16

30−2 12 Oct 16 33−19 12 Oct 16

30−3 12 Oct 16 33−20 12 Oct 16

30−4 12 Oct 16 33−21 12 Oct 16

30−5 12 Oct 16 33−22 12 Oct 16

30−6 12 Oct 16 33−23 12 Oct 16

30−7 12 Oct 16 33−24 12 Oct 16



Airplane: CL 601

Revision No: 02 Page No: XX Date: 12 Oct 16


CHAPTER PAGE DATE CHAPTER PAGE DATE 34 34−1 12 Oct 16 34−44 12 Oct 16

34−2 12 Oct 16 34−45 12 Oct 16

34−3 12 Oct 16 34−46 12 Oct 16

34−4 12 Oct 16 34−47 12 Oct 16

34−5 12 Oct 16 34−48 12 Oct 16

34−6 12 Oct 16 34−49 12 Oct 16

34−7 12 Oct 16 34−50 12 Oct 16

34−8 12 Oct 16 34−51 12 Oct 16

34−9 12 Oct 16 34−52 12 Oct 16

34−10 12 Oct 16 34−53 12 Oct 16

34−11 12 Oct 16 34−54 12 Oct 16

34−12 12 Oct 16

34−13 12 Oct 16 35 35−1 12 Oct 16

34−14 12 Oct 16 35−2 12 Oct 16

34−15 12 Oct 16 35−3 12 Oct 16

34−16 12 Oct 16 35−4 12 Oct 16

34−17 12 Oct 16 35−5 12 Oct 16

34−18 12 Oct 16 35−6 12 Oct 16

34−19 12 Oct 16

34−20 12 Oct 16 36 36−1 12 Oct 16

34−21 12 Oct 16 36−2 12 Oct 16

34−22 12 Oct 16 36−3 12 Oct 16

34−23 12 Oct 16 36−4 12 Oct 16

34−24 12 Oct 16

34−25 12 Oct 16 38 38−1 12 Oct 16

34−26 12 Oct 16 38−2 12 Oct 16

34−27 12 Oct 16 38−3 12 Oct 16

34−28 12 Oct 16 38−4 12 Oct 16

34−29 12 Oct 16

34−30 12 Oct 16 46 46−1 12 Oct 16

34−31 12 Oct 16 46−2 12 Oct 16

34−32 12 Oct 16

34−33 12 Oct 16 49 49−1 12 Oct 16

34−34 12 Oct 16 49−2 12 Oct 16

34−35 12 Oct 16 49−3 12 Oct 16

34−36 12 Oct 16 49−4 12 Oct 16

34−37 12 Oct 16

34−38 12 Oct 16 52 52−1 12 Oct 16

34−39 12 Oct 16 52−2 12 Oct 16

34−40 12 Oct 16 52−3 12 Oct 16

34−41 12 Oct 16 52−4 12 Oct 16

34−42 12 Oct 16 52−5 12 Oct 16

34−43 12 Oct 16 52−6 12 Oct 16

52−7 12 Oct 16

52−8 12 Oct 16



Airplane: CL 601

Revision No: 02 Page No: XXI Date: 12 Oct 16



52−9 12 Oct 16

52−10 12 Oct 16

71 71−1 12 Oct 16

71−2 12 Oct 16

73 73−1 12 Oct 16

73−2 12 Oct 16

73−3 12 Oct 16

73−4 12 Oct 16

73−5 12 Oct 16

73−6 12 Oct 16

74 74−1 12 Oct 16

74−2 12 Oct 16

74−3 12 Oct 16

74−4 12 Oct 16

76 76−1 12 Oct 16

76−2 12 Oct 16

77 77−1 12 Oct 16

77−2 12 Oct 16

77−3 12 Oct 16

77−4 12 Oct 16

77−5 12 Oct 16

77−6 12 Oct 16

77−7 12 Oct 16

77−8 12 Oct 16

77−9 12 Oct 16

77−10 12 Oct 16

78 78−1 12 Oct 16

78−2 12 Oct 16

79 79−1 12 Oct 16

79−2 12 Oct 16



Airplane: CL 601

Revision No: 02 Page No: XXII Date: 12 Oct 16





Airplane: CL 601

Revision No: 02 Page No: XXIII Date: 12 Oct 16

DEFINITIONS

1. System Definitions. System numbers are based on the Air Transport Association (ATA) Specification Number 102 and items are numbered sequentially. a. "Item" (Column 1) means the equipment, system, component, or function listed in the

"Item" column.

NOTE: The item number in column 1 follows the MMEL. Those items, which are not applicable to this airplane, do not appear so the numbering is not in sequence.

b. "Number Installed" (Column 2) is the number (quantity) of items normally installed in the

airplane. This number represents the airplane configuration considered in developing this MEL. Should the number be a variable (e.g., passenger cabin items) a number is not required.

c. "Number Required for Dispatch" (Column 3) is the minimum number (quantity) of items

required for operation provided the conditions specified in Column 4 are met. d. "Remarks or Exceptions" (Column 4) in this column includes a statement either

prohibiting or permitting operation with a specific number of items inoperative, provisos (conditions and limitations) for such operation, and appropriate notes. The Alphabetical symbol in Column 4 indicates a proviso (condition or limitation) that must be complied with for operation with the listed item inoperative.

e. A “vertical bar” (change bar) in the margin indicates a change, addition or deletion in the

adjacent text for the current revision of that page only. The change bar is dropped at the next revision of that page.

2. "Airplane Flight Manual" (AFM is the document required for type certification and approved by the SM CAA. The approved AFM for the specific airplane is listed on the applicable Type Certificate Data Sheet. 3. "-" symbol in Column 2 and/or Column 3 indicates a variable number (quantity) of the item installed. 4. “Commencement of flight” the point when an airplane begins to move under its own power for the purpose of preparing for take-off. 5. “Considered Inoperative”, as used in the provisos means that item must be treated for dispatch, taxi and flight purposes as though it were inoperative. The item shall not be used or operated until the original deferred item is repaired. Additional actions include: documenting the item on the dispatch release (if applicable), placarding, and complying with all remarks, exceptions, and related MEL provisions, including any (M) and (O) procedures and observing the repair category. 6. "Day of Discovery" is the calendar day an equipment/instrument malfunction was recorded in the airplane maintenance log and or record. This day is excluded from the calendar days or flight days specified in the MEL for the repair of an inoperative item of equipment. This provision is applicable to all MEL items, i.e., categories "A, B, C, and D."



Airplane: CL 601

Revision No: 02 Page No: XXIV Date: 12 Oct 16

DEFINITIONS

7. “Day operation” is any flight conducted from the point of take-off to landing between 30 minutes before sunrise and 30 minutes after sunset. 8. "Deactivated" and "Secured" means that the specified component must be put into an acceptable condition for safe flight. An acceptable method of securing or deactivating will be stated in the applicable (M) procedure. 9. "Excess Items" means those items that have been installed that are redundant to the requirements of the SM CAR OPS 2. 10. “Extended flight over water” means a flight operated over water at a distance of more than 93 km (50 NM), or 30 minutes at normal cruising speed, whichever is the lesser, away from land suitable for making an emergency landing.

11. "Flight Day" means a 24 hour period (from midnight to midnight) Universal Coordinated Time (UTC) during which at least one flight is initiated for the affected airplane. 12. "Icing Conditions" means an atmospheric environment that may cause ice to form on the airplane (structural) or in the engine(s) (induction). 13. ”Inoperative" means a system and/or component malfunction to the extent that it does not accomplish its intended purpose and/or is not consistently functioning normally within its approved operating limit(s) or tolerance(s). 14. “Inoperative components of an inoperative system”. Inoperative items which are components of a system which is inoperative are usually considered components directly associated with and having no other function than to support that system. (Warning/caution systems associated with the inoperative system must be operative unless relief is specifically authorized per the MEL). 15. “Is not used” in the provisos, remarks or exceptions for an MEL item may specify that another item relieved in the MEL “is not used.” In such cases, crewmembers should not activate, actuate, or otherwise utilize that component or system under normal operations. It is not necessary for the operators to accomplish the (M) procedures associated with the item. However, operational requirements must be complied with, and an additional placard must be affixed, to the extent practical, adjacent to the control or indicator for the item that is not used to inform crewmembers that a component or system is not to be used under normal operations. 16. "(M)" symbol indicates a requirement for a specific maintenance procedure which must be accomplished prior to operation with the listed item inoperative. All applicable (M) procedures requiring specialized knowledge or skill, or requiring the use of tools or test equipment should be accomplished by an authorized licensed maintenance engineer or a CAR 145 approved organization as well as a crew review of the airplane Check-List (Normal, Abnormal, Emergency). The satisfactory accomplishment of all maintenance procedures, regardless of who performs them, is the responsibility of the authorized licensed Maintenance engineer who signs off the Technical log for that item. 17. ”Notes" in Column 4 provides additional information for crewmember or maintenance consideration and do not relieve the flight crew and/or maintenance personnel of the responsibility for compliance with all applicable requirements. Notes are not part of the provisos.



Airplane: CL 601

Revision No: 02 Page No: XXV Date: 12 Oct 16

DEFINITIONS

18. "(O)" symbols indicate a requirement for a specific operations procedure which must be accomplished in planning for and/or operating with the listed item inoperative. Normally these procedures are accomplished by the flight crew; however, other personnel may be qualified and authorized to perform certain functions. The satisfactory accomplishment of all procedures, regardless of who performs them, is the responsibility of the Commander and all applicable (O) symbols require a review of the Airplane Flight Manual, Check-List (Normal, Abnormal, Emergency), Operations Manual and crew review. 19. "Passenger Convenience Items": means those items related to passenger convenience, comfort or entertainment such as, but not limited to, galley equipment, movie equipment, ash trays, stereo equipment, overhead reading lamps, etc. They are those items that if inoperative, damaged or missing have no effect on the airplane’s ability to be operated safely under all operational conditions. Passenger Convenience items, which have an applicable (O) and/or (M) procedure are identified in the MEL 25-60-3. 20. “Reduced Vertical Separation Minimum” (RVSM) airspace” means any airspace or route where airplane are separated by 1020 feet vertically between FL 290 and FL 410.

21. "Visual Flight Rules" (VFR) is as defined in CAR DEF. This precludes a pilot from filing an Instrument Flight Rules (IFR) flight plan. 22. "Visual Meteorological Conditions" (VMC) means the atmospheric environment is such that would allow a flight to proceed under the visual flight rules applicable to the flight. This does not preclude operating under Instrument Flight Rules. 23. "Visible Moisture" means an atmospheric environment containing water in any form that can be seen in natural or artificial light; for example, clouds, fog, rain, sleet, hail, or snow.



Airplane: CL 601

Revision No: 02 Page No: XXVI Date: 12 Oct 16

DEFINITIONS




Airplane: CL 601

Revision No: 02 Page No: XXVII Date: 12 Oct 16

ABBREVIATIONS and ACRONYMS

The following abbreviations and acronyms may be used on flight compartment displays, radio tuning units and the flight management system or may be found in this manual. Some abbreviations may appear in upper or lower case letters. Abbreviations which have limited usage are explained in the chapters where they are used.

A

A/C Air Conditioning

A/G Air/Ground

A/ICE Anti-ice

A/P Autopilot

A/S Airspeed

A/SKID Anti-skid

ABS Absolute

AC Alternating Current

ACARS ARINC Communications Addressing and reporting System

ACCEL Acceleration, accelerate(d), accelerometers

ACM Air Cycle Machine

ACMP Alternating Current Motor Pump/ Electric Hydraulic Pump

ACT Active

ACU Air Conditioning Unit

ADC Air Data Computer

ADDR Address

ADF Automatic Direction Finder

ADG Air Driven Generator

ADI Attitude Director Indicator

ADS Air Data System

AFCS Automatic Flight Control System

AFM Airplane Flight Manual

AFT Afterward

AGL Above Ground Level

AHC Attitude Heading Computer

AHRS Attitude Heading Reference System

AIL Aileron

ALIGN Aligning, alignment

ALPHA alpha

ALT Altitude, Altimeter

ALT Altitude Hold (PFD/FD)

ALT CAP Altitude Capture (PFD/FD)

ALT HOLD Altitude Hold

ALTN Alternate

ALTS Selected Altitude Arm/Abort (PFD/FD)

AM Amplitude Modulation

AMB Ambient

AMP Amperes

ANNUN Annunciator

ANT Antenna

AOA Angle of Attack

AP Autopilot

APC Auxiliary Power Control

APP Approach

APPROX Approximately

APR Automatic Performance Reserve

APU Auxiliary Power Unit

ARINC Aeronautical Radio Incorporated

ARP Air Data Reference Panel

ASYM Asymmetrical

ATA Air Transport Association

ATC Air Traffic Control

ATT Attitude

ATTD Attitude

ATTND Attendant

AUTO Automatic

AUTO BAL Automatic Balance

AUTO XFER Automatic Transfer

AUX Auxiliary

AV Avionics

AVAIL Available

AZ Azimuth



Airplane: CL 601

Revision No: 02 Page No: XXVIII Date: 12 Oct 16


B

B/AIR Bleed Air

B/C Back Course

B/CRS Back Course

B/LEAK Bleed Leak

BAG DR Baggage Door

BARO Barometric

BAT Battery

BATT Battery

BDI Bearing Distance Indicator

BFO Beat Frequency Oscillator

BITE Built-In-Test Equipment

BK Brake

BLD Bleed

BOOM Headset microphone

BRG Bearing

BRKR(s) Breaker(s)

BRT Bright

BTL Bottle

BTMS Brake Temperature Monitoring System

BTMU Brake Temperature Monitoring Unit

BYPS Bypass

C

C Center, Caution, Cabin

CAA Civil Aviation Authority (San Marino)

CAL Calibrate

CAP Capture

CAPT Captain

CAS Calibrated Air Speed

CAT Category

CAT II Category II

CB, C/B Circuit Breaker

CBP Circuit Breaker Panel

CCW Counter Clockwise

CDL Configuration Deviation List

CDP Compressor Discharge Pressure

CDU Control Display Unit

CFM Cubic Feet Per Minute

CG Center of Gravity

CH Chapter, Channel

CHAN Channel

CHGR Charger

CHR Chronograph

CHRT Chart

CK Check

CKPT Cockpit

CKT Circuit

CLB Climb

CLK Clock

cm Centimeters

CMD Command

CMPS Compass

CMPTR Computer

CO2 Carbon Dioxide

COM Communication

COMM Communication

COMP Compressor, Comparator

COMPT Compartment

COND Condition, Continued

CONFIG Configuration

CONN Connection

CONT Control, Continuous, Contactor, Controller

COOL Cooling

CORR Correction

CPAM Cabin Pressure Acquisition Module

CPLT Copilot

CRS Course

CRT Cathode Ray Tube

CRZ Cruise

CSD Constant Speed Drive

CTR Center

CVR Cockpit Voice Recorder

CW Clockwise

CYL Cylinder



Airplane: CL 601

Revision No: 02 Page No: XXIX Date: 12 Oct 16


D

DA Drift Angle

DBU Data Base Unit

DC Direct Current

DCP Display Control Panel

DCU Data Concentrator Unit

DECEL Decelerate(d)

DECR Decrease

DEFL Defuel

DEG Degree

DEPR Depressurize

DEPT Departure

DEST Destination

DET Detector

DEV Deviation

DFDAU Digital Flight Data Acquisition Unit

DFDR Digital Flight Data Recorder

DG Directional Gyro

DH Decision Height

DIFF Differential

DIM Dimming

DIR Direct

DIS Distance (to way point), Disconnect

DISC Disconnect

DISCH Discharge

DISP Dispatch, Display

DIST Distance

DME Distance Measuring Equipment

DN Down

DR Door

DUCT MON Duct Monitor

E

EADI Electronic Attitude Direction Indicator

EAS Equivalent Airspeed

ECAM Electronic Centralized Airplane Monitoring System

ECS Environmental Control System

ECU Electronic Control Unit

EDP Engine Driven Pump/Engine Primary Hydraulic Pump

EFIS Electronic Flight Instrument System

EGT Exhaust Gas Temperature

EHSI Electronic Horizontal Situation Indicator

EL Elevation

ELEC Electrical

ELEV Elevator, Elevation

ELT Emergency Locator Transmitter

EMER(G) Emergency

EMI Electro-Magnetic Interference

ENG Engine

EPC External Power Contactor

EQUIP Equipment

ERP Eye Reference Position Datum

ESS Essential

ET Elapsed Time

ETA Estimated Time of Arrival

ETE Estimated Time Enroute

EVAC Evacuation

EXH Exhaust

EXTIN Extinguish(ed)

F

F/CTL Flight Controls

FAIL Failure

FCC Flight Control Computer

FCU Fuel Control Unit

FD, F/D Flight Director

FDAU Flight Data Acquisition Unit

FDR Flight Data Recorder (Digital)

FECU Flaps Electronic Control Unit

FEED Feeder

FF, F/F Fuel Flow

FIRE BTL Fire Bottle

FIREX Fire Extinguisher



Airplane: CL 601

Revision No: 02 Page No: XXX Date: 12 Oct 16


FL CH Flight Level Change

FLD Field

FLT Flight

FLT DIR Flight Director

FLUOR Fluorescent

FM Fan Marker

FMS Flight Management System

FPM Feet Per Minute

FREQ Frequency

ft Feet, Foot

FW Fire Wall

FWD Forward

G

G (+/-) Receiver Gain

G/S Glide slope

GA Go-around

GAL Gallon

GALY Galley

GCS Ground Clutter Suppression

GCU Generator Control Unit

GE General Electric

GEN Generator

GLD Ground Lift Dumping

GMT Greenwich Mean Time

GND Ground

GPM Gallons Per Minute

GPWS Ground Proximity Warning System

GR Gear

GRAV Gravity

GS Ground Speed

GUIDE Guidance

GW Gross Weight

H

HDG Heading

HDG HOLD Heading Hold

HDG SEL Heading Select

HEAT Heater

HF High Frequency (3 - 30 mHz)

Hg Mercury

HGS Head-up Guidance System

HI High

HIRF High Intensity Radiated Fields

HLDR Holder

HOR, HORIZ Horizontal

HOT High Oil Temperature

HP High Pressure

HPA Hecto Pascals

HSI Horizontal Situation Indicator

HSTA Horizontal Stabilizer Trim

HSTCU Horizontal Stabilizer Trim Control Unit

HTR Heater

HUD Heads-up Display

HYD Hydraulic

Hz Hertz

I

IB,I/B,INBD Inboard

I/C Intercom, Inspection Check

IAPS Integrated Avionics Processor System

IAS Indicated Air Speed

ICAO International Civil Aviation Organization

ICS Idle Corrected Speed

ID Identification

IDENT Identification

IDG Integrated Drive Generator

IFR Instrument Flight Rules

IGN Ignition

ILS Instrument Landing System

IM ILS Inner Marker

IMC Instrument Meteorological Conditions

IMP. Imperial

in. Inch, Inches

in. Hg Inches of Mercury

INCR Increase

IND Indication, Indicator



Airplane: CL 601

Revision No: 02 Page No: XXXI Date: 12 Oct 16


INFLT In Flight

INHIB Inhibit

INOP Inoperative

INPH Interphone

INSP Inspection

INST(S) Instrument(s)

INST, INSTR Instrument

INT Internal, Integral, Intersection

INTEG Integral

IRS Inertial Reference System

IRU Inertial Reference Unit

ISA International Standard Atmosphere

ISDU Inertial System Display Unit

ISO International Standard Organization

ISOL Isolation, Isolated

ITT Inter Turbine Temperature

J

JAA Joint Aviation Authority

K

K, KT, KTS Knots

kg Kilogram(s)

kHz KiloHertz

KIAS Knots Indicated Airspeed

kW(s) KiloWatt(s)L

L Left, Landing

L/R Left/Right

L/T Landing/Taxi

LAV Lavatory

lb Pound(s)

LCN Load Classification Number

LCV Load Control Valve

LDG Landing

LDG GR Landing Gear

LDU Lamp Driver Unit

LE Leading Edge

LED Light Emitting Diode,

Leading Edge Device

LG Landing Gear

LGC Landing Gear Controller

LGW Landing Gross Weight

LH Left Hand

LIM Limit

LK Leak

LN Left Nose

LNAV Lateral Navigation

LOC ILS Localizer

LOGO Logo Graphic

LOM, MM Compass Locator at Outer Marker

LOP Low Oil Pressure

LP Low Pressure

LPM Liter Per Minute

LR Left Rear

LRC Long Range Cruise

LRU Line Replaceable Unit

LSB Lower Side Band

LT(s) Light(s)

LW Left Wing

LWD Left Wing Down

LWR Lower

M

M Mach Number

m Meter

MAA Maximum Authorized IFR Altitude

MAC Mean Aerodynamic Chord

MAG Magnetic

MAINT Maintenance

MALF Malfunction

MAN Manual



Airplane: CL 601

Revision No: 02 Page No: XXXII Date: 12 Oct 16


MAP Ground Map (WXR)

MASI Mach Air Speed Indicator

MAX Maximum

MAZ MLS Azimuth

MB Millibars

MCA Minimum Crossing Altitude

MCT Maximum Continuous Thrust

MDA Minimum Descent Altitude

MEA Minimum Enroute IFR Altitude

MECH Mechanic

MED Medium

MEL Minimum Equipment List

MFD Multifunction Display

MGP MLS Glideslope

MHz MegaHertz

MI Miles

MIC Microphone

MID AFT Middle Afterward

MID FWD Middle Forward

MILS .021 of an inch

MIN Minimum

MISC Miscellaneous

MKR Marker

MLG Main Landing Gear

MLI Magnetic Level Indicator

MLU Midlife Update

MLW Maximum Landing Weight

MM ILS Middle Marker

MMEL Master Minimum Equipment List

MMO Maximum Operating Speed in

Mach Number

MOCA Minimum Obstruction Clearance Altitude

MOD Module

MON Monitor

MPH Miles Per Hour

MRA Minimum Reception Altitude

MSG Message

MSL Mean Sea Level

MTBF Mean Time Before Failure

MTG Miles to Go

MTOW Maximum Takeoff Weight

MTW Maximum Taxi Weight

MZFW Maximum Zero Fuel Weight

Misc

% Percent

& and

°C Degrees Centigrade

°F Degrees Fahrenheit

N

N/A Not applicable

N1 Low Pressure Rotor

N2 High Pressure Rotor

NAV Navigation

ND Nose Down, Navigation Display

NDB (ADF) Non directional Beacon (Automatic Direction Finder)

NEG Negative

NEUT Neutral

NL Nose Left

NLG Nose Landing Gear

NM Nautical Mile(s)

No. Number

NOPT No Procedure Turn Required

NORM Normal

NOSE Nosewheel

NR Nose Right

NU Nose Up

O

OAT Outside Air Temperature

OB/OUTBD Outboard

OBS Observer

OEI One Engine Inoperative

OEW Operating Empty Weight

OH, OVHD Overhead

OK Okay

OM ILS Outer Marker

OVBD Overboard

OVHT, OH Overheat

OVLD Overload

OVSP Overspeed



Airplane: CL 601

Revision No: 02 Page No: XXXIII Date: 12 Oct 16


OVSPD Overspeed

OVTEMP Over Temperature

OXY, O2 Oxygen

P

P#6 Panel 6

P/S Pitot/Static

PA Passenger Address

PASS Passenger

PBE Portable Breathing Equipment (Smoke Hood)

PCU Power Control Unit

PF Pilot Flying

PFD Primary Flight Display

PIC Pilot-in-Command

PLA Power Lever Angle

PNF Pilot Not Flying

PNLS(s) Panel(s)

PO Outside Air Pressure

POS Position

PPH Pounds Per Hour

PRESS Pressure, Pressurization

PRI Primary

PRIM Primary

PROC Procedure

PROT Protection

PROX Proximity

PSEU Proximity Sensor Electronics Unit

PSI Pounds Per Square Inch

PSIG Pounds Per Square Inch Gauge

PSS Proximity Sensor System

PSU Passenger Service Unit

PT2 Engine Inlet Pressure

PTCT Protect

PTT Push To Talk

PWR Power

Q

QAR Quick Access Recorder QEC Quick Engine Change

QFE Local Station Pressure

QNH Altimeter Setting

QTY Quantity

R

R Right RA Radio Altitude

Resolution Advisory

RAT Ram Air Turbine

RCCB Remote Controlled Circuit Breaker

RCDR Recorder

RCVR Receiver

RDR Radar

REC Receiver, Recorder

RECOG Recognition

REF(s) Reference(s)

REFL Refuel

REV Reverse

RH Right Hand

RMI Radio Magnetic Indicator

RMU Radio Management Unit

ROT Rotation

RPM Revolutions Per Minute

RT, R/T Receiver-Transmitter

RTE Route

RTE DATA Route Data

RTO Rejected Takeoff

RTU Radio Tuning Unit

RUD Rudder

RVR Runway Visual Range

RVSM Reduced Vertical Separation Minimum

RVSR Reverser

RW Right Wing

RWD Right Wing Down

RWY Runway



Airplane: CL 601

Revision No: 02 Page No: XXXIV Date: 12 Oct 16


S

S Status SAT Static Air Temperature

SCAV Scavenge

SDS Status Display System

SEC Second, Secondary

SECS Spoiler Electronic Control System

SECU Spoiler Electronic Control Unit

SEL Select, Selector

SEL CAL Selective Call

SENS Sensitivity, Sensor

SERV, SVCE Service

SM CAA San Marino CAA

SMKG Smoking

SOV Shutoff Valve

SP, SPD Speed

SPKR Speaker

SPLR(s) Spoiler(s)

SQL Squelch

SSB Single Side Band

STA Station

STAB Stabilizer

STAT Status

STBY Standby

STEER Steering

SUPPL Supply

SW(s) Switches

SYN Synchronize

SYNC Synchronous

SYS, SYST System

T

T/C Top of Climb

T/D Top of Descent

T/R Thrust Reverser

TA Traffic Alert

TACAN UHF Tactical Air Navigation Aid

TAS True Airspeed

TAT Total Air Temperature

TCAS Traffic Alert and Collision Avoidance System

TE Trailing Edge

TEMP Temperature

TGT Target

TO, T/O Takeoff

TOC Top of Climb

TOD Top of Descent

TOL Tolerance

TRB, TURB Turbulence

TRK Track

TRM Trim

TRU Transformer Rectifier Unit

TT2 Engine Inlet Temperature

U

UHF Ultra High Frequency

UNSCHD Unscheduled

USB Upper Side Band

UTIL Utility

V



Airplane: CL 601

Revision No: 02 Page No: XXXV Date: 12 Oct 16


V Volt

VA Design Maneuvering Speed

VB Design Speed for Maximum

Gust Intensity

VC Design Cruising Speed

VD Design Diving Speed

VDF/MDF Demonstrated flight diving

speed.

VF Design Flap Speed

VDF/MFC Maximum Speed for Stability

Characteristics

VFE Maximum Flap Extended Speed

VH Maximum Speed in Level Flight

with Maximum Continuous Power

VLE Maximum Landing Gear

Extended Speed

VLO Maximum Landing Gear

Operating Speed

VLOF Lift-off Speed

VMC Minimum Control Speed with

the Critical Engine Inoperative

VMO/MMO Maximum Operating Limit

Speed

VMU Minimum Unstick Speed

VNE Never-exceed Speed

VNO Maximum Structural Cruising

Speed

VR Rotation Speed

VS Stalling Speed or the Minimum

Steady Flight Speed at which the Airplane is Controllable

VS0 Stalling Speed or the Minimum

Steady Flight Speed in the Landing Configuration

VS1 Stalling Speed or the Minimum

Steady Flight Speed Obtained in a Specific Configuration

VX Speed for Best Angle of Climb

VY Speed for Best Rate of Climb

V1 Takeoff Decision Speed

(formerly Denoted as Critical Engine Failure Speed)

V2 Takeoff Safety Speed

V2 MIN Minimum Takeoff Safety Speed

V/S Vertical Speed

VERT Vertical

VFR Visual Flight Rules

VG Vertical Gyro

VHF Very High Frequency

(30 - 302 mHz)

VIB Vibration

VMC Visual Meteorological Conditions

VNAV Vertical Navigation

VOL Volume

VOLT Voltage

VOR VHF Omnidirectional Range Station

VORTAC VOR and TACAN Co-located

VSI Vertical Speed Indicator

W

W Warning

W/C Wind Component

W/S Wind Shear

W/W Wheel Well

WARN Warning

WF Runway Length Limited Weight

WGT Weight

WHLS Wheels

WIND Window

WOW Weight-On-Wheels

WPT(s) Waypoint(s)

WRN Warning

WS Second Segment Limited Weight

WSHLD Windshield

WX Weather

WXR Weather Radar

X

X Cross Transfer

XFER, XFR Transfer

XFLOW Cross Flow

XMIT Transmit



Airplane: CL 601

Revision No: 02 Page No: XXXVI Date: 12 Oct 16


XPNDR Transponder

XTK Cross Track

XWC Cross Wind Component

Y

YD, Y/D Yaw Damper

Z

ZFW Zero Fuel Weight



Airplane: CL 601

Revision No: 02 Page No: XXXVII Date: 12 Oct 16

PREAMBLE

1 Introduction The Minimum Equipment List (MEL) is based on the FAA Master Minimum Equipment List (MMEL) and the Bombardier Dispatch Deviation Guide (for (O) and (M) procedures), with the revision and date as shown on the cover page. This MEL takes into consideration ‘Golden Falcon Aviation S.r.l.’ (known as the operator), particular airplane equipment, configuration and operational conditions, routes being flown and requirements set by the SM CAA. This MEL will not deviate from any applicable Airworthiness Directive or any other Mandatory Requirement, and will be no less restrictive than the MMEL. The MEL is intended to permit operations with inoperative items of equipment for a period of time until rectification can be accomplished. Rectification is to be accomplished at the earliest opportunity. MEL Conditions and Limitations do not relieve the pilot-in-command from determining that the airplane is in a fit condition for safe operation with specified unserviceabilities allowed by the MEL. The provisions of the MEL are applicable until the airplane commences the flight, i.e. begins to move under its own power for the purpose of preparing for take-off. Any decision to continue a flight following a failure or unserviceability which becomes apparent after the commencement of a flight must be the subject of pilot judgement and good airmanship. The pilot-in-command may continue to make reference to and use of the MEL as appropriate. By the approval of the MEL, the CAA approves dispatch of the airplane for flight with certain items or components inoperative, provided an acceptable level of safety is maintained by use of appropriate operational or maintenance procedures, by transfer of the function to another operating component, or by reference to other instruments or components providing the required information. 2 Contents of MEL The MEL contains only those items required by operating regulations or those items of airworthiness significance which may be inoperative prior to dispatch, provided that appropriate limitations and procedures are observed. Equipment obviously basic to airplane airworthiness such as wings, rudders, flaps, engines, landing gear, etc. are not listed and must be operative for all flights.

It is important to note that: ALL ITEMS WHICH ARE RELATED TO THE AIRWORTHINESS OF THE AIRPLANE AND ARE NOT INCLUDED IN THE LIST ARE AUTOMATICALLY REQUIRED TO BE OPERATIVE. 3 Criteria for Dispatch The decision of the pilot-in-command of the flight to have allowable inoperative items corrected prior to flight will take precedence over the provisions contained in the MEL.



Airplane: CL 601

Revision No: 02 Page No: XXXVIII Date: 12 Oct 16

PREAMBLE

The pilot-in-command may request requirements above the minimum listed whenever in his judgement such added equipment is essential to the safety of a particular flight under the particular conditions prevailing at the time. The MEL cannot take into account all multiple unserviceabilities. Therefore, before dispatching an airplane with multiple MEL items inoperative, it must be assured that any interaction or interrelationship between inoperative items will not result in degradation in the level of safety and/or an undue increase in crew workload. It is particularly in this area of multiple deficiencies (and especially deficiencies in related systems) that good judgement – based on the circumstances of the case, including climatic and en-route conditions – must be used. 4 Maintenance Action Every effort shall be made by the contracted maintenance organisation to correct all technical defects as early as practicable, and to ensure that the airplane is released from a maintenance station in fully operational condition. The pilot-in-command must be informed by maintenance as soon as practicable should it be impossible to rectify the inoperative item prior to departure. Whenever an airplane is released by Maintenance for dispatch with items inoperative, the following is required: a. The log book, or equivalent, aboard the airplane must contain a detailed description of the

inoperative item(s), special advice to the flight crew, if necessary, and information about corrective action taken.

b. When they are accessible to the crew in flight, the control(s), and/or indicator(s) related to

inoperative unit(s) or component(s) must be clearly placarded either as indicated in the MEL or “INOPERATIVE” or “INOP” and clearly identified.

c. If inadvertent operation could produce a hazard such equipment must be rendered

inoperative (physically) as given in the appropriate maintenance procedure.

d. Install an "INOP." placard below in the position specified in the MEL. When the position is

not specified then the placard shall be placed on or immediately adjacent to the defective instrument, control, switch, or device

e. If an "INOP." placard is not available, a temporary placard may be made from dymo tape

or paper and tape as follows. The placard should contain the wording from the MEL.

f. The relevant operational (O) and maintenance (M) procedures are specifically identified in

each System and Item Sequence Number in this MEL. g. Unserviceable equipment must not be removed from the airplane unless specifically

permitted by the MEL or associated (M) procedures.



Airplane: CL 601

Revision No: 02 Page No: XXXIX Date: 12 Oct 16

PREAMBLE

5 Rectification Intervals Inoperative items or components, deferred in accordance with the MEL, must be rectified at or prior to the Rectification Intervals established by the following letter designators given in the ‘Rectification Interval Category’ column of the MEL.

Category A Items in this category shall be rectified within the limitations specified in the MEL entry, commencing at 02:01 on the day following discovery for those items specified in calendar days. Category B Items in this category shall be rectified within three (3) consecutive calendar days, excluding the day of discovery. Category C Items in this category shall be rectified within ten (10) consecutive calendar days, excluding the day of discovery. Category D Items in this category shall be rectified within one hundred and twenty (120) consecutive calendar days, excluding the day of discovery. The letter designators are inserted adjacent to Column 2.

6 Operations outside the Scope of the MEL In exceptional circumstances, the CAA may exempt Golden Falcon Aviation S.r.l. from compliance with the MEL on an individual case-by-case basis.

7 Non-standard Operations Ferry flights are flights carrying neither passengers nor freight, for the purpose of returning the airplane to a place where it can be repaired. These flights may be dispatched with less than the equipment specified in the MEL provided all the equipment expected to be utilised in flight is operable and any relevant Sections of the Flight Manual are applied. Permission for such a flight, however, must be granted by the SM CAA before the flight takes place. Other non-standard operations include Demonstration Flights, Test Flights (after maintenance) and Training Flights. Similar provisions apply to these flights, but the Operations Manual must include specific guidance on their conduct, and such flights must not take place without general or specific permission from the CAA.



Airplane: CL 601

Revision No: 02 Page No: XXXX Date: 12 Oct 16

PREAMBLE

8 Amendment Timescales This MEL will be amended to ensure that it remains no less restrictive than the MMEL upon which it is based. When the MMEL or MMEL Supplement is amended to become more restrictive than the MEL, the MEL will be correspondingly amended as soon as possible, and in any case within 30 days of receipt of the MMEL or Supplement revision. The MEL will not necessarily be amended when the MMEL or MMEL Supplement is amended to be less restrictive The MEL will also be amended as soon as possible, and in any case within 30 days of a requirement by the CAA to amend the MEL. In other cases, including those amendments instigated by Golden Falcon Aviation S.r.l. to reflect changes to equipment or operations, the MEL will be amended as soon as convenient, and in any case within 90 days of the change that prompted the amendment. Changes to other documents, such as the (O) and (M) procedures contained in the Bombardier Dispatch Deviation Guide that affect the content of the MEL will also be reflected in the MEL within 90 days of receipt of the relevant revision, except where the amendment is clearly more restrictive than the current procedures in the MEL. In this case, the procedures will be amended as soon as possible and in any case within 30 days of receipt of the amendment. 9. Deferring Procedures and Control – Maintenance

If a defect has been deferred by the flight crew (Section 4) re-defer in accordance with the following:

a. The defect will be entered in the Technical Log Book as “deferred in accordance with MEL ATA#...” and signed by an appropriately qualified and certified mechanic designated by Maintenance.

b. Wherever information appears in the MEL “Remarks and Exceptions Column”, the qualified and certified mechanic will specify the requirements and/or limitations to conduct the flight and provide briefing to the crew. Such requirements and/or limitations shall come from the applicable “(O) and/or (M) procedures contained in this MEL.

c. A placard will be placed in the airplane either as described by the MEL or at paragraph 4e.

d. The Technical Log Book must be checked to ensure that when operating with multiple inoperative items, the interrelationship between those items and the effect on airplane operation and crew workload will be considered.

e. The deferral will be tracked by the Golden Falcon Aviation S.r.l. Airworthiness Coordinator to ensure a timely rectification with regard to the categorization.

f. After defect rectification, remove the placard from the airplane and make an entry in the airplane Technical Log Book to confirm rectification of the defect. This entry must be signed by a qualified AME designated by Golden Falcon Aviation S.r.l.

g. It is mandatory that all defects not cleared when the Technical Log Book expires be transferred to the new Technical Log Book with all details.



Airplane: CL 601

Revision No: 02 Page No: XXXXI Date: 12 Oct 16

PREAMBLE

10. Use of MEL – Flight Crew

Once a defect has been established as being deferrable, the Pilot-in-Command (PIC) may defer the defect in accordance with the MEL providing the following procedures are adhered to:

a. The PIC will enter the defect in the Technical Log Book.

b. The PIC will advise the Maintenance department as soon as practicable.

c. Where required the flight crew will adhere to all restrictions and perform (O) procedures as applicable.

d. Flight Crews may not perform Maintenance procedures if the defect involves an item designated in the MEL as (M) – which denotes MAINTENANCE PERSONNEL REQUIRED. The airplane may not proceed until maintenance carries out the required procedures.

e. The Technical Log Book must be checked by the PIC for multiple inoperative items. The interrelationship between those items and the resultant effect on airplane operation and crew workload will be considered by the PIC before making a GO/ NO-GO decision.

f. The PIC will enter in the Technical Log Book, adjacent to the defect, under what authority the defect has been deferred i.e. “deferred in accordance with MEL ATA Number...”, the time of day, his/her signature and pilot’s license number.

g. If any doubt exists, this does not preclude the pilot from consulting maintenance to confirm the ATA item and procedure has been deferred correctly prior to subsequent dispatch.

h. The airplane may proceed on a planned itinerary to a base where maintenance will rectify or re-defer the defect in accordance with the procedures set forth in this MEL.

WHEN USING THE MEL, COMPLIANCE WITH THE STATED INTENT OF THE PREAMBLE, DEFINITIONS, CONDITIONS, AND LIMITATIONS SPECIFIED IN THE MEL IS REQUIRED.



Airplane: CL 601

Revision No: 02 Page No: XXXXII Date: 12 Oct 16

PREAMBLE




Airplane: CL 601

Revision No: 02 Page No: 21-1 Date: 12 Oct 16

AIR CONDITIONING

System & Item 1

Sequence Numbers

2 Number Installed

1

3 Number Required for Dispatch 21 AIR CONDITIONING

21−20−1 Heat Exchanger Fan C (Footwarmer Demist)

0

4 Remarks or Exceptions

.

1. PLACARD

A. Put a HEAT EXCHANGER FAN INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601


AIR CONDITIONING

System & Item 1

Sequence Numbers

2 Number Installed

1


21−30−1 Emergency C Pressurization System

0


(O) May be inoperative provided airplane is operated unpressurized.

1. PLACARD

A. Put an EMERERGENCY PRESSURIZATION SYSTEM INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Procedure for unpressurized flight:

After engine start:

a) EMER DEPRESS switch/light ...........................Press in ON light on.

During Flight:

Operate the airplane at or below altitude 10 020 ft.

NOTE: 1. Airplane is allowed to operate at a higher altitude only if crew and passengers are provided with supplemental oxygen.

NOTE 2. Air Conditioning System operation: refer to AIRPLANE FLIGHT MANUAL − Normal Procedures.



Airplane: CL 601


AIR CONDITIONING

System & Item Sequence Numbers

1 2 Number Installed

1


0

0


(O) May be inoperative provided Cabin Altitude Aural (Horn) Warning System is operative.


21−30−2 Cabin Altitude Warning

System

1. Visual (CABIN PRESS LOW Light)

C

C

1

1. PLACARD

A. Put a CABIN PRESS LOW LIGHT INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. For an inoperative cabin altitude warning light, the PIC must check cabin altitude pressure during initial climb and every 10 minutes in cruise.

B. For unpressurized flight, do the steps that follow:

(1) After engine start, press in the EMER DEPRESS switch/light. Make sure that the ON light comes on.

(2) During flight, operate the airplane at or below 10 020 altitude.

NOTE 1: Airplane is allowed to operate at a higher altitude only if crew and passengers are provided with supplemental oxygen.

NOTE 2: Air Conditioning System operation: refer to AIRPLANE FLIGHT MANUAL −

Normal Procedures.



Airplane: CL 601


AIR CONDITIONING

System & Item

Sequence Numbers


1


0

0

0


(O) May be inoperative provided Cabin Altitude Visual (Light) Warning System is operative.

(O) May be inoperative provided airplane is operated at or below 10,020 feet MSL.


21−30−2 Cabin Altitude Warning

System

2. Aural (Horn) D

C

1

C

1

1. PLACARD

A. Put a HORN INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. For an inoperative cabin altitude warning horn, do the steps that follow:

(1) On the pilot/co-pilot facia panel, put the WARN LTS switch to the TEST position.

(2) On the overhead CABIN PRESSURIZATION control panel, make sure that the CABIN PRESS LOW light comes on.

(3) Release the TEST switch.

(4) Make sure that CABIN PRESS LOW light goes out.

B. For flights below 10,020 feet MSL, the flight crew must determine minimum safe altitudes on all route segments to ensure that flight plan (as planned or revised) from take-off to landing can be accomplished.

C. For unpressurized flight, do the steps that follow:




Airplane: CL 601


AIR CONDITIONING

(2) During flight, operate the airplane at or below 10 020 MSL.


NOTE 2 Air conditioning System operation: refer to AIRPLANE FLIGHT MANUAL − Normal Procedures.



Airplane: CL 601


AIR CONDITIONING

System & Item 1

Sequence Numbers 2 Number Installed

1

1

3 Number Required for Dispatch

21 AIR CONDITIONING

21−30−3 Cabin Altitude Indicator C

C

0

0


(O) May be inoperative provided:

a) Cabin Differential Pressure Indicator is operative, and

b) A chart is provided to convert cabin differential pressure to cabin altitude.

(O) May be inoperative provided

a) Pressurization System is considered inoperative, and

b) Airplane is operated

unpressurized.

1. PLACARD

A. Put a CABIN ALTITUDE INDICATOR INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. For pressurized flight, do the steps that follow:

(1) During flight, continuously monitor cabin differential pressure and airplane altitude indicators. Using chart displayed on Figure 1 determine cabin altitude.



(2) During flight, operate the airplane at or below altitude 10 020 ft MSL.

NOTE: 1. Airplane is allowed to operate at a higher altitude only if crew and passengers are provided with supplemental oxygen. NOTE 2. Air Conditioning System operation: refer to AIRPLANE FLIGHT MANUAL − Normal Procedures.



Airplane: CL 601


AIR CONDITIONING

Effect of Cabin Differential on Cabin Altitude

Figure 1



Airplane: CL 601


AIR CONDITIONING

System & Item 1


1

1


21 AIR CONDITIONING

21−30−4 Cabin Differential C Pressure Indicator

C

0

0



a) Cabin Altitude Indicator is operative, and

b) A chart is provided to convert cabin altitude to cabin differential pressure.

(O) May be inoperative provided; a) Pressurization System is

considered inoperative, and

b) Airplane is operated unpressurized.

1. PLACARD

A. Put a CABIN ALTITUDE INDICATOR INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. For pressurized flight, do the step that follows:

(1) During flight, continuously monitor cabin and airplane altitude indicators. Using chart displayed on Figure 2 determine cabin altitude.



(2) During flight, operate the airplane at or below 10 020 ft MSL.

NOTE:1. Airplane is allowed to operate at a higher altitude only if crew and passengers are provided with supplemental oxygen. NOTE 2. Air Conditioning System operation: refer to AIRPLANE FLIGHT MANUAL − Normal Procedures.



Airplane: CL 601


AIR CONDITIONING

Effect of Cabin Differential on Cabin Altitude

Figure 1



Airplane: CL 601


AIR CONDITIONING

System & Item 1

Sequence Numbers

2 Number Installed

1

1


21−30−5 Cabin Rate of Climb C Indicator

C

0

0


May be inoperative provided:

a) Cabin Altitude Indicator is operative,

b) Cabin Differential Pressure Indicator is operative, and

c) Cabin Pressurization Control System Automatic Mode is operative.


1. PLACARD

A. Put a CABIN RATE OF CLIMB INDICATOR INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. For pressurized flight, do the step that follows:

a) During flight, continuously monitor cabin and airplane altitude indicators.

B. For pressurized flight, do the steps that follows:

a) After engine start:

EMER DEPRESS switch/light ...........................Press in ON light on.

b) During Flight:

Operate the airplane at or below 10 020 MSL.

NOTE:1. Airplane is allowed to operate at a higher altitude only if crew and passengers are provided with supplemental oxygen. NOTE 2. Air Conditioning System operation: refer to the Airplane Flight Manual – NORMAL PROCEDURES.



Airplane: CL 601


AIR CONDITIONING

System & Item 1

Sequence Numbers

2 Number Installed

2


21−31−1 Cabin Pressurization Control System

1. Automatic and C Manual Modes

0


(O) Both may be inoperative provided:

a) Airplane is operated unpressurized, and

b) Extended flight over water operations are prohibited.

NOTE

During ground operations at ambient temperatures above 45°C (113°F), operation of electrical/ avionics equipment must be limited to thirty minutes unless at least one ACU/Pack is operating and cabin doors are closed as per AFM.

1. PLACARD

A. Put a CABIN PRESSURIZATION CONTROL SYSTEM INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

Procedure for unpressurized flight: After engine start:


NOTE: During ground operation at ambient temperature above 45°C (113°F), operation of electrical/avionics equipment must be limited to 30 minutes unless at least one air conditioning unit is operating and cabin doors are CLOSED.



Airplane: CL 601


AIR CONDITIONING

During Flight:

a) Operate the airplane at or below 10 020 MSL.

NOTE: 1. Airplane is allowed to operate at a higher altitude only if crew and passengers are provided with supplemental oxygen as required by regulations.

NOTE 2. Air Conditioning System operation: refer to the Airplane Flight Manual – NORMAL PROCEDURES.



Airplane: CL 601


AIR CONDITIONING

System & Item 1

Sequence Numbers

2 Number Installed

1

1



2. Automatic Mode C

C

0

0



a) Cabin Pressurization Control System Manual Mode is operative,

b) Airplane is not operated more than 60 minutes from a suitable airport.


a) Total fuel carried includes at least 50% more than the fuel load required for the planned flight, and

b) Airplane is operated at or below 302 KIAS when airplane is at or below 12,502 feet.

1. PLACARD


2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. For flights within 60 minutes of a suitable airport, do as follows

a) After engine start operate the cabin pressurization control system in manual mode as per AFM – NORMAL PROCEDURES – AIR CONDITIONING AND PRESSURIZATION.

b) Before Take-Off, refer to AFM − NORMAL PROCEDURES − AIR

CONDITIONING AND PRESSURIZATION.



Airplane: CL 601


AIR CONDITIONING

B. Operations are not to be conducted more than 60 minutes from a suitable airport.



Airplane: CL 601


AIR CONDITIONING

System & Item 1

Sequence Numbers

2 Number Installed

1



4. Manual Mode C

0



a) Cabin Pressurization Control

System Automatic Mode is operative,

b) Operations are not conducted more than 60 minutes from a suitable airport, and

c) Extended flight over water operations are prohibited.

1. PLACARD


2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601


AIR CONDITIONING

System & Item 1

Sequence Numbers

2 Number Installed

2


21−32−1 Outflow / Safety Valves B

0


(M) (O) One or both may be inoperative provided:

a) Affected valve(s) is secured open,

b) Airplane is operated unpressurized at or below 10,020 feet MSL, and

c) Extended flight over water operations are prohibited, and

d) Takeoffs and landings must not be conducted on runways that may lead to imminent ditching

1. PLACARD

A. Put an OUTFLOW / SAFETY VALVES INOPERATIVE placard on the instrument panel. 2. MAINTENANCE (M)

Before Flight:

A. Single valve inoperative:

NOTE: The deactivation procedure is the same for both outflow safety valves.

(1) Connect the external electrical power to the airplane.

(2) On the CABIN PRESSURIZATION control panel, set MODE switch to MAN.

(3) Remove the floor panels necessary to gain access to outflow valves (refer to AIRPLANE MAINTENANCE MANUAL, Chapter 53−20−11).

(4) Access to the aft side of outflow valves can be gained through the rear equipment bay door 311BB.

(5) Using equal pressure, carefully push the poppet of the affected outflow safety valve to the open position.

(6) Cut a piece of hose (rubber or plastic) approximately 12 inches (30.5 cm) in length. The specifications for the hose are as follows:

- MFG: NORTON TYGON TUBING B−44−4X inner braided tubing or equivalent

- CANADAIR spec: CMS 534−03 TYPE II or equivalent



Airplane: CL 601


AIR CONDITIONING

- Maximum outer diameter = 0.625 inch (15.87 mm)

- Minimum inner diameter = 0.375 inch (9.53 mm).

(7) Install the hose through the outflow safety valve from one side to the other.

(8) Attach the hose to the side arm with tie wraps.

(9) Open and collar the circuit breaker that follows:

CB PANEL CB NO. NAME ZONE

CBP−B 302 CABIN PRESS – CONT 222

(10) Remove the external electrical power.

(11) Close the floor panels and the access door removed in the step (3).

B. Both valves inoperative:

(1) Connect the external electrical power.

(2) On the CABIN PRESSURIZATION control panel, set MODE switch to MAN.

(3) Remove the floor panels necessary to gain access to outflow valves (refer to AIRPLANE MAINTENANCE MANUAL, Chapter 53−20−11). Access to the aft side of outflow valves can be gained through the rear equipment bay door 311BB.

(4) Using equal pressure, carefully push the poppet of the affected outflow safety valve to the open position.

(5) Cut a piece of hose (rubber or plastic) approximately 36 inches (91.44 cm) in length. The specifications for the hose are as follows:

- MFG: NORTON TYGON TUBING B−44−4X inner braided tubing

- CANADAIR spec: CMS 534−03 TYPE II

- Maximum outer diameter = 0.625 inch (15.87 mm)

- Minimum inner diameter = 0.375 inch (9.53 mm).

(6) Install the hose through the outflow safety valves.

(7) Repeat steps (4) to (6) for the opposite outflow safety valve.

(8) Attach the hose to the side arm of the outflow valves with tie wraps.

(9) Open and collar the circuit breaker that follows:



Airplane: CL 601


AIR CONDITIONING


CBP−B 302 CABIN PRESS – CONT 222

(10) Remove the external electrical power.

(11) Close the floor panel and the access door removed in the step (3).

3. OPERATIONS (O)

After Engine Start:

a) EMER DEPRESS switch/light ...........................Press in ON light on. During Flight: a) Operate the airplane at or below 10 020 ft MSL

NOTE: 1. Airplane is allowed to operate at a higher altitude only if crew and passengers are provided with supplemental oxygen. NOTE 2. Air Conditioning System operation: refer to AIRPLANE FLIGHT MANUAL − Normal Procedures.



Airplane: CL 601


AIR CONDITIONING

System & Item 1

Sequence Numbers

2 Number Installed

2

2

2


21−51−1 Air Conditioning Units C (ACUs)

C

C

1

1

0


One may be inoperative provided:

a) Ram Air Vent Valve is operative,

b) Associated cowl anti−ice is selected ON when airplane is operated above FL 402, and

c) Operations are not conducted more than 60 minutes from a suitable airport.


a) Total fuel carried includes at least 50% more than the fuel load required for the planned flight, and

b) Airplane speed is limited to 302 KIAS when at or below 12,502 feet.


a) Ram Air Vent Valve is operative, and

b) Airplane is operated unpressurized.

NOTE: During ground operations at ambient temperatures above 45° C (113° F), operation of electrical/avionics equipment must be limited to 30 minutes unless at least one ACU is operating and cabin doors are closed as per AFM.

1. PLACARD

A. Put an AIR CONDITIONING UNITS INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. If both ACUs are inoperative, do as follows::



Airplane: CL 601


AIR CONDITIONING

a) On the CABIN PRESSURIZATION control panel, press the RAM AIR VENT switch/light. Make sure the light comes ON.

After engine start:


During Flight:

a) Operate the airplane at or below 10 020 ft MSL.


NOTE 2 Air Conditioning System operation: refer to the Airplane Flight Manual − NORMAL PROCEDURES.

NOTE 3. During ground operation at ambient temperature above 45° C (113° F) operation of electrical / avionics equipment must be limited to 30 minutes unless at least one ACU is operating and cabin doors are closed as per AFM.



Airplane: CL 601


AIR CONDITIONING

System & Item 1

Sequence Numbers

2 Number Installed

1

1


21−52−1 Ram Air Vent Valve C

C

0

0


(M) May be inoperative CLOSED provided:

a) Valve is deactivated CLOSED, and

b) Both ACUs / Packs are operative.

(M) May be inoperative OPEN provided:

a) Valve is deactivated OPEN,

b) RH ACU/Pack is operative,

c) LH ACU/Pack is selected OFF,

d) Associated (LH) cowl anti−ice is selected ON when airplane is operated above FL 402, and

e) Airplane is not operated more than 60 minutes from a suitable airport.

1. PLACARD

A. Put a RAM AIR VENT VALVE INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Deactivate the Ram Air Shutoff Valve closed as follows:

(1) On the overhead panel put the BATTERY MASTER switch to ON.

(2) On the overhead CABIN PRESSURIZATION control panel, make sure that the RAM AIR VENT ON switch/light is off.

(3) Disconnect the electrical connector from the ram air shutoff valve.

(4) Protect the electrical connector as follows:

(a) Enclose the electrical connector in S1244 conduit (Canadair part number S1244C12−57 or S1244C18−4) doubled back and spot tied.

(b) Secure the connector by tying it to a supporting electrical cable run or a structural member so that it cannot swing.

(5) On the overhead panel put the BATTERY MASTER switch to OFF.



Airplane: CL 601


AIR CONDITIONING

B. Deactivate the Ram Air Shutoff Valve open as follows:

(1) On the overhead panel put the BATTERY MASTER switch to ON.

(2) On the overhead CABIN PRESSURIZATION control panel, make sure that the RAM AIR VENT ON switch/light is on.

(3) Disconnect the electrical connector from the Ram Air Shutoff Valve.

(4) Protect the electrical connector as follows:

(a) Enclose the electrical connector in S1244 conduit (Canadair part number S1244C12−57 or S1244C18−4) doubled back and spot tied.

(b) Secure the connector by tying it to a supporting electrical cable run or a structural member so that it cannot swing.

(5) On the overhead panel put the BATTERY MASTER switch to OFF.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601


AIR CONDITIONING

System & Item 1

Sequence Numbers

2 Number Installed

1


21−53−1 Right Foot warmer C De−Mist Pressure Regulating and Shut−Off Valve

0


1. PLACARD

A. Put a RIGHT FOOTWARMER DE−MIST PRESSURE REGULATING AND SHUT−OFF VALVE INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601


AIR CONDITIONING

System & Item 1


3

3


21 AIR CONDITIONING

21−61−1 Temperature Control System

1. Cockpit Modes C (NORMAL, STANDBY, MANUAL)

C

1

0


Any or all may be inoperative provided all Cabin modes are operative.

1. PLACARD

A. Put a COCKPIT MODES INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601


AIR CONDITIONING

System & Item 1


3

3


21 AIR CONDITIONING

21−61−1 Temperature Control System

2. Cabin Modes C (NORMAL, STANDBY, MANUAL)

C

1

0


Any or all may be inoperative provided all Cockpit modes are operative.

1. PLACARD

A. Put a CABIN MODES INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601


AIR CONDITIONING

System & Item 1


1


21 AIR CONDITIONING

21−61−2 Cabin Temperature C Indicating System

0


1. PLACARD

A. Put a CABIN TEMPERATURE INDICATOR INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601


AUTO FLIGHT

System & Item 1

Sequence Numbers

2 Number Installed

1

3 Number Required for Dispatch 22 AUTO FLIGHT

22−10−1 Autopilot Systems 1. B

0


(M) (O) Except when enroute operations

or approach procedures require its use, may be inoperative provided:

a) Automatic Cabin Pressurization Control System is operative, and

b) System is deactivated after Mach Trim test is verified operative prior to each flight.

1. PLACARD

A. Put an AUTOPILOT SYSTEMS INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

Before Flight:

A. Open and collar the autopilot circuit breakers that follow:


CBP−C 337 AP COMP CHAN 1 221

CBP−B 273 AUTO PILOT COMP CHAN 2 222

CBP−A 41 AP COMP CHAN 2 221

CBP−A 117 AP COMP CHAN 1 221

3. OPERATIONS (O)

Before First Flight:

A. Do the Mach Trim test (Refer to AIRPLANE FLIGHT MANUAL, NORMAL

PROCEDURES, SYSTEMS OPERATION − MACH TRIM).

NOTE: You must do the Mach Trim test before you open the autopilot circuit breakers. If you do not do this, the WOW signal will be lost to the Stability Augmentation Computer and the test will not give the expected result.



Airplane: CL 601


AUTO FLIGHT

System & Item 1

Sequence Numbers

2 Number Installed

2


22−10−1 Autopilot Systems

1.

a) Roll Axis Channel C

1


(O) May be inoperative provided the

opposite roll channel and roll monitor are verified operative prior to each flight.

1. PLACARD

A. Put a ROLL AXIS CHANNEL INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

Before Flight:

A. Check the opposite roll channel as follows:

(1) On the center pedestal, press the failed ROLL CHANNEL (1 or 2) and make sure that the OFF light comes on.

(2) Engage the autopilot.

(3) Press the TEST 1 or TEST 2 ROLL MON switch. Select operative channel and hold for 6 seconds. Make sure that the autopilot disengages and AFCS light comes on.

(4) Release the ROLL MON TEST 1 or TEST 2 switch.

(5) Press the control column AP/SP DISC push-button, make sure that the AFCS light goes out.



Airplane: CL 601


AUTO FLIGHT

System & Item 1

Sequence Numbers

2 Number Installed

2


22−10−1 Autopilot Systems

1.

b) Pitch Axis C Channel

1


(O) May be inoperative provided the

opposite pitch channel is verified operative prior to each flight.

1. PLACARD

A. Put a PITCH AXIS CHANNEL INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

Before Flight:

A. Check the opposite pitch axis channel as follows:

(1) Amber AP FAIL Light on, Pitch 1 OFF or Pitch 2 OFF light on.

(2) In case of a channel failure, the system automatically reverts to the other channel (single channel operation).

(3) Press to cancel the AP Fail flashing light.



Airplane: CL 601


AUTO FLIGHT

System & Item 1 Sequence Numbers

2 Number Installed

2

2


22 AUTO FLIGHT

22−10−2 Flight Directors

C

B

1

0


(O) One may be inoperative provided approach or operating procedures are not dependent on its use.

NOTE 1: Flight Director and Transporter must use same ADC data for RVSM Operations.

NOTE 2: Associated TOGA switch will be inoperative.

(O) Except for RVSM Operations, both may be inoperative provided approach minimums or operating procedures are not dependent on their use.

NOTE 1: Associated TOGA switches will be inoperative.

NOTE 2: Autopilot will be inoperative

1. PLACARD

A. Put a FLIGHT DIRECTORS INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. If one flight director is inoperative, the PIC must brief on monitoring procedures and the pilot with the serviceable Flight Director must fly the airplane whilst the pilot not flying must monitor flight attitudes, altitudes and performance.

NOTE: 1. Flight Director and Transponder must use same ADC data for RVSM operations.

NOTE 2. Associated TOGA switch will be inoperative.

B. If both flight directors are inoperative, the PIC must fly the airplane whilst the pilot not flying must monitor flight attitudes, altitudes and performance:



Airplane: CL 601


AUTO FLIGHT

NOTE: 1. The autopilot will be inoperative.

NOTE 2. Both TOGA switches will be inoperative.



Airplane: CL 601


AUTO FLIGHT

System & Item 1

Sequence Numbers

2 Number Installed

2

2


22−11−1 Autopilot Disconnect C Switches (Control Wheel Buttons)

B

1

0


(O) One may be inoperative provided:

a) It is verified on every originating check that both control wheel autopilot disconnect switches can disengage the stick pusher function of stall protection system, and

b) Autopilot is not used below 1502 feet AGL, and

c) Approach minimums do not require its use


a) It is verified on every originating check that both control wheel autopilot disconnect switches can disengage the stick pusher function of stall protection system, and

b) Autopilot system is not used.

1. PLACARD

A. Put an AUTOPILOT DISCONNECT SWITCHES INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. For one inoperative:

Before First Flight

a) If one autopilot disconnect button is inoperative, do the steps that follow: (1) On both STALL PROTECTION control panels, put the PUSHER switches

to the ON position



Airplane: CL 601


AUTO FLIGHT

(2) Make sure that the affected stall protection pusher disconnect function is operative as follows:

(a) Hold both STALL PROTECTION TEST switches to the TEST

position and note the following:

1) ALT COMP FAIL caution message comes on. 2) Pilot’s and co-pilot’s stick shakers are activated. 3) IGN A ON, IGN B ON and CONT IGN lights come on. 4) STALL/PUSH and STALL PROTECT FAIL lights flash. 5) Stall aural warning sounds.

(b) While in stick pusher mode, press the affected control wheel AP/SP

DISC switch and note that the affected control wheel stick pusher is de-activated. Release the affected control wheel AP/SP DISC switch and note that the stick pusher is re-engaged.

(c) While in stick pusher mode, press the non-affected control wheel

AP/SP DISC switch and note that the non-affected control wheel stick pusher is de-activated. Release the non-affected control wheel AP/SP DISC switch and note that the stick pusher is re-engaged.

(d) Release the STALL PROTECTION TEST switches and note the

following:

1) Stick pushers are de-activated. 2) All messages and lights go out.

3) Stall aural warning stops.

During Flight:

With the autopilot engaged, pilot controlling the airplane has an operative AP/SP DISC switch.

B. For Two Inoperative:


a) If two autopilot disconnect buttons are inoperative, do the steps that follow:

(1) On both STALL PROTECTION control panels, put the PUSHER switches to the ON position.

(2) Make sure that the stall protection pusher disconnect functions are operative as follows:



Airplane: CL 601


AUTO FLIGHT

(a) Hold both STALL PROTECTION TEST switches to the TEST position and note the following:

1) ALT COMP FAIL caution message comes on. 2) Pilot’s and co-pilot’s stick shakers are activated. 3) IGN A ON, IGN B ON and CONT IGN lights come on. 4) STALL/PUSH and STALL PROTECT FAIL lights flash. 5) Stall aural warning sounds.

(b) While in stick pusher mode, press the control wheel AP/SP DISC

switches and note that the control wheel stick pushers are de-activated. Release the control wheel AP/SP DISC switches and note that the stick pushers are re-engaged.

(c) Release the STALL PROTECTION TEST switches and note the

following:

1) Stick pushers are de-activated. 2) All messages and lights go out. 3) Stall aural warning stops.



Airplane: CL 601


AUTO FLIGHT

System & Item 1


2


22 AUTO FLIGHT

22−11−2 Touch Control Steering C (TCS) Switches

0


1. PLACARD

A. Put a TOUCH CONTROL STEERING SWITCHES INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601


AUTO FLIGHT

System & Item 1

Sequence Numbers

2 Number Installed

2


22−11−4 Take−Off/Go−Around C (TOGA) Switches

0


(O) May be inoperative provided procedures below are used.

1. PLACARD

A. Put a TOGA SWITCHES INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. For operation of airplane without TOGA switch(es), initially establish 10 degrees pitch using the attitude Director Indicator for take-off and go around.



Airplane: CL 601


AUTO FLIGHT

System & Item 1


1

1


22 AUTO FLIGHT

22−20−1 Mach Trim System C

C

0

0


May be inoperative provided autopilot is engaged in flight.

May be inoperative provided airspeed is limited to 250 KIAS / 0.7 Mach when the autopilot is not engaged.

NOTE: Autopilot must be engaged during RVSM Operations.

1. PLACARD

A. Put a MACH TRIM SYSTEM INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601


AUTO FLIGHT

System & Item 1

Sequence Numbers

2 Number Installed

2


22−20−2 Yaw Damper Channels C

1


(O) One channel may be inoperative provided the rudder is verified in the central position before each flight

1. PLACARD

A. Put a YAW DAMPER CHANNELS INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. During the after start check and prior to take-off the rudder must be verified in the central position on the control surface position indicator panel.



Airplane: CL 601


AUTO FLIGHT


2 Number Installed

2


22 AUTO FLIGHT

22−20−3 Yaw Rate Gyros C

1


One may be inoperative provided Standby Attitude Indicator is operative.

1. PLACARD

A. Put a YAW RATE GYROS INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required

3. OPERATIONS (O)

A. Not required



Airplane: CL 601


AUTO FLIGHT




Airplane: CL 601


COMMUNICATIONS

System & Item 1

Sequence Numbers

2 Number Installed

3

3 Number Required for Dispatch 23 COMMUNICATIONS

23−11−1 Communication Systems

VHF D

2


Any in excess of those required may be inoperative provided: a) It is not powered by the battery bus, and

b) It is not required for emergency purposes.

NOTE 1: VHF #1 must be operative.

1. PLACARD

A. Put a VHF No. # COMMUNICATION SYSTEMS INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Not required



Airplane: CL 601


COMMUNICATIONS

System & Item 1

Sequence Numbers

2 Number Installed

4


23−11−1 Communication Systems (VHF)

3. Frequency Selector C Button/Knob

2


One knob may be inoperative on each control unit.

1. PLACARD

A. Put a CONTROL UNIT FREQUENCY SELECTOR INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Not required



Airplane: CL 601


COMMUNICATIONS

System & Item 1

Sequence Numbers

2 Number Installed

4



4. Frequency Indication C

2


.

1. PLACARD

A. FREQUENCY TRANSFER BUTTON/KEY INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required. 3. OPERATIONS (O)

A. Not required



Airplane: CL 601


COMMUNICATIONS

System & Item 1

Sequence Numbers

2 Number Installed

4



4. Frequency Indication

c. Control Unit Frequency Indication C

2


.

One frequency indication may be inoperative on each control unit

1. PLACARD

A. Place a CONTROL UNIT FREQUENCY INDICATION INOPERATIVE placard on the center pedestal.

2. MAINTENANCE (M)


A. Not required



Airplane: CL 601


COMMUNICATIONS

System & Item 1

Sequence Numbers

2 Number Installed

1


23−11−3 Inflight Telephone D System

0


1. PLACARD

A. Put an INFLIGHT TELEPHONE SYSTEM INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601


COMMUNICATIONS

System & Item 1

Sequence Numbers

2 Number Installed

2

2

3 Number Required for Dispatch 23 COMMUNICATIONS 23−12−1 High Frequency (HF)

Communication Systems

C

D

1

1


(O) May be inoperative while conducting operations that require two Long Range Communication Systems (LRCS) provided:

a) SATCOM Voice or Data Link operates normally,

b) Alternate procedures below are used,

c) SATCOM voice coverage is available over the intended route of flight, and

d) If SATCOM Voice is to be used

over the intended route of flight, SATCOM Voice short codes (INMARSAT) or direct dial commercial numbers (IRIDIUM) must be available. If not available, prior coordination with appropriate ATS (FIR) facility is required.

NOTE : SATCOM Voice is to be used only as a backup to normal HF communications HF may be inoperative provided adequate VHF communication coverage is available for the entire route of flight.

1. PLACARD

A. Put a HF COMMUNICATION SYSTEMS INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.



Airplane: CL 601


COMMUNICATIONS

3. OPERATIONS (O)

A. Prior coordination with the appropriate ATS (FIR) facility is required when Inmarsat codes for SATCOM voice are not available.

B. SATCOM datalink system to be used as an alternate to an inoperative HF system.

C. Prior to taxy ensure SATCOM Voice operates normally,



Airplane: CL 601


COMMUNICATIONS

System & Item 1

Sequence Numbers

2 Number Installed

1

1


23−21−1 Selective Call C (SELCAL) System

D

0 0


(O) May be inoperative provided alternate procedures below are used.

May be inoperative provided procedures do not require its use.

1. PLACARD

A. Put a SELCAL SYSTEM INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. One flight crewmember must monitor the appropriate ATC designated frequencies at all times.



Airplane: CL 601


COMMUNICATIONS

System & Item 1

Sequence Numbers

2 Number Installed

5

5


23−21−1 Selective Call (SELCAL) System

1. Channels C

D

0

0



alternate procedures below are used.

May be inoperative provided procedures do not require its use.

1. PLACARD

A. Put a SELCAL SYSTEM CHANNELS INOPERATIVE placard on the center pedestal.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Manual frequency selection to be made and cross-checked



Airplane: CL 601


COMMUNICATIONS

System & Item 1

Sequence Numbers

2 Number Installed

1

1


23−21−2 Satellite Communications D (SATCOM) System

D

0

0


(O) May be inoperative provided procedures below are used.

May be inoperative provided routine procedures do not require its use.

1. PLACARD

A. Put a SATCOM SYSTEMS INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Two HF must be operative.



Airplane: CL 601


COMMUNICATIONS

System & Item 1

Sequence Numbers

2 Number Installed

1


23−31−1 Passenger Address (PA) System

1. Passenger B Configuration

0



a) Alternate, normal and emergency procedures are/or operating restrictions below are used,

b) Flight Compartment/Cabin Interphone System and aural alerting (chime) operates normally.

NOTE: Any station function(s) that operates normally may be used

1. PLACARD

A. Put a PASSENGER ADDRESS SYSTEM INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. A crew member will orally brief the passengers on the items for which he/she would normally use the Passenger Address System.

B. During normal, abnormal or emergency conditions, a crewmember shall face the

passengers from the cockpit and perform such announcements and/or give such instructions as are appropriate to the situation.

C. When crew members are the only occupants of the airplane, flight attendant(s) must be briefed verbally from the flight deck.



Airplane: CL 601


COMMUNICATIONS

System & Item 1

Sequence Numbers

2 Number Installed

1


23−41−1 Crewmember Interphone System

1) Flight Deck B to Cabin, Cabin to Flight Deck Functions

0



a) PA system is verified operative, and can be used as alternate communications link between the flight compartment and the cabin; and

b) Alternate procedures below are used.

1. PLACARD

A. Put a CREW MEMBER INTERPHONE SYSTEM INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. The PIC will brief cabin attendants prior to each departure on operational issues and the need to communicate verbally. During normal, abnormal or emergency conditions, a pilot shall face the flight attendant(s) from the cockpit and perform such announcements and/or give such instructions as are appropriate to the situation.



Airplane: CL 601


COMMUNICATIONS

System & Item 1

Sequence Numbers

2 Number Installed

1

1


23−41−1 Crewmember Interphone System

2) Flight Deck to Ground C

D

0 0


(M)(O) May be inoperative provided alternate procedures below are used. May be inoperative provided procedure do not require its use

1. PLACARD

A. Put a CREW MEMBER INTERPHONE SYSTEM INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. If a system failure is accompanied by static noise, do as follows:

(1) Disconnect and stow the connector from the affected interphone unit.

(2) Put a FLIGHT DECK TO GROUND COMMUNICATION IS INOPERATIVE placard on the affected interphone control panel.

3. OPERATIONS (O)

A. Before departure brief ground crew and use standard hand signals as alternate communication procedures between the flight deck and ground. On arrival notify handling agent to ensure ground crew are aware that standard and signals will be used.



Airplane: CL 601


COMMUNICATIONS

System & Item 1

Sequence Numbers

2 Number Installed

2


23−50−1 Cockpit Speakers C

0


One or both may be inoperative provided:

a) Aural alerts, messages and other communications which are normally routed through speakers are audible through the headsets.

b) Headsets are installed and used by each person on flight compartment duty, and

c) Spare headset is available in flight compartment.

1. PLACARD

A. Put a COCKPIT SPEAKERS INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601


COMMUNICATIONS

System & Item 1

Sequence Numbers

2 Number Installed

1


23−50−2 Cabin Alerting System (Chime/Light)

1. Flight Deck Call Light B

0


May be inoperative provided the flight deck chime is operative.

NOTE: Flight deck chime must always be operative.

1. PLACARD

A. Put a FLIGHT DECK CALL LIGHT INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601


COMMUNICATIONS

System & Item 1

Sequence Numbers

2 Number Installed

1



2. Flight Attendant / B Cabin Call Lights

0



a) PA System is operative, and

b) Affected light is not used for Lavatory Smoke Detector Alerting, and

c) Alternate procedures below are used for contacting flight attendants.

1. PLACARD

A. Put a FLIGHT ATTENDANT / CABIN CALL LIGHTS INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Pilots must use the crew member interphone system or PA to contact flight attendants.



Airplane: CL 601


COMMUNICATIONS

System & Item 1

Sequence Numbers

2 Number Installed

1



3. Flight Attendant B Cabin Chimes

0



a) PA System is operative, and

b) Affected Chime is not used for Lavatory Smoke Detector Alerting, and

c) Alternate procedures below are used for contacting flight attendants.

1. PLACARD

A. Put a FLIGHT ATTENDANT / CABIN CHIMES INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Pilots must use the crew member interphone system or PA to contact flight attendants.



Airplane: CL 601


COMMUNICATIONS

System & Item 1

Sequence Numbers

2 Number Installed

1


23−50−4 Lavatory Speakers C

0



1. PLACARD

A. Put a LAVATORY SPEAKERS INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. A crewmember will personally check to see if the lavatory with the inoperative speaker is vacant. If not, advise the person concerning the announcements.



Airplane: CL 601


COMMUNICATIONS

System & Item 1

Sequence Numbers

2 Number Installed

2


23−51−1 Headset Boom Microphones

A

0


May be inoperative provided; a) Associated hand microphone is

installed and operates normally, and

b) repairs are made within three flight days.

1. PLACARD

A. Put a HEADSET BOOM MICROPHONE INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601


COMMUNICATIONS

System & Item 1

Sequence Numbers

2 Number Installed

2


23−51−2 Flight Deck Hand Microphones C

0



a) Associated boom microphone operates normally, and

b) Each (Control Wheel) Press−To−Talk Switch is operative.

1. PLACARD

A. Put a FLIGHT DECK HAND MICROPHONES INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601


COMMUNICATIONS

System & Item 1


2


23 COMMUNICATIONS

23−51−3 Press−To−Talk (PTT) C Switches (Control Wheel)

0



a) Switch(es) are not stuck in the transmit position, and

b) Flight Deck Hand Microphone on affected side is operative.

1. PLACARD

A. Put a PRESS−TO−TALK SWITCHES INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601


COMMUNICATIONS

System & Item 1

Sequence Numbers

2 Number Installed

2

2


23−51−5 Headsets Earphones/Headphones C

a) Active Noise Cancelling/ D Reduction Function

1

0


May be inoperative provided associated flight deck speaker operates normally

May be inoperative provided normal audio function of headset is operative.

1. PLACARD

A. Put a HEADSET EARPHONES/HEADPHONES INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601


COMMUNICATIONS

System & Item 1

Sequence Numbers

2 Number Installed

1


23−71−1 Cockpit Voice Recorder (CVR) System

1. Flight Data Recorder A (FDR) Installed

0


(M) May be inoperative provided,

a) Flight Data Recorder (FDR) operates normally; and

b) Repairs are made within three flight days

1. PLACARD

A. Put a COCKPIT VOICE RECORDER SYSTEM INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Verify Flight Data Recorder (FDR) operative before start.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601


COMMUNICATIONS




Airplane: CL 601


ELECTRICAL POWER

System & Item 1


1


24 ELECTRICAL POWER

24−22−1 Auxiliary Power Unit (APU) AC Loadmeter

2. Airplane with IDG P/Ns C 720845

0


(M) May be inoperative provided:

a) Main generator with IDG#2 must have more than 150 operation hours

b) APU generator is not used, and

c) APU generator switch is selected to OFF/RESET.

1. PLACARD

A. Put an APU AC LOADMETER INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Check installation records to ensure that if serviceable IDG#2 has achieved an operational life in excess of 150 operating hours.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601


ELECTRICAL POWER

System & Item 1


1


24 ELECTRICAL POWER

24−22−2 Auxiliary Power Unit (APU) AC Generator System

1) Airplane with IDG P/Ns C 720845

0



a) RH main generator with IDG P/N 720845 must have more than 150 operation hours

1. PLACARD

A. Put an APU AC GENERATOR INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Check installation records to ensure that the serviceable RH main generator with IDG P/N 720845 has achieved an operational life in excess of 150 operating hours.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601


ELECTRICAL POWER

System & Item 1

Sequence Numbers

2 Number Installed

1

3 Number Required for Dispatch 24 ELECTRICAL POWER

24−23−1 Air Driven Generator C (ADG) Auto−Deployment System

0


(M) May be inoperative provided the Auto-Deployment System is deactivated.

1. PLACARD

A. Put an AIR DRIVEN GENERATOR INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Deactivate the Air Driven Generator Auto Deployment System as follows:

(1) Open and collar the circuit breakers that follow:

CB PANEL

CB NO.

NAME

ZONE

CBP−A 54 ADG DEP SENSE 221

CBP−B 210 ADG DEP SENSE 222

CBP−B 283 ADG AUTO DEP CONT 222

CBP−E 395 ADG DEP CONT 311

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601


ELECTRICAL POWER


2 Number Installed

1


24 ELECTRICAL POWER

24−30−3 APU Start Battery D

0


1. PLACARD

A. Put an APU START BATTERY INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601


ELECTRICAL POWER

System & Item 1

Sequence Numbers

2 Number Installed

1


24−30−5 Battery Ammeter D

0


1. PLACARD

A. Put a BATTERY AMMETER INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601


ELECTRICAL POWER

System & Item 1


3


24 ELECTRICAL POWER

24−31−1 TRU Cooling Fan

C

1


(M) One or two may be inoperative

provided:

a) ESS TRU Cooling Fan is operative, and

b) Forward equipment doors are opened for stationary ground operations when OAT is >30°C.

1. PLACARD

A. Put a TRU COOLING FANS INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. During ground operation, do the steps that follow:

(1) Open the forward equipment doors 211AL and 212AR if the temperature is greater than 30°C (86°F).

(2) Make sure that ESS TRU cooling fan is operative.

(3) Immediately prior to dispatch, close the forward equipment doors 211AL and 212AR.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601


ELECTRICAL POWER

System & Item 1

Sequence Numbers

2 Number Installed

1


24−32−5 Battery Temperature D Monitors

0


1. PLACARD

A. Put a BATTERY TEMPERATURE MONITORS INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601


ELECTRICAL POWER

System & Item 1

Sequence Numbers

2 Number Installed

1


24−41−1 AC External Power C System

0


1. PLACARD

A. Put an AC EXTERNAL POWER SYSTEM INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601


ELECTRICAL POWER

System & Item 1

Sequence Numbers

2 Number Installed

1


24−42−1 DC External Power C System

0


1. PLACARD

A. Put a DC EXTERNAL POWER SYSTEM INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601


ELECTRICAL POWER




Airplane: CL 601


EQUIPMENT/FURNISHINGS

System & Item 1

Sequence Numbers

2 Number Installed

2


25 EQUIPMENT/FURNISHINGS

25−11−1 Pilot Seats

1. Lumbar Support C

0



a) The lumbar support position is at the lowest position, and

b) Seat is acceptable to affected crewmember.

1. PLACARD

A. Put a PILOT SEATS INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601



System & Item 1

Sequence Numbers

2 Number Installed

4

3 Number Required for Dispatch 25 EQUIPMENT/FURNISHINGS


2. Arm Rests C

0


(M) May be inoperative or missing

provided:

a) Affected arm rest is secured in the upright position,

b) Egress is not impaired, and

c) Seat is acceptable to affected crewmember.

1. PLACARD

A. Put a PILOT SEATS ARM RESTS INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Secure the affected armrests in the upright position.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601



System & Item 1

Sequence Numbers

2 Number Installed

2



3. Height Adjustments B

0



a) Seat is secured in vertical position acceptable to affected crewmember,

b) Fore/Aft Adjustment is verified operative, and

c) Egress is not impaired.

1. PLACARD

A. Put a PILOT SEATS HEIGHT ADJUSTMENTS INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. With the height adjustment inoperative, do as follows:

(1) Secure the affected seat(s) in a vertical position acceptable to the affected crewmember(s).

(2) Use the fore/aft adjustments to make sure that the seat(s) go forward and aft.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601



System & Item 1

Sequence Numbers

2 Number Installed

2



4. Fore/Aft Adjustments B

0



a) Seat is secured in fore/aft position acceptable to affected crewmember,

b) Height Adjustment is verified operative, and

c) Egress is not impaired.

1. PLACARD

A. Put a PILOT SEATS FORE/AFT ADJUSTMENTS INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. With the fore/aft adjustment inoperative, do as follows:

(1) Secure the affected seat(s) in a fore/aft position acceptable to the affected crewmember(s).

(2) Use the height adjustments to make sure that the seat(s) go up and down.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601



System & Item 1

Sequence Numbers

2 Number Installed

2



5. Recline Adjustments B

0


(M) May be inoperative provided

backrest is secured in a position acceptable to affected crewmember.

1. PLACARD

A. Put a PILOT SEATS RECLINE ADJUSTMENTS INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Secure the affected backrest(s) in a position acceptable to the affected crewmember(s).

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601



System & Item 1

Sequence Numbers

2 Number Installed

2



6. Thigh Supports C

0


May be inoperative provided seat is

acceptable to affected crewmember.

1. PLACARD


2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601



System & Item 1

Sequence Numbers

2 Number Installed

2



7. Seat Belt Inertia Reel C

0


May be inoperative in the rearward

position (locked position).

1. PLACARD


2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601



System & Item 1

Sequence Numbers

2 Number Installed

2


25−11−2 Cockpit Sunvisors C

0


May be inoperative or missing provided there are no visual restrictions to crewmembers.

1. PLACARD

A. Put a COCKPIT SUNVISORS INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601



System & Item 1

Sequence Numbers

2 Number Installed

1

1


25−12−1 Primary Observer Seat A (including associated equipment)

A

0

0


May be inoperative provided;

a) a passenger seat in passenger cabin is made available to any Inspector for performance of official duties; and

b) repairs are made within two flight days


a) Required minimum safety equipment (safety belt and oxygen) is available to any Inspector for performance of official duties, and

b) Seat is acceptable to the Inspector for performance of official duties, and

c) repairs are made within two flight days

NOTE 1: These provisos are intended to provide for occupancy of the above seat by an Inspector when minimum safety equipment (oxygen and safety belt) is functional and the Inspector determines the conditions to be acceptable.

NOTE 2:Pilot-in-command will determine if minimum safety equipment is functional for other persons authorized to occupy the observer seat.

NOTE 3: Associated equipment also includes shoulder harness, audio control panel, microphone, headset, lights, etc.

1. PLACARD

A. Put an OBSERVER SEAT INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601



System & Item 1

Sequence Numbers

2 Number Installed

9


25−20−1 Passenger Seats D

0



a) Seat does not block an emergency exit,

b) Seat does not restrict any passenger from access to the main aisle, and

c) Affected seat(s) is not used and is blocked and placarded “DO NOT OCCUPY”.

NOTE 1: A seat with an inoperative seat belt and/or shoulder harness is considered inoperative.

NOTE 2: Inoperative seats do not affect required number of flight attendants

NOTE 3: Affected seat(s) may include the seat(s) behind and/or adjacent outboard seats.

1. PLACARD

A. Put a PASSENGER SEATS INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Secure the affected seat in the upright position.

B. Put a “DO NOT OCCUPY” placard on affected seat.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601



System & Item 1

Sequence Numbers

2 Number Installed

6


25−20−1 Passenger Seats

1. Recline Mechanism C

0


(M) May be inoperative provided the

seat is secured in the full upright position.

1. PLACARD


2. MAINTENANCE (M)

A. Make the unserviceable seat safe as follows:

(1) Secure the unserviceable seat in the upright position.

(2) Put the seat in a position that does not cause a blockage of the exits.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601



System & Item 1

Sequence Numbers

2 Number Installed

6



25−20−1 Passenger Seats

3. Track/Swivel D Mechanism

0


(M) May be inoperative and seat

occupied provided the seat is secured in the normal take−off position.

1. PLACARD


2. MAINTENANCE (M)

A. Secure the affected seat in the normal take-off position.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601



System & Item 1

Sequence Numbers

2 Number Installed

3



25−20−4 Divan Seat Berthing D Belt

0


May be inoperative or missing provided divan seat is not used for berthing.

1. PLACARD

A. Put a DIVAN SEAT BERTHING BELT INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Not required



Airplane: CL 601



System & Item 1

Sequence Numbers

2 Number Installed

11


25−20−5 Cabin Gasper Vents D

0


1. PLACARD

A. Put a CABIN GASPER VENTS INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601



System & Item 1

Sequence Numbers

2 Number Installed

4


25−29−1 Cabin Power Outlet D

0

4

(M)

Remarks or Exceptions

1. PLACARD

A. Put a POWER OUTLET INOPERATIVE placard on the affected cabin power outlet(s).

2. MAINTENANCE (M)

A. Open and tag the applicable circuit breaker.

B. Put a POWER OUTLET INOPERATIVE placard on the affected cabin power outlet(s).

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601



System & Item 1

Sequence Numbers

2 Number Installed

37

37


25−30−1 Overhead Storage C Bin(s)/Cabin and Galley Storage Compartments/Closets

C

0

0



a) Procedures below are used to secure the affected bin, compartment, or closet in the closed position,

b) Affected bin, compartment, or closet is prominently placarded DO NOT USE,

c) Any emergency equipment located in the affected compartment is considered inoperative, and

d) Affected bin, compartment or closet is not used for storage of any item(s) except for those permanently affixed.

NOTE An inoperative lid/door latch renders the door inoperative.

(M)(O) May be inoperative provided:

a) For non-retractable doors, affected door is removed,

b) For retractable doors, affected door is removed or secured in the retracted (fully open) position,

c) Affected bin, compartment or closet is not used for storage of any items, except those permanently affixed,

d) Affected bin, compartment or closet is prominently placarded DO NOT USE,

e) Procedures below are used to alert crew members and passengers of inoperative bins, compartments or closets and

f) Passengers are briefed that affected bin, compartment or closet is not used.



Airplane: CL 601



System & Item 1

Sequence Numbers

2 Number Installed


25−30−1 Overhead Storage Bin(s)/Cabin and Galley Storage Compartments/Closets (Cont)


NOTE 1 : For overhead bins, if no partitions are installed, the entire overhead bin is considered inoperative.

NOTE 2 : Any emergency equipment located in the associated compartment (permanently affixed) is available for use.

1. PLACARD

A. Put an OVERHEAD STORAGE BINS INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Put a DO NOT USE placard on the affected bin, compartment or closet.

B. Remove loose items from affected bin, compartment or closet

C. Use tape to secure the bin, compartment or closet if lid/latch is inoperative. Where permanently affixed emergency equipment is stored in the affected bin, compartment or closet a minimal amount of securing tape should be used

D. For non-retractable doors, affected door is removed

E. For retractable doors, remove affected door or secure in the fully open position.

3. OPERATIONS (O)

A. PIC to brief all crew on the location of inoperative bin, compartment or closet.

B. PIC to brief all crew on the type and availability of any emergency equipment located in the affected bin, compartment or closet

C. PIC to ensure all passengers are briefed that the affected bin, compartment or closet is not used



Airplane: CL 601



System & Item 1


1

1


24. EQUIPMENT/FURNISHINGS

25−50−1 Cargo Restraint A Systems

C

0

0


(M) May be inoperative or missing provided; a) Acceptable cargo loading limits from

an approved source such as the airplane weight and balance document are observed;

b) Repairs are made prior to the completion of the next heavy maintenance visit.

May be inoperative or missing provided baggage compartment remains empty.

1. PLACARD

A. Put a CARGO RESTRAINT SYSTEMS INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Cargo must be restrained observing the current airplane weight & balance sheet.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601



System & Item 1

Sequence Numbers

2 Number Installed

12

1


25−60−1 Flotation Equipment (Crew and Passenger)

1) Life Vests D

2) Life Rafts D

0

0


When flying over water and beyond gliding distance from land suitable for an emergency landing, a life preserver equipped with an approved survivor locator light is required for each occupant of the airplane.

Except for extended flight over water operations, may be inoperative or missing

1. PLACARD

A. Put a FLOTATION EQUIPMENT INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601



System & Item 1

Sequence Numbers

2 Number Installed

1


25−60−2 Emergency Locator Transmitter (ELT)

1) Fixed ELT A

0


(M)(O) May be inoperative provided;

a) System is deactivated, and

b) Repairs are made within 90 days; and

c) Survival ELT must be on board for all flights.

1. PLACARD

A. Put an ELT INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Turn switch off at unit located at top left aft fuselage (between frames 759 & 794).

3. OPERATIONS (O)

A. An operative Survival ELT must be carried by a crew member for all flights.



Airplane: CL 601



System & Item 1

Sequence Numbers

2 Number Installed

1


25−60−3 Passenger Convenience Items

0


Passenger Convenience Items, as expressed in this MEL, are those related to passenger convenience, comfort or entertainment such as, but not limited to, galley equipment, movie equipment, ashtrays, stereo equipment, overhead reading lamps.

Items addressed elsewhere in this document are not included under this item.

NOTE 1: Lavatory door ashtrays are not considered convenience items.

NOTE 2: Gallery Equipment

restraining devices such as latches, etc. must be serviceable or compartment must not be used for storage and placarded “INOPERATIVE DO NOT USE”.

NOTE 3: Audio or audio−visual

entertainment equipment which is used as the sole means of providing safety briefings and demonstrations is not considered as passenger convenience items.

1. PLACARD

A. Put a PASSENGER CONVENIENCE ITEMS INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Coffee maker – pull and secure circuit breaker(s).

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601



System & Item 1

Sequence Numbers

2 Number Installed

1


25−60−4 Airshow Cockpit Monitor D System

0

4

(M)

Remarks or Exceptions

May be inoperative provided system is deactivated.

1. PLACARD

A. Put an AIRSHOW COCKPIT MONITOR SYSTEM INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Pull and collar circuit breaker marked “Cabin Display”.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601



System & Item 1

Sequence Numbers

2 Number Installed

2



25−60−6 Flashlights / Flashlight Holders

1. Flashlights C

0


(O) May be inoperative or missing

provided affected crewmember has a flashlight or equivalent characteristics readily available.

1. PLACARD

A. Put a FLASHLIGHTS INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. For an inoperative or missing flashlight, do as follows:

(1) The flight crew shall verify that any flashlight to be used in lieu of an inoperative or missing flashlight is of equivalent characteristics (ie, having a ruggedized, electrically insulated exterior, uses two “D” size batteries, and has a shatter-resistant lens and reflector) that is in good condition, has fresh batteries, and is functioning properly. This flashlight is not to be stowed in a passenger-seat back pocket.

(2) For rechargeable flashlights, the crew must verify the flashlight operates normally, and that the batteries have been freshly charged before the first flight of the day.



Airplane: CL 601



System & Item 1

Sequence Numbers

2 Number Installed

2


25−60−6 Flashlights / Flashlight Holders

2. Holders C

0


(O) May be inoperative or missing

provided alternate stowage provisions are provided.

1. PLACARD

A. Put a FLASHLIGHT HOLDERS INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. For an inoperative or missing flashlight holder, do as follows:

(1) A suitable flashlight stowage location must be identified in lieu of the inoperative or missing flashlight holder. A passenger-seat back pocket is not to be used for the stowage of the flight attendant’s flashlight. The stowage location selected must be immediately accessible to the flight attendant assigned to the seat with the inoperative flashlight holder.

(2) For rechargeable flashlights, the crew must verify the flashlight operates normally and that the batteries have been freshly charged before the first flight of the day.



Airplane: CL 601



System & Item 1

Sequence Numbers

2 Number Installed

2



25−60−8 “FASTEN SEAT BELT C WHILE SEATED” sign on placard

0


One or more signs or placards may be illegible or missing provided a legible sign or placard is visible from each occupied passenger seat.

1. PLACARD

A. Put a “FASTEN SEAT BELT WHILE SEATED” SIGN INOPERATIVE placard on the instrument panel.

B. Put a legible sign or placard next to the inoperative sign and ensure it is visible from each occupied passenger seat.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601



System & Item 1

Sequence Numbers

2 Number Installed

1


25−60−9 First Aid Kit

3. First Aid Kit Seal A

0


(O) The seal affixed on the exterior of the first aid kit may be missing or inoperative provided:

a) The first aid kit is resealed in a manner that will identify it as a unit that cannot be mistaken for a fully serviceable unit; and,

b) Replacements are made within one flight day.

1. PLACARD

A. Put a FIRST AID KIT INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. A pilot must brief all crew members on the missing or broken seal, and designate one crew member to perform an inventory to determine the content status prior to departure.



Airplane: CL 601



System & Item 1

Sequence Numbers

2 Number Installed

1


25−70−1 Galley Waste C Receptacles Access Doors/Covers

0


(M) (O) May be inoperative provided:

a) The container is empty and the access is secured to prevent waste introduction into the compartment, and

b) Procedures below are used to ensure that sufficient galley waste receptacles are available to accommodate all waste that may be generated on a flight.

1. PLACARD

A. Put a GALLEY WASTE RECEPTACLES ACCESS DOORS INOPERATIVE placard on the instrument panel.

B. Put a DO NOT USE placard on the inoperative receptacle door.

2. MAINTENANCE (M)

A. Safety the galley waste receptacles access doors/covers as follows:

(1) Make sure that the waste receptacle container is empty.

(2) Safety the container access closed.

(3) Make sure that sufficient alternate receptacles are available to accommodate all waste generated on a flight.

3. OPERATIONS (O)

A. PIC to brief flight attendant(s) of inoperative receptacle and need to accommodate all waste in the available receptacles by minimizing bulky items before disposal and judicious use of those receptacles.



Airplane: CL 601



System & Item 1

Sequence Numbers

2 Number Installed

1


25−70−2 Exterior Lavatory Door Ashtray

A

0


May be missing or inoperative for 10 days.

.

1. PLACARD

A. Put an EXTERIOR LAVATORY DOOR ASHTRAY INOPERATIVE placard on the instrument panel.

B. Put an INOPERATIVE placard on the ashtray.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601


FIRE PROTECTION

System & Item 1

Sequence Numbers

2 Number Installed

1

1

3 Number Required for Dispatch 26 FIRE PROTECTION

26−10−1 APU Fire Detection System

C

C

0

0



a) RH main generator (IDG#2) must have more than 150 operating hours, and

b) APU is not used.


a) RH main generator (IDG#2) must have more than 150 operating hours,

b) APU is used on ground for engine start only,

c) APU is pneumatically loaded only,

d) APU enclosure access panels are opened,

e) APU is visually monitored,

f) A functioning portable fire extinguisher is available in the area near the APU,

g) Total APU operating time shall not exceed five minutes, and

h) APU is not used after start.

1. PLACARD

A. Put an APU FIRE DETECTION SYSTEM INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. For an APU fire detection system inoperative and to consider the APU inoperative, do as follows:

(1) Check installation records to ensure that the serviceable RH main generator

(IDG#2) has achieved an operational life in excess of 150 operating hours.



Airplane: CL 601


FIRE PROTECTION

(2) Deactivate the APU as follows:

Open and tag the applicable

circuit breaker(s) that

follow: CB

PANEL

CB NO. NAME ZONE

CBP−A 63 APU CONT 221

CBP−A 154 APU − CONT 221

B. For an APU fire detection system inoperative and to use the APU for engine start, do as follows:

(1) Check installation records to ensure that the serviceable IDG#2 has achieved an

operational life in excess of 150 operating hours. (2) Make sure that the applicable circuit breakers for APU start are closed. (3) Open the APU enclosure access panel. (4) Start the APU and let it run for a maximum of five minutes. (5) While the APU is operating on the ground, qualified personnel must visually

monitor the APU for condition (no smoke or fire condition). (6) Qualified personnel must be readily available to communicate with the flight crew

using a suitable headset in the event of a required shutdown. (7) Qualified personnel must be readily available with portable fire extinguishers. (8) Start the engine using the APU.

(9) Stop the APU.


(a) Open and tag the applicable circuit breaker(s) that follow:




(11) Close the APU enclosure access panel.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601


FIRE PROTECTION

System & Item 1

Sequence Numbers

2 Number Installed

1


26−10−2 Lavatory Smoke C Detection Systems

0


(M))O) May be inoperative provided:

a) Lavatory waste receptacle is empty,

b) Lavatory door is locked closed and placarded INOPERATIVE DO NOT ENTER, and

c) Lavatory is used only by crewmembers.

NOTE: These provisos are not intended to prohibit lavatory use or inspections by crew members.

1. PLACARD

A. Put an LAVATORY SMOKE DETECTION SYSTEM INOPERATIVE on the instrument panel.

2. MAINTENANCE (M)

A. Ensure lavatory waste receptacle is empty before departure.

B. Place a DO NOT ENTER placard on the lavatory door.

3. OPERATIONS (O)

A. Flight attendant(s) must inspect the lavatory periodically and re-lock the door.

B. Make sure that the lavatory with the unserviceable smoke detector system is made safe as follows:

i. For each lavatory, the lavatory smoke detector system may be inoperative provided:

(a) The lavatory waste receptacle is empty.

(b) The lavatory door is locked and is not to be used for any purpose.

C. The PIC is to brief crew members on the inoperative lavatory smoke detection system(s) and the above requirements.



Airplane: CL 601


FIRE PROTECTION

System & Item 1

Sequence Numbers

2 Number Installed

1


26 FIRE PROTECTION

26−10−3 Baggage Compartment C Fire Detection / Suppression System

0


(O) May be inoperative provided;

a) the baggage compartment remains empty, or

b) contains only empty cargo handling equipment and/or Fly Away kits..

1. PLACARD

A. Put a BAGGAGE COMPARTMENT FIRE DETECTION SYSTEM INOPERATIVE placard on the instrument panel.

B. Put a BAGGAGE COMPARTMENT NOT TO BE USED placard in the baggage compartment.

2. MAINTENANCE (M)

A. Not required

3. OPERATIONS (O)

A. The Fly Away Kit may be carried when the suppression system is inoperative provided it contains only non-flammable items such as spare parts and tools, spare wheel and tyre assemblies, jacking pads and spare bulbs. Oil and fuel additives must not be carried when suppression system is inoperative.



Airplane: CL 601


FIRE PROTECTION

System & Item 1

Sequence Numbers

2 Number Installed

1


26 FIRE PROTECTION

26−14−1 Main Landing Gear Bay A Overheat Detection System

0



a) Brakes are inspected prior to each flight,

b) After take−off the landing gear is left extended for ten minutes, and

c) Take−off is not conducted in icing conditions and/or contaminated runways, and

d) Repairs are made within one flight day.

NOTE: In case of engine failure after V1, performance is the prime consideration and the landing gear should be retracted normally until performance penalty with gear down is not a problem.

1. PLACARD

A. Put a MLG BAY OVERHEAT DETECTION SYSTEM INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

Before Flight:

A. Do the visual inspection of the brakes as follows:

(1) Inspect the brakes for condition, leakage, and safety of installation.

WARNING: BE CAREFUL WHEN YOU TOUCH THE BRAKES. THE BRAKES MAY BE HOT. IF YOU DO NOT DO THIS, YOU CAN CAUSE INJURY TO PERSONS.

(2) The brakes must be cool to the touch.

3. OPERATIONS (O)

After Take-Off:

A. Leave the landing gear extended for 10 minutes after take-off.



Airplane: CL 601


FIRE PROTECTION

B. PIC to determine after take-off segment climb performance from the Airplane Flight Manual – Performance meets the obstacle clearance requirements for the departure runway.

C. The PIC to include in the before departure briefing that performance is the prime consideration after take-off and in case of engine failure after V1 the landing gear should be retracted normally until performance penalty with gear down is not a problem.



Airplane: CL 601


FIRE PROTECTION

System & Item 1

Sequence Numbers

2 Number Installed

1

1


26 FIRE PROTECTION

26−20−1 Lavatory Fire C Extinguisher System

C

0

0


(O) May be inoperative provided the Lavatory Smoke Detection System is operative.

(M)(O) May be inoperative in the lavatory provided:

a) Lavatory waste receptacle is empty,

b) Lavatory door is locked closed and placarded “INOPERATIVE − DO NOT ENTER”, and

c) Lavatory is not used for any purpose.

NOTE 1: These provisos are not

intended to preclude lavatory inspections by crewmembers.

1. PLACARD

A. Put a LAVATORY FIRE EXTINGUISHER SYSTEM INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Put a “INOPERATIVE – DO NOT ENTER” placard on the lavatory door.

3. OPERATIONS (O)

A. Ensure there are no current log entries or deferrals related to the Lavatory Smoke Detection System. PIC to brief flight attendant(s) on requirements at section 4 above.



Airplane: CL 601


FIRE PROTECTION

System & Item 1

Sequence Numbers

2 Number Installed

1


26 FIRE PROTECTION

26−20−3 Baggage Compartment C Smoke Detection System

0


May be inoperative provided the compartment is empty.

NOTE: For ballast purposes, use of bags (made of glass fibre or kevlar) or sand or ingots of non−magnetic metals (such as lead) is acceptable.

1. PLACARD

A. Put a BAGGAGE COMPARTMENT SMOKE DETECTION SYSTEM INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601


FIRE PROTECTION


2 Number Installed

1


26 FIRE PROTECTION

26−20−5 APU FIREX Bottle Low Pressure Switch

C

0



a) RH main generator (IDG#2) must have more than 150 operating hours,

b) The APU is used for ground operations only,

c) Firex bottle charge pressure is visually verified at bottle pressure gauge prior to each APU start,

d) APU fire detection system is operative

e) APU enclosure access panels are kept closed, and

f) APU is not used after engine start.

1. PLACARD

A. Put an APU FIREX BOTTLE LOW PRESSURE SWITCH INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. For an APU firex bottle low pressure switch inoperative and to use the APU on the ground, do as follows:

(1) Make sure the APU enclosure access panels are kept closed.

(2) Check installation records to ensure that the serviceable RH main generator (IDG#2) has achieved an operational life in excess of 150 operating hours.

(3) Before starting the APU, do a visual check of the APU firex bottle pressure gauge and make sure the pressure is in an acceptable range.

(4) Do the operational test of the APU fire detection system (refer to AIRPLANE

MAINTENANCE MANUAL, Chapter 26−10−02).



Airplane: CL 601


FIRE PROTECTION

(5) Make sure that the applicable circuit breakers for APU start are closed

(6) Start the APU.

(7) Qualified personnel must be readily available to communicate with the flight crew using a suitable headset in the event of a required shutdown.

(8) As soon as the use of the APU is no longer required stop the APU.


(a) Open and tag the applicable circuit breaker(s) that follow:




3. OPERATIONS (O)

A. In the event of an APU fire when the APU is started on the ground:

APU Fire Detected:

a) APU FIRE PUSH switch/light comes on ........................................................Push

b) BOTTLE ARMED PUSH TO DISCH .............................................. Push to extinguish the fire.

NOTE: The BOTTLE ARMED PUSH TO DISCH switch/light does not come on



Airplane: CL 601


FIRE PROTECTION

System & Item 1

Sequence Numbers

2 Number Installed

3


26−25−1 Portable Fire D Extinguishers

2


(M) (O) May be inoperative or missing provided:

a) The fire extinguisher is tagged inoperative, removed from the installed location and placed out of sight so it cannot be mistaken for a functional unit, and,

b) Required distribution of one in cockpit and one in cabin is maintained.

1. PLACARD

A. Put an INOPERATIVE placard on the fire extinguisher and secure out of sight.

2. MAINTENANCE (M)

A. Put an UNSERVICEABLE TAG on the unserviceable portable fire extinguisher and stow it where it cannot be used, until it can be removed from the airframe at the next available maintenance base.

B. Make sure that the required distribution of serviceable extinguishers is maintained throughout the airplane.

3. OPERATIONS (O)

A. The PIC must brief all crew members of the location of the remaining operative portable fire extinguishers.



Airplane: CL 601


FIRE PROTECTION




Airplane: CL 601


FLIGHT CONTROLS

System & Item 1

Sequence Numbers

2 Number Installed

7

3 Number Required for Dispatch 27 FLIGHT CONTROLS

27−05−1 Control Surface Position Indicators

2. FLT SPLRL/R C AILERON L/R, ELEVATOR L/R RUDDER)

0


(M)(O) Any or all indicators may be

inoperative provided; a) affected indicator is covered; and

b) Affected Control Surface is visually checked for full, free and correct movement prior to each flight.

1. PLACARD

A. Put a CONTROL SURFACE POSITION INDICATORS INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. If at least one indicator is operative, do not deactivate the circuit breakers. Put a placard on the inoperative indicator(s).

B. If all indicators are inoperative, deactivate the Control Surface Position Indicators by

opening and collaring the circuit breakers that follow:


CBP−A 10 R SURF POSN 221

CBP−C 349 L SURF POSN 221

3. OPERATIONS (O)

Before Flight:

A. Apply external AC power.

B. Pressurize hydraulic systems 1, 2 and 3.

C. Check the flight control surfaces as follows:

NOTE: Two persons are required for the next steps, one in the flight compartment and the other to view the control surface movement.

(1) Check the flight spoiler movement as follows:



Airplane: CL 601


FLIGHT CONTROLS

(a) Set spoiler control lever to 0 position.

(b) Check that the LEFT and RIGHT flight spoiler lights on the center pedestal are out.

(c) Move spoiler control lever to first detent and check that the flight spoilers do not move.

(d) Set spoiler control lever gradually to ¼, ½, ¾, and MAX positions. At each position make sure that flight spoilers extend smoothly and freely.

(e) Check that the FLIGHT SPOILERS LEFT and RIGHT lights on center pedestal come on when spoiler control lever is above the ½ position.

(f) Set the spoiler control lever to 0 and make sure that the flight spoilers fully retract.

(g) Check that the LEFT and RIGHT flight spoiler lights on the center pedestal are out.

(2) Check the aileron movement as follows:

(a) Set the aileron trim at neutral.

(b) Turn the control wheel counterclockwise.

(c) Make sure the left aileron control surface moves up and the right aileron control surface moves down.

(d) Bring the control wheel to the neutral position and verify that the aileron surfaces are in the neutral position.

(e) Turn the control wheel full clockwise.

(f) Make sure that the right aileron control surface moves up and the left aileron control surface moves down.

(g) Bring the control wheel to the neutral position and verify that the aileron surfaces are in the neutral position.

(3) Check the elevator movement as follows:

(a) Set control column to the neutral position.

(b) Push the control wheel to the full forward position.

(c) Make sure the elevator control surfaces move to the full down position.

(d) Bring the control column to the neutral position and verify that the elevator surfaces are in the neutral position.

(e) Pull the control wheel to the full aft position.



Airplane: CL 601


FLIGHT CONTROLS

(f) Make sure that the elevator control surfaces move to the full up position.

(g) Bring the control column to the neutral position and verify that the elevator surfaces are in the neutral position.

(4) Check the rudder movement as follows:

(a) Set rudder trim at neutral.

(b) Push the left rudder pedal until the rudder moves fully left.

(c) Make sure that the rudder control surface moves fully left.

(d) Release the rudder pedal and verify that the rudder control surface is in the neutral position.

(e) Push the right rudder pedal until the rudder moves fully right.

(f) Make sure that the rudder control surface moves fully right.

(g) Release the rudder pedal and verify that the rudder control surface is in the neutral position.

D. Release hydraulic systems pressure.

E. Remove external AC power.



Airplane: CL 601


FLIGHT CONTROLS


2 Number Installed

1


27 FLIGHT CONTROLS

27−05−3 Servo Monitor System C

0



a) All Powered Control Units (PCUs) are checked prior to take−off to ensure correct operation using each hydraulic system individually, and

b) Parking Brake SOV is verified open.

1. PLACARD

A. Put a SERVO MONITOR SYSTEM INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

Before Flight:

Check that parking brake shut-off valve is open (refer to AIRPLANE MAINTENANCE MANUAL, Chapter 32−45−31).

3. OPERATIONS (O)

A. With AC power available, and all hydraulic systems unpressurized, do the steps that follow:


(1) Check the aileron movement as follows:

(a) Pressurize hydraulic system No. 3.

(b) Make sure that the aileron trim is at neutral.

(c) Rotate the pilot’s control wheel clockwise until the stops are reached. Visually check that the right aileron is up and the left aileron is down.

(d) Rotate the pilot’s control wheel to the neutral position. Visually check that both aileron surfaces are at the neutral position.

(e) Rotate the pilot’s control wheel counterclockwise until the stops are reached. Visually check that the right aileron is down and the left aileron is up.

(f) Rotate the control wheel to the neutral position. Visually check that both aileron surfaces are at the neutral position.



Airplane: CL 601


FLIGHT CONTROLS

(g) Depressurize hydraulic system No. 3.

(h) Pressurize hydraulic system No. 1.

(i) Pull out and rotate the ROLL DISCON handle.

(j) Rotate the pilot’s control wheel clockwise until the stops are reached. Visually check that the left aileron is down.

(k) Rotate the pilot’s control wheel to the neutral position. Visually check that the left aileron is at the neutral position.

(l) Rotate the pilot’s control wheel counterclockwise until the stops are reached. Visually check that the left aileron is up.

(m) Rotate the pilot’s control wheel to the neutral position. Visually check that the left aileron is at the neutral position.

(n) Depressurize hydraulic system No. 1.

(o) Pressurize hydraulic system No. 2.

(p) Rotate the co−pilot’s control wheel clockwise until the stops are reached. Visually check that the right aileron is up.

(q) Rotate the co−pilot’s control wheel to the neutral position. Visually check that the right aileron is at the neutral position.

(r) Rotate the co−pilot’s control wheel counterclockwise until the stops are reached. Visually check that the right aileron is down.

(s) Rotate the co−pilot’s control wheel to the neutral position. Visually check that the right aileron is at the neutral position.

(t) Rotate and push in the ROLL DISCON handle.

(u) Pressurize hydraulic system No. 1 and No. 3.

(v) Rotate the pilot’s control wheel clockwise until the stops are reached. Visually check that the right aileron is up and the left aileron is down.

(w) Rotate the pilot’s control wheel to the neutral position. Visually check that both aileron surfaces are at the neutral position.

(x) Rotate the pilot’s control wheel counterclockwise until the stops are reached. Visually check that the right aileron is down and the left aileron is up.

(y) Rotate the control wheel to the neutral position. Visually check that both aileron surfaces are at the neutral position.



Airplane: CL 601


FLIGHT CONTROLS

(2) Check the elevator movement as follows:

(a) Keep the hydraulic system No. 3 pressurized and depressurize hydraulic systems No. 1 and No. 2.

(b) Set the control column to the neutral position.

(c) Push the control column forward until the stops are reached. Visually check that both elevator surfaces are down.

(d) Return the control column to the neutral position. Visually check that both elevator surfaces are in the neutral position.

(e) Pull the control column to the rear until the stops are reached. Visually check that both elevator surfaces are up.

(f) Return the control column to the neutral position. visually check that both elevator surfaces are in the neutral position.

(g) Depressurize hydraulic system No. 3.

(h) Pressurize hydraulic system No. 1.

(i) Pull out and rotate the PITCH DISC handle.

(j) Push the pilot’s control column forward until the stops are reached. Visually check that the left elevator is down.

(k) Return the pilot’s control column to the neutral position. Visually check that the left elevator is in the neutral position.

(l) Pull the pilot’s control column to the rear until the stops are reached. Visually check that the left elevator is up.

(m) Return the pilot’s control column to the neutral position. Visually check that the left elevator is in the neutral position.

(n) Depressurize hydraulic system No. 1.

(o) Pressurize hydraulic system No. 2.

(p) Push the co-pilot’s control column forward until the stops are reached. Visually check that the right elevator is down.

(q) Return the co-pilot’s control column to the neutral position. Visually check that the right elevator is in the neutral position.

(r) Pull the co-pilot’s column to the rear until the stops are reached. Visually check that the right elevator is up.



Airplane: CL 601


FLIGHT CONTROLS

(s) Return the co-pilot’s control column to the neutral position. Visually check that the right elevator is in the neutral position.

(t) Rotate and push in the PITCH DISC handle.

(u) Pressurize hydraulic systems No. 1 and No. 3.

(v) Push the pilot’s control column forward until the stops are reached. Visually check that both elevator surfaces are down.

(w) Return the pilot’s control column to the neutral position. Visually check that both elevator surfaces are in the neutral position.

(x) Pull the pilot’s control column to the rear until the stops are reached. Visually check that both elevator surfaces are up.

(y) Return the pilot’s control column to the neutral position. Visually check that both elevator surfaces are in the neutral position.

(3) Check rudder movement as follows:

(a) Keep hydraulic system No. 3 pressurized and depressurize hydraulic systems No. 1 and No. 2.

(b) Make sure that the rudder trim is at neutral.

(c) Push the left rudder pedal until the stop is reached. Visually check that the rudder is fully left.

(d) Return the rudder pedal to the neutral position. Visually check that the rudder is at the neutral position.

(e) Push the right rudder pedal until the stop is reached. Visually check that the rudder is fully right.

(f) Return the rudder pedal to the neutral position. Visually check that the rudder is at the neutral position.

(g) Repeat steps 3 to 6 with hydraulic system No. 1 pressurized and hydraulic systems No. 2 and No. 3 depressurized.

(h) Repeat steps 3 to 6 with hydraulic system No. 2 pressurized and hydraulic systems No. 1 and No. 3 depressurized.



Airplane: CL 601


FLIGHT CONTROLS


2 Number Installed

2


27 FLIGHT CONTROLS

27−05−4 LH/RH Flight Spoiler C Indication (Glareshield)

0



a) Flight Spoiler Control Surface Position Indication is operative,

b) Flight Spoiler Indication on center pedestal is verified operative prior to each flight,

c) Flight Spoilers are verified stowed before take−off, and

d) Flight Spoilers are not used during approach.

1. PLACARD

A. Put a FLIGHT SPOILER INDICATION INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

Before Flight:

A. With AC power available:

NOTE: Two persons are required for the next steps, one in the flight compartment and the other to view the flight spoilers movement.

(1) Pressurize hydraulic systems 1 and 2.

(2) Check flight spoiler movement as follows:

(a) Check that FLIGHT SPOILERS LEFT and RIGHT lights on center pedestal come on with control handle positioned between 1/2 and 3/4.

(b) Retract spoilers and check that lights go out.

(c) Visually check that flight spoilers are fully retracted.



Airplane: CL 601


FLIGHT CONTROLS

System & Item 1

Sequence Numbers

2 Number Installed

1


27−12−1 Aileron Trim System B

0



a) Autopilot is operative,

b) Aileron Trim System is centered, and

c) Main fuel tanks left and right are balanced prior to take−off.

1. PLACARD

A. Put an AILERON TRIM SYSTEM INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601


FLIGHT CONTROLS

System & Item 1

Sequence Numbers

2 Number Installed

2


27−40−1 Trim Indicators C (Ailerons, Rudder)

1


(O) One may be inoperative provided the affected control surface is checked visually as being in the appropriate take−off position prior to each take−off.

1. PLACARD

A. Put a TRIM INDICATORS SYSTEMS INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

Before Flight:

A. Pressurize hydraulic systems 1, 2 and 3.

B. Check the flight control systems as follows:


(1) Check the aileron trim system as follows:

(a) On the center pedestal, hold the AIL TRIM control switch to the left and check the following:

1) Check that both control wheels move counterclockwise.

2) Check that left aileron is up and right aileron is down.

(b) On the center pedestal, hold the AIL TRIM control switch to the right and check the following:

1) Check that both control wheels move clockwise.

2) Check that left aileron is down and right aileron is up.

(c) Operate the trim switches to set ailerons to neutral position. Check that aileron surfaces are in neutral position.

(2) Check the rudder trim system as follows:



Airplane: CL 601


FLIGHT CONTROLS

(a) On the center pedestal, hold the rudder trim switch to the left until maximum left trim is attained.

(b) Make sure that the rudder control surface moves fully left.

(c) On the center pedestal hold the rudder trim switch to the right until maximum right trim is attained.

(d) Make sure that the rudder control surface moves fully right.

(e) Operate the rudder switches to set the rudder to neutral position. Check that rudder surface is in neutral position.



Airplane: CL 601


FLIGHT CONTROLS

System & Item 1

Sequence Numbers

2 Number Installed

2


27−50−1 Flap Power Drive Unit C (PDU) Motors

1



a) Affected motor is deactivated,

b) Operations are conducted in accordance with AFM Supplement 14, Operations with Airplane Systems Inoperative).

NOTE: With only one motor

operational, the flaps will operate at half speed.

1. PLACARD

A. Put a FLAP PDU MOTORS INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Isolate the affected flap motor by opening and collaring the applicable FLAP MOTOR 1 or FLAP MOTOR 2 circuit breaker that follows:

NOTE: With only one motor operational, the flaps will operate at half speed.


CBP−A 20 FLAP MOTOR 1 221

CBP−B 176 FLAP MOTOR 2 222

B. Do operational test of the Flap Power Drive Unit as follows:

Refer to Aircraft Maintenance Manual, Chapter 27−50−21, POWER DRIVE UNIT (PDU), MAINTENANCE PRACTICES.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601


FLIGHT CONTROLS

System & Item 1

Sequence Numbers

2 Number Installed

2


27−52−1 Rudder Pedal C Adjustment Mechanism

0



a) Rudder pedals can be secured in a position acceptable to affected crewmember, and

b) Rudder and brake pedals are checked for full and unrestricted movement at both pilot stations.

NOTE: Full range of operation must be available to the crewmember in seated position.

1. PLACARD

A. Put a RUDDER PEDAL ADJUSTMENT MECHANISM INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. If the pedal adjustment is difficult to move (such as stiff or jammed) do the (O) Operations Procedure only, for any other instance (such as free-wheeling, slipping or a broken shaft), do as follows.

(1) Remove the two screws from the side panel to open the pedal cover.

(2) Make sure that the pedal adjustment link (rod) is not broken.

(a) If it is broken, remove the broken pedal adjustment link (rod), along with any broken parts.

(3) Install the side panel of the pedal cover.

3. OPERATIONS (O)

A. Make sure that the pedal adjustment is in a position that meets the affected pilot’s requirements.

B. Push the pedals and make sure that the pedal adjustment remains in a fixed position. C. Make sure that the pedals travel in a full and unrestricted movement at both pilot

stations as follows.

(1) Pressurize the hydraulic systems 1, 2, and 3.

(2) Push the left rudder pedal to the maximum stops.



Airplane: CL 601


FLIGHT CONTROLS

(3) Push the left brake pedal to the maximum stops.

(4) Release the left rudder pedal.

(5) Release the left brake pedal.

(6) Push the right rudder pedal to the maximum stops.

(7) Push the right brake pedal to the maximum stops.

(8) Release the right rudder pedal.

(9) Release the right brake pedal.

(10) Release the pressure from the hydraulic systems.



Airplane: CL 601


FLIGHT CONTROLS

System & Item 1

Sequence Numbers

2 Number Installed

2


27−60−2 Flight Spoiler Lights C Flashing Feature

0



a) Flight Spoilers are not used below 702 ft AGL,

b) Flight Spoilers are not used when flaps are extended, and

c) All Flight Spoilers indications are operative.

1. PLACARD

A. Put a FLIGHT SPOILER LIGHTS FLASHING FEATURE INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601


FLIGHT CONTROLS




Airplane: CL 601


FUEL

System & Item 1

Sequence Numbers

2 Number Installed

6

3 Number Required for Dispatch 28 FUEL

28−11−1 Water Drain Valves C

4



a) One drain valve at each wing tank, lowest level point is operative,

b) Main Boost Pump drain valves are operative, and

c) There is no evidence of leakage.

1. PLACARD

A. Put a WATER DRAIN VALVES INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601


FUEL

System & Sequence

Item Numbers


1


28 FUEL

0



a) Tail Cone fuel tank refuel / defuel SOVs are verified closed, and

b) Tail cone fuel tank is empty.

28−13−1 Tail Cone Fuel Tank C

System

1. PLACARD

A. Put a TAIL CONE FUEL TANK SYSTEM INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

Before Flight:

A. Make sure that the tail fuel tank is empty.

B. Make sure that the forward and aft Refuel/Defuel Shutoff Valves (SOVs) are in the closed position as follows:

(1) On the Refuel/Defuel control panel, set POWER switch to ON.

(2) Make sure that the TAIL switch is set to OFF and the CL light is illuminated.

(3) Set power switch to OFF.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601


FUEL

System & Item 1

Sequence Numbers

2 Number Installed

2


28−13−3 Turbulator Vanes (Fuel C Jettison Mast, Tail Tank Fuel Systems)

0


(M) One or both turbulator vanes may be damaged or missing provided the;

a) Tail Tank remains empty,

b) Tail Tank Refuel/Defuel SOVs are verified closed.

1. PLACARD

A. Put a TURBULATOR VANES INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

Before Flight:

A. Make sure that the tail fuel tank is empty. Refer to AIRCRAFT MAINTENANCE MANUAL Chapter 12-10-28

B. Pressure refuel the auxiliary fuel tank, refer to AIRCRAFT MAINTENANCE MANUAL, Chapter 12−10−28. Make sure that the tail tank fuel quantity indication on the flight compartment FUEL QUANTITY control panel does not increase.

NOTE: If it is necessary to add fuel to the auxiliary tanks, precaution should be taken

to keep the aircraft CG in safe limits at all times.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601


FUEL

System & Item 1

Sequence Numbers

2 Number Installed

2


28−15−1 Tank Ejectors (Aux B Tank)

1


One may be inoperative provided Aux Tank (and Tail Tank) remain empty.

1. PLACARD

A. Put a TANK EJECTORS INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601


FUEL


2 Number Installed

2


28 FUEL

28−15−2 Crossfeed Shutoff Valves

1. Left to Right, Right to C Left

0


One or both may be inoperative closed provided:

a) Affected Valve is verified CLOSED

b) All Fuel Quantity Indications are operative,

c) Aileron Trim system is operative, and

d) Airplane is operated in accordance with AFM procedures if fuel crossfeed is required.

1. PLACARD

A. Put a CROSSFEED SHUTOFF VALVES INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601


FUEL

System & Item 1

Sequence Numbers

2 Number Installed

2


28−23−1 Fuel (Boost) Pumps

A

1


(M) (O) One may be inoperative provided:

a) Affected fuel (boost) pump is selected OFF and deactivated,

b) If left boost pump is inoperative, APU is operated continuously throughout flight and APU generator is verified operative prior to flight,

c) AFM performance corrections for APU ON are applied,

d) Both fuel feed line check valves are verified operative prior to the first flight,

e) Crossflow (Left to Right, Right to Left) SOVs are operative,

f) Repairs are made within one flight day.

1. PLACARD

A. Put a FUEL BOOST PUMPS INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Deactivate the inoperative fuel boost pump as follows:

(1) Connect external electrical power to the airplane.

(2) Open and collar the affected circuit breaker that follows:


CBP−A 156 LEFT FUEL PUMP 221

OR


CBP−B 239 RIGHT FUEL PUMP 222



Airplane: CL 601


FUEL

(3) On FUEL CONTROL panel, press the PUMP switch/light of the inoperative pump and make sure that the INOP light comes on.

B. If the left boost pump is inoperative, check the APU generator as follows:

(1) Start the APU.

(2) On the center pedestal AC POWER control panel, put the APU generator switch to the ON position. Make sure that electric load is shown on the gauge.

(3) Shut down the APU.

C. Remove the external electrical power from the airplane.

3. OPERATIONS (O)

A. Make sure that both fuel feed line check valves are operative as follows:

WARNING: ABSENCE OF THE “L (R) FUEL LOW PRESS” CAUTION LIGHT DURING THIS CHECK IS AN INDICATION THAT A FUEL FEED CHECK VALVE HAS FAILED IN THE OPEN POSITION, OR THAT A FUEL PRESSURE INDICATION FAULT EXISTS. NO DISPATCH IS ALLOWED.

(1) Start one engine and do the steps that follow:

(a) Press out the operative fuel boost pump switch/light and check for the following:

1) L and R PUMP ON lights are out.

2) L and R PUMP INOP lights are on.

(b) On the FUEL CONTROL panel, check that the LOW PRESS light is on for the non−operating engine.

(c) After two minutes, if the LOW PRESS light is still not displayed for the non−operating engine, do the steps that follow:

1) Dry motor the non−started engine for a maximum of 30 seconds.

2) The applicable fuel LOW PRESS caution message should be on during the dry motoring as the residual fuel pressure is reduced.

(d) On the FUEL CONTROL panel, check that LOW PRESS light is on for the non−operating engine.

(2) Start the second engine and do the steps that follow:

(a) Shutdown the engine that was started first.



Airplane: CL 601


FUEL

(b) Press out the operative fuel boost pump switch/light and check for the following:

1) L and R PUMP ON lights are out.

2) L and R PUMP INOP lights are on.

(c) On the FUEL CONTROL panel, check that the LOW PRESS light is on for the non−operating engine.

(d) After two minutes, if the LOW PRESS light is still not displayed for the non−operating engine, do the steps that follow:

1) Dry motor the non−started engine for a maximum of 30 seconds.

2) The applicable fuel LOW PRESS light should be on during the dry motoring as the residual fuel pressure is reduced.

(e) On the FUEL CONTROL panel, check that the LOW PRESS light is on for the non−operating engine.

B. Start the engine that was previously shutdown.

C. If the left boost pump is inoperative, start the APU and operate it continuously during flight.



Airplane: CL 601


FUEL

System & Item 1

Sequence Numbers

2 Number Installed

1

1


28−25−1 APU Fuel Pump C

C

0

0



a) APU is operated for a maximum of 10 minutes from start-up to shutdown,

b) APU is used only to start one engine,

c) APU generator adapter temperature is below 40°C prior to engine start,

d) APU is started with the left main engine electric fuel pump, and

e) APU is shutdown and considered inoperative in flight.

May be inoperative provided APU is considered inoperative and is not used.

1. PLACARD

A. Put an APU FUEL PUMP INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

Open and collar the APU fuel pump circuit breaker that follows:


CBP–B 312 APU FUEL PUMP 222

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601


FUEL

System & Item 1

Sequence Numbers

2 Number Installed

2


28−25−2 APU Fuel Shutoff C Valves

0


(M) One or both may be inoperative closed provided APU is not used.

1. PLACARD

A. Put an APU FUEL SHUTOFF VALVES INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Open and collar the applicable APU Fuel SOV circuit breaker that follows:


CBP–A 135 FUEL SOV−APU 221

B. Connect external pneumatic supply to ground air supply valve for engine start.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601


FUEL

System & Item 1

Sequence Numbers

2 Number Installed

1


28−25−3 APU Negative G Feed C Check Valve

0


(O) May be inoperative provided flight operations are not dependent on use of the APU.

1. PLACARD

A. Put an APU NEGATIVE G FEED CHECK VALVE INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

NOTE: With the APU Negative G Feed Check Valve failed open, the before−flight check of the right engine fuel−feed check−valve may not give the expected result if the APU is operating. This procedure is to make sure that the APU is shut down.

A. Do the operational check of the right engine fuel-feed check-valve as follows:

(1) Make sure that the left boost pump is not operating.

(2) With right engine and APU operating and the left engine shut-down, shut-down the APU and check the following message:

On the overhead FUEL CONTROL panel, the LEFT ENG FUEL LOW PRESS switch/light comes on.

(3) If the APU is on during the engine fuel-feed check-valve test, the indication (switch light/message) will not be displayed.



Airplane: CL 601


FUEL

System & Item 1

Sequence Numbers

2 Number Installed

1


28−27−1 Single Point Pressure C Refueling System

0


(O) May be inoperative provided alternate refueling procedures below are used.

1. PLACARD

A. Put a SINGLE POINT PRESSURE REFUELLING SYSTEM INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. After refueling physically verify that the gravity filler caps are properly installed.



Airplane: CL 601


FUEL

System & Item 1

Sequence Numbers

2 Number Installed

1


28−27−1 Single Point Pressure Refueling System

1) External Refuel/Defuel C Control Panel

0


May be inoperative provided internal Refuel/Defuel control panel is operative.

1. PLACARD

A. Put an EXTERNAL REFUEL/DEFUEL CONTROL PANEL INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)


A. Not required.



Airplane: CL 601


FUEL

System & Item 1

Sequence Numbers

2 Number Installed

1

1


28−27−1 Single Point Pressure Refueling System

2) Internal Refuel/Defuel D Control Panel

a) Fuel Quantity Display

D

0

0



alternate means is used to determine the amount of fuel.

1. PLACARD

A. Put an INTERNAL REFUEL/DEFUEL CONTROL PANEL INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)


A. Use the external Refuel/Defuel Control panel to determine the amount of fuel.



Airplane: CL 601


FUEL

System & Item 1

Sequence Numbers

2 Number Installed

3


28−27−2 Refuel/Defuel Shut−Off Valves

1. Left, Right, Aux C

0



a) Alternate refueling procedures below are used,

b) Ensure that the calculated static airplane CG with full mission fuel load is aft of the fwd airplane Take−off Limit Line (ref. AFM), and

c) Fuel Quantity Indication Systems (cockpit) are operative.

1. PLACARD

A. Put a REFUEL / DEFUEL SHUTOFF VALVES INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. After authorized personnel refuel the airplane by gravity, make sure that the gravity filler caps are properly installed as follow:

(1) For the center tank, make sure that the access cover is closed.

(2) For the main tanks, make sure that the arrow on the cap aligns with the arrow on the adaptor assembly.

B. Refer to Airplane Flight Manual, LIMITATIONS to make sure the CG is calculated to be aft of the forward Take−off Limit Line.



Airplane: CL 601


FUEL

System & Item 1

Sequence Numbers

2 Number Installed

2

2


28−27−2 Refuel/Defuel Shut−Off Valves

2. Tail C

C

0

0


(O) May be inoperative closed provided

Aux and Tail Fuel Tanks remain empty.


a) Alternate refueling procedures below are used,

b) Ensure that the calculated static airplane CG with full mission fuel load is aft of the fwd airplane Take−off Limit Line (ref. AFM), and

c) Left, Right, Aux Refuel/Defuel SOVs are closed.

1. PLACARD

A. Put a REFUEL / DEFUEL SHUTOFF VALVES INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. With the shutoff valves failed in the closed position make sure that the AUX and TAIL tanks remain empty.

B. With the shutoff valves failed in the open position do as follows:

(1) After authorized personnel refuel the airplane by gravity, make sure that the center−tank gravity filler−cap and access cover are properly installed.

(2) Refer to the Airplane Flight Manual, LIMITATIONS to make sure the CG is calculated to be aft of the forward Take-off Limit Line.

(3) On the refuel/defuel panel, close the L MAIN (L MN), R MAIN (R MN) and AUX refuel/defuel shutoff valves (SOV). Make sure that the valves show closed.



Airplane: CL 601


FUEL

System & Item 1

Sequence Numbers

2 Number Installed

1


28−27−3 Refuel/Defuel Adapter C Cap

0


(M) May be inoperative or missing provided:

a) Refuel / Defuel adapter is visually checked for contamination prior to each refueling,

b) Adapter poppet is visually checked closed after each refueling,

c) No leakage can be detected after refueling is complete, and

d) All Refuel/Defuel Shut-off valves are verified closed after each refueling.

1. PLACARD

A. Put a REFUEL / DEFUEL ADAPTER CAP INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. With the Refuel/Defuel adapter cap inoperative or missing, do the steps that follow:

Before each refueling:

(1) Do a visual check of the refuel/defuel adapter for cleanliness. Remove all foreign matter before you connect the refueling nozzle.

After each refueling:

(1) Visually check that the adapter poppet is closed.

(2) Visually inspect for leakage. No leakage is permitted.

(3) On the refuel/defuel control panel, make sure that the refuel/defuel shutoff valves are in the closed position.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601


FUEL


2 Number Installed

2


28 FUEL

28−41−1 Fuel Quantity Indicating Systems (Cockpit)

1. Main Fuel Tanks − C Left and Right

1


(M) (O) One may be inoperative provided:

a) Alternate gravity refueling procedures below are used,

b) Both main tanks are visually confirmed full,

c) Total full carried includes 10% more than the required fuel load for the planned flight,

d) Aux Fuel Tank Quantity Indicator is operative or the Aux Fuel Tank is empty,

e) Fuel Flow Indicating Systems and associated engine instruments are operative,

f) Gravity Crossflow SOV is verified operative,

g) Crossfeed SOVs (if installed) remain closed,

h) Lateral fuel balance is maintained during flight,

i) Fuel Totalizer is considered inoperative,

j) After takeoff, power is set by matching fuel flow indications on both engines, and

k) An in−flight log of fuel burned is maintained.

1. PLACARD

A. Put a MAIN FUEL TANKS INOPERATIVE placard on the instrument panel.



Airplane: CL 601


FUEL

2. MAINTENANCE (M)

Before flight:

A. Gravity refuel airplane (refer to AIRPLANE MAINTENANCE MANUAL, Chapter 12−10−28). Visually make sure that both fuel tank are full and balanced.

B. If the AUX fuel tank quantity indicator is inoperative, defuel the AUX and tail (if installed) fuel tanks (refer to AIRPLANE MAINTENANCE MANUAL, Chapter 12−10−28).

3. OPERATIONS (O)

A. Apply AC power to the airplane and check the following:

(1) Select the engine instrument TEST switch to position 1 and check the following:

(a) The flowmeter digital readout indicates 888.

(b) The vertical scale indicates full scale reading.

(c) The operative fuel quantity indicators digital readout indicates 8880.

(2) Select the engine instrument TEST switch to position 2 and check the following:

(a) The flowmeter digital readout indicates 888.

(b) The vertical scale indicates full scale reading.

(c) The operative fuel quantity indicators digital readout indicates 8880.

(3) On the FUEL CONTROL panel, make sure that the X-FLOW shut-off valve is operative.

B. Ensure lateral fuel balance (e.g. trim, fuel flow; log etc.)

C. Maintain an in-flight fuel log as follows (Figure 1):

(1) Record initial fuel load (1) and operative fuel quantity indications in the 0+02 column.

Each 30 minutes do the steps that follow:

(a) Record fuel remaining in tanks with operative gauges and total (2).

(b) Record engine fuel used from the fuel used indications.

(c) Compute APU fuel used and record on line provided.

(d) Compute total fuel used (3).



Airplane: CL 601


FUEL

(e) Add total remaining (2) and total fuel used (3) to acquire total fuel accounted for (4).

(f) Subtract total fuel accounted for (4) from initial fuel load (1) to acquire fuel remaining in the tank with inoperative gauge (5)

.



Airplane: CL 601


FUEL

In−Flight Fuel Log

Figure 1



Airplane: CL 601


FUEL


2 Number Installed

1


28 FUEL


3. Aux Fuel Tank (With C Tail Tank Installed)

0


(M) May be inoperative provided the Aux and Tail Fuel Tanks remain empty.

1. PLACARD

A. Put an AUX FUEL TANK INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

Before Flight:

A. Do a defueling of the Tail and Aux tanks (refer to the AIRPLANE MAINTENANCE MANUAL, Chapter 12−10−28).

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601


FUEL


2 Number Installed

1


28 FUEL


4. Fuel Totalizer C

0


1. PLACARD

A. Put a FUEL TOTALIZER INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601


FUEL




Airplane: CL 601


HYDRAULIC POWER

System & Item 1

Sequence Numbers

2 Number Installed

3

3 Number Required for Dispatch 29 HYDRAULIC POWER

29−11−2 Hydraulic Accumulator C Pressure Gauges (Systems 1, 2 and 3)

0


(M) All may be inoperative provided accumulator pre-charge is checked using a suitable gauge before the first flight of each day.

1. PLACARD

A. Put a HYDRAULIC ACCUMULATOR PRESSURE GAUGES INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

Before flight:

A. Before the first flight of each day, do the steps that follow:

WARNING: OBEY ALL THE HYDRAULIC SAFETY PRECAUTIONS WHEN YOU DO WORK ON THE HYDRAULIC SYSTEM AND/OR A HYDRAULIC SYSTEM COMPONENT. IF YOU DO NOT DO THIS, YOU CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO EQUIPMENT.

(1) Make sure that the hydraulic pressure for the applicable system is at 0 psi (0 kPa).

(2) Remove the cap from the nitrogen charge valve for the applicable accumulator.

(3) Connect the charging and gauging kit (GSE REF # 12−20−03) to the nitrogen charge valve for the applicable system.

(4) Open the nitrogen charge valve and make sure that the accumulator shows a pressure of 1502 ± 50 PSI (10342 ± 345 kPa) on the gauge kit.

(5) Close the nitrogen charge valve.

(6) Remove the charging and gauging kit from the nitrogen charge valve.

(7) Install the cap on the nitrogen charge valve.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601


HYDRAULIC POWER

System & Item 1

Sequence Numbers

2 Number Installed

3


29−11−3 Hydraulic Accumulators C (Systems 1, 2 and 3)

1


System 1 and/or System 2 accumulator(s) may be inoperative provided System 3 is operative.

1. PLACARD

A. Put a HYDRAULIC ACCUMULATORS INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601


HYDRAULIC POWER


2 Number Installed

1


29 HYDRAULIC POWER

29−11−4 Hydraulic Heat C Exchanger Cooling Fan

0


(M)(O) May be inoperative provided ground operation of hydraulic systems 1 and 2 is limited to 30 minutes when OAT is above 45°C (113°F).

1. PLACARD

A. Put a HYDRAULIC HEAT EXCHANGER COOLING FAN INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Open and tag the hydraulic heat exchanger cooling fan circuit breakers that follow:

CB PANEL

CB NO.

NAME

ZONE

CB−B 182 HYD SYST FAN 222

CB−B 247 HYD SYST FAN CONT 222

B. Ensure ground operation of hydraulic systems 1 and 2 is limited to 30 minutes when OAT is above 45°C (113°F).

3. OPERATIONS (O)

A. Ensure ground operation of hydraulic systems 1 and 2 is limited to 30 minutes when OAT is above 45°C (113°F).



Airplane: CL 601


HYDRAULIC POWER

System & Item 1

Sequence Numbers

2 Number Installed

3


29−11−7 Return Manifold Filter − A Differential Pressure Indications

0


(M) Any or all may be inoperative provided:

a) Filter element is verified free of any metal contaminant, and

b) Repairs are made within one flight day.

1. PLACARD

A. Put a RETURN MANIFOLD FILTERS INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

WARNING: OBEY ALL THE HYDRAULIC SAFETY PRECAUTIONS WHEN YOU DO WORK ON THE HYDRAULIC SYSTEM AND/OR A HYDRAULIC SYSTEM COMPONENT. IF YOU DO NOT DO THIS, YOU CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO EQUIPMENT.

A. Remove the return filter element (refer to AIRPLANE MAINTENANCE MANUAL, TASK 29−11−41).

B. Examine the return filter element for contamination. If contamination is found, determine the cause and replace the filter.

C. If no contamination is found, re-install the filter element (refer to AIRPLANE MAINTENANCE MANUAL, TASK 29−11−41).

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601


HYDRAULIC POWER

System & Item 1

Sequence Numbers

2 Number Installed

1


29−12−1 Electric Pump A (System 3A) (ACMP)

0



a) All other hydraulic pumps (engine driven and electrical) are operative.

b) 3B pump is operated continuously throughout the flight, and

c) Repairs are made within one flight day

1. PLACARD

A. Put a HYDRAULIC ELECTRIC PUMP INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601


HYDRAULIC POWER


2 Number Installed

3


29 HYDRAULIC POWER

29−31−1 Hydraulic Pressure C Indicators (Cockpit)

2



a) All four Electric Motor Driven Hydraulic Pumps are operative,

b) Hydraulic Pump Low Pressure (ELECT PUMP or L/R ENG PUMP) Caution Lights for associated system is operative,

c) Hydraulic Pump HI TEMP Caution Light for associated system is operative, and

d) Brake Pressure Indicator is operative.

1. PLACARD

A. Put a HYDRAULIC PRESSURE INDICATORS INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601


HYDRAULIC POWER


2 Number Installed

3


29 HYDRAULIC POWER

29−31−2 Hydraulic Reservoir C Quantity Indications (Systems 1, 2 and 3) (Cockpit)

0


(M) One or all may be inoperative provided:

a) Affected reservoir quantity is confirmed within limits prior to each flight,

b) Associated Hydraulic Pressure Indicator is operative,

c) Associated Hydraulic Pump Low Pressure (ELEC PUMP or L/H ENG PUMP) Caution Lights are operative, and

d) Associated Hydraulic HI TEMP Caution Light is operative.

1. PLACARD

A. Put a HYDRAULIC RESERVOIR QUANTITY INDICATIONS INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

Before Flight:

A. Check that low pressure warning light for each pump of affected system is operative (refer to operational test, AIRCRAFT MAINTENANCE MANUAL, Chapter 29–10–02).

B. Check that HI TEMP caution light illuminates by selecting WARN LTS TEST switch,

on pilot’s or co−pilot’s facia panel, to TEST.

C. Check reservoir quantity by utilizing the direct reading fluid level indicator attached to the affected system reservoir prior to each flight.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601


HYDRAULIC POWER

System & Item 1

Sequence Numbers

2 Number Installed

6


29−34−1 Hydraulic Pump Low C Pressure Switches

3



a) At least one Low Pressure Switch is operative for each hydraulic system,

b) Associated Hydraulic Pressure and Quantity Indicating Systems are verified operative.

1. PLACARD

A. Put a HYDRAULIC PUMP LOW PRESSURE SWITCHES INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601


HYDRAULIC POWER


2 Number Installed

3


29 HYDRAULIC POWER

29−35−1 Hydraulic HI TEMP C Caution Lights (Systems 1, 2 and 3)

2



a) Associated Hydraulic Pressure Indicator is operative

b) Associated Hydraulic Reservoir Quantity Indicator is operative, and

c) Hydraulic Heat Exchanger Cooling Fan is operative System 1 and 2 only).

1. PLACARD

A. Put a HYDRAULIC HI TEMP CAUTION LIGHTS INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601


HYDRAULIC POWER

System & Item

Sequence Numbers


6


29 HYDRAULIC POWER

3


One per system may be inoperative provided:

a) Associated Hydraulic Pressure Indicator is operative

b) Associated Hydraulic Reservoir Quantity Indicator is operative, and

c) Associated Hydraulic HI TEMP Caution Light is operative.

29−37−1 Hydraulic Pump Low C

Pressure Caution Lights

(Light function only)

(ELEC PUMP, L ENG

PUMP, R ENG PUMP)

1. PLACARD

A. Put a HYDRAULIC PUMP LOW PRESSURE CAUTION LIGHTS INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601


ICE AND RAIN PROTECTION

System & Item 1


1

1


30 ICE AND RAIN PROTECTION

30−12−1 Wing Anti−Ice System

3. Normal Control C

C

0 0


(M) May be inoperative provided Wing

Anti−Ice System Standby Control is operative.


a) Both Ice Detection Systems are operative, and

b) Airplane is not operated in known or forecast icing conditions.

1. PLACARD

A. Put a WING ANTI−ICE NORMAL CONTROL SYSTEM INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Check that the wing anti-ice system standby control is operative as follows:

(1) Start the engine (refer to AIRPLANE MAINTENANCE MANUAL, TASK 71–02–02).

(2) On the ANTI-ICE control panel, set the WING switch to STANDBY.

(3) Check that the L FAIL and R FAIL lights come on and then go out within 10 seconds.

(4) Check that the L/R HEAT lights are on.

(5) Check that the wing anti-icing airflow is exhausting from exits at the bottom of both wings.

(6) Increase the thrust to 75% N2, check that ITT increases noticeably when anti-ice

valve opens, and decreases when valve closes.

(7) Monitor the system for at least one full cycle.

(8) Set the anti-ice control WING switch to OFF.Shut down the engine (refer to AIRPLANE MAINTENANCE MANUAL, TASK 71–02–02).

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601



System & Item 1


1

1



30−12−1 Wing Anti−Ice System

4. Standby Control C

C

0

0


May be inoperative provided Wing Anti−Ice System Normal Control is operative.



b) Flight is not conducted in known or forecast icing conditions.

1. PLACARD

A. Put a WING ANTI−ICE STANDBY CONTROL SYSTEM INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601



System & Item 1

Sequence Numbers

2 Number Installed

2

3 Number Required for Dispatch 30 ICE AND RAIN PROTECTION

30−12−2 Wing Anti−Ice System C Modulating and Shut−off Valves

0


One or both may be inoperative CLOSED provided:



1. PLACARD

A. Put a WING ANTI−ICE SYSTEM MODULATING AND SOVs INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601



System & Item 1


1

1



30−12−3 Wing Anti−Ice Isolation C Valve

C

0

0


May be inoperative OPEN.

May be inoperative CLOSED provided:



1. PLACARD

A. Put a WING ANTI−ICE ISOLATION VALVE INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601



System & Item 1

Sequence Numbers

2 Number Installed

2


30−20−1 Engine Cowl Anti−Ice C Pressure Regulating and Shutoff Valves

1


(M) One may be inoperative provided:

a) Affected valve is secured closed,

b) Both Ice Detection Systems are operative,

c) Associated ACU/Pack is selected ON above FL 402, and

d) Flight is not conducted in known or forecast icing conditions.

1. PLACARD

A. Put an ENGINE COWL ANTI−ICE PRESSURE REGULATING AND SOVs INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Secure the affected valve closed as follows:

(1) For Kaiser valve with P/N’s 601−97097−1, −3, −5, or −7, do as follows:

(a) Remove the quick release pin from its stowed position.

(b) Install the quick release pin into the lock position hole.

(c) Pin cannot be installed unless the valve is fully closed.

(2) For Dukes valve with P/N 601−97097−9, do as follows:

(a) Remove the cap from the manual override mechanism, located on the side of the valve body.

(b) Lock the valve closed using a 3/32 in. hex key to tighten the override screw until it stops (approximately 16 turns).

(c) Install the override cap and torque to 40–50 lb-in (4.52−5.65 Nm).

(d) Lockwire the cap to the valve.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601



System & Item 1

Sequence Numbers

2 Number Installed

2


30−20−2 Engine Cowl Anti−Ice

Pressure Relief Blow−Off Valves

C

1


One may be inoperative OPEN provided:

a) Associated Thrust Reverser is verified operative prior to each flight,

b) Associated Bleed Air 14th Stage SOV is operative, and

c) Operations are conducted in accordance with AFM Supplement 14, Operations with Airplane Systems Inoperative.

1. PLACARD

A. Put an ENGINE COWL ANTI−ICE PRESSURE RELIEF BLOW−OFF VALVES INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601



System & Item 1

Sequence Numbers

2 Number Installed

2


30−31−1 Probe Heaters

1. Pitot Probes B

1


(M) Except for RVSM Operations, one of

each may be inoperative provided:

a) Airplane is not operated in visible moisture (including standing water and slush) in any form,


c) Flight is not conducted in known or forecast icing conditions, and

d) Airplane is operated in day VMC only.

1. PLACARD

A. Put a PITOT PROBE HEATERS INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Open and tag the circuit breaker that follows:

For the left pitot heater,


CBP−C 330 LEFT P-S HTR 221

For the right pitot heater,


CBP−B 197 HEATERS RIGHT PITOT 222

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601



System & Item 1

Sequence Numbers

2 Number Installed

2



2. Static Probes B

1








1. PLACARD

A. Put a STATIC PROBE HEATERS INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)


For the left static heater;


CBP−A 42 HEATERS LEFT STATIC 221

For the right static heater,


CBP−B 198 HEATERS RIGHT STATIC 222

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601



System & Item 1

Sequence Numbers

2 Number Installed

2



3. Angle of Attack B Vanes

1








1. PLACARD

A. Put an ANGLE OF ATTACK VANES PROBE HEATERS INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Open and tag the circuit breaker that follows: For he left vane heater,


CBP−C 331 L HTR AOA 221

For the right vane heater,


CBP−B 199 HEATERS AOA 222

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601



System & Item 1

Sequence Numbers

2 Number Installed

1



4. TAT Probe B

0







1. PLACARD

A. Put a TAT PROBE HEATER INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)



CBP−A 43 HEATER TAT 221

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601



System & Item 1

Sequence Numbers

2 Number Installed

4


30−41−1 Left and Right Windshield.. C and Side Window Heating Systems

3



a) Operations are not conducted in known or forecast icing conditions, and

b) Pilot’s (Left) Side Window heating is operative.

1. PLACARD

A. Put a WINDSHIELD AND SIDE WINDOW HEATING SYSTEMS INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601



System & Item 1

Sequence Numbers

2 Number Installed

1


30−71−1 Drain Mast Heater C

0



a) Associated sink is not used, and

b) Sink and/or coffee water supply is turned off.

1. PLACARD

A. Put a DRAIN MAST HEATER INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Place a prominent DO NOT USE SINK placard in the sink.

B. Coffee maker – pull and secure circuit breaker(s).

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601



System & Item 1

Sequence Numbers

2 Number Installed

2

2


30−80−1 Ice Detection Systems C

A

1

0



a) Wing and Engine Cowl Anti−Ice Systems are ON when SAT on the ground is 10°C or less and visible moisture in any form is present, and

b) Wing and Engine Cowl Anti−Ice Systems are ON when TAT in flight is 10°C or less and visible moisture in any form is present.

Both may be inoperative provided:

a) Flight is not conducted in known or forecast icing conditions, and

b) Repairs are made within one flight day.

1. PLACARD

A. Put an ICE DETECTION SYSTEMS INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601






Airplane: CL 601


INDICATING/RECORDING SYSTEMS

System & Item

Sequence Numbers


1

5


31 INDICATING/RECORDING

0

2



a) Cockpit Voice Recorder (CVR) operates normally, and

b) Airplane is not dispatched from an airport with contracted maintenance facility (in MME) unless;

1) FDR failure occurs after pushback but prior to take-off, or

2) FDR repair was attempted but was not successful.

c) In those cases where repair is attempted but not successful, the aircraft may be dispatched on a flight or series of flights until the next designated airport where repair must be accomplished prior to dispatch, and

d) Repairs are made within three flight days

Up to three (3) parameters may be inoperative provided;

a) Cockpit Voice Recorder operates normally; and

b) Repairs are made within 20 calendar days

SYSTEMS 31−31−1 Flight Data Recorder A

(FDR) System

FDR Recording Parameters

A

1. PLACARD

A. Put an FLIGHT DATA RECORDER SYSTEM INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. With the Flight Data Recorder (FDR) inoperative, verify the operation of the Cockpit Voice Recorder (CVR) as follows:



Airplane: CL 601



(1) Connect headphones to the CVR control panel. (2) Push the TEST switch for a minimum of half a second. (3) Make sure that you hear a tone in the headphones. (4) Make sure that the test indicator (light and/or meter) indicates operation.

(5) Disconnect the headphones from the CVR control panel..



Airplane: CL 601



System & Item

Sequence Numbers


1


31 INDICATING/RECORDING

0



a) Light is not illuminated, and

b) BRT / DIM function on the 10−channel annunciator panel is confirmed operative prior to each flight.

SYSTEMS 31−50−1 Auto CB Fail Light B

(10−Channel Annunciator)

1. PLACARD

A. Put an AUTO CB FAIL LIGHT INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601



System & Item 1

Sequence Numbers

2 Number Installed

2


31 INDICATING/RECORDING SYSTEMS 31−60−1 Clocks

C

0



a) A reliable and functioning time−piece is readily available, and

b) Alternate procedures below are used to determine elapsed time.

1. PLACARD

A. Put a CLOCKS INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Make sure that a reliable and functioning time−piece is readily available.

B. If both clocks are inoperative, one crewmember will use a reliable and functioning time-piece to determine elapsed time.



Airplane: CL 601


LANDING GEAR

System & Item 1

Sequence Numbers

2 Number Installed

1

3 Number Required for Dispatch 32 LANDING GEAR

32−30−1 Landing Gear Selector C Handle Anti−Retraction Mechanism

0


(M) May be inoperative in the LOCKED position (DOWN) provided the downlock release mechanism is operative.

1. PLACARD

A. Put a LANDING GEAR SELECTOR HANDLE ANTI−RETRACTION MECHANISM INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Make sure that all hydraulic pressure is released from hydraulic system No. 3.

B. Install the downlock safety pins in the nose landing gear and both the main landing gears.

C. Depress the downlock release button on the LDG gear panel and move the landing gear handle to the up position. Make sure the handle moves freely.

D. Move the landing gear handle to the down position. Make sure the handle moves freely and locks in the DN position.

E. Remove the three landing gear safety pins.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601


LANDING GEAR

System & Item 1

Sequence Numbers

2 Number Installed

2


32−43−1 Brake Accumulator C Pressure Gauges

0


(M) One or both may be inoperative provided the accumulator pre−charge pressure is checked using a suitable pressure gauge before the first flight of each day.

1. PLACARD

A. Put a BRAKE ACCUMULATOR PRESSURE GAUGES INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)


A. Check the accumulator pre-charge pressure as follows:

(1) Open the NLG forward doors (711−AL and 712−AR).

(2) Remove the cap from the nitrogen charge valve and connect the charging and gauging kit (GSE REF # 12−20−03) (P/N 14−6805−6020).

(3) Make sure that the pressure gauge on the charging and gauging kit shows a minimum of 750 psi (5171 kPa).

NOTE: The procedure is applicable to the pressure gauges of the inboard and outboard brake accumulators.

(4) Disconnect the charging and gauging kit and install the cap on the nitrogen charge valve.

(5) Close the NLG forward doors (711−AL and 712−AR).

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601


LANDING GEAR


2 Number Installed

2


32 LANDING GEAR

32−43−2 Brake Pressure C Indications

0


(M) One or both may be inoperative provided:

a) Brake accumulator(s) nitrogen pressure is checked prior to the first flight of each day,

b) Capability of brake accumulators to retain adequate hydraulic fluid for brakes is verified prior to the first flight of each day, and

c) Hydraulic Pressure Indication is operative.

1. PLACARD

A. Put a BRAKE PRESSURE INDICATIONS INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)


A. Check the brake pressure as follows:

(1) Pressurize the hydraulic system No. 2 and/or No. 3 (refer to AIRPLANE MAINTENANCE MANUAL, Chapter 12−02−02).

(2) Release the pressure from the hydraulic system to 0 psi without using the pilot’s or copilot’s brake pedals (refer to AIRPLANE MAINTENANCE MANUAL, Chapter 12−02−02).

(3) 15 minutes after release of the hydraulic pressure, record the brake accumulator hydraulic pressure from the brake accumulator gauge.

(4) The brake pressure recorded in step 1.C. must be more than 2302 psi to demonstrate proper brake hydraulic pressure retention.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601


LANDING GEAR


2 Number Installed

1


32 LANDING GEAR

32−45−1 Parking Brake Light C

0


(O) May be inoperative provided the procedures below are used to ensure the amber anti−skid fail lights INBD FAIL and OUTBD FAIL illuminate as the parking brake is set.

1. PLACARD

A. Put a PARKING BRAKE LIGHT INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

Before taxi:

A. PARKING BRAKE handle ........................................... Set Check antiskid

INBD FAIL and OUTBD FAIL lights come on.

B. PARKING BRAKE handle ......................................OFF Check antiskid INBD FAIL and OUTBD FAIL lights go out.



Airplane: CL 601


LANDING GEAR

System & Item 1

Sequence Numbers

2 Number Installed

1

1


32−50−2 Remote Nose Gear D Door Release Mechanism

D

0

0


(M) May be inoperative in the “DOOR CLOSED” position provided:

a) Mechanism is verified to be in the “DOOR CLOSED” position, and

b) Actuator arm is secured in the “DOOR CLOSED” position.

(M) May be inoperative in the “DOOR CLOSED” position provided:

a) Mechanism is verified to be in the “DOOR CLOSED” position, and

b) Actuator arm is removed from the nose wheel well fitting.

1. PLACARD

A. Put a REMOTE NOSE GEAR DOOR RELEASE MECHANISM INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Actuator arm secured

(1) Ensure that the nose landing gear door release handle is in the stowed position.

(2) Secure linkage in the nose wheel well where release cable attaches to the nose wheel door release lever.

(3) Secure cable to structure with tie wrap.

(4) Assure that there is no obstruction in the nose wheel well.

B. Actuator arm removed

(1) Ensure that the nose landing gear door release handle is in the stowed position.

(2) Disconnect linkage in the nose wheel well where release cable attaches to the nose wheel door release lever.

(3) Secure cable to structure with tie wrap.

(4) Assure that there is no obstruction in the nose wheel well.

3. OPERATIONS(O)

A. Not required.



Airplane: CL 601


LANDING GEAR




Airplane: CL 601


LIGHTS

System & Item 1

Sequence Numbers

2 Number Installed

3

3

3 Number Required for Dispatch 33 LIGHTS

33−12−1 Lighting Control Panels

(Center Pedestal & L/R Facia Panels)

1. Floodlight System

a. BRT/DIM C Systems

C

0

0


Any or all may be inoperative provided:

a) BRT/DIM switch is selected to OFF position, and

b) Brightening System is operative.

May be inoperative provided Cockpit lighting and intensity is sufficient for crewmembers to perform their duties throughout flight.

1. PLACARD

A. Put a FLOODLIGHT BRT/DIM SYSTEMS INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601


LIGHTS


2 Number Installed

3

3


33 LIGHTS

33−12−1 Lighting Control Panels (Center Pedestal & L/R Facia Panels)

1. Floodlight System

b. Brightening C Systems

C

0

0


Any or all may be inoperative provided the associated BRT/DIM system is operative.

May be inoperative provided Cockpit lighting is sufficient for crewmembers to perform their duties throughout flight.

1. PLACARD

A. Put a FLOODLIGHT BRIGHTENING SYSTEMS INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601


LIGHTS


2 Number Installed

3


33 LIGHTS


2. Instrument C Brightening Systems

0



1. PLACARD

A. Put an INSTRUMENT BRIGHTENING SYSTEMS INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601


LIGHTS


2 Number Installed

2


33 LIGHTS


3. Floor Light Systems C

0



1. PLACARD

A. Put a FLOOR LIGHT SYSTEMS INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601


LIGHTS


2 Number Installed

1

1


33 LIGHTS

33−12−3 PBA BRT/DIM system

(10 Channel Annunciator Panel)

C

C

0

0


May be inoperative provided the DIM mode is operative for night operations

May be inoperative provided the BRT mode is operative for day operations

1. PLACARD

A. Put a PBA BRT/DIM SYSTEM INOPERATIVE placard on the instrument panel. 2. MAINTENANCE (M)


A. Not required.



Airplane: CL 601


LIGHTS

System &Item 1

Sequence Numbers

2 Number Installed

1


33−12−4 Overhead Instrument C Panel Brightening System

0


May be inoperative provided Cockpit lighting is sufficient for flight crewmembers to perform their duties throughout flight.

1. PLACARD

A. Put an OVERHEAD INSTRUMENT PANEL BRIGHTENING SYSTEM INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601


LIGHTS

System & Item 1

Sequence Numbers

2 Number Installed

5


33−13−1 Cockpit/Flight Deck/ C Flight Compartment and Instrument Panel Lighting Systems (Excluding EFIS)

2


Individual lights may be inoperative provided the remaining lighting system lights are:

a) Not required for an emergency procedure,

b) Sufficient to clearly illuminate all required instruments, controls, and other devices for which they are provided,

c) Positioned so that direct rays and reflections are shielded from the pilots’ eyes, and

d) Lighting configuration and intensity is acceptable to the flight crew.

NOTE: Individual button/switch lights and annunciator/indications are excluded from this relief

1. PLACARD

A. Put a COCKPIT AND INSTRUMENT PANEL LIGHTING SYSTEMS INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601


LIGHTS

System & Item 1

Sequence Numbers

2 Number Installed

2


33−14−1 Map Reading Lights

D

0


May be inoperative provided cockpit lighting is sufficient for crewmembers to perform their duties throughout flight.

1. PLACARD

A. Put a MAP READING LIGHTS INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601


LIGHTS

System & Item 1

Sequence Numbers

2 Number Installed

40


33−20−1 Cabin Interior Lights C

10



a) Sufficient lighting is operative to permit the crew to perform their required duties, and

b) Lighting configuration upon departure is acceptable to the flight crew.

1. PLACARD

A. Put a CABIN INTERIOR LIGHTS INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601


LIGHTS

System & Item 1

Sequence Numbers

2 Number Installed

1


33−20−2 Miscellaneous Lights

1. Boarding and Dome D lights

0


1. PLACARD

A. Put a BOARDING AND DOME LIGHTS INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601


LIGHTS

System & Item 1

Sequence Numbers

2 Number Installed

1


33−20−3 Lavatory Vanity / D Reading Lights

0


1. PLACARD

A. Put a LAVATORY VANITY / READING LIGHTS INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601


LIGHTS

System & Item 1

Sequence Numbers

2 Number Installed

2


33−23−1 Fasten Seat Belt and

No Smoking Warning Signs

1. Passenger Configuration C

0


(O)(M) May be inoperative provided procedures below are used to notify cabin occupants.

1. PLACARD

A. Put a FASTEN SEAT BELTS AND NO SMOKING WARNING SIGNS INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Put an INOPERATIVE placard next to the affected sign.

3. OPERATIONS (O)

A. Ensure a readily legible NO SMOKING/FASTEN SEATBELT sign can be seen from passenger or flight attendant(s) seats.

B. Flight crew to advise flight attendant(s) and passengers verbally using PA announcement when it is necessary to:

(1) Remain seated with seat belts fastened.

(2) Extinguish smoking material

(3) Advise any lavatory occupant of to return to seat, fasten seatbelt and to refrain from smoking.



Airplane: CL 601


LIGHTS

System & Item 1

Sequence Numbers

2 Number Installed

5


33−31−1 Service Lights D

0


1. PLACARD

A. Put a SERVICE LIGHTS INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601


LIGHTS

System & Item 1


4

4


33 LIGHTS

33−40−1 Position Lights (Navigation)

1. Wing Tip Position C Light Bulbs

C

2

0


Two may be inoperative provided at least one bulb is operative at each position.

May be inoperative provided airplane is not operated at night.

1. PLACARD

A. Put a WING TIP POSITION LIGHT BULBS INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601


LIGHTS

System & Item 1


1

1

1


33 LIGHTS


2. Upper Aft Position C Light Bulb

C

C

0

0

0


May be inoperative provided Lower Aft Position Light is operative.

May be inoperative provided both winglet lights are operative May be inoperative provided airplane is not operated at night.

1. PLACARD

A. Put an UPPER AFT POSITION LIGHT BULB INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601


LIGHTS

System & Item 1


2

2

2

2


33 LIGHTS


4. Lower Aft C

Position Light Bulbs

C

C

C

1

0

0

0


Both may be inoperative provided Upper Aft Position Light is operative.

Both may be inoperative provided both winglet lights are operative. May be inoperative provided airplane is not operated at night.

1. PLACARD

A. Put a LOWER AFT POSITION LIGHT BULBS INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601


LIGHTS

System & Item 1

Sequence Numbers

2 Number Installed

1

1


33−40−2 High Intensity or Strobe C Light System

C

0

0


May be inoperative provided an approved Anti−Collision Beacon Light System is installed and operative.


1. PLACARD

A. Put a HIGH INTENSITY OR STROBE LIGHT SYSTEM INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601


LIGHTS

System & Item 1


1

1


33 LIGHTS

33−40−3 Anti−Collision Beacon C Light System

C

0

0


May be inoperative provided the High Intensity or Strobe Light System is installed and operative.


1. PLACARD

A. Put an ANTI−COLLISION BEACON LIGHT SYSTEM INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601


LIGHTS



4

4

4


33 LIGHTS

C

C

C

3

1

0


Three may be inoperative provided both Taxi / Recognition Lights are operative.

All may be inoperative provided airplane is not operated at night.

33−40−4 Landing Lights

(Wing Leading Edge and nose)

1. PLACARD

A. Put a LANDING LIGHTS INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601


LIGHTS

System & Item 1

Sequence Numbers

2 Number Installed

1


33−40−5 Landing Lights

3. Pulse Light Function C

0


(M) May be inoperative provided Pulselight

system is deactivated.

1. PLACARD

A. Put a PULSELIGHT LANDING LIGHT INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Open and collar the circuit breaker that follows:


CBP−B 219 PULSE LITE 222

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601


LIGHTS

System & Item 1

Sequence Numbers

2 Number Installed

1


33−40−7 Logo Light System D

0


(M) May be inoperative provided Logo Light System is deactivated

1. PLACARD

A. Put a LOGO LIGHT SYSTEM INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Open and collar the Circuit Breaker marked Logo Light.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601


LIGHTS

System & Item 1


2


33 LIGHTS

33−40−8 Taxi / Recognition Lights (in Leading Edge)

C

0


One or both may be inoperative provided affected lights are not required to support inoperative Landing Lights.

1. PLACARD

A. Put a TAXI / RECOGNITION LIGHTS INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601


LIGHTS

System & Item 1

Sequence Numbers

2 Number Installed

2

2

2

2


33−43−1 Wing Inspection Lights C

C

C

C

1

1

0

0


May be inoperative provided one Ice Detection System is operative.

One may be inoperative provided flight is not conducted in known or forecast icing conditions at night.


a) One Ice Detection System is operative, and

b) A portable lamp / light of adequate capacity for wing and/or control surface inspection is available for night operations in icing conditions.

Both may be inoperative provided flight is not conducted in known or forecast icing conditions at night.

1. PLACARD

A. Put a WING INSPECTION LIGHTS INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601


LIGHTS

System & Item 1

Sequence Numbers

2 Number Installed

4


33−50−1 Exterior Emergency C Lights

0


Any or all may be inoperative provided airplane is not operated at night.

1. PLACARD

A. Put an EXTERIOR EMERGENCY LIGHTS INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601


NAVIGATION


2 Number Installed

1


34 NAVIGATION

34−12−1 Standby Altimeter C

0


May be inoperative provided pilot’s

altimeter is pneumatic or servo /pneumatic and is operative.

1. PLACARD

A. Put a STANDBY ALTIMETER INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601


NAVIGATION


2 Number Installed

1


34 NAVIGATION

34−13−1 True Airspeed (TAS), Static Air Temperature (SAT), Total Air Temperature (TAT), Indicating Systems

1. TAS Indication C

0


May be inoperative provided other required systems (FMS etc.) do not depend on TAS data.

1. PLACARD

A. Put a TAS INDICATION SYSTEM INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601


NAVIGATION

System & Item 1

Sequence Numbers

2 Number Installed

1

3 Number Required for Dispatch 34 NAVIGATION

34−13−1 True Airspeed (TAS),

Static Air Temperature (SAT), Total Air Temperature (TAT), Indicating Systems

2. SAT Indication C

0



a) TAT is operative,

b) Other required systems (FMS etc) do not depend on SAT data, and

c) TAT/SAT conversion method is provided.

NOTE: The SAT/TAT Conversion Chart (Figure 1) is provided as supporting material.



Airplane: CL 601


NAVIGATION

SAT/TAT Conversion Chart Figure 1

1. PLACARD

A. Put a SAT INDICATION SYSTEM INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601


NAVIGATION


2 Number Installed

1


34 NAVIGATION

34−13−1 True Airspeed (TAS), Static Air Temperature (SAT), Total Air Temperature (TAT), Indicating Systems

3. TAT Indication C

0


May be inoperative provided SAT is operative.

1. PLACARD

A. Put a TAT INDICATION SYSTEM INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601


NAVIGATION


2 Number Installed

2


34 NAVIGATION

34−13−2 Vertical Speed B Indicators (VSIs)

1


One may be inoperative provided;

a) Airplane is operated in day VMC,

b) Pilot flying airplane has an operative VSI at his station.

c)

1. PLACARD

A. Put a VERTICAL SPEED INDICATORS INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601


NAVIGATION

System & Item 1

Sequence Numbers

2 Number Installed

1


34−17−1 Altitude Alerting System A

0



a) Auto−pilot with altitude hold and altitude capture operates normally, and

b) Enroute operations i.e. RVSM do not require its use

c) Airplane does not depart KWI, AMM or IST airport where repair or replacement can be made, and

d) Repairs are made within three flight days.

1. PLACARD

A. Put an ALTITUDE ALERTING SYSTEM INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Prior to take off, pilots to refer to operations manual, Chapter 8 on standard calls to ensure that assigned altitudes are adhered to.



Airplane: CL 601


NAVIGATION

System & Item 1

Sequence Numbers

2 Number Installed

1


34−17−1 Altitude Alerting System

3. Aural Alert C

0



a) Visual alert operates normally, and

b) Autopilot with altitude hold and capture operates normally.

1. PLACARD

A. Put an AURAL ALERT INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Not required



Airplane: CL 601


NAVIGATION

System & Item 1

Sequence Numbers

2 Number Installed

1


34−17−1 Altitude Alerting System

4. Visual Alert C

0



a) Aural alert operates normally, and

b) Autopilot with altitude hold and capture operates normally.

1. PLACARD

A. Put a VISAL ALERT INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Not required



Airplane: CL 601


NAVIGATION


2 Number Installed

1


34 NAVIGATION

34−21−1 Instrument Comparator C Monitor

0


(O) May be inoperative provided;

a) procedures below are established that do not require the use of the affected system

b) approach minimums are not dependent on its use.

1. PLACARD

A. Put an INSTRUMENT COMPARATOR MONITOR INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Normal SOP checks and callouts to be observed whilst using navigation aids with special emphasis on cross check below MSALT.



Airplane: CL 601


NAVIGATION


2 Number Installed

2

2


34 NAVIGATION

34−21−2 Non−EFIS ADI Annunciators / Displays

1. ADI - Glideslope Pointers B

B

0

0


One or both may be inoperative provided Glideslope Pointers are operative on the adjacent HSI.

One or both may be inoperative provided procedures are not dependent on their use.

1. PLACARD

A. Put a ADI - GLIDESLOPE POINTERS INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601


NAVIGATION


2 Number Installed

2

2


34 NAVIGATION


2. ADI-Localizer Pointers B

B

0

0


One or both may be inoperative provided expanded Localizer Pointers are operative on the adjacent HSI.


1. PLACARD

A. Put a ADI - LOCALIZER POINTERS INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601


NAVIGATION


2 Number Installed

2


34 NAVIGATION


3. Pitch and Roll B Command Bars

0


One or both may be inoperative provided approach minimums are not dependent on their use.

1. PLACARD

A. Put a PITCH AND ROLL COMMAND BARS INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601


NAVIGATION


2 Number Installed

2


34 NAVIGATION


4. ADI-Radio Altimeter C Display

0


May be inoperative provided weather minimums or operating procedures are not dependent on its use.

1. PLACARD

A. Put a RADIO ALTIMETER DISPLAY INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601


NAVIGATION


2 Number Installed

2


34 NAVIGATION


5. ADI - Rate of Turn C Indicators

0



a) Associated Turn and Slip indicators are operative, and

b) Standby Attitude Indicator is operative.

1. PLACARD

A. Put a ADI - RATE OF TURN INDICATORS INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601


NAVIGATION


2 Number Installed

2

2


34 NAVIGATION

34−21−3 Non−EFIS HSI Annunciators / Displays

1. HSI Bearing Pointers C

C

0

0


One or both may be inoperative provided equivalent display is available on the RMIs.


1. PLACARD

A. Put a HSI BEARING POINTERS INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601


NAVIGATION


2 Number Installed

2


34 NAVIGATION


2. HSI Distance Measuring C Equipment (DME) Displays

0



a) Procedures are not dependent on its use, and

b) FMS accuracy without DME update is acceptable for the intended operation.

1. PLACARD

A. Put a HSI DME DISPLAYS INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601


NAVIGATION


2 Number Installed

2

2


34 NAVIGATION


3. HSI Glideslope Pointers B

B

0

0


One or both may be inoperative provided Glideslope Pointers are operative on the adjacent ADI.


1. PLACARD

A. Put a HSI GLIDESLOPE POINTERS INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601


NAVIGATION


2 Number Installed

2


34 NAVIGATION


4. Heading Displays B

1



a) Standby Compass is operative, and

b) Adjacent RMI is operative.

1. PLACARD

A. Put a HEADING DISPLAYS INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601


NAVIGATION


2 Number Installed

2

2


34 NAVIGATION


5. Localizer Pointers B

B

0

0


One or both may be inoperative provided Localizer Pointers are operative on the adjacent ADI.


1. PLACARD

A. Put a LOCALIZER POINTERS INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601


NAVIGATION


2 Number Installed

2


34 NAVIGATION

34−22−2 Turn and Slip Indicators C

0


Both may be inoperative provided the associated Rate of Turn Indications are operative.

1. PLACARD

A. Put a TURN AND SLIP INDICATORS INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601


NAVIGATION


2 Number Installed

1


34 NAVIGATION

34−23−1 Vertical Navigation C System (VNAV)

0


Except for RVSM Operations, may be inoperative.

1. PLACARD

A. Put a VERTICAL NAVIGATION SYSTEM INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601


NAVIGATION


2 Number Installed

1


34 NAVIGATION

34−23−2 Inertial Reference Systems (IRSs)

C

0


Except when enroute operations require its use, may be inoperative provided:

a) Independent attitude indication is selected at each pilot’s panel, and

b) Independent directional compass indication is selected at each pilot’s panel.

1. PLACARD

A. Put an INERTIAL REFERENCE SYSTEMS INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601


NAVIGATION


2 Number Installed

1


34 NAVIGATION 34−23−4 Emergency Battery D

Packs for Backup COMM/NAV

0


1. PLACARD

A. Put an EMERGENCY BATTERY PACKS FOR BACKUP COMM/NAV INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)


A. Not required.



Airplane: CL 601


NAVIGATION


2 Number Installed

1


34 NAVIGATION

34−23−5 IRS Backup Battery D

0


1. PLACARD

A. Put an IRS BACKUP BATTERY INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601


NAVIGATION

System & Item 1

Sequence Numbers

2 Number Installed

1

1

1


34−27−1 Magnetic Compass B (Standby)

B

B

0

0

0


(O) May be inoperative provided any combination of three Gyro or INS (IRU) stabilized compass system are operative.


a) Any combination of two Gyro or INS (IRU) stabilized compass system are operative, and

b) Airplane is operated with dual independent navigation capability, and under positive radar control by ATC during the enroute flight phase.

(O) May be inoperative for flights that are entirely within areas of magnetic unreliability provided at least two stabilized directional gyro systems are installed, operative and used in conjunction with approved free gyro navigation techniques.

1. PLACARD

A. Put a MAGNETIC COMPASS INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Any combination of three gyros or INS (IRU) stabilized compass systems must be verified as operative after start unless airplane will be operated under positive radar control by ATC for enroute portion of flight

B. In addition, flight in areas of magnetic unreliability require the use of free gyro navigation techniques as described in the Operating Manual (PSP 601-4).



Airplane: CL 601


NAVIGATION


2 Number Installed

1


34 NAVIGATION

34−28−1 Standby Attitude Indicator

B

0



a) Operations are conducted in day VMC only,

b) Operations are not conducted into known or forecast over-the-top conditions.

1. PLACARD

A. Put a STANDBY ATTITUDE INDICATOR INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601


NAVIGATION

System & Item 1

Sequence Numbers

2 Number Installed

1


34−40−1 Windshear Alert System D

0


May be inoperative provided alternate procedures below are used

1. PLACARD

A. Put a WINDSHEAR ALERT SYSTEM INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Flight crew must maintain awareness of airplane configuration, altitude and flight path for Terrain Avoidance and Windshear Avoidance / Recovery. This may include flight crew use of all airplane systems available (autopilot, ILS, FMS) and flight crew review of Minimum Enroute Altitudes and Altitude Callouts.

B. PNF must monitor flight path during takeoff, approach and landing and alert the pilot

flying if any of the following possible windshear conditions exist:

- Excessive descent rate. - Excessive terrain closure rate. - Altitude loss after takeoff or go-around. - Unsafe terrain clearance while in landing mode. - Deviation from glideslope.



Airplane: CL 601


NAVIGATION

System & Item 1

Sequence Numbers

2 Number Installed

1


34−41−1 Weather Radar System C

0


May be inoperative provided no hazardous weather conditions or thunderstorms are forecast in the area of the planned route.

1. PLACARD

A. Put a WEATHER RADAR SYSTEM INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601


NAVIGATION

System & Item 1

Sequence Numbers

2 Number Installed

2

2


34−42−1 Radio Altimeter C Systems

A

1

0



a) Radio altitude data is either available to, or not required by other required systems, and

b) Approach minimums or operating procedures are not dependent on its use.


a) Alternate procedures are

established and used, and

b) Repairs are made within two flight days.

NOTE 1: Radio altitude data is required for Autopilot, Flight Director System, TCAS, GPWS (TAWS).

1. PLACARD

A. Put a RADIO ALTIMETER SYSTEMS INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Monitor and cross check flight instruments for possible miscompares. PNF to set minima + 50 ft for all instrument approaches and announce “50 to go”.



Airplane: CL 601


NAVIGATION

System & Item 1

Sequence Numbers

2 Number Installed

1


34−42−2 Terrain Awareness and

Warning System (TAWS) / Ground Proximity Warning System (GPWS)

1. GPWS/TAWS A

0

4 Remarks or Exceptions (O) May be inoperative provided:

a) Alternate procedures below are used, and

b) Repairs are made within two (2) flight days.

1. PLACARD

A. Put a GPWS/TAWS INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)



flying if any of the following conditions exist:




Airplane: CL 601


NAVIGATION

System & Item 1

Sequence Numbers

2 Number Installed

4




1. GPWS/TAWS

a. Modes 1−4 A

0



a) Alternate procedures below are used, and


1. PLACARD

A. Put a GPWS/TAWS MODES 1−4 INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)







Airplane: CL 601


NAVIGATION

System & Item 1

Sequence Numbers

2 Number Installed

1




1. GPWS/TAWS

b. Test Mode A

0



a) GPWS/TAWS is considered inoperative, and


1. PLACARD

A. Put a GPWS/TAWS TEST MODE INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601


NAVIGATION

System & Item 1

Sequence Numbers

2 Number Installed

1



Warning System (TAWS) / Ground Proximity Warning System (GPWS

1. GPWS/TAWS

d. Advisory Callouts B

(Mode 6)

0



1. PLACARD

A. Put a GPWS/TAWS ADVISORY CALLOUT INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Flight crew must maintain awareness of airplane configuration, altitude and flight path for Terrain Avoidance and Windshear Avoidance / Recovery. This may include flight crew use of all airplane systems available (autopilot, ILS) and flight crew review of Minimum Enroute Altitudes and Altitude Callouts.






Airplane: CL 601


NAVIGATION

System & Item 1

Sequence Numbers

2 Number Installed

1

1




1. GPWS/TAWS

e. Windshear Mode B (Reactive)

C

0

0



NOTE: Operator’s alternate procedures include reviewing windshear avoidance and windshear recovery procedures.


a) Alternate procedures below are

used, and

b) Windshear Detection and Avoidance System (Predictive) operates normally.

1. PLACARD

A. Put a GPWS/TAWS WINDSHEAR MODE INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Crew briefings will include aural callouts through use of appropriate airplane

equipment i.e., airspeed, IVSI etc., and available weather reports for detection and prompt resolution of windshear encounter.

B. Crew briefing must also include review windshear avoidance and windshear recovery procedures.



Airplane: CL 601


NAVIGATION

System & Item 1


1


34 NAVIGATION



2. Terrain System − B Forward Looking Terrain Avoidance (FLTA) and Premature Descent Alert (PDA) Functions

0

4 Remarks or Exceptions (O) May be inoperative provided alternate

procedures below are used.

1. PLACARD

A. Put a GPWS/TAWS FLTA/PDA FUNCTIONS INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Flight crew must maintain awareness of airplane configuration, altitude and flight path on descent and review Minimum Enroute Altitudes and Altitude Callouts prior to descent.



Airplane: CL 601


NAVIGATION

System & Item 1

Sequence Numbers

2 Number Installed

1




3. Terrain Displays B

0


1. PLACARD

A. Put a GPWS/TAWS TERRAIN DISPLAYS INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601


NAVIGATION



1


34 NAVIGATION

0


(M) May be inoperative provided;

a) the system is deactivated and secured,

b) enroute or approach procedures do not require its use.

34−43−1 Traffic Collision B

Avoidance System 2) TCAS II

1. PLACARD

A. Put a TCAS INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Open and collar the circuit breaker that follows:


CBP−A ---- TCAS 38

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601


NAVIGATION

System & Item 1


2


34 NAVIGATION

34−43−1 Traffic Collision

Avoidance System (TCAS)

2)a) Combined Traffic Alert (TA) and Resolution Advisory (RA) Dual Displays

C

1


(O) One may be inoperative on the

non−flying pilot side provided TA and RA visual display and audio functions are operative on flying pilot side.

1. PLACARD

A. Put a TCAS INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Make sure that TA and RA elements and audio functions are operative on Pilot Flying side.



Airplane: CL 601


NAVIGATION



2

2


1

0


May be inoperative on the non−flying pilot side.


a) All TA visual display and audio functions are operative, and

b) TA only mode is selected by the crew, and

c) Enroute or approach procedures do not require its use.



2)b) . RA Display System(s) C

C

1. PLACARD

A. Put a RESOLUTION ADVISORY (RA) TCAS DISPLAY SYSTEM INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Make sure that all TA display elements and voice command audio functions are operative.

B. Select TA mode only.

C. Monitor the operative indications and advisories and respond as appropriate



Airplane: CL 601


NAVIGATION



2


34 NAVIGATION

0


(O) May be inoperative provided,

a) all installed RA visual display and audio functions are operative, and

b) enroute or approach procedures do not require its use.



2)c) . TA Display System(s)

C

1. PLACARD

A. Put a TA DISPLAY SYSTEMS INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Make sure that all installed RA display and audio functions are operative.

B. Monitor the operative indications and advisories and respond as appropriate



Airplane: CL 601


NAVIGATION

System & Item 1


2

2


34 NAVIGATION

34−50−1 Long Range Navigation C Systems (GPS)

D

1

0



a) Affected system is not required for attitude or heading source, and

b) System is not required for the operation conducted.

May be inoperative provided routine procedures do not require its use.

1. PLACARD

A. Put a LONG RANGE NAVIGATION SYSTEMS INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601


NAVIGATION

System & Item 1

Sequence Numbers

2 Number Installed

2


34−51−1 VHF Navigation C Systems (VOR / ILS)

0


May be inoperative provided approach minimums are not dependent on its use.

Note: May be required for FMS

1. PLACARD

A. Put a VHF NAVIGATION SYSTEMS INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601


NAVIGATION

System & Item 1

Sequence Numbers

2 Number Installed

2


34−51−2 Marker Beacon C Systems

0


May be inoperative provided approach minimums do not require use of affected system.

1. PLACARD

A. Put a MARKER BEACON SYSTEMS INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601


NAVIGATION


2 Number Installed

5


34 NAVIGATION

34−51−3 NAV / COM

1. Preselect Tuning C

0


May be inoperative provided direct tuning mode is operative.

1. PLACARD

A. Put a PRESELECT TUNING INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601


NAVIGATION


2 Number Installed

5


34 NAVIGATION

34−51−3 NAV / COM

2. Memory Channels C

0


May be inoperative provided direct tuning mode is operative.

1. PLACARD

A. Put a MEMORY CHANNELS INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601


NAVIGATION


2 Number Installed

2


34 NAVIGATION

34−51−4 Radio Magnetic Indicators (RMIs)

C

0


One or both may be inoperative provided both HSIs are operative.

1. PLACARD

A. Put a RADIO MAGNETIC INDICATORS INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601


NAVIGATION

System & Item 1

Sequence Numbers

2 Number Installed

2


34−52−1 Automatic Direction C Finding (ADF) Systems

0


One or more may be inoperative provided navigation procedures for the planned routes to be flown are not dependent upon the use of affected ADF.

1. PLACARD

A. Put an AUTOMATIC DIRECTION FINDING SYSTEMS INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601


NAVIGATION


2 Number Installed

2


34 NAVIGATION

34−53−1 Distance Measuring D Equipment (DME) Systems

0



a) Procedures are not dependent on its use, and

b) FMS accuracy without DME update is acceptable for the intended operation

1. PLACARD

A. Put a DISTANCE MEASURING EQUIPMENT SYSTEMS INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601


NAVIGATION

System & Item 1

Sequence Numbers

2 Number Installed

2


34−54−1 Air Traffic Control (ATC) B Transponders and Automatic Altitude Reporting Systems

1



a) Operations do not require its use; and

b) Prior to flight, approval is obtained from ATC facilities having jurisdiction over the planned route of flight

NOTE: Transponder and Flight Director / Autopilot must use same ADC data for RVSM Operations.

1. PLACARD

A. Put an ATC TRANSPONDERS AND AUTOMATIC ALTITUDE REPORTING SYSTEM INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601


NAVIGATION

System & Item 1

Sequence Numbers

2 Number Installed

2


34−54−2 Remote Transponder D Ident Buttons

0


(M)(O) Any or all may be inoperative provided:

a) IDENT button had not faulted to the ON condition, and

b) IDENT button on Transponder Control Unit / RTU is operative.

1. PLACARD

A. Put a REMOTE TRANSPONDER IDENT BUTTONS INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Confirm IDENT button had not faulted to the ON condition, and

B. Confirm IDENT button on Transponder Control Unit / RTU is operative.

3. OPERATIONS (O)

A. Flight crew to verify ATC transponder (34-54-1) is operative.



Airplane: CL 601


NAVIGATION

System & Item 1

Sequence Numbers

2 Number Installed

1


34−60−1 Datanav System C

0



a)…...Procedures below are used that do not require use of affected system, and

b) Approved checklists are carried in cockpit

1. PLACARD

A. Put a DATANAV SYSTEM INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Use Operating Manual procedures and checklists for all operations.



Airplane: CL 601


NAVIGATION

System & Item

Sequence Numbers


2


34 NAVIGATION

0


(O) Except when enroute operations require its use, may be inoperative provided alternate means for initializing the INS is available. (AFM Supplement 31)

34−61−1 Flight Management

Systems (FMS)

C

1. PLACARD

A. Put a FLIGHT MANAGEMENT SYSTEMS INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. MNPS operations not permitted.

B. Enroute operations must be conducted using normal INS and radio aid procedures.

C. Refer to AFM Supplement 31 for initializing procedure for INS



Airplane: CL 601


NAVIGATION

System & Item 1

Sequence Numbers

2 Number Installed

2


34−61−1 Flight Management Systems (FMS)

7. Navigation Databases C

0


(O) Except when enroute operations

require its use, may be out of currency provided:

a) Current Aeronautical Charts are used to verify Navigation Fixes prior to dispatch,

b) Procedures below are used to verify status and suitability of Navigation Facilities used to define route of flight, and

c) Approach Navigation Radios are manually tuned and identified.

1. PLACARD

A. Put a NAVIGATION DATABASES INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Check NOTAMS and charts against the out-of-date navigation database.

B. Manually input route structure, if needed.



Airplane: CL 601


OXYGEN

System & Item 1


1

3 Number Required for Dispatch 35 OXYGEN

35−10−1 Crew Oxygen Pressure B Gauge

0


(M) May be inoperative provided both the fill point gauge and the bottles mounted gauge are checked prior to each flight.

1. PLACARD

A. Put a CREW OXYGEN PRESSURE GAUGE INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

Before flight:

A. Check oxygen pressure reading on the oxygen bottle and on the ground servicing pressure gauge. Pressure readings must be within ±4% of each other.

B. Oxygen quantity must be adequate before each departure.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601


OXYGEN

System & Item 1

Sequence Numbers

2 Number Installed

1


35−20−1 Passenger Oxygen B System

0



a) All components of the cabin pressurization, warning and indicating systems are operative;

b) Operations are conducted so that Minimum en route altitude (MEA) does not exceed 13,020 ft MSL,

c) Operations are conducted at or below FL 250,

d) Portable oxygen units are provided for all crew members and 10% of the passengers for half an hour (supplemental oxygen),

e) Procedures below are used to ensure that passengers are appropriately briefed to accommodate revised equipment.

f) Both Air Conditioning Packs are verified operative,

1. PLACARD

A. Put a PASSENGER OXYGEN SYSTEM INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. PIC to brief the passengers as to the revised equipment.

B. Make sure that both air conditioning packs are operative (Refer to AIRPLANE FLIGHT MANUAL − NORMAL PROCEDURES − AIR−CONDITIONING AND PRESSURIZATION).

C. Refer to FCOM Supplement regarding oxygen endurance.



Airplane: CL 601


OXYGEN

System & Item 1

Sequence Numbers

2 Number Installed

16

16


35−20−1 Passenger Oxygen System

1). Cabin Passenger B Oxygen Drop Out panels

B

0

0


(M)(O) May be inoperative provided passenger Oxygen System is considered inoperative

(M) May be inoperative with no flight altitude restriction provided:

a) Affected seats are blocked and placarded to prevent occupancy,

b) No more than two consecutive banks of seats and their adjacent banks of seats have inoperative PSU, and

c) Units operate normally for all flight attendant locations.

1. PLACARD

A. Put a PSU INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Secure the unserviceable PSU as follows:

(1) If the door does not remain closed, use adhesive tape to secure it.

(2) Rope, tie, or otherwise block the seats with the unserviceable units against passenger use. Do likewise if unserviceable unit is in lavatory.

3. OPERATIONS (O)

A. Comply with item 35-20-1 if Passenger Oxygen System considered inoperative.

B. Otherwise PIC to brief flight attendant(s) (if carried) or passengers (if flight attendant(s) not carried) that seats which have a PSU inoperative placard are not to be used.

C. Passengers to be briefed on oxygen mask access. D. Assigned flight attendant to locations which are operative.



Airplane: CL 601


OXYGEN

System & Item 1


1


35 OXYGEN


2) Lavatory Oxygen B Drop Out System

0


(O) May be inoperative provided the procedures below are used to block the lavatory when the airplane is above FL250:

1. PLACARD

A. Place an TOILET COMPARTMENT PASSENGER OXYGEN DROP OUT PANEL INOPERATIVE placard on the lavatory door

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. When the airplane is planned to operate above FL 250,

(1) Use the lavatory door lock to block off access, and

(2) Do not use for any purpose, and

(3) Brief passengers well in advance of departure if possible.



Airplane: CL 601


OXYGEN

System & Item 1


1


35 OXYGEN


3) Pressure Gauge B

0


(M) May be inoperative provided the fill point gauge and bottle mounted gauge are checked before each take-off

1. PLACARD

A. Put a PASSENGER OXYGEN SYSTEM PRESSURE GAUGE INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

Before flight:

A. Check oxygen pressure reading on the oxygen bottle and on the ground servicing pressure gauge. Pressure readings must be within ±4% of each other.

B. Oxygen quantity must be adequate before each departure.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601


OXYGEN




Airplane: CL 601


PNEUMATIC

System & Item 1

Sequence Numbers

2 Number Installed

2

3 Number Required for Dispatch 36 PNEUMATIC

36−10−1 Engine Bleed Air SOVs C (14th Stage)

1



a) Affected valve is secured CLOSED,


c) Associated Thrust Reverser is deactivated (78-30-1), stowed and locked in forward thrust position,

d) Airplane is not operated in known or forecast icing conditions,

e) Airplane is operated at or below FL 402, and

f) Wing Anti−Ice Isolation Valve is operative.

1. PLACARD

A. Put an ENGINE BLEED AIR SOVs INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Secure the affected SOV in the closed position as follows:

(1) Connect the external electrical power to the airplane.

(2) Open the rear equipment bay access door 311BB.

(3) In the rear equipment bay, install the streamer and the blanking cap (G601R301021–9, part of G601R301021–1 bleed air leak test kit) in the anti-ice bleed-air duct, upstream (outboard) of the affected shutoff valve.

(4) Deactivate the left or right thrust reverser, refer to AIRPLANE MAINTENANCE MANUAL, TASK 78−30−02.

B. Close the rear equipment bay access door 311BB.

C. Remove the external electrical power from the airplane.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601


PNEUMATIC


2 Number Installed

2


36 PNEUMATIC

36−20−1 Bleed Air Pressure Indicators (LH & RH)

2. 10th Stage C

1


(O) One may be inoperative provided

bleed air pressure is checked to be available from both engines.

1. PLACARD

A. Put a BLEED AIR PRESSURE INDICATORS INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. With APU operating:

a) On the APU CONTROL panel BLEED AIR switch/light ......................................Press in OPEN light on.

b) On the BLEED AIR control panel, 10th STAGE ISOL switch/light ............................ Press in OPEN light on.

c) ACU R switch/light.................................... Press in Check conditioned air available in cabin and flight compartment and the remaining bleed air pressure readout registers pressure.

B. With both engines operating:

a) On the BLEED AIR Control panel, 10th STAGE ISOL switch/light ...................... Press in OPEN light on.

b) 10th Stage L switch/light.............................Press in Bleed CLOSED light out. Check operation and bleed air pressure readout on BLEED AIR pressure gauge registers pressure



Airplane: CL 601


PNEUMATIC

c) 10th Stage L switch/light..............................Press out Bleed CLOSED light on.

d) Any ACU switch/light Press in ACU light out. Remaining pressure readout registers 0 pressure

e) Applicable ACU switch/light Press out ACU OFF light on

f) 10th Stage Rswitch/light .............................Press in Bleed CLOSED light out.

Check operation and bleed air pressure readout on BLEED AIR pressure gauge registers pressure.



Airplane: CL 601


PNEUMATIC

System & Item 1

Sequence Numbers

2 Number Installed

2

3 Number Required for Dispatch 36 PNEUMATIC

36−23−1 Bleed Air Overheat Sensing Loops A and B

C

1


Either loop A or B may be inoperative provided a) Remaining loop is operative, and b) DUCT MON switch is selected to

operative loop position.

1. PLACARD

A. Put a BLEED AIR OVERHEAT SENSING LOOPS INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601


WATER/WASTE

System & Item 1

Sequence Numbers

2

Number Installed

1

1

3 Number Required for Dispatch 38 WATER/WASTE

38−10−1 Potable Water System C

C

0

0


(M) Individual components may be inoperative provided

a) Associated components are deactivated or isolated, and

b) Associated system components are verified not to have leaks.

NOTE: Any portion of system which operates normally may be used.

(M) May be inoperative provided;

a) system is drained, and

b) procedures below are used to ensure the system is not serviced.

1. PLACARD

A. Put a POTABLE WATER SYSTEM INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. May be inoperative provided:

(1) System is drained.

(2) Deactivate or isolate the associated inoperative component(s) as required.

(3) Install placard on the inside of the exterior potable water service panel stating: POTABLE WATER SYSTEM INOPERATIVE – DO NOT SERVICE.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601


WATER/WASTE

System & Item 1

Sequence Numbers

2 Number Installed

1


38−10−2 Lavatory Waste C Systems

0


(M)(O) Associated lavatory systems may be inoperative provided:

a) Waste is drained and system is inspected for leakage,

b) Procedures below are used to deactivate system components, and

c) Lavatory door is locked closed and placarded, “INOPERATIVE − DO NOT ENTER”.

1. PLACARD

A. Put an LAVATORY WASTE SYSTEMS INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Individual components may be inoperative provided;

B. Waste is drained, and system is inspected for leakage.

C. Associated components are deactivated or isolated.

D. Install placard on the inside of the exterior potable water service panel stating: LAVATORY WASTE SYSTEM INOPERATIVE – DO NOT SERVICE.

E. Lock the lavatory door closed.

3. OPERATIONS (O)

A. Flight crew to inspect the locked lavatory periodically.



Airplane: CL 601


WATER/WASTE

System & Item 1

Sequence Numbers

2 Number Installed

1


38−10−3 Lavatory External C Service Cap

0


(M) May be inoperative or missing provided:

a) The waste valve is verified closed prior to each flight, and

b) No leakage can be detected after each servicing.

1. PLACARD

A. Put a LAVATORY EXTERNAL SERVICE CAP INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Drain the waste and inspect the system for leakage.

(1) No leakage is allowed after servicing.

B. Make sure that the waste valve is closed.

C. Use lockwire to secure the waste valve lever closed.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601


WATER/WASTE




Airplane: CL 601


AIRBORNE AUXILIARY POWER

System & Item 1

Sequence Numbers

2 Number Installed

1

3 Number Required for Dispatch 49 AIRBORNE AUXILIARY POWER

49−02−1 APU Bleed Air SOV C (Load Control Valve)

0


(M) May be inoperative CLOSED.

1. PLACARD

A. Put an APU BLEED AIR SOV LOAD CONTROL VALVE INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Secure the APU Load Control Valve in the closed position as follows:

(1) Connect the external AC power to the aircraft.

(2) Make sure that the APU LCV switch/light OPEN light on the BLEED AIR control panel is off.

(3) Disconnect the external AC power from the aircraft.

(4) Open the aft equipment compartment door (311BB).

(5) Gain access to the APU LCV, which is installed between the top of the plenum chamber and the top of the APU enclosure.

(6) Do a visual check of the position indicator on the valve assembly to make sure

that the APU LCV is in the closed position. (7) Disconnect the electrical connector from the LCV solenoid.

(8) Cap and stow the electrical connector.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601





1


49 AIRBORNE AUXILIARY POWER

0


(M) May be inoperative provided RH main

generator (IDG#2) has more than 150 operating hours.

49−02−2 Auxiliary Power Unit

(APU)

C

1. PLACARD

A. Put an APU INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Check installation records to ensure that the serviceable RH main generator (IDG#2) has achieved an operational life in excess of 150 operating hours.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601



System & Item 1

Sequence Numbers

2 Number Installed

1


49−61−1 Electronic Control Unit (ECU)

C

0


(M) May be inoperative provided the APU

is considered inoperative.

1. PLACARD

A. Put an ECU INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Open and tag the circuit breaker(s) that follow:

CB PANEL

CB NO.

NAME

ZONE


CBP−A 154 APU – CONT 221

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601



System & Item 1

Sequence Numbers

2

Number Installed

1


49−70−1 APU Hour Meter C

0


(O) May be inoperative provided the alternate means of recording below is used.

1. PLACARD

A. Put an APU HOUR METER INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Crew to enter the APU running duration in the Technical Log at the completion of each flight.



Airplane: CL 601


DOORS

System & Item 1

Sequence Numbers

2 Number Installed

1

3 Number Required for Dispatch 52 DOORS

52−02−1 Exterior Door Key Locks

1. Passenger Door Key D Lock

0


May be inoperative or missing provided door opens and closes normally.

1. PLACARD

A. Put a PASSENGER DOOR KEY LOCK INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601


DOORS

System & Item 1

Sequence Numbers

2 Number Installed

1



2. Cargo/Baggage Door D Key Lock

0



1. PLACARD

A. Put a CARGO/BAGGAGE DOOR KEY LOCK INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601


DOORS

System & Item 1

Sequence Numbers

2 Number Installed

1



3. Aft−Equipment D Compartment Door Key Lock

0



1. PLACARD

A. Put an AFT−EQUIPMENT COMPARTMENT DOOR KEY LOCK INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601


DOORS

System & Item 1

Sequence Numbers

2 Number Installed

7



4. External Service D Doors Key Locks

0



1. PLACARD

A. Put an EXTERNAL SERVICE DOORS KEY LOCKS INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601


DOORS

System & Item 1

Sequence Numbers

2 Number Installed

1


52−11−1 Passenger Door Manual C Retract Handle

0


May be inoperative provided door is verified manually operative (OPEN and CLOSED) without any interference.

1. PLACARD

A. Put a PASSENGER DOOR MANUAL RETRACT HANDLE INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601


DOORS

System & Item 1

Sequence Numbers

2 Number Installed

1


52 DOORS

52−11−2 Storage Compartment C Door (Main Entry Door)

0


(M) May be inoperative operated:

a) Storage content is relocated, and

b) Door is secured closed.

1. PLACARD

A. Put a STORAGE COMPARTMENT DOOR INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Relocate the contents of the main entry door storage compartment.

B. Make sure that the main entry door storage compartment door is secured closed.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601


DOORS

System & Item

Sequence Numbers


1


52 DOORS

0


(M) May be inoperative provided the door is manual ly ver i f ied operat ive OPEN and CLOSED without any interference.

52−12−1 Main Cabin Door Power C

Assist System

1. PLACARD

A. Put a MAIN CABIN DOOR POWER ASSIST SYSTEM INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Open and close the door manually to ensure there is no interference.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601


DOORS

System & Item 1

Sequence Numbers

2 Number Installed

2


52−30−1 Baggage Door C Counterbalance Systems (balance springs)

0


(M) Both may be inoperative provided baggage door is verified closed, latched, locked and not used.

NOTE: Baggage compartment is accessible through the door located in the aft cabin.

1. PLACARD

A. Put a BAGGAGE DOOR INOPERATIVE placard on both the interior and the exterior of the baggage door.

2. MAINTENANCE (M)

A. Make sure that the baggage door is closed and latched.

B. Make sure that the external handle is seated flush with the door.

C. Put a BAGGAGE DOOR INOPERATIVE – DO NOT OPEN placard on both the interior and the exterior of the baggage door.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601


DOORS


2 Number Installed

1


52 DOORS

52−70−1 Main Cabin Door C Indication System

0



a) All four latches are engaged as indicated by witness marks,

b) Inner Handle is verified stowed,

c) External handle is properly stowed, and verified by dispatch crew,

1. PLACARD

A. Put a MAIN CABIN DOOR INDICATION SYSTEM INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601


DOORS

System & Item 1

Sequence Numbers

2 Number Installed

1


52−70−3 BAG DR UNSAFE C Caution Light

0


May be inoperative provided it can be verified before flight that the door is closed and latched.

1. PLACARD

A. Put a BAG DR UNSAFE CAUTION LIGHT INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)


A. Not required



Airplane: CL 601


POWER PLANT

System & Item 1

Sequence Numbers

2 Number Installed

2

3 Number Required for Dispatch 71 POWER PLANT

71−70−1 Ecology Tank C Ejector Pumps

1


(M) May be inoperative provided procedures below are used to drain tank;

a) before the first flight of each day.

b) after three normal shutdowns, and

c) after two false (wet) starts..

1. PLACARD

A. Put an ECOLOGY TANK EJECTOR PUMPS INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Drain the affected ecology tank as follows:

(1) Remove the tank drain plug and draining fuel into a container. (2) Dispose of the fuel in an approved location. (3) Install the drain plug and secure with lockwire.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601


POWER PLANT




Airplane: CL 601


ENGINE FUEL AND CONTROL

System & Item 1

Sequence Numbers

2 Number Installed

2

3 Number Required for Dispatch 73 ENGINE FUEL AND CONTROL

73−30−1 Fuel Temperature C Indicating Systems

1


One may be inoperative provided icing inhibitor is added to the fuel.

1. PLACARD

A. Put a FUEL TEMPERATURE INDICATING SYSTEMS INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601




2 Number Installed

4


73 ENGINE FUEL AND CONTROL

73−31−1 Fuel Flow Indications B

2


(M) Either vertical scale or digital indication but not both may be inoperative on each side provided:

a) Fuel Quantity Indicating System is operative, and

b) N1, N2 and ITT indications for the associated engine are operative, and

c) Affected digital indicator is covered.

NOTE: Inoperative Fuel Flow Indicating System may cause Fuel Used Indicating System to be inoperative.

1. PLACARD

A. Put a FUEL FLOW INDICATING SYSTEMS INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. With the vertical scale or the digital indication, but not both, inoperative on each side, do as follows:

(1) Cover the affected digital indicator with tape.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601



System & Item

Sequence Numbers


28



14


(O) May be inoperative provided no two adjacent lamps on the affected scale are inoperative

73−31−1 Fuel Flow Indicating

Systems

1. Left Vertical Scale C Lamps

1. PLACARD

A. Put a LEFT VERTICAL SCALE LAMPS INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. On the engine instrument control panel, do the lamp test.

B. Make sure that no two adjacent lamps on the affected scale are inoperative.

C. Monitor engine parameters more frequently than on a regular flight.



Airplane: CL 601



System &Item

Sequence Numbers


28



14


a) May be inoperative provided no two adjacent lamps on the affected scale are inoperative

73−31−1 Fuel Flow Indicating

Systems

2. Right Vertical Scale C Lamps

1. PLACARD

A. Put a RIGHT VERTICAL SCALE LAMPS INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. On the engine instrument control panel, do the lamp test.

B. Make sure that no two adjacent lamps on the affected scale are inoperative.

C. Monitor engine parameters more frequently than on a regular flight.



Airplane: CL 601



System & Item 1

Sequence Numbers

2 Number Installed

2

3 Number Required for Dispatch 73 ENGINE FUEL AND CONTROL

73−31−4 Fuel Low Pressure Indication

C

1


One Fuel LOW PRESS Light may be inoperative provided both fuel boost pumps are operative.

1. PLACARD

A. Put a FUEL LOW PRESSURE INDICATION INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601






Airplane: CL 601


IGNITION

System & Item 1


2


74 IGNITION

74−11−1 Ignition Systems

1. A Systems B

1

4 Remarks or Exceptions One may be inoperative provided:

a) Both B Systems are operative, and

b) Take−off in heavy precipitation, or on a runway surface covered with standing water, slush or snow is prohibited.

1. PLACARD

A. Put an IGNITION SYSTEMS INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601


IGNITION

System & Item 1


2


74 IGNITION

74−11−1 Ignition Systems

2. B Systems B

0



a) Both A Systems are operative, and

b) Take−off in heavy precipitation, or on a runway surface covered with standing water, slush or snow is prohibited.

1. PLACARD

A. Put an IGNITION SYSTEMS INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601


IGNITION


2 Number Installed

1

1


74 IGNITION

74−11−2 Relight Ignition System C Switch

C

0

0


May be inoperative provided Continuous Ignition Systems A and B modes for both engines are verified operative prior to each flight.

May be inoperative provided In Flight Start Ignition is verified operative on both engines and is used in lieu of relight switch.

1. PLACARD

A. Put a RELIGHT IGNITION SYSTEM SWITCH INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601


IGNITION




Airplane: CL 601


ENGINE CONTROLS

System & Item 1

Sequence Numbers

2 Number Installed

2

3 Number Required for Dispatch 76 ENGINE CONTROLS

76−02−1 Engine Speed Control Systems

C

0


(O) One or both may be inoperative

provided:

a) Both ENG SPEED CONTROL switches are selected OFF,

b) APR is selected OFF,

c) Operations are conducted in accordance with AFM APR inoperative performance data.

1. PLACARD

A. Put an ENGINE SPEED CONTROL SYSTEMS INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

Before Start:

A. Make sure that both engine ENG SPEED CONTROL switches are in the OFF position.

B. Make sure that the APR switch is in the OFF position.

During Starting: A. Monitor the ITT indicator. Refer to AFM, LIMITATIONS, POWER PLANT, ENGINE

OPERATING LIMITS.

NOTE: Disengaging engine speed control will inhibit APR. In-Flight: A. Monitor the ITT indicator. Refer to AFM, LIMITATIONS, POWER PLANT, ENGINE

OPERATING LIMITS.



Airplane: CL 601


ENGINE CONTROLS

System & Item 1


1


76 ENGINE CONTROLS

76−10−1 Automatic Power C Reserve (APR) System

0


May be inoperative in accordance with the performance requirements defined in the AFM applicable to take−off with the APR selected OFF.

1. PLACARD

A. Put an APR SYSTEM INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601


ENGINE INDICATING

1. PLACARD

A. Put a LEFT N1 VERTICAL SCALE LAMPS INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Before Flight:

Do the lamp test and make sure of the following: - No two adjacent lamps are inoperative

- The lowest lamp in the red zone is operative

- The highest lamp in the green zone is operative

B. Monitor engine parameters more frequently than on a regular flight.


2 Number Installed

28


77 ENGINE INDICATING

77−10−1 N1 Vertical Scale Indicators

1) Left C

14


(O) One or more lamps may be inoperative provided:

a) No two adjacent lamps are inoperative,

b) The lowest lamp in the red zone and the highest lamp in the green zone are operative,

c) A test is conducted before each flight to determine the inoperative lamps



Airplane: CL 601


ENGINE INDICATING

1. PLACARD

A. Put a RIGHT N1 VERTICAL SCALE LAMPS INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

Before Flight:

A. Do the lamp test and make sure of the following:

- No two adjacent lamps are inoperative

- The lowest lamp in the red zone is operative

- The highest lamp in the green zone is operative



2 Number Installed

28




2) Right C

14




b) The lowest lamp in the red zone and the highest lamp in the green zone are operative,

c) A test is conducted before each flight to determine the inoperative lamps



Airplane: CL 601


ENGINE INDICATING


2 Number Installed

28




2)a) Left C

14




b) The highest lamp in the green zone, the yellow lamp and the lowest lamp in the red zone are operative,

c) A test is conducted before each flight to determine the inoperative lamps, and

d) Engine parameters are monitored during flight.

1. PLACARD

A. Put a LEFT N2 VERTICAL SCALE LAMPS INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

Before Flight:

A. On the engine instrument control panel, do the lamp test and make sure of the following:

− No two adjacent lamps are inoperative

− The highest lamp in the green zone is operative

− The yellow lamp is operative

− The lowest lamp in the red zone is operative.




Airplane: CL 601


ENGINE INDICATING


2 Number Installed

28




2)b) Right C

14




b) The highest lamp in the green zone, the yellow lamp and the lowest lamp in the red zone are operative,


d) Engine parameters are monitored during flight.

1. PLACARD

A. Put a RIGHT N2 VERTICAL SCALE LAMPS INDICATORS INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

Before Flight:


− No two adjacent lamps are inoperative

− The highest lamp in the green zone is operative

− The yellow lamp is operative

− The lowest lamp in the red zone is operative.




Airplane: CL 601


ENGINE INDICATING


2 Number Installed

4



77−20−1 ITT Indicators B

2


Either the digital or the vertical scale indicators, but not both, may be inoperative for each engine.

NOTE: If starting with DC Electrical Power Only:

1. When the Right Engine Digital ITT Indication is inoperative, a Left Engine start must be accomplished first.

2. When the Left Engine Vertical Scale ITT Indication is inoperative, a Right Engine start must be accomplished first.

1. PLACARD

A. Put an ITT INDICATORS INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601


ENGINE INDICATING


2 Number Installed

28



77−20−1 ITT Indicators


a. Left B

14



a) No two adjacent lamps may be inoperative,

b) The lowest lamp in the red zone and highest lamp in the yellow zone are operative,


1. PLACARD

A. Put a LEFT VERTICAL SCALE LAMPS INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

Before Flight:


– No two adjacent lamps are inoperative

– The lowest lamp in the red zone is operative.

– The highest lamp in the yellow zone is operative




Airplane: CL 601


ENGINE INDICATING


2 Number Installed

28



77−20−1 ITT Indicators


b. Right B

14



a) No two adjacent lamps may be inoperative,

b) The lowest lamp in the red zone and the highest lamp in the yellow zone are operative,


1. PLACARD

A. Put a RIGHT VERTICAL SCALE LAMPS INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

Before Flight:


– No two adjacent lamps are inoperative

– The lowest lamp in the red zone is operative.

– The highest lamp in the yellow zone is operative




Airplane: CL 601


ENGINE INDICATING


2 Number Installed

1



77−20−2 DGT OFF Switch C

0


(M) May be inoperative in the ON position provided any inoperative digital indicator is covered.

1. PLACARD

A. Put a DGT OFF SWITCH INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. With the DGT OFF switch inoperative in the ON position, cover the applicable digital indicator(s) with tape

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601


ENGINE INDICATING

System & Item 1

Sequence Numbers

2 Number Installed

2

3 Number Required for Dispatch 77 ENGINE INDICATING

77−30−1 Engine Vibration B Monitor

1



a) Flight is not conducted in known or forecast icing conditions, and

b) One Ice Detection System is operative.

1. PLACARD

A. Put an ENGINE VIBRATION MONITOR INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Not required.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601


ENGINE INDICATING




Airplane: CL 601


EXHAUST

1. PLACARD

A. Put a THRUST REVERSER SYSTEMS INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Make sure that the affected thrust reverser does not have any structural damage other than cracks in the cascades. A maximum of 25% of the vanes in a bay may have cracks.

B. Do a deactivation of the affected thrust reverser (refer to AIRPLANE MAINTENANCE MANUAL, TASK 78−30−02−040−801).

NOTE:Cracks in the cascades must be repaired or the cascades replaced before the affected thrust reverser is activated.

3. OPERATIONS (O)

A. Not required.


2 Number Installed

2


78 EXHAUST

78−30−1 Thrust Reverser C Systems

1



a) Affected Thrust Reverser does not have structural damages other than cracks in the cascades,

b) Affected Thrust Reverser is deactivated and secured,

c) Nosewheel Steering System is operative,

d) For Take−off on wet or contaminated runways and landing on contaminated runways, operations are conducted in accordance with AFM Supplement 2 (Operations on Contaminated Runways.)

NOTE: Cracks in the cascades must be repaired or the cascades replaced before the affected thrust reverser is activated.



Airplane: CL 601


EXHAUST




Airplane: CL 601


ENGINE OIL

System & Item 1


1


79 ENGINE OIL

79−12−1 Oil Replenishment C System

0


(M) One may be inoperative provided alternate methods below for checking engine oil levels and servicing engine oil are used

1. PLACARD

A. Put an OIL REPLENISHMENT SYSTEM INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. Oil quantity is checked prior to dispatch as follows:

(1) Engine oil tank levels have been verified on the oil tank level sight gauges within the permissible time interval.

OR

(2) Do a visual check of the oil level on the left and right engine oil tanks by removing the filler cap and checking the dipstick within the permissible time interval.

B. If found low, engine oil tank levels must be refilled manually to the oil tank full level. Make sure that there is no evidence of excessive consumption or leakage.

3. OPERATIONS (O)

A. Not required.



Airplane: CL 601


ENGINE OIL


2 Number Installed

2


79 ENGINE OIL

79−30−1 Oil Low Pressure Indicator Lights B

1


(M) One may be inoperative provided the procedures below are used to ensure that indicator light is either extinguished or blanked

1. PLACARD

A. Put an OIL LOW PRESSURE INDICATOR LIGHTS INOPERATIVE placard on the instrument panel.

2. MAINTENANCE (M)

A. The indicator light must be blanked

3. OPERATIONS (O)

A. Not required.

Documents

MINIMUM EQUIPMENT LIST CANADAIR CHALLENGER CL 601 T7- …