MODEL CL−600−2A12 AIRPLANE FLIGHT MANUAL PSP 601−1A−1 · 2012. 6. 27. · canadair chailenqer MODEL CL-600-2A12 AIRPLANE FLIGHT MANUAL PSP 601-1A-1 LIST OF ILLUSTRATIONS £12Numbe"r

DOT ApprovedSep 11/0644,600/45,100

LIMITATIONS

− CONTENTSPage i

LIMITATIONS

TABLE OF CONTENTS

Page

1. STRUCTURAL WEIGHT LIMITATION 1. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

2. CENTRE OF GRAVITY (LIMITS) 2. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

3. OPERATING LIMITATIONS 4B. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

A. Types of Operation 4B. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . B. Altitude and Temperature Operating Limits 4B. . . . . . . . . . . . . . . . . . . . . . . . . C. Runway Surface 4B. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . D. Runway Slopes 6. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . E. Tailwind Conditions 6. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . F. Minimum Flight Crew 6. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . G. Maximum Occupants 6. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . H. Operation in Icing Conditions 6A. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . I. Cold Weather Operations 6C. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

4. POWER PLANT LIMITATIONS 7. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

A. Engines 7. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . B. Engine Operating Limits 7. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . C. Automatic Performance Reserve (APR) 8. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . D. Oil Temperature 8. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . E. Oil Pressure 8. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . F. Engine Airstart 8. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . G. Air Turbine Starter 8. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . H. Fuel Temperature 10. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . I. Fuel Grades 10. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . J. Fuel Additives 11. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . K. Oil Grades 12. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . L. Oil Replenishment System 12. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . M. Auxiliary Power Unit (APU) Operating Limits 12. . . . . . . . . . . . . . . . . . . . . . . N. Power Plant Instrument Markings 15. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

5. MAXIMUM OPERATING LIMIT SPEEDS 17. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

A. Maximum Operating Speed (VMO) and Mach Number (MMO) 17. . . . . . . . . . . . . . . . B. RVSM Maximum Operating Speed 17. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . C. Design Manoeuvering Speed (VA) 17. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . D. Flaps Extended Speed (VFE) 19. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . E. Maximum Landing Gear Operating Speed (VLO) 19. . . . . . . . . . . . . . . . . . . . . . . . . F. Maximum Landing Gear Extended Speed (VLE) 19. . . . . . . . . . . . . . . . . . . . . . . . . . G. Tire Limit Speed 19. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . H. Maximum Airspeed for ADG Operation 19. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . I. Turbulence Penetration Speed 19. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

MODEL CL−600−2A12

AIRPLANE FLIGHT MANUAL

PSP 601−1A−1

DOT ApprovedJan 30/07

44,600/45,100

LIMITATIONS

− CONTENTSPage ii

Page

6. MINIMUM OPERATING LIMIT SPEED 20. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

7. MANOEUVERING LIMIT LOAD FACTORS 20. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

8. SYSTEMS LIMITATIONS 21. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

A. Air Conditioning and Pressurization (Structural Limitations) 21. . . . . . B. Automatic Flight Control System 21. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . C. Electrical Systems 22. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . D. Flight Controls − Lift/Drag Devices 25. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . E. Fuel System 26. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . F. Stall Protection System 27. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . G. NOT USED 28. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . H. NOT USED 28. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . I. NOT USED 28. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . J. Wheel Brake Cooling Limitations 28. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . K. Wheel Brakes Anti-Skid 28. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . L. Bleed Air Systems 28. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . M. NOT USED 28. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . N. Tire Pressures 28. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . O. Thrust Reversers 31. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . P. Taxi Lights 31. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Q. Air Data System 31. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

9. CONFIGURATION DEVIATION LIST 31. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

LIST OF ILLUSTRATIONS

Figure Title PageNumber

1 Centre of Gravity Limits 3. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

1A Centre of Gravity Limits (A/C incorporating Service Bulletin 601-0360) 4. . . . . . . . . . . . . . . . . . . . .

2 Altitude and Temperature Operating Limits 5. . . . . . . . . . . . . . . . . . . . . . . . .

3 Start Envelope 9. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

4 APU In-Flight Envelope (Airplanes NOT incorporating Service Bulletin 601-0568 or 601−0581) 14A. . . . . . . . . . . . . . . . . . . . . . . . . .

4A APU In-Flight Envelope (Airplanes incorporating Service Bulletin 601-0568 or 601−0581) 14B. . . . . . . . . . . . . . . . . . . . . . . . . .

5 Design Manoeuvering Speed − VA 18. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

6 Maximum Permissible Loads on DC Electrical System − Ground Operation 23. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .



PSP 601−1A−1

canadairchailenqer

MODEL CL-600-2A12AIRPLANE FLIGHT MANUAL

PSP 601-1A-1

LIST OF ILLUSTRATIONS

£12" Title PageNumber

Maximum Permissible Loads on DC Electrical System -Ground Operation - Airplanes 3051 and Subsequent andAirplanes Incorporating Canadair ServiceBulletin 601-0107 24

Tire Pressures vs Maximum Take-Off Weight (MTOW)(25.75 x 6.75 - 14 PR Tires) 29

Tire Pressures vs Maximum Take-Off Weight (MTOW)(A/C incorporating Service Bulletin 601-0360)(25.75 x 6.75 - 14 PR Tires) 30

DOT Approved LIMITATIONSSep 25/90 - CONTENTS44,600 Page i i i

canatiairchaneriQer


PSP 601-1A-1

LIMITATIONS

Observance of the limitations contained within the LIMITATIONS section of theAirplane Flight Manual is mandatory.

1. STRUCTURAL HEIGHT LIMITATION

45,250 1b (20,525 kg) (see NOTE 2)Maximum taxi and ramp weight: 44,750 lb (20,298 kg) (see NOTE 1) I

Maximum take-off weight: 44,600 lb (20,230 kg) (see NOTE 1) I

45,100 lb (20,457 kg) (see NOTE 2) |

Maximum landing weight: 36,000 lb (16,329 kg)

Maximum zero fuel weight: 31,000 lb (14,061 kg)

Minimum f l i gh t weight: 25,000 lb (11,340 kg)N O T E

1. Canadair Service Bulletin 601-0280, must beincorporated for airplane to operate at themaximum taxi and ramp weight of 44,750 lb I(20,298 kg) and at the maximum take-off |weight of 44,600 lb (20,230 kg).

2. Canadair Service Bulletin 601-0360,Modification - Increased MTOH - 45,100 lb,must be incorporated to operate at themaximum taxi and ramp weight of 45,250 lb(20,525 kg) and at the maximum take-offweight of 45,100 lb (20,457 kg).

3. The maximum take-off weight (MTOW) and/ormaximum landing weight (MLH) may be furtherlimited due to tire pressures, brake kineticenergy, tire limit speeds and/or performanceconsiderations (refer to LIMITATIONS - TIREPRESSURES, NORMAL PROCEDURES andPERFORMANCE).

DOT ApprovedSep 25/90 LIMITATIONS44,600 Page 1

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PSP 601-1A-1

CENTRE OF GRAVITY (LIMITS)

The maximum permissible centre of gravity (CG) range with landing gear extendedis shown in Figure 1 and Figure 1A. The airplane must be loaded in accordancewith the loading instructions associated with the Weight and Balance Report,Reference RAW-601-***, pertaining to the particular aircraft. The effect oflanding gear retraction on CG position is negligible.

***Each report is identified by the airplane serial number.

LIMITATIONS TPage 2 44,600

canadair

MODEL CL-600-2A12


PSP 601-1A-1

CENTRE OF GRAVITY LIMITS

MILLIMETRES AFT OF DATUM

46

45

44

43.

42.

41.

40.

39.

38

37.CD

. 36.

2 35.l

?34o

* 3 3

32.

31,

30.

29.

28

27.

26

25

24

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ftC

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MA

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12929INCH!

50 LE

600 L

.AND If

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12979

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511

- 20

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10 36C

> FUEL

FLICK

13030OF D

513

298 K

)230 >

00 LB

3100

T 250

13081ATUM

515

5 29.f

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- 16,

0 LB •

00 L6

1313,

517

. X

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52:

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20.0

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16

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o§I

O

.15.0

14.0

.13.0

.12.0

.11.0

12 14 16 18 20 22 24 26 28 30 32 34 36 38 40X M.A.C.

DOT ApprovedNov 07/8944,600

Centre of Gravity LimitsFigure 1 LIMITATIONS

Page 3

canadairchanencjer


PSP 601-1A-1

CENTRE OF GRAVITY LIMITS

46

44

43.

42.

41

40.

39.

38

37CD

8- 35

5 34.

32

31

30

29

28

27

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IM

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,14.0

.13.0

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.11.0

12 14 16 18 20 22 24 26 28 30 32 34 36 38 40X M.A.C.

LIMITATIONSPage 4

Centre of Gravity Limits(A/C incorporating Service Bulletin 601-0360)

Figure 1ADOT Approved

Sep 25/9044,600


PSP 601-1A-1

THIS PAGE INTENTIONALLY LEFT BLANK

DOT ApprovedSf 25/90 LIMITATIONS44,600 P a g e 4 A


PSP 601-1A-1

3. OPERATING LIMITATIONS

A. TYPES OF OPERATION

This airplane is certificated in the transport category and is eligiblefor the following kinds of operations when the appropriate instrumentsand equipment required by the airworthiness and/or operating certificateare installed and approved and are in operable condition.

Day and nightVFRIFRIcing conditions

On airplanes incorporating Canadair Service Bulletin 601-0484, ReducedVertical Separation Minimum (RVSM) - 1000 Ft. Aircraft QualificationRequirements:This airplane is certificated capable of RVSM operations in accordancewith FAA "Interim guidance material on the approval of operations/aircraft for RVSM operations", 91-RVSM, dated March 14, 1994.

NOTE

Compliance with the standard noted above doesnot constitute RVSM operational approval.

B. ALTITUDE AND TEMPERATURE OPERATING LIMITS

Maximum airport pressure altitude for take-off and landing is10,000 feet.Maximum operating altitude is 41,000 feet.

Maximum air temperature approved for take-off and landing is ISA +35°C(+50°C (122°F)).Minimum temperature approved for take-off is -40°C (-40°F).

When the ambient temperature is -30°C (-22°F) or below, the engines mustbe motored for 60 seconds and the fan must rotate before engine start isinitiated.

C. RUNWAY SURFACE

Both igniters on both engines must be on continuously for take-off andlanding on runway surfaces covered with standing water, slush or snow orin icing conditions.

DOT ApprovedLIMITATIONS fl Mar 27/97Page 4B 44,600/45,100

nr MODEL CL-600-2A12

AIRPLANE FUGHT MANUAL PSP 601-1A-1

TAHEO. UllDffllG UMBS

-80- -fe-AMBIENT ERATURE

v—'—r l—'—nr •100 -80 - 6 0 - 4 0 - 2 0 0 20 40 60 80 100 120 140

AMBIENT TEMPERATURE - °F

DOT Approved Oct 28/96 44,600/45,100

Altitude and Temperature Operating Limits Figure 2 LIMITATIONS

Page 5

canadairchanenqer


PSP 601-1A-1

3. OPERATING LIMITATIONS (Cont'd)

D. RUNWAY SLOPES

The maximum runway slopes approved for take-off and landing are:

+2% (uphill)-2% (downhill)

E. TAILWIND CONDITIONS

The maximum tail wind component approved for take-off and landing is 10knots.

F. MINIMUM FLIGHT CREW

The minimum flight crew is one pilot and one copilot.

G. MAXIMUM OCCUPANTS

The total number of occupants, including no more than nineteen passengers,must not exceed the lesser of the following:

(1) Twenty-two or,

(2) The number for which seating accomodation approved for take-off andlanding is provided.

DOT ApprovedLIMITATIONS Apr 21/03Page 6 44,600/45,100

canadairchanenqer


PSP 601-1A-1


H. OPERATION IN ICING CONDITIONS

During cold weather operations, the flight crew must ensure that theairplane fuselage, wings and tail surfaces are free from ice, snow orfrost.

(1) Cowl Anti-ice System

(a) Ground OperationsThe engine cowl anti-ice system must be on when the OAT is 10°C(50°F) or below and visible moisture in any form is present(such as fog with visibility of one mile or less, rain, snow,sleet and ice crystals).The engine cowl anti-ice system must also be on when the OAT is10°C (50°F) or below when operating on runways, ramps, ortaxi ways where surface snow, ice, standing water or slush ispresent.

(b) Flight Operations

NOTEIcing conditions exist in flight at a TAT of10°C (50°F) or below and visible moisture inany form is encountered (such as clouds,rain, snow, sleet or ice crystals), exceptwhen the SAT is -40°C (-40°F) or below.

The engine cowl anti-ice system must be on:

At or above 22,000 feet:• when ice is indicated by the ice detection system, or• when in icing conditions, if an ice detector has failed.

Below 22,000 feet:• when in icing conditions, or• when ice is indicated by the ice detection system.

DOT ApprovedApr 21/03 LIMITATIONS44,600/45,100 P a g e 6 A

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PSP 601-1A-1


H. OPERATION IN ICING CONDITIONS (Cont'd)

(2) Wing Anti-ice System

(a) Ground Operations

The wing anti-ice system must be on for take-off when the OAT is5°C (41°F) or below and visible moisture in any form is present(such as fog with visibility of one mile or less, rain, snow,sleet and ice crystals).

The wing anti-ice system must also be on for take-off when theOAT is 5°C (41°F) or below and the runway is contaminated withsurface snow, slush or standing water.

When Type II, III or IV anti-icing fluids have been applied, thewing anti-ice system must only be selected on, if required, justprior to thrust increase for take-off.

(b) Flight Operations

NOTEIcing conditions exist in flight at a TAT of10°C (50°F) or below and visible moisture inany form is encountered (such as clouds,rain, snow, sleet or ice crystals), exceptwhen the SAT is -40°C (-40°F) or below.

The wing anti-ice system must be on:

At or above 22,000 feet:• when ice is indicated by the ice detection system, or• when in icing conditions, if an ice detector has failed.

Below 22,000 feet:• when in icing conditions, or• when ice is indicated by the ice detection system.

(3) Super-Cooled Large Droplet Icing

Continued operation in areas where super-cooled large droplet (SLD)icing conditions exist is prohibited.

SLD icing conditions are indicated by ice accretion on the flightcompartment side windows.

• The wing anti-icing system must be ON in SLD icing conditions.

• The cowl anti-icing system must be ON in SLD icing conditions.

• Leave icing conditions when side window icing occurs.

DOT ApprovedLIMITATIONS Jan 14/05Page 6B 44,600/45,100


LIMITATIONSPage 6C

3. OPERATING LIMITATIONS (Cont’d)

I. COLD WEATHER OPERATIONS

Take-off is prohibited with frost, ice, snow or slush adhering to anycritical surface (wings, horizontal stabilizer, vertical stabilizer,control surfaces, engine inlets and upper surface of the fuselage).

W A R N I N G

Even small amounts of frost, ice, snow orslush on the wing leading edges and forwardupper wing surface may adversely change thestall speeds, stall characteristics and theprotection provided by the stall protectionsystem, which may result in loss of controlon take-off.

N O T E1. Comprehensive procedures for operating in

cold weather are provided in the OperatingManual Volume 1, SUPPLEMENTARY PROCEDURES,Cold Weather Operations.

2. Take-off is permitted with frost adhering tothe underside of the wing that is caused bycold soaked fuel, in accordance with theinstructions provided in the Operating ManualVolume 1, SUPPLEMENTARY PROCEDURES, ColdWeather Operations, Pre-Flight Preparation,External Safety Inspection.

In addition to a visual check, a tactile check of the wing leading edge,wing forward upper surface and wing rear upper surface is required duringthe Walkaround Check List inspection to determine that the wing is freefrom frost, ice, snow or slush when the outside air temperature (OAT) is5�C (41�F) or less, or it cannot be determined that the wing fueltemperature is above 0�C (32�F); and:

� There is visible moisture (rain, drizzle, sleet, snow, fog, etc); or

� Water is present on the wing; or

� The difference between the dew point temperature and the OAT is3�C (5�F) or less; or

� The atmospheric conditions have been conducive to frost formation.

N O T EIce and frost may continue to adhere to wingsurfaces for some time even at outside airtemperatures above 5�C (41�F).



PSP 601−1A−1

LIMITATIONSPage 6D

DOT ApprovedSep 11/06

44,600/45,100




PSP 601−1A−1

DOT ApprovedJan 30/0744,600/45,100

LIMITATIONSPage 7

4. POWER PLANT LIMITATIONS

A. ENGINES

Type: Two General Electric CF34-1A orTwo General Electric CF34-3A orTwo General Electric CF34-3A2

N O T E

Mixing of CF34-1A, CF34-3A and CF34-3A2engines is permitted.

B. ENGINE OPERATING LIMITS

Condition N1(% rpm)

N2(% rpm)

ITT(�C)

Time Limitfor ITT

Maximum take-off (APR operating) 98.6 99.4 857 5 minutes886 2 minutes

Normal take-off 96.2 98.3 842 5 minutes864 2 minutes

Maximum continuous 98.6 99.2 838 −

Start/relight 930889

16 seconds50 seconds

Minimum idle in icing conditions(cowl anti-ice only)

− 64.0 − −

N O T E

1. The above take-off and maximum continuouslimits for N1, N2 and ITT are engine limitsand are not presented for purposes ofsetting power. The pilot must observe thetake-off and maximum continuous powersettings for the appropriate pressurealtitude, ambient temperature and bleed airextraction as presented in the PERFORMANCEsection of this manual.

2. Above 40,000 feet one ACU or cowl anti-icemust be selected on for each engine.



PSP 601−1A−1


PSP 601-1A-1

4. POWER PLANT LIMITATIONS (Coni/d)

C. AUTOMATIC PERFORMANCE RESERVE (APR)

(1) If take-off performance is predicated upon the use of APR, take-offwith the APR system armed must not be attempted until satisfactorystatic and dynamic APR system tests have been achieved.

(2) The APR system must be selected OFF for take-off if:

(a) Pre-flight static or dynamic tests fail.

(b) Ambient temperature is below -20°C (-4°F).

D. OIL TEMPERATURE

Minimum for starting: -40°CMaximum permissible: +163°C (15 minutes maximum)Maximum for single engine climb: +155°C (60 minutes maximum)Maximum continuous: +150°C

E. OIL PRESSURE

Transient cold start:(Six minutes maximum)

Minimum at steady state idle:Minimum at take-off (power):Maximum continuous:

F. ENGINE AIRSTART

100 psi (transmitter limit)(Engine must remain at idle until oilpressure returns to normal range.)25 psi40 psi95 psi

Engine starting in flight is permitted only within the envelope definedin Figure 3.

AIR TURBINE STARTER

The starter must not be used if indicated N2 rpm exceeds 55%.

Starter Duty Cvcie

Normal engine start

Motoring and enginestart at -30°C (-22°F)and below

Motoring with enginefuel and ignition OFF

JMITWriONSr'age 8

Three consecutive engine start cycleswith 5 minutes cooling betweenadditional cycles.

Motor engines for 60 seconds and assurefan rotation. Then two consecutiveengine start cycles with 5 minutescooling between additional cycles.

90 seconds with 5 minutes coolingbetween additional cycles of 30 seconds.

DOT ApprovedApr 20/98

44,600/45,100

LIMITATIONSPage 9

Start EnvelopeFigure 3


ASSOCIATED CONDITIONS

For air turbine starts in flight: For air turbine starts on the ground:

At initiation of thrust lever movement: At initiation of thrust lever movement:

1) ITT is to be 90�C or less. 1) ITT is to be 120�C or less.2) N2 must be 28% or greater. 2) N2 must be 20% or greater.

For windmill starts:

At initiation of thrust lever movement:

1) ITT must be 120�C or less.2) Above 10,000 feet, N2 must be 13% and

stable or increasing.

At or below 10,000 feet, N2 mustbe 12% and stable or increasing.

ÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎÎ

ÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏ

ALT

ITU

DE

X 1

000

FT.

0 100 200 300 360KIAS (KNOTS)

25

20

15

10

5

0

21,000 FEET

STARTERASSISTED

10,000 FEET

N2�13%W’MILL

W’MILL

N2�12%



PSP 601−1A−1


44,600/45,100LIMITATIONSPage 10

4. POWER PLANT LIMITATIONS (Cont’d)

H. FUEL TEMPERATURE

Take-off with engine fuel temperature indications below 5 °C (41 °F) isprohibited.

Take-off with a bulk fuel temperature below the following limits isprohibited.

Fuel Bulk Fuel Take-off Limit Bulk Fuel Freezing Point

ASTM D1655 − JET A −30 °C * −40 °C

ASTM D1655 − JET A1 −37 °C * −47 °C

ASTM D6615 − JET B −40 °C * −50 °C

MIL-DTL-5624 − JP 4 −48 °C * −58 °C

MIL-DTL-5624 − JP 5 −36 °C * −46 °C

MIL-DTL-83133 − JP 8 −40 °C * −50 °C

GB 6537 − No. 3 JET −37 °C * −47 °C

* When OAT is within 5 °C of take-off limit or colder, determinebulk fuel temperature using a fuel sample from a water drain.

I. FUEL GRADES

Fuel conforming to any of the following specifications are approved foruse. Mixing of fuels is permitted.

Canadian American British

Kerosene Type

CAN 2 − 3.23 ASTM D1655 − JET A D. ENG. RD. 2494

CAN 2 − 3.23 ASTM D1655 − JET A1 D. ENG. RD. 2494

− MIL-DTL-83133 − JP 8 D. ENG. RD. 2453

− MIL-DTL-5624 − JP 5 D. ENG. RD. 2452

Wide Cut Type

CAN 2 − 3.22 ASTM D6615 − JET B D. ENG. RD. 2486

CAN 2 − 3.22 MIL-DTL-5624 − JP 4 D. ENG. RD. 2454



PSP 601−1A−1


LIMITATIONSPage 11


J. FUEL ADDITIVES

The following additives, used individually or in combination, areapproved:

(1) Anti-icing

Anti-icing additives to the latest revision of specificationsMIL-I-27686E or MIL−DTL−85470B or any direct equivalent, at aconcentration of 0.10 to 0.15% by volume.

C A U T I O N

Do not add unblended PRIST additive directlyinto the fuel tank, as this may damage fueltank components.

Anti-icing Methyl Cellosolve at concentrations of 0.10 to 0.15% byvolume.

(2) Biocide

SOHIO Biobor JF biocide additive at a concentration not in excess of270 parts per million (20 parts per million elemental boron) for theinitial dose to prevent the growth of micro-organisms. A maintenancedose of 135 parts per million should be used thereafter.

Kathon FP 1.5 biocide additive at a concentration not in excess of100 parts per million for the initial dose to prevent the growth ofmicro-organisms. A maintenance dose of 50 parts per million should beused thereafter.

(3) Anti-static

Stadis 450 anti-static additive at a concentration of 5 mg/L.

(4) Corrosion inhibitor

Corrosion inhibitors listed below are approved, by the concentrationsindicated, for hydro-treated fuels only. It is recommended thatcorrosion inhibitors, conforming to MlL−I−25017, be blended with thefuel to provide lubricity. The corrosion inhibitor must be addedafter water removal and downstream of any clay filters (theseprocesses remove the inhibitor).

� Appollo PRI-19, at a maximum concentration of 0.0227 g/l;� Octel DCI-4A or DCI-6A, at a maximum concentration of 0.0227 g/l;

� Hitec E-515, at a maximum concentration of 0.0457 g/l;� Hitec E-580, at a maximum concentration of 0.0227 g/l;� Nalco 5403 or 5405, at a maximum concentration of 0.0227 g/l;� Tolad 245, at a maximum concentration of 0.0340 g/l.



PSP 601−1A−1




K. OIL GRADES

Refer to appropriate maintenance or servicing manual for approved oilgrades.

L. OIL REPLENISHMENT SYSTEM

The oil replenishment system must not be operated before fifteen (15)minutes have elapsed after engine shutdown.

M. AUXILIARY POWER UNIT (APU) OPERATING LIMITS

On airplanes incorporating Service Bulletin 601−0568 or 601−0581:APU type: 36-150(CL)

On airplanes not incorporating Service Bulletin 601−0568 or 601−0581:APU type: GTCP-36-100(E)

The APU must not be operated if APU generator oil leakage is evident.

Unless it has been established that any main generator with a part number720845, 720845A or 720845B has more than 150 operating hours, theAuxiliary Power Unit (APU) and APU generator systems must be serviceablefor dispatch.

Maximum rpm: 110%

The APU overspeed control will automatically shutdown the APU at 107% rpm(110% on airplanes not incorporating Service Bulletin 601−0568 or601−0581).

Maximum EGT: 732�C

Starting:

Minimum ambient temperature for starting a cold soaked APU on the groundis −40�C

The following APU start cycles are permitted:

(a) Using aircraft batteries on the ground or for normal in-flight start:

Three start attempts, each of 30 seconds continuous cranking,followed by a 20-minute off-time, followed by two further attemptseach of 30 seconds continuous cranking.

(b) Using ground power:

Two start attempts, each of 15 seconds continuous cranking, followedby a 20-minute off-time, followed by two further attempts each of 15seconds continuous cranking.

If, in either case (a) or (b) a successful start is not obtained, afurther start must not be attempted for a period of at least 35 minutes.



PSP 601−1A−1

DOT ApprovedDec 21/0644,600/45,100

LIMITATIONSPage 13


M. AUXILIARY POWER UNIT (APU) OPERATING LIMITS (Cont’d)

The APU RDY light must be on within 60 seconds of operating the APU startswitch.

Maximum EGT: 974�C not to be exceeded under any operating conditions.

Hung start:

On airplanes not incorporating Service Bulletin 601−0568 or 601−0581:Below 60% rpm − maximum 20 secondsBetween 60% and 95% rpm − maximum 10 seconds

On airplanes incorporating Service Bulletin 601−0568 or 601−0581:If not greater than 30% rpm within 60 seconds

APU starting and operation is permitted within the following operatingenvelope:

Airspeed: Sea level to 10,000 feet: 0 to 290 KIAS10,000 feet to 20,000 feet: 141 KIAS to 290 KIAS

Temperature: Refer to Figure 2

Altitude: Refer to Figure 4 or 4A

Do not operate the APU in-flight if a main engine fails and engine rotorburst damage is suspected.

In-Flight Starting:

On airplanes not incorporating Service Bulletin 601−0568 or 601−0581:In-flight starting is guaranteed at altitudes up to 15,000 feetand has been demonstrated at altitudes up to 20,000 feet.

On airplanes incorporating Service Bulletin 601−0568 or 601−0581:In-flight starting is guaranteed at altitudes up to 20,000 feet.

Air Conditioning:

On airplanes not incorporating Service Bulletin 601−0568 or 601−0581:(a) APU bleed air extraction is not permitted above 14,500 feet pressure

altitude.

(b) APU bleed air extraction is not permitted in flight whenever standbyelectrical power is required from the APU.

On airplanes incorporating Service Bulletin 601−0568 or 601−0581:(a) APU bleed air extraction is not permitted above 15,000 feet pressure

altitude.



PSP 601−1A−1




M. AUXILIARY POWER UNIT (APU) OPERATING LIMITS (Cont’d)

Main Engine Starting:

During double engine failure conditions, APU bleed air extraction forengine starts is permitted.

On airplanes not incorporating Service Bulletin 601−0568 or 601−0581:In-flight APU main engine starts have been demonstrated to 10,000 feet.

On airplanes incorporating Service Bulletin 601−0568 or 601−0581:In-flight APU main engine starts have been demonstrated to 15,000 feet.

APU Generator:

The maximum permissible load on the APU generator in flight is 30 kVA.

On airplanes not incorporating Service Bulletin 601−0568 or 601−0581:(a) With APU supplying bleed air during take-off and landing, the APU

generator must be selected OFF.

(b) In-flight use of the APU generator is intended only if both maingenerators have failed. Use of the APU generator is not permittedunless both main generators are off line.



PSP 601−1A−1


LIMITATIONSPage 14A

APU In-Flight Envelope(Airplanes NOT Incorporating

Service Bulletin 601−0568 or 601−0581)Figure 4

AIRSPEED: 0 to 290 KIAS

AIRSPEED: 141 KIAS to 290 KIAS



PSP 601−1A−1


44,600/45,100LIMITATIONSPage 14B

APU In-Flight Envelope(Airplanes Incorporating

Service Bulletin 601−0568 or 601−0581)Figure 4A

ALT

ITU

DE

X 1

000

FT.

APU start and generator operation guaranteed − 20,000 feet

0 100 200 300

KIAS (KNOTS)

25

20

15

10

0

141 290

APU in-flight starting is guaranteed up to 20,000 feet.

APU Operation is permitted up to 20,000 feet.

pneumatic operation guaranteed − 15,000 feet

Main engine starting is guaranteed up to 15,000 feet.

APU generator operation is guaranteed up to 20,000 feet.

APU pneumatic operation is guaranteed up to 15,000 feet.

5

Main engine start and



PSP 601−1A−1

canadairchanenqer


PSP 601-1A-1

4. POWER PLANT LIMITATIONS (Cont'd)

N. POWER PLANT INSTRUMENT MARKINGS

Maximum and minimum limitations: Red radial lineTakeoff and caution range: Yellow vertical bandNormal operating range: Green vertical band

(1) FAN SPEED RPM INDICATION (N1) % RPM

98.6% Red radial line0 to 98.6% Green vertical band

(2) INTERSTAGE TURBINE TEMPERATURE INDICATOR (ITT)

857°C Red radial line838°C to 857°C Yellow vertical band

0 to 838°C Green vertrical band

L/R red overtemperature warning lights will comeon when ITT reaches 856°C.

(3) TURBINE SPEED RPM INDICATOR (N2) % RPM

99.4% Red radial line99.2 to 99.4% Yellow vertical band

0 to 99.2% Green vertical band

(4) OIL TEMPERATURE INDICATOR

163°C Red radial line150°C to 163°C Yellow horizontal band-40°C to 150°C Green vertical band

(5) OIL PRESSURE INDICATOR

100 psi Red radial line95 psi to 100 psi Yellow vertical band25 psi to 95 psi Green vertical band

25 psi Red horizontal line

The low oil pressure warning lights will come onwhen oil pressure drops below 28±3 psi.

(6) FUEL TEMPERATURE INDICATOR

60°C to 70°C Yellow band5°C to 60°C Green band

-20°C to 5°C Yellow band

DOT ApprovedO c t 25/ 0 2 ,nn LIMITATIONS44,600/45,100 P a g e 1 5

canadairchanenqer


PSP 601-1A-1

4. POWER PLANT LIMITATIONS (Cont'd)

N. POWER PLANT INSTRUMENT MARKINGS (Cont'd)

(7) ENGINE VIBRATION INDICATOR

1.7 MILS D.A. to 4.0 MILS D.A. Yellow band0 MILS D.A. to 1.7 MILS D.A. Green band

(8) APU EXHAUST GAS TEMPERATURE (EGT) INDICATION

730°C Red radial line680°C to 730°C Yellow band

0°C to 680°C Green band

(9) APU TACHOMETER INDICATOR % RPM

110% Red radial line105% to 110% Yellow band0% to 105% Green band

DOT ApprovedLIMITATIONS Oct 25/02Page 16 44,600/45,100

canadairchanenqer


PSP 601-1A-1

5. MAXIMUM OPERATING LIMIT SPEEDS

Maximum operating limit speeds must not be deliberately exceeded in anyregime of flight (climb, cruise or descent), unless a higher speed isspecifically authorized for flight test or training operations.

A. MAXIMUM OPERATING SPEED (VMO) AND MACH NUMBER (MMO)

Altitude

Pilot'sAltimeter

0 to 10,000

10,000 to21,420

21,420 to25,740

25,740 to28,640

28,640 andabove.

; (feet)

Copilot'sAltimeter

0 to 10,000

10,000 to21,270

21,270 to25,590

25,590 to28,200

28,200 andabove.

Maximum Operati

VMO (KIAS)

301

360

—

330

ng Limi

MMO

0

0.

t Speed

(MI)

_

—

.79

—

835

B. RVSM MAXIMUM OPERATING SPEED

On airplanes incorporating Canadair Service Bulletin 601-0484, ReducedVertical Separation Minimum (RVSM) - 1000 Ft. Aircraft QualificationRequirements, the maximum cruise mach number during flight in RVSMairspace is 0.82.

C. DESIGN MANOEUVERING SPEED (VA)

Full application of rudder and aileron controls as well as manoeuversthat involve angles of attack near the stall, must be confined to speedsbelow VA. Values of VA are given in Figure 5 for varying airplanealtitudes and weights.

Avoid rapid and large alternating controlinputs, especially in combination with largechanges in pitch, roll, or yaw (e.g. largeside slip angles), as they may causestructural failure at any speed, includingbelow VA.

DOT ApprovedJul 16/0444,600/45,100

LIMITATIONSPage 17


PSP 601-1A-1

WeightOb)

Weight(kg)

Altitude(feet)

Sea Level

10,000

15,000

20,000

25,000

30,000

35,000

40,000

45,000

24,525

11,124

172

174

179

186

194

203

211

218

225

31,000

14,061

193

201

209

219

229

238

245

248

-

36,000

16,329

Design ̂

211

224

234

245

255

264

268

-

-

38,000

17,237

lanoeuveri(KIAS

217

232

243

254

265

274

276

-

-

43,100

19,550

ng Speed)

236

256

267

278

289

294

-

-

-

44,600

20,230

(VA)

241

263

275

286

297

304

-

-

-

45,100

20,457(SB 601-0360)

243

265

278

290

299

304

-

-

-

LIMITATIONSPage 18

Design Manoeuvering Speed - VAFigure 5


44,600

canacfairchauenQerMODEL CL-600-2A12

AIRPLANE FLIGHT MANUALPSP 601-1A-1

5. MAXIMUM OPERATING LIMIT SPEEDS (Cont'd)

D. FLAPS EXTENDED SPEED (VFE) |

The maximum speeds at which the flaps may be extended are:

flaps to 20 degrees: 232 KIAS



E. MAXIMUM LANDING GEAR OPERATING SPEED (VL0) |

The maximum airspeed at which the landing gear may be lowered or raised is197 KIAS/0.7 M L

F. MAXIMUM LANDING GEAR EXTENDED SPEED (VLE) |

The maximum airspeed at which the airplane may be flown with the landinggear extended and locked is 250 KIAS/0.7 Mi.

On airplanes incorporating Canadair Service Bulletin 601-0329 Part B(3),Special Check/Modification - Main Landing Gear Door - Hinge andFasteners, but not Part C, the maximum airspeed at which the airplane maybe flown with the landing gear extended and locked is 197 KIAS.

G. TIRE LIMIT SPEED |

The tire limit speed is 183 knots ground speed.

H. MAXIMUM AIRSPEED FOR ADG OPERATION |

The maximum airspeed for continuous operation of the air driven generatorfollowing automatic or manual deployment is 250 KIAS. When operationallynecessary, speeds up to 330 KIAS are permitted for a period of twelve (12)minutes reducing to a period of four (4) minutes at VMO with linearinterpolation. For flight test or pilot training deployment, the maximumairspeed is 215 KIAS.

I. TURBULENCE PENETRATION SPEED |

Turbulence penetration speed is 280 KIAS or 0.75 Mi, whichever is lower.

DOT ApprovedMf 27/97 LIMITATIONS44,600/45,100 Page- 1 9


PSP 601-1A-1

6. MINIMUM OPERATING LIMIT SPEED

Intentional speed reduction below the onset of stal l warning, as defined byst ick shaker operation, is prohibited unless a lower speed is speci f ical lyauthorized for f l i gh t test or training operations.

7. MANOEUVERING LIMIT LOAD FACTORS

These load factors l im i t the permissible angles of bank in turns and theseverity of pull-up manoeuvers:

Flaps up: -1.0 G to 2.56 G

Flaps down: 0.0 G to 2.0 G

DOT Approved

LIMITATIONS °(lPage 20

canadairchauenqer


PSP 601-1A-1

8. SYSTEMS LIMITATIONS (Cont'd)

A. AIR CONDITIONING AND PRESSURIZATION (STRUCTURAL LIMITATIONS)

The maximum relief differential pressure is 9.20 psi.

During taxi, take-off and landing, the pressure differential must notexceed 1.0 psi.

B. AUTOMATIC FLIGHT CONTROL SYSTEM

Operation of the autopilot is prohibited at altitudes below 200 feet aboveground level.

The autopilot must be disengaged at speeds below VR^p.

The autopilot is not approved for continued approach following enginefailure on final approach (refer to EMERGENCY PROCEDURES - AUTOMATIC FLIGHTCONTROL SYSTEM EMERGENCIES).

Maximum flap angle for single engine autopilot coupled approach is 20degrees with V R E F + 20 KIAS.

DOT ApprovedMar 10/89 LIMITATIONS44,600 Page 21

canadairchanenqer


PSP 601-1A-1


C. ELECTRICAL SYSTEMS

Unless it has been established that any AC Generator with a part number720845, 720845A or 720845B has more than 150 operating hours:

Prior to every flight a visual inspection of the engine cowls anddrains for evidence of AC Generator oil leakage must be conducted.If generator oil leakage is evident, generator must be replaced.

Unless it has been established that an APU Generator with a part number720845, 720845A or 720845B has more than 150 operating hours:

Prior to every flight a visual inspection of the APU drains forevidence of generator oil leakage must be conducted. If oil leakageis evident, APU Generator must be replaced unless it has beenestablished that AC Generators with part numbers 720845, 720845A or720845B are not installed, or if installed, both have more than 150operating hours.

(1) Permissible Loads on AC Systems

Individual AC generator loading, as indicated by the loadmeters, mustnot exceed the following values:

Altitude(feet)

0 - 11,000

11,000 - 20,000

20,000 - 35,000

35,000 and above

L o a d Limitation(kV

Main Generator(each)

30

30

30

25

mi tat ionVA)

APU GeneratorC

O

CO

CD

C

D

LIMITATIONSPage 22

DOT ApprovedOct 25/02

44,600/45,100

canadairchanenqer


PSP 601-1A-1


C. ELECTRICAL SYSTEMS (Cont'd)

(2) Permissible Loads on DC Systems

(a) In Flight

The maximum permissible continuous load on TRU 1 or TRU 2 is100 amps.

The maximum permissible continuous load on TRU 3 is 50 amps.

(b) Ground Operation

Total combined loads on TRU 1 and TRU 2 must not exceed limitsshown in Figure 6 or Figure 7.

Individual loads on TRU 1 and TRU 2 must not exceed 100 amps. IfTRUs are inadvertently operated at limiting loads for periodslonger than those shown, the nose bay doors must be opened for10 minutes minimum prior to taxi for take-off.

(3) Permissible Operating Time

During ground operation at ambient temperatures above 45°C (113°F),operation of electrical/avionics equipment must be limited to30 minutes unless at least one environmental control system isoperating and cabin doors closed.

DOT ApprovedO c t 25/ 0 2 ,nn LIMITATIONS44,600/45,100 P a g e

canadairchanenqer


PSP 601-1A-1


DOT ApprovedLIMITATIONS Oct 25/02Page 22B 44,600/45,100

canadairchaiienqier


PSP 601-1A-1

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DOT ApprovedMar 10/8944,600

Maximum Permissible Loads on DC Electrical System -Ground Operation

Figure 6 LIMITATIONSPage 23

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PSP 601-1A-1

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Incorporating Canadair Service Bulletin 601-0107Figure 7

LIMITATIONSPage 24

DOT ApprovedMar 10/89

44,600

DOT ApprovedApr 20/9844,600/45,100

LIMITATIONSPage 25

8. SYSTEMS LIMITATIONS (Cont’d)

D. FLIGHT CONTROLS − LIFT/DRAG DEVICES

(1) Flaps

En-route use of flaps is prohibited.

Flight at altitudes above 15,500 feet with flaps extended isprohibited.

(2) Flight Spoilers

On airplanes 3001 to 3039 which do not incorporate Canadair ServiceBulletin 601-0040, Modification − Central Warning System − FlightSpoilers, or on airplanes incorporating Canadair Service Bulletin601-0040 (Initial issue) and Canadair Service Bulletin 601-0095,Modification − Flight Spoiler Warning System − Elimination ofSpurious Warnings:

(a) Flight below an altitude of 700 feet agl with flight spoilersextended and the flaps retracted is prohibited.

(b) Flight spoilers must not be extended in flight with flapsextended.

On airplanes 3013, 3018 to 3023, 3040 and subsequent and airplanesincorporating Canadair Service Bulletin 601-0040 (Initial issue) only(i.e. Service Bulletin 601-0095 not incorporated) or Canadair ServiceBulletin 601-0040 (Rev. 1):

(a) Flight below an altitude of 300 feet agl with flight spoilersextended is prohibited.

(b) To ensure adequate manoeuvre margins, flight spoilers must notbe extended in flight at airspeeds below the recommendedapproach speed (refer to PERFORMANCE − LANDING) plus 10 KIAS.

(3) Ground Spoilers

On airplanes 3001 to 3059 which do not incorporate Canadair ServiceBulletin 601-0113, Modification − Ground Spoilers − Auto Deployment:

The spoiler lever must not be selected to the GROUND SPOILER positionin flight.



PSP 601−1A−1




E. FUEL SYSTEM

The maximum permissible fuel imbalance between the contents of the mainfuel tanks is 800 lb (363 kg).

Take-off with up to 500 lb (230 kg) of fuel in the auxiliary tank ispermitted, provided that there is at least 1500 lb (690 kg) of fuel ineach wing tank and no fuel in the tail tank (if installed).

Take-off with more than 500 lb (230 kg) of fuel in the auxiliary tank ispermitted, provided that there is at least 4400 lb (1996 kg) of fuel ineach wing tank.

Fuel remaining in a tank when the appropriate fuel quantity indicator readszero is not usable.

The maximum usable fuel quantities shown below are achieved by pressurefueling and are based on maximum achievable capacity with wings level,aircraft 1/2� nose down and a standard day conversion factor of 6.8 lb/USG.

To determine approximate maximum usable fuel quantities by gravity fueling,reduce selected weight by 7%.

1. On airplanes 3001 − 3014 equipped with Forward and Aft fuselage fueltanks, maximum usable fuel quantity is:

Left Main Tank 4,879 lb (2,213 kg)Right Main Tank 4,879 lb (2,213 kg)Fuselage Tanks 6,868 lb (3,115 kg)

Total 16,626 lb (7,541 kg)

2. On airplanes 3001 − 3014 equipped with Aft fuselage fuel tank only,maximum usable fuel quantity is:


Total 15,494 lb (7,027 kg)

3. On airplanes 3001 − 3014 equipped with Forward and Aft fuselage fueltanks, incorporating Canadair Service Bulletin 601−0535, maximumusable fuel quantity is:


Total 12,368 lb (5,610 kg)



PSP 601−1A−1


LIMITATIONSPage 27


E. FUEL SYSTEM (Cont’d)

4. On airplanes 3015 and subsequent equipped with Forward and Aftfuselage fuel tanks, maximum usable fuel quantity is:


Total 16,686 lb (7,569 kg)

5. On airplanes 3015 and subsequent equipped with Aft fuselage fuel tankonly, maximum usable fuel quantity is:


Total 15,554 lb (7,055 kg)

6. On airplanes 3015 and subsequent equipped with Forward and Aftfuselage fuel tanks, incorporating Canadair Service Bulletin 601−0535,maximum usable fuel quantity is:


Total 12,428 lb (5,638 kg)

On airplanes incorporating Canadair Service Bulletin 601−0535, operationwith more than 2,610 lb (1,184 kg) of fuel in the auxiliary tank isprohibited.

N O T E

Following a rejected take-off on airplanesincorporating Canadair Service Bulletin601−0535, inspect the forward auxiliary tankto ensure that there has been no migration offuel, in accordance with paragraph 2.C. ofCanadair Service Bulletin 601−0535.

F. STALL PROTECTION SYSTEM

Both stall protection systems must be fully operative for take-off andremain on for all phases of flight.

The stall protection test indicator must only be used for S.P.S.functional test purposes.



PSP 601−1A−1




G. NOT USED

H. NOT USED

I. NOT USED

J. WHEEL BRAKE COOLING LIMITATIONS

Brake cooling times (established in accordance with the procedures inNORMAL PROCEDURES-LANDING GEAR WHEELS AND BRAKES) must be observedbetween a landing or a low-energy rejected take-off (RTO) and asubsequent take-off, to ensure that sufficient brake energy is availableto bring the airplane to a complete stop, if the subsequent take-off isrejected.

If a fusible plug releases, the affected wheel, brakes and the anti-skidwheel speed sensors must be inspected in accordance with the proceduresin the CL-601 Time Limits/Maintenance Checks, PSP601−5, and any damagerectified before the next take-off.

K. WHEEL BRAKES ANTI-SKID

Take-off with the wheel brakes anti-skid system inoperative isprohibited.

L. BLEED AIR SYSTEMS

The bleed air 10th stage valves must be closed for take-off and landingwith cowl and/or wing anti-ice systems on.

M. NOT USED

N. TIRE PRESSURES

When operating with 25.75 x 6.75 − 14 PR mainwheel tires at unloadedinflation pressures between 198 psi and 145 psi, the maximum take-offweight (MTOW) is limited (refer to Figures 8 and 9).

The maximum nosewheel tire pressure is 151 psi (1041 kPa) +5%, −0 on theground.

On airplanes incorporating Canadair Service Bulletin 601−0205,Modification − Flight Compartment Tire Pressure Caution Placard − SpecialOperating Conditions Only:Tire pressures must be verified daily and a placard installed on thepilot’s instrument panel.



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O. THRUST REVERSERS

Thrust reversers are approved for ground use only.

The thrust reverser pre-flight checks (NORMAL PROCEDURES) must besuccessfully accomplished and the proper indications obtained on eachoperative thrust reverser prior to each take-off.

Thrust reversers are intended for use during full stop landings. Do notattempt a go-around manoeuvre after deployment of the thrust reversers.

Application of reverse thrust above 60% N1 is not permitted at airspeedsbelow 60 KIAS.

The maximum demonstrated crosswind component approved for use of reversethrust is 24 knots (at 33 feet (10 meters) tower height). This value wasdemonstrated on a dry runway and is considered limiting.

P. TAXI LIGHTS

Taxi lights must be switched off whenever the airplane is stationary inexcess of 10 minutes.

Q. AIR DATA SYSTEM

On airplanes incorporating Canadair Service Bulletin 601−0484, ReducedVertical Separation Minimum (RVSM) − 1000 Ft. Aircraft QualificationRequirements;

� The ADC source coupled to the active autopilot must be the same as thatcoupled to the ATC transponder during flight in RVSM airspace.

� If alternate static source is selected, airplane must not be operatedin RVSM airspace.

9. CONFIGURATION DEVIATION LIST

If the airplane is to be operated with certain secondary airframe and/ornacelle parts missing, operation must be in accordance with the limitationsspecified in the basic Airplane Flight Manual, and as amended by theConfiguration Deviation List (Appendix 1).



PSP 601−1A−1

Documents

MODEL CL−600−2A12 AIRPLANE FLIGHT MANUAL PSP 601−1A−1 · 2012. 6. 27. · canadair chailenqer MODEL CL-600-2A12 AIRPLANE FLIGHT MANUAL PSP 601-1A-1 LIST OF ILLUSTRATIONS £12Numbe"r