MODEL CL−600−2A12
AIRPLANE FLIGHT MANUAL
PSP 601−1A−1
LIMITATIONS
TABLE OF CONTENTS
Page
1.
STRUCTURAL WEIGHT LIMITATION . ........................................... 1
2.
CENTRE OF GRAVITY (LIMITS) . ............................................. 2
3.
OPERATING LIMITATIONS . ................................................. 4B
A.
B.
C.
D.
E.
F.
G.
H.
I.
4.
POWER PLANT LIMITATIONS . ................................................ 7
A.
B.
C.
D.
E.
F.
G.
H.
I.
J.
K.
L.
M.
N.
5.
Types of Operation . ............................................... 4B
Altitude and Temperature Operating Limits . ........................ 4B
Runway Surface . ................................................... 4B
Runway Slopes . ..................................................... 6
Tailwind Conditions . ............................................... 6
Minimum Flight Crew . .................................... ........... 6
Maximum Occupants . ................................................. 6
Operation in Icing Conditions . .................................... 6A
Cold Weather Operations . .......................................... 6C
Engines ............................................................ 7
Engine Operating Limits . ........ ................................... 7
Automatic Performance Reserve (APR) . ............................... 8
Oil Temperature . ................................................... 8
Oil Pressure . ...................................................... 8
Engine Airstart . ................................................... 8
Air Turbine Starter . ............................................... 8
Fuel Temperature . ................................................. 10
Fuel Grades . ...................................................... 10
Fuel Additives . ................................................... 11
Oil Grades . ....................................................... 12
Oil Replenishment System . ......................................... 12
Auxiliary Power Unit (APU) Operating Limits . ...................... 12
Power Plant Instrument Markings . ........................... ....... 15
MAXIMUM OPERATING LIMIT SPEEDS . ........................................ 17
A.
B.
C.
D.
E.
F.
G.
H.
I.
Maximum Operating Speed (VMO) and Mach Number (MMO) . ...............
RVSM Maximum Operating Speed . .....................................
Design Manoeuvering Speed (VA) . ....................................
Flaps Extended Speed (VFE) . ........................................
Maximum Landing Gear Operating Speed (VLO) . ........................
Maximum Landing Gear Extended Speed (VLE) . .........................
Tire Limit Speed . .................................................
Maximum Airspeed for ADG Operation . ...............................
Turbulence Penetration Speed . .....................................
DOT Approved
Sep 11/06
44,600/45,100
17
17
17
19
19
19
19
19
19
LIMITATIONS
− CONTENTS
Page i
MODEL CL−600−2A12
AIRPLANE FLIGHT MANUAL
PSP 601−1A−1
Page
6.
MINIMUM OPERATING LIMIT SPEED . ......................................... 20
7.
MANOEUVERING LIMIT LOAD FACTORS . ....................................... 20
8.
SYSTEMS LIMITATIONS . ................................................... 21
A.
B.
C.
D.
E.
F.
G.
H.
I.
J.
K.
L.
M.
N.
O.
P.
Q.
9.
Air Conditioning and Pressurization (Structural Limitations) . .....
Automatic Flight Control System . .................................
Electrical Systems . ..............................................
Flight Controls − Lift/Drag Devices . .............................
Fuel System . .....................................................
Stall Protection System . ..........................................
NOT USED . .........................................................
NOT USED . .........................................................
NOT USED . .........................................................
Wheel Brake Cooling Limitations . ..................................
Wheel Brakes Anti-Skid . ..........................................
Bleed Air Systems . ...............................................
NOT USED . .........................................................
Tire Pressures . ..................................................
Thrust Reversers . ................................................
Taxi Lights . ......................................................
Air Data System . ..................................................
21
21
22
25
26
27
28
28
28
28
28
28
28
28
31
31
31
CONFIGURATION DEVIATION LIST . .......................................... 31
LIST OF ILLUSTRATIONS
Title
Figure
Number
Page
1
Centre of Gravity Limits . .......................................... 3
1A
Centre of Gravity Limits
(A/C incorporating Service Bulletin 601-0360) . .................... 4
2
3
Altitude and Temperature Operating Limits . ........................
Start Envelope . ...................................................
4
APU In-Flight Envelope (Airplanes NOT incorporating
Service Bulletin 601-0568 or 601−0581) . ......................... 14A
APU In-Flight Envelope (Airplanes incorporating
Service Bulletin 601-0568 or 601−0581) . ......................... 14B
4A
5
6
Design Manoeuvering Speed − VA . ................................... 18
Maximum Permissible Loads on DC Electrical System −
Ground Operation . ................................................ 23
LIMITATIONS
− CONTENTS
Page ii
5
9
DOT Approved
Jan 30/07
44,600/45,100
canadair
chailenqer
MODEL CL-600-2A12
AIRPLANE FLIGHT MANUAL
PSP 601-1A-1
LIST OF ILLUSTRATIONS
£12"
Number
Title
Maximum Permissible Loads on DC Electrical System Ground Operation - Airplanes 3051 and Subsequent and
Airplanes Incorporating Canadair Service
Bulletin 601-0107
DOT Approved
Sep 25/90
44,600
Page
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
LIMITATIONS
- CONTENTS
Page i i i
canatiair
chaneriQer
MODEL CL-600-2A12
AIRPLANE FLIGHT MANUAL
PSP 601-1A-1
LIMITATIONS
Observance of the limitations contained within the LIMITATIONS section of the
Airplane Flight Manual is mandatory.
1. STRUCTURAL HEIGHT LIMITATION
Maximum taxi and ramp weight: 44,750 lb (20,298 kg) (see NOTE 1)
45,250 1b (20,525 kg) (see NOTE 2)
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 g h t weight:
25,000 lb (11,340 kg)
NOTE
1. Canadair Service Bulletin 601-0280, must be
incorporated for airplane to operate at the
maximum taxi and ramp weight of 44,750 lb
(20,298 kg) and at the maximum take-off
weight of 44,600 lb (20,230 kg).
I
|
2. Canadair Service Bulletin 601-0360,
Modification - Increased MTOH - 45,100 lb,
must be incorporated to operate at the
maximum taxi and ramp weight of 45,250 lb
(20,525 kg) and at the maximum take-off
weight of 45,100 lb (20,457 kg).
3. The maximum take-off weight (MTOW) and/or
maximum landing weight (MLH) may be further
limited due to tire pressures, brake kinetic
energy, tire limit speeds and/or performance
considerations (refer to LIMITATIONS - TIRE
PRESSURES, NORMAL PROCEDURES and
PERFORMANCE).
DOT Approved
Sep 25/90
44,600
LIMITATIONS
Page 1
canadair
chanenQer
MODEL CL-600-2A12
AIRPLANE FLIGHT MANUAL
PSP 601-1A-1
CENTRE OF GRAVITY (LIMITS)
The maximum permissible centre of gravity (CG) range with landing gear extended
is shown in Figure 1 and Figure 1A. The airplane must be loaded in accordance
with the loading instructions associated with the Weight and Balance Report,
Reference RAW-601-***, pertaining to the particular aircraft. The effect of
landing gear retraction on CG position is negligible.
***Each report is identified by the airplane serial number.
LIMITATIONS
Page
2
T
44,600
canadair
MODEL CL-600-2A12
AIRPLANE FLIGHT MANUAL
PSP 601-1A-1
CENTRE OF GRAVITY
12 25 12776 12*27 12(878
M
ftC
46
503
5•05
LIMITS
MILLIMETRES AFT OF DATUM
13081 1313,I 13183
12929 12979 13030
INCH!:s AFI OF DATUM
511
i» 7
513
515
517
323 3 132C u
521
519
52:
16. 0 X M*X RAI JP 4 4 ! 50 LE - 2 0298 K 5 29.f. X
45
MAX
AKE ( IFF 44 600 L B - 2()230 > C
A
20.0
44
•
•
43.
.19.0
42.
41.
40.
39.
38
37.
CD
V
\
\
V
\\
r
\
\
. 36.
2
.18.0
MAX 1 .AND If 10 36C 00 LB - 16, \29 K(
35.
l
?34
1
o
*33
32.
31,
.17.0
o
o
16
o§
I
O
.15.0
\
MA ( ZER< > FUEL 3100 0 LB •- 140( 11 KG \
14.0
30.
29.
.13.0
28
27.
.12.0
26
25
Ml JIMUM FLICK T 250 00 L6 -
ii;140 KC
2( . O X
24
12
DOT Approved
Nov 07/89
44,600
35 .0 X
.11.0
14 16 18 20 22 24 26 28 30 32 34 36 38 40
X M.A.C.
Centre of Gravity Limits
Figure 1
LIMITATIONS
Page
3
canadair
chanencjer
MODEL CL-600-2A12
AIRPLANE FLIGHT MANUAL
PSP 601-1A-1
CENTRE OF GRAVITY L I M I T S
Ml LLIME TRES i KF1 OF' OATUIM
12" '25 12776 13"827 1 2878
46
5<II
503
9« 5
17.0 X
16. 0 % MKK
*AX
M>7
RAJ IP
AKEOf
1313 I 13183
13081
12929 12979 13030
ATUM
INCHIIS AF1r OF o
i
i
509
511
45: 50
LE
F 45100 LB
513
517
515
519
I32J 3 1321
52.
521
.0 *
*25 K ; 29.1 X
157 IS
20.0
44
43.
\
42.
,19.0
\
41
\
40.
.18.0
39.
38
J7.0
\
37
\
o
CD
MAX LAND NG 3< • 0 0 0 L 8
-1
>329 1
o
8
- 35
.16.0 2
1
\
A
5 34.
5
-
.15.0 ^
32
MA < ZER( > FUEl 3100 0 LB - 140< 1 KG
31
,14.0
30
29
.13.0
28
27
.12.0
?6
Ml VIMUM FLIGt T 250
00 LB -
25
ii; >40 K(
:
24
12
LIMITATIONS
Page
4
: : * .OX
14
16
18
20
35 .0
22
24 26 28
X M.A.C.
30
32
34
x
36
Centre of Gravity Limits
(A/C incorporating Service Bulletin 601-0360)
Figure 1A
.11.0
38 40
DOT Approved
Sep 25/90
44,600
MODEL CL-600-2A12
AIRPLANE FLIGHT MANUAL
PSP 601-1A-1
THIS PAGE INTENTIONALLY LEFT BLANK
DOT Approved
S f 25/90
44,600
LIMITATIONS
Page
4A
MODEL CL-600-2A12
AIRPLANE FLIGHT MANUAL
PSP 601-1A-1
3. OPERATING LIMITATIONS
A. TYPES OF OPERATION
This airplane is certificated in the transport category and is eligible
for the following kinds of operations when the appropriate instruments
and equipment required by the airworthiness and/or operating certificate
are installed and approved and are in operable condition.
Day and night
VFR
IFR
Icing conditions
On airplanes incorporating Canadair Service Bulletin 601-0484, Reduced
Vertical Separation Minimum (RVSM) - 1000 Ft. Aircraft Qualification
Requirements:
This airplane is certificated capable of RVSM operations in accordance
with 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 does
not constitute RVSM operational approval.
B. ALTITUDE AND TEMPERATURE OPERATING LIMITS
Maximum airport pressure altitude for take-off and landing is
10,000 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 must
be motored for 60 seconds and the fan must rotate before engine start is
initiated.
C. RUNWAY SURFACE
Both igniters on both engines must be on continuously for take-off and
landing on runway surfaces covered with standing water, slush or snow or
in icing conditions.
DOT Approved
LIMITATIONS
Page 4B
fl
Mar 27/97
44,600/45,100
nr
MODEL CL-600-2A12
AIRPLANE FUGHT MANUAL
PSP 601-1A-1
TAHEO.
UllDffllG UMBS
-80-
-fe-
AMBIENT
v—'—r
•100 - 8 0
DOT Approved
Oct 28/96
44,600/45,100
-60
ERATURE
l—'—nr
-40
-20
0
20
40
60
AMBIENT TEMPERATURE - °F
80
Altitude and Temperature Operating Limits
Figure 2
100
120
140
LIMITATIONS
Page 5
canadair
chanenqer
MODEL CL-600-2A12
AIRPLANE FLIGHT MANUAL
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 10
knots.
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 and
landing is provided.
DOT Approved
LIMITATIONS
Page 6
A
pr 21/03
44,600/45,100
canadair
chanenqer
MODEL CL-600-2A12
AIRPLANE FLIGHT MANUAL
PSP 601-1A-1
3. OPERATING LIMITATIONS (Cont'd)
H. OPERATION IN ICING CONDITIONS
During cold weather operations, the flight crew must ensure that the
airplane fuselage, wings and tail surfaces are free from ice, snow or
frost.
(1) Cowl Anti-ice System
(a) Ground Operations
The 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 is
10°C (50°F) or below when operating on runways, ramps, or
taxi ways where surface snow, ice, standing water or slush is
present.
(b) Flight Operations
NOTE
Icing conditions exist in flight at a TAT of
10°C (50°F) or below and visible moisture in
any form is encountered (such as clouds,
rain, snow, sleet or ice crystals), except
when 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 Approved
Apr 21/03
44,600/45,100
LIMITATIONS
Page 6A
canadair
chanenqer
MODEL CL-600-2A12
AIRPLANE FLIGHT MANUAL
PSP 601-1A-1
3. OPERATING LIMITATIONS (Cont'd)
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 is
5°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 the
OAT is 5°C (41°F) or below and the runway is contaminated with
surface snow, slush or standing water.
When Type II, III or IV anti-icing fluids have been applied, the
wing anti-ice system must only be selected on, if required, just
prior to thrust increase for take-off.
(b) Flight Operations
NOTE
Icing conditions exist in flight at a TAT of
10°C (50°F) or below and visible moisture in
any form is encountered (such as clouds,
rain, snow, sleet or ice crystals), except
when 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 flight
compartment 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.
LIMITATIONS
Page 6B
DOT Approved
Jan 14/05
44,600/45,100
MODEL CL−600−2A12
AIRPLANE FLIGHT MANUAL
PSP 601−1A−1
3. OPERATING LIMITATIONS (Cont’d)
I. COLD WEATHER OPERATIONS
Take-off is prohibited with frost, ice, snow or slush adhering to any
critical surface (wings, horizontal stabilizer, vertical stabilizer,
control surfaces, engine inlets and upper surface of the fuselage).
WARNING
Even small amounts of frost, ice, snow or
slush on the wing leading edges and forward
upper wing surface may adversely change the
stall speeds, stall characteristics and the
protection provided by the stall protection
system, which may result in loss of control
on take-off.
NOTE
1. Comprehensive procedures for operating in
cold weather are provided in the Operating
Manual Volume 1, SUPPLEMENTARY PROCEDURES,
Cold Weather Operations.
2. Take-off is permitted with frost adhering to
the underside of the wing that is caused by
cold soaked fuel, in accordance with the
instructions provided in the Operating Manual
Volume 1, SUPPLEMENTARY PROCEDURES, Cold
Weather 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 during
the Walkaround Check List inspection to determine that the wing is free
from frost, ice, snow or slush when the outside air temperature (OAT) is
5_C (41_F) or less, or it cannot be determined that the wing fuel
temperature is above 0_C (32_F); and:
S There is visible moisture (rain, drizzle, sleet, snow, fog, etc); or
S Water is present on the wing; or
S The difference between the dew point temperature and the OAT is
3_C (5_F) or less; or
S The atmospheric conditions have been conducive to frost formation.
NOTE
Ice and frost may continue to adhere to wing
surfaces for some time even at outside air
temperatures above 5_C (41_F).
DOT Approved
Sep 11/06
44,600/45,100
LIMITATIONS
Page 6C
MODEL CL−600−2A12
AIRPLANE FLIGHT MANUAL
PSP 601−1A−1
THIS PAGE INTENTIONALLY LEFT BLANK
LIMITATIONS
Page 6D
DOT Approved
Sep 11/06
44,600/45,100
MODEL CL−600−2A12
AIRPLANE FLIGHT MANUAL
PSP 601−1A−1
4. POWER PLANT LIMITATIONS
A. ENGINES
Type:
Two General Electric CF34-1A or
Two General Electric CF34-3A or
Two General Electric CF34-3A2
NOTE
Mixing of CF34-1A, CF34-3A and CF34-3A2
engines is permitted.
B. ENGINE OPERATING LIMITS
Condition
N1
N2
(% rpm) (% rpm)
ITT
(_C)
Time Limit
for ITT
Maximum take-off (APR operating)
98.6
99.4
857
886
5 minutes
2 minutes
Normal take-off
96.2
98.3
842
864
5 minutes
2 minutes
Maximum continuous
98.6
99.2
838
−
930
889
16 seconds
50 seconds
−
−
Start/relight
Minimum idle in icing conditions
(cowl anti-ice only)
−
64.0
NOTE
1. The above take-off and maximum continuous
limits for N1, N2 and ITT are engine limits
and are not presented for purposes of
setting power. The pilot must observe the
take-off and maximum continuous power
settings for the appropriate pressure
altitude, ambient temperature and bleed air
extraction as presented in the PERFORMANCE
section of this manual.
2. Above 40,000 feet one ACU or cowl anti-ice
must be selected on for each engine.
DOT Approved
Jan 30/07
44,600/45,100
LIMITATIONS
Page 7
MODEL CL-600-2A12
AIRPLANE FLIGHT MANUAL
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-off
with the APR system armed must not be attempted until satisfactory
static 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°C
Maximum 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:
100 psi (transmitter limit)
(Engine must remain at idle until oil
pressure returns to normal range.)
25 psi
40 psi
95 psi
F. ENGINE AIRSTART
Engine starting in flight is permitted only within the envelope defined
in 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 engine
start at -30°C (-22°F)
and below
Motoring with engine
fuel and ignition OFF
JMITWriONS
r'age 8
Three consecutive engine start cycles
with 5 minutes cooling between
additional cycles.
Motor engines for 60 seconds and assure
fan rotation. Then two consecutive
engine start cycles with 5 minutes
cooling between additional cycles.
90 seconds with 5 minutes cooling
between additional cycles of 30 seconds.
DOT Approved
Apr 20/98
44,600/45,100
MODEL CL−600−2A12
AIRPLANE FLIGHT MANUAL
PSP 601−1A−1
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.
2) N2 must be 28% or greater.
1)
2)
ITT is to be 120_C or less.
N2 must be 20% or greater.
For windmill starts:
At initiation of thrust lever movement:
1)
2)
ITT must be 120_C or less.
Above 10,000 feet, N2 must be 13% and
stable or increasing.
At or below 10,000 feet, N2 must
be 12% and stable or increasing.
25
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21,000 FEET
ALTITUDE X 1000 FT.
20
N2w13%
W’MILL
15
10
STARTER
ASSISTED
10,000 FEET
W’MILL
N2w12%
5
0
0
100
DOT Approved
Jan 30/07
44,600/45,100
200
KIAS (KNOTS)
Start Envelope
Figure 3
300
360
LIMITATIONS
Page 9
MODEL CL−600−2A12
AIRPLANE FLIGHT MANUAL
PSP 601−1A−1
4. POWER PLANT LIMITATIONS (Cont’d)
H. FUEL TEMPERATURE
Take-off with engine fuel temperature indications below 5 °C (41 °F) is
prohibited.
Take-off with a bulk fuel temperature below the following limits is
prohibited.
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, determine
bulk fuel temperature using a fuel sample from a water drain.
I. FUEL GRADES
Fuel conforming to any of the following specifications are approved for
use. 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
LIMITATIONS
Page 10
DOT Approved
Sep 11/06
44,600/45,100
MODEL CL−600−2A12
AIRPLANE FLIGHT MANUAL
PSP 601−1A−1
4. POWER PLANT LIMITATIONS (Cont’d)
J. FUEL ADDITIVES
The following additives, used individually or in combination, are
approved:
(1)
Anti-icing
Anti-icing additives to the latest revision of specifications
MIL-I-27686E or MIL−DTL−85470B or any direct equivalent, at a
concentration of 0.10 to 0.15% by volume.
CAUTION
Do not add unblended PRIST additive directly
into the fuel tank, as this may damage fuel
tank components.
Anti-icing Methyl Cellosolve at concentrations of 0.10 to 0.15% by
volume.
(2)
Biocide
SOHIO Biobor JF biocide additive at a concentration not in excess of
270 parts per million (20 parts per million elemental boron) for the
initial dose to prevent the growth of micro-organisms. A maintenance
dose of 135 parts per million should be used thereafter.
Kathon FP 1.5 biocide additive at a concentration not in excess of
100 parts per million for the initial dose to prevent the growth of
micro-organisms. A maintenance dose of 50 parts per million should be
used 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 concentrations
indicated, for hydro-treated fuels only. It is recommended that
corrosion inhibitors, conforming to MlL−I−25017, be blended with the
fuel to provide lubricity. The corrosion inhibitor must be added
after water removal and downstream of any clay filters (these
processes remove the inhibitor).
S Appollo PRI-19, at a maximum concentration of 0.0227 g/l;
S Octel DCI-4A or DCI-6A, at a maximum concentration of 0.0227 g/l;
S Hitec E-515, at a maximum concentration of 0.0457 g/l;
S Hitec E-580, at a maximum concentration of 0.0227 g/l;
S Nalco 5403 or 5405, at a maximum concentration of 0.0227 g/l;
S Tolad 245, at a maximum concentration of 0.0340 g/l.
DOT Approved
Sep 11/06
LIMITATIONS
44,600/45,100
Page 11
MODEL CL−600−2A12
AIRPLANE FLIGHT MANUAL
PSP 601−1A−1
4. POWER PLANT LIMITATIONS (Cont’d)
K. OIL GRADES
Refer to appropriate maintenance or servicing manual for approved oil
grades.
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 number
720845, 720845A or 720845B has more than 150 operating hours, the
Auxiliary Power Unit (APU) and APU generator systems must be serviceable
for 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 or
601−0581).
Maximum EGT:
732_C
Starting:
Minimum ambient temperature for starting a cold soaked APU on the ground
is −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 attempts
each of 30 seconds continuous cranking.
(b)
Using ground power:
Two start attempts, each of 15 seconds continuous cranking, followed
by a 20-minute off-time, followed by two further attempts each of 15
seconds continuous cranking.
If, in either case (a) or (b) a successful start is not obtained, a
further start must not be attempted for a period of at least 35 minutes.
DOT Approved
Sep 11/06
LIMITATIONS
44,600/45,100
Page 12
MODEL CL−600−2A12
AIRPLANE FLIGHT MANUAL
PSP 601−1A−1
4. POWER PLANT LIMITATIONS (Cont’d)
M. AUXILIARY POWER UNIT (APU) OPERATING LIMITS (Cont’d)
The APU RDY light must be on within 60 seconds of operating the APU start
switch.
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 seconds
Between 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 operating
envelope:
Airspeed:
Temperature:
Sea level to 10,000 feet:
10,000 feet to 20,000 feet:
Altitude:
0 to 290 KIAS
141 KIAS to 290 KIAS
Refer to Figure 2
Refer to Figure 4 or 4A
Do not operate the APU in-flight if a main engine fails and engine rotor
burst 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 feet
and 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 standby
electrical 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.
DOT Approved
Dec 21/06
44,600/45,100
LIMITATIONS
Page 13
MODEL CL−600−2A12
AIRPLANE FLIGHT MANUAL
PSP 601−1A−1
4. POWER PLANT LIMITATIONS (Cont’d)
M. AUXILIARY POWER UNIT (APU) OPERATING LIMITS (Cont’d)
Main Engine Starting:
During double engine failure conditions, APU bleed air extraction for
engine 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 main
generators have failed. Use of the APU generator is not permitted
unless both main generators are off line.
LIMITATIONS
Page 14
DOT Approved
Sep 11/06
44,600/45,100
DOT Approved
Sep 11/06
44,600/45,100
AIRSPEED: 0 to 290 KIAS
AIRSPEED: 141 KIAS to 290 KIAS
MODEL CL−600−2A12
AIRPLANE FLIGHT MANUAL
PSP 601−1A−1
APU In-Flight Envelope
(Airplanes NOT Incorporating
Service Bulletin 601−0568 or 601−0581)
Figure 4
LIMITATIONS
Page 14A
MODEL CL−600−2A12
AIRPLANE FLIGHT MANUAL
PSP 601−1A−1
APU Operation is permitted up to 20,000 feet.
APU in-flight starting is guaranteed up to 20,000 feet.
Main engine starting is guaranteed up to 15,000 feet.
25
APU generator operation is guaranteed up to 20,000 feet.
APU pneumatic operation is guaranteed up to 15,000 feet.
APU start and generator operation guaranteed − 20,000 feet
20
Main engine start and
pneumatic operation guaranteed − 15,000 feet
ALTITUDE X 1000 FT.
15
10
5
0
0
100
141
LIMITATIONS
Page 14B
200
KIAS (KNOTS)
APU In-Flight Envelope
(Airplanes Incorporating
Service Bulletin 601−0568 or 601−0581)
Figure 4A
300
290
DOT Approved
Sep 11/06
44,600/45,100
canadair
chanenqer
MODEL CL-600-2A12
AIRPLANE FLIGHT MANUAL
PSP 601-1A-1
4. POWER PLANT LIMITATIONS (Cont'd)
N. POWER PLANT INSTRUMENT MARKINGS
Maximum and minimum limitations:
Takeoff and caution range:
Normal operating range:
(1)
FAN SPEED RPM INDICATION (N1) % RPM
98.6%
0 to 98.6%
(2)
Red radial line
Yellow vertical band
Green vertical band
Red radial line
Green vertical band
INTERSTAGE TURBINE TEMPERATURE INDICATOR (ITT)
857°C
Red radial line
838°C to 857°C
Yellow vertical band
0 to 838°C
Green vertrical band
L/R red overtemperature warning lights will come
on when ITT reaches 856°C.
(3)
TURBINE SPEED RPM INDICATOR (N2) % RPM
99.4%
99.2 to 99.4%
0 to 99.2%
(4)
OIL TEMPERATURE INDICATOR
163°C
150°C to 163°C
-40°C to 150°C
(5)
Red radial line
Yellow vertical band
Green vertical band
Red radial line
Yellow horizontal band
Green vertical band
OIL PRESSURE INDICATOR
100 psi
Red radial line
95 psi to 100 psi
Yellow vertical band
25 psi to 95 psi
Green vertical band
25 psi
Red horizontal line
The low oil pressure warning lights will come on
when oil pressure drops below 28±3 psi.
(6)
FUEL TEMPERATURE INDICATOR
60°C to 70°C
5°C to 60°C
-20°C to 5°C
DOT Approved
2 5 / 0 2 ,nn
Oct
44,600/45,100
Yellow band
Green band
Yellow band
LIMITATIONS
Page 15
canadair
chanenqer
MODEL CL-600-2A12
AIRPLANE FLIGHT MANUAL
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.
0 MILS D.A. to 1.7 MILS D.A.
Yellow band
Green band
(8) APU EXHAUST GAS TEMPERATURE (EGT) INDICATION
730°C
680°C to 730°C
0°C to 680°C
Red radial line
Yellow band
Green band
(9) APU TACHOMETER INDICATOR % RPM
110%
105% to 110%
0% to 105%
Red radial line
Yellow band
Green band
DOT Approved
LIMITATIONS
Page 16
Oct 25/02
44,600/45,100
canadair
chanenqer
MODEL CL-600-2A12
AIRPLANE FLIGHT MANUAL
PSP 601-1A-1
5. MAXIMUM OPERATING LIMIT SPEEDS
Maximum operating limit speeds must not be deliberately exceeded in any
regime of flight (climb, cruise or descent), unless a higher speed is
specifically authorized for flight test or training operations.
A. MAXIMUM OPERATING SPEED (VMO) AND MACH NUMBER (MMO)
Altitude; (feet)
Pilot's
Altimeter
Copilot's
Altimeter
0 to 10,000
10,000 to
21,420
21,420 to
25,740
25,740 to
28,640
28,640 and
above.
0 to 10,000
10,000 to
21,270
21,270 to
25,590
25,590 to
28,200
28,200 and
above.
Maximum Operati ng Limi t Speed
VMO
(KIAS)
MMO
(MI)
301
360
_
—
0.79
330
—
—
0.835
B. RVSM MAXIMUM OPERATING SPEED
On airplanes incorporating Canadair Service Bulletin 601-0484, Reduced
Vertical Separation Minimum (RVSM) - 1000 Ft. Aircraft Qualification
Requirements, the maximum cruise mach number during flight in RVSM
airspace is 0.82.
C. DESIGN MANOEUVERING SPEED (VA)
Full application of rudder and aileron controls as well as manoeuvers
that involve angles of attack near the stall, must be confined to speeds
below VA. Values of VA are given in Figure 5 for varying airplane
altitudes and weights.
Avoid rapid and large alternating control
inputs, especially in combination with large
changes in pitch, roll, or yaw (e.g. large
side slip angles), as they may cause
structural failure at any speed, including
below VA.
DOT Approved
Jul 16/04
44,600/45,100
LIMITATIONS
Page 17
MODEL CL-600-2A12
AIRPLANE FLIGHT MANUAL
PSP 601-1A-1
Weight
Ob)
Weight
(kg)
24,525
31,000
36,000
38,000
43,100
44,600
45,100
11,124
14,061
16,329
17,237
19,550
20,230
20,457
(SB 601-0360)
Design ^lanoeuveri ng Speed (VA)
(KIAS)
Altitude
(feet)
Sea Level
172
193
211
217
236
241
243
10,000
174
201
224
232
256
263
265
15,000
179
209
234
243
267
275
278
20,000
186
219
245
254
278
286
290
25,000
194
229
255
265
289
297
299
30,000
203
238
264
274
294
304
304
35,000
211
245
268
276
-
-
-
40,000
218
248
-
-
-
-
-
45,000
225
-
-
-
-
-
-
LIMITATIONS
Page 18
Design Manoeuvering Speed - VA
Figure 5
DOT Approved
Sep 25/90
44,600
canacfair
chauenQer
MODEL CL-600-2A12
AIRPLANE FLIGHT MANUAL
PSP 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
flaps to 30 degrees:
198 KIAS
flaps to 45 degrees:
190 KIAS
E. MAXIMUM LANDING GEAR OPERATING SPEED (VL0)
|
The maximum airspeed at which the landing gear may be lowered or raised is
197 KIAS/0.7 M L
F. MAXIMUM LANDING GEAR EXTENDED SPEED (VLE)
|
The maximum airspeed at which the airplane may be flown with the landing
gear 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 and
Fasteners, but not Part C, the maximum airspeed at which the airplane may
be 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 generator
following automatic or manual deployment is 250 KIAS. When operationally
necessary, 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 linear
interpolation. For flight test or pilot training deployment, the maximum
airspeed is 215 KIAS.
I. TURBULENCE PENETRATION SPEED
|
Turbulence penetration speed is 280 KIAS or 0.75 Mi, whichever is lower.
DOT Approved
Mf 27/97
44,600/45,100
LIMITATIONS
Page - 1 9
MODEL CL-600-2A12
AIRPLANE FLIGHT MANUAL
PSP 601-1A-1
6. MINIMUM OPERATING LIMIT SPEED
Intentional speed reduction below the onset of stall warning, as defined by
stick shaker operation, is prohibited unless a lower speed is specifically
authorized for f l i g h t test or training operations.
7. MANOEUVERING LIMIT LOAD FACTORS
These load factors l i m i t the permissible angles of bank in turns and the
severity of pull-up manoeuvers:
Flaps up:
Flaps down:
-1.0 G to 2.56 G
0.0 G to 2.0 G
DOT Approved
LIMITATIONS
Page 20
°(l
canadair
chauenqer
MODEL CL-600-2A12
AIRPLANE FLIGHT MANUAL
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 not
exceed 1.0 psi.
B. AUTOMATIC FLIGHT CONTROL SYSTEM
Operation of the autopilot is prohibited at altitudes below 200 feet above
ground level.
The autopilot must be disengaged at speeds below VR^p.
The autopilot is not approved for continued approach following engine
failure on final approach (refer to EMERGENCY PROCEDURES - AUTOMATIC FLIGHT
CONTROL SYSTEM EMERGENCIES).
Maximum flap angle for single engine autopilot coupled approach is 20
degrees with V R E F + 20 KIAS.
DOT Approved
Mar 10/89
44,600
LIMITATIONS
Page 21
canadair
chanenqer
MODEL CL-600-2A12
AIRPLANE FLIGHT MANUAL
PSP 601-1A-1
8. SYSTEMS LIMITATIONS (Cont'd)
C. ELECTRICAL SYSTEMS
Unless it has been established that any AC Generator with a part number
720845, 720845A or 720845B has more than 150 operating hours:
Prior to every flight a visual inspection of the engine cowls and
drains 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 number
720845, 720845A or 720845B has more than 150 operating hours:
Prior to every flight a visual inspection of the APU drains for
evidence of generator oil leakage must be conducted. If oil leakage
is evident, APU Generator must be replaced unless it has been
established that AC Generators with part numbers 720845, 720845A or
720845B are not installed, or if installed, both have more than 150
operating hours.
(1)
Permissible Loads on AC Systems
Individual AC generator loading, as indicated by the loadmeters, must
not exceed the following values:
L o a d Limitationmi tat ion
(kVVA)
0
11,000
20,000
35,000
- 11,000
- 20,000
- 35,000
and above
30
30
30
25
APU Generator
CO
CD
Main Generator
(each)
CO
CD
Altitude
(feet)
DOT Approved
LIMITATIONS
Page 22
Oct 25/02
44,600/45,100
canadair
chanenqer
MODEL CL-600-2A12
AIRPLANE FLIGHT MANUAL
PSP 601-1A-1
8. SYSTEMS LIMITATIONS (Cont'd)
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 is
100 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 limits
shown in Figure 6 or Figure 7.
Individual loads on TRU 1 and TRU 2 must not exceed 100 amps. If
TRUs are inadvertently operated at limiting loads for periods
longer than those shown, the nose bay doors must be opened for
10 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 to
30 minutes unless at least one environmental control system is
operating and cabin doors closed.
DOT Approved
2 5 / 0 2 ,nn
Oct
44,600/45,100
LIMITATIONS
Page
canadair
chanenqer
MODEL CL-600-2A12
AIRPLANE FLIGHT MANUAL
PSP 601-1A-1
THIS PAGE INTENTIONALLY LEFT BLANK
DOT Approved
LIMITATIONS
Page 22B
Oct 25/02
44,600/45,100
canadair
chaiienqier
MODEL CL-600-2A12
AIRPLANE FLIGHT MANUAL
PSP 601-1A-1
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DOT Approved
Mar 10/89
44,600
Maximum Permissible Loads on DC Electrical System Ground Operation
Figure 6
LIMITATIONS
Page 23
canadair
chanencjer
MODEL CL-600-2A12
AIRPLANE FLIGHT MANUAL
PSP 601-1A-1
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Maximum Permissible Loads on DC Electrical System - Ground
Operation - Airplanes 3040 and Subsequent and Airplanes
Incorporating Canadair Service Bulletin 601-0107
Figure 7
LIMITATIONS
Page 24
DOT Approved
Mar 10/89
44,600
MODEL CL−600−2A12
AIRPLANE FLIGHT MANUAL
PSP 601−1A−1
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 is
prohibited.
(2)
Flight Spoilers
On airplanes 3001 to 3039 which do not incorporate Canadair Service
Bulletin 601-0040, Modification − Central Warning System − Flight
Spoilers, or on airplanes incorporating Canadair Service Bulletin
601-0040 (Initial issue) and Canadair Service Bulletin 601-0095,
Modification − Flight Spoiler Warning System − Elimination of
Spurious Warnings:
(a) Flight below an altitude of 700 feet agl with flight spoilers
extended and the flaps retracted is prohibited.
(b) Flight spoilers must not be extended in flight with flaps
extended.
On airplanes 3013, 3018 to 3023, 3040 and subsequent and airplanes
incorporating Canadair Service Bulletin 601-0040 (Initial issue) only
(i.e. Service Bulletin 601-0095 not incorporated) or Canadair Service
Bulletin 601-0040 (Rev. 1):
(a) Flight below an altitude of 300 feet agl with flight spoilers
extended is prohibited.
(b) To ensure adequate manoeuvre margins, flight spoilers must not
be extended in flight at airspeeds below the recommended
approach speed (refer to PERFORMANCE − LANDING) plus 10 KIAS.
(3)
Ground Spoilers
On airplanes 3001 to 3059 which do not incorporate Canadair Service
Bulletin 601-0113, Modification − Ground Spoilers − Auto Deployment:
The spoiler lever must not be selected to the GROUND SPOILER position
in flight.
DOT Approved
Apr 20/98
44,600/45,100
LIMITATIONS
Page 25
MODEL CL−600−2A12
AIRPLANE FLIGHT MANUAL
PSP 601−1A−1
8. SYSTEMS LIMITATIONS (Cont’d)
E. FUEL SYSTEM
The maximum permissible fuel imbalance between the contents of the main
fuel tanks is 800 lb (363 kg).
Take-off with up to 500 lb (230 kg) of fuel in the auxiliary tank is
permitted, provided that there is at least 1500 lb (690 kg) of fuel in
each 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 is
permitted, provided that there is at least 4400 lb (1996 kg) of fuel in
each wing tank.
Fuel remaining in a tank when the appropriate fuel quantity indicator reads
zero is not usable.
The maximum usable fuel quantities shown below are achieved by pressure
fueling 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 fuel
tanks, maximum usable fuel quantity is:
Left Main Tank
Right Main Tank
Fuselage Tanks
Total
2.
Total
16,626 lb
(7,541 kg)
4,879 lb
4,879 lb
5,736 lb
(2,213 kg)
(2,213 kg)
(2,601 kg)
15,494 lb
(7,027 kg)
On airplanes 3001 − 3014 equipped with Forward and Aft fuselage fuel
tanks, incorporating Canadair Service Bulletin 601−0535, maximum
usable fuel quantity is:
Left Main Tank
Right Main Tank
Fuselage Tanks
Total
LIMITATIONS
Page 26
(2,213 kg)
(2,213 kg)
(3,115 kg)
On airplanes 3001 − 3014 equipped with Aft fuselage fuel tank only,
maximum usable fuel quantity is:
Left Main Tank
Right Main Tank
Fuselage Tanks
3.
4,879 lb
4,879 lb
6,868 lb
4,879 lb
4,879 lb
2,610 lb
(2,213 kg)
(2,213 kg)
(1,184 kg)
12,368 lb
(5,610 kg)
DOT Approved
Jan 19/07
44,600/45,100
MODEL CL−600−2A12
AIRPLANE FLIGHT MANUAL
PSP 601−1A−1
8. SYSTEMS LIMITATIONS (Cont’d)
E. FUEL SYSTEM (Cont’d)
4.
On airplanes 3015 and subsequent equipped with Forward and Aft
fuselage fuel tanks, maximum usable fuel quantity is:
Left Main Tank
Right Main Tank
Fuselage Tanks
Total
5.
(2,227 kg)
(2,227 kg)
(3,115 kg)
16,686 lb
(7,569 kg)
On airplanes 3015 and subsequent equipped with Aft fuselage fuel tank
only, maximum usable fuel quantity is:
Left Main Tank
Right Main Tank
Fuselage Tanks
Total
6.
4,909 lb
4,909 lb
6,868 lb
4,909 lb
4,909 lb
5,736 lb
(2,227 kg)
(2,227 kg)
(2,601 kg)
15,554 lb
(7,055 kg)
On airplanes 3015 and subsequent equipped with Forward and Aft
fuselage fuel tanks, incorporating Canadair Service Bulletin 601−0535,
maximum usable fuel quantity is:
Left Main Tank
Right Main Tank
Fuselage Tanks
Total
4,909 lb
4,909 lb
2,610 lb
(2,227 kg)
(2,227 kg)
(1,184 kg)
12,428 lb
(5,638 kg)
On airplanes incorporating Canadair Service Bulletin 601−0535, operation
with more than 2,610 lb (1,184 kg) of fuel in the auxiliary tank is
prohibited.
NOTE
Following a rejected take-off on airplanes
incorporating Canadair Service Bulletin
601−0535, inspect the forward auxiliary tank
to ensure that there has been no migration of
fuel, in accordance with paragraph 2.C. of
Canadair Service Bulletin 601−0535.
F. STALL PROTECTION SYSTEM
Both stall protection systems must be fully operative for take-off and
remain on for all phases of flight.
The stall protection test indicator must only be used for S.P.S.
functional test purposes.
DOT Approved
Jan 19/07
44,600/45,100
LIMITATIONS
Page 27
MODEL CL−600−2A12
AIRPLANE FLIGHT MANUAL
PSP 601−1A−1
8. SYSTEMS LIMITATIONS (Cont’d)
G. NOT USED
H. NOT USED
I. NOT USED
J. WHEEL BRAKE COOLING LIMITATIONS
Brake cooling times (established in accordance with the procedures in
NORMAL PROCEDURES-LANDING GEAR WHEELS AND BRAKES) must be observed
between a landing or a low-energy rejected take-off (RTO) and a
subsequent take-off, to ensure that sufficient brake energy is available
to bring the airplane to a complete stop, if the subsequent take-off is
rejected.
If a fusible plug releases, the affected wheel, brakes and the anti-skid
wheel speed sensors must be inspected in accordance with the procedures
in the CL-601 Time Limits/Maintenance Checks, PSP601−5, and any damage
rectified before the next take-off.
K. WHEEL BRAKES ANTI-SKID
Take-off with the wheel brakes anti-skid system inoperative is
prohibited.
L. BLEED AIR SYSTEMS
The bleed air 10th stage valves must be closed for take-off and landing
with 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 unloaded
inflation pressures between 198 psi and 145 psi, the maximum take-off
weight (MTOW) is limited (refer to Figures 8 and 9).
The maximum nosewheel tire pressure is 151 psi (1041 kPa) +5%, −0 on the
ground.
On airplanes incorporating Canadair Service Bulletin 601−0205,
Modification − Flight Compartment Tire Pressure Caution Placard − Special
Operating Conditions Only:
Tire pressures must be verified daily and a placard installed on the
pilot’s instrument panel.
LIMITATIONS
Page 28
DOT Approved
Jan 19/07
44,600/45,100
canadair
chaiienQer
MODEL CL-600-2A12
AIRPLANE FLIGHT MANUAL
PSP 601-1A-1
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DOT Approved
Mar 10/89
44,600
Tire Pressures vs Maximum Take-Off Weight (MTOW)
(25.75 x 6.75 - 14 PR Tires)
Figure 8
LIMITATIONS
Page 29
canadair
chanenqer
MODEL CL-600-2A12
AIRPLANE FLIGHT MANUAL
PSP 601-1A-1
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LIMITATIONS
Page 30
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Tire pressures vs Maximum Take-Off Weight (MTOW)
(A/C incorporating Service Bulletin 601-0360)
(25.75 x 6.75 - 14 PR tires)
Figure 9
DOT Approved
Sep 25/90
44,600
MODEL CL−600−2A12
AIRPLANE FLIGHT MANUAL
PSP 601−1A−1
8. SYSTEMS LIMITATIONS (Cont’d)
O. THRUST REVERSERS
Thrust reversers are approved for ground use only.
The thrust reverser pre-flight checks (NORMAL PROCEDURES) must be
successfully accomplished and the proper indications obtained on each
operative thrust reverser prior to each take-off.
Thrust reversers are intended for use during full stop landings. Do not
attempt a go-around manoeuvre after deployment of the thrust reversers.
Application of reverse thrust above 60% N1 is not permitted at airspeeds
below 60 KIAS.
The maximum demonstrated crosswind component approved for use of reverse
thrust is 24 knots (at 33 feet (10 meters) tower height). This value was
demonstrated on a dry runway and is considered limiting.
P. TAXI LIGHTS
Taxi lights must be switched off whenever the airplane is stationary in
excess of 10 minutes.
Q. AIR DATA SYSTEM
On airplanes incorporating Canadair Service Bulletin 601−0484, Reduced
Vertical Separation Minimum (RVSM) − 1000 Ft. Aircraft Qualification
Requirements;
S The ADC source coupled to the active autopilot must be the same as that
coupled to the ATC transponder during flight in RVSM airspace.
S If alternate static source is selected, airplane must not be operated
in RVSM airspace.
9. CONFIGURATION DEVIATION LIST
If the airplane is to be operated with certain secondary airframe and/or
nacelle parts missing, operation must be in accordance with the limitations
specified in the basic Airplane Flight Manual, and as amended by the
Configuration Deviation List (Appendix 1).
DOT Approved
Jan 19/07
44,600/45,100
LIMITATIONS
Page 31