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in auxiliary tank.
• Auxiliary tank quantity must be continuously monitored for overfill during manual tail
tank fuel transfer.
DFM0205_003
3
0.5
1.0
1.5
2.0
2.5
3.0
TAIL TANK QUANTITY X 1000 LB
AUXILIARY TANK QUANTITY X 1000 LB
AUXILIARY TANK QUANTITY X 1000 KG
TAIL TANK QUANTITY X 1000 KG
0.25
7
6
5
4
3
1
0
0.50 0.75 1.0 1.25
2
0 1 2
AUXILIARY/TAIL TANK
FUEL QUANTITY MUST
REMAIN IN THIS ZONE
MANUAL TRANSFER
Manual Fuel Transfer − Auxiliary Tank Quantity vs Tail Tank Quantity
Figure 02−05−5
LIMITATIONS
Power Plant
Vol. 1 02−05−14
REV 71, Oct 31/07
CL−604 Operating Manual
PSP 604−6
8. FUEL (CONT'D)
E. Fuel Jettison
Fuel jettison must only be carried out with flaps set to 0.
Jettisoning of fuel in known lightning conditions is prohibited.
9. OIL GRADES
Refer to appropriate maintenance or servicing manual for approved oil grades.
10. OIL CONSUMPTION
Maximum oil consumption, on each engine, is 189 cubic centimeter per hour
(6.4 ounces per hour/0.05 US gallons per hour).
11. OIL REPLENISHMENT SYSTEM
The engine oil level should be checked between 15 minutes to 2 hours after engine shutdown.
The engines must be motored if the replenishment period is exceeded. Maximum refill allowable
is 1,890 cubic centilitres (2 US quarts) without dry motoring the engine.
12. AUXILIARY POWER UNIT
A. Type:
36–150 (CL)
On airplanes 5301 to 5630 NOT incorporating Service Bulletin 604–49–006 or
604–49–009:
GTCP-36-100(E)
B. Maximum RPM: 110%
The APU overspeed control will automatically shutdown the APU at 107% rpm.
On airplanes 5301 to 5630 NOT incorporating Service Bulletin 604–49–006 or
604–49–009:
The APU overspeed control will automatically shutdown the APU at 110% rpm.
C. Maximum EGT: 731°C
LIMITATIONS
Power Plant
Vol. 1 02−05−15
REV 71, Oct 31/07
CL−604 Operating Manual
PSP 604−6
12. AUXILIARY POWER UNIT (CONT'D)
D. Starting:
(1) Minimum ambient temperature for starting a cold soaked APU on the ground is –40°C.
(2) The following APU start cycles are permitted:
(a) Using airplane 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.
(c) If, in either case (2)(a) or (2)(b) a successful start is not obtained, a further start must
not be attempted for a period of at least 35 minutes.
(3) Maximum EGT:
974°C (not to be exceeded under any operating conditions)
(4) Hung start:
If not greater than 30% rpm within 60 seconds
On airplanes 5301 to 5630 NOT incorporating Service Bulletin 604–49–006 or
604–49–009:
Below 60% rpm – maximum 20 seconds
Between 60% and 95% rpm – maximum 10 seconds
(5) APU starting and operation is permitted within the following operating envelope:
• Temperature – Refer to Figure 02–04–1.
• Altitude and Airspeed – Refer to Figure 02−05−6 or Figure 02−05−7.
(6) In-flight start:
In-flight starting is guaranteed at altitudes up to 20,000 feet.
On airplanes 5301 to 5630 NOT incorporating Service Bulletin 604–49–006 or
604–49–009:
In-flight starting is guaranteed at altitudes up to 15,000 feet and has been demonstrated
at altitudes up to 20,000 feet.
LIMITATIONS
Power Plant
Vol. 1 02−05−16
REV 71, Oct 31/07
CL−604 Operating Manual
PSP 604−6
12. AUXILIARY POWER UNIT (CONT'D)
E. APU Bleed Air
(1) Engine-start during ground operations up to 15,000 feet:
(a) No bleed air extraction limitation. Each engine may be started using the APU as a
bleed air source.
(b) If both engines are to be started using the APU bleed air, then the operating engine’s
thrust must not exceed 70% N2.
(2) Engine-start during flight:
(a) During single engine operations, APU bleed air extraction for an engine start is not
permitted.
(b) During double engine failure conditions, APU bleed air extraction for engine starts is
　
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