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Figure 02−05−3
LIMITATIONS
Power Plant
Vol. 1 02−05−11
Oct 05/06
CL−605 Flight Crew Operating Manual
PSP 605−6
10. OIL GRADES
Refer to appropriate maintenance or servicing manual for approved oil grades.
11. OIL CONSUMPTION
Maximum oil consumption, on each engine, is 189 cubic centimeters per hour
(6.4 ounces per hour/0.05 US gallons per hour).
12. 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.
13. AUXILIARY POWER UNIT
A. Type
36–150 (CL)
B. Maximum RPM: 110%
The APU overspeed control will automatically shutdown the APU at 107% rpm.
C. Maximum EGT: 731°C
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.
LIMITATIONS
Power Plant
Vol. 1 02−05−12
Oct 05/06
CL−605 Flight Crew Operating Manual
PSP 605−6
13. AUXILIARY POWER UNIT (CONT'D)
D. Starting: (Cont’d)
(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 02−05−4.
(6) In-flight start:
In-flight starting is guaranteed at altitudes up to 20,000 feet.
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
permitted.
Inflight APU main engine starts have been demonstrated to 15,000 feet.
(3) Air Conditioning:
(a) Bleed air extraction from the APU is not permitted above 15,000 feet.
F. APU Generator
The maximum permissible load on the APU generator in flight is 30kVA.
G. APU Indications
The APU limit display markings on the EICAS must be used to determine compliance with the
maximum/minimum limits and precautionary ranges. If EICAS markings show more
conservative limits than those specified below, the limit markings on the EICAS should be
used.
INDICATION
RED
(MAX LIMITATIONS)
AMBER
(CAUTION RANGE)
GREEN
(NORMAL RANGE)
APU
EGT °C
start scale 974 and above – 0 to 973
normal scale 731 and above 680 to 730 0 to 679
APU RPM % 110 and above 105 to 109 0 to 104
LIMITATIONS
Power Plant
Vol. 1 02−05−13
Oct 05/06
CL−605 Flight Crew Operating Manual
PSP 605−6
13. AUXILIARY POWER UNIT (CONT'D)
LIMITATIONS
Power Plant
Vol. 1 02−05−14
Oct 05/06
APU In-Flight Envelope
Figure 02−05−4
CL−605 Flight Crew Operating Manual
PSP 605−6
1. MAXIMUM OPERATING SPEED AND MACH NUMBER
Maximum operating limit speeds as given in Figure 02−06−1, 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.
DFM0206_001
Maximum Operating Speed and Mach Number
Figure 02−06−1
2. RVSM MAXIMUM OPERATING SPEED
The maximum cruise mach number during flight in RVSM airspace is 0.83.
　
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