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During taxi, take-off and landing, the pressure differential must not exceed 0.2 psi.
The airplane must be completely depressurized prior to opening any of the airplane doors.
2. AUTOMATIC FLIGHT CONTROL SYSTEM
The minimum autopilot engage height after take-off is 320 feet AGL.
The minimum autopilot use height for visual and non-precision approaches is 320 feet
AGL.
The minimum autopilot use height for precision approaches (ILS) is 80 feet AGL.
Operations with an ILS glidepath angle that exceeds 3.5 degrees are prohibited.
On airplanes incorporating Canadair Service Bulletin 604–34–012:
The ADC source coupled to the active autopilot must be the same as that coupled to the
ATC transponder during flight in RVSM airspace.
3. BLEED AIR SYSTEMS
The bleed air 10th stage valves must be closed for take-off and landing if the engine cowl
and/or wing anti-ice systems have been selected on.
If above 40,000 feet, one air-conditioning unit or cowl anti-ice system must be selected on
for each engine.
15/05/95
CL-604 Airplane Flight Manual
PSP 604–1
DOT Approved
REV 54, Jul 16/04
LIMITATIONS
Systems Limitations
02–08–2
4. ELECTRICAL SYSTEMS
A. A/C Generators
Unless it has been established that an A/C main 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, the
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 AC generator
oil leakage must be conducted. If generator oil leakage is evident, the 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, that both have more
than 150 operating hours.
B. Permissible Loads on AC System
Individual AC generator loading must not exceed the following values:
ALTITUDE
LOAD LIMITATION
(kVA)
(FEET) MAIN GENERATOR
(EACH)
APU GENERATOR
0 - 20,000 30 30
20,001 to 35,000 30 0
35,001 and above 25 0
C. Permissible Loads on DC Systems
The maximum permissible continuous load on each TRU is 100 amps.
5. FLIGHT CONTROLS - LIFT/DRAG DEVICES
A. Flaps
En-route use of flaps is prohibited.
Flight with flaps extended at altitudes above 15,500 feet is prohibited.
B. Flight Spoilers
Flight below an altitude of 300 feet AGL with flight spoilers extended is prohibited.
To ensure adequate maneuver margins, flight spoilers must not be extended in flight at
airspeeds below the recommended approach speed plus 10 KIAS (refer to Chapter 6;
PERFORMANCE - LANDING PERFORMANCE).
6. STALL PROTECTION SYSTEM
Both stall protection system pusher switches must remain on for all phases of flight.
The stall protection test indicator must only be used for stall protection system functional test
purposes.
15/05/95
CL-604 Airplane Flight Manual
PSP 604–1
DOT Approved
REV 26, Apr 20/98
LIMITATIONS
Systems Limitations
02–08–3
7. THRUST REVERSERS
Thrust reversers are approved for ground use only.
The thrust reversers are intended for use during full stop landings. Do not attempt a
go-around maneuver after deployment of the thrust reversers.
Backing the airplane with the use of reverse thrust is prohibited.
Take-off with any of the following thrust reverser icons, or EICAS messages displayed is
prohibited:
REV icon on N1 gauge,
L or R REV UNLOCKED caution message, and
L or R REV UNSAFE caution message.
During landing, application of maximum reverse thrust is not permitted, at airspeeds below
60 KIAS. Below 60 KIAS, reverse thrust must be reduced to 60% N1 or less.
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.
8. TAXI LIGHTS
The taxi lights must be selected off whenever the airplane is stationary in excess of 10 minutes.
9. WHEEL BRAKE COOLING LIMITATIONS
Brake cooling times (established in accordance with the procedures in Chapter 6–
PERFORMANCE – MINIMUM TURN-AROUND TIME must be observed between a landing or a
low-energy rejected take-off (RTO) and a subsequent take-off, to ensure that sufficient brake
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