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CL−604 Airplane Flight Manual
PSP 604−1
1. FLIGHT CONTROLS (CONT'D)
C. Rudder System Jammed (Cont’d)
NOTE
After touchdown, use nose wheel steering and, if necessary, differential
braking to maintain directional control, as the airplane will turn in the
direction of the jammed rudder.
END
EMERGENCY PROCEDURES
Flight Controls
03−12−5
REV 74, Nov 07/08
DOT Approved
CL−604 Airplane Flight Manual
PSP 604−1
1. FLIGHT CONTROLS (CONT'D)
D. Stabilizer Trim Runaway
Indication: Abnormal/uncommanded change in pitch attitude.
Stabilizer trim changes without pilot input.
Higher or lower than normal and increasing or decreasing pitch control
forces.
(1) Control column ..................................................Assume manual control and override
runaway.
(2) Both STAB TRIM DISC switches ..........................Press hold and release.
(3) Control .............................................................. Transfer to pilot (left) side.
(4) STAB CH1 and CH2 HSTCU
circuit breakers (2F8 and 4B8) .............................. Open
(5) Airspeed ...............................................................Adjust to minimize out of trim
condition.
NOTE
1. If a pull force is required, increase airspeed. If a push force
is required, decrease airspeed.
2. Do not exceed VMO /MMO or minimum maneuvering speed
as appropriate.
3. Flight spoilers will reduce airspeed and provide nose up
pitch.
4. Reducing thrust will reduce airspeed and provide nose up
pitch.
5. Autopilot, stabilizer trim and Mach trim are not available.
(6) Land immediately at the nearest suitable airport.
Prior to landing:
(7) GPWS/FLAP OVRD switch
(if installed) ...........................................................Select to OVRD, to mute the flap
aural warning.
(8) Recommended FLAPS.........................................Select to 20° for landing.
CAUTION
Selection of Flaps 20 will increase nose down pitching moment slightly,
and therefore should be selected just prior to approach in the event of a
full nose down stabilizer position. Selection of Flaps 20 significantly
reduces landing field length compared to Flaps 0.
If control forces are excessive, some relief may be gained by adjusting
airspeed or flap position. Reduced flap settings generally reduce pull
forces. Increased flap settings generally reduce push forces.
EMERGENCY PROCEDURES
Flight Controls
03−12−6
REV 74, Nov 07/08
▼
DOT Approved
CL−604 Airplane Flight Manual
PSP 604−1
1. FLIGHT CONTROLS (CONT'D)
D. Stabilizer Trim Runaway (Cont’d)
(9) Final approach speed...........................VREF (Flaps 45°)
+ ΔVREF for applicable flap setting.
(10) Actual landing distance .................................... Increase by factor given below:
Flaps Setting
(Degrees)
Δ VREF
(KTS)
ALD Factor
Without Thrust Reversers With Thrust Reversers
0 30 1.80 (80%) 1.75 (75%)
20 14 1.55 (55%) 1.50 (50%)
30 7 1.40 (40%) 1.35 (35%)
CAUTION
Do not jettison fuel if trim runaway is in nose down direction.
Fuel jettison will cause the CG to move forward requiring a larger pull
force to counter and causing any push force to be reduced.
Consider use of fuel jettison in the event of a nose-up trim runaway
condition.
A landing may be made with fuel in the tail tank.
WARNING
In the event of a go-around, increasing thrust will increase nose down
forces. Increase thrust slowly to avoid excessive pitch force.
END
EMERGENCY PROCEDURES
Flight Controls
03−12−7
REV 74, Nov 07/08
DOT Approved
CL−604 Airplane Flight Manual
PSP 604−1
EMERGENCY PROCEDURES
Flight Controls
03−12−8
REV 74, Nov 07/08
DOT Approved
CL−604 Airplane Flight Manual
PSP 604−1
THIS PAGE INTENTIONALLY LEFT BLANK
1. FUEL SYSTEM
A. Low Fuel
Indication: The EICAS fuel quantities turn amber when either main tank is less than
230 kg (500 lb), or the total fuel quantity is less than 460 kg (1,000 lb).
(1) Airplane ...............................................Not more than 5°
nose up
(2) Fuel balance.........................................................Check
(3) Land at the nearest suitable airport.
NOTE
Do not attempt go-around. The minimum fuel quantity for go-around is
230 kg (500 lb) per wing (with the airplane level), and assuming a
maximum airplane climb attitude of 10° nose up.
　
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