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4. FIRE TEST Switchlight .........................................................................RELEASE
5. ENGINE FIRE Checklist.....................................................................COMPLETE
05-13-20: Fire Detection System Fault
ENG FLT LOOP ALRT (AMBER)
Each of the two (LOOP A and LOOP B) fire detection loops of each engine is provided
with a fault discriminator circuit. FAULT/OFF switchlights [one for each of the four loops
and a single FAULT TEST button (to test all four loops)] are located in the ENGINE
CONTROL section of the overhead panel.
If a fire detection loop develops a fault, the associated amber FAULT light will illuminate
and an amber ENG FLT LOOP ALRT caution message will be displayed on CAS,
accompanied by a two chime aural caution tone. Since both loops must sense a fire or
overheat condition in order to trigger an engine fire warning, the faulty loop will preclude
that capability until it has been isolated from the system. The faulty loop is isolated and
the fire detection system is restored to normal operation by depressing the associated
amber FAULT/OFF switchlight, resulting in the OFF legend illuminating in the switchlight.
OPERATING MANUAL
EXPANDED ABNORMAL / EMERGENCY PROCEDURES 05-13-00
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May 31/00
Revision 0
OPERATING MANUAL
THIS PAGE IS INTENTIONALLY LEFT BLANK.
05-13-00 EXPANDED ABNORMAL / EMERGENCY PROCEDURES
Page 2
May 31/00
FLAPS SYSTEM
05-14-10: Failure Of Stabilizer / Flap Interconnect
STAB FLAP FAIL (AMBER)
Failure of the stabilizer / flap interconnect may be indicated by display of an amber STAB
FLAP FAIL caution message on CAS. It will be confirmed by unsynchronized movement
of the stabilizer (HOR STAB) and FLAP needles on the stabilizer/flap position indicator,
as well as an out of trim condition as the flaps are moved.
SHOULD FAILURE OF THE STABILIZER / FLAP INTERCONNECT OCCUR,
PROCEED AS FOLLOWS:
1. Further Flap Movement ...............................................................................STOP
2. Airplane .............................................................LAND AS SOON AS POSSIBLE
IF FURTHER FLIGHT IS NECESSARY:
A. Flaps .................................................MATCH TO STABILIZER POSITION
B. Placard Speeds..........................................................................OBSERVE
3. GPWS / GND SPLR FLAP ORIDE ...................................................................ON
4. Landing.................................ACCOMPLISH ACCORDING TO FLAP POSITION
IF STABILIZER HAS FAILED AT 20° OR 39° POSITION, PERFORM STEPS A
AND B. IF STABILIZER HAS FAILED AT 0° OR 10° POSITION, PERFORM
STEPS C AND D.
STABILIZER FAILED AT 20° OR 39° POSITION:
A. Flaps .................................................MATCH TO STABILIZER POSITION
If appropriate, see Section 05-14-30: Partial Flaps Landings.
IF RUNWAY LENGTH IS LIMITED AND STABILIZER IS IN 20° POSITION:
B. 39° Flaps...................................................MAY BE USED FOR LANDING
If landing in this configuration, use full NOSE UP elevator trim as required
and expect heavy control column pull forces on final approach and during
landing.
STABILIZER FAILED AT 0° OR 10° POSITION:
C. Flaps .................................................MATCH TO STABILIZER POSITION
If appropriate, see Section 05-14-30: Partial Flaps Landings.
IF RUNWAY LENGTH IS LIMITED:
D. 20° Flaps...................................................MAY BE USED FOR LANDING
If landing in this configuration, use full NOSE UP elevator trim as required
and expect heavy control column pull forces on final approach and during
landing.
05-14-20: Wing Flaps - Alternate Operation
1. Use of Normal Flap Control:
If both the Combined Hydraulic System and Utility Hydraulic System fail, Auxiliary
Hydraulic System pressure can be used to operate the flaps. Regardless of the
pressure source used for flaps operation (Combined, Utility or Auxiliary), the
OPERATING MANUAL
EXPANDED ABNORMAL / EMERGENCY PROCEDURES 05-14-00
Page 1
May 31/00
Revision 0
normal FLAP control handle is still used to select flap position. Asymmetry
protection is still provided.
CAUTION
IF COMBINED (OR UTILITY) HYDRAULIC SYSTEM
OPERATING PRESSURE READS ZERO (0)
IMMEDIATELY AFTER SELECTING FLAPS, PULL
BOTH THE FLAP CONTROL CIRCUIT BREAKER
(COPILOT’S OVERHEAD, B-1) AND MANUAL FLAP
CONTROL CIRCUIT BREAKER (COPILOT’S
OVERHEAD, A-1) BEFORE SELECTING THE
AUXILIARY HYDRAULIC PUMP ON. THIS WILL
ENSURE THAT AUXILIARY HYDRAULIC SYSTEM
FLUID WILL BE AVAILABLE FOR BRAKING AFTER
　
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