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C. L MAIN / R MAIN DC SENSE Circuit Breakers (CBs) ....................PULL
OPERATING MANUAL
05-07-00 EXPANDED ABNORMAL / EMERGENCY PROCEDURES
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October 11/01
Revision 5
• L MAIN DC SENSE: Pilot’s Aft Panel, H-14
• R MAIN DC SENSE: Pilot’s Aft Panel, I-14
D. STANDBY ELECTRICAL POWER STBY ELEC Switch.......................ON
E. STANDBY ELECTRICAL POWER TRU Switch....................................ON
F. Battery Ammeters.....................MONITOR / LOAD SHED IF REQUIRED
NOTE:
Steps 6B through 6F cause DU 2 to be unpowered,
DU 6 to “Red X” and the copilot’s PFD to auto-transfer
to DU 5 (SPZ-8400 equipped aircraft ony). Selecting
SYMBOL GENERATOR CONTROL to NORM-ALTALT
on the SG Reversionary Panel will restore the
copilot’s displays to normal. DU 2 will remain
unpowered for the remainder of the flight.
G. Engine Power ..........................MAINTAIN 67% HP RPM WHILE IN THIS
CONFIGURATION
H. Approach And Landing...................................PERFORM AS FOLLOWS
NOTE:
The flight crew may elect to land with “batteries only”
powering the essential bus provided there is power to
the main buses from the converters. Load shedding of
the MAIN fuel boost pumps and opening the crossflow
valve prior to landing should be sufficient to preserve
batteries.
(1) Gear Handle...........................................................................DOWN
(2) Flaps.................................................................SET FOR LANDING
(3) Emergency Batteries ..................................................................ON
(4) Ground Spoilers........................................................................OFF
(5) Engine Power .....MAINTAIN 67% HP RPM UNTIL TOUCHDOWN
NOTE:
Once the airplane is on the ground, there is no need to
continue to maintain 67% HP RPM. The Standby
Electrical Power system will stay on line during normal
taxi maneuvers. If the Standby Electrical Power
system is interrupted, cycle the STANDBY
ELECTRICAL POWER STBY ELEC Switch OFF, then
ON, to regain power.
(6) Reverse Thrust ..........................................................DO NOT USE
ON TOUCHDOWN:
(7) Flight Spoilers ..............................MANUALLY DEPLOY SLOWLY
(APPROXIMATELY 5 SECONDS)
(8) Airplane....................................STOP USING NORMAL BRAKING
OPERATING MANUAL
EXPANDED ABNORMAL / EMERGENCY PROCEDURES 05-07-00
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October 11/01
Revision 5
OPERATING MANUAL
THIS PAGE IS INTENTIONALLY LEFT BLANK.
05-07-00 EXPANDED ABNORMAL / EMERGENCY PROCEDURES
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ENGINE CONTROL SYSTEM
05-08-10: Engine Synchronizer Failure
Failure of the engine synchronizer will be evident by the left engine failing to maintain
synchronization with the right engine on either Low Pressure Turbine (LP % RPM) or
High Pressure Turbine (HP % RPM) speed. Should this occur, select the engine
synchronizer (SYNC OFF/ON switch) to OFF.
The engine synchronizer has also failed if, when selecting the system off, the operating
light fails to extinguish after fifteen (15) seconds. Should this occur, pull the ENG SYNC
circuit breaker, located on the Pilot’s Aft CB Panel, K-9.
If the engine synchronizer has failed, power lever stagger and asymmetric reverse thrust
may be expected but should not present control problems. With the engine synchronizer
in the failed mode, the approach idle system will not limit the engine to its minimum
approach idle speed of 67% HP RPM. Therefore, engine RPM must be monitored on
approach.
On airplanes Serial Number (SN) 1214 and subsequent and SN 1000 through 1213
having drawing 1159SB40761/1159SB40762 incorporated, the engine synchronizer
function is controlled by the autothrottle. The engine synchronizer function is only
available when the autothrottle is engaged and autothrottle is in a speed control mode,
i.e., CRUISE mode, V/S mode, V PATH mode or PITCH HOLD mode. The engine
synchronizer function is enabled with the autothrottle engaged by use of the SYNC
OFF/ON switch and HP/LP selector switches located on the cockpit overhead panel.
05-08-20: Approach Idle System Failure
1. Amber L-R ENG IDLE Light Illuminated:
A. In Flight:
(1) If flaps are at less than 39° (DOWN), minimum idle for
corresponding engine may increase to 67% HP RPM.
(2) If flaps are at 39° (DOWN), the flight crew must manually maintain
minimum engine RPM to 67% HP RPM on approach.
B. On Ground:
(1) Minimum idle for corresponding engine may increase to 67% HP
RPM.
2. Approach Idle System Failure - Amber L-R ENG IDLE Light not Illuminated:
　
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