NUMBER REQUIRED FOR DISPATCH
3 0 REMARKS OR EXCEPTIONS
EICAS STATUS MESSAGES
None
PLACARD
As appropriate
B757 - 200 MINIMUM EQUIPMENT LIST
EICAS STATUS MESSAGES
None
PLACARD
Hydraulic control panel as appropriate - __ PUMP OVHT LIGHT(S) INOP MAINTENANCE (M)
Check affected pump operation as follows:
CAUTION: DURING GROUND OPERATION OF THE AFFECTED PUMP, TO PREVENT HYDRAULIC
PUMP DAMAGE FROM OVERHEAT, DO NOT OPERATE PUMPS WITHOUT MINIMUM OF 300 KG OF FUEL IN TANKS.
NOTE 1: The pump being tested must be the only pump operating within the related hydraulic system at the time of the test.
NOTE 2: When running right engine (EDP) the PTU will pressurize the FLAP/SLAT and the LANDING GEAR hydraulic systems. The PTU can be deactivated by opening the HYDRAULICS PTU CONT circuit breaker on the P11 panel before engine start.
Test pump.
A. Engine driven pump:
Ensure that personnel are clear of flight controls.
Set the parking brake.
Turn associated EMP OFF.
With affected engine running, turn HYD PUMPS ENG switch to ON.
HYD PRESS reading on EICAS must be 2850 to 3150 psig.
B757 - 200 MINIMUM EQUIPMENT LIST
HYD TEMP reading on EICAS must be below 80°C after stabilization.
Restore airplane to its required configuration.
NOTE: If the PTU was deactivated during the test procedure, make sure the PTU is reactivated before engine start by closing the HYDRAULICS PTU CONT circuit breaker on the P11 panel.
B. Alternating current motor pump:
Ensure that personnel are clear of flight controls.
With electrical power on airplane, press affected HYD PUMPS ELEC switch to ON.
HYD PRESS reading on EICAS must be 2850 to 3150 psig.
HYD TEMP reading on EICAS must be below 80°C after stabilization.
Restore airplane to its required configuration.
B757 - 200 MINIMUM EQUIPMENT LIST
REPAIR INTERVAL NUMBER INSTALLED
ITEM NUMBER REQUIRED FOR DISPATCH
REMARKS OR EXCEPTIONS
29-33-1 Hydraulic System Low QTY
or RSVR Lights C 3 0 May be inoperative provided HYD QTY indication(s) operates normally.
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