(c)
Install a new packing (2) into the bowl cavity in the filter head (1). 1) Turn the bowl clockwise with your hand until the flange of
the bowl touches the filter head. 2) Tighten the bowl to 300 inch-pounds.
S 424-039-N00
(3)
Install a lockwire from the filter bowl to the filter head.
(4)
Remove the DO-NOT-OPERATE tags from the thrust levers.
S 864-031-N00
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
78-34-14
ALL ú ú N01 Page 406 ú Oct 18/01
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
S 424-009-N00
(5) Do the activation procedure for the thurst reverser
(AMM 78-31-00/201).
NOTE: Pressurize the hydraulic system with the EDP or the demand
____
pump (AMM 29-11-00/201).
S 794-019-N00
(6) Examine the filter bowl for leakage.
(a) If you find leakage, replace packing and/or filter bowl.
S 864-029-N00
(7) Remove electrical power if it is not necessary for other operations (AMM 24-22-00/201).
S 414-030-N00
CAUTION: MAKE SURE YOU LATCH THE FAIRING DOORS ON THE TRAILING EDGE
_______ CORRECTLY. DAMAGE CAN OCCUR IF THE DOORS OPEN DURING A FLIGHT.
(8)
Close the fairing doors on the trailing edge of the applicable strut (AMM 54-62-00/201).
E.
Put the Airplane Back to Its Usual Condition.
S 444-010-N00
(1) Do the activation procedure for the speed brake control system (AMM 27-62-00/201).
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
78-34-14
ALL ú ú N01 Page 407 ú Jun 10/94
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
THRUST REVERSER INDICATION SYSTEM - DESCRIPTION AND OPERATION
_____________________________________________________________
1. General
_______
A. The system for the thrust reverser indication provides the flight crew with visual indication of operation and position of the thrust reverser, and indication of a fault occurring in the control system for the thrust reverser (Ref 78-34-00/001).
B. Indication is provided for reverser unlocked and reverser deployed by a REV display on the upper display of the Engine Indication and Crew Alerting System (EICAS) in the flight compartment.
(1)
The REV display is colored amber when the center actuator locks are disengaged, the sync locks are unlocked and the system is in transit, and changes to green when the system reaches the fully deployed position.
C.
An ENG REV DISAGREE message on the upper EICAS display in the flight compartment is caused by a disagreement of isolation valve operation as it relates to the commanded reverser position. Other malfunctions that could cause an ENG REV DISAGREE indication are a failure of the air/ground relay, a relay for the airborne auto restow failed closed, a proximity sensor for the airborne stow failing, or a locking actuator which allows the sleeves to come unstowed.
D.
A linear variable differential transformer (LVDT) for the reverser position feedback provides reverser position to the EEC which commands the interlock actuator for the thrust lever to ensure proper sequencing of engine power with thrust reverser position.
2. Indicating System for the Thrust Reverser Position (Fig. 1)
__________________________________________________
A. Two proximity sensors on each thrust reverser sleeve signals the thrust reverser position to the PSEU.
(1)
A deploy proximity sensor (S1609,S1610) is mounted on the stop bracket for the center locking hydraulic actuator. The sensor target is mounted to the actuator feedback screw.
(2)
A proximity sensor (S1607,S1608) for the actuator lock is mounted on the center locking hydraulic actuator body. The sensor target is mounted on the actuator lockout lever.
B.
The proximity sensors output is processed by the PSEU (Proximity Switch Electronics Unit) which contains logic to close the appropriate internal switch which provides a ground for the appropriate EICAS message.
中国航空网 www.aero.cn
航空翻译 www.aviation.cn
本文链接地址：747-400 AMM 飞机维护手册 EXHAUST 2(95)
