737NG机组操作手册Flight Crew Operations Manual FCOM 2(125)

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The thrust reverser can be deployed when either radio altimeter senses less than 10 feet altitude, or when the air/ground safety sensor is in the ground mode. Movement of the reverse thrust levers is mechanically restricted until the forward thrust levers are in the idle position.
When reverse thrust is selected, an electro–mechanical lock releases, the isolation valve opens and the thrust reverser control valve moves to the deploy position, allowing hydraulic pressure to unlock and deploy the reverser system. An interlock mechanism restricts movement of the reverse thrust lever until the reverser sleeves have approached the deployed position. When either reverser sleeve moves from the stowed position, the amber REV indication, located on the upper display unit, illuminates. As the thrust reverser reaches the deployed position, the REV indication illuminates green and the reverse thrust lever can be raised to detent No. 2. This position provides adequate reverse thrust for normal operations. When necessary, the reverse thrust lever can be pulled beyond detent No. 2, providing maximum reverse thrust.
Downward motion of the reverse thrust lever past detent No. 1 (reverse idle thrust) initiates the command to stow the reverser. When the lever reaches the full down position, the control valve moves to the stow position allowing hydraulic pressure to stow and lock the reverser sleeves. After the thrust reverser is stowed, the isolation valve closes and the electro–mechanical lock engages.
Copyright . The Boeing Company. See title page for details.
7.20.12  June 1, 2003

Engines, APU -Engine System Description
737 Flight Crew Operations Manual
The REVERSER light, located on the aft overhead panel, illuminates when the thrust reverser is commanded to stow and extinguishes 10 seconds later when the isolation valve closes. Any time the REVERSER light illuminates for more than approximately 12 seconds, a malfunction has occurred and the MASTER CAUTION and ENG system annunciator lights illuminate.
Note: A pause in movement of the reverse thrust levers past detent No. 1 toward
the stow position may cause MASTER CAUTION and ENG system
annunciator lights to illuminate. A pause of approximately 16 seconds
engages the electro-mechanical lock and prevents the thrust reverser
sleeves from further movement. Cycling the thrust reversers may clear the
fault and restore normal operation.
When the reverser sleeves are in the stow position, an electro–mechanical lock and a hydraulically operated locking actuator inhibit motion to each reverser sleeve until reverser extension is selected. Additionally, an auto–restow circuit compares the actual reverser sleeve position and the commanded reverser position. In the event of incomplete stowage or uncommanded movement of the reverser sleeves toward the deployed position, the auto–restow circuit opens the isolation valve and commands the control valve to the stow position directing hydraulic pressure to stow the reverser sleeves. Once the auto–restow circuit is activated, the isolation valve remains open and the control valve is held in the stowed position until the thrust reverser is commanded to deploy or until corrective maintenance action is taken.
WARNING: Actuation of the thrust reversers on the ground without suitable precautions is dangerous to ground personnel.
Copyright . The Boeing Company. See title page for details.
June 1, 2003  7.20.13
Engines, APU -Engine System Description
737 Flight Crew Operations Manual
Thrust Reverser Schematic
DETENT NO. 2
MAXIMUM REVERSE THRUST DETENT NO. 1
INTERLOCK
STOWED
FORWARD THRUST LEVER
REVERSE THRUST (STOWED) REVERSE THRUST (DEPLOYED)
SYSTEM STANDBY SYSTEM
SYSTEM STANDBY SYSTEM A SYSTEM B
A SYSTEM B
ENGINE 1  ENGINE 2  ENGINE 1  ENGINE 2 
SYSTEM A  SYSTEM B  SYSTEM A  SYSTEM B 
HYDRAULIC  HYDRAULIC  HYDRAULIC  HYDRAULIC 
PRESSURE  CONTROL VALVE PRESSURE  ACTUATOR  PRESSURE  CONTROL VALVE PRESSURE  ACTUATOR 
(STOW)  LOCKED STOWED AND  (DEPLOY)  DEPLOY 

ELECTRO-ISOLATION
ELECTRO-VALVE
ISOLATION MECHANICAL VALVE
MECHANICAL (CLOSED)
LOCK (OPEN)
LOCK (LOCKED)
(UNLOCKED)
BLOCKER DOOR
FAN FLOW FAN FLOW
CASCADE TRANSLATING
TRANSLATING VANES SLEEVE
CASCADE SLEEVE VANES
Copyright . The Boeing Company. See title page for details.
7.20.14  June 1, 2003

737 Flight Crew Operations Manual

Introduction
The auxiliary power unit (APU) is a self–contained gas turbine engine installed within a fireproof compartment located in the tail of the airplane.
The APU supplies bleed air for engine starting or air conditioning. An AC electrical generator on the APU provides an auxiliary AC power source.
　
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