78-34-11
ALL ú ú C01 Page 402 ú Mar 15/95
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
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CFM56 ENGINES
737-300/400/500/ /MAINTENANCE MANUAL ////////////////////////
TASK 78-34-11-404-003-C00
3. Install the Shuttle Valve_________________________
A. Consumable Materials
(1)
D00153 Fluid - Hydraulic, BMS 3-11
B.
References
(1)
AMM 29-09-00/201, Hydraulic Reservoir Pressurization System
(2)
AMM 29-15-00/201, Hydraulic Systems A, B and Standby
(3)
AMM 70-20-02/201, Tightening Practices and Torque Values
(4)
AMM 70-30-01/201, Seals (Preformed Packings and O-rings) and Gaskets
C.
Access
(1)
Location Zones
216 Left Main Landing Gear Wheel Well
217 Right Main Landing Gear Wheel Well
D.
Procedure
S 424-004-C00
(1) Install the Shuttle Valve (Fig. 401).
(a)
Install the unions and new O-rings in the left (right) shuttle valve. 1) Lightly lubricate O-rings and threaded fittings with
hydraulic fluid (AMM 70-30-01/201).
(b)
Install the restrictor and a new O-ring in the shuttle valve.
1) Lightly lubricate the O-rings and the threaded fittings with the hydraulic fluid (AMM 70-30-01/201).
(c)
Put the shuttle valve on the bulkhead and attach it with two bolts, two washers, and two nuts. 1) Tighten the nuts (AMM 70-20-02/201).
(d)
Remove the protective caps from the hydraulic lines and the left (right) shuttle valve.
(e)
Connect the hydraulic lines to the shuttle valve. 1) Tighten the nuts (AMM 70-20-02/201).
S 864-005-C00
(2) Put the Airplane Back to Its Usual Condition.
WARNING: KEEP PERSONS AND EQUIPMENT CLEAR OF THE FLIGHT CONTROL
_______ SURFACES, THE THRUST REVERSERS, AND THE LANDING GEAR. THESE COMPONENTS CAN MOVE SUDDENLY WHEN YOU SUPPPLY HYDRAULIC POWER. THIS CAN CAUSE INJURIES TO PERSONS AND DAMAGE TO EQUIPMENT.
(a)
Supply hydraulic power (AMM 29-15-00/201).
(b)
Look for hydraulic fluid around the left (right) shuttle valve.
(c)
Do the Normal Operation Test (AMM 78-31-00/501).
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78-34-11
ALL ú ú C01 Page 403 ú Mar 15/95
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
////////////////////////A / /
CFM56 ENGINES
737-300/400/500/ /MAINTENANCE MANUAL ////////////////////////
THRUST REVERSER INDICATING SYSTEM - DESCRIPTION AND OPERATION
_____________________________________________________________
1. General
_______
A. The thrust reverser indicating system provides a display of translating sleeve position (stowed or deployed) and reverser system condition (disagreement between selected position and system control component condition).
B. System components include indicator lights, proximity switches and associated wiring. Electrical power for indicating system control circuits is 28 volts dc supplied from dc bus 1 for engine No. 1, dc bus 2 for engine No. 2. Illumination power for the indicator lights is supplied from the master dim and test system.
C. System information for the TWO, SIX, and SIXTEEN LIGHT ENGINE ACCESSORY UNIT will be included for all operators to provide the greatest flexibilty when exchanging EAUs. The TWO, SIX, AND SIXTEEN LIGHT EAUs are interchangeable per Boeing Service Letter 737-SL-78-18-B.
(1) Some of the SIX LIGHT EAUS contain a Digital FLight Data Recorder (DFDR) circuit which transmits the sleeve position to the DFDR. Information for both configurations is provided.
2. Thrust Reverser Indicator Lights
________________________________
A. One amber 'REVERSER UNLOCKED' light for each engine is installed on the pilots' center instrument panel.
(1)
An illuminated light indicates that one or two translating sleeves on the applicable engine are not at the fully stowed position.
B.
One amber 'REVERSER' light (referred to as the "fault" light) for each engine is installed on the PMC module on the pilots' aft overhead panel and functions as a "disagreement" light to indicate faults within the reverser system.
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