H29424
500  Tailpipe Extension Installation 
Nov 01/75  Figure 401  78-32-211 
Page 403 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

F.  Reactivate thrust reverser hydraulic system by removing ground locks from both thrust reverser isolation valves. Check operation of thrust reverser per 78-32-01.
WARNING:  PERSONNEL MUST STAY CLEAR OF THRUST REVERSER WHEN IT IS ACTUATED TO PREVENT BEING CAUGHT BY ROTATING DEFLECTOR DOORS.
G.  Actuate deflector doors through five cycles to bleed thrust reverser hydraulic system. Check for leaks.
H.  Deactivate thrust reverser hydraulic system by installing ground locks on both thrust reverser isolation valves.
WARNING:  SERIOUS INJURY CAN RESULT TO PERSONNEL IF GROUND LOCKS ARE NOT PROPERLY INSTALLED. ATTEMPT TO DEPLOY THRUST REVERSERS AFTER INSTALLING GROUND LOCKS. REVERSERS SHOULD NOT DEPLOY.
6.  Restore Airplane to Normal
A.  Install engine side cowl panels per 71-11-11 and tailpipe fairings per 78-32-162.
B.  Reactivate thrust reverser hydraulic system by removing ground locks from both thrust reverser isolation valves.
500 
78-32-211 Page 404  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  May 15/71 

ACOUSTIC TAILPIPE EXTENSION - INSPECTION/CHECK
1. Inspect Acoustic Tailpipe Extension - Aft Flange Weld
A.  Inspect the engine tailpipe extension for cracks in the aft flange welds (Fig. 601). If cracks are found the following applies.
(1)  
Stop drill all cracks with a 0.125 inch drill before further flight.

(2)  
If the total length of one or more cracks in either the inner or outer welds is less than 8.0 inches in length the unit can remain in service with 240-flight hour inspection intervals.

(3)  
If the total length of one or more cracks in either the inner or outer welds is less than 20 inches in length the unit can remain in service with 120-flight hour inspection intervals.

(4)  
If the total length of one or more cracks exceeds 20.0 inches in either the inner or outer welds the tailpipe should be removed from service.

2.  Inspect Acoustic Tailpipe Extension - Forward Flange Weld
A.  Inspect the engine tailpipe extension for cracks in the forward flange welds (Fig. 601). If cracks are found the following applies.
(1)  
Stop drill all cracks with a 0.125 inch drill before further flight.

(2)  
If the total length of one or more cracks in either the inner or outer welds is less than 8.0 inches in length the unit can remain in service with 250-flight hour inspection intervals.

(3)  
If the total length of one or more cracks in either the inner or outer welds is less than 20 inches in length the unit can remain in service with 120-flight hour inspection intervals.

(4)  
If the total length of one or more cracks exceeds 20.0 inches in either the inner outer welds the tailpipe should be removed from service.

500 
Feb 20/91  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  78-32-211 Page 601 

H29429
Engine Acoustic Tailpipe Assembly - Inspection  500 
78-32-211  Figure 601  Jun 20/87 
Page 602 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

THRUST REVERSER CONTROL SYSTEM -DESCRIPTION AND OPERATION
1. General
A.  There are two separate, identical, thrust reverser control systems for engine No. 1 and engine No. 2. The thrust reverser control system is operated by a reverse thrust lever located on the throttle lever (forward thrust lever) for each engine. The control system directs System A hydraulic pressure to position the thrust reverser in the appropriate forward or reverse thrust position as selected with the reverse thrust lever.
B.  The major components of the thrust reverser control system are a thrust reverser control cam, rocker arm (cam follower), control valve and follow-up controls, a thrust reverser push-pull cable, and thrust reverser isolation valve. The thrust reverser isolation valves are located in the air conditioning bay. A main hydraulic pressure source, and an alternate hydraulic pressure source provide hydraulic pressure to the control valve, and from the control valve to the thrust reverser.
(1)  
Main Hydraulic Pressure Source

(a)  The thrust reverser main hydraulic power source is system A hydraulic pressure from the main landing gear down line. Hydraulic power is available from this line whenever the landing gear selector lever is in the DOWN position.
　
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