(b)
Install the splined end of flex shaft (1 or 7) into the splined hole of the hydraulic actuator.
(c)
Engage one or two threads of the tube nut (9).
(d)
Put the flex shaft tube in the support blocks for the hydraulic tubes. 1) Tighten the fasteners to attach the flex shaft tubes.
(e)
Loosen and move the tube nuts (9) back to make sure the splined end of the flex shaft (1 or 7) are engaged in the hydraulic actuator.
(f)
Install the tube nut (9).
1) Tighten the tube nut (9) to 30-35 pound-feet (48-55 newton-meters).
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
78-31-17
ALL ú ú N03 Page 418 ú Oct 18/00
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
S 414-140-N00
(17)
Install the sync lock on the lower non-locking hydraulic actuator.
S 864-121-N00
(18)
Extend and retract the thrust reverser three times with hydraulic power (AMM 78-31-00/201).
S 844-043-N00
(19)
Remove the hydraulic pressure (AMM 29-11-00/201).
(a) If the airplane hydraulic power was used, do the steps that follow: 1) For the applicable engine, open this circuit breaker and
attach the DO-NOT-CLOSE tags: a) P6 Main Power Distribution Panel
1.
6F13 T/R CONT ENG 1
_
2.
6E13 T/R CONT ENG 2
_
3.
6D13 T/R CONT ENG 3
_
4.
6C13 T/R CONT ENG 4
_ 2) Push the deactivation slide into the isolation valve housing. 3) Install the streamered pin to hold the deactivation slide
in the ground deactivation position. 4) Install the hitch pin in the streamered pin. 5) Connect the electrical connector (D4180 and D4182) for the
engine strut.
(b) If the hydraulic service cart was used, do the steps that follow: 1) Operate the hydraulic service cart to decrease the pressure
to zero. 2) Disconnect the hydraulic service cart from the retract line flex hose. 3) Install the retract line flex hose to the strut hydraulic connection. 4) Remove electrical power, if it is not necessary (AMM 24-22-00/201).
S 224-122-N00
(20)
Make sure the rod end clearance for the center locking actuator (dimension "A" in Fig. 401) is not more than 0.100 inch with the hydraulic power removed.
S 864-045-N00
(21)
Manually turn the actuator system through one full cycle to check the feedback rod posistional reference (AMM 78-31-00/201).
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
78-31-17
ALL ú ú N02 Page 419 ú Feb 18/01
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
////////////////////////A / PW4000 SERIES /747-400 / ENGINES/MAINTENANCE MANUAL ////////////////////////
S 824-044-N00
(22) If you do not have the feedback rod positional reference for the rod end to the hydraulic actuator, do the procedure in AMM 78-31-17/501.
NOTE: You do not have the feedback positional reference if the rod
____ end has been turned in relation to the gimbal ring. The feedback positional reference is correct when the dimensions shown in Fig. 402 are correct for both the extend and retract positions.
S 434-046-N00
(23)
Install the actuator lock proximity sensor (10) and actuator deploy
proximity sensor (18) on the center locking hydraulic actuator
(Fig. 402) (AMM 78-36-01/401).
S 824-117-N00
(24)
Do the adjustment procedure for the Thrust Reverser Position
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