Horizontal Stabilizer Body Seal Door Mechanism Wear Limits
Figure 602 (Sheet 2)
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
27-41-14
ALL ú ú 01 Page 606 ú Feb 18/00
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400 MAINTENANCE MANUAL
STABILIZER TRIM RETURN FILTER ELEMENT - REMOVAL/INSTALLATION
____________________________________________________________
1. General_______
A. There are two tasks in this procedure. There is one task for the removal and one task for the installation of the stabilizer trim return filter element (which is referred to as the "filter element"). The procedure has these parts:
(1)
The removal of the filter element
(2)
The installation of the replacement filter element
(3)
An operational test of the filter element.
B.
The removal and installation procedure is the same for the left or the right filter element.
C.
The filter elements are on the support structures on the two sides of the stabilizer jackscrew.
TASK 27-41-15-004-001
2. Stabilizer Trim Return Filter Element Removal_____________________________________________
A. Standard Tools and Equipment
(1)
Bucket - 1 gallon capacity
B.
References
(1)
AMM 06-09-05/201, Body Section 48 Access Doors and Panels
(2)
AMM 24-22-00/201, Manual Control
(3)
AIPC 27-41-15, Fig. 2
C.
Access
(1)
Location Zone
311 Area Aft of Pressure Bulkhead, LH
312 Area Aft of Pressure Bulkhead, RH
(2)
Access Panel 312A Horizontal Stabilizer Jackscrew Access Door
D.
Procedure
(1)
Do this task: "Supply Electrical Power" (AMM 24-22-00/201).
S 864-004
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
27-41-15
ALL ú ú 01 Page 401 ú Jun 18/01
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400
MAINTENANCE MANUAL
SEE B
FWD
SEE A
SEE C
FILTERSEE C FILTER
FWD FWD
LEFT STABILIZER TRIM MODULE RIGHT STABILIZER TRIM MODULE
AB
DIFFERENTIAL PRESSURE INDICATOR DIFFERENTIAL PRESSURE INDICATOR
(SHOW IN SATIFACTORY CONDITION) (SHOW IN UNSATIFACTORY CONDITION)
C C
Stabilizer Trim Filter Module Element Installation
Figure 401
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
27-41-15
ALL ú ú 01 Page 402 ú Oct 18/00
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400 MAINTENANCE MANUAL
S 864-005
(2)
Set the STAB TRIM 2 and 3 switches on the control stand to CUTOUT.
S 864-006
(3)
Open these circuit breakers and attach DO-NOT-CLOSE tags:
(a)
P7, Overhead Circuit Breaker Panel
1) 7E7, L STAB TRIM S/O VALVE
2) 7E20, R STAB TRIM S/O VALVE
S 864-007
(4)
Do this task: "Remove Electrical Power" (AMM 24-22-00/201).
S 014-008
(5)
Open the access door 312A (AMM 06-09-05/201).
S 214-025
(6)
Examine the differential pressure indicators on the filter module. (Fig. 401).
S 024-026
(7)
If a differential pressure indicator shows an unsatisfactory condition, do the following:
(a)
Disconnect the hydraulic line H1.
(b)
Use a bucket to catch the fluid leakage.
(c)
Remove the filter element (Fig. 401):
(d)
Remove the filter element housing.
(e)
Remove the filter element and discard it.
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 飞行操纵 FLIGHT CONTROLS 4(18)