(2)
27-51-00/201, Trailing Edge Flap System
(3)
51-21-04/701, Alodized Surfaces
C. Access
(1) Location Zone 193 Fairing - Wing-to-Body, Aft, Lower Half, Left 194 Fairing - Wing-to-Body, Aft, Lower Half, Right
D. Procedure
S 497-003
WARNING: YOU MUST CAREFULLY DO THE STEPS IN THE TASK BELOW TO INSTALL
_______ THE DOOR LOCKS ON THE LANDING GEAR DOORS. THE DOORS CAN CLOSE QUICKLY IF YOU DO NOT INSTALL THE DOOR LOCKS CORRECTLY. THIS CAN CAUSE INJURY TO PERSONS OR DAMAGE TO EQUIPMENT.
(1)
Install the door locks for the landing gear door (Ref 32-00-30/201).
S 867-014
(2)
Fully extend the inboard TE flaps to get access to the rub strip area on the wing-to-body fairing (Ref 27-51-00/201).
S 867-015
WARNING: YOU MUST CAREFULLY DO THE STEPS IN THE TASK BELOW TO DEACTIVATE
_______ THE TE FLAPS. THE TE FLAPS CAN MOVE QUICKLY IF YOU DO NOT DO THIS TASK CORRECTLY. THIS CAN CAUSE INJURY TO PERSONS OR DAMAGE TO EQUIPMENT.
(3) Disconnect the power for the inboard TE flaps (Ref 27-51-00/201).
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MAINTENANCE MANUAL
Flap-to-Body Rub Strip
Figure 701
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(4) S 027-005Remove the fasteners for the rub strips.
(5) S 037-013Remove the rub strips.
(6) S 377-006Apply Alodine 1000 on all surfaces of each rub strip (Ref 51-21-04/701).
(7) S 377-007Apply primer only on the side of the rub strips that touch the fuselage skin.
(8) S 427-008Install the rub strips.
(9) S 867-009Move the TE flaps through one full cycle to make sure you have a smooth operation of the seals.
S 867-011
(10) Retract the TE flaps.
S 867-012 WARNING: YOU MUST CAREFULLY DO THE STEPS IN THE TASK BELOW TO REMOVE THE
_______ DOOR LOCKS ON THE LANDING GEAR DOORS. THE DOORS CAN CLOSE QUICKLY IF YOU DO NOT REMOVE THE DOOR LOCKS CORRECTLY. THIS CAN CAUSE INJURY TO PERSONS OR DAMAGE TO EQUIPMENT.
(11) Remove the door locks for the landing gear doors (Ref 32-00-30/201).
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747-400 MAINTENANCE MANUAL
TAIL SECTION: STATION 2360 TO STATION 2792 - DESCRIPTION AND OPERATION
_______________________________________________________________________
General (Fig. 1)
_______
A. The fuselage tail section, section 48, consists of the fuselage aft of station 2360. The tail section is not pressurized and contains the aft pressure bulkhead, vertical fin, and horizontal stabilizer attach fittings, and the Auxiliary Power Unit (APU). This section is divided into three main assemblies: the upper lobe from station 2360 to 2598 above WL 269.87; the lower lobe immediately below the upper lobe; and the section aft of station 2598.
B. Maintenance panels installed to the aft, left, and right of the stabilizer jackscrew access door provide a platform on which to stand when performing maintenance in the area. The panels are finished with a walkway coating (Ref 51-24-09).
C. The stabilizer to body seal track is formed from aluminum sheet and is riveted to the forward end of the stabilizer cutout fairing. The track is finished with an abrasion-resistant material (Ref 51-24-04).
Bulkheads (Fig. 1)
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