H24267
Main Gear Wheel Well Blade - Type Seal Installation 500
32-12-12 Figure 401 Feb 15/70
Page 402
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
MAIN GEAR WHEEL WELL BLADE-TYPE SEAL - INSPECTION/CHECK
1. Main Gear Wheel Well Blade-Type Seal Segment Inspection
A. Examine the blade seal segments for tears in the half - thickness (overlap) areas (Fig. 601).
(1) If you find a tear in the overlap area of a blade seal segment, do the steps that follow:
NOTE: It is not necessary to apply sealant to the cut edge of the blade seal.
(a)
Cut a sufficient area from the overlap to fully remove the tear. Use scissors or a utility blade.
(b)
The area of damage removal must be over or under an undamaged area of the adjacent blade seal segment.
1) If the area of damage removal is over or under an undamaged area of the adjacent blade seal segment, then no further action is necessary for the overlap area.
2) If the area of damage removal is over or under a damaged area of the adjacent blade seal segment, then replace one or both of the adjacent blade seal segments.
NOTE: The replacement of only one blade seal segment will satisfy the requirements of step (b) 1) above.
B. Examine the blade seal segments for tears in the full - thickness area.
(1) If you find a tear in a blade seal segment, replace the segment per AMM 32-12-12/401.
C. Examine the seal segments for damage possibly caused by a spinning tire entering the wheel well.
(1) If you find damage to the blade seals that appear to have been caused by spinning tires, do the steps that do a check of the adjustment of the landing gear lever "UP" switch per AMM 32-42-51/501.
501
Sep 01/02 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 32-12-12 Page 601
M54362H24267
Main Landing Gear Wheel Well Blade Seal -Inspection/Check 500
32-12-12 Figure 601 (Sheet 1) Sep 01/02
Page 602
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
500 Main Landing Gear Wheel Well Blade Seal -Inspection/Check
Sep 01/02 Figure 601 (Sheet 2) 32-12-12
Page 603
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
MAIN GEAR SHOCK STRUT DOORS - DESCRIPTION AND OPERATION
1. General
A. The main gear shock strut doors close over the opening in the wing for shock strut and drag strut when the gear is retracted (Fig. 1). The installation consists of three doors. A center door is attached to the shock strut and the drag strut. An outer door is hinged to the wing, and an inner door is hinged to the inboard edge of the center door. Linkage from the trunnion link and the universal side strut attachment operate during extension and retraction to open and close the doors. Shock strut doors remain open when the gear is extended. A support rod attached to the lowest shock strut clamp, prevents center and inner doors from moving out of adjustment under vibration or heavy air loads.
2. Center Door
A. The center door is a composite bonded assembly or is built up from a frame, inner and outer skins, and a honeycomb core. Reinforced points support attachment fittings, and the lower edge carries a hinge half for the inner door. The door is secured by clamps to the shock strut and the drag strut. Adjustable fittings between the door and clamps are provided to fair the door with the surface of wing. A bulb type seal is mounted along the outboard edge of door. A rub strip on the aft edge and an angle riveted on the forward edge contact seals along the respective edges of the opening in wing when the door is closed.
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