527 Emergency Exit Hatch Closing Force Adjustment
Feb 15/72 Figure 502 (Sheet 2) 52-21-0
Page 505
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
(b)
If forces are still too high, loosen 30 panel attachment fasteners around periphery of hatch panel and pull inboard. Retighten fasteners. Recheck forces.
(c)
If forces are still too high, add additional shims to filler (22 places) as required between hatch lining support and hatch structure.
(5) Install emergency exit hatch lining and check force required to close hatch is within limits.
2. Emergency Exit Hatch Test
A. Test hatch opening and closing operations from inside and outside airplane.
CAUTION: TO AVOID POSSIBLE DAMAGE TO HATCH WHEN CHECKING HATCH OPENING FROM OUTSIDE, AN ASSISTANT SHOULD BE INSIDE AIRPLANE TO RECEIVE HATCH.
(1)
Check hatch for freedom from binding or obstructions throughout opening cycle.
(2)
Close hatch and check that force required to close hatch is between 10 and 25 pounds with lining installed, also check hatch for freedom from binding or obstructions throughout closing cycle.
B. Check correct sealing of seal around hatch periphery.
NOTE: This check may be made from outside airplane by viewing seal through gap between hatch and fuselage skin.
527
52-21-0 Page 506 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Feb 15/72
EMERGENCY EXIT HATCH - INSPECTION/CHECK
1. Emergency Exit Hatch Inspection
A. Examine Emergency Exit Hatch
(1)
Examine external skin and framing around opening, for cracks, corrosion, loose and missing fasteners.
(2)
Examine frames, and internal brackets for cracks, corrosion, and loose bolts.
(3)
Examine window and frame for cracks and corrosion.
(4)
Examine hatch operating mechanism for cracks, corrosion, excessive wear, and loose bolts.
(5)
Examine latch rollers, latches, lower pivot fitting, and lower pivot hook for cracks, corrosion, and foreign particles lodged in latches or attached to stops.
(6)
Examine operating handle seal for cracks, cuts, tears and signs of deterioration.
(7)
Examine hatch peripheral seal for cracks, cuts and tears, signs of deterioration, and correct seating when hatch is in closed position.
NOTE: This check could be made from outside airplane by viewing seal through gap between hatch and fuselage skin.
500
May 15/67 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 52-21-0 Page 601
EMERGENCY EXIT HATCH LINING - REMOVAL/INSTALLATION
1. Remove Emergency Exit Hatch Lining
A. Remove emergency exit hatch (Ref 52-21-0 R/I).
B. With the handle in the down position, remove three screws that attach molded cover to clamp on handle and remove cover (Detail A, Fig. 401).
C. Remove two quick-release fasteners attaching lift handle access molding to hatch structure and remove molding (Detail D, Fig. 401).
D. Remove two fasteners below lift handle molding attaching handle support zee to hatch structure.
E. Remove 30 screws around hatch periphery attaching trim panel and seal to hatch structure.
F. Remove trim panel and seal.
G. Deleted.
2. Install Emergency Exit Hatch Lining
A. Deleted.
B. Position trim panel on hatch structure and engage two fasteners below lift handle molding attaching handle support zee to hatch structure.
C. With seal in place around periphery of hatch structure, engage 30 screws attaching trim panel and seal to hatch structure.
533
May 01/01 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 52-21-12 Page 401
Emergency Exit Hatch Lining Installation 533
52-21-12 Figure 401 (Sheet 1) Feb 15/72
Page 402
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
533 Emergency Exit Hatch Lining Installation
Feb 15/72 Figure 401 (Sheet 2) 52-21-12
Page 403
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
Emergency Exit Hatch Lining Installation 533
52-21-12 Figure 401 (Sheet 3) Sep 01/02
Page 404
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
D. Install lift handle access molding using two quick-release fasteners (Detail D, Fig. 401).
中国航空网 www.aero.cn
航空翻译 www.aviation.cn
本文链接地址：737 AMM 飞机维护手册 舱门 DOORS(67)
