(3)
Remove door heating blankets (Ref Chapter 21, Heating).
(4)
Depressurize hydraulic system B (Ref Chapter 29, Hydraulic Power).
(5)
Open main cargo door control circuit breaker on load control center P6.
(6)
The following conditions must be satisfied only while door is being closed for the purpose of checking latch and door centering cam clearances. Refer to steps (1) and (3) of par. C.
(a)
Airplane must be on its wheels (no jack support) and without tail stand.
(b)
Fuel tanks empty.
(c)
Airplane shall be substantially complete with all major components installed, except that interior items such as seats, galleys, lavatories, etc., may be missing. Electronic "Black Boxes" may also be missing.
(d)
All tools, equipment, and personnel must be removed from airplane. Tools and equipment may be placed directly over main gear if removal is not convenient.
(e)
All airplane parts of significant weight (30 pounds) that are on airplane but not installed should be placed in the approximate position they will occupy when installed.
511
Feb 20/94 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 52-32-11 Page 501
Main Cargo Door Centering Guide Roller Adjustment 511
52-32-11 Figure 501 Aug 15/77
Page 502
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
C. Adjust Main Cargo Door
(1)
Adjust Door Centering Guide Rollers (Fig. 501)
(a)
The distance between the forward edge of the front centering cam and the aft edge of the rear centering cam is 135.90 +0.03 inches. The distance between the guide rollers on the body door frame should be 0.00 to 0.03 inch greater than the distance between the centering cams (dimension A). Adjust distance by varying gage of shims under guide roller brackets.
(b)
Ensure distances from roller surface to frame surfaces at station 360 and station 500 are 2.04 inches nominal, 1.98 inches minimum.
(2)
Adjust Lock Mechanism (Fig. 502)
(a)
Open locking handle until control cable assembly bottoms out and locking pins retract.
(b)
Apply an aft preload of 20 +5 pounds to the No. 8 lockpin (STA 490).
(c)
Adjust pushrods to position lockpins on face of latch support fittings as shown on detail A. Adjust bellcrank pushrod for No. 2 lockpin first and then adjust No. 1 pin. Progressively work aft to pin No. 8.
NOTE: An adjustable stop on the lower beam at lockpin No. 7 is used to limit the overtravel (backlash) of the lockpin mechanism in the unlocked position. Provide clearance between stop and bellcrank until stop pin unlock position adjustments are completed, then reset to suit final position of pin No. 7.
(d)
Remove preload from No. 8 lockpin.
(e)
Close locking handle then apply a forward preload of 20 +5 pounds to No. 8 lockpin.
(f)
Check that lockpins are positioned in latch support fittings as shown in detail A. Repeat adjustments as necessary to obtain desired results.
(g)
Remove preload from No. 8 lockpin. Operate lock handle. Operation of mechanism should be free from binding and force required to move handle should not exceed 35 pounds throughout entire cycle.
517
May 1/76 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 52-32-11 Page 503
Main Cargo Door Locking Mechanism Adjustment 517
52-32-11 Figure 502 (Sheet 1) Jan 15/71
Page 504
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
520 Locking Mechanism Adjustment
May 01/76 Figure 502 (Sheet 2) 52-32-11
Page 505
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
Latch Mechanism Adjustment 511
52-32-11 Figure 503 (Sheet 1) Feb 20/94
Page 506
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
511 Latch Mechanism Adjustment Feb 20/94 Figure 503 (Sheet 2) 52-32-11 Page 506A/506B BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
506 Latch Mechanism Adjustment
Feb 1/74 Figure 503 (Sheet 2) 52-32-11
Page 507
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
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