1. Equipment and Materials
A. Laminated shims, BACS4OK13A32
2. Remove Section 48 Access and Blowout Door
A. Open door fully.
B. Remove bolt attaching lower end of jury strut to door. (See figure 401.)
C. Remove bolt, washer and nut attaching ground cable to door structure.
D. Support door and remove hinge bolts and shims attaching door hinges to door.
NOTE: Collect and tag shims.
E. Lower door from airplane.
3. Install Section 48 Access and Blowout Door
NOTE: If a new door is to be installed, trim door edges to fit door frame within 0.04 to 0.10 inch gap. Gap must be equal within 0.03 inch on both sides of door.
A. Raise door and provide adequate support.
B. Attach hinges to door with hinge bolts and shims. (See figure 401.) Add or delaminate shims as required to obtain contact between door and door frame around complete periphery.
C. Check that door opens freely.
D. Attach lower end of jury strut to door with bolt. Tighten bolt within torque range of 25 to 30 inch-pounds.
E. Attach ground cable to door with bolt, washer and nut.
F. Adjust and test door in accordance with adjustment/test procedure.
500
Nov 15/68 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 52-49-11 Page 401
Section 48 Access and Blowout Door Installation 500
52-49-11Page 402 Figure 401 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Nov 15/68
1. General
A. The section 48 access and blowout door functions as access to the stabilizer jackscrew compartment and as a blowout door in case of pressure bulkhead leakage or rupture of the air conditioning air duct. (Refer to, Servicing, Door 3701, Chapter 12.)
2. Section 48 Access and Blowout Door Adjustment
A. Adjust Section 48 Access and Blowout Door
(1)
Adjust gap between spring aft end plate nut and spring aft end plate to allow door to meet flushness requirements of +0.02/-0.02 inch. (See figure 501.) Ensure that gap does not exceed 0.06 inch minimum dimension.
NOTE: Two types of latches are used on the door; a Boeing designed latch on earlier airplanes and a Hartwell latch on later airplanes. If a Boeing designed latch is installed on the door, drill a new 0.078 (+0.003/-0.000) inch cotter pin hole in spring assembly rod 0.10 inch aft of original hole if necessary to allow for further slackening of spring.
(2)
With door closed and latched, check 0.41 (+0.01/-0.00) inch dimension.
NOTE: This check may be made by using modeling clay or any other approved method. (3) If 0.41 (+0.01/-0.00) inch dimension is not met, remove door stops and serrated plates by removing attachment bolts.
(4)
Shim door stops to meet 0.41 (+0.01/-0.00) inch dimension and install door stops and serrated plates temporarily to meet flushness requirement of +0.02/-0.02 inch.
(5)
Check that rollers contact door stops at each stop location.
(a)
Insert a 0.020 feeler gage between roller and door stop at stringer 23.
(b)
Using feeler gages, check that gap between roller and door stop at stringer 21 is within 0.002 to 0.020 inch. Adjust the serrated plate behind stop to obtain this dimension.
(6)
Test door per paragraph 3. If load range of 52 to 75 pounds cannot be met, repeat steps (1) thru (5) as necessary.
(7)
When load range of 52 to 75 pounds is met, install door stops and serrated plates permanently.
500
Feb 15/80 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 52-49-11 Page 501
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