NOTE: Locate balance cable under the spacer on the pulley brackets. The spacer is used only as a bracket separator.
F. Install and bolt four cable pulleys (5) in place.
G. Hook springs (3) to door structure and splice plate (2).
H. Bolt cable clevis to splice plate.
I. Check condition of cable assembly. If cable assembly becomes contaminated with foreign matter (debris due to machining operations)
(1)
Gain access to affected portion and wipe with a clean, dry cloth.
(2)
After cleaning cable, immediately apply a minimum quantity of grease sufficient to produce a continuous thin visible ribbon of grease in cable grooves. Application may be done by hand or by a grease applicator.
CAUTION: DO NOT CLEAN CABLE BY SOLVENT DEGREASING OR WIPING WITH SOLVENT WETTED CLOTH.
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52-31-11 Page 404 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. May 15/70
CAUTION: GREASE APPLIED MUST NOT BE THINNED BY HEATING OR DILUTING WITH SOLVENT.
J. With cable properly seated in grooves of all pulleys, pull 8 to 10 inches of cable from door and place clamp on cable to prevent retraction.
K. Bolt cable clevis (7) to cable clip (9) on overhead floor beam (1); remove clamp placed on cable.
L. Install insulation pad and secure with lining retainer studs.
M. Install cable drum access panel and screws.
N. Check balance mechanism for proper operation. When door is released, it should move smoothly upward to or near its up-latched position.
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Aug 15/77 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 52-31-11 Page 405
CARGO COMPARTMENT DOOR SNUBBER - INSPECTION/CHECK
1. Operational Check - Cargo Compartment Door Snubber
A. Do the operational check of the snubbers as follows:
(1)
Open the cargo compartment door.
WARNING: MAKE SURE YOU INSTALL THE DOOR SUPPORT BRACE TO KEEP THE DOOR IN THE OPEN POSITION. IF THE DOOR BALANCE MECHANISM AND THE SNUBBER ARE DISCONNECTED AND THE DOOR IS LATCHED OPEN, THE DOOR CAN FALL TO THE CLOSED POSITION AND RESULT IN INJURY OR DAMAGE.
(2)
Use the door support brace to keep the door in the open position.
(3)
Disconnect the balance mechanism cable (Ref 52-31-00/401).
(4)
Remove the door support brace and see that the snubber does not let the door close quickly.
(5)
Open the cargo compartment door.
WARNING: MAKE SURE YOU INSTALL THE DOOR SUPPORT BRACE TO KEEP THE DOOR IN THE OPEN POSITION. IF THE DOOR BALANCE MECHANISM AND THE SNUBBER ARE DISCONNECTED AND THE DOOR IS LATCHED OPEN, THE DOOR CAN FALL TO THE CLOSED POSITION AND RESULT IN INJURY OR DAMAGE.
(6)
Use the door support brace to keep the door in the open position.
(7)
Connect the balance mechanism cable (Ref 52-31-00/401).
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Jun 20/92 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 52-31-13 Page 601
MAIN CARGO DOOR SYSTEM - DESCRIPTION AND OPERATION
EFFECTIVITY
Cargo Airplanes Only
1. General
A. The main cargo door, installed on the upper left side of the fuselage, provides an access for loading cargo into the main compartment of the airplane. The cargo door hinges outward and normally opens to two positions, canopy and full open. However, the door may be hydraulically locked open at any position up to full open. The lower edge of the door opens to a minimum of 124 inches above the floor of the fuselage when in the canopy position. The highest point of the door when in the canopy position does not exceed 157 inches above the floor of the fuselage. The full open position provides complete vertical clearance up to the door opening. The forward edge of the cargo door is at station 360. The aft edge of the cargo door is at station 500. The main cargo door is normally operated open and closed with a hydraulic latch actuator and a hydraulic lift actuator powered from hydraulic system B. However, the cargo door may also be opened using a manual pump to supply hydraulic pressure for the actuators. Controls for the main cargo door consist of a manual unlocking and locking handle mounted flush on the outside of the door, which is accessible from the forward entryway and a control panel installed on the bulkhead adjacent to the forward left entryway.
B. The main cargo door is hinged at the top with 12 removable hinge pins and 10 hinge segments. (See figure 1.) Centering cams are installed on the lower forward and aft edges of the door. The centering cams mate with rollers installed on the lower forward and aft door body frames. A latching mechanism and latch locking mechanism are installed along the lower portion of the door. The latch mechanism consists of eight mechanical latch hooks which pull the door completely closed and latch the door to latch pins on the fuselage doorsill. A hydraulically operated latch actuator, installed in the lower center of the door, moves the latching mechanism. The latching mechanism also opens the door enough to break a bulb-type pressure seal around the perimeter of the door. The latch lock mechanism consists of eight lockpins, with interconnecting mechanism and a manually operated control handle. The lockpins prevent the latch mechanism from operating until the latch lock mechanism is unlocked. The latch lock mechanism is unlocked with a flush-mounted external locking handle on the forward outboard side of the door. Access
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