(3)
The door latch fittings are on the forward and aft door frames of the fuselage cutout. The latch fittings are the receivers for the latch crank rollers on each door. The interface of these parts can give general wear data.
NOTE:____Make sure the correct latch fittings are installed. Fittings are different for some locations.
(4)
The door centering guide ball is on the aft side of the door and slides in the guide track mounted on the fuselage aft frame. The guide track has a hard plastic surface to minimize the wear on the guide ball.
NOTE: Wear on these items in an indication of other door component
____
wear.
(5) The replacement of a worn or damaged component to correct a problem in one door cycle can impact the door adjustment for the other door cycles.
2. Fault Isolation Tips
____________________
A. Follow the fault isolation procedure until you have a solution to the problem.
B. Repair or replace the components as necessary.
C. Make sure the door is correctly adjusted after the fault-isolation procedure is completed (AMM 52-11-00/501 Main Entry Door, AMM 52-13-00/501 Aft Entry Door, AMM 52-41-00/501 Galley Service Doors).
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3. Fault Isolation Procedures__________________________ ~........................................................................ |Figure 102 | General Door Fault Isolation | .......................................................................... |Figure 103 | The Latch Fittings Have Worn Areas | .......................................................................... |Figure 104 | The Guide Arm Cam Follower Pin Binds In The Cam Plate | | | Tracks | .......................................................................... |Figure 105 | The Fault Is In The Door Open/Close Cycle | .......................................................................... |Figure 106 | The Fault Is In The Door Cocking Cycle | .......................................................................... |Figure 107 | The Fault Is In The Door Latch/Unlatch Cycle | 2...........…............................................................1
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A
737-300/400/500MAINTENANCE MANUAL
OPENOPEN
INTERIOR
HANDLE
2. DOOR NOT LATCHED - UPPER AND LOWER
GATES FOLDED IN - MOTION TO COCK BEGINS 1. CLOSED AND LATCHED
OPEN
OPEN
4. DOOR NOT FULLY OPEN
3. DOOR FULLY COCKED - READY TO BE OPENED
5. DOOR FULLY OPEN
Passenger Door Cycles Figure 101
L15271
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A 737-300/400/500MAINTENANCE MANUAL
GENERAL DOOR PREREQUISITES
FAULT ISOLATION
NONE
YES
1 DO A VISUAL CHECK OF THE
21 DO THE APPLICABLE
DOOR AND ITS RELATION TO THE PROCEDURE IN THE AIRCRAFT
FUSELAGE CUTOUT.MAINTENANCE MANUAL.
CAN YOU DETERMINE FAULT?
NO
YES2 OPEN, CLOSE AND DO A TEST 22 DO THE APPLICABLE
(AMM 52-11-00/501, PROCEDURE IN THE AIRCRAFT
AMM 52-13-00/501, MAINTENANCE MANUAL.
AMM 52-41-00/501)
OF THE APPLICABLE DOOR. LOOK
FOR THE FOLLOWING:
. DAMAGE ON THE FUSELAGE
CUTOUT, DOOR SKIN OR SCUFF
PLATE.
. UNWANTED MATERIAL ANYWHERE IN THE OPENING OR ON THE DOOR FRAMES OR GATES.
. WORN AREAS ON THE INTERFACE BETWEEN DOOR COMPONENETS.
. DOOR COMPONENTS THAT HAVE BEEN BENT, TWISTED OR CRUSHED.
. BROKEN OR LOOSE DOOR COMPONENTS
. VIBRATION CHATTER OR NOISE THAT CAN BE FELT, HEARD OR SEEN.
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