AFT ENTRY DOOR – INSPECTION CHECK
EFFECTIVITY
Airplanes Without Aft Airstairs
1. Aft Entry Door Inspection
A. Examine Aft Entry Door
(1)
Examine external and internal skins for cracks and corrosion; hinge fairings for looseness and missing screws.
(2)
Examine frames, internal brackets, handle mechanism housing, and hinges for cracks, corrosion, and loose bolts.
(3)
Examine door operating mechanism for cracks, corrosion, excessive wear, and loose bolts.
(4)
Examine latch rollers, latches, and door stops for cracks, corrosion, and foreign particles lodged in latches or attached to stops.
(5)
Examine drain holes for obstruction.
(6)
Examine door seals for cracks, cuts and tears, and correct seating when door is in closed position.
(7)
Examine roller cam plates and guide arm roller for excessive wear, which may cause door to malfunction (Ref 52-13-31 R/I).
(8)
Check that snubber operates correctly to retard or snub rapid motion of door towards stowed and cocked position.
2. Aft Entry Door Hinge Inspection (Fig. 601)
A. Measure the clearance at the top and bottom of the doors. Refer to 52-13-00/501 for clearance limits.
B. Visually inspect clearance around hinge arm covers and hinge links. Make sure hinge arm covers and hinge links do not contact the outer skin of the fuselage or the outer skin of the door throughout the opening and closing cycle.
C. Visually inspect clearance between upper hinge link and guide plate. Make sure the upper hinge link does not contact the guide plate throughout the opening and closing cycle.
May 01/98 52-13-0 Page 601
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
Aft Entry Door Hinge Inspection 500
52-13-0 Figure 601 May 01/98
Page 602
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
AFT ENTRY DOOR HINGE ARMS - REMOVAL/INSTALLATION
EFFECTIVITY
Airplanes Without Aft Airstair
General
A. The aft entry door hinge arms are similar to the galley service door hinge arms. For removal/installation of the aft entry door hinge arms, refer to Galley Service Door Hinge Arms -Removal/Installation, section 52-41-11.
May 15/73 52-13-11 Page 401
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
AFT ENTRY DOOR LINING - REMOVAL/INSTALLATION
EFFECTIVITY
Airplanes Without Aft Airstair
1. General
A. The lining and insulation installed on the aft entry door is similar to that installed on the galley service doors. For removal/installation of aft entry door lining, refer to Galley Service Door Lining and Insulation - Removal/Installation, section 52-41-31.
May 15/73 52-13-21 Page 401
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
AFT ENTRY DOOR GUIDE ARM AND ROLLER - REMOVAL/INSTALLATION
EFFECTIVITY
Airplanes Without Aft Airstair
1. General
A. The aft entry door guide arm and roller is similar to the galley service door guide arm and roller. For removal/installation of the aft entry door guide arm and roller, refer to 52-41-21, Galley Service Door Guide Arm and Roller.
May 15/73 52-13-31 Page 401
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
AFT ENTRY DOOR STRUCTURE TORQUE TUBE - REMOVAL/INSTALLATION
EFFECTIVITY
Airplanes Without Aft Airstair
1. Equipment and Materials
A. Grease - MIL-G-21164 (Ref. 20-60-2)
2. Remove Aft Entry Door Structure Torque Tube (Fig. 401)
A. Remove door from airplane (Ref. 52-13-0, Removal/Installation).
B. Remove access panel on outside of body between the upper and lower door hinge cutouts to obtain access to structure torque tube.
C. Remove bolts securing sleeves to torque tube and upper and lower hinge link pin. Slide the sleeves clear of hinge link pins.
D. Raise and lower torque tube to remove sleeves.
E. Remove torque tube by withdrawing outboard through upper or lower hole in structure.
3. Install Aft Entry Door Structure Torque Tube (Fig. 401)
NOTE: Hinge link pins, sleeves, and torque tube spares are supplied as a matched assembly or as individual undrilled parts. Undrilled hinge link pins and torque tubes or a combination of undrilled hinge link pins/sleeves or torque tube/sleeves may be installed and drilled during installation.
A. Apply a thin coat of grease to mating surfaces of hinge link pins, sleeves and torque tube.
B. Install hinge link pins in upper and lower hinge link.
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