Forward Entry Door Assist Spring Installation 500
52-11-41 Figure 401 (Sheet 1) Aug 15/68
Page 402
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552 Forward Entry Door Assist Spring Installation
Oct 20/83 Figure 401 (Sheet 2) 52-11-41
Page 403
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C. Remove two spring attach bolts (15, detail A) from stop fittings (8) and slide upper and lower torsion springs (7) off ends of torque tube assembly.
D. Remove torque tube assembly, center spring, and lower stop fitting as a unit from airplane.
(1)
Remove bolts (9, 18 and 19, section A-A) and screw (14) attaching lower stop fitting to stop support fitting (6).
(2)
Lower torque tube assembly until clear of upper stop fitting.
E. Remove center torsion spring from torque tube assembly.
7. Install Forward Entry Door Assist Spring (Fig. 401)
A. Assemble torque tube assembly, center spring, and lower stop fitting as a unit.
NOTE: During assembly, hand lubricate center assist torsion spring (16) and adjacent surfaces of upper torque tube (17) with grease.
B. Coat mating splines of spigots and torque tube with corrosion preventive compound. If spigots have been removed (Ref 52-11-01, R/I) coat mating surfaces of spigots, hinge arms, links, and support fitting bearings with grease.
C. Install torque tube assembly, center spring, and lower stop fitting as a unit on airplane.
(1)
Fill cavities of upper and lower spigot support housings with grease.
(2)
Raise torque tube assembly through upper stop fitting.
(3)
Attach lower stop fitting to stop support fitting with bolts (9, 18 and 19, section A-A) and screw (14).
D. Position upper and lower torsion springs (7, detail A) on ends of torque tube assembly and attach to stop fittings (8) with spring attach bolts (15).
E. Extend torque tube assembly and engage ends with upper spigot (5) and lower spigot (13).
NOTE: Ensure that ends of torque tube assembly are aligned with reference marks on upper and lower spigots.
F. Install upper, center, and lower spring mounting bolts (10) on torque tube assembly.
G. Install reveal (2) between upper and lower hinge arms of door.
H. Install interior lining (3) between upper and lower hinge arms of door (Ref Chapter 25, Forward Entry Door Sidewall Lining).
8. Restore Airplane to Normal
A. Remove wood block support from door.
B. Install cover (2, Fig. 401) between upper hinge arm (l) and lower hinge arm (4).
C. Install interior lining (3) between upper and lower hinge arms (Ref Chapter 25, Doorway Sidewall Linings).
D. Install evacuation slide (5) on door (Ref 52-11-31).
593
52-11-41 Page 404 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Feb 20/84
AFT ENTRY DOOR - DESCRIPTION AND OPERATION
EFFECTIVITY
Airplanes without Aft Airstairs
1. General
A. The aft entry door is located near the aft end of the fuselage on the left side of the airplane. The door is included in the door warning system and is provided with a switch, attached to the door frame, in circuit with the warning light for the door. Refer to 52-71-0, Door Warning System. The aft entry door is similar to the galley service door. For information applicable to the aft entry door, refer to 52- 41-0, Galley Service Door.
Aug 15/71 52-13-0 Page 1
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
AFT ENTRY DOOR - REMOVAL/INSTALLATION
EFFECTIVITY
Standard Passenger Airplanes
1. General
A. The aft entry door is similar to the galley service door. For removal/installation of the aft entry door, refer to 52-41-0, Galley Service Door.
Feb 15/69 52-13-0 Page 401
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AFT ENTRY DOOR – ADJUSTMENT/TEST
EFFECTIVITY
Airplanes without Aft Airstairs
1. General
A. The aft entry door adjustment/test procedures are similar to those covered in 52-41-0, Galley Service Door, except Fig. 501 for aft entry door flushness requirements.
532 Aft Entry Door Flushness Requirements
Feb 20/91 Figure 501 52-13-0
Page 501
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