NOTE:  Adjustment plate (5), splined eccentric (8) and cam follower (1) should be installed during adjustment of lockout assembly performed in par. 6.C.
E.  Position crank assembly (11) in housing to align with installation holes for spindle (12) and install spindle (12) through housing and crank.
F.  Position spacer (13) to align with installation holes for bolt (13) in housing, and install bolt (13) with washer through spindle flange, housing and spacer. Hook end of spring(s) over spacer. Install bolt, washer, and spacer with corrosion preventive compound.
NOTE:  Crank assembly shall rotate freely after bolt is tightened.
G.  Install baseplate assembly.
H.  Lubricate splined pivot link (24) and latch shaft assembly (21) with grease. Install splined pivot link (24) through bushing in baseplate flange and insert latch shaft assembly (21) through baseplate flanges so that smaller diameter splined end of shaft mates with pivot link splines. Secure shaft to pivot link with screw (22) and washer. Lubricate washer and screw with corrosion preventive compound.
I.  Lubricate splined surfaces of latch crank (17) and latch shaft assembly (21) with grease. Install latch crank on latch shaft with bolt (14), washer (16) and nut (15).
NOTE:  If crank (17) contacts structure during actuation, index spline on crank may be removed by machining per standard industry practice to permit re-indexing of crank to eliminate contact with structure during actuation.
J.  Install pivot link (25) through baseplate flange. Install so that clevis holes in link (24 and 25) are aligned. Position plate (27) between pivot links and with correct flange oriented in up position, connect plate to clevis of link (29) with bolt, nut, and washer.
K.  Rotate plate (27) to align with flanges on pivot links (24 and 25), and install bolt (23), nut, and washer. Tighten nut to 100-140 pound-inches torque.
L.  Assemble spacers (37), springs (36, 41) on latch arm (38) with bolt (35) and washers (39) on each end of bolt. Install nut (40), but do not tighten.
CAUTION: AVOID DAMAGE TO DAY FILM-LUBRICATED SURFACE OF LATCH.
500 
52-14-21 Page 406  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  Feb 15/79 

M.  Lubricate splines and bearing surfaces of latch shaft (34) with grease and insert latch shaft (34) through baseplate, latch arm (38) and latch crank (31). Tighten bolt, washer, and nut (33) on latch arm (38) and bolt, washer and nut (32) on latch crank (31). Tighten nut to 50-70 pound-inches torque. Provide only enough end play for free movement.
CAUTION:  LATCH CRANK (31) CAN BE INSTALLED ON SHAFT (34) TWO DIFFERENT WAYS. CORRECT INSTALLATION OF CRANK (31) POSITIONS BOLT (30), WASHER, NUT, AND BUSHING IN OUTBOARD END OF SLOT IN FORK LINK
(28) WHEN LINK (28) IS INSTALLED (STEP P).
N.  Connect springs (36, 41) to eyebolts on mounting bracket.
O.  Connect plate assembly (27) to link (28) with bolt, washer and nut (26). Tighten nuts to 100-140 pound-inches torque. Install bolts with corrosion preventive compound.
CAUTION:  AVOID DAMAGE TO TEFLON SURFACES OF BEARINGS IN PLATE AND LINK ASSEMBLIES.
P.  Lubricate splines of latch crank (31) with grease and assemble latch crank and link (28) with bolt, bushing, washer, and nut (30).
Q.  Lubricate splined surfaces on actuating arm (45) and both splined and bearing surfaces on adapter (44) with grease.
R.  Install actuating arm (45), laminated shims (46) and adapter (44) on mounting bracket with adapter bolt, retaining cap (43), washer and nut (42).
NOTE:  Shims should be installed so that the forward face of the upper portion of actuation arm is 0.05 +0.02/-0.00 inch from aft surface of forward flange on airstair hinge.
6.  Restore Airplane to Normal
A.  Install emergency extension torsion bar (Ref 52-14-31, Removal/Installation). Do not attempt to arm emergency extension system.
B.  Install aft airstair control console (Ref 52-14-11, Removal/Installation). Do not attempt to arm emergency extension system.
C.  Adjust torsion bar latch assembly and lockout assembly and test emergency extension mechanism (Ref Aft Airstair Emergency Extension Mechanism - Adjustment/Test).
D.  Install pneumatic ducting.
E.  Install cargo compartment sidewall lining and bulkhead panels (Ref Chapter 25, Cargo Compartment Sidewall Lining and Cargo Compartment Bulkhead Lining).
500 
Aug 15/79  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  52-14-21 Page 407 

AFT AIRSTAIR EMERGENCY EXTENSION MECHANISM - ADJUSTMENT/TEST
　
中國航空網 m.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：737 AMM 飛機維護手冊 艙門 DOORS(54)