S 034-017
(4) Remove the bolt, the washer, the nut, the bushing, and the spacer
from the bottom of the arm assembly (Refer to Fig. 401, Item C).
S 434-018
(5) Replace the bushing on the bottom of the arm assembly with the
rigging set bushing.
S 824-019
(6) Carefully adjust the transducer rod end so a bolt or a rod with
0.312/0.311 inch diameter can be put freely through the rigging
bushing and arm assembly without loading the force transducer.
NOTE:____ Do not apply any external loads to the transducer while
it is being adjusted.
S 214-020
(7)
Lock the adjustment and make sure the bolt or rod can be put freely through. Make sure there is no load on the transducer assembly.
S 434-021
(8)
Put a lockwire on the locknut and the fine adjustment screw on the transducer.
S 034-022
(9)
Remove the rigging bushing.
S 434-023
(10)
Install the first bushing, spacer, bolt, washer, and nut on the arm assembly.
S 434-024
(11)
Connect the transducer's electrical connectors to the airplane wiring.
S 434-025
(12)
Install the wire bundle clamp.
S 034-026
(13)
Remove rig pin E/ST-6 (Ref 20-10-24).
S 864-027
(14)
Remove the DO-NOT-CLOSE tags and close these circuit breakers on the P11 panel:
(a)
11E17, FLT CONT COMPUTER POWER LEFT
(b)
11E18, FLT CONT COMPUTER SERVO LEFT
(c)
11E20, FLIGHT CONT CMPTR PWR CENTER
(d)
11E21, FLT CONT CMPTR SERVO CENTER
(e)
11E35, FLT CONT CMPTR PWR RIGHT
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. AIRPLANES WITH CONTROL ú
22-12-03
WHEEL STEERING ú ú 03 Page 406 ú Dec 20/96
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
757 MAINTENANCE MANUAL
(f)
11E36, FLT CONT CMPTR SERVO RIGHT
(g)
11H17, FLT CONT SHUTOFF TAIL LEFT
(h)
11H18, FLT CONT SHUTOFF TAIL CENTER
(i)
11H28, FLT CONT SHUTOFF TAIL RIGHT
S 864-028
(15)
Remove the DO-NOT-OPERATE tags and set the L, C, and R FLT CONTROL SHUTOFF switches to the ON position.
S 034-029
(16)
Remove the DO-NOT-OPERATE tags from the control columns.
E. Test the Elevator Control Force Transducer.
S 864-030
(1) Make sure these circuit breakers on the P11 panel are closed:
(a)
11C30, LANDING GEAR POS SYS 1
(b)
11E16, MODE CONT PNL LEFT
(c)
11E34, MODE CONT PNL RIGHT
(d)
11S4, MAINT CONT DSPL
(e)
11S15, AIR/GND SYS 1
(f)
11S19, AIR/GND SYS 2
(g)
11S23, POS SYS 2
S 864-031
(2)
Pressurize the L, C, and R Hydraulic Systems (Ref 29-11-00).
S 744-032
(3)
Start MCDP Ground Test 66-XDCR OUTPUTS (Ref 22-00-02).
S 744-039
(4)
Push the YES/ADV switch until the MCDP top line message shows 66 (L or R) COL-LBS/LCR.
(5)
Make sure the MCDP bottom line values are 0 |2 lbs.
S 214-033
NOTE: If the bottom line values are out of tolerance, do MCDP Test
____ 66 again with the elevator feel pitot system pressurized to 350 knots.
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. AIRPLANES WITH CONTROL ú
22-12-03
WHEEL STEERING ú ú 11 Page 407 ú Jan 20/98
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
757 MAINTENANCE MANUAL
S 744-034
(6)
For the left elevator control force transducer, do MCDP Ground Test 14-L COL XDCR (Ref 22-00-02).
中国航空网 www.aero.cn
航空翻译 www.aviation.cn
本文链接地址：757 AMM 飞机维护手册 自动飞行 AUTOFLIGHT 1(150)
