(2)
In lower nose compartment, adjust turnbuckles to tighten flap control cables WFA and WFB to load specified for ambient temperature.
(3)
Position flap control lever all the way forward and then release lever.
(4)
Check that lever springs back to rigging position.
(5)
Install turnbuckle-locking clips.
(6)
Remove clamp from flap control lever.
(7)
Check that flap lever moves smoothly without binding through full range of travel.
(8) Position flap control lever in FLAP UP detent. AA. Connect and tighten all thrust control cables by adjusting turnbuckles (Fig. 407). Remove
clamps (AMM 76-11-0 A/T). AB. Tighten all engine start control cables (Fig. 407). Remove clamps (AMM 76-11-0 A/T). AC. Adjust speed brake control lever.
(1)
Place speed brake control lever in DOWN detent. Ensure that lever latch is in detent on control stand (Fig. 408).
(2)
In lower nose compartment, check that rigging pin SB-1 can be freely installed through speed brake forward drum into structure. If pin cannot be installed freely, accomplish following:
(a)
Disconnect upper end of lower control rod from idler link.
(b)
Loosen checknut and adjust rod end until rod end bolt fits freely with rigging pin SB-1 installed.
(c)
Install rod end bolt with washer under bolt head. Secure bolt with washer and locknut.
(d)
Tighten checknut on rod end.
(e)
Ensure that rod end is visible in inspection hole in control rod.
500
May 01/03 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 76-11-11 Page 409
Stabilizer Trim Chain Assembly Adjustment 500
76-11-11 Figure 405 Nov 15/67
Page 410
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
501 Flap Control Lever Rigging
May 15/69 Figure 406 (Sheet 1) 76-11-11
Page 411
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
Flap Control Lever Rigging 500
76-11-11 Figure 406 (Sheet 2) Nov 15/67
Page 412
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
(f)
Remove rigging pin SB-1. AD. Close forward nose compartment and electronics equipment access door 1201. AE. Connect external electrical power to airplane and perform following:
(1)
On forward overhead panel, position GRD INTERCONNECT switch to CLOSE.
(2)
Close circuit breakers as follows:
(a)
Hydraulic pump depressurize valve on P6-2 panel.
(b)
Pump B on P6-12 panel.
(c)
Pump B on P6-11 panel.
(3)
On forward overhead panel, position switches as follows:
(a) Hydraulic system B ELEC 1 and ELEC 2 pump switches to ON.
(b)
Hydraulic system A ENG 1 and ENG 2 pump switches to ON. AF. If no further requirement exists for external electrical power, disconnect from airplane. AG. Test engine start and thrust control systems. Refer to 76-11-0, Engine Control System -
Adjustment/Test.
500
May 15/68 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 76-11-11 Page 413
Engine Control System Cable Locations and Definitions 500
76-11-11 Figure 407 Aug 15/77
Page 414
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
500 Speed Brake Control Lever Adjustment
Nov 15/67 Figure 408 76-11-11
Page 415
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
ENGINE CONTROL CABLES - MAINTENANCE PRACTICES
1. General
A. No engine control cable maintenance practices are provided in this section. Instead, illustrations and tables are used to show cable lengths and terminal fittings, and pulley and turnbuckle locations.
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