G43214
Tab Control Linkage 521
27-11-0 Figure 507 Nov 15/69
Page 520
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
(d) Shorten or lengthen adjustable aileron tab control rods as follows: 1) Note amount and direction of required adjustment of tab trailing edge relative to
the aileron. Take measurements at trailing edge back of tab rod attachment. 2) Remove bolts attaching tab rods to forward fittings (Fig. 507). 3) Remove aileron tab hinge bolts and remove tab and rods from aileron. 4) Loosen jamnuts on tab rod being careful not to reposition rod end or rod barrel. 5) Turn the rod barrel the required number of turns being careful to restrain the rod
and rod end angularly.
6) Check that witness holes in barrel are covered. Tighten jamnuts 100-140 pound-inches for the smaller jamnut and 100 pound-inches (maximum) for the larger jamnut. Lockwire jamnuts.
7) Reinstall tab and rods on aileron. Attach bolts for tab rods must be inserted with fingers only to ensure there is no binding between rod and bolt or deflection of rods. Readjust length of rod if binding or deflection occurs.
(8)
Check aileron control system rigging as follows:
(a)
Provide systems A and B hydraulic power (Ref 27-11-0).
(b)
Ensure flight controls system A and B switches are on.
(c)
Ensure that aileron trim knob indicator is in zero trim position. Check that trim roller is properly seated against cam detent.
(d)
Center aileron control wheels by gently moving control wheel within backlash band. The center of this band is control wheels neutral position.
(e)
Check that rigging pins A/S-1, A/S-1A, A/S-3, A/S-4 and A/S-13 may be inserted and removed without binding.
(f)
Check that ailerons align with index marks on wing structure per Fig. 506.
(g)
Check that motion gaps between upper bus drum lug and stop bolts on lower drum are within limits (Section A-A, Fig. 505).
(h)
If installed, check that index mark on control wheel hub aligns with zero on control column marker.
(i)
Rotate control wheel through several cycles and check that aileron spring cartridge is not compressing and is free from binding.
(9)
Test aileron and aileron trim control system per par. 2.
(10)
Return airplane to normal configuration.
(a)
Remove systems A and B hydraulic power (Ref 27-11-0, Maintenance Practices).
(b)
Remove electrical power if no longer required.
(c)
Close access panels and doors.
521
Feb 15/73 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-11-0 Page 521
2. Aileron and Aileron Trim Control System Test
A. General
(1)
The following tests of the aileron and aileron trim control systems cover the measurement of residual system friction, operation of transfer mechanism, measurement of aileron deflection and test of autopilot authority.
(2)
Prior to initiating the test, carefully check all accessible mechanical components for condition and security.
B. Equipment and Materials
(1)
Control Column Protractor Assembly-4MIT65B80307-1 (Preferred) or F52485-500 (Optional) which is used with the following adapters:
(a)
Aileron Control Wheel Protractor Mount-F72790
(b)
Forward Thrust Lever Protractor Adapter-F72952-2
(2)
Spring Scale-capacity 0 to 150 pounds
(3)
Rudder Trim Knob Torque Adapter-SE27-2011 (Preferred) or SE27-2008 (Optional)
NOTE: SE 27-2008 Adapter may still be used if it adequately grips the currently used trim knobs.
(4)
Voltmeter-General Purpose VTVM
(5)
Control Wheel Torque and Force Test Adapter-F72867-1
(6)
Protractor-Aileron Tab Alignment-F80222-1 which consists of a -2 protractor assembly (Ref 27-09-700, Maintenance Practices)
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27-11-0 Page 522 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. May 01/99
G03311
500 Control Wheel Torque and Force Test Adapter
Nov 15/72 Figure 508 27-11-0
Page 523
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
C. Prepare Aileron and Aileron Trim Control System for Test
(1)
Install protractor and protractor mount on first officer's aileron control wheel.
(2)
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