B61352 B61295
Chain Assembly Adjustment 500
27-41-0 Figure 502 (Sheet 1) Feb 20/93
Page 506
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
501 Chain Assembly Adjustment
Feb 20/93 Figure 502 (Sheet 2) 27-41-0
Page 507
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
(b)
If clearance between grommet and cable is not within specified limits, release tension in cable and chain assembly by adjusting forward and aft support links. Disconnect chain assembly at connector link and add or remove links from chain as necessary to obtain correct clearance. Install cotter pins on outboard side of chain per Detail A, Fig. 502.
NOTE: Adding or removing a chain link will change clearance at grommet 0.22 inch.
(c)
Adjust cables and chain assembly as required per step (3).
(6)
Check that there is a minimum of 3/4-inch clearance between aileron bus control cable and sprocket chain.
(7)
Adjust position indicator.
(a)
Manually operate stabilizer until B dimension is 41.57 +0.05 inches. Disconnect flexible drive shaft (l, Fig. 502) from forward mechanism if required.
(b)
Rotate flexible drive shaft until stabilizer position indicator is at 3 +1/4 units trim.
(c)
Connect flexible drive shaft to forward trim mechanism. Check for positive engagement of flexible drive shaft with spline in forward mechanism before tightening nut.
(8)
Adjust stabilizer trim limit switches (Ref 27-41-101, Adjustment/Test).
(9)
Adjust stabilizer takeoff warning airplane nose up switch per 31-26-0, Adjustment/Test. The takeoff warning airplane nose down switch is combined with the stabilizer airplane nose down trim limit switch and is adjusted per previous step.
(10)
Adjust stabilizer trim brake (Ref 27-41-51, Adjustment/Test).
(11)
Test system per par. 3.
E. Restore Airplane to Normal Configuration
(1)
Remove electrical power, if no longer required.
(2)
Install access panel.
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27-41-0 Page 508 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Aug 15/78
3. Horizontal Stabilizer Trim System Test
A. Equipment and Materials
(1)
Actuator Trammel Bar - F80055-1
(2)
Adapter - F71252 or Pinion Gear Wrench Assembly, F71267
NOTE: F71267 performs same function as F71252 - but has retaining handle which locates in gearbox housing, thus eliminating necessity of using wrench to prevent rotation.
(3)
Torque Wrench Adapter - F70326-1 (preferred), TE65-20804 (optional)
B. Test Stabilizer Trim System
(1)
Open stabilizer trim access door 3701 (Ref Chapter 12).
(2)
Check that control column is in neutral and is unrestrained.
(3)
Test stabilizer manual travel limits.
(a)
Rotate captain's stabilizer trim wheel counterclockwise until stabilizer trim jackscrew up stop is just contacted.
(b)
Check that B dimension is 45.84 +0.10 inches (Fig. 501).
(c)
Check that stabilizer trim indicator indicates 0.0 +1/2 units AIRPLANE NOSEDOWN trim.
(d)
Turn captain's stabilizer trim wheel clockwise until lower stop is just contacted and check that B dimension is 21.32 +0.10 inches.
(e)
Check that stabilizer trim indicator indicates 17 +1/2 units AIRPLANE NOSE UP trim.
(f)
Check that position indicator on right side agrees with indicator on left side at all stabilizer positions within 1/2 trim unit.
(4)
Check maximum force required during manual trimming at several places from one extreme of travel to other in both directions. Check that force does not exceed 14.7 pounds (60 pound-inches torque) measured at trim wheel handle.
NOTE: If the torque wrench adapter is used, remove the adapter and install the tie rod and nuts before you do the system test.
(5)
Manually operate system through one complete cycle and check that system runs smoothly without binding.
(6)
Test clutch friction.
500
Feb 20/94 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-41-0 Page 509
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