(g)
Compare the rudder right and left positions.
1) If the difference is more than 0.2 inch, adjust the standby actuator.
(h)
Set the FLT CONTROL A and B switches to ON.
S 715-041
(9)
Do a test of the secondary slide on the dual servo valve of the rudder power control unit:
(a)
Supply the rudder hydraulic power systems A and B
(AMM 27-21-00/201).
(b)
Slowly push the captain's left pedal forward until it touches the stop then release.
(c)
As fast as possible, push the captain's right pedal forward. 1) Make sure the right pedal move smoothly forward until it touches the stop.
2) If the right pedal moves in the opposite direction of the applied force, replace the rudder power control unit (AMM 27-21-91/401).
(d)
Release the right pedal.
(e)
Slowly push the captain's right pedal forward until it touches the stop then release.
(f)
As fast as possible, push the captain's left pedal forward. 1) Make sure the left pedal move smoothly forward until it touches the stop.
2) If the left pedal moves in the opposite direction of the applied force, replace the rudder power control unit (AMM 27-21-91/401).
(g)
Release the left pedal.
(h)
Slowly push the first officer's left pedal forward until it touches the stop then release.
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
27-21-00
ALL ú ú 02 Page 523 ú Nov 12/99
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A 737-300/400/500MAINTENANCE MANUAL
(i) As fast as possible, push the first officer's right pedal forward.
1) Make sure the right pedal move smoothly forward until it touches the stop.
2) If the right pedal moves in the opposite direction of the applied force, replace the rudder power control unit (AMM 27-21-91/401).
(j)
Release the right pedal.
(k)
Slowly push the first officer's right pedal forward until it touches the stop then release.
(l)
As fast as possible, push the first officer's left pedal forward. 1) Make sure the left pedal move smoothly forward until it
touches the stop.
2) If the left pedal moves in the opposite direction of the applied force, replace the rudder power control unit (AMM 27-21-91/401).
(m) Release the left pedal.
S 735-033
(10)
Do a test of the rudder trim control system.
S 715-044
(11)
AIRPLANES WITH 10-60447 YAW DAMPER COUPLER; Do the system test of the yaw damper (AMM 22-12-00/501).
S 715-045
(12)
AIRPLANES WITH 10-62253 YAW DAMPER COUPLER; Do the operational test of the yaw damper (AMM 22-12-01/501).
TASK 27-21-00-735-034
4. Rudder Trim Control System Test
_______________________________
A. Standard Tools and Equipment
(1) Scale - 0-2 feet, in inches, tenths, and hundreths of an inch increments
(2) F70207-69, -78 or -83 - Rig Pins Kit ~............................................................................... | | | DIAMETER | LENGTH | | | REF NO. | F70207-( ) | (INCHES) | (INCHES) | FUNCTION | .................................................................................
| R-1 | -14 | 0.309-0.311 | 12.7 |0.25 |CAPTAINS RUDDER PEDAL |
| R-2 | -14 | 0.309-0.311 | 12.7 |0.25 |FIRST OFFICERS RUDDER PEDAL|
| R-3 | -11 | 0.309-0.311 | 6.7 |0.25 |CAPTAINS RUDDER FORWARD |
| | | | | QUADRANT |
| R-4 | -11 | 0.309-0.311 | 6.7 |0.25 |FIRST OFFICERS RUDDER |
| | | | | FORWARD QUADRANT |
| R-5 | -11 | 0.309-0.311 | 6.7 |0.25 |RUDDER FEEL AND CENTERING |
| | | | | UNIT |
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本文鏈接地址：737-300 400 500 AMM 飛機維護手冊 飛行操縱 FLIGHT CONTROLS 2(26)
