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(e) Move the rudder trim knob to NOSE RIGHT until the rudder stops.
1) Make sure the rudder moves 16.89 ±0.93 in. (429.0 ±23.6 mm) (18.03 +/- 1.00
degrees) to the right side.
2) Make sure the rudder trim indicator is at least 15 units of trim.
(f) Move the rudder trim knob to NOSE LEFT until the rudder trim indicator shows 10.0 +/-
0.25 units of trim.
1) Make sure the rudder moves 10.12 ±1.26 in. (257.0 ±32.1 mm) (10.74 +/- 1.35
degrees) to the left side.
737-600/700/800/900
AIRCRAFT MAINTENANCE MANUAL
EFFECTIVITY
GUN 001-005, 155-157, 201-999 PRE SB 737-27-1253 27-21-00
Config 1
Page 549
Jun 10/2007
D633A101-GUN
BOEING PROPRIETARY - Copyright#Unpublished Work - See title page for details
(g) Move the rudder trim knob to NOSE LEFT until the rudder stops.
1) Make sure the rudder moves 16.89 ±0.93 in. (429.0 ±23.6 mm) (18.03 +/- 1.00
degrees) to the left side.
2) Make sure the rudder trim indicator is at least 15 units of trim.
(h) Make sure the rudder trim knob operates smoothly and goes back to the center freely.
SUBTASK 27-21-00-860-110-001
(3) Do this task: Put the Rudder Hydraulic systems A, B, and Standby Back to the Condition
Before the Pressurization, TASK 27-21-00-840-801.
------------------------- END OF TASK ---------------------------
TASK 27-21-00-700-820-001
14. Wheel to Rudder Interconnect System Test
A. General
(1) Use this test to make sure the wheel to rudder function of the standby rudder power control unit
(PCU) operates correctly.
B. References
Reference Title
27-21-00-800-801 Rudder Hydraulic System A, B, or Standby Pressurization (P/B 201)
27-21-00-840-801 Put the Rudder Hydraulic systems A, B, and Standby Back to the
Condition Before the Pressurization (P/B 201)
27-51-00-860-803 Extend the Trailing Edge Flaps (P/B 201)
27-51-00-860-804 Retract the Trailing Edge Flaps (P/B 201)
34-21-00-820-801 Air Data Inertial Reference System - Alignment from the FMC CDU
(P/B 201)
34-21-00-820-802 Air Data Inertial Reference System - Alignment from the ISDU
(P/B 201)
C. Location Zones
Zone Area
211 Flight Compartment - Left
212 Flight Compartment - Right
325 Vertical Fin - Rudder
D. Procedure
SUBTASK 27-21-00-860-162-001
(1) Make sure that this circuit breaker is closed:
CAPT Electrical System Panel, P18-2
Row Col Number Name
C 8 C00544 FLIGHT RECORDER POSITION SENSOR
737-600/700/800/900
AIRCRAFT MAINTENANCE MANUAL
EFFECTIVITY
GUN 001-005, 155-157, 201-999 PRE SB 737-27-1253 27-21-00
Config 1
Page 550
Oct 10/2007
D633A101-GUN
BOEING PROPRIETARY - Copyright#Unpublished Work - See title page for details
SUBTASK 27-21-00-860-111-001
WARNING: MAKE SURE THAT PERSONS AND EQUIPMENT ARE CLEAR OF ALL CONTROL
SURFACES BEFORE YOU SUPPLY HYDRAULIC POWER. AILERONS, RUDDER,
ELEVATORS, FLAPS, SPOILERS, SLATS, AND THRUST REVERSERS CAN MOVE
QUICKLY WHEN YOU SUPPLY HYDRAULIC POWER. THIS CAN CAUSE INJURY TO
PERSONS AND DAMAGE TO EQUIPMENT.
(2) Pressurize the rudder hydraulic systems A and B, do this task: Rudder Hydraulic System A, B,
or Standby Pressurization, TASK 27-21-00-800-801.
SUBTASK 27-21-00-860-112-001
(3) Align the ADIRS. To align the ADIRS, do this task: Air Data Inertial Reference System -
Alignment from the ISDU, TASK 34-21-00-820-802 or Air Data Inertial Reference System -
Alignment from the FMC CDU, TASK 34-21-00-820-801.
SUBTASK 27-21-00-860-113-001
(4) Make sure that the mode select switch on the inertial reference system (IRS) mode select unit
(MSU) is set to the NAV position.
SUBTASK 27-21-00-860-114-001
(5) Move the flaps to a position other than up position. To move them, do this task: Extend the
Trailing Edge Flaps, TASK 27-51-00-860-803.
SUBTASK 27-21-00-730-023-001
(6) Do the test of the wheel to rudder interconnect system:
NOTE: The rudder will move pass the center position to the opposite direction when the
control wheel returns to the neutral position. To return the rudder to the center position
with the control wheel at neutral, you must set the YAW DAMPER switch on the
overhead panel to the OFF position then back to the ON position.
(a) Make sure the rudder is in the neutral position.
1) Make sure the rudder trim indicator is at 0.0 +/- 0.25 unit of trim.
2) If it is necessary, move the rudder pedals lightly to put the rudder to the neutral
position.
(b) Set the FLT CONTROL A and B switches, on the forward overhead panel, P5, to the STBY
RUD position.
(c) Set the YAW DAMPER switch, on the forward overhead panel, P5, to the ON position.
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737-600/700/800/900 AIRCRAFT MAINTENANCE MANUAL飞机维护手册2(39)
