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the tabs.
(e) N1 equal for both engines
(f) Wing fuel loads equal
(g) Flaps up
SUBTASK 27-31-00-710-009
(2) Set the SPOILER A and B switches on the forward overhead panel, P5, to the OFF position.
SUBTASK 27-31-00-860-110
(3) Set the FLT CONTROL A and B switches on the forward overhead panel, P5, to the STDBY RUD
position.
NOTE: To successfully complete the test, the airplane must be re-trimmed to the same
airspeed. To provide a greater precision for the maneuver, someone other than the
pilot in command should set the switches.
SUBTASK 27-31-00-860-128
(4) Set the autopilot stabilizer trim switch to cutout.
NOTE: A speed trim fail master caution annunciation may occur if thresholds are exceeded.
NOTE: As soon as you complete the power off flight test, you must move the autopilot
stabilizer trim switch from the cutout position.
SUBTASK 27-31-00-860-111
(5) If the airplane pitches, use the elevator to re-trim the airplane to the same airspeed:
737-600/700/800/900
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EFFECTIVITY
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(a) Manually turn the stabilizer trim wheel to reduce column force to zero.
(b) Keep a record of the number of turns required to re-trim the airplane.
NOTE: During the initial rotation of the stabilizer trim wheel, there might be some
freeplay. Do not count the turns until you remove the freeplay.
(c) Keep a record of the center of gravity of the airplane.
SUBTASK 27-31-00-860-161
(6) After completing the elevator power-off flight test portion of the flight, return the switches (that
were moved for the power-off flight test) to their normal flight positions.
SUBTASK 27-31-00-700-005
(7) Make sure the number of turns of the stabilizer trim wheel in the airplane Nose Up or Nose Down
direction, are within the limits of the corresponding region in the referenced figure.
SUBTASK 27-31-00-700-002
(8) If the number of turns of the stabilizer trim wheel in the airplane Nose Up or Nose Down
direction, are more than the limits, do the steps that follow:
(a) Make sure the rigging of the elevator control pushrods, the input rod of the elevator power
control unit (PCU), and the output rod of the elevator feel and centering unit is correct.
(b) If the rigging of the elevator control pushrods, the input rod of the elevator PCU, and the
output rod of the elevator feel and centering unit is satisfactory, then, do this task: Elevator
Tab Pushrod - Adjustment after the Elevator Power-Off Flight Test,
TASK 27-31-00-820-808.
------------------------- END OF TASK ---------------------------
737-600/700/800/900
AIRCRAFT MAINTENANCE MANUAL
EFFECTIVITY
GUN ALL 27-31-00
Page 598.12
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737-700 Elevator Tab Rig Adjustment Chart
Figure 517/27-31-00-990-843
737-600/700/800/900
AIRCRAFT MAINTENANCE MANUAL
EFFECTIVITY
GUN 101-122 27-31-00
Page 598.13
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737-800 Elevator Tab Rig Adjustment Chart
Figure 518/27-31-00-990-834
737-600/700/800/900
AIRCRAFT MAINTENANCE MANUAL
EFFECTIVITY
GUN 156, 201-204, 206 PRE SB 737-55A1080 27-31-00
Page 598.14
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737-800 Elevator Tab Rig Adjustment Chart
Figure 519/27-31-00-990-846
737-600/700/800/900
AIRCRAFT MAINTENANCE MANUAL
EFFECTIVITY
GUN 001-099, 155, 157, 205, 207-999; GUN 156, 201-204, 206
POST SB 737-55A1080
27-31-00
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Elevator Hinge Assemblies
Figure 520 (Sheet 1 of 4)/27-31-00-990-820
737-600/700/800/900
AIRCRAFT MAINTENANCE MANUAL
EFFECTIVITY
GUN ALL 27-31-00
Page 598.16
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Elevator Hinge Assemblies
Figure 520 (Sheet 2 of 4)/27-31-00-990-820
737-600/700/800/900
AIRCRAFT MAINTENANCE MANUAL
EFFECTIVITY
GUN ALL 27-31-00
Page 598.17
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Elevator Hinge Assemblies
Figure 520 (Sheet 3 of 4)/27-31-00-990-820
737-600/700/800/900
AIRCRAFT MAINTENANCE MANUAL
　
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