曝光臺(tái) 注意防騙 網(wǎng)曝天貓店富美金盛家居專(zhuān)營(yíng)店坑蒙拐騙欺詐消費(fèi)者

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C. Location Zones
Zone Area
112 Area Forward of Nose Landing Gear Wheel Well
133 Main Landing Gear Wheel Well, Body Station 663.75 to Body Station
727.00 - Left
134 Main Landing Gear Wheel Well, Body Station 663.75 to Body Station
727.00 - Right
211 Flight Compartment - Left
212 Flight Compartment - Right
572 Left Wing - Aileron
672 Right Wing - Aileron
D. Access Panels
Number Name/Location
112A Forward Access Door
E. Prepare for the Check
SUBTASK 27-11-00-480-012
WARNING: MAKE SURE THE DOWNLOCK PINS ARE INSTALLED ON ALL THE LANDING GEARS.
WITHOUT THE DOWNLOCK PINS, THE LANDING GEARS COULD RETRACT AND
CAUSE INJURIES TO PERSONS AND DAMAGE TO EQUIPMENT.
(1) If the downlock pins are not installed on all the landing gears, do this task: Landing Gear
Downlock Pins Installation, TASK 32-00-01-480-801.
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SUBTASK 27-11-00-010-002
(2) Open this access panel:
Number Name/Location
112A Forward Access Door
F. Do a Check of the Aileron System Adjustment
SUBTASK 27-11-00-820-014
(1) Do a check of the aileron system adjustment:
(a) Attach the straightedge, SPL-1671 on the captain’s and first officer’s control wheels.
(b) Make sure you can freely install rig pin A/S-4, from the rig pin kit, SPL-1585, in the aileron
bus drum (Figure 501).
1) If you cannot freely install rig pin A/S-4, do this task: Pogo and Power Control Unit
(PCU) Adjustment, TASK 27-11-00-820-802.
(c) Remove rig pin A/S-4 from the aileron bus drum.
(d) Remove the straightedge, SPL-1671 from the captain’s and first officer’s control wheels.
WARNING: MAKE SURE ALL PERSONS AND EQUIPMENT ARE CLEAR OF THE FLIGHT
CONTROL SURFACES, THE THRUST REVERSERS, AND THE LANDING GEAR.
THE CONTROL SURFACES, THE THRUST REVERSERS, AND THE LANDING GEAR
CAN MOVE SUDDENLY WITH THE PRESSURIZATION OF A HYDRAULIC SYSTEM.
THIS CAN CAUSE INJURY TO PERSONS AND DAMAGE TO EQUIPMENT.
(e) Pressurize hydraulic systems A and B, do this task: Hydraulic System A or B
Pressurization, TASK 29-11-00-860-801.
(f) Operate the aileron trim switches on the control stand panel, P8, until you can freely install
and remove the rig pin A/S-15 from the rig pin kit, SPL-1585 (Figure 501).
(g) Make sure the captain’s control wheel is the center of the neutral position.
1) Gently move the control wheel in the backlash band.
2) Make sure the center of the backlash band aligns with the protractor zero position.
(h) Make sure the index mark on the captain’s control wheel aligns with the zero mark on the
control column.
(i) Attach the straightedge, SPL-1671 on the captain’s and first officer’s control wheels.
(j) Make sure the top ends of the control wheels touch the straightedge, SPL-1671.
(k) Make sure that one end of the first officer’s control wheel is no more than 0.20 inch (5.1 mm)
from the straightedge, SPL-1671.
1) If the control wheels do not align, adjust the cables ACBA ACBB. To adjust the cables,
do this task: Aileron Cables Adjustment, TASK 27-11-00-820-801.
(l) Make sure you can freely install and remove these rig pins from the rig pin kit, SPL-1585
(Figure 501):
NOTE: Install these rig pins at the same time.
1) Rig pins A/S-1 and A/S-1A at the forward drum
2) Rig pin A/S-3 in the aileron input crank
3) Rig pin A/S-4 in the aileron bus drum
4) Rig pin A/S-15 in the aileron trim actuator.
737-600/700/800/900
AIRCRAFT MAINTENANCE MANUAL
EFFECTIVITY
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(m) If you cannot freely install and remove the above rig pins, adjust the cables AA and AB. To
adjust the cables, do this task: Aileron Cables Adjustment, TASK 27-11-00-820-801.
(n) Remove the straightedge, SPL-1671 from the captain’s and first officer’s control wheels.
WARNING: MAKE SURE PERSONS AND EQUPIMENT ARE CLEAR OF THE TRAILING EDGE
FLAPS, THE LEADING EDGE FLAPS AND SLATS. THE FLAPS AND SLATS WILL
EXTEND. THIS CAN CAUSE INJURY TO PERSONS AND DAMAGE TO EQUIPMENT.
(o) Do this task: Extend the Trailing Edge Flaps, TASK 27-51-00-860-803.
GUN 101-122
(p) Make sure the aileron is in the rig position (Figure 506).
NOTE: The aileron rig position is when the outboard edge of the aileron lower surface is
0.49 ±0.03 inch (12.4 ±0.8 millimeters) below the adjacent fixed lower trailing
　
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