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3) Install the washer [28], washer [29] and nut [30] on the bolt [27].
(e) Do this task: Spoiler Hydraulic Systems A and B Pressurization, TASK 27-61-00-800-801.
(f) Remove the rig pin A/S-4.
SUBTASK 27-61-41-420-005
(7) Connect the ratio changer input rod [35] to the upper control crank [15]:
(a) Install the rig pin A/S-14 from the test set rig pin kit, SPL-1585 in the spoiler mixer [33].
(b) Make sure you can easily install the bolt [16] in the ratio changer input rod [35].
(c) If you cannot easily install the bolt [16], adjust the length of the rod:
1) Loosen the checknut on the ratio changer input rod [35].
2) Adjust the ratio changer input rod end [35] until you can easily install the bolt [16] in the
rod end.
3) Tighten the checknut on the ratio changer input rod end [35].
(d) Install the bolt [16] to attach the ratio chanter input rod [35] to the upper control crank [15].
(e) Install the washer [17], washer [18] and nut [19] on the bolt [16].
(f) Remove the rig pin A/S-14.
SUBTASK 27-61-41-420-006
(8) Attach the spoiler cable quadrant [5] to the quadrant shaft [36]:
(a) Install the bolts [6] to attach the spoiler cable quadrant [5] to the quadrant shaft [36].
(b) Install the washers [7], washers [8] and nuts [9] on the bolt [6].
SUBTASK 27-61-41-420-007
(9) Connect the right aileron control cable AA [1] and cable AB [3]:
(a) Use the cable retaining plates to attach the cables to the spoiler cable quadrant [5].
(b) Connect aileron control cable AA [1] and cable AB [3] at the cable turnbuckles [2].
(c) Remove the cable clamps from aileron control cable AA [1] and cable AB [3].
(d) Remove the rig pins A/S-1, A/S-1A and A/S-3.
SUBTASK 27-61-41-820-001
(10) Do this task: Aileron Cables Adjustment, TASK 27-11-00-820-801.
SUBTASK 27-61-41-720-001
(11) Do this task: Spoiler Control Quadrant Functional Test, TASK 27-61-41-000-802.
G. Put the Airplane Back to Its Usual Condition
SUBTASK 27-61-41-410-001
(1) Close this access panel:
Number Name/Location
112A Forward Access Door
SUBTASK 27-61-41-410-002
(2) Install the right floor panel between the seat tracks at the second window aft of the wind escape
hatch:
(a) Do this task: Passenger Cabin Floor Panel Installation, TASK 53-21-00-400-801.
(b) Do this task: Carpet Installation, TASK 25-27-15-400-801.
737-600/700/800/900
AIRCRAFT MAINTENANCE MANUAL
EFFECTIVITY
GUN ALL 27-61-41
Page 410
Oct 10/2006
D633A101-GUN
BOEING PROPRIETARY - Copyright#Unpublished Work - See title page for details
(c) Do this task: Passenger Seat Installation, TASK 25-22-00-400-802.
------------------------- END OF TASK ---------------------------
TASK 27-61-41-000-802
4. Spoiler Control Quadrant Functional Test
A. References
Reference Title
24-22-00-860-811 Supply Electrical Power (P/B 201)
27-61-00-840-801 Put the Spoiler Hydraulic systems A and B Back to the Condition
Before the Pressurization (P/B 201)
27-62-00-800-801 Speed Brake Hydraulic Systems A and B Pressurization (P/B 201)
B. Tools/Equipment
NOTE: When more than one tool part number is listed under the same "Reference" number, the
tools shown are alternates to each other within the same airplane series. Tool part numbers
that are replaced or non-procurable are preceded by "Opt:", which stands for Optional.
Reference Description
COM-1691 Protractor - Digital, Vertical or Horizontal
(Part #: KS5549, Supplier: 75245, A/P Effectivity: 737-ALL)
SPL-1585 Kit - Rigging Pins, All Systems
(Part #: F70207-109, Supplier: 81205, A/P Effectivity: 737-600, -700,
-700C, -700ER, -700QC, -800, -900, -900ER, -BBJ)
SPL-1670 Mount - Control Wheel Protractor
(Part #: F72790, Supplier: 81205, A/P Effectivity: 737-100, -200, -200C,
-300, -400, -500, -600, -700, -700C, -700ER, -700QC, -800, -900, -900ER,
-BBJ)
SPL-1680 Protractor - Assembly, Control Column
(Part #: 4MIT65B80307-1, Supplier: 81205, A/P Effectivity: 737-100,
-200, -200C, -300, -400, -500, -600, -700, -700C, -700ER, -700QC, -800,
-900, -900ER, -BBJ)
(Part #: A27021-29, Supplier: 81205, A/P Effectivity: 737-100, -200,
-200C, -300, -400, -500, -600, -700, -700C, -700ER, -700QC, -800, -900,
-900ER, -BBJ)
C. Location Zones
Zone Area
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
210 Subzone - Control Compartment - Body Station 178.00 to Body
Station 259.50
563 Left Wing - Spoiler No. 4
565 Left Wing - Spoiler No. 2
662 Right Wing - Spoiler No. 8
664 Right Wing - Spoiler No. 10
　
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