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SUBTASK 27-51-00-860-054
(7) Move the ALTERNATE FLAPS ARM switch to the OFF position.
NOTE: The leading edge flaps and slats will retract.
SUBTASK 27-51-00-710-007
(8) Move the ALTERNATE FLAPS ARM switch to the ARM position.
SUBTASK 27-51-00-860-055
(9) Move the flap control lever to the 1-unit position.
(a) Make sure the flaps do not move.
(10) Hold the ALTERNATE FLAPS CONTROL switch in the DOWN position until the trailing edge flaps
are in the 1-unit position.
NOTE: The leading edge flaps and slats will extend.
(11) Release the ALTERNATE FLAPS CONTROL switch to the OFF position.
(12) Move the ALTERNATE FLAPS ARM switch to the OFF position.
SUBTASK 27-51-00-720-012
(13) Do a test of the time necessary to retract the trailing edge flaps from the 1-unit position:
(a) Move the ALTERNATE FLAPS ARM switch to the ARM position.
(b) Move the flap control lever to the UP position.
(c) Use a stopwatch, STD-1139 to measure the time necessary to retract the flaps to the UP
position.
(d) Move the ALTERNATE FLAPS CONTROL switch to the UP position until the trailing edge
flaps stop.
NOTE: The flap retraction is controlled by a limit switch.
(e) Make sure the time it takes for the flaps to move from the 1-unit position to the retracted
position is 47 to 58 seconds.
NOTE: The leading edge flaps and slats will retract.
(f) Move the ALTERNATE FLAPS CONTROL switch to the OFF position.
(g) Move the ALTERNATE FLAPS ARM switch to the OFF position.
G. Put the Airplane Back to Its Usual Condition
SUBTASK 27-51-00-860-056
(1) Remove system B hydraulic power, do this task: Hydraulic System A or B Power Removal,
TASK 29-11-00-860-805.
------------------------- END OF TASK ---------------------------
737-600/700/800/900
AIRCRAFT MAINTENANCE MANUAL
EFFECTIVITY
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TASK 27-51-00-710-802
12. Transmission No-Back Brake Operational Test
(Figure 501)
A. General
(1) During this operational test, you make sure the no-back brakes in the transmissions operate.
(2) This test involves listening for a ratchet sound from the transmissions while the flaps extend.
(3) A minimum of two people are necessary to do this test.
B. References
Reference Title
24-22-00-860-811 Supply Electrical Power (P/B 201)
27-51-00-860-801 Trailing Edge Flap System Operation With Primary Control (P/B 201)
27-51-18-000-802 Inboard Flap Support Aft Fairing Removal (P/B 401)
27-51-18-400-802 Inboard Flap Support Aft Fairing Installation (P/B 401)
27-51-28-000-802 Outboard Flap Outboard Support Aft Fairing Removal (P/B 401)
27-51-28-000-804 Outboard Flap Inboard Support Aft Fairing Removal (P/B 401)
27-51-28-400-802 Outboard Flap Outboard Support Aft Fairing Installation (P/B 401)
27-51-28-400-804 Outboard Flap Inboard Support Aft Fairing Installation (P/B 401)
29-11-00-860-801 Hydraulic System A or B Pressurization (P/B 201)
29-11-00-860-805 Hydraulic System A or B Power Removal (P/B 201)
32-00-01-480-801 Landing Gear Downlock Pins Installation (P/B 201)
C. 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-1797 Stethoscope - Mechanics, 12 Inch Probe
(Part #: GA111D, Supplier: 55719, A/P Effectivity: 737-ALL)
(Opt Part #: GA111C, Supplier: 55719, A/P Effectivity: 737-ALL)
D. 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
211 Flight Compartment - Left
212 Flight Compartment - Right
542 Left Wing - Fairing Flap Support No. 3
543 Left Wing - Fairing Flap Support No. 2
544 Left Wing - Fairing Flap Support No. 1
642 Right Wing - Fairing Flap Support No. 6
643 Right Wing - Fairing Flap Support No. 7
644 Right Wing - Fairing Flap Support No. 8
737-600/700/800/900
AIRCRAFT MAINTENANCE MANUAL
EFFECTIVITY
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E. Prepare for the Operational Test
SUBTASK 27-51-00-480-009
WARNING: MAKE SURE THE DOWNLOCK PINS ARE INSTALLED ON ALL THE LANDING GEAR.
WITHOUT THE DOWNLOCK PINS, THE LANDING GEAR CAN RETRACT AND CAUSE
　
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