(m)
Position flap control lever in FLAP UP detent.
(n)
Position both alternate flaps switches to OFF.
WARNING: LEADING EDGE CONTROL SURFACES WILL RETRACT. ENSURE THAT PERSONNEL AND EQUIPMENT ARE CLEAR.
(7) Check Flap Control Lever Operating Force
(a) Check that tangential force required to move flap control lever between detents does not exceed 2.5 pounds, excluding cable cushion. Measure force at end of lever.
B. Restore Airplane to Normal
(1)
Remove hydraulic system A power (Ref 27-51-0 MP).
(2)
Remove electrical power if no longer required.
(3)
Lockwire alternate flaps arm switch.
3. Flap Load Limiter Test
A. Equipment and Materials
(1) A vacuum source and barometer or equivalent capable of measuring a differential pressure of up to 1.5 inches of mercury to an accuracy of士0.015 inches of mercury.
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27-51-01 Page 522 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Apr 01/97
B. Prepare to test flap load limiter system.
CAUTION: TO PREVENT DAMAGE TO EQUIPMENT AND INSTRUMENTS, CHECK FOLLOWING PRECAUTIONS BEFORE APPLYING PRESSURE TO THE PITOT STATIC SYSTEM.
(1)
Ensure that pitot static probe heaters remain off during testing.
(2)
Apply pitot line pressure with a suitable connection to the auxiliary pitot tubes.
CAUTION: THE PITOT PRESSURE SHALL ALWAYS EQUAL OR EXCEED STATIC LINE PRESSURE AND DIFFERENCE (DIFFERENTIAL PRESSURE) SHALL NOT EXCEED 10.00 INCHES OF MERCURY.
(3)
Apply static absolute pressure to auxiliary static system by connecting vacuum source to drain fittings located in electronics bay or to pitot static probe ports.
CAUTION: INSTRUMENTS WILL BE DAMAGED IF STATIC PRESSURE EXCEEDS PITOT PRESSURE EVEN MOMENTARILY. STATIC PRESSURE SHALL NOT EXCEED 8000 FEET ABOVE ACTUAL AIRPORT ALTITUDE AND APPLICATION OR RELEASE OF VACUUM SHALL BE MADE AT A RATE OF CLIMB OR DESCENT OF APPROXIMATELY 3000 FEET PER MINUTE OR LESS.
(4)
Seal all unused auxiliary system static ports in such a way that removal of seal will be complete leaving no deposits or roughness in or about static ports.
(5)
Close the FLAP LOAD LIMITER circuit breaker on the P6 panel.
(6)
Connect external electrical power to the airplane.
(7)
Provide hydraulic system A power (Ref AMM 27-51-0).
(8)
Position flap control lever to FLAPS UP detent.
(9)
Check that flaps retract to FLAP UP position.
(10)
Position flap control lever to 40-unit detent.
(11)
Check that flaps extend to 40-unit position.
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Oct 20/86 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-51-01 Page 523
PITOT PRESSURE VALUES
ACTUAL .P1 REQUIRED .P1 ACTUAL .P2 REQUIRED .P2 ACTUAL .P1-.P2 REQUIRED .P1-.P2
1.121 in Hg (152 kts) to 1.274 in Hg (162 kts) 1.046 in Hg (147 kts) to 1.197 in Hg (157 kts) 0.075 in Hg (5 kts) min
Table IV
C. Test flap load limiter system.
(1)
Increase pressure in pitot static system until flaps start to retract.
(2)
Check that actual differential pressure (.P1) is within required range in Table IV. Record actual .P1 in table.
(3)
Check that flaps retract to 30-unit position.
(4)
Decrease differential pressure in pitot static system until flaps start to extend.
(5)
Check that actual differential pressure (.P2) is within required range in Table IV. Record actual .P2 in table.
(6)
Check that actual .P1-.P2 agrees with required .P1-.P2 in Table IV.
(7)
Check that flaps extend to 40-unit position.
(8)
Depressurize pitot static system and return to normal.
(9)
Position flap load limiter test switch on equipment bay light panel in electronics compartment to SYSTEM TEST position and check that flaps retract to approximate 30-unit position.
NOTE: If airplane is on jacks compress right-hand main gear strut approximately 5 inches to ground position.
(10)
Release test switch, and check that flaps extend to 40-unit position.
(11)
Position flap control lever to 30-unit detent.
(12)
Check that flaps retract to 30-unit position.
(13)
Position flap load limiter test switch to SWITCH TEST position.
(14)
Check that test lamp lights and extinguishes upon release of switch.
(15)
Position flap control lever to FLAP UP (0-unit) detent.
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本文链接地址：737 AMM 飞机维护手册 飞行操纵 FLIGHT CONTROLS 3(5)
