Feb 20/94 31-26-0
Page 505
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
(2) Test Flap Versus Landing Gear Warning With EPR Override.
(a)
Connect a regulated air pressure source to engine No. 1 PT7 exhaust probe manifold fitting at the aft end of the engine. Maintain an EPR less than 1.55.
(b)
Remove lockpins and place any or all landing gear in a not down and locked position. Place landing gear handle to OFF.
NOTE: Throttle levers must be advanced greater than 17 degrees from idle stops.
(c)
Extend flaps to 25 units. Check that a continuous warning horn sounds. Continue to extend flaps and check that horn sounds at all greater positions.
(d)
Retract flaps to 25 units. Check that horn continues to sound.
(e)
Gradually increase air supply pressure at PT7 exhaust probe manifold and monitor engine EPR indicator. Check that the horn stops at an EPR indication of 1.55 or greater, but less than 1.71.
(f)
Continue increasing EPR to 2.40; do not exceed 2.50 EPR. Check that the horn remains silent.
(g)
Reduce EPR to 1.00. Check that a continuous horn sounds at an EPR equal to or greater than 1.55 (but less than 1.71) and remains sounding at the lower EPR.
(h)
Repeat steps (a) thru (g) using engine No. 2 PT7 exhaust manifold fitting.
(i)
Open EPR WARN circuit breaker on P6 panel. Check that horn is silenced. Close circuit breaker. Check that a continuous horn sounds.
(j)
Open ENG NO. 1 EPR & L.G. WARN circuit breaker on P6 panel. Check that horn is silenced. Close circuit breaker. Check that continuous horn sounds.
(k)
Open ENG NO. 2 EPR & L.G. WARN circuit breaker on P6 panel. Check that horn is silenced. Close circuit breakers. Check that continuous horn sounds.
(l)
Retract flaps to 10 units then full retract flaps. Check that horn is silent at 10 units and less.
(m)
Open ENG NO. 1 EPR & L.G. WARN circuit breaker and extend flaps to 30 units then fully extend flaps. Check that a continuous horn sounds at 30 units and greater.
(n)
Retract flaps to 25 units then fully retract flaps. Check that horn is silent at 25 units and less.
(o)
Lower and lock landing gear.
E. Restore Airplane to Normal.
(1)
Install gear ground lockpins in all landing gear.
(2)
Remove protractor and adapter from thrust lever.
(3)
Remove electrical power, if no longer required.
(4)
Remove hydraulic power, if no longer required (Ref 29-11-0).
(5)
Lower airplane and remove jacks (Ref Chapter 27, Jacking Airplane).
31-26-0 Feb 15/78 Page 506/507-509
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
5. Takeoff Warning System Adjustment
A. Equipment and Materials
(1)
Ohmmeter
(2)
Airplane Control Surface Protractor Assembly - F52485-500, F70044-500 or 4MIT65B80307-1
(3)
Protractor Adapter (Engine Cross-Shaft) - 2MIT65-45109-22
(4)
Protractor Adapter (Thrust Lever) - F72952-2
(5)
Stabilizer Actuator Trammel Bar - F80055-1
(6)
Fuel Control Unit Idle Rig Pin - F70207-50 (Ref kit F70207-3
B. Adjust Takeoff Warning System
(1) Adjust Thrust Lever Actuated Takeoff Warning Switch S283 or S133 (Fig. 502, Sheet 1). [Airplanes without EPR Activated T/O Warn System]
NOTE: The engine control system must be properly rigged prior to adjusting the switch (Ref 76-11-0 A/T).
(a)
Open circuit breakers LANDING GEAR LIGHTS and ANTI-SKID FAIL WARN & PARK BRAKE on panel P6.
(b)
Retard associated thrust lever to idle stop, on airplanes incorporating SB 31-1024 and/or SB 31-1026 (Ref skip to step (h)).
(c)
Open right side engine cowling on associated engine.
(d)
At engine fuel control unit, insert fuel control unit idle rig pin in thrust crank to fix thrust crank in idle position (Fig. 503, Sheet 2).
(e)
Remove rig pin bracket (Fig. 503, Sheet 1).
(f)
Mount protractor on engine cross-shaft hexnut using adapter; then, zero protractor (Fig. 503, Sheet 1).
(g)
Remove fuel control unit idle rig pin.
(h)
Disconnect electrical wiring from one set of takeoff warning switch terminals (Fig. 502, Sheet 1).
(i)
Connect ohmmeter across terminals C and NO of switch and check that switch is not actuated (no continuity through switch).
(j)
Advance associated thrust lever until takeoff warning switch actuates (continuity through switch). On airplanes not incorporating SB 31-1024 or SB 31-1026, check engine cross-shaft rotates to position required in Fig. 503, Sheet 1. On airplanes incorporating SB 31-1024 and/or SB 31-1026, check thrust lever position is 12.5 +1 degrees forward of idle stop using protractor on thrust lever.
中国航空网 www.aero.cn
航空翻译 www.aviation.cn
本文链接地址：737 AMM 飞机维护手册 通讯描述和操作(61)
