(e)
Adjust switch as required by bending switch actuator tab.
(f)
Remove ohmmeter and set speed brake lever to DOWN position.
501
31-26-0 Page 518 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Jun 20/89
H23645 H23641 H30034
Engine Cross-Shaft Positioning for Thrust Lever
501 Actuated Takeoff Warning Switch Adjustment
Feb 20/89 Figure 503 (Sheet 1) 31-26-0
Page 519
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
Engine Cross-Shaft Positioning for Thrust Lever
Actuated Takeoff Warning Switch Adjustment 501
31-26-0 Figure 503 (Sheet 2) Feb 20/89
Page 520
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
501 No. 4 Flap Jackscrew Positioning for Flap Takeoff Warning Switch Adjustment
Feb 20/89 Figure 504 31-26-0
Page 521
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
6. Takeoff Warning System Test
A. General
(1)
The takeoff warning system should be tested after maintenance has been performed on a component to ensure the system is functioning properly. The prepare to test steps must be completed prior to performing any test.
(2)
The test procedure contains separate checks to enable components to be tested individually when required. Two methods are provided to test EPR takeoff warning circuits. One method uses the self-test switch on each engine accessory module and the other method requires the engines to be running.
(3)
A leading edge and trailing edge flap position aural warning circuits test is provided at end of these procedures.
B. Equipment and Materials
(1)
Protractor - F52485-500
(2)
Protractor Adapter (Engine Cross-Shaft) - 2MIT65-45109-22
(3)
Protractor Adapter (Thrust Lever) - F72952-2, F70044-500 or 4MIT65B80307-1
(4)
Fuel Control Unit Idle Rig Pin - F70207-50. Rig pin is part of kit, F70207-3.
(5)
Leading Edge Locks - F-80048
(6)
Copper shield - 1.5 x 2.5 x 0.060 inches
Prepare to Test Takeoff Warning System
(1)
Provide electrical power.
(2)
Provide trailing edge flap system A hydraulic power (Ref\27-51-0\MP or 29-11-0 MP).
(3)
Position stabilizer so position indicator pointer is within one unit of center of green band.
(4)
Place flap control lever at zero UNITS.
(5)
Place speed brake control lever to DOWN.
(6)
Check that LANDING GEAR LIGHTS and AURAL WARNING circuit breakers on panel P6 are closed.
(7)
On airplanes with EPR activated T.O. warn system,
(a)
Check that EPR WARNING, ENG NO. 1 EPR & L.G. WARNING, and ENG NO. 2 EPR & L.G. WARNING circuit breakers on panel P6 are closed.
(b)
Place thrust levers at maximum forward thrust position.
(8)
On airplanes with leading and trailing edge flap position aural warning circuits, check that circuit breakers FLAP POSITION INDICATION LEADING EDGE AC and DC on P6 panel are closed.
(9)
Chock landing gear wheels.
(10)
Release parking brake (airplanes incorporating SB\31-1049).
NOTE: On airplanes with SB 31-1049, the intermittent horn will sound if the parking brake lever has not been released.
On airplanes with SB 31-1073, the aural warning horn will operate if the parking brake is not released.
503
31-26-0 Page 522 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Jun 20/92
D. Test Takeoff Warning System (Airplanes without EPR Activated T/O Warn System)
(1) Test Thrust Lever Actuated Takeoff Warning Switches (S283, S133).
(a) On airplanes not incorporating SB 31-1024 or SB 31-1026, perform the following:
1) At engine fuel control unit, insert fuel control unit idle rig pin in thrust crank to fix thrust crack in idle position (Fig. 503, Sheet 2). Remove rig pin bracket (Fig. 503, Sheet 1).
2) Mount protractor on No. 1 engine cross-shaft hexnut using adapter; then, zero
protractor (Fig. 503, Sheet 1). 3) Remove fuel control unit idle rig pin. 4) Position stabilizer outside green band range. 5) Advance No. 1 thrust lever forward until warning horn sounds. Check that cross-
shaft is within range in table in Fig. 503. 6) Return thrust lever to idle stop, remove protractor with adapter and replace rig
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