501
Oct 20/90 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 31-26-0 Page 525
(6) Test autobrake off ramp switch (S585) (Fig. 502), as applicable.
NOTE: If common attachment bolts which secure speed brake takeoff warning switch, arming switch and autobrake off ramp switch were loosened, the autobrake off ramp switch should be tested. If an adjustment was not made to the speed brake takeoff-warning switch this test is not necessary.
(a)
Set speed brake lever to DOWN position.
(b)
Connect ohmmeter across terminals C and NO of switch and check for continuity between switch terminals.
(c)
Move speed brake lever aft until open circuit is obtained between switch terminals.
(d)
Check the speed brake lever is 3.28 to 3.84 inches aft from down and locked position.
(e)
Remove ohmmeter and set speed brake lever to down position.
(7) Test air/ground relay.
(a)
Place flap control lever in 0 detent.
(b)
Advance No. 1 thrust lever until warning horn sounds.
(c)
Actuate the air-sensing switch on the landing gear accessory module on the E3-2 electrical shelf. Check that horn is silenced.
(d)
Release the air-sensing switch. Check the intermittent horn sounds.
(e)
Fully retard the No. 1 thrust lever. Check that horn is silenced.
31-26-0 Oct 20/90
E. Test Takeoff Warning System (Airplanes with SB 31-1033, EPR Activated T/O Warn System)
(1)
Perform Prepare to Test Takeoff Warning System Procedures (par. 6.C.)
(2)
Test EPR Takeoff Warning Circuits (Self-Test Method)
(a)
Press and hold ENGINE No. 1 EPR test switch on the engine accessory module on the E3-2 electrical shelf. Check that the intermittent warning horn sounds and the EITHER EPR greater than 1.4 light on the engine accessory module illuminates.
(b)
Release the test switch. Check that the horn is silenced and the EPR light goes off.
(c)
Repeat steps (a) and (b) using ENGINE NO. 2 EPR test switch.
(d)
Press and hold either EPR test switch while opening and closing each of the following circuit breakers: AURAL WARNING; LANDING GEAR LIGHTS; EPR WARNING. Check that the intermittent horn stops when each circuit breaker is opened and starts when each circuit breaker is closed.
(e)
While pressing either EPR test switch, actuate the air-sensing switch on the landing gear accessory module on the E3-2 electrical shelf. Check that the horn is silenced.
(f)
Release the air-sensing switch. Check that the intermittent horn sounds.
(g)
Release the EPR test switch. Check that the horn is silenced and the EPR light goes off.
(3)
Test EPR Takeoff Warning Circuits (Engines Running Method)
(a)
Place thrust levers at idle stop position.
(b)
AIRPLANES WITH SB 31-1073;
Release the parking brake.
Apply the main landing gear brakes.
(c)
AIRPLANES WITHOUT SB 31-1073;
Set the parking brake.
(d)
Start engines No. 1 and 2 (Ref Chapter 71).
WARNING: OBSERVE ALL GROUND SAFETY PRECAUTIONS TO PREVENT INJURY TO PERSONNEL.
(e)
Slowly advance engine No. 1 thrust lever. Check that intermittnt horn sounds before pilot's EPR indicator reads 1.48 maximum.
(f)
Slowly retard thrust lever. Check that horn is silenced before EPR indicator reads
1.32 minimum.
(g)
Return thrust lever to idle stop.
NOTE: Below approximately -20°F (-29°C), an indicated EPR of 1.48 may be commanded before the thrust lever reaches 13.5 degrees from idle stop, depending on the engine model installed. Under these conditions, the intermittent horn will sound at 13.5 degrees maximum thrust lever travel from idle stop and the indicated EPR may exceed 1.48.
(h)
Repeat steps (e) thru (g) using engine No. 2.
(i)
Shut down engines (Ref Chapter 71).
501
May 01/00 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 31-26-0 Page 527
502
31-26-0 Page 528 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Oct 20/93
NOTE: The remaining tests in par. (4) thru (8) are performed with engines not running.
(4)
Test Thrust Lever Actuated Takeoff Warning Switches (S283, S133).
(a)
Verify both thrust levers are at idle stop.
(b)
Place protractor with adapter on No. 1 thrust lever and set protractor to zero degree (Fig. 501).
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