(2)
Provide electrical power (Ref 24-22-00).
(3)
Verify that VHF-1 is tuned to an ILS frequency (Ref 34-31-00).
(4)
Verify that cockpit interphone system is operating (Ref 23-51-00).
(5)
Verify that landing gear selector is in DN position.
(6)
Verify that inboard trailing edge flaps are in 20 degrees.
B. Test System
(1)
Press and hold GROUND PROXIMITY TEST switch for 5 seconds. Check that aural warning consisting of GLIDE SLOPE and WHOOP WHOOP PULL UP occurs. Check that GPWS, GPWS INOP, and BELOW GS indicators illuminate.
(2)
Release test switch. Check that visual and aural warnings go off.
XA (3) ALL EXCEPT AF, IB, AND GN WITH SB 34-2171; Maintain STALL WARNING test switch (P5 panel) on test position while repeating step (1) and check that no visual or aural warning occur. Return stall warning test switch to HTR OFF position.
4. System Test
___________
A. Equipment and Materials
(1)
Pitot-static test set, probe adapter and gages (Ref 34-11-00)
(2)
LRRA Altitude Simulator
(3)
Signal Generator, Collins 479T-2 or equivalent
B. Prepare to test
(1)
Set up pitot-static test set and adapter to captain's pitot-static system (Ref 34-11-00), such that predetermined altitude rates from No. 1 CADC may be obtained (Ref 34-12-00).
(2)
Set up LRRA altitude simulator such that radio altitude from No. 1 LRRA may be set and varied.
(3)
Set up signal generator such that glide slope deviation signals may be set and varied.
EFFECTIVITY
AIRPLANES WITH SUNDSTRAND CONFIG 2 MARK II COMPUTERS ATG Page 501 Apr 25/96
34-46-00
(4)
Ensure that movement of landing gear selector lever will not result in movement of landing gear.
CAUTION:_______ALL LANDING GEAR GROUND LOCKS MUST BE INSTALLED. THERE MUST BE NO PRESSURE ON ANY OF FOUR HYDRAULIC SYSTEMS. NO ATTEMPT SHALL BE MADE TO DISTURB FLAG IN LANDING GEAR HANDLE AND NO ATTEMPT SHALL BE MADE TO MOVE HANDLE INTO UP POSITION.
(5)
Ensure that trailing edge flaps and drive system are correctly installed and rigged, ready for actuation.
CAUTION: ENSURE THAT GROUND EQUIPMENT IS OUT OF FLAP TRAVEL; THAT
_______ ALL PERSONNEL SAFETY PRECAUTIONS AND WARNINGS ARE IN EFFECT.
C. Test System
(1)
Perform Operational Test. Leave power on.
(2)
In-flight Self-Test
(a)
Set landing gear selector to OFF.
(b)
Set inboard trailing edge flaps to 20 degrees.
(c)
Set CADC No. 1 altitude rate to 0 feet per minute, and radio altitude of 1200 feet.
(d)
Press and hold GROUND PROXIMITY TEST switch. Check that GPWS and BELOW G/S indicators come on and WHOOP WHOOP PULL UP aural warning repeats until the test switch is released.
(3)
Test Take Off Descent Warning
NOTE: GPWS visual and aural indications referred to as GPWS
____
warning from here on.
(a)
Using radio altimeter test set, simulate a 0 feet radio altitude (for a minimum of 2 seconds).
(b)
Using pitot static test set, set an altitude such that a descent rate of 300 feet per minute may be maintained.
(c)
Verify that landing gear selector is set at OFF position.
(d)
Verify that inboard trailing edge flaps are set at 20 degrees.
(e)
Verify that VHF NAV No. 1 is tuned to a VOR frequency.
(f)
Set radio altitude to 200 feet.
(g)
Simulate a barometric altitude sink rate of 300 feet per minute. Check that GPWS indicator illuminates and DONT SINK aural warning is actuated following a delay of approximately 5 seconds.
(h)
Return barometric sink rate to 0 feet per minute. Check that warnings go off.
(i)
Reset barometric sink rate to 300 feet per minute. Check that warnings are reactivated.
(j)
Increase radio altitude to 1200 feet. Check that warnings go off within 3 seconds.
(4) Test Terrain Clearance
EFFECTIVITY
中國航空網 www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：747飛機維護手冊AMM CHAPTER 34 - NAVIGATION 第34章導航4(51)
