X = warning flag showing
____All warning flags show OFF except altimeters which show STBY.
NOTE:
Flag Test Figure 501A
E51677
EFFECTIVITYALL 121,122,157,161,183,184
799 Page 506
34-12-00
Sep 25/94
1) While computer servos are slewing to their normal positions, ALT, M and TAS chassis warning lamps illuminate. The CAS lamp will illuminate momentarily when SELF-TEST switch is released.
2) When normal position is reached, the three lamps extinguish.
3) The indicators (except for the altimeter) slew to their original position and warning flags are out of view.
4) The servo-pneumatic altimeter remains in standby mode.
(15) If CADC No. 2 is a Boeing P/N 60B40126, perform the following tests:
(a)
Set functional test select switch to A/R position; depress button A and hold. All chassis warning lights should illuminate within 6 seconds and then extinguish within a maximum of 130 seconds.
(b)
With button A depressed, check that warning flags are displayed on first officer's altimeter and indicated airspeed/mach indicator; and the SAT indicator.
(c)
With button A depressed, check that first officer's servo-pneumatic altimeter reverts to standby mode, a STBY flag is displayed, and readout reverts to altitude previously set before altitude readout has slewed approximately 550 feet.
(d)
While three chassis warning lights are illuminated, observe that first officer's indicator readout of mach number; and readout of SAT are all slewing.
NOTE: Since warning flags cover above indicator counters,
____ actual readout cannot readily be seen. It is possible, however, to observe that indicator readout is slewing.
(e) Release button A and check that: 1) While computer outputs are slewing to their normal positions, ALT chassis warning light illuminates. 2) When normal position is reached, the light will extinguish. 3) The indicators (except for the altimeter) slew to their
original position and warning flags are out of view. 4) The servo-pneumatic altimeter remains in standby mode.
(16) If CADC No. 2 is a P/N HG480C1 or HG480C2, perform the following test:
(a)
On CADC front panel, set TEST SELECT switch to SLF-TST, depress and hold PUSH-TO-TEST button.
(b)
Check that warning flags are displayed on first officer's servo-pneumatic altimeter and mach/airspeed indicator and the SAT indicator.
(c)
Check that first officer's servo-pneumatic altimeter reverts to the standby mode before the altimeter readout has slewed 550 feet. Altimeter will return to the barometeric altitude noted in step 10.
(d)
Check that first officer's mach/airspeed indicator and the SAT indicator are slewing.
EFFECTIVITY
ALL 39.101 Page 507 Oct 25/98
34-12-00
NOTE: Since warning flags cover above indicator counters,
____ actual readout cannot readily be seen. It is possible, however, to observe that indicator readout is slewing.
(e)
On CADC front panel, check that TEST VALID WHEN LIT light comes on and indicators step slewing within 130 seconds.
(f)
Release the SLF-TST button, TEST VALID WHEN LIT light will go out.
(g)
The first officer's mach/airspeed indicator and the SAT indicator will slew to original values and warning flags will be out of view.
(h)
The first officer's servo-pneumatic altimeter will remain in the standby mode.
(i)
Open the CADC 2 circuit breaker on the P7 Overhead Panel.
(j)
Close the CADC 2 circuit breaker on the P7 Overhead Panel.
(17)
On pilots' and flight engineer's total air temperature indicators, note that OFF flag is not displayed and indicator is reading approximate airfield temperature.
(18)
AF 121, 122, 157, 161, 183, 184; on flight engineer's total air temperature indicator and TAT readout on TAT/N1 indicator, note that OFF flag is not displayed and indicator is reading approximate airfield temperature.
(19)
Remove electrical power if no longer required (Ref 24-22-00).
3. System Test - Central Air Data Computer System and Air Data Pressure
____________________________________________________________________
Instruments
___________
A. General
(1)
The system test, in addition to the operational test, checks that
(l) both temperature sensing systems are accurate for at least one temperature, (2) the air data instruments give accurate readouts of computed and raw air data over a range of data points and in various modes of operation, (3) the pressure transducers in the computers and air data instruments are functioning accurately, and (4) altitude digital encoders in both computers are operating. 中国航空网 www.aero.cn 航空翻译 www.aviation.cn 本文链接地址：747飞机维护手册AMM CHAPTER 34 - NAVIGATION 第34章导航1(66)
