(b)
Press PERF DATA key on the PMS CDU. Push the CDU slew switch as required to advance the display to PERF DATA.....2/4 page. The right part of data line 1 indicates the altitude selected (clearance altitude) on the ALT SEL counter (on the A/P-F/D MSP) as:
'CLR XXXXX'
Vary the ALT SEL counter on the A/P-F/D MSP and verify that the CDU display follows the selected altitude within |100 feet. Allow sufficient time for the display on the CDU to stabilize.
(c) Using the pneumatic test unit, simulate the following altitudes on CADC No. 2.
5,000 feet
10,000 feet
20,000 feet
30,000 feet
The right part of data line 2 on the CDU display indicates the actual altitude as:
ALT XXXXX
For each test altitude verify that the CDU display is within |100 feet of the reading on the F/O's altimeter. Allow sufficient time for the display on the CDU to stabilize.
For each test altitude vary the baro set knob on the altimeter to change the altitude reading on the altimeter. Verify that the ALT reading on data line 2 of the CDU display tracks the altimeter reading within |50 feet. Before proceding to the next test altitude, return the altimeter baro set knob to 29.92 inches of mercury.
(4) Mach Number and CAS.
(a)
Push the CDU slew switch as required to display PERF DATA.....1/4 page. The left two spaces on data line 1 indicate CAS and Mach respectively as follows:
'XXX/.XXX'
(b)
Using the pneumatic test unit, simulate on CADC No. 2 the altitude and airspeed given for each following test step.
EFFECTIVITY
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ALTITUDE AIRSPEED
TEST IN IN
STEP____ ________FEET ________KNOTS
1.
5,000 300
2.
10,000 330
3.
20,000 350
4.
30,000 348
For each test step, verify that the CDU display is within 10 knots and .01 mach of the reading on the F/O's mach/airspeed indicator. Allow sufficient time for the display on the CDU to stabilize.
(5)
Press CDU CLEAR key.
(6)
Return the airplane pitot static system to ambient pressure, and disconnect the pneumatic test unit from the airplane pitot static system (Ref 34-11-00).
(7)
Open PMS ADS REF circuit breaker. Within 30 seconds PMS warning must come on. Close circuit breaker. Reset PMS warning and INS malfunction codes.
(8)
Repeat step (7) for CADC-2 PWR circuit breaker.
(9) If the PMS is no longer required, restore airplane to normal. AB. Total Air Temperature (TAT) Probe Interface.
(1)
If required prepare for test as described in paragraph D.
(2)
Press PERF DATA key on the PMS CDU. Push the CDU slew switch as required to advance the display to PERF DATA.....4/4 page. The right three spaces on data line 1 will indicate ASP (or ASP*). ASP indicates a non-aspirated probe; ASP* indicates an aspirated probe. Note the type of probe.
(3)
Push the PMS CDU slew switch as required to display PERF DATA.....1/4 page. The fourth space on data line 1 indicates TAT as follows:
XXX/. XXX +.XXXG |XX. |XX.
(CAS/MACH) (ALONG TRACK TAT SAT ACCEL)
(4)
Observe the TAT display on the CDU, and on the LI. Verify each display is within five degrees centigrade of the TAT reading on the flight engineers (P4 panel) TAT indicator.
(5)
Apply power to heater of left TAT probe, by operating left probe heater switch on probe heater control panel (Ref 30-31-00, Adjustment/Test). The heater control panel is located on the P5 overhead panel.
(6)
Verify that TAT displays on the CDU and LI, each show increasing TAT value.
(7)
Allow the TAT display on the CDU, and on the LI, to increase to between +50.C and +60.C. Verify that the displays are in agreement with each other.
EFFECTIVITY
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(8)
On airplanes with non-aspirated TAT probes, press the T/O DRY key on the PMS LSP, then allow the TAT displays to increase above +60.C. When TAT is above +60.C verify the PMS annunciator on the CDU remains off, and that the TAT displays on the CDU and LI indicate dashes.
(9)
Place the left probe heater switch to OFF. Verify that the CDU and LI displays show decreasing TAT as the probe heater cools.
(10)
Press CDU CLEAR key.
(11) If the PMS is no longer required, restore airplane to normal. AC. Flap System Interface
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本文链接地址：747飞机维护手册AMM CHAPTER 34 - NAVIGATION 第34章导航4(154)
