speaker. 3) The >OVERSPEED warning message shows on the main EICAS display. 4) The airspeed and altitude displays begin to increase on the captain's PFD.
(b)
On the applicable PFD make sure you see these conditions: 1) The SPD flag replaces the airspeed display. 2) The ALT flag replaces the altitude display.
(c)
On the applicable PFD, make sure you see these conditions: 1) The airspeed display replaces the SPD flag. 2) The airspeed display moves to 137 knots. 3) The altitude display replaces the ALT flag. 4) The altitude display drives to 10,000 feet.
S 745-205
(2) When the CDU shows "DID THE OVERSPEED AURAL WARNING GO ON AND OFF?", push the applicable LSK for YES or NO.
(a) Look for PASS or FAIL> adjacent to the test prompt.
NOTE: If a PASS indication shows, no failures occurred during
____
the test.
(b)
If FAIL> shows: 1) Push the LSK that is adjacent to FAIL> to see the GROUND TEST MSG pages for the failure. 2) Push the NEXT PAGE key until you find all the GROUND TEST MSG pages. 3) Make a list of all CMCS messages, CMCS message numbers, and ATA numbers that show on the GROUND TEST MSG pages.
4) Go to the CMCS Message Index of the Fault Isolation Manual (FIM) to find the corrective action for each CMCS message.
(c)
Make sure of these conditions on the applicable PFD: 1) No air data system related flags are shown.
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34-12-00
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400 MAINTENANCE MANUAL
2) The altitude display moves to field elevation. 3) The airspeed display shows approximately zero knots.
F. Put the Airplane Back to Its Usual Condition
S 865-125
(1) Remove the DO-NOT-CLOSE tags and close these circuit breakers:
(a) P7 Overhead Circuit Breaker Panel
1) 7C10, FLT CONT ELEC 2L AC
2) 7C12, FLT CONT ELEC 1L AC
3) 7C14, FLT CONT ELEC 1R AC
4) 7C16, FLT CONT ELEC 2R AC
5) 7D05, STICK SHAKER L
6) 7D19, STICK SHAKER R
S 865-206
(2)
Set the GND TESTS switch to the NORM position.
S 865-188
(3)
Remove electrical power if it is not necessary (Ref 24-22-00/201).
TASK 34-12-00-735-020
3. System Test - Air Data System
_____________________________
A. General
(1)
The system test examines the system with external test equipment. Air data system inputs of altitude, airspeed, angle-of-attack (AOA), and total air temperature (TAT) are supplied. System outputs are monitored on displays from the integrated display system (IDS) or an ARINC 429 bus reader.
(2)
These tests do not have to be completed in sequence. Each test can be done one at a time.
(3)
To be accurate, the ambient air temperature must be 25 (|5)°C and the relative humidity must be less than 85% in the main equipment center and on the flight deck. If necessary, use equipment cooling air (Ref 21-58-00/501) and flight deck temperature control (Ref 21-61-00/501) to get these conditions.
B. Standard Tools and Equipment
(1)
AIRPLANES WITH A CONRAK AOA SENSOR;
Angular displacement measuring tool - G34002
(2)
AIRPLANES WITH A ROSEMOUNT AOA SENSOR;
Angular displacement measuring tool - J34002-2
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