(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. Data line 1 displays the trailing edge flap and the leading edge flap positions respectively as follows:
'FLP XX. LE-FLP XX'
(3)
Operate the flap control lever, to set the trailing edge (TE) flaps and leading edge (LE) flaps fully up. Confirm the TE flap position on the TE flap position indicator (left outboard) on the P2 panel and LE flap position (left set 2 and right set 3) on the P4 panel. Verify that the flap position is indicated on CDU data line 1 as follows:
'FLP 00. LE FLP __ __'
NOTE: For trailing edge flap operation refer to (27-51-00,
____ Maintenance Practices). For leading edge flap operation refer to 27-81-00, (Maintenance Practices).
(4) Operate the flap control lever, to move the trailing edge (TE) flaps and leading edge (LE) flaps from fully retracted to fully extended position. At each intermediate flap position the flap indication shall be as follows:
TE LE FLAP PMS CDU DISPLAY LEFT OUTBD INDICATION (P4) PERF DATA.....4/4 PAGE. FLAP LEFT RIGHT DATA LINE 1 INDICATION -2 -3 (P2) GREEN GREEN
_____________________________________________________________
0 OFF OFF FLP 0. LE-FLP - -
1 ON OFF FLP 1. LE-FLP 2 -
5 ON ON FLP 5. LE-FLP 2 3
10 ON ON FLP 10. LE-FLP 2 3
20 ON ON FLP 20. LE-FLP 2 3
25 ON ON FLP 25. LE-FLP 2 3
30 ON ON FLP 30. LE-FLP 2 3
EFFECTIVITY
AIRPLANES WITH PMS 12 Page 536 Apr 25/89
34-62-00
(5)
Retract the trailing edge (TE) flaps and leading edge (LE) flaps to the full up position.
(6)
Press CDU CLEAR key.
(7) If the PMS is no longer required, restore airplane to normal. AD. Landing Gear System 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. With the airplane on the ground, verify that data line 3 displays the word 'GND'.
(3)
Simulate AIR mode by opening GND SAFETY RELAY circuit breaker on the P6 circuit breaker panel. Verify that the word on CDU data line 3 changes from 'GND' to 'AIR'.
NOTE: Before opening circuit breaker for AIR mode simulation,
____ refer to 32-09-02 and observe all necessary safety
precautions.
(4) (5) Close the GND SAFETY RELAY circuit breaker. display returns to 'GND'.Press CDU CLEAR key. Verify that the CDU
(6) If the PMS is no longer required, restore airplane to normal. AE. Auxiliary Fuel Tank System Interface
(1)
If required prepare for test as described in paragraph D.
(2)
To check interface of reserve fuel tanks 2 and 3, on the PMS CDU; press PERF DATA key on CDU, then push slew switch as required to advance the display to PERF DATA.....4/4 page. Verify that PMS CDU display appears as shown below:
NOTE: Fuel gauges for reserve tanks 2 and 3 are on the flight
____ engineer's (P4) panel.
(a)
On airplanes without fuel in reserve tanks 2 and 3, or on airplanes without auxiliary fuel tanks, the left three spaces on CDU data line 2 appear as either:
'AUX', or '310', or '342'.
(b)
On airplanes with fuel in reserve tanks 2 and/or 3, the left three spaces on CDU data line 2 appear as either:
'AUX*', or '310*', or '342*'.
(3) Press CDU CLEAR key.
(4) If the PMS is no longer required restore airplane to normal. AF. Wing Anti-Ice (WAI) System Interface
(1) If required prepare for test as described in paragraph D.
EFFECTIVITY
AIRPLANES WITH PMS 12 Page 537 Apr 25/89
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(2)
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 left part of data line 2 displays the anti-ice system status for engines 1, 2, 3 and 4, and the wing respectively as follows:
(3)
With the WING ANTI-ICE switch, on the P5 panel, in the OFF position verify that the CDU display appears as follows:
'A/I X X X X __'
(4)
Place the WING ANTI-ICE switch to the ON position and verify that the CDU display changes to:
'A/I X X X X W' 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(155)
