Table II. ~............................................................................... | TABLE II | ................................................................................. | ALTERNATE ELECTRIC MOTOR CURRENT DRAW AND RELAYS CHECK | ................................................................................. | TEST NO. | *[1] | *[2]| RESULT | CORRECTIVE ACTION | .................................................................................
| TEST 1 | B,C,D | AC | 1.5 - 3.5 AMPS | OK - CHECK NEXT RELAY |
| (PHASE | | | (ALL PHASES) | (SEE TABLE I) |
| CHECK | | | OVER 3.5 AMPS | |
| WITH | | | (ANY PHASE) | MEASURE BRAKE CURRENT (TEST 2) |
| MOTOR | | | UNDER 1.5 AMPS | |
| RUNNING)| | | (ANY PHASE) | CHECK RELAY COIL (TEST 3) |
| | | | | |
| TEST 2 | BRAKE | DC | .5 - 1.7 AMPS | REPLACE MOTOR AND REPEAT TEST 1 |
| (MEASURE | | | UNDER .5 OR | |
| BRAKE | | | OVER 1.7 AMPS | REPLACE RELAY AND REPEAT TEST 1 |
| CURRENT)| | | | |
| | | | | |
| TEST 3 | RELAY | DC | 60 - 120 mA | REPLACE MOTOR AND REPEAT TEST 1 |
| (CHECK | COIL | | UNDER 60 OR | |
| RELAY | | | OVER 120 mA | REPLACE RELAY AND REPEAT TEST 1 |
| COIL) | | | | |
...........….......….....…...................…................................... | *[1] TEST BOX SWITCH POSITION | | *[2] AMMETER | 2...............................................................................1
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400 MAINTENANCE MANUAL
H. Put the Airplane Back to its Usual Condition S 865-067
(1)
Remove No. 1 and 4 hydraulic power (Ref 29-11-00/201). S 865-068
(2)
Remove pneumatic power (Ref 36-00-00/201).
S 865-069
(3)
Remove electrical power (Ref 24-22-00/201).
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400 MAINTENANCE MANUAL
KRUEGER FLAPS - REMOVAL/INSTALLATION
____________________________________
1. General_______
A. There are two tasks in this procedure. There is a task for the removal and a task for the installation of the Krueger flaps in the leading edge flap system. The procedure has these parts:
(1)
The installation of the safety locks
(2)
The removal of the folding fairing
(3)
The removal of the Krueger flaps
(4)
The installation of the folding fairing
(5)
The installation of the Krueger flaps.
B.
The three inboard flaps in each wing are the Krueger flaps. Each Krueger flap has an attached folding fairing.
C.
The removal and installation procedure is the same for all the Krueger flaps.
TASK 27-81-01-004-001
2. Krueger Flaps Removal_____________________
A. Special Tools and Equipment
(1)
17MIT65B04017 Leading Edge Flap Drive Unit Lock
(2)
G27013-9 Inboard Krueger Flap No. 11 thru 16 Rigging Set
B.
References
(1)
AMM 24-22-00/201, Manual Control
(2)
AMM 27-81-00/201, Leading Edge Flap System
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