ILF 101, 151, 156-199, 301, 304, 308, 310, 314, 315, 317-319, 323, 331-399, 402, 405, 424, 425, 427-429, 451, 452,
491-504, 507-510, 512-516, 518-520, 523-528, 530-533, 535-537, 541, 542, 552-557, 559-564, 567-569, 571-577,
581, 583, 585, 588-590, 592-599, 601-603, 606, 607, 610-615, 620, 625-627, 671, 672, 686, 691-699, 703, 707-710,
803-813, 821, 822, 831-838, 841, 842, 851, 852, 854-858, 861-863, 871-874, 947, 948, 968-973, 980-999; ILF 401,
406, 409, 410, 412, 416 POST SB 737-24-1128 (Continued)
(f) Install the cover [3] on the rigid bus assembly so that all of the terminal studs [7] fit
through the holes in the cover [3].
NOTE: Make sure that the bushings [6] are installed between each terminal stud [7] and
the cover [3].
(g) Install the three screws [4] and washers [5] that hold the cover [3].
(h) Tighten the screws [4] to 48 ±2 in-lb (5 ±1 N·m).
(i) Tighten the three screws [12] to 22 ±1 in-lb (2 ±1 N·m).
NOTE: Use the access holes in the cover [3] located just above the terminal studs, to
tighten these screws.
(j) Install the four screws [13] that hold the cover [3] and the retainer [14] together.
(k) Tighten the screws [13] to 11 ±1 in-lb (1 ±0 N·m).
(l) Install the aft two screws and washers that hold the cooling duct assembly to the bottom
of the cover [3]. Tighten all four screws that hold the duct to the rigid bus assembly.
ILF ALL
SUBTASK 24-21-71-420-002
(3) Do the following steps to install the power feeders on the power distribution panel:
(a) Use the identification tags to install the power feeders on the correct terminal studs.
(b) Install the nuts [2] and washers [1] on each terminal stud.
(c) Tighten the nuts to 190 ±10 in-lb (21 ±2 N·m).
NOTE: When you install and tighten the power feeders to the rigid bus assembly, there
may be some axial movement of the terminal studs (particularly TB5004 and
TB5008). A small amount of movement is normal and should not affect the
tightening of the nuts to the specified torque.
ILF 401, 406, 409, 410, 412, 416 PRE SB 737-24-1128
SUBTASK 24-21-71-700-005
CAUTION
THESE SCREWS MUST BE RE-TORQUED WHEN THE FEEDER CABLES
HAVE BEEN REMOVED AND RE-INSTALLED. FAILURE TO DO THIS STEP
CAN CAUSE SEVERE DAMAGE TO THE POWER DISTRIBUTION PANELS.
(4) AIRPLANES WITH OLD RIGID BUS ASSEMBLIES (PRE- SB 24-1128) (PRE - PRR 38317);
do a check of the torque on the six screws [12] that hold the terminal studs to the rigid bus:
NOTE: The old rigid bus assemblies should have a decal on the back that reads:
"CAUTION, ENSURE POWER OFF. AFTER INSTALLATION OF FEEDER CABLES,
LOOSEN 6 SCREWS ONE FULL TURN (ACCESSED THROUGH THE IN COVER).
THEN RE-TORQUE TO 25 ±1 in-lb (3 ±0 N·m) USING A 9/64 IN HEX DRIVER."
NOTE: Do not do re-torque on airplanes with new rigid bus assemblies, (WITH SB24-1128)
(POST PRR 38317).
(a) Access to these screws is gained through six holes above and adjacent to the terminal
studs.
737-600/700/800/900
AIRCRAFT MAINTENANCE MANUAL
24-21-71
Page 415
D633A101-ILF Oct 15/2019
ECCN 9E991 BOEING PROPRIETARY - Copyright © Unpublished Work - See title page for details
EFFECTIVITY
ILF ALL
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