C

AIRCRAFT MAINTENANCE MANUAL

FUEL
LIST OF EFFECTIVE PAGES

Chapter Chapter
Section Section
Subject Config Page Date Subject Config Page Date
28 − Effective 1 * Dec 10/2005 28−00−00 201 Apr 20/2004
Pages 202 Apr 20/2004
2 * Dec 10/2005 203 Aug 10/2005
3 * Dec 10/2005
4 * Dec 10/2005
28−00−00 501 Apr 20/2004
5 * Dec 10/2005
502 * Dec 10/2005
6 * Dec 10/2005
503 Apr 20/2004
7 Aug 10/2005
504 Apr 20/2004
8 * Dec 10/2005
505 Apr 20/2004
9 * Dec 10/2005
506 Apr 20/2004
10 * Dec 10/2005
507 Apr 20/2004
11 * Dec 10/2005
508 Apr 20/2004

28 − Contents 1 Apr 20/2004

28−00−00 601 Jun 22/2004
2 Apr 20/2004
602 Jun 22/2004
3 Aug 10/2005
603 Apr 20/2004
4 Aug 10/2005
604 Apr 20/2004
5 Aug 10/2005
605 Aug 10/2005
6 Aug 10/2005
606 Aug 10/2005
7 * Dec 10/2005
607 Dec 15/2004
8 Aug 10/2005
608 Aug 10/2005
9 Aug 10/2005
609 Dec 15/2004
10 Aug 10/2005
610 Apr 20/2004
11 Aug 10/2005
12 Aug 10/2005
13 Aug 10/2005 28−10−00 1 Apr 20/2004
14 Aug 10/2005 2 Apr 20/2004
15 Aug 10/2005 3 Apr 20/2004
16 Aug 10/2005
17 Aug 10/2005 28−11−00 1 Apr 20/2004
18 Aug 10/2005 2 Apr 20/2004
19 Aug 10/2005 3 Apr 20/2004
20 Aug 10/2005 4 Apr 20/2004
21 Aug 10/2005 5 Apr 20/2004
22 Aug 10/2005 6 Apr 20/2004
23 Aug 10/2005 7 Apr 20/2004
24 Aug 10/2005 8 Apr 20/2004
25 Aug 10/2005 9 Apr 20/2004
26 Aug 10/2005 10 Apr 20/2004
27 Aug 10/2005 11 Apr 20/2004

28−00−00 1 Apr 20/2004

Master
EFFECTIVITY: ALL
28−Effective Page 1
Pages Dec 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL

Chapter Chapter
Section Section
Subject Config Page Date Subject Config Page Date
28−11−00 201 Mar 15/2005 630 Aug 10/2005
202 Apr 20/2004 631 Aug 10/2005
203 * Dec 10/2005 632 Aug 10/2005
204 Aug 10/2005 633 Aug 10/2005
205 Aug 10/2005 634 Aug 10/2005
206 * Dec 10/2005 635 Aug 10/2005
207 Mar 15/2005 636 Aug 10/2005
208 Mar 15/2005 637 Aug 10/2005
209 * Dec 10/2005 638 Aug 10/2005
210 * Dec 10/2005 639 Aug 10/2005
211 * Dec 10/2005 640 Aug 10/2005
212 * Dec 10/2005 641 Aug 10/2005
213 * Dec 10/2005 642 Aug 10/2005
214 * Dec 10/2005
28−11−00 801 Apr 20/2004
28−11−00 601 Dec 15/2004
602 Aug 10/2005
28−11−01 401 Apr 20/2004
603 Dec 15/2004
402 * Dec 10/2005
604 Dec 15/2004
403 * Dec 10/2005
605 Aug 10/2005
404 Apr 20/2004
606 * Dec 10/2005
405 Mar 15/2005
607 * Dec 10/2005
406 Mar 15/2005
608 * Dec 10/2005
407 * Dec 10/2005
609 Aug 10/2005
408 * Dec 10/2005
610 Aug 10/2005
409 Apr 20/2004
611 Aug 10/2005
410 * Dec 10/2005
612 Aug 10/2005
411 * Dec 10/2005
613 Aug 10/2005
412 Apr 20/2004
614 Aug 10/2005
413 Apr 20/2004
615 Aug 10/2005
414 * Dec 10/2005
616 Aug 10/2005
415 * Dec 10/2005
617 Aug 10/2005
416 * Dec 10/2005
618 Aug 10/2005
417 * Dec 10/2005
619 Aug 10/2005
418 * Dec 10/2005
620 Aug 10/2005
419 * Dec 10/2005
621 Aug 10/2005
622 Aug 10/2005
623 Aug 10/2005 28−11−01 601 Dec 15/2004
624 Aug 10/2005 602 Dec 15/2004
625 Aug 10/2005 603 Apr 20/2004
626 Aug 10/2005 604 Apr 20/2004
627 Aug 10/2005 605 Apr 20/2004
628 Aug 10/2005 606 Apr 20/2004
629 Aug 10/2005

Master
EFFECTIVITY: ALL
28−Effective Page 2
Pages Dec 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL

Chapter Chapter
Section Section
Subject Config Page Date Subject Config Page Date
607 Aug 10/2005 404 Apr 20/2004
608 Aug 10/2005 405 Apr 20/2004
406 Apr 20/2004
407 Apr 20/2004
28−11−01 801 Apr 20/2004
408 Apr 20/2004
802 Apr 20/2004
409 Apr 20/2004
803 Apr 20/2004
410 Apr 20/2004
804 Apr 20/2004
411 Apr 20/2004
412 Apr 20/2004
28−11−03 401 Sep 10/2004 413 Apr 20/2004
402 Sep 10/2004 414 Apr 20/2004
403 Sep 10/2004 415 Apr 20/2004
404 Apr 20/2004
405 Apr 20/2004
28−11−14 401 Apr 20/2004
406 Sep 10/2004
402 Apr 20/2004
407 Sep 10/2004
403 Apr 20/2004
408 Sep 10/2004
404 Apr 20/2004
409 Jun 22/2004
405 Apr 20/2004

28−11−05 401 Apr 20/2004

28−11−17 401 Apr 20/2004
402 Apr 20/2004
402 Apr 20/2004
403 Apr 20/2004
403 Apr 20/2004
404 Apr 20/2004
404 Dec 15/2004
405 Apr 20/2004
405 Dec 15/2004
406 Apr 20/2004
28−11−05 501 Aug 10/2005
502 Apr 20/2004
28−11−17 601 Apr 20/2004
503 Aug 10/2005
602 Apr 20/2004
504 Aug 10/2005

28−12−00 1 * Dec 10/2005

28−11−07 401 Apr 20/2004
2 * Dec 10/2005
402 Apr 20/2004
3 * Dec 10/2005
403 Apr 20/2004
4 * Dec 10/2005
404 Apr 20/2004
5 * Dec 10/2005
405 Apr 20/2004
6 Apr 20/2004
7 Apr 20/2004
28−11−13 201 Apr 20/2004 8 Apr 20/2004
202 Apr 20/2004 9 Apr 20/2004
203 Apr 20/2004 10 Apr 20/2004

28−11−13 401 Apr 20/2004

402 Apr 20/2004
403 Apr 20/2004

Master
EFFECTIVITY: ALL
28−Effective Page 3
Pages Dec 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL

Chapter Chapter
Section Section
Subject Config Page Date Subject Config Page Date
28−12−01 401 Apr 20/2004 28−13−00 1 Apr 20/2004
402 Apr 20/2004 2 Apr 20/2004
403 Apr 20/2004 3 Apr 20/2004
404 Apr 20/2004 4 Apr 20/2004
405 Apr 20/2004 5 Apr 20/2004
6 Apr 20/2004
28−12−01 501 Apr 20/2004 7 Apr 20/2004
8 Apr 20/2004
9 Apr 20/2004
28−12−02 401 Sep 10/2004 10 Apr 20/2004
402 Sep 10/2004 11 Apr 20/2004
403 Apr 20/2004 12 Apr 20/2004
404 Sep 10/2004 13 Apr 20/2004
405 Sep 10/2004
28−13−00 501 Sep 10/2004
28−12−02 501 Apr 20/2004 502 Sep 10/2004
503 Sep 10/2004
28−12−04 401 Apr 20/2004
402 * Dec 10/2005 28−13−01 401 Sep 10/2004
403 Apr 20/2004 402 Sep 10/2004
404 Apr 20/2004 403 Apr 20/2004
405 Apr 20/2004 404 Sep 10/2004
406 Apr 20/2004 405 Sep 10/2004
407 * Dec 10/2005
408 * Dec 10/2005
409 * Dec 10/2005 28−13−01 501 Apr 20/2004
502 Apr 20/2004

28−12−06 401 * Dec 10/2005

28−13−16 401 Mar 15/2005
402 * Dec 10/2005
402 Mar 15/2005
403 * Dec 10/2005
403 * Dec 10/2005
404 Sep 10/2004
404 Mar 15/2005
405 Apr 20/2004
405 Mar 15/2005
406 Apr 20/2004
406 Mar 15/2005
407 Apr 20/2004
408 Sep 10/2004 407 * Dec 10/2005
408 Mar 15/2005
409 * Dec 10/2005
409 * Dec 10/2005
410 * Dec 10/2005
410 Mar 15/2005
411 * Dec 10/2005
411 Mar 15/2005
412 Mar 15/2005
28−12−10 501 Mar 15/2005 413 Mar 15/2005
502 Mar 15/2005 414 Mar 15/2005
503 Mar 15/2005 415 Mar 15/2005
504 Apr 20/2004 416 Mar 15/2005

Master
EFFECTIVITY: ALL
28−Effective Page 4
Pages Dec 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL

Chapter Chapter
Section Section
Subject Config Page Date Subject Config Page Date
28−13−16 501 Apr 20/2004 28−13−43 501 * Dec 10/2005
502 Apr 20/2004 502 * Dec 10/2005
503 * Dec 10/2005
28−13−19 401 Apr 20/2004
402 Apr 20/2004 28−13−45 401 Apr 20/2004
403 Apr 20/2004 402 Apr 20/2004
404 Apr 20/2004 403 * Dec 10/2005
405 Apr 20/2004 404 Apr 20/2004
405 Apr 20/2004
406 Aug 10/2005
28−13−22 401 Sep 10/2004
407 Aug 10/2005
402 Sep 10/2004
408 * Dec 10/2005
403 Apr 20/2004
409 Aug 10/2005
404 Aug 10/2005
405 Aug 10/2005
28−13−45 501 Apr 20/2004
28−13−22 501 Apr 20/2004 502 Apr 20/2004
502 Apr 20/2004
28−20−00 1 Apr 20/2004
2 Apr 20/2004
28−13−28 401 Sep 10/2004
3 Apr 20/2004
402 Sep 10/2004
4 Apr 20/2004
403 Apr 20/2004
404 Sep 10/2004
405 Sep 10/2004 28−20−01 401 Sep 10/2004
402 Apr 20/2004
403 Aug 10/2005
28−13−31 401 Apr 20/2004
404 Sep 10/2004
402 Apr 20/2004
405 Sep 10/2004
403 Apr 20/2004
406 Sep 10/2004
404 Apr 20/2004
407 * Dec 10/2005
405 Apr 20/2004
408 * Dec 10/2005
409 Aug 10/2005
28−13−43 401 Apr 20/2004 410 Aug 10/2005
402 * Dec 10/2005 411 * Dec 10/2005
403 * Dec 10/2005 412 Apr 20/2004
404 Dec 15/2004 413 Apr 20/2004
405 Apr 20/2004 414 Apr 20/2004
406 Apr 20/2004 415 Apr 20/2004
407 * Dec 10/2005 416 Apr 20/2004
408 Aug 10/2005 417 Aug 10/2005
409 * Dec 10/2005 418 Aug 10/2005
410 * Dec 10/2005 419 Aug 10/2005
411 Aug 10/2005 420 Aug 10/2005
421 Aug 10/2005

Master
EFFECTIVITY: ALL
28−Effective Page 5
Pages Dec 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL

Chapter Chapter
Section Section
Subject Config Page Date Subject Config Page Date
422 Aug 10/2005 521 Apr 20/2004
423 Aug 10/2005 522 Apr 20/2004
424 Aug 10/2005
425 * Dec 10/2005
28−20−05 401 Apr 20/2004
426 Aug 10/2005
402 * Dec 10/2005
427 * Dec 10/2005
403 Apr 20/2004
428 Aug 10/2005
404 Apr 20/2004
429 * Dec 10/2005
405 Apr 20/2004
430 Aug 10/2005
406 * Dec 10/2005
431 Aug 10/2005
407 Apr 20/2004
432 Aug 10/2005
433 Aug 10/2005
434 Aug 10/2005 28−21−00 1 Apr 20/2004
435 Aug 10/2005 2 Apr 20/2004
436 Aug 10/2005 3 Apr 20/2004
437 Aug 10/2005 4 Apr 20/2004
438 Aug 10/2005 5 Apr 20/2004
439 Aug 10/2005
440 Aug 10/2005 28−21−00 501 Dec 15/2004
441 Aug 10/2005 502 Dec 15/2004
442 Aug 10/2005 503 Dec 15/2004
443 Aug 10/2005

28−21−01 401 Apr 20/2004

28−20−01 501 Apr 20/2004 402 Apr 20/2004
502 Apr 20/2004 403 Apr 20/2004
503 Apr 20/2004 404 Apr 20/2004
504 Apr 20/2004 405 Apr 20/2004
505 Apr 20/2004
506 Apr 20/2004
507 Apr 20/2004 28−21−01 501 Apr 20/2004
508 Apr 20/2004 502 Apr 20/2004
509 Apr 20/2004
510 Apr 20/2004 28−21−04 401 Apr 20/2004
511 Apr 20/2004 402 Apr 20/2004
512 Apr 20/2004 403 Apr 20/2004
513 Apr 20/2004 404 Apr 20/2004
514 Apr 20/2004 405 Apr 20/2004
515 Apr 20/2004 406 Apr 20/2004
516 Apr 20/2004
517 Apr 20/2004
28−21−04 501 Apr 20/2004
518 Apr 20/2004
502 Apr 20/2004
519 Apr 20/2004
503 Apr 20/2004
520 Apr 20/2004

Master
EFFECTIVITY: ALL
28−Effective Page 6
Pages Dec 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL

Chapter Chapter
Section Section
Subject Config Page Date Subject Config Page Date
28−21−07 401 Apr 20/2004 28−22−00 1 Apr 20/2004
402 Apr 20/2004 2 Apr 20/2004
403 Apr 20/2004 3 Apr 20/2004
404 Apr 20/2004 4 Apr 20/2004
405 Apr 20/2004 5 Apr 20/2004
406 Apr 20/2004
407 Apr 20/2004
28−22−01 401 Apr 20/2004
408 Apr 20/2004
402 Apr 20/2004
409 Apr 20/2004
403 Apr 20/2004
410 Apr 20/2004
404 Apr 20/2004
405 Apr 20/2004
28−21−07 501 Apr 20/2004
502 Apr 20/2004
28−22−04 401 Apr 20/2004
503 Apr 20/2004
402 Apr 20/2004
504 Apr 20/2004
403 Apr 20/2004
505 Apr 20/2004
404 Apr 20/2004
506 Apr 20/2004
405 Apr 20/2004
507 Apr 20/2004
508 Apr 20/2004
28−22−07 401 Apr 20/2004
402 Apr 20/2004
28−21−13 401 Sep 10/2004
403 Apr 20/2004
402 Sep 10/2004
404 Apr 20/2004
403 Sep 10/2004
405 Apr 20/2004
404 Sep 10/2004
405 Apr 20/2004
406 Apr 20/2004 28−22−09 401 Apr 20/2004
407 Apr 20/2004 402 Apr 20/2004
408 Sep 10/2004 403 Apr 20/2004
409 Sep 10/2004 404 Apr 20/2004
410 Sep 10/2004 405 Apr 20/2004
411 Sep 10/2004
412 Sep 10/2004 28−22−09 501 Apr 20/2004
413 Sep 10/2004 502 Apr 20/2004
503 Apr 20/2004
28−21−13 501 Apr 20/2004 504 Apr 20/2004
502 Apr 20/2004
503 Apr 20/2004 28−22−11 501 Apr 20/2004
504 Apr 20/2004 502 Apr 20/2004
505 Apr 20/2004 503 Apr 20/2004
506 Apr 20/2004 504 Apr 20/2004
507 Apr 20/2004

Master
EFFECTIVITY: ALL
28−Effective Page 7
Pages Aug 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL

Chapter Chapter
Section Section
Subject Config Page Date Subject Config Page Date
28−23−00 1 Apr 20/2004 28−23−07 401 Sep 10/2004
2 Apr 20/2004 402 Sep 10/2004
3 Apr 20/2004 403 Sep 10/2004
4 Apr 20/2004 404 Apr 20/2004
5 Apr 20/2004 405 Apr 20/2004
6 Apr 20/2004 406 Sep 10/2004
7 Apr 20/2004 407 Sep 10/2004
408 Sep 10/2004
28−23−01 401 Apr 20/2004
402 Apr 20/2004 28−23−07 501 Apr 20/2004
403 Apr 20/2004 502 Jun 22/2004
404 Apr 20/2004 503 Apr 20/2004
405 Apr 20/2004
28−24−00 1 Apr 20/2004
28−23−01 501 Apr 20/2004 2 Apr 20/2004
502 Apr 20/2004 3 Apr 20/2004
4 Apr 20/2004
5 Apr 20/2004
28−23−03 401 Apr 20/2004
6 Apr 20/2004
402 Dec 15/2004
403 Dec 15/2004
404 * Dec 10/2005 28−24−01 401 Sep 10/2004
405 Dec 15/2004 402 Sep 10/2004
406 Dec 15/2004 403 Apr 20/2004
407 Dec 15/2004 404 Jun 22/2004
408 Dec 15/2004 405 Jun 22/2004
409 Aug 10/2005 406 Apr 20/2004
410 * Dec 10/2005 407 Apr 20/2004
411 Mar 15/2005 408 Apr 20/2004
412 Aug 10/2005 409 Jun 22/2004
413 Aug 10/2005 410 Jun 22/2004
414 Aug 10/2005 411 Apr 20/2004
415 Aug 10/2005
416 * Dec 10/2005
28−24−01 501 Apr 20/2004
417 Aug 10/2005
418 Mar 15/2005
419 Mar 15/2005 28−24−07 401 Apr 20/2004
402 Apr 20/2004
403 Apr 20/2004
28−23−04 401 Apr 20/2004
404 Apr 20/2004
402 Apr 20/2004
405 Apr 20/2004
403 Apr 20/2004
404 Apr 20/2004
405 Apr 20/2004

Master
EFFECTIVITY: ALL
28−Effective Page 8
Pages Dec 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL

Chapter Chapter
Section Section
Subject Config Page Date Subject Config Page Date
28−24−10 401 Apr 20/2004 604 Apr 20/2004
402 Apr 20/2004 605 Apr 20/2004
403 Apr 20/2004
404 Apr 20/2004
28−25−00 1 * Dec 10/2005
2 * Dec 10/2005
28−24−23 401 Apr 20/2004 3 * Dec 10/2005
402 Apr 20/2004 4 * Dec 10/2005
403 Apr 20/2004 5 Apr 20/2004
404 Apr 20/2004 6 Apr 20/2004
405 Apr 20/2004 7 Apr 20/2004
406 Apr 20/2004 8 * Dec 10/2005
407 Apr 20/2004 9 * Dec 10/2005
10 Apr 20/2004
11 Apr 20/2004
28−24−23 501 Apr 20/2004
12 Apr 20/2004
502 Apr 20/2004
13 Apr 20/2004
503 Apr 20/2004
504 Apr 20/2004 14 Apr 20/2004
15 Apr 20/2004
505 Apr 20/2004
16 Apr 20/2004

28−24−25 401 Apr 20/2004

28−25−00 501 Apr 20/2004
402 Apr 20/2004
502 * Dec 10/2005
403 Apr 20/2004
503 * Dec 10/2005
404 Apr 20/2004
504 * Dec 10/2005
405 Apr 20/2004
505 * Dec 10/2005
406 Apr 20/2004
407 Apr 20/2004 506 * Dec 10/2005
507 * Dec 10/2005
408 Apr 20/2004
508 Apr 20/2004
409 Apr 20/2004
509 Apr 20/2004
410 Apr 20/2004

28−25−01 401 Sep 10/2004

28−24−25 501 Apr 20/2004
402 * Dec 10/2005
502 Apr 20/2004
403 Sep 10/2004
503 Apr 20/2004
404 Apr 20/2004
504 Apr 20/2004
505 Apr 20/2004 405 Sep 10/2004
506 Apr 20/2004 406 * Dec 10/2005
407 Sep 10/2004
507 Apr 20/2004

28−25−04 401 Sep 10/2004

28−24−25 601 Apr 20/2004
402 Sep 10/2004
602 Apr 20/2004
403 Sep 10/2004
603 Apr 20/2004
404 Apr 20/2004

Master
EFFECTIVITY: ALL
28−Effective Page 9
Pages Dec 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL

Chapter Chapter
Section Section
Subject Config Page Date Subject Config Page Date
405 Sep 10/2004 28−40−00 1 Apr 20/2004
406 Sep 10/2004 2 Apr 20/2004
3 Apr 20/2004
28−25−07 401 Aug 10/2005
402 Apr 20/2004 28−41−00 1 Apr 20/2004
403 * Dec 10/2005 2 Apr 20/2004
404 * Dec 10/2005 3 Apr 20/2004
405 Aug 10/2005 4 Apr 20/2004
406 Aug 10/2005 5 Apr 20/2004
407 * Dec 10/2005 6 Apr 20/2004
408 * Dec 10/2005 7 Apr 20/2004
409 * Dec 10/2005
410 * Dec 10/2005
28−41−04 401 Apr 20/2004
411 Aug 10/2005
402 Apr 20/2004
403 * Dec 10/2005
28−25−13 401 Apr 20/2004 404 Apr 20/2004
402 * Dec 10/2005 405 Apr 20/2004
403 Apr 20/2004 406 * Dec 10/2005
404 Apr 20/2004 407 Apr 20/2004
405 Apr 20/2004
406 * Dec 10/2005
28−41−04 501 Apr 20/2004
407 Apr 20/2004
502 Apr 20/2004
503 Mar 15/2005
28−25−16 401 * Dec 10/2005 504 Mar 15/2005
402 Apr 20/2004 505 Apr 20/2004
403 Apr 20/2004
404 Apr 20/2004
28−41−10 401 Apr 20/2004
405 * Dec 10/2005
402 Apr 20/2004
406 * Dec 10/2005
403 Apr 20/2004
407 * Dec 10/2005
404 Apr 20/2004
408 Apr 20/2004
405 Apr 20/2004
409 Sep 10/2004
410 * Dec 10/2005
28−41−16 401 Apr 20/2004
402 * Dec 10/2005
28−31−01 401 Apr 20/2004
403 Apr 20/2004
402 Apr 20/2004
404 Apr 20/2004
403 Apr 20/2004
405 * Dec 10/2005
404 Apr 20/2004
405 Apr 20/2004
28−41−16 501 Apr 20/2004
502 Sep 10/2004
503 Apr 20/2004
504 Apr 20/2004

Master
EFFECTIVITY: ALL
28−Effective Page 10
Pages Dec 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL

Chapter Chapter
Section Section
Subject Config Page Date Subject Config Page Date
505 Apr 20/2004 28−42−07 401 * Dec 10/2005
506 Apr 20/2004 402 Apr 20/2004
403 Apr 20/2004
404 Apr 20/2004
28−41−17 401 Apr 20/2004
405 Apr 20/2004
402 Apr 20/2004
403 Apr 20/2004
404 Apr 20/2004 28−42−10 401 Apr 20/2004
405 Apr 20/2004 402 * Dec 10/2005
403 Apr 20/2004
404 Apr 20/2004
28−41−19 401 Apr 20/2004
405 Apr 20/2004
402 * Dec 10/2005
406 * Dec 10/2005
403 Apr 20/2004
407 Apr 20/2004
404 Apr 20/2004
405 Apr 20/2004
406 * Dec 10/2005 28−42−15 401 Apr 20/2004
402 * Dec 10/2005
403 Apr 20/2004
28−41−23 401 * Dec 10/2005
404 Apr 20/2004
402 * Dec 10/2005
405 * Dec 10/2005
403 Apr 20/2004
404 Apr 20/2004
405 * Dec 10/2005 28−42−15 501 Apr 20/2004
406 * Dec 10/2005 502 Dec 15/2004
407 Apr 20/2004 503 Apr 20/2004
504 Dec 15/2004
28−42−00 1 Mar 15/2005
2 Apr 20/2004
3 Mar 15/2005
4 Apr 20/2004
5 Apr 20/2004
6 Apr 20/2004

28−42−01 401 Apr 20/2004

402 Apr 20/2004
403 Apr 20/2004
404 Apr 20/2004
405 Apr 20/2004

28−42−04 401 Apr 20/2004

402 Apr 20/2004
403 Apr 20/2004
404 Apr 20/2004
405 Apr 20/2004

Master
EFFECTIVITY: ALL
28−Effective Page 11
Pages Dec 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
FUEL
TABLE OF CONTENTS

Chapter
Section
Subject Subject Page

FUEL SYSTEM 28−00−00

Description and Operation 1
Effectivity: ON A/C ALL
General
Description
Storage System
Distribution System
Indicating System
Maintenance Practices 201
Effectivity: ON A/C ALL
General
Fuel Safety Precautions
Adjustment/Test 501
Effectivity: ON A/C ALL
General
Operational Test of the Fuel System
Inspection/Check 601
Effectivity: ON A/C ALL
General
Contamination Check of the Fuel System
Components (Water)
Contamination Check of the Fuel System 603
Components (Hydraulic Fluid)

STORAGE SYSTEM 28−10−00

Description and Operation 1
Effectivity: ON A/C ALL
General
Description
Fuel Tank System

Master
EFFECTIVITY: ALL
28−Contents Page 1
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
Chapter
Section
Subject Subject Page

Vent System
Transfer System
Operation
Fuel Tank System
Vent System
Transfer System 2

FUEL TANK SYSTEM 28−11−00

Description and Operation 1
Effectivity: ON A/C ALL
General
Component Details
Main Tank
Center Tank
Wing−Tank Gravity Filler−Cap 2
Center−Tank Gravity Filler−Cap
Wing−Tank Adapter Assembly
Center−Tank Adapter Assembly
Collector Tank
Collector−Tank Check Valve 3
Fuel−Tank Access Panel
Balancing Pipe
One−Way Flow Valve
Restrictor
Fuel Drain Valve 4
Water Drain Valve
Operation
Component Location Index 5
Maintenance Practices 201
Effectivity: ON A/C ALL
General
Prepare Fuel Tank for Access

Master
EFFECTIVITY: ALL
28−Contents Page 2
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
Chapter
Section
Subject Subject Page

Removal of Fuel Fumes 207

Biocide Treatment of the Fuel Tanks 209
Inspection/Check 601
Effectivity: ON A/C ALL
General
Visual Check of the Fuel Tank Exterior
General Visual Inspection of the Fuel Access 602
Panels and the Fuel and Water Drain Valves
Detailed Inspection of the Sealant on In−Tank 605
LRUs
Functional Check of the Critical Bonding Jumpers 625
Detailed Inspection of the Critical Bonding 629
Jumpers
Pressurization of the Fuel Tanks Using Shop Air 633
Leak Rate Check of the Fuel Tank 639
Repairs 801
Effectivity: ON A/C ALL
Fuel−Tanks Seal Repair

PANEL, FUEL TANK ACCESS 28−11−01

Removal/Installation 401
Effectivity: ON A/C ALL
General
Removal of the Honeycomb Access Panel
Installation of the Honeycomb Access Panel 405
Removal of the Aluminum Access Panel 409
Installation of the Aluminum Access Panel 414
Inspection/Check 601
Effectivity: ON A/C ALL
General
Damage Check of the Honeycomb Access Panel
Damage Check of the Aluminum Access Panel 604

Master
EFFECTIVITY: ALL
28−Contents Page 3
Aug 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
Chapter
Section
Subject Subject Page

Detailed Inspection of the Fuel Access−Panels 607

and the Fuel and Water Drain Valves and
Fasteners
Repairs 801
Effectivity: ON A/C ALL
General
Repair of the Fuel−Resistant Coating
Replacement of the Phenolic Strip 803

TANK, COLLECTOR 28−11−03

Removal/Installation 401
Effectivity: ON A/C ALL
General
Removal of the Collector Tank
Installation of the Collector Tank 406

CHECK VALVE, COLLECTOR TANK 28−11−05

Removal/Installation 401
Effectivity: ON A/C ALL
General
Removal of the Collector Tank Check Valve
Installation of the Collector Tank Check Valve 404
Adjustment/Test 501
Effectivity: ON A/C ALL
General
Functional Test of the Collector Tank Check Valve

VALVE, ONE−WAY FLOW 28−11−07

Removal/Installation 401
Effectivity: ON A/C ALL
General

Master
EFFECTIVITY: ALL
28−Contents Page 4
Aug 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
Chapter
Section
Subject Subject Page

Removal of the One−Way Flow Valve

Installation of the One−Way Flow Valve 404

VALVE, WATER DRAIN 28−11−13

Maintenance Practices 201
Effectivity: ON A/C ALL
General
Replacement of the Preformed Packing
Removal/Installation 401
Effectivity: ON A/C ALL
General
Removal of the Water Drain Valve
Installation of the Water Drain Valve 404
Removal of the Water Drain Housing 406
Installation of the Water Drain Housing 412

VALVE, FUEL DRAIN 28−11−14

Removal/Installation 401
Effectivity: ON A/C ALL
General
Removal of the Fuel Drain Valve
Installation of the Fuel Drain Valve 404

FILLER CAP, GRAVITY FUEL FEED, CENTER TANK 28−11−17

Removal/Installation 401
Effectivity: ON A/C ALL
General
Removal of the Center−Tank Gravity−Fuel−Feed−
Filler Installation
Installation of the Center−Tank Gravity−Fuel− 404
Feed−Filler Installation

Master
EFFECTIVITY: ALL
28−Contents Page 5
Aug 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
Chapter
Section
Subject Subject Page

Inspection/Check 601
Effectivity: ON A/C ALL
General
Visual Check of the Fuel Filler−Cap "O" Ring

VENT SYSTEM 28−12−00

Description and Operation 1
Effectivity: ON A/C ALL
General
Component Details
Main−Tank Relief Valve 2
Center−Tank Relief Valve
Vent−Line−Purge Check Valve
Vent−Flapper Check Valve
Vent Line Tubing 3
Vent Line Shrouds
Operation
Operation 4
Component Location Index

VALVE, MAIN TANK RELIEF 28−12−01

Removal/Installation 401
Effectivity: ON A/C ALL
General
Removal of the Main Tank Relief Valve
Installation of the Main Tank Relief Valve 404
Adjustment/Test 501
Effectivity: ON A/C ALL
General
Operational Test of the Main Tank Relief Valve

Master
EFFECTIVITY: ALL
28−Contents Page 6
Aug 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
Chapter
Section
Subject Subject Page

VALVE, CENTER TANK RELIEF 28−12−02

Removal/Installation 401
Effectivity: ON A/C ALL
General
Removal of the Center Tank Relief Valve
Installation of the Center Tank Relief Valve 404
Adjustment/Test 501
Effectivity: ON A/C ALL
General
Operational Test of the Center−Tank Relief Valve

CHECK VALVE, VENT LINE PURGE 28−12−04

Removal/Installation 401
Effectivity: ON A/C ALL
General
Removal of the Vent−Line−Purge Check Valve
Installation of the Vent−Line−Purge Check Valve 407

VALVE, VENT LINE, FLAPPER CHECK 28−12−06

Removal/Installation 401
Effectivity: ON A/C 7003−7007, 7009−7010, 7015−7016,
7019−7021, 7023−7025, 7036, 7045, 7047, 7049, 7051,
7053−7054, 7057−7060, 7064−7065, 7071, 7073−7074, 7078,
7081−7084, 7086−7087, 7089−7090, 7093, 7095−7098, 7104,
7107, 7110−7990, 8000−8064, 8066−8068 and ON A/C 7008,
7011−7014, 7017−7018, 7022, 7026−7035, 7037−7044, 7046,
7048, 7050, 7052, 7055−7056, 7061−7063, 7066−7067,
7069−7070, 7072, 7075−7077, 7079−7080, 7085, 7088,
7091−7092, 7094, 7099−7103, 7105−7106, 7108−7109 Post
SB601R−28−024
General
Removal of the Flapper Valve
Installation of the Flapper Valve 408

Master
EFFECTIVITY: ALL
28−Contents Page 7
Dec 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
Chapter
Section
Subject Subject Page

FUEL TANK VENT AND FUEL LINE SHROUDS 28−12−10

Adjustment/Test 501
Effectivity: ON A/C ALL
General
Pressure Leak Test of the Fuel Tank Vent and
Fuel Line Shrouds

TRANSFER SYSTEM 28−13−00

Description and Operation 1
Effectivity: ON A/C ALL
General
Component Details
Transfer Ejector Pump
Transfer Ejector Screen
Aft Scavenge−Ejector Pump 2
Scavenge Ejector Screen
Gravity−Feed Check Valve
Fuel−Transfer Shutoff Valve
Gravity−Crossflow Shutoff Valve
Crossflow Check Valve 3
Fuel−Crossflow Shutoff Valve
Fuel Crossflow Restrictor
GRAVITY XFLOW Switch/Light
XFLOW L and R Switch/Lights 4
AUTO OVERRIDE Switch/Light
Operation
Component Location Index 6
Adjustment/Test 501
Effectivity: ON A/C ALL
General
Operational Test of the Fuel Manual−Crossflow
System

Master
EFFECTIVITY: ALL
28−Contents Page 8
Aug 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
Chapter
Section
Subject Subject Page

PUMP, TRANSFER EJECTOR 28−13−01

Removal/Installation 401
Effectivity: ON A/C ALL
General
Removal of the Transfer Ejector Pump
Installation of the Transfer Ejector Pump 404
Adjustment/Test 501
Effectivity: ON A/C ALL
General
Operational Test of the Transfer Ejector Pump

VALVE, GRAVITY CROSSFLOW SHUTOFF 28−13−16

Removal/Installation 401
Effectivity: ON A/C ALL
General
Removal of the Gravity Crossflow Shutoff Valve
Installation of the Gravity Crossflow Shutoff Valve 407
Removal of the Gravity Crossflow Shutoff Valve 411
Electrical Actuator.
Installation of the Gravity Crossflow Shutoff Valve 414
Electrical Actuator
Adjustment/Test 501
Effectivity: ON A/C ALL
General
Operational Test of the Gravity Crossflow Shutoff
Valve

CHECK VALVE, CROSSFLOW 28−13−19

Removal/Installation 401
Effectivity: ON A/C ALL
General

Master
EFFECTIVITY: ALL
28−Contents Page 9
Aug 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
Chapter
Section
Subject Subject Page

Removal of the Crossflow Check Valve

Installation of the Crossflow Check Valve 404

PUMP, AFT SCAVENGE EJECTOR 28−13−22

Removal/Installation 401
Effectivity: ON A/C ALL
General
Removal of the Aft Scavenge Ejector Pump
Installation of the Aft Scavenge Ejector Pump 404
Adjustment/Test 501
Effectivity: ON A/C ALL
General
Operational Test of the Aft Scavenge Ejector
Pump

MANIFOLD, GRAVITY FEED 28−13−28

Removal/Installation 401
Effectivity: ON A/C ALL
General
Removal of the Gravity Feed Manifold
Installation of the Gravity Feed Manifold 404

SWITCH/LIGHT, FUEL CROSSFLOW 28−13−31

Removal/Installation 401
Effectivity: ON A/C ALL
General
Removal of the Fuel Crossflow Switch/Light
Installation of the Fuel Crossflow Switch/Light 404

Master
EFFECTIVITY: ALL
28−Contents Page 10
Aug 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
Chapter
Section
Subject Subject Page

VALVE, FUEL TRANSFER SHUTOFF 28−13−43

Removal/Installation
Effectivity: ON A/C ALL
General
Removal of the Fuel−Transfer Shutoff Valve
Installation of the Fuel−Transfer Shutoff Valve 407
Adjustment/Test 501
Effectivity: ON A/C ALL
General
Operational Test of the Fuel−Transfer Shutoff
Valve

VALVE, FUEL CROSSFLOW SHUTOFF 28−13−45

Removal/Installation 401
Effectivity: ON A/C ALL
General
Removal of the Fuel Crossflow Shutoff Valve
Installation of the Fuel Crossflow Shutoff Valve 406
Adjustment/Test 501
Effectivity: ON A/C ALL
General
Operational Test of the Fuel Crossflow Shutoff
Valve

DISTRIBUTION SYSTEM 28−20−00

Description and Operation 1
Effectivity: ON A/C ALL
General
Description
Engine Fuel−Feed System
Motive Flow System
Standby Fuel−Feed System

Master
EFFECTIVITY: ALL
28−Contents Page 11
Aug 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
Chapter
Section
Subject Subject Page

APU Fuel−Feed System

Pressure Refuel/Defuel System
Operation
Engine Fuel−Feed System
Motive Flow System 2
Standby Fuel−Feed System
APU Fuel−Feed System
Pressure Refuel/Defuel System

SHROUD, FUEL LINE 28−20−01

Removal/Installation 401
Effectivity: ON A/C ALL
General
Removal of the Fuel Lines Shroud (FS559.00 to
FS621.00)
Installation of the Fuel Lines Shroud (FS559 to 423
621)
Adjustment/Test 501
Effectivity: ON A/C ALL
General
Pressure and Blockage Test of the Fuel Line
Shroud Forward of FS 621.00
Pressure and Blockage Test of the Engine Fuel− 504
Feed Line
Pressure and Blockage Test of the Motive Flow− 511
Fuel Feed Line
Pressure and Blockage Test of the APU Fuel− 517
Feed Line

Master
EFFECTIVITY: ALL
28−Contents Page 12
Aug 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
Chapter
Section
Subject Subject Page

TUBE, SHROUD DRAIN, PRESSURE BOX 28−20−05

Removal/Installation 401
Effectivity: ON A/C ALL
General
Removal of the Pressure−Box−Shroud−Drain
Tube
Installation of the Pressure−Box−Shroud−Drain 405
Tube

ENGINE FUEL FEED SYSTEM 28−21−00

Description and Operation 1
Effectivity: ON A/C ALL
General
Component Details
Primary Ejector Pump
Fuel−Feed Check Valve
Engine−Fuel−Feed Shutoff Valve
Fuel Line Shroud 2
Operation
Component Location Index
Adjustment/Test 501
Effectivity: ON A/C ALL
General
Leak Test of the Engine Fuel−Feed Tubes

PUMP, PRIMARY EJECTOR 28−21−01

Removal/Installation 401
Effectivity: ON A/C ALL
General
Removal of the Primary Ejector Pump
Installation of the Primary Ejector Pump 404

Master
EFFECTIVITY: ALL
28−Contents Page 13
Aug 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
Chapter
Section
Subject Subject Page

Adjustment/Test 501
Effectivity: ON A/C ALL
General
Operational Test of the Primary Ejector Pump

CHECK VALVE, ENGINE−FUEL−FEED LINE 28−21−04

Removal/Installation 401
Effectivity: ON A/C ALL
General
Removal of the Fuel Feed Line Check Valve
Installation of the Fuel Feed Line Check Valve 404
Adjustment/Test 501
Effectivity: ON A/C ALL
General
Operational Test of the Engine−Fuel−Feed−Line
Check Valve

VALVE, ENGINE FUEL FEED SHUTOFF 28−21−07

Removal/Installation 401
Effectivity: ON A/C ALL
General
Removal of the Engine−Fuel−Feed Shutoff Valve
Installation of the Engine−Fuel−Feed Shutoff 404
Valve
Removal of the Engine−Fuel−Feed Shutoff Valve 406
Electrical Actuator
Installation of the Engine−Fuel−Feed Shutoff 409
Valve Electrical Actuator
Adjustment/Test 501
Effectivity: ON A/C ALL
General

Master
EFFECTIVITY: ALL
28−Contents Page 14
Aug 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
Chapter
Section
Subject Subject Page

Operational Test of the Engine−Fuel−Feed

Shutoff Valve
Operation Test of the Engine−Fuel−Shutoff−Valve 507
Position Indicators

SHROUD, ENGINE FUEL FEED 28−21−13

Removal/Installation 401
Effectivity: ON A/C ALL
General
Removal of the Shroud and Engine−Fuel−Feed
Tube from FS621.00 to the Engine Pylon
Firewall
Installation of the Shroud and the Engine Fuel− 408
Feed Line from FS621.00 to the Engine Pylon
Firewall
Adjustment/Test 501
Effectivity: ON A/C ALL
General
Pressure and Blockage Test of the Engine Fuel−
Feed Shroud, FS 621.00 to the Engine Pylon
Firewall
Pressure and Leak Test of the Above Wing Fuel− 505
Feed Shrouds at FS 501.4, the Motive Flow
Shrouds at FS 503.9 and the APU Shroud at FS
506.4

MOTIVE FLOW SYSTEM 28−22−00

Description and Operation 1
Effectivity: ON A/C ALL
General
Component Details
Wash Filter

Master
EFFECTIVITY: ALL
28−Contents Page 15
Aug 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
Chapter
Section
Subject Subject Page

Motive−Flow Check Valve

Venturi
Venturi Tube 2
Operation
Component Location Index

FILTER, WASH 28−22−01

Removal/Installation 401
Effectivity: ON A/C ALL
General
Removal of the Wash Filter
Installation of the Wash Filter 404

CHECK VALVE, MOTIVE FLOW 28−22−04

Removal/Installation 401
Effectivity: ON A/C ALL
General
Removal of the Motive Flow Check Valve
Installation of the Motive Flow Check Valve 404

VENTURI 28−22−07
Removal/Installation 401
Effectivity: ON A/C ALL
General
Removal of the Venturi
Installation of the Venturi 404

LINES, MOTIVE FLOW 28−22−09

Removal/Installation 401
Effectivity: ON A/C ALL
General
Removal of the Motive Flow Lines

Master
EFFECTIVITY: ALL
28−Contents Page 16
Aug 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
Chapter
Section
Subject Subject Page

Installation of the Motive Flow Lines 404

Adjustment/Test 501
Effectivity: ON A/C ALL
General
Pressure Blockage Test and Leak Test of the
Motive Flow Lines

SHROUD, MOTIVE FLOW 28−22−11

Adjustment/Test 501
Effectivity: ON A/C ALL
General
Pressure and Blockage Test of the Motive Flow
Shroud, FS 621.00 to the Engine Pylon Firewall

STANDBY FUEL FEED SYSTEM 28−23−00

Description and Operation 1
Effectivity: ON A/C ALL
General
Component Details
Electric Boost Pump
Boost Pump Canister
Standby−Fuel−Feed Check Valve 2
Boost Pump Switch/Light
Operation
Component Location Index 3

PUMP, ELECTRIC BOOST 28−23−01

Removal/Installation 401
Effectivity: ON A/C ALL
General
Removal of the Electric Boost Pump
Installation of the Electric Boost Pump 404

Master
EFFECTIVITY: ALL
28−Contents Page 17
Aug 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
Chapter
Section
Subject Subject Page

Adjustment/Test 501
Effectivity: ON A/C ALL
General
Operational Test of the Electric Boost Pump

CANISTER, BOOST PUMP 28−23−03

Removal/Installation 401
Effectivity: ON A/C ALL
General
Removal of the Boost Pump Canister
Installation of the Boost Pump Canister 409

SWITCH/LIGHT, BOOST PUMP 28−23−04

Removal/Installation 401
Effectivity: ON A/C ALL
General
Removal of the Boost Pump Switch/Light
Installation of the Boost Pump Switch/Light 404

CHECK VALVE, STANDBY−FUEL−FEED LINE 28−23−07

Removal/Installation 401
Effectivity: ON A/C ALL
General
Removal of the Standby−Fuel−Feed−Line Check
Valve
Installation of the Standby−Fuel−Feed−Line 406
Check Valve
Adjustment/Test 501
Effectivity: ON A/C ALL
General
Operational Test of the Standby−Fuel−Feed
Check Valve

Master
EFFECTIVITY: ALL
28−Contents Page 18
Aug 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
Chapter
Section
Subject Subject Page

AUXILIARY POWER UNIT (APU) FUEL FEED 28−24−00

SYSTEM
Description and Operation 1
Effectivity: ON A/C ALL
General
Component Details
APU Fuel Pump
APU−Feed−Line Check Valve
APU−Pump Inlet Screen 2
APU Negative−Gravity−Feed Valve
APU−Fuel−Feed Shutoff Valve
APU Fuel−Line Shroud
Operation
Component Location Index 3

PUMP, AUXILIARY POWER UNIT (APU) FUEL 28−24−01

Removal/Installation 401
Effectivity: ON A/C ALL
General
Removal of the APU Fuel Pump Cartridge
Installation of the APU Fuel Pump Cartridge 404
Removal of the APU Fuel Pump Canister 406
Installation of the APU Fuel Pump Canister 409
Adjustment/Test 501
Effectivity: ON A/C ALL
General
Operational Test of the APU Fuel Pump

CHECK VALVE, AUXILIARY POWER UNIT (APU) 28−24−07

FEED LINE
Removal/Installation 401
Effectivity: ON A/C ALL

Master
EFFECTIVITY: ALL
28−Contents Page 19
Aug 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
Chapter
Section
Subject Subject Page

General 401
Removal of the APU Feed Line Check Valve
Installation of the APU Feed Line Check Valve 404

CHECK VALVE, AUXILIARY POWER UNIT (APU) 28−24−10

NEGATIVE−GRAVITY FEED
Removal/Installation 401
Effectivity: ON A/C ALL
General
Removal of the APU Negative−Gravity Feed
Check Valve
Installation of the APU Negative−Gravity Feed 404
Check Valve

SHROUD, AUXILIARY POWER UNIT (APU) FEED 28−24−23

Removal/Installation 401
Effectivity: ON A/C ALL
General
Removal of the APU Feed Shroud
Installation of the APU Feed Shroud 405
Adjustment/Test 501
Effectivity: ON A/C ALL
General
Pressure and Blockage Test of the APU Feed
Shroud

VALVE, AUXILIARY POWER UNIT (APU) FUEL 28−24−25

FEED SHUTOFF
Removal/Installation 401
Effectivity: ON A/C ALL
General
Removal of the APU Fuel Feed Shutoff Valve

Master
EFFECTIVITY: ALL
28−Contents Page 20
Aug 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
Chapter
Section
Subject Subject Page

Installation of the APU Fuel Feed Shutoff Valve 404

Removal of the APU Fuel Feed Shutoff Valve 406
Electrical Actuator
Installation of the APU Fuel Feed Shutoff Valve 409
Electrical Actuator
Adjustment/Test 501
Effectivity: ON A/C ALL
General
Operational Test of the APU Fuel−Feed Shutoff−
Valve
Operation Test of APU Fuel−Feed Shutoff−Valve 504
Position−Indicator
Leak Test of the APU Fuel−Feed Shutoff−Valve 506
Inspection/Check 601
Effectivity: ON A/C ALL
General
Internal Leak Check

PRESSURE REFUEL/DEFUEL SYSTEM 28−25−00

Description and Operation 1
Effectivity: ON A/C ALL
General
Component Details 2
Refuel/Defuel Single−Point Adapter
Refuel/Defuel Check Valve
Refuel/Defuel Control Panel 3
Refuel Shutoff Valve 5
Restrictor 6
High−Level Sensor
Operation
Component Location Index 7

Master
EFFECTIVITY: ALL
28−Contents Page 21
Aug 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
Chapter
Section
Subject Subject Page

Adjustment/Test 501
Effectivity: ON A/C ALL
General
Operational Test of the Refuel/Defuel System

ADAPTER, REFUELING 28−25−01

Removal/Installation 401
Effectivity: ON A/C ALL
General
Removal of the Refueling Adapter
Installation of the Refueling Adapter 405

CHECK VALVE, REFUEL/DEFUEL 28−25−04

Removal/Installation 401
Effectivity: ON A/C ALL
General
Removal of the Refuel/Defuel Check Valve
Installation of the Refuel/Defuel Check Valve 405

VALVE, REFUEL SHUTOFF 28−25−07

Removal/Installation 401
Effectivity: ON A/C ALL
General
Removal of the Refuel Shutoff Valve
Installation of the Refuel Shutoff Valve 407

SENSOR, HIGH−LEVEL 28−25−13

Removal/Installation 401
Effectivity: ON A/C ALL
General
Removal of the High−Level Sensor
Installation of the High−Level Sensor 405

Master
EFFECTIVITY: ALL
28−Contents Page 22
Aug 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
Chapter
Section
Subject Subject Page

PANEL, REFUEL/DEFUEL CONTROL 28−25−16

Removal/Installation
Effectivity: ON A/C ALL
General
Removal of the Fuselage−Refuel/Defuel Control
Panel
Installation of the Fuselage−Refuel/Defuel Control 404
Panel
Removal of the Flight−Compartment− 406
Refuel/Defuel Control Panel
Installation of the Flight−Compartment− 409
Refuel/Defuel Control Panel

PANEL, FUEL CONTROL 28−31−01

Removal/Installation 401
Effectivity: ON A/C ALL
General
Removal of the FUEL Control Panel
Installation of the FUEL Control Panel 404

INDICATING SYSTEM 28−40−00

Description and Operation 1
Effectivity: ON A/C ALL
General
Description
Fuel−Quantity Gauging System
Fuel Warning System
Operation
Fuel−Quantity Gauging System
Fuel Warning System

Master
EFFECTIVITY: ALL
28−Contents Page 23
Aug 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
Chapter
Section
Subject Subject Page

FUEL QUANTITY GAUGING SYSTEM 28−41−00

Description and Operation
Effectivity: ON A/C ALL
General
Component Details
Fuel−Quantity Transmitter Probe
Compensator
Fuel Magnetic Level−Indicator
Fuel System Computer 2
Aircraft Attitude Indicator
Operation
Component Location Index 3

PROBE, FUEL QUANTITY TRANSMITTER 28−41−04

Removal/Installation 401
Effectivity: ON A/C ALL
General
Removal of the Fuel Quantity Transmitter Probe
Installation of the Fuel Quantity Transmitter Probe 405
Adjustment/Test 501
Effectivity: ON A/C ALL
Functional Test of the Fuel Quantity Transmitter
Probes

INDICATOR, FUEL MAGNETIC LEVEL 28−41−10

Removal/Installation 401
Effectivity: ON A/C ALL
General
Removal of the Fuel Magnetic Level Indicator
Installation of the Fuel Magnetic Level Indicator 404

Master
EFFECTIVITY: ALL
28−Contents Page 24
Aug 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
Chapter
Section
Subject Subject Page

COMPUTER, FUEL SYSTEM 28−41−16

Removal/Installation
Effectivity: ON A/C ALL
General
Removal of the Fuel System Computer
Installation of the Fuel System Computer 404
Adjustment/Test 501
Effectivity: ON A/C ALL
General
Fuel Computer Bite Check

FILTER, ELECTRONIC 28−41−17

Removal/Installation 401
Effectivity: ON A/C 7288, 7368, 7528, 7801 Post SB601R−28−043
General
Removal of the Fuel System Electronic Filter
Installation of the Fuel System Electronic Filter 404

COMPENSATOR 28−41−19
Removal/Installation 401
Effectivity: ON A/C ALL
General
Removal of the Compensator
Installation of the Compensator 405

ATTITUDE INDICATORS 28−41−23

Removal/Installation 401
Effectivity: ON A/C ALL
General
Removal of the Attitude Indicators
Installation of the Attitude Indicators 405

Master
EFFECTIVITY: ALL
28−Contents Page 25
Aug 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
Chapter
Section
Subject Subject Page

FUEL WARNING SYSTEM 28−42−00

Description and Operation 1
Effectivity: ON A/C ALL
General
Component Details
Boost−Pump Pressure Switch
Engine−Fuel−Feed Pressure Switch
Scavenge−Ejector Differential−Pressure Switch 2
APU−Fuel−Pump Pressure Switch
Fuel Temperature Sensor
Operation
Component Location Index 3

PRESSURE SWITCH, BOOST PUMP 28−42−01

Removal/Installation 401
Effectivity: ON A/C ALL
General
Removal of the Boost Pump Pressure Switch
Installation of the Boost Pump Pressure Switch 404

PRESSURE SWITCH, ENGINE FUEL FEED 28−42−04

Removal/Installation 401
Effectivity: ON A/C ALL
General
Removal of the Engine Fuel Feed Pressure
Switch
Installation of the Engine Fuel Feed Pressure 404
Switch

Master
EFFECTIVITY: ALL
28−Contents Page 26
Aug 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
Chapter
Section
Subject Subject Page

PRESSURE SWITCH, SCAVENGE EJECTOR 28−42−07

DIFFERENTIAL
Removal/Installation
Effectivity: ON A/C ALL
General
Removal of the Scavenge Ejector Differential
Pressure Switch
Installation of the Scavenge Ejector Differential 404
Pressure Switch

PRESSURE SWITCH, AUXILIARY POWER UNIT 28−42−10

(APU) FUEL PUMP
Removal/Installation 401
Effectivity: ON A/C ALL
General
Removal of the APU Fuel Pump Pressure Switch
Installation of the APU Fuel Pump Pressure 405
Switch

SENSOR, FUEL TEMPERATURE 28−42−15

Removal/Installation 401
Effectivity: ON A/C ALL
General
Removal of the Fuel Temperature Sensor
Installation of the Fuel Temperature Sensor 404
Adjustment/Test 501
Effectivity: ON A/C ALL
General
Functional Test of the Fuel Temperature Sensor

Master
EFFECTIVITY: ALL
28−Contents Page 27
Aug 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C ALL
FUEL SYSTEM − DESCRIPTION AND OPERATION

1. General
A. The fuel system contains and supplies fuel to the engines and the auxiliary power unit
(APU). The fuel system lets you refuel and defuel the aircraft by pressure. You can also
measure the quantity of fuel in the tanks. The fuel system has the systems that follow:
± Storage system (28−10−00)
± Distribution system (28−20−00)
± Indicating system (28−40−00).
2. Description
A. Storage System
(1) The storage system has three fuel tanks, two main tanks and a center tank. These
tanks contain fuel for the engines and the APU. A collector tank, connected to each
main tank, supplies constant fuel flow to the engines at all aircraft attitudes. Over
wing ports let you refuel each fuel tank by gravity. A system of air scoops, vent
lines, and vent valves control the pressure in the fuel tanks. The storage system
also moves fuel between main tanks to keep the aircraft balanced about a lateral
axis.
B. Distribution System
(1) Refuel and defuel operations are controlled by the distribution system. It also
controls the flow of fuel to the engines and the APU. And, it supplies motive flow
pressure to operate the ejector pumps in the fuel system. In the case of a fuel
system failure the distribution system will supply standby fuel to the engines.
C. Indicating System
(1) The indicating system monitors the fuel level in the fuel system. This data is used
by the fuel system computer to display fuel quantity and to control the automatic
operation of the fuel system. The indicating system also monitors fuel pressure and
temperature in the fuel system. Fuel pressure and temperature data is used to
make displays that tell the flight crew of fuel system status.

Master
EFFECTIVITY: See Pageblock 28−00−00 page 1
28−00−00 Page 1
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C ALL
FUEL SYSTEM − MAINTENANCE PRACTICES

1. General
A. The maintenance procedure that follows is for the fuel safety precautions. These safety
precautions are necessary to do work on a fuel system component or in a fuel tank. The
fuel safety precautions are divided into general safety precautions and fuel−tank safety
precautions.

TASK 28−00−00−910−801
Fuel Safety Precautions

1. General Safety Precautions

Subtask 28−00−00−910−001
A. General
WARNING: OBEY ALL THE FUEL SAFETY PRECAUTIONS WHEN YOU DO WORK
ON THE FUEL SYSTEM AND/OR A FUEL SYSTEM COMPONENT. IF
YOU DO NOT DO THIS, YOU CAN CAUSE INJURIES TO PERSONS
AND/OR DAMAGE TO EQUIPMENT.
(1) Obey all local safety regulations during fuel system maintenance.
(2) Before maintenance is done on the fuel system, make sure that all persons read
and fully know the maintenance practices that follow. To keep the system
serviceable, carefully and accurately obey these practices.
(3) Do fuel system maintenance only in areas that permit free movement of fire fighting
equipment and other emergency equipment. Sufficient fire fighting equipment and
persons who know how to use it must be immediately available at all times.
(4) Make sure that the wind does not move fuel fumes to a building in which fuel fumes
can collect. Make sure that the wind does not move fuel fumes to a flame or
equipment that causes sparks.
(5) Remove all equipment that causes sparks from the aircraft and the maintenance
area. Equipment that causes sparks includes electrically−powered tools, vacuum
cleaners, and electronic test equipment.
(6) Connect the grounding cable to an approved ground and to an aircraft ground point.
(7) Ground the maintenance stands to the same ground as the aircraft. Bond the air
mover to the aircraft.
(8) Do not smoke or use a flame near the aircraft.
(9) If you discard fuel, obey all of the applicable regulations.
(10) Prevent fuel leakage. Fuel leakage increases the risk of a fire and can cause
incorrect leakage reports. If there is fuel leakage, do the steps that follow:
± Stop all work in the area until the fuel is removed
± Have the area cleaned
± Make sure that the area is safe.

Master
EFFECTIVITY: See Pageblock 28−00−00 page 201
28−00−00 Page 201
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
Subtask 28−00−00−910−002
B. Health Safety
(1) Do not get fuel in your eyes or on your skin. If you get fuel in your eyes, flush your
eyes with water. If you get fuel on your skin, clean your skin with water.
(2) Do not breathe fuel fumes. Do not drink fuel. If you breathe the fuel fumes or drink
the fuel, get medical aid immediately.
(3) If a person breathes a high concentration of fuel fumes, a person can get
headaches, become drowsy, or faint. If a person’s breathing becomes slow or
stops, use continuous artificial respiration and get medical aid.
(4) Supply clean air if the person has headaches or eye irritations.
(5) If chemical antioxidants, metal deactivators, or corrosion inhibitors from the fuel get
in a person’s eyes, do the steps that follow:
± Flush the eyes with water for a minimum of 15 minutes
± While you flush the eyes, frequently lift the top and bottom eyelids to make sure
that the eyes are fully cleaned
± Get medical aid.

2. Fuel Tank Safety Precautions

Subtask 28−00−00−910−003
A. Electrical Safety
(1) Put a dust cap on all electrical connectors. Do not let fuel, moisture, or other
unwanted material go into the electrical connectors.
(2) Do not use electrical testing equipment that can cause sparks in a fuel tank.
(3) Do not connect or disconnect electrical equipment to or from energized outlets that
are less than 100 feet from an open fuel tank or a fuel leakage.
(4) Use lamps that are resistant to explosion, have good electrical connections, and
have serviceable extension cords.
(5) Use floodlights that are resistant to explosion and drop cords for external lighting.

Subtask 28−00−00−910−004
B. Tools and Equipment
(1) Keep a list of all the tools, equipment, material, and persons when they go in and
out of the fuel tank. Before the tank is closed, make sure that all of the items on the
list are removed from the fuel tank.
(2) After the fuel tank maintenance is completed, make sure that all the tools,
equipment, and material are removed from the fuel tank.
(3) Persons who do work near open fuel tanks must not have the items that follow:
± Metal objects
± Matches
± Pocket warmers
± Shoes with metal clips or nails

Master
EFFECTIVITY: See Pageblock 28−00−00 page 201
28−00−00 Page 202
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
± Jewelry
± Hearing−aid devices or other battery−operated equipment.
± Steel Wool of any type
(4) Use only air−driven power tools in the fuel tank.
CAUTION: DO NOT USE METAL BOXES OR OTHER TYPES OF CONTAINERS
WITH SHARP OR ROUGH EDGES IN THE FUEL TANK. DAMAGE TO
THE TANK SEALANT CAN OCCUR.
(5) When you have tools in the fuel tank, use containers that do not make static
electricity and have rounded corners. If you use a sharp−edged tool in the fuel tank,
put it in an applicable container when the work is completed.

Subtask 28−00−00−910−005
C. Electrostatic Discharge
(1) Use cotton coveralls with buttons or zippers that do not cause sparks in the fuel
tanks. Do not put on wool, silk, nylon, or other synthetic clothing.
(2) Use only sponges and cotton rags to absorb fuel. If you use other materials, you
can cause a static discharge.

Subtask 28−00−00−910−006
D. Fuel Tank Contamination
(1) When you go into the fuel tanks, use hair covers, shoe covers, and clean, cotton
coveralls that have no lint. Clean the cuffs of the pants to remove all the dirt or lint.
(2) Make sure that all equipment that you put into the fuel tanks has no dirt and dust.
(3) Make sure that the air ducts that supply air in the fuel tanks are internally and
externally clean.
(4) Make sure that all the equipment used to supply air has sufficient filters.
(5) Do not let dirt, dust, or other unwanted materials get into the fuel tank. Remove all
the unwanted material from the open fuel tanks with a vacuum hose.
WARNING: DO NOT USE STEEL WOOL OF ANY TYPE IN THE FUEL TANKS.
PIECES OF STEEL WOOL CAN BREAK OFF AND CAUSE DAMAGE
OR AN EXPLOSION IF THEY TOUCH ELECTRICAL COMPONENTS.
(6) Do not use steel wool filament of any type to clean the fuel tanks. The usage of
steel wool for any purpose is forbidden in the fuel tank.
(7) Close all of the tanks when maintenance stops.
(8) Use a vacuum hose in the fuel tank after a large quantity of work is done in the fuel
tank.
(9) Put a cap or plug on all lines and components that are disconnected or removed.
Do not let unwanted material go into the lines or components.

Master
EFFECTIVITY: See Pageblock 28−00−00 page 201
28−00−00 Page 203
Aug 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C ALL
FUEL SYSTEM − ADJUSTMENT/TEST

1. General
A. The maintenance procedure that follows is for the operational test of the fuel system.

TASK 28−00−00−710−801
Operational Test of the Fuel System

1. Job Set−Up Information

Subtask 28−00−00−946−002
A. Reference Information
REFERENCE DESIGNATION
TASK 12−11−28−650−802 Manual Pressure Refueling
TASK 12−00−07−861−801 Connect External AC Power
TASK 12−00−07−861−802 Remove External AC Power

2. Job Set−Up
**ON A/C 7004−7019, 7021−7044, 7046, 7048, 7050, 7052, 7055−7056, 7059, 7061−7064,
7066−7067, 7069−7070, 7072−7073, 7075−7077, 7079−7080, 7085−7086, 7088−7094,
7099−7106, 7108−7111, 7113−7117, 7119, 7121−7123, 7125, 7127−7143, 7145−7152, 7154,
7156−7159, 7162−7163, 7165, 7167−7169, 7171−7176, 7178−7181, 7185−7196, 7199−7200,
7202−7222, 7224−7233, 7235−7236, 7238−7271, 7273−7294 Pre SB601R−24−090

Subtask 28−00−00−865−001
A. Make sure that the circuit breakers that follow are closed:
CB PANEL CB NO. NAME ZONE
CBP−1 M6 L FUEL PUMP 221
CBP−1 M7 L FUEL PUMP CONT 221
CBP−1 M8 XFLOW SOV 221
CBP−1 M12 FUEL SYST CONT 221
CBP−1 N10 XFER/APU FUEL PUMP 221
CBP−1 N11 XFER/APU CONT 221
CBP−1 N12 XFER/APU APU ECU 221
CBP−1 S1 FUEL SOV R ENG 221
CBP−1 S2 FUEL SOV L ENG 221
CBP−2 G10 R FUEL PUMP 222
CBP−2 G11 R FUEL PUMP CONT 222
CBP−4 B9 FUEL GRAV XFLOW 222
CBP−4 B10 FUEL SYST CONT 222

Master
EFFECTIVITY: See Pageblock 28−00−00 page 501
28−00−00 Page 501
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

CB PANEL CB NO. NAME ZONE

CBP−5 B14 FUEL DEFL 311
CBP−5 B15 EMRG REFL 311

**ON A/C 7003, 7020, 7045, 7047, 7049, 7051, 7053−7054, 7057−7058, 7060, 7065, 7071, 7074,
7078, 7081−7084, 7087, 7095−7098, 7107, 7112, 7118, 7120, 7124, 7126, 7144, 7153, 7155,
7160−7161, 7164, 7166, 7170, 7177, 7182−7184, 7197−7198, 7201, 7223, 7234, 7237, 7272,
7295−7990, 8000−8064, 8066−8068 and ON A/C 7004−7019, 7021−7044, 7046, 7048, 7050,
7052, 7055−7056, 7059, 7061−7064, 7066−7067, 7069−7070, 7072−7073, 7075−7077,
7079−7080, 7085−7086, 7088−7094, 7099−7106, 7108−7111, 7113−7117, 7119, 7121−7123,
7125, 7127−7143, 7145−7152, 7154, 7156−7159, 7162−7163, 7165, 7167−7169, 7171−7176,
7178−7181, 7185−7196, 7199−7200, 7202−7222, 7224−7233, 7235−7236, 7238−7271,
7273−7294 Post SB601R−24−090

Subtask 28−00−00−865−002
B. Make sure that the circuit breakers that follow are closed:
CB PANEL CB NO. NAME ZONE
CBP−1 M6 L FUEL PUMP 221
CBP−1 M7 L FUEL PUMP CONT 221
CBP−1 M8 XFLOW SOV 221
CBP−1 M12 FUEL SYST CONT 221
CBP−1 N10 XFER/APU FUEL PUMP 221
CBP−1 N11 XFER/APU CONT 221
CBP−1 N12 XFER/APU APU ECU 221
CBP−1 S1 FUEL SOV R ENG 221
CBP−1 S2 FUEL SOV L ENG 221
CBP−2 G10 R FUEL PUMP 222
CBP−2 G11 R FUEL PUMP CONT 222
CBP−4 B9 FUEL GRAV XFLOW 222
CBP−4 B10 FUEL SYST CONT 222
CBP−5 B6 FUEL DEFL 311
CBP−5 B7 EMRG REFL 311

**ON A/C ALL

Subtask 28−00−00−010−001
C. Open the access doors that follow:
ACCESS DESIGNATION
162AB Fuel/defuel control panel door
811 Main avionics compartment door

Master
EFFECTIVITY: See Pageblock 28−00−00 page 501
28−00−00 Page 502
Dec 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
Subtask 28−00−00−650−001
D. Make sure that each main tank has a minimum of 200 pounds (90.8 kg) of fuel. Refuel if
necessary (Ref. TASK 12−11−28−650−802).

Subtask 28−00−00−861−001
E. Connect the external AC power to the aircraft (Ref. TASK 12−00−07−861−801).
F. On the fuel system computer installed on the right side of the main avionics
compartment, push the RESET button.
G. Push the FUEL pushbutton on the engine indication and crew alerting system (EICAS)
control panel to get the FUEL synoptic display.

3. Procedure
Subtask 28−00−00−710−002
A. Do an operational test of the fuel system as follows:
(1) Make sure that the switch/lights that follow are not on:
(a) On the pilot’s and copilot’s glareshield panels:
± LH ENG FIRE PUSH switch/light
± RH ENG FIRE PUSH switch/light
± APU FIRE PUSH switch/light.
(b) On the FUEL control panel:
± XFLOW AUTO OVERRIDE switch/light
± L BOOST PUMP switch/light
± R BOOST PUMP switch/light
± XFLOW L switch/light
± XFLOW R switch/light
± GRAVITY XFLOW switch/light.
(c) On the APU control panel:
± PWR FUEL switch/light.

Subtask 28−00−00−710−004
B. Continue the operational test of the fuel system as follows:
(1) On the FUEL control panel, push in the L BOOST PUMP switch/light. Make sure
that the L and R BOOST PUMP ON lights come on and that the two INOP lights do
not come on.
NOTE: When the L BOOST PUMP switch/light is pushed, the left and the right
boost pump come on line.
(2) Make sure that the results that follow also occur:
(a) On the status page of the secondary EICAS display, make sure that the L and
R FUEL PUMP ON advisory indications are shown.

Master
EFFECTIVITY: See Pageblock 28−00−00 page 501
28−00−00 Page 503
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
(b) On the primary EICAS display, make sure that the L and R FUEL PUMP
caution indications are not shown.
(c) On the FUEL synoptic display of the EICAS, make sure that the left and the
right electric boost−pump outlines are shown in green.
(d) On the FUEL synoptic display, also make sure that the left and the right shutoff
valve outlines are shown in white. Make sure that the two shutoff valves are
shown in the open position and their flow lines in green.
WARNING: DO NOT PUSH THE "BOTTLE 1 ARMED PUSH TO DISCH"
SWITCH/LIGHT OR THE "BOTTLE 2 ARMED PUSH TO DISCH"
SWITCH/LIGHT DURING THE REMAINING STEPS OF THIS TEST.
THE HALON CAN COME OUT OF THE FIREX BOTTLE AND CAUSE
INJURIES.
(3) On the pilot’s glareshield panel, push in the LH ENG FIRE PUSH switch/light.
(4) Make sure the following conditions occur:
(a) On the primary EICAS display, make sure that the L ENG SOV CLSD caution
indication is shown.
(b) On the pilot’s and copilot’s glareshield panels, the two MASTER CAUTION
pushbutton−annunciators start to flash followed by an audible chime.
(c) On the FUEL synoptic display, make sure that the left shutoff valve outline is
shown in amber and in the closed position, and its green flow line is not
shown.
(5) On the pilot’s glareshield panel, push out the LH ENG FIRE PUSH switch/light.
(6) Make sure the following conditions occur:
(a) On the primary EICAS display, make sure that the L ENG SOV CLSD caution
indication is not shown.
(b) On the pilot’s and copilot’s glareshield panels, the two MASTER CAUTION
pushbutton−annunciators go off.
(c) On the FUEL synoptic display, make sure that the left shutoff valve outline is
shown in white and in the open position, and its flow line in green.
(7) On the FUEL control panel, push out the L BOOST PUMP switch/light. Make sure
that the L and R BOOST PUMP ON lights go off and the two INOP lights come on.
NOTE: When the L BOOST PUMP switch/light is pushed out, the left and the
right electric boost pump stop.
(8) Make sure that the results that follow also occur:
(a) On the FUEL synoptic display, make sure that the left and the right electric
boost−pump outlines are shown in amber.
(b) On the status page of the secondary EICAS display, make sure that the L and
R FUEL PUMP ON advisory indications are not shown.
(c) On the primary EICAS display, make sure that the L and R FUEL PUMP
caution indications are shown.
(9) On the FUEL control panel, push in the R BOOST PUMP switch/light. Make sure
that the L and R BOOST PUMP ON lights come on and that the two INOP lights do

Master
EFFECTIVITY: See Pageblock 28−00−00 page 501
28−00−00 Page 504
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
not come on.
NOTE: When the R BOOST PUMP switch/light is pushed, the left and the right
boost pump come on line.
(10) Make sure that the results that follow also occur:
(a) On the status page of the secondary EICAS display, make sure that the L and
R FUEL PUMP ON advisory indications are shown.
(b) On the primary EICAS display, make sure that the L and R FUEL PUMP
caution indications are not shown.
(c) On the FUEL synoptic display of the EICAS, make sure that the left and the
right electric boost−pump outlines are shown in green.
(d) On the FUEL synoptic display, also make sure that the left and the right shutoff
valve outlines are shown in white. Make sure that the two shutoff valves are
shown in the open position and their flow lines in green.
WARNING: DO NOT PUSH THE "BOTTLE 1 ARMED PUSH TO DISCH"
SWITCH/LIGHT OR THE "BOTTLE 2 ARMED PUSH TO DISCH"
SWITCH/LIGHT DURING THE REMAINING STEPS OF THIS TEST.
THE HALON CAN COME OUT OF THE FIREX BOTTLE AND CAUSE
INJURIES.
(11) On the copilot’s glareshield panel, push in the RH ENG FIRE PUSH switch/light.
(12) Make sure the following conditions occur:
(a) On the primary EICAS display, make sure that the R ENG SOV CLSD caution
indication is shown.
(b) On the pilot’s and copilot’s glareshield panels, the two MASTER CAUTION
pushbutton−annunciators start to flash followed by an audible chime.
(c) On the FUEL synoptic display, make sure that the right shutoff valve outline is
shown in amber and in the closed position, and its green flow line is not
shown.
(13) On the copilot’s glareshield panel, push out the RH ENG FIRE PUSH switch/light.
(14) Make sure the following conditions occur:
(a) On the primary EICAS display, make sure that the R ENG SOV CLSD caution
indication is not shown.
(b) On the pilot’s and copilot’s glareshield panels, the two MASTER CAUTION
pushbutton−annunciators go off.
(c) On the FUEL synoptic display, make sure that the right shutoff valve outline is
shown in white and in the open position, and its flow line in green.
(15) On the FUEL control panel, push out the R BOOST PUMP switch/light. Make sure
that the L and R BOOST PUMP ON lights go off and the two INOP lights come on.
NOTE: When the R BOOST PUMP switch/light is pushed out, the left and the
right electric boost pump stop.
(16) Make sure that the results that follow also occur:
(a) On the FUEL synoptic display, make sure that the left and the right electric
boost−pump outlines are shown in amber.

Master
EFFECTIVITY: See Pageblock 28−00−00 page 501
28−00−00 Page 505
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
(b) On the status page of the secondary EICAS display, make sure that the L and
R FUEL PUMP ON advisory indications are not shown.
(c) On the primary EICAS display, make sure that the L and R FUEL PUMP
caution indications are shown.

Subtask 28−00−00−710−005
C. Continue the operational test of the fuel system as follows:
(1) On the APU control panel, push in the PWR FUEL switch/light. Make sure that the
PUMP FAIL and the SOV FAIL lights do not come on.
(2) On the FUEL synoptic display of the EICAS, make sure that the APU fuel−pump
outline is shown in green.
(3) On the FUEL synoptic display, also make sure that the APU−fuel−feed
shutoff−valve (written as the "shutoff valve" in this procedure) outline is shown in
white. Make sure that the shutoff valve is shown in the open position and its flow
line in green.
WARNING: DO NOT PUSH THE "BOTTLE ARMED PUSH TO DISCH"
SWITCH/LIGHT DURING THE REMAINING STEPS OF THIS TEST.
THE HALON CAN COME OUT OF THE FIREX BOTTLE AND CAUSE
INJURIES.
(4) On the copilot’s glareshield panel, push in the APU FIRE PUSH switch/light.
(5) Make sure that the results that follow occur:
(a) The APU fuel pump stops. On the FUEL synoptic display, make sure that the
APU fuel−pump outline is shown in white.
(b) On the FUEL synoptic display, also make sure that the shutoff valve is shown
in the closed position and its green flow line is not shown.
(6) On the copilot’s glareshield panel, push out the APU FIRE PUSH switch/light.
(7) Make sure that the results that follow occur:
(a) The APU fuel pump comes on. On the FUEL synoptic display, make sure that
the APU fuel−pump outline is shown in green.
(b) On the FUEL synoptic display, also make sure that the shutoff valve is shown
in the open position and its green flow line is shown.
(8) On the APU control panel, push out the PWR FUEL switch/light.

Subtask 28−00−00−710−008
D. Continue the operational test of the fuel system as follows:
(1) On the FUEL control panel, push in the XFLOW AUTO OVERRIDE switch/light.
Make sure that the MAN light comes on.
(2) On the FUEL control panel, also push in the XFLOW L switch/light. Make sure that
the ON light comes on and that the FAIL light does not come on.
(3) On the status page of the secondary EICAS display, make sure that the MAN
XFLOW and the L XFLOW ON status indications are shown.
(4) On the FUEL synoptic display of the EICAS, make sure of the conditions that follow:

Master
EFFECTIVITY: See Pageblock 28−00−00 page 501
28−00−00 Page 506
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
(a) The APU fuel−pump outline is shown in green.
(b) The left and the right fuel−crossflow shutoff−valve (written as the "shutoff
valve" in this procedure) outlines are shown in white.
(c) The left shutoff valve is shown in the open position and its flow line in green.
(d) The right shutoff valve is shown in the closed position and its green flow line is
not shown.
(5) On the FUEL control panel, push out the XFLOW L switch/light. Make sure that the
ON light goes off.
(6) On the status page of the secondary EICAS display, make sure that the L XFLOW
ON status indication is not shown.
(7) On the FUEL synoptic display, make sure that the left shutoff valve is shown in the
closed position and its green flow line is not shown.
(8) On the FUEL control panel, push in the XFLOW R switch/light. Make sure that the
ON light comes on and that the FAIL light does not come on.
(9) On the status page of the secondary EICAS display, make sure that the MAN
XFLOW and the R XFLOW ON status indications are shown.
(10) On the FUEL synoptic display, make sure of the conditions that follow:
(a) The APU fuel−pump outline is shown in green.
(b) The left and the right fuel−crossflow shutoff−valve outlines are shown in white.
(c) The right shutoff valve is shown in the open position and its flow line in green.
(d) The left shutoff valve is shown in the closed position and its green flow line in
not shown.
(11) On the FUEL control panel, push out the XFLOW R switch/light. Make sure that the
ON light goes off.
(12) On the FUEL control panel, also push out the XFLOW AUTO OVERRIDE
switch/light. Make sure that the MAN light goes off.
(13) On the status page of the secondary EICAS display, make sure that the MAN
XFLOW and the R XFLOW ON status indications are not shown.
(14) On the FUEL synoptic display, make sure that the right shutoff valve is shown in the
closed position and its green flow line is not shown.

Subtask 28−00−00−710−006
E. Continue the operational test of the fuel system as follows:
(1) Before proceeding with the operational test of the gravity−crossflow shutoff valve
(written as the "shutoff valve" in this procedure), make sure of the following
conditions:
(a) On the status page of the secondary EICAS display, make sure that the FUEL
CH 1 FAIL and the FUEL CH 2 FAIL status indications are not shown.
(b) On the primary EICAS display, make sure that the FUEL IMBALANCE caution
indication is not shown.
(2) On the FUEL control panel, push in the GRAVITY XFLOW switch/light. Make sure
that the OPEN light comes on and that the FAIL light does not come on.

Master
EFFECTIVITY: See Pageblock 28−00−00 page 501
28−00−00 Page 507
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
(3) Make sure that the results that follow also occur:
(a) On the FUEL synoptic display of the EICAS, make sure that the shutoff valve
outline is shown in white. Make also sure that the shutoff valve is shown in the
open position and its flow line in green.
(b) On the status page of the secondary EICAS display, make sure that the GRAV
XFLOW OPEN advisory indication is shown.
(4) On the FUEL control panel, push out the GRAVITY XFLOW switch/light. Make sure
that the OPEN light goes off.
(a) On the FUEL synoptic display, make sure that the shutoff valve outline is
shown in the closed position and its green flow line is not shown.
(b) On the status page of the secondary EICAS display, make sure that the GRAV
XFLOW OPEN advisory indication is not shown.

Subtask 28−00−00−710−007
F. Continue the operational test of the fuel system as follows:
(1) On the refuel/defuel control panel installed in the right fuselage, forward of the wing
root, push and hold the BITE INITIA. button. Make sure that there are no fault
codes shown on the fuel quantity indicators.

4. Close Out
Subtask 28−00−00−410−002
A. Close the access doors that follow:
ACCESS DESIGNATION
162AB Fuel/defuel control panel door
811 Main avionics compartment door

Subtask 28−00−00−861−002
B. Remove the external AC power from the aircraft (Ref. TASK 12−00−07−861−802).

Master
EFFECTIVITY: See Pageblock 28−00−00 page 501
28−00−00 Page 508
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C ALL
FUEL SYSTEM − INSPECTION/CHECK

1. General
A. The maintenance procedures that follow are for the contamination checks of the fuel.
These checks are necessary if the fuel system is refueled with fuel that has
contamination or if a hydraulic leak into a fuel tank is suspected. When a contamination
check is done for the fuel system, also do a contamination check in the systems that
follow:
± Engine equipment (chapter 71)
± Engine fuel system (chapter 73)
± Auxiliary power unit (chapter 49).
B. The maintenance procedures include the necessary checks if it is suspected that the fuel
system has been contaminated by hydraulic fluid. This contamination would be caused
by a break in a hydraulic line located in a fuel tank. These procedures are only
necessary when a hydraulic system has been serviced more than two times between
two consecutive flights while you troubleshoot a hydraulic leak.
C. There are two inspection methods to determine if a hydraulic leakage occurs in a fuel
tank. A visual inspection of a fuel sample from the main tank water drain or a
spectrochemical analysis of fuel tank samples can detect hydraulic contamination.

TASK 28−00−00−210−801
Contamination Check of the Fuel System Components (Water)

1. Job Set−Up Information

Subtask 28−00−00−946−001
A. Reference Information
REFERENCE DESIGNATION
TASK 12−11−28−650−804 Suction Defueling
TASK 28−00−00−910−801 Fuel Safety Precautions
TASK 28−11−00−840−801 Prepare Fuel Tank for Access
TASK 28−11−00−840−802 Removal of Fuel Fumes
TASK 28−23−01−000−801 Removal of the Electric Boost Pump
TASK 28−23−01−400−801 Installation of the Electric Boost Pump

Master
EFFECTIVITY: See Pageblock 28−00−00 page 601
28−00−00 Page 601
Jun 22/2004
 C
AIRCRAFT MAINTENANCE MANUAL
2. Procedure
Subtask 28−00−00−910−007
WARNING: OBEY ALL THE FUEL SAFETY PRECAUTIONS WHEN YOU DO WORK ON THE
FUEL SYSTEM AND/OR A FUEL SYSTEM COMPONENT. IF YOU DO NOT DO
THIS, YOU CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO
EQUIPMENT.
A. Obey all the fuel safety precautions (Ref. TASK 28−00−00−910−801).

Subtask 28−00−00−210−001
B. Do a contamination check of the fuel system as follows:
(1) Remove the two boost pumps (Ref. TASK 28−23−01−000−801).
(2) Do an inspection for corrosion in the boost pump.

Subtask 28−00−00−110−001
C. If corrosion is found, do the steps that follow as soon as possible:
(1) Defuel the aircraft TASK 12−11−28−650−804).
(2) Prepare all of the fuel tanks for access (Ref. TASK 28−11−00−840−801).
(3) Remove the fuel fumes from all of the fuel tanks (Ref. (Ref. TASK
28−11−00−840−802)).
(4) Do a visual inspection of all of the fuel tanks and the fuel system components.
(5) Remove, disassemble, and clean, or remove and replace the fuel system
components, as necessary.
(6) If necessary, clean the fuel tanks with a soft brush and lint free cloth.
(7) Flush the fuel lines with clean fuel.

3. Close Out
Subtask 28−00−00−410−001
A. Install the two boost pumps TASK 28−23−01−400−801).

Master
EFFECTIVITY: See Pageblock 28−00−00 page 601
28−00−00 Page 602
Jun 22/2004
 C
AIRCRAFT MAINTENANCE MANUAL
TASK 28−00−00−210−802
Contamination Check of the Fuel System Components (Hydraulic Fluid)

1. Job Set−Up Information

Subtask 28−00−00−946−003
A. Reference Information
REFERENCE DESIGNATION
TASK 12−11−28−650−801 Automatic Pressure Refueling
TASK 12−11−28−650−804 Suction Defueling
TASK 20−22−00−220−802 Inspection Requirements for Damaged Tubing
TASK 20−22−00−910−802 Repairs of Hydraulic and Pneumatic Tubing −
Deutsch Permaswage Fittings
TASK 28−00−00−910−801 Fuel Safety Precautions
TASK 28−11−00−840−801 Prepare Fuel Tank for Access
TASK 28−11−01−000−802 Removal of the Aluminum Access Panel
TASK 28−11−01−400−802 Installation of the Aluminum Access Panel
TASK 29−10−00−617−801 Flush Hydraulic System No. 1
TASK 29−10−00−617−802 Flush Hydraulic System No. 2
TASK 29−10−00−617−803 Flush Hydraulic System No. 3
TASK 49−10−00−000−801 Removal of the APU
TASK 49−10−00−400−801 Installation of the APU
TASK 49−10−00−800−801 APU Start Sequence
TASK 49−10−00−800−803 APU Stop Sequence (Normal)
TASK 49−30−00−790−801 APU Fuel and Oil Leak Check
TASK 49−31−01−000−801 Removal of the Fuel Control Unit (FCU)
TASK 49−31−01−400−801 Installation of the Fuel Control Unit (FCU)
TASK 49−31−03−000−801 Removal of the Fuel Filter Element
TASK 49−31−03−400−801 Installation of the Fuel Filter Element
TASK 49−31−05−000−801 Removal of the APU Fuel Solenoid Shutoff Valve
TASK 49−31−05−400−801 Installation of the APU Fuel Solenoid Shutoff
Valve
TASK 49−31−11−000−801 Removal of the APU Fuel Flow Dividers
TASK 49−31−11−400−801 Installation of the APU Fuel Flow Dividers
TASK 71−00−00−710−808 Engine Power Assurance Check
TASK 71−00−00−868−806 Engine Start
TASK 71−00−00−868−807 Engine Shutdown (Normal)
TASK 71−00−00−868−812 Engine Wet Motor Cycle
TASK 72−00−00−200−802 On−Aircraft Borescope Inspection of the Engine
and its Components
TASK 73−11−01−000−801 Removal of the Fuel Pump
TASK 73−11−01−400−801 Installation of the Fuel Pump
TASK 73−11−03−000−801 Removal of the Fuel Filter

Master
EFFECTIVITY: See Pageblock 28−00−00 page 601
28−00−00 Page 603
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

REFERENCE DESIGNATION
TASK 73−11−03−400−801 Installation of the Fuel Filter
TASK 73−21−01−000−801 Removal of the Main Fuel Control
TASK 73−21−01−400−801 Installation of the Main Fuel Control
CMM 49−26−41, Section 49−20−00 APU Hot Section Inspection
SRM 51−23−02 Sealant Repair Procedure
SRM 51−25−34 Integral Fuel Tank Coating

2. Procedure
Subtask 28−00−00−910−008
WARNING: OBEY ALL THE FUEL SAFETY PRECAUTIONS WHEN YOU DO WORK ON THE
FUEL SYSTEM AND/OR A FUEL SYSTEM COMPONENT. IF YOU DO NOT DO
THIS, YOU CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO
EQUIPMENT.
A. Obey all the fuel safety precautions (Ref. TASK 28−00−00−910−801).

Subtask 28−00−00−210−002
B. If there is a suspected hydraulic leak into a fuel tank, get fuel samples from the fuel tank
water drains that are listed in the table that follows:
NOTE: Get the fuel samples from the appropriate wing tank water drains at the end of
the flight, before refueling. Remove enough fuel from the wing tank so that
there is no water or dirt in the samples.
Hydraulic System requiring Wing Tank to be Sampled
frequent/multiple servicing
1 Left Wing (Main) Tank Water Drains
2 Right Wing (Main) Tank Water Drains
3 Left and Right Wing (Main) Tank Water Drains
C. Do a visual inspection of the fuel samples.
D. Do a Spectrochemical Analysis (ASTM D3605 or D5708) of the fuel samples to measure
phosphorous content in the wing tank.
NOTE: If a hydraulic system requires frequent servicing but no hydraulic fluid is visible
in the fuel samples taken from the water drains, it is recommended to do a
Spectrochemical Analysis to measure phosphorous content in the wing tank.
When the results are determined, do the appropriate steps that follow for the
phosphorus contamination found in the fuel.
E. If the phosphorous content of all the fuel samples is < 20 PPM (0.002% mass) but one
fuel sample is > 5 PPM (0.0005% mass), return the aircraft to service and monitor the
hydraulic fluid consumption for that system.
NOTE: A contamination level of 5 PPM indicates a tube defect small enough that it
would be difficult to locate.

Master
EFFECTIVITY: See Pageblock 28−00−00 page 601
28−00−00 Page 604
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
F. If the phosphorous content of all fuel samples is < 100 PPM (0.01% mass) but at least
one fuel sample reads > 20 PPM (0.002% mass) or if hydraulic fluid accumulation is
visible in the fuel sample do the steps that follow:
(1) Defuel the affected tank (Ref. TASK 12−11−28−650−804).
(2) To inspect the applicable fuel tank do the steps that follow:
(a) Prepare the fuel tank for access (Ref. TASK 28−11−00−840−801).
(b) Open all the wing access panels for the fuel tank with the hydraulic leak (Ref.
TASK 28−11−01−000−802).
(c) Inspect the paint and sealant for condition.
NOTE: A hydraulic leak that occurred at the outboard end of the wing may
cause hydraulic fluid to be trapped in the recesses in the wing and
stagnate. Tank sealant and paint exposed to phosphate−ester based
fluid could degrade over time.
(d) Repair all fuel tank paint and sealant defects (Ref SRM 51−25−34) and (Ref.
SRM 51−23−02).
(3) Inspect the hydraulic tubing (Ref. TASK 20−22−00−220−802).
(4) Repair the hydraulic tubing (Ref. TASK 20−22−00−910−802).
(5) Flush the applicable hydraulic system (Ref. TASK 29−10−00−617−801) or (Ref.
TASK 29−10−00−617−802) or (Ref. TASK 29−10−00−617−803).
(6) To clean the applicable fuel tank do the steps that follow:
(a) Wipe dry the areas where hydraulic fluid has collected using a lint free cloth.
(b) Remove the hydraulic fluid accumulated in the recesses with a soft brush
soaked in clean fuel.
(7) Install the applicable fuel tank wing access panels (Ref. TASK
28−11−01−400−802).
(8) To remove the applicable fuel tank of any traces of hydraulic fluid, do the steps that
follow:
(a) Refuel the main tank to its maximum capacity (Ref. TASK
12−11−28−650−801).
(b) Gently shake the wing tips up and down for a one minute period, once an hour,
for the next four hours.
NOTE: The wing tips must not deflect more than 6.0 in. (15.25 cm) up or
down.
(9) Start both engines (Ref. TASK 71−00−00−868−806) and the APU (Ref. TASK
49−10−00−800−801).
(10) Operate both engines at idle and the APU for 15 minutes.
(11) Shutdown both engines (Ref. TASK 71−00−00−868−807) and the APU (Ref. TASK
49−10−00−800−803).
G. If the phosphorous content of any fuel sample is >100 PPM (0.01% mass) but < 350
PPM (0.035% mass), do the steps that follow:
(1) Defuel the affected tank (Ref. TASK 12−11−28−650−804).
(2) To inspect the applicable fuel tank do the steps that follow:

Master
EFFECTIVITY: See Pageblock 28−00−00 page 601
28−00−00 Page 605
Aug 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
(a) Prepare the fuel tank for access (Ref. TASK 28−11−00−840−801).
(b) Open all the wing access panels for the fuel tank with the hydraulic leak (Ref.
TASK 28−11−01−000−802).
(c) Inspect the paint and sealant for condition.
NOTE: A hydraulic leak that occurred at the outboard end of the wing may
cause hydraulic fluid to be trapped in the recesses in the wing and
stagnate. Tank sealant and paint exposed to phosphate−ester based
fluid could degrade over time.
(d) Repair all fuel tank paint and sealant defects (Ref SRM 51−25−34) and (Ref.
SRM 51−23−02).
(3) Inspect the hydraulic tubing (Ref. TASK 20−22−00−220−802).
(4) Repair the hydraulic tubing (Ref. TASK 20−22−00−910−802).
(5) Flush the applicable hydraulic system (Ref. TASK 29−10−00−617−801) or (Ref.
TASK 29−10−00−617−802) or (Ref. TASK 29−10−00−617−803).
(6) To clean the applicable fuel tank do the steps that follow:
(a) Wipe dry the areas where hydraulic fluid has collected using a lint free cloth.
(b) Remove the hydraulic fluid accumulated in the recesses with a soft brush
soaked in clean fuel.
(7) Install the applicable fuel tank wing access panels (Ref. TASK
28−11−01−400−802).
(8) To remove any traces of hydraulic fluid from the applicable fuel tank, do the steps
that follow:
(a) Refuel the main tank to its maximum capacity (Ref. TASK
12−11−28−650−801).
(b) Gently shake the wing tips up and down for a one minute period, once an hour,
for the next four hours.
NOTE: The wing tips must not deflect more than 6.0 in. (15.25 cm) up or
down.
(9) If it is suspected that an engine(s) operated with contaminated fuel, do the steps
that follow:
(a) Get a fuel sample from the affected engine(s).
NOTE: The fuel sample can be taken by removing the fuel filter drain plug.
(b) Do a Spectrochemical Analysis of the fuel sample(s) to determine the
phosphorous content of the fuel in the engine(s).
NOTE: If the phosphorous content of the fuel sample(s) removed from the
fuel filter(s) is < 100 PPM (0.01% mass) no further action is required.
(c) If the phosphorous content of the fuel sample(s) removed from the fuel filter(s)
is > 100 PPM (0.01% mass) do the steps that follow:
NOTE: Contact the engine manufacturer with the details of the hydraulic
leak, the corrective actions to be taken, and the test results of the
Spectrochemical Analysis. Make a request from the manufacturer for
any additional instructions that may be necessary.

Master
EFFECTIVITY: See Pageblock 28−00−00 page 601
28−00−00 Page 606
Aug 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
1 Do an On−Aircraft Borescope Inspection of the Engine and its Components
(Ref. TASK 72−00−00−200−802).
NOTE: Supply pictures of the borescope results to the engine
manufacturer.
2 Disconnect the engine fuel feed line at the engine interface.
3 Do an Engine Wet Motor Cycle to remove the remaining contaminated fuel
from the engine fuel system (Ref. TASK 71−00−00−868−812).
4 Replace the engine Main Fuel Control (Ref. TASK 73−21−01−000−801)
and (Ref. TASK 73−21−01−400−801).
5 Replace the engine fuel pump (Ref. TASK 73−11−01−000−801) and (Ref.
TASK 73−11−01−400−801).
6 Replace the engine fuel filter (Ref. TASK 73−11−03−000−801) and (Ref.
TASK 73−11−03−400−801)
7 Connect the engine fuel feed line at the engine interface.
8 Do an Engine Wet Motor Cycle to check for fuel leaks (Ref. TASK
71−00−00−868−812).
9 Start both engines (Ref. TASK 71−00−00−868−806).
10 Do an engine power assurance check (Ref. TASK 71−00−00−710−808).
NOTE: Both engines must be operated for a minimum of 15 minutes at
idle to ensure that the hydraulic fluid contamination is removed
from the fuel system.
11 Shutdown both engines (Ref. TASK 71−00−00−868−807).
12 Get a fuel sample from the collector tank and wing tank drains of the
affected system and do a Spectrochemical Analysis to ensure that the
phosphorous content is < 100 PPM (0.01% mass).
H. If the phosphorous content of any fuel sample is >350 PPM (0.035% mass), do the steps
that follow:
(1) Defuel the affected tank (Ref. TASK 12−11−28−650−804).
(2) To inspect the applicable fuel tank do the steps that follow:
(a) Prepare the fuel tank for access (Ref. TASK 28−11−00−840−801).
(b) Open all the wing access panels for the fuel tank with the hydraulic leak (Ref.
TASK 28−11−01−000−802).
(c) Inspect the paint and sealant for condition.
NOTE: A hydraulic leak that occurred at the outboard end of the wing may
cause hydraulic fluid to be trapped in the recesses in the wing and
stagnate. Tank sealant and paint exposed to phosphate−ester based
fluid could degrade over time.
(d) Repair all fuel tank paint and sealant defects (Ref SRM 51−25−34) and (Ref.
SRM 51−23−02).
(3) Inspect the hydraulic tubing (Ref. TASK 20−22−00−220−802).
(4) Repair the hydraulic tubing (Ref. TASK 20−22−00−910−802).
(5) Flush the applicable hydraulic system (Ref. TASK 29−10−00−617−801) or (Ref.
TASK 29−10−00−617−802) or (Ref. TASK 29−10−00−617−803).

Master
EFFECTIVITY: See Pageblock 28−00−00 page 601
28−00−00 Page 607
Dec 15/2004
 C
AIRCRAFT MAINTENANCE MANUAL
(6) To clean the applicable fuel tank do the steps that follow:
(a) Wipe dry the areas where hydraulic fluid has collected using a lint free cloth.
(b) Remove the hydraulic fluid accumulated in the recesses with a soft brush
soaked in clean fuel.
(7) Install the applicable fuel tank wing access panels (Ref. TASK
28−11−01−400−802).
(8) To remove any traces of hydraulic fluid from the applicable fuel tank, do the steps
that follow:
(a) Refuel the main tank to its maximum capacity (Ref. TASK
12−11−28−650−801).
(b) Gently shake the wing tips up and down for a one minute period, once an hour,
for the next four hours.
NOTE: The wing tips must not deflect more than 6.0 in. (15.25 cm) up or
down.
(9) If it is suspected that an engine(s) operated with contaminated fuel, do the steps
that follow:
(a) Get a fuel sample from the affected engine(s).
NOTE: The fuel sample can be taken by removing the fuel filter drain plug.
(b) Do a Spectrochemical Analysis of the fuel sample(s) to determine the
phosphorous content of the fuel in the engine(s).
NOTE: If the phosphorous content of the fuel sample(s) removed from the
fuel filter(s) is < 100 PPM (0.01% mass) no further action is required.
(c) If the phosphorous content of the fuel sample(s) removed from the fuel filter(s)
is > 100 PPM (0.01% mass) do the steps that follow:
NOTE: Contact the engine manufacturer with the details of the hydraulic
leak, the corrective actions to be taken, and the test results of the
Spectrochemical Analysis. Make a request from the manufacturer for
any additional instructions that may be necessary.
1 Do an On−Aircraft Borescope Inspection of the Engine and its Components
(Ref. TASK 72−00−00−200−802).
NOTE: Supply pictures of the borescope results to the engine
manufacturer.
2 Disconnect the engine fuel feed line at the engine interface.
3 Do an Engine Wet Motor Cycle to remove the remaining contaminated fuel
from the engine fuel system (Ref. TASK 71−00−00−868−812).
4 Replace the engine Main Fuel Control (Ref. TASK 73−21−01−000−801)
and (Ref. TASK 73−21−01−400−801).
5 Replace the engine fuel pump (Ref. TASK 73−11−01−000−801) and (Ref.
TASK 73−11−01−400−801).
6 Replace the engine fuel filter (Ref. TASK 73−11−03−000−801) and (Ref.
TASK 73−11−03−400−801)
7 Connect the engine fuel feed line at the engine interface.

Master
EFFECTIVITY: See Pageblock 28−00−00 page 601
28−00−00 Page 608
Aug 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
8 Start both engines (Ref. TASK 71−00−00−868−806).
9 Do an Engine Wet Motor Cycle to check for fuel leaks (Ref. TASK
71−00−00−868−812).
10 Do an engine power assurance check (Ref. TASK 71−00−00−710−808).
NOTE: Both engines must be operate for a minimum of 15 minutes at
idle to ensure that the hydraulic fluid contamination is removed
from the fuel system.
11 Shutdown both engines (Ref. TASK 71−00−00−868−807).
(d) If the phosphorous content of any fuel sample is >350 PPM (0.035% mass) but
< 700 PPM (0.07% mass) do the steps that follow to service the APU:
1 Remove the APU from the aircraft (Ref. TASK 49−10−00−000−801).
2 Do a Hot Section Inspection (HSI) (Ref. CMM TASK 49−26−41, Section
49−20−00).
3 Drain the APU of all the residual fuel.
4 Install the APU (Ref. TASK 49−10−00−000−801).
5 Do the APU fuel and oil leak check (Ref. TASK 49−30−00−790−801).
NOTE: The APU must be operated for a minimum of 30 minutes to
ensure that the hydraulic contamination has been removed from
the APU fuel system.
6 Get a fuel sample from the collector tank and wing tank drains of the
affected system and do a Spectrochemical Analysis to ensure that the
phosphorous content is < 100 PPM (0.01% mass).
(e) If the phosphorous content of any fuel sample is > 700 PPM (0.07% mass) do
the steps that follow to service the APU:
1 Remove the APU from the aircraft (Ref. TASK 49−10−00−000−801).
2 Do a Hot Section Inspection (HSI) (Ref. CMM TASK 49−26−41, Section
49−20−00).
3 Drain the APU of all the residual fuel.
4 Replace the APU Fuel Control Unit (FCU) (Ref. TASK 49−31−01−000−801
and (Ref. TASK 49−31−01−400−801).
5 Replace the APU fuel flow dividers (Ref. TASK 49−31−11−000−801) and
(Ref. TASK 49−31−11−400−801)
6 Replace the APU fuel filter element (Ref. TASK 49−31−03−000−801 and
(Ref. TASK 49−31−03−400−801).
7 Replace the packings on the APU fuel solenoid shutoff valve(Ref. TASK
49−31−05−000−801) and (Ref. TASK 49−31−05−400−801)
8 Install the APU (Ref. TASK 49−10−00−000−801).
9 Do the APU fuel and oil leak check (Ref. TASK 49−30−00−790−801).
NOTE: The APU must be operated for a minimum of 30 minutes to
ensure that the hydraulic contamination has been removed from
the APU fuel system.
10 Get a fuel sample from the collector tank and wing tank drains of the
affected system and do a Spectrochemical Analysis to ensure that the

Master
EFFECTIVITY: See Pageblock 28−00−00 page 601
28−00−00 Page 609
Dec 15/2004
 C
AIRCRAFT MAINTENANCE MANUAL
phosphorous content is < 100 PPM (0.01%) mass.

3. Close Out
Subtask 28−00−00−941−001
A. Remove all tools, equipment, and unwanted materials from the area.

Master
EFFECTIVITY: See Pageblock 28−00−00 page 601
28−00−00 Page 610
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C ALL
STORAGE SYSTEM − DESCRIPTION AND OPERATION

1. General
A. The storage system has the fuel tanks, and the components that release pressure from
the fuel tanks and control the movement of fuel. The storage system includes the
systems that follow:
± Fuel tank system (28−11−00)
± Vent system (28−12−00)
± Transfer system (28−13−00).
2. Description
A. Fuel Tank System
(1) The fuel tank system includes the fuel tanks and their related components for
gravity refueling, draining, and fuel flow in each tank. The fuel tank system has two
main tanks, two collector tanks, and one center tank. The main tanks and the center
tank are integral−type tanks. Each main tank is equipped with a fuel drain valve,
water drain valves, one−way flow valves, balancing pipes, and a gravity filler cap.
The center tank has a fuel drain valve, water drain valves, and a gravity filler cap.
B. Vent System
(1) The vent system controls the pressure in the main tanks and the center tank. This
system includes vent lines, shrouds, and check valves. The vent system also
includes relief valves as a safety release in case of fuel tank overpressure.
C. Transfer System
(1) The transfer system moves the fuel from one tank to another for lateral balance of
the aircraft and to supply sufficient fuel for engine feed. It includes ejector pumps,
shutoff valves, and check valves to control the flow of fuel to each tank.
3. Operation
Refer to Figure 1.
A. Fuel Tank System
(1) The main tanks are the primary fuel tanks of the fuel system. The main tanks are
connected to the collector tanks and the center tank through the transfer system.
(2) The collector tanks are fuel reservoirs in the center wing box that are used to supply
the engine fuel−feed system (28−21−00) and the standby fuel−feed system
(28−23−00). Fuel is moved to the collector tanks from their related main tank by the
scavenge ejector.
(3) The center tank is an auxiliary tank that is used to extend the range of the aircraft.
Fuel from this tank is moved to the main tanks through the transfer system.
(4) The main tanks and the center tank are refueled through the pressure refuel/defuel
system (28−25−00).
B. Vent System
(1) The fuel tanks are pressurized through an air scoop at the lower trailing edge of
each wing. In flight, the ram air effect at the air scoop supplies a small amount of
pressure in the tanks for tank pressurization. This pressure is supplied to each of
the tanks through vent lines.

Master
EFFECTIVITY: See Pageblock 28−10−00 page 1
28−10−00 Page 1
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
(2) There are four inverted U−shapes in the vent lines in the center fuselage to stop
fuel flow in the lines. Two of the U−shaped lines are the climb vent lines. The other
two U−shaped lines are the main vents. Any fuel in the main vent lines is sucked by
the left hand or right hand scavenge ejector through a check valve.
C. Transfer System
(1) Fuel is moved in the fuel tanks through five different functions as follows:
(a) Fuel is moved from the center tank to the main tank by the transfer function.
Fuel is moved by the transfer ejector pumps and the transfer−ejector shutoff
valves in the center tank.
(b) Fuel is moved from the main tanks to the collector tanks by the gravity feed
function through the gravity feed lines. Gravity feed is controlled by check
valves which prevent reverse flow in these lines.
(c) Fuel is moved from the main tanks to the collector tanks by the scavenge
function. This function uses the aft scavenge−ejector pumps in the main tanks.
(d) Fuel is moved between the main tanks by the power fuel−crossflow function.
This function uses the fuel−crossflow shutoff valves and the APU fuel pump in
the center wing box.
(e) Fuel is moved between the main tanks by the gravity fuel−crossflow function.
Fuel moves from one main tank to the other through the gravity−crossflow
shutoff valve.
(2) The transfer of fuel from the center tank to the main tanks, and the power fuel
crossflow between the main tanks are automatically controlled by the fuel
quantity−gauging system (28−41−00). In case of a failure, the power fuel−crossflow
function and the gravity fuel−crossflow function are operated manually. The
scavenge function is controlled automatically by the motive−flow feed system
(28−22−00). The gravity feed function operates independently by gravity.

Master
EFFECTIVITY: See Pageblock 28−10−00 page 1
28−10−00 Page 2
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

28−25−00
REFUEL/ VENT
DEFUEL
LEFT MAIN TANK

28−41−00
TRANSFER
FUEL QTY
FUNCTION
INDICATING

28−22−00 GRAVITY
MOTIVE SCAVENGE
FEED
FLOW FUNCTION
FUNCTION

28−21−00
ENGINE CENTER
TANK VENT
FUEL
FEED
COLLECTOR
TANK
28−23−00 GRAVITY POWER
STANDBY FUEL FUEL
FUEL XFLOW XFLOW
FEED FUNCTION FUNCTION
COLLECTOR
TANK
28−21−00
28−25−00
ENGINE
REFUEL/
FUEL
DEFUEL
FEED

28−22−00 GRAVITY
MOTIVE SCAVENGE
FEED
FLOW FUNCTION
FUNCTION

28−41−00
TRANSFER
FUEL QTY
FUNCTION
INDICATING ram2810000_001(1).dg, pb, 11/03/93

RIGHT MAIN TANK

28−25−00
REFUEL/ VENT
DEFUEL

Storage System − Block Diagram

Figure 1

Master
EFFECTIVITY: See Pageblock 28−10−00 page 1
28−10−00 Page 3
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C ALL
FUEL TANK SYSTEM − DESCRIPTION AND OPERATION

1. General
A. The fuel tank system has the physical structure of the fuel tanks and their related
components. The fuel tank system includes the components that follow:
± Two main tanks
± One center tank
± Two wing−tank gravity filler−caps
± One center−tank gravity filler−cap
± Two wing−tank adapter assemblies
± One center−tank adapter assembly
± Two collector tanks
± Two collector−tank check valves
± Thirty−two fuel−tank access panels
± Eight balancing pipes
± Thirty one−way flow valves
± Two restrictors
± Three fuel drain valves
± Fourteen water drain valves.
2. Component Details
A. Main Tank
Refer to Figure 1.
(1) The main tanks are integral−type fuel tanks that use the wet−wing design and are
the primary supply of the fuel system. The main tanks are contained in the structure
of the applicable wing and are sealed with fuel−resistant sealants.
(2) Each main fuel tank is formed by the structural members that follow:
± Front and rear wing spars
± Upper and lower wing skin panels
± Wing ribs
± Bulkhead of the center wing box.
(3) Each main tank is divided into 14 compartments. Access is supplied into each
compartment through the fuel−tank access panels on the lower wing skin.
B. Center Tank
Refer to Figure 1.
(1) The center tank is an integral−type fuel tank that uses the wet−wing design. This
fuel tank is used to extend the range of the aircraft. The center tank is contained in
the structure of the center wing box and is sealed with fuel−resistant sealants.
(2) The center tank is formed by the bulkheads of the center wing box and is divided
into four compartments. Access is supplied into each compartment through the
fuel−tank access panels on the lower wing skin.

Master
EFFECTIVITY: See Pageblock 28−11−00 page 1
28−11−00 Page 1
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
C. Wing−Tank Gravity Filler−Cap
Refer to Figure 1.
(1) The wing−tank gravity filler−caps are bayonet−type, sealed caps that are used to
close the wing−tank adapter assembly. They are located at the center of each
upper wing skin.
(2) Each gravity filler cap for the wing tank has a latch, a retainer, a seal, a cap plug,
and a bayonet fitting. To open the gravity filler cap, the operator lifts the latch which
releases the seal in the main tank. The operator then turns the cap plug until the
bayonet fitting disengages the adapter assembly. The cap plug is then removed
from the adapter assembly for gravity refueling.
D. Center−Tank Gravity Filler−Cap
(1) The gravity filler cap for the center tank operates in the same way as the gravity
filler cap for the wing tank. It is located on an inboard part of the upper wing skin of
the right wing below an access panel.
E. Wing−Tank Adapter Assembly
(1) The wing−tank adapter assemblies are structural refuel ports that let the operator
gravity refuel the main tanks. They are installed on the upper wing surface. The
adapter assemblies for the main tanks are installed aligned with the upper wing
skin.
(2) Each adapter assembly has a bayonet fitting and a refuel port. The bayonet fitting
connects to the bayonet fitting of the applicable gravity filler cap. When the cap is
removed, fuel can be supplied to the tanks through the refuel port. For the adapter
assembly of the center tank, all fuel that is fallen around the refuel port is drained
through the overspill drain line.
F. Center−Tank Adapter Assembly
(1) The center−tank adapter assembly operates in the same way as the wing−tank
adapter assembly. It is located on an inboard part of the upper wing skin of the right
wing, installed in a recessed port. The recessed port has an overspill drain line to
drain all fuel that is fallen around the center−tank adapter assembly during
refueling.
G. Collector Tank
Refer to Figure 1.
(1) The collector tanks are composite containers located in the forward section of the
center wing box. They are used to keep a full supply of fuel for the engines at all
aircraft attitudes.
(2) Each collector tank has two inlet ports (for fuel gravity supply and fuel scavenge
supply), four outlet ports (for fuel overflow, water drain, primary ejector feed, and
boost pump feed), and an internal filter screen. Fuel flows into the collector tank
through the gravity−feed manifold port and the scavenge manifold port. Because
this supply is more than what is necessary for engine feed, there is a buildup of fuel
pressure. This fuel pressure is released through the fuel overflow port. The overflow
port lets unwanted fuel drain back into the main tank. The fuel that stays in the
collector tank flows through the filter screen where it can flow into the
primary−ejector feed port or the boost−pump feed port.
(3) When the aircraft is not in use, all water or other contamination in the collector tank
collect at the bottom. From the bottom of the collector tank, they flow out through

Master
EFFECTIVITY: See Pageblock 28−11−00 page 1
28−11−00 Page 2
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
the water drain port.
H. Collector−Tank Check Valve
Refer to Figure 1.
(1) The collector−tank check valves are flapper−type valves that prevent opposite fuel
flow out of the collector tanks. They are located in the collector tanks, connected to
the gravity feed manifolds.
(2) Each collector−tank check valve has a swing assembly and a bracket. The bracket
holds the swing assembly in position on the open port of the gravity feed manifold.
Fuel in the gravity feed manifold pushes against the swing assembly, which lets the
fuel flow into the collector tank. In case of reverse flow, the fuel in the collector tank
pushes the swing assembly closed, and closes the port of the gravity feed manifold.
I. Fuel−Tank Access Panel
(1) The fuel−tank access panels are flush−mounted sealed−panel assemblies. There
are two types of fuel−tank access panels: 27 graphite panels and 5 honeycomb
panels. All of the fuel−tank access panels are located on the lower skin of the wings
and the center wing box.
(2) Each graphite panel has a pre−impregnated polyester panel, a graphite outer door
assembly, and a rubber seal. When the graphite panel is installed, it makes a
fuel−tight seal between the polyester panel and the outer door.
(3) Each honeycomb panel has a honeycomb−core inner door, a knitted wire gasket,
and a sealing ring. When the honeycomb panel is installed, it makes a fuel−tight
seal between the inner door and the sealing ring.
J. Balancing Pipe
Refer to Figure 2.
(1) The balancing pipes are structural tubes that are installed in the main tanks and are
used to control the flow of fuel in the main tanks during aircraft maneuvers. They
are installed through the internal bulkheads of the main tanks to let fuel flow
between different sections of the fuel tank.
K. One−Way Flow Valve
Refer to Figure 2.
(1) The one−way flow valves are flapper−type check valves that let fuel flow inboard in
the main tanks, but prevent flow of fuel outboard. They are located in the main
tanks, attached to the lower ribs.
(2) Each one−way flow valve has a swing assembly and a bracket. The bracket holds
the swing assembly in position on the lightening holes in the lower ribs. As fuel
flows from the outboard section of the main tanks to the inboard sections, the fuel
pushes against the swing assembly. When the swing assembly opens, fuel flows
through the lightening hole. In case of reverse flow, the fuel in the main tank pushes
the swing assembly closed and closes the lightening hole.
L. Restrictor
Refer to Figure 2.
(1) The restrictors are bulkhead−mounted flow restrictors that keep fuel pressure in the
collector tanks, but let unwanted fuel to flow out. They are installed on the bulkhead
between the center wing box and the applicable main tank. The restrictors are
connected to the end of the collector−tank overflow lines.

Master
EFFECTIVITY: See Pageblock 28−11−00 page 1
28−11−00 Page 3
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
(2) Each restrictor has a bulkhead mounting plate and a restrictor union. The open
diameter of the restrictor union is smaller than the output end of the collector−tank
overflow line.
M. Fuel Drain Valve
Refer to Figure 3.
(1) The fuel drain valves are manually−operated, spring−loaded poppet valves that are
used to remove fuel from the fuel tanks. There is one fuel drain valve located in the
center tank and each of the main tanks.
(2) Each fuel drain valve has a plug, a poppet, a spring, and a valve body. To open the
fuel drain valve, an operator removes the plug from the lower wing skin and puts an
adapter into the poppet. This pushes the poppet up which opens the passage in the
valve body. When the valve opens, fuel flows through the valve and out of the fuel
tank. When the operator removes the adapter, the spring pushes the valve poppet
back into position and closes the valve.
N. Water Drain Valve
Refer to Figure 3.
(1) The water drain valves are manually−operated, spring−loaded poppet valves that
are used to remove water and other contamination from the fuel tanks. They are
located on the lower wing skin at the low points of each fuel tank. The water drain
valves are located as follows:
± Four water drain valves are installed in each main tank
± Two water drain valves are installed in the center tank
± Two water drain valves are installed at the end of the water drain lines from the
collector tanks
± Two water drain valves are installed in the pickup assemblies of the electric
boost pumps.
(2) The water drain valves for the collector tanks and the pickup assemblies are
installed in the center wing box.
(3) Each water drain valve has a poppet, a spring, and a valve body. To open the water
drain valve, an operator puts a tool into the poppet on the lower wing skin. This
pushes the poppet up which opens the passage in the valve body and lets water or
other contamination flow through the valve and out of the fuel tank. When the
operator removes the tool, the spring pushes the valve poppet back into position
and closes the valve.
3. Operation
Refer to Figure 4.
A. The fuel tank system holds the fuel in the fuel system. The physical structure of the fuel
tanks has two main tanks, two collector tanks, and a center tank. The main tanks are the
primary supply of fuel in the system, and constantly supply fuel to the collector tanks.
The collector tanks are extensions of the main tanks and are kept at full capacity by the
transfer system. Fuel is supplied to the collector tanks at a higher rate than can be used
by the engines. As a result, a full supply is available to the engines at all aircraft
attitudes.
B. The center tank is an auxiliary fuel tank and is used to extend the aircraft range. The fuel
system computer controls the transfer system to move fuel from the center tank to the

Master
EFFECTIVITY: See Pageblock 28−11−00 page 1
28−11−00 Page 4
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
main tanks.
C. The main and center tanks have fuel−tank access panels that are a part of the tanks. All
of the fuel−tank access panels are in the lower wing skin.
D. The center tank and each main tank have components to add fuel, remove fuel, and
drain water. The wing−tank and center−tank gravity filler−caps seal the adapter
assemblies that are used for over−the−wing gravity refueling. The fuel drain valves
permit the tanks to be gravity drained, or permit unwanted fuel to be drained after the
aircraft has been suction defueled. The water drain valves permit fuel samples to be
removed from the fuel tank to examine the fuel for water or other contamination.
E. The main tank also has one−way flow valves and balancing pipes that are used to
control the shift of fuel in the main tank during flight. The one−way flow valves let fuel
flow inboard through the internal main tank bulkheads, but do not let fuel flow back
outboard. This supplies a stable flow of fuel to the inboard sections of the main tank
where it can be moved into the collector tanks by the transfer system. The balancing
pipes let fuel move through the main tanks during refueling and decrease the flow of fuel
to the wingtips during an aircraft climb.
F. The collector tanks are connected to water drain valves, collector−tank check valves,
and restrictors. The water drain valves are used to remove fuel samples from the
collector tanks to examine the fuel for water. They are also used to drain the fuel from
the collector tanks after the aircraft has been defueled. During usual operation, the
collector tanks are supplied with more fuel than is used by the engines, which supplies a
positive fuel pressure in the collector tanks. To control this pressure, overflow lines with
restrictors let a controlled flow of fuel to flow back to the main tanks. The collector−tank
check valves prevent gravity fuel flow from the collector tanks to the main tanks.
4. Component Location Index
Refer to Figure 5.
COMPONENT NAME QTY ACCESS/ZONE REFERENCE
Access panel, fuel tank 34 Lower wing surface 28−11−01
Assembly, adapter 3 Upper wing surface 28−11−23
Cap, center tank gravity filler 1 Upper wing surface 28−11−20
Cap, wing tank gravity filler 2 Upper wing surface 28−11−17
Check valve, collector tank 2 510AB, 610AB 28−11−05
Pipe, balancing 8 540EB, 540FB, 640EB, 28−11−27
640FB
Restrictor 2 510BB, 610BB 28−11−10
Tank, collector 2 510AB, 610AB 28−11−03
Valve, fuel drain 3 540BB, 510AB, 640BB 28−11−14
Valve, one−way flow, at WS85.5 14 540CB, 540DB, 640CB, 28−11−07
640DB
Valve, one−way flow, at WS148.0 14 540FB, 550AB, 640FB, 28−11−07
650AB
Valve, one−way flow, at WS220.0 2 550DB, 550CB, 650DB, 28−11−07
650CB
Valve, water drain, center wing box 6 510AB, 610AB 28−11−13

Master
EFFECTIVITY: See Pageblock 28−11−00 page 1
28−11−00 Page 5
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

COMPONENT NAME QTY ACCESS/ZONE REFERENCE

Valve, water drain, at WS48.0 2 540AB, 640AB 28−11−13
Valve, water drain, at WS69.0 2 540CB, 640CB 28−11−13
Valve, water drain, at WS88.5 2 540DB, 640DB 28−11−13
Valve, water drain, at WS151.0 2 550AB, 650AB 28−11−13

Master
EFFECTIVITY: See Pageblock 28−11−00 page 1
28−11−00 Page 6
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

MAIN TANK

B
A

CENTER TANK

MAIN TANK

GRAVITY FILLER CAP

B
AND ADAPTER ASSEMBLY

C
ram2811000_003(1).dc, dm/gg, 08/08/95

A COLLECTOR TANK

COLLECTOR TANK
C CHECK VALVE

Fuel Tank System − Component Location/Recognition

Figure 1

Master
EFFECTIVITY: See Pageblock 28−11−00 page 1
28−11−00 Page 7
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

BALANCING PIPE

A B

BALANCING PIPE

ram2811000_004.dc RF/DM, 26/06/91

A ONE−WAY FLOW VALVE B RESTRICTOR

Fuel Tank System Movement Provisions − Component Location/Recognition

Figure 2

Master
EFFECTIVITY: See Pageblock 28−11−00 page 1
28−11−00 Page 8
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

FUEL DRAIN VALVE

ram2811000_005.dc, pb, 20/08/92

WATER DRAIN VALVE

Fuel Tank System Drain Valves − Component Location/Recognition

Figure 3

Master
EFFECTIVITY: See Pageblock 28−11−00 page 1
28−11−00 Page 9
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

BALANCING RESTRICTOR FUEL COLLECTOR

PIPE DRAIN TANK CHECK
VALVE VALVE

ONE−WAY ONE−WAY
COLLECTOR COLLECTOR FLOW
FLOW TANK TANK
VALVES VALVES

MAIN MAIN
TANK WATER DRAIN TANK
GRAVITY VALVES GRAVITY
FILLER FILLER
CAP CENTER TANK CAP
GRAVITY
FILLER CAP

FUEL FUEL WATER

DRAIN DRAIN DRAIN
VALVE VALVE VALVES

ram2811000_001(1).dc, gd, 11/03/93

Fuel Tank System − Schematic

Figure 4

Master
EFFECTIVITY: See Pageblock 28−11−00 page 1
28−11−00 Page 10
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

610BB 610AB 510AB

640BB 540BB
640AB
640CB
540DB
640DB
550DB
650DB

540FB 540EB 510BB 540AB 540CB

640FB 640EB

NOTE
500 series panels are on the left side.
600 series panels are on the right side.

ram2811000_002(2).dg, kms/pm, 04/02/99

Fuel Tank System − Component Access

Figure 5

Master
EFFECTIVITY: See Pageblock 28−11−00 page 1
28−11−00 Page 11
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C ALL
FUEL TANK SYSTEM − MAINTENANCE PRACTICES

1. General
A. The maintenance procedures that follow are maintenance practices for the fuel tanks.
The procedures include the maintenance practices that follow:
± Preparation of the fuel tank for access
± Removal of fuel fumes
± Biocide treatment of the fuel tanks.
Prepare the fuel tank and remove the fuel fumes before you do maintenance in a fuel
tank.

TASK 28−11−00−840−801
Prepare Fuel Tank for Access

1. Job Set−Up Information

Subtask 28−11−00−943−001
A. Tools and Equipment
REFERENCE DESIGNATION
G601R280001−001 Kit, breathing apparatus
4552693 MiniWarn B Kit (gas detector)

Subtask 28−11−00−944−001
B. Consumable Materials
REFERENCE DESIGNATION
05−001A Cloth, cotton, low−lint
05−042 Sponge, natural

Subtask 28−11−00−946−001
C. Reference Information
REFERENCE DESIGNATION
TASK 12−11−28−650−804 Suction Defueling
TASK 12−11−28−650−805 Gravity Defueling
TASK 28−00−00−910−801 Fuel Safety Precautions
TASK 28−11−00−840−802 Removal of Fuel Fumes
TASK 28−11−01−000−801 Removal of the Honeycomb Access Panel
TASK 28−11−01−000−802 Removal of the Graphite Access Panel
TASK 28−11−01−400−801 Installation of the Honeycomb Access Panel
TASK 28−11−01−400−802 Installation of the Graphite Access Panel

Master
EFFECTIVITY: See Pageblock 28−11−00 page 201
28−11−00 Page 201
Mar 15/2005
 C
AIRCRAFT MAINTENANCE MANUAL
2. Job Set−Up
Subtask 28−11−00−910−001
WARNING: OBEY ALL THE FUEL SAFETY PRECAUTIONS WHEN YOU DO WORK ON THE
FUEL SYSTEM AND/OR A FUEL SYSTEM COMPONENT. IF YOU DO NOT DO
THIS, YOU CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO
EQUIPMENT.
A. Obey all the fuel safety precautions (Ref. TASK 28−00−00−910−801).

Subtask 28−11−00−040−001
B. Disconnect all ac and dc electrical power to the aircraft. Put a DO NOT CONNECT −
FUEL TANK MAINTENANCE placard on the ground power receptacles.
C. Disconnect the battery. Put a DO NOT CONNECT − FUEL TANK MAINTENANCE
placard on the battery.

**ON A/C 7004−7019, 7021−7044, 7046, 7048, 7050, 7052, 7055−7056, 7059, 7061−7064,
7066−7067, 7069−7070, 7072−7073, 7075−7077, 7079−7080, 7085−7086, 7088−7094,
7099−7106, 7108−7111, 7113−7117, 7119, 7121−7123, 7125, 7127−7143, 7145−7152, 7154,
7156−7159, 7162−7163, 7165, 7167−7169, 7171−7176, 7178−7181, 7185−7196, 7199−7200,
7202−7222, 7224−7233, 7235−7236, 7238−7271, 7273−7294 Pre SB601R−24−090

Subtask 28−11−00−865−001
D. Open, safety, and tag the circuit breakers that follow:
CB PANEL CB NO. NAME ZONE
CBP−1 M6 L FUEL PUMP 221
CBP−1 M7 L FUEL PUMP CONT 221
CBP−1 M8 X/FLOW SOV 221
CBP−1 S1 FUEL SOV R ENG 221
CBP−1 S2 FUEL SOV L ENG 221
CBP−1 M12 FUEL SYST CONT 221
CBP−1 N10 XFER/APU FUEL PUMP 221
CBP−1 N11 XFER/APU CONT 221
CBP−1 N12 XFER/APU APU ECU 221
CBP−2 G10 R FUEL PUMP 222
CBP−2 G11 R FUEL PUMP CONT 222
CBP−4 B9 GRAV XFLOW 222
CBP−4 B10 FUEL SYST CONT 222
CBP−5 B14 FUEL DEFL 311
CBP−5 B15 EMRG REFL 311

Master
EFFECTIVITY: See Pageblock 28−11−00 page 201
28−11−00 Page 202
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C 7003, 7020, 7045, 7047, 7049, 7051, 7053−7054, 7057−7058, 7060, 7065, 7071, 7074,
7078, 7081−7084, 7087, 7095−7098, 7107, 7112, 7118, 7120, 7124, 7126, 7144, 7153, 7155,
7160−7161, 7164, 7166, 7170, 7177, 7182−7184, 7197−7198, 7201, 7223, 7234, 7237, 7272,
7295−7990, 8000−8064, 8066−8068 and ON A/C 7004−7019, 7021−7044, 7046, 7048, 7050,
7052, 7055−7056, 7059, 7061−7064, 7066−7067, 7069−7070, 7072−7073, 7075−7077,
7079−7080, 7085−7086, 7088−7094, 7099−7106, 7108−7111, 7113−7117, 7119, 7121−7123,
7125, 7127−7143, 7145−7152, 7154, 7156−7159, 7162−7163, 7165, 7167−7169, 7171−7176,
7178−7181, 7185−7196, 7199−7200, 7202−7222, 7224−7233, 7235−7236, 7238−7271,
7273−7294 Post SB601R−24−090

Subtask 28−11−00−865−003
E. Open, safety, and tag the circuit breakers that follow:
CB PANEL CB NO. NAME ZONE
CBP−1 M6 L FUEL PUMP 221
CBP−1 M7 L FUEL PUMP CONT 221
CBP−1 M8 X/FLOW SOV 221
CBP−1 S1 FUEL SOV R ENG 221
CBP−1 S2 FUEL SOV L ENG 221
CBP−1 M12 FUEL SYST CONT 221
CBP−1 N10 XFER/APU FUEL PUMP 221
CBP−1 N11 XFER/APU CONT 221
CBP−1 N12 XFER/APU APU ECU 221
CBP−2 G10 R FUEL PUMP 222
CBP−2 G11 R FUEL PUMP CONT 222
CBP−4 B9 GRAV XFLOW 222
CBP−4 B10 FUEL SYST CONT 222
CBP−5 B6 FUEL DEFL 311
CBP−5 B7 EMRG REFL 311

**ON A/C ALL

Subtask 28−11−00−650−001
F. Remove the fuel from the fuel tanks (Ref. TASK 12−11−28−650−804).
G. Drain the remaining fuel from the fuel tanks (Ref. TASK 12−11−28−650−805).

Subtask 28−11−00−840−001
H. Remove the fuel fumes from the fuel tanks (Ref. TASK 28−11−00−840−802).

Master
EFFECTIVITY: See Pageblock 28−11−00 page 201
28−11−00 Page 203
Dec 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
3. Procedure
Subtask 28−11−00−840−002
A. Prepare the fuel tank for access as follows:
(1) Before you use the breathing apparatus, examine the breathing apparatus for good
condition.
(2) Remove the applicable access panel to do work in the fuel tank (Ref. TASK
28−11−01−000−801 or TASK 28−11−01−000−802).
(3) If you go fully into the fuel tank, make sure that there is an observer to monitor
persons in the fuel tank. Make sure that the observer uses a breathing apparatus.
(4) Use cotton cloths or a natural sponge to soak up the remaining fuel. Put the fuel
from the cloths or the sponge into the non−static fuel container. Put the cloths or the
sponge in the fuel container. Count each cloth or sponge to make sure that you do
not let the cloths or sponges stay in the fuel tank.
(5) Clean the cloths or the sponge in water and let them dry. Discard the cloths or the
sponge. Discard the fuel.
(6) Connect the explosion−proof lights to the electrical power before you put the lights
in the fuel tank or use explosion−proof flashlights. Use only explosion−proof drop
cords in the fuel tank.
WARNING: DO NOT USE STEEL WOOL OF ANY TYPE IN THE FUEL TANKS.
PIECES OF STEEL WOOL CAN BREAK OFF AND CAUSE DAMAGE
OR AN EXPLOSION IF THEY TOUCH ELECTRICAL COMPONENTS.
(7) Put all the tools in a non−static container with rounded corners. Keep all your tools
in the container when they are not used.
(8) Continue to remove fuel fumes from the fuel tank. If you do work in the fuel tank,
continue to use the breathing apparatus.
(9) Use the gas detector to find the fuel−fume concentration in the tank. Do not remove
the breathing apparatus until the gas detector shows a fuel−fume concentration
lower than the safe limit.
WARNING: DO NOT USE AN AIR BLOWER UNTIL THE GAS DETECTOR SHOWS
25 PERCENT OR LESS OF THE LOWER EXPLOSIVE LIMIT. HIGHER
FUEL−FUME CONCENTRATIONS CAN CAUSE EXPLOSIONS.
(10) To use an air blower in the fuel tank, do the steps that follow:
NOTE: An air blower is not necessary, but it makes the work easier for the
persons in the fuel tank.
(a) Make sure that there is no dirt or dust in the hose of the air blower.
(b) Start the air blower.
(c) Put the hose in the fuel tank near the persons in the fuel tank.

Master
EFFECTIVITY: See Pageblock 28−11−00 page 201
28−11−00 Page 204
Aug 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
4. Close Out
Subtask 28−11−00−941−001
A. When all maintenance is completed, do the steps that follow:
(1) Remove the blower hose from the fuel tank.
(2) Stop the blower.
(3) Remove all the tools and equipment from the fuel tanks.
(4) Install all of the applicable fuel−tank access panels (Ref. TASK 28−11−01−400−801
or TASK 28−11−01−400−802).

Subtask 28−11−00−440−001
B. Connect the battery. Remove the DO NOT CONNECT − FUEL TANK MAINTENANCE
placard from the battery.

**ON A/C 7004−7019, 7021−7044, 7046, 7048, 7050, 7052, 7055−7056, 7059, 7061−7064,
7066−7067, 7069−7070, 7072−7073, 7075−7077, 7079−7080, 7085−7086, 7088−7094,
7099−7106, 7108−7111, 7113−7117, 7119, 7121−7123, 7125, 7127−7143, 7145−7152, 7154,
7156−7159, 7162−7163, 7165, 7167−7169, 7171−7176, 7178−7181, 7185−7196, 7199−7200,
7202−7222, 7224−7233, 7235−7236, 7238−7271, 7273−7294 Pre SB601R−24−090

Subtask 28−11−00−865−002
C. Close the circuit breakers that follow:
CB PANEL CB NO. NAME ZONE
CBP−1 M6 L FUEL PUMP 221
CBP−1 M7 L FUEL PUMP CONT 221
CBP−1 M8 X/FLOW SOV 221
CBP−1 S1 FUEL SOV R ENG 221
CBP−1 S2 FUEL SOV L ENG 221
CBP−1 M12 FUEL SYST CONT 221
CBP−1 N10 XFER/APU FUEL PUMP 221
CBP−1 N11 XFER/APU CONT 221
CBP−1 N12 XFER/APU APU ECU 221
CBP−2 G10 R FUEL PUMP 222
CBP−2 G11 R FUEL PUMP CONT 222
CBP−4 B9 GRAV XFLOW 222
CBP−4 B10 FUEL SYST CONT 222
CBP−5 B14 FUEL DEFL 311
CBP−5 B15 EMRG REFL 311

Master
EFFECTIVITY: See Pageblock 28−11−00 page 201
28−11−00 Page 205
Aug 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C 7003, 7020, 7045, 7047, 7049, 7051, 7053−7054, 7057−7058, 7060, 7065, 7071, 7074,
7078, 7081−7084, 7087, 7095−7098, 7107, 7112, 7118, 7120, 7124, 7126, 7144, 7153, 7155,
7160−7161, 7164, 7166, 7170, 7177, 7182−7184, 7197−7198, 7201, 7223, 7234, 7237, 7272,
7295−7990, 8000−8064, 8066−8068 and ON A/C 7004−7019, 7021−7044, 7046, 7048, 7050,
7052, 7055−7056, 7059, 7061−7064, 7066−7067, 7069−7070, 7072−7073, 7075−7077,
7079−7080, 7085−7086, 7088−7094, 7099−7106, 7108−7111, 7113−7117, 7119, 7121−7123,
7125, 7127−7143, 7145−7152, 7154, 7156−7159, 7162−7163, 7165, 7167−7169, 7171−7176,
7178−7181, 7185−7196, 7199−7200, 7202−7222, 7224−7233, 7235−7236, 7238−7271,
7273−7294 Post SB601R−24−090

Subtask 28−11−00−865−004
D. Close the circuit breakers that follow:
CB PANEL CB NO. NAME ZONE
CBP−1 M6 L FUEL PUMP 221
CBP−1 M7 L FUEL PUMP CONT 221
CBP−1 M8 X/FLOW SOV 221
CBP−1 S1 FUEL SOV R ENG 221
CBP−1 S2 FUEL SOV L ENG 221
CBP−1 M12 FUEL SYST CONT 221
CBP−1 N10 XFER/APU FUEL PUMP 221
CBP−1 N11 XFER/APU CONT 221
CBP−1 N12 XFER/APU APU ECU 221
CBP−2 G10 R FUEL PUMP 222
CBP−2 G11 R FUEL PUMP CONT 222
CBP−4 B9 GRAV XFLOW 222
CBP−4 B10 FUEL SYST CONT 222
CBP−5 B6 FUEL DEFL 311
CBP−5 B7 EMRG REFL 311

**ON A/C ALL

Subtask 28−11−00−941−002
E. Remove all tools, equipment, and unwanted materials from the area.

Master
EFFECTIVITY: See Pageblock 28−11−00 page 201
28−11−00 Page 206
Dec 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
TASK 28−11−00−840−802
Removal of Fuel Fumes

1. Job Set−Up Information

Subtask 28−11−00−943−006
A. Tools and Equipment
REFERENCE DESIGNATION
G670−281102−1 Outboard Fuel−Tank Venting Kit
G670−281103−1 Inboard Fuel−Tank Venting Kit
4552693 MiniWarn B Kit (gas detector)

Subtask 28−11−00−946−002
B. Reference Information
REFERENCE DESIGNATION
TASK 28−00−00−910−801 Fuel Safety Precautions
TASK 28−11−01−000−802 Removal of the Graphite Access Panel

2. Job Set−Up
Subtask 28−11−00−910−002
WARNING: OBEY ALL THE FUEL SAFETY PRECAUTIONS WHEN YOU DO WORK ON THE
FUEL SYSTEM AND/OR A FUEL SYSTEM COMPONENT. IF YOU DO NOT DO
THIS, YOU CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO
EQUIPMENT.
A. Obey all the fuel safety precautions (Ref. TASK 28−00−00−910−801).

Subtask 28−11−00−010−002
B. To prepare the fuel tank for the removal of fumes, do the steps that follow (Ref. TASK
28−11−01−000−802):
(1) For the main tanks, remove one access panel at the wing root and one access
panel at the wingtip.
(2) For the center tank, remove one access panel from each side of the center wing
box.

3. Procedure
Subtask 28−11−00−840−003
A. Remove the fuel fumes from the fuel tank as follows:
(1) Put a portable air compressor more than 100 feet (30 m) from the aircraft.
(2) Connect the portable air compressor to the same ground as the aircraft.

Master
EFFECTIVITY: See Pageblock 28−11−00 page 201
28−11−00 Page 207
Mar 15/2005
 C
AIRCRAFT MAINTENANCE MANUAL
(3) Install the outboard fuel−tank venting kit on the outboard access panel opening.
NOTE: The fuel tank venting−kit pushes clean air through the fuel tank and out of
the other access panel opening.
(4) Install the inboard fuel−tank venting kit on the inboard access panel opening.
(5) Connect the air hose from the portable air compressor to the inlet adapter of the
fuel tank venting−kit.
WARNING: MAKE SURE THAT ALL EQUIPMENT IS CLEAR OF THE AIR MOVER
EXHAUST−DUCT. AIRFLOW FROM THE AIR MOVER CAN CAUSE
STATIC ELECTRICITY. THIS CAN CAUSE AN EXPLOSION.
(6) Connect the exhaust hose to the outlet adaptor of the fuel tank venting−kit.
(7) Put the exhaust hose outside in the open air.
WARNING: IF THE INDICATOR NEEDLE ON THE GAS DETECTOR INCREASES
TO THE TOP OF THE SCALE, TURN THE INSTRUMENT SWITCH TO
"OFF". FUEL−FUME MIXTURES AT THIS CONCENTRATION ARE
VERY DANGEROUS. EXPLOSIONS CAN OCCUR IN THE CHAMBER
OF THE GAS DETECTOR.
(8) After 30 minutes, put the sampling line from the gas detector far into the fuel tank
from the access opening. Follow the manufacturer’s instructions to measure the
fuel−fume concentration.
(9) Do not do maintenance in the fuel tank until the gas detector shows that the
fuel−fume concentration is less than the lower explosive limit.
(10) Continue to regularly measure the fuel−fume concentration while work is done in
the fuel tank.
WARNING: MAKE SURE THAT THERE ARE NO PERSONS IN THE FUEL TANK IF
THE FUEL−FUME CONCENTRATION IS MORE THAN THE LOWER
EXPLOSIVE LIMIT. INJURIES TO PERSONS CAN OCCUR.
(11) If the fuel−fume concentration increases more than the lower explosive limit,
remove all persons from the fuel tank.

Master
EFFECTIVITY: See Pageblock 28−11−00 page 201
28−11−00 Page 208
Mar 15/2005
 C
AIRCRAFT MAINTENANCE MANUAL
TASK 28−11−00−620−801
Biocide Treatment of the Fuel Tanks
1. General
A. The maintenance procedure that follows is applicable only if no biocide fuel additive is
already present in the fuel system. The procedure is necessary to sterilize (shock
treatment) and keep (regular maintenance) the fuel system clean from the biological
contamination as a result of the microbial growth of the fungi and bacteria in the fuel.
These fungi grow into long strings and form large mats or globules.
NOTE: To most effectively control biological contamination, remove all the water and
debris from the fuel system before, and regularly after, the biocide treatment.
The water in the fuel tanks will cause the formation of solids.
NOTE: The maintenance procedure for the shock treatment and the regular
maintenance is identical (unless otherwise indicated). The shock treatment is
necessary when the microbial growth is first found in the fuel tanks. The
regular maintenance is then applied as a preventive measure, for new fuel
tanks or when the aircraft is scheduled to operate in very hot climatic
conditions.
NOTE: After a shock treatment, a fuel sample is taken to check for water, biological
growth, and corrosion particle contamination. Dying microorganisms may
release particles of dirt and corrosion that have been caught in the mats. Slime
will come off the fuel tank wall and structure as it is killed. If slime, biological
growth, or corrosion particle contaminants are found in the fuel, the fuel
system and components are inspected.
NOTE: For Biobor JF, the concentrations of biocide fuel additive are given as parts per
million (ppm) by weight. The maximum allowable concentration of the biocide
fuel additive is 270 ppm.
NOTE: For Biobor JF, to avoid the formation of solids, do not let the concentration of
biocide fuel additive be more than 1000 ppm at any time.
NOTE: For Biobor JF, to be most effective, let the biocide fuel additive stay in the fuel
tanks for a period of 36 to 72 hours.
NOTE: You may do the biocide treatment only in the main tanks, only if the center
tank never contained fuel.
NOTE: Fuel containing biocide fuel additive can be used for operation as specified in
the Flight Crew Operating Manual (FCOM).

2. Job Set−Up Information

Subtask 28−11−00−943−003
A. Tools and Equipment
REFERENCE DESIGNATION
Model 600 Metered Injection System−Fuel Additive,
Hammonds Fuel Additive Inc.
None specified Soft bristle brush

Master
EFFECTIVITY: See Pageblock 28−11−00 page 201
28−11−00 Page 209
Dec 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
Subtask 28−11−00−944−002
B. Consumable Materials
REFERENCE DESIGNATION
17−001 Fuel additive, biocide
17−001A Fuel additive, biocide

Subtask 28−11−00−946−003
C. Reference Information
REFERENCE DESIGNATION
TASK 12−11−28−280−801 Microbial Growth Test
TASK 12−11−28−650−801 Automatic Pressure Refueling
TASK 12−11−28−650−804 Suction Defueling
TASK 12−11−28−650−805 Gravity Defueling
TASK 12−11−28−750−805 Fuel Check for Particle Contamination
TASK 28−00−00−210−801 Contamination Check of the Fuel System
Components
TASK 28−11−01−400−801 Installation of the Honeycomb Access Panel
TASK 28−11−01−400−802 Installation of the Graphite Access Panel
TASK 49−31−03−000−801 Removal of the APU Fuel−Filter Element
TASK 49−31−03−400−801 Installation of the APU Fuel−Filter Element
TASK 73−11−05−000−801 Removal of the Fuel−Filter Element
TASK 73−11−05−400−801 Installation of the Fuel−Filter Element

3. Job Set−Up
Subtask 28−11−00−280−002
A. Do the microbial growth test (Ref. TASK 12−11−28−280−801).

Subtask 28−11−00−280−004
B. If microbial growth is detected, sterilize (shock treatment) the fuel system with the
following concentration of biocide fuel additive, as applicable:
± For Biobor JF, sterilize the fuel system with the shock treatment concentration of 270
ppm of biocide fuel additive.
± For Kathon FP 1.5, sterilize the fuel system with the concentration as per the
manufacturer’s instruction.

Master
EFFECTIVITY: See Pageblock 28−11−00 page 201
28−11−00 Page 210
Dec 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
Subtask 28−11−00−280−003
C. If no microbial growth is detected, as a preventive measure, sterilize (regular
maintenance) the fuel system with the following concentration of biocide fuel additive to
keep the fuel system clean:
± For Biobor JF, sterilize the fuel system with the shock treatment concentration of 135
ppm of biocide fuel additive.
± For Kathon FP 1.5, sterilize the fuel system with the concentration as per the
manufacturer’s instruction.

Subtask 28−11−00−840−005
D. For Biobor JF, to calculate the correct amount of biocide additive for the applicable
method do one of the steps that follow:
(1) To make an estimate of the fluid ounces necessary to get a concentration of 270
ppm of the additive, multiply the mass of the fuel in pounds (lbs), by 0.004 (one
U.S. gallon of biocide fuel additive for 5,000 U.S. gallons of untreated fuel).
(2) To make an estimate of the milliliters (ml) necessary to get a concentration of 270
ppm of the additive, multiply the mass of the in kilograms (kg), by 0.0536 (one liter
(L) of biocide fuel additive for 4,730 L of untreated fuel).
(3) To make an estimate of the fluid ounces necessary to get a concentration of 135
ppm of the additive, multiply mass of the fuel in pounds (lbs), by 0.002 (one U.S.
gallon of biocide fuel additive for 10,000 U.S. gallons of untreated fuel).
(4) To make an estimate of the milliliters (ml) necessary to get a concentration of 135
ppm of the additive, multiply the mass of the fuel in kilograms (kg), by 0.0268 (one
liter (L) of biocide fuel additive for 9,640 L of untreated fuel).
FUEL QUANTITY BIOBOR JF ADDITIVE (270 PPM)
Gallons Gallons Ounces Ounces
Pounds Kilos Liters Pounds Kilos Milliliters
(U.S.) (Imp.) (U.S.) (Imp.)
685 310.71 100 83.26 378.54 0.18 0.08 2.74 2.85 81.03
1370 621.43 200 166.53 757.08 0.37 0.16 5.48 5.70 162.11
2055 932.14 300 249.80 1135.62 0.56 0.25 8.22 8.55 243.09
2740 1242.86 400 333.06 1514.16 0.74 0.33 10.96 11.40 324.12
3425 1553.58 500 416.33 1892.70 0.93 0.42 13.70 14.25 405.15
5480 2485.72 800 666.13 3028.32 1.49 0.67 21.92 22.81 648.25
6850 3107.16 1000 832.67 3785.40 1.87 0.84 27.40 28.51 810.31
13700 6214.32 2000 1665.34 7570.80 3.74 1.69 54.80 57.03 1620.62
14385 6525.05 2100 1748.61 7949.34 3.93 1.78 57.54 59.89 1701.66
15070 6835.75 2200 1831.88 8327.88 4.12 1.86 60.28 62.70 1782.69

FUEL QUANTITY BIOBOR JF ADDITIVE (135 PPM)

Gallons Gallons Ounces Ounces
Pounds Kilos Liters Pounds Kilos Milliliters
(U.S.) (Imp.) (U.S.) (Imp.)
685 310.71 100 83.26 378.54 0.087 0.03 1.37 1.42 40
1370 621.43 200 166.53 757.08 0.18 0.08 2.74 2.85 80

Master
EFFECTIVITY: See Pageblock 28−11−00 page 201
28−11−00 Page 211
Dec 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL

FUEL QUANTITY BIOBOR JF ADDITIVE (135 PPM)

2055 932.14 300 249.80 1135.62 0.28 0.12 4.11 4.27 120
2740 1242.86 400 333.06 1514.16 0.36 0.16 5.48 5.70 160
3425 1553.58 500 416.33 1892.70 0.46 0.20 6.85 7.12 200
5480 2485.72 800 666.13 3028.32 0.74 0.33 10.96 11.40 320
6850 3107.16 1000 832.67 3785.40 0.93 0.42 13.70 14.25 400
13700 6214.32 2000 1665.34 7570.80 1.87 0.84 27.40 28.51 810
14385 6525.05 2100 1748.61 7949.34 1.96 0.88 28.77 29.94 850
15070 6835.75 2200 1831.88 8327.88 2.05 0.92 30.14 31.37 890

4. Procedure
WARNING: OBEY THE PRECAUTIONS THAT FOLLOW WHEN YOU USE A FUEL ADDITIVE:
± USE APPROVED EYE, MOUTH, AND BODY PROTECTION.
± DO THE WORK IN AN AREA THAT HAS A GOOD FLOW OF CLEAN AIR.
± MAKE SURE THAT THE AREA HAS NO SPARKS, FLAMES, OR HOT
SURFACES.
± OBEY THE MANUFACTURER’S INSTRUCTIONS.
± DO NOT LET THE FUEL ADDITIVE TOUCH YOUR SKIN, EYES, OR MOUTH.
± IF IRRITATION OCCURS, GET MEDICAL AID IMMEDIATELY.
FUEL ADDITIVES ARE POISONOUS AND CAN CAUSE DAMAGE TO SKIN, EYE,
AND LUNG TISSUE.
Subtask 28−11−00−650−002
NOTE: Two methods are given to add the biocide fuel additive to the fuel tanks. The metered
injection is the preferred method. The batch blending method may be used as an
alternative.
A. Metered Injection
(1) Make sure that the fuel tanks have less than 500 lbs of fuel before introducing the
biocide treatment, and that this remaining amount of fuel is considered in the
mixture calculation to obtain the necessary biocide concentration. If necessary,
adjust the fuel quantity as follows, as applicable:
± Do a suction defueling (Ref. TASK 12−11−28−650−804)
± Do a gravity defueling (Ref. TASK 12−11−28−650−805).
CAUTION: DO NOT PUT THE FUEL ADDITIVE DIRECTLY INTO THE FUEL
TANKS. HIGH CONCENTRATIONS OF THE FUEL ADDITIVE CAN
CAUSE SALT PARTICLES IN THE FUEL TANK.
(2) For Biobor JF, do the steps that follow:
(a) Add the biocide fuel additive to the fuel stream at a rate of 270 ppm (shock
treatment) or 135 ppm (regular maintenance). Fully refuel the aircraft.
(b) If possible, let the biocide fuel additive stay in the fuel tanks for a period of 36
to 72 hours.

Master
EFFECTIVITY: See Pageblock 28−11−00 page 201
28−11−00 Page 212
Dec 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
(3) For Kathon FP 1.5, do the steps that follow:
(a) Add the biocide fuel additive to the fuel stream as per the manufacturer’s
instructions.
(b) Let the biocide fuel additive stay in the fuel tanks for a period of time per the
manufacturer’s instructions.
(4) Remove the APU fuel−filter element (Ref. TASK 49−31−03−000−801).
(5) Install a new APU fuel−filter element (Ref. TASK 49−31−03−400−801).
(6) Remove the engine fuel−filter element (Ref. TASK 73−11−05−000−801).
(7) Install a new engine fuel−filter element (Ref. TASK 73−11−05−400−801).
B. Batch Blending
(1) Make sure that the fuel tanks have less than 500 lbs of fuel before introducing the
biocide treatment, and that this remaining amount of fuel is considered in the
mixture calculation to obtain the necessary biocide concentration. If necessary,
adjust the fuel quantity as follows, as applicable:
± Do a suction defueling (Ref. TASK 12−11−28−650−804)
± Do a gravity defueling (Ref. TASK 12−11−28−650−805).
(2) For Biobor JF, do the steps that follow:
(a) Calculate the amount of biocide fuel additive required to prepare a batch with a
concentration of 270 ppm (shock treatment) or 135 ppm (regular
maintenance).
(b) Use a large container free of dirt, water or other contaminants. Fill the
container one half full with the fuel first, then continue to add fuel and the
biocide fuel additive at the same time to ensure proper dispersion and dilution.
NOTE: To ensure the proper dilution of the biocide fuel additive, a tank truck
may be required for the mixing.
(c) Make sure that you fully refuel the aircraft to ensure complete sterilization.
(d) If possible, let the biocide fuel additive stay in the aircraft fuel tanks for a period
of 36 to 72 hours.
(e) Do the Inspection After Biocide Treatment.
(3) For Kathon FP 1.5, do the steps that follow:
(a) Calculate the amount of biocide fuel additive required to prepare a batch per
the manufacturer’s instructions.
(b) Use a large container free of dirt, water or other contaminants. Fill the
container one half full with the fuel first, then continue to add fuel and the
biocide fuel additive at the same time to ensure proper dispersion and dilution.
NOTE: To ensure the proper dilution of the biocide fuel additive, a tank truck
may be required for the mixing.
(c) Make sure that you fully refuel the aircraft to ensure complete sterilization.
(d) If possible, let the biocide fuel additive stay in the aircraft fuel tanks for a period
of time per the manufacturer’s instructions.
(e) Do the Inspection After Biocide Treatment.
C. Inspection After Biocide Treatment

Master
EFFECTIVITY: See Pageblock 28−11−00 page 201
28−11−00 Page 213
Dec 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
(1) After the waiting period, do a fuel check for particle contamination. Examine the fuel
sample for water and particle contaminants (Ref: TASK 12−11−28−750−805).
(2) If you do not find any slime, biological growth, or corrosion particles in the removed
fuel, do the steps that follow:
(a) Remove the APU fuel−filter element (Ref. TASK 49−31−03−000−801).
(b) Install a new APU fuel−filter element (Ref. TASK 49−31−03−400−801).
(c) Remove the engine fuel−filter element (Ref. TASK 73−11−05−000−801).
(d) Install a new engine fuel−filter element (Ref. TASK 73−11−05−400−801).
(e) Return the aircraft to service.
NOTE: Fuel containing biocide fuel additive can be used for operation as
specified in the Flight Crew Operating Manual (FCOM).
(3) If slime, biological growth, or corrosion particle contaminants are found in the
removed fuel, do the steps that follow:
(a) Do a contamination check of the fuel system components (Ref: TASK
28−00−00−210−801).
(b) Clean the biological contaminant accumulation from the fuel tank structure and
fuel system components as necessary with a soft bristle brush.
(c) Install all of the applicable fuel−tank access panels (Ref. TASK
28−11−01−400−801 or TASK 28−11−01−400−802).
(d) Remove the APU fuel−filter element (Ref. TASK 49−31−03−000−801).
(e) Install a new APU fuel−filter element (Ref. TASK 49−31−03−400−801).
(f) Remove the engine fuel−filter element (Ref. TASK 73−11−05−000−801).
(g) Install a new engine fuel−filter element (Ref. TASK 73−11−05−400−801).
(h) Return the aircraft to service.
NOTE: Fuel containing biocide fuel additive can be used for operation as
specified in the Flight Crew Operating Manual (FCOM).

5. Close Out
Subtask 28−11−00−550−001
CAUTION: DO NOT OPERATE THE ENGINES AND/OR THE APU WHEN THE BIOCIDE
CONCENTRATION IN THE FUEL IS MORE THAN 1000 PPM. A HIGH
CONCENTRATION OF BIOCIDE CAN CAUSE DAMAGE TO THE ENGINES
AND/OR THE APU.
A. After the aircraft has returned to service, do the steps that follow:
(1) Repeat the microbial growth test in the next 500 flight hours (Ref. TASK
12−11−28−280−801).
(2) If the test shows microbial growth, repeat the biocide treatment of the fuel tanks.

Master
EFFECTIVITY: See Pageblock 28−11−00 page 201
28−11−00 Page 214
Dec 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C ALL
FUEL TANK SYSTEM − INSPECTION/CHECK

1. General
A. The procedures that follow are for the inspection/checks of the fuel tank. The checks are
as follows:
± Visual check of the fuel tank exterior
± General visual inspection of the fuel access panels and fuel and water drain valves
± Detailed inspection of the sealant on in−tank LRUs
± Functional check of the critical bonding jumpers
± Detailed inspection of the critical bonding jumpers
± Pressurization of the fuel tanks using shop air
± Leak rate check of the fuel tank.

TASK 28−11−00−210−801
Visual Check of the Fuel Tank Exterior
1. General
A. The procedure that follows is for the inspection of the access panels, the fuel drain
valves, and the water drain valves.

2. Procedure
Subtask 28−11−00−210−001
A. Do a visual check of the access panels, the fuel drain valves, and the water drain valves.

Master
EFFECTIVITY: See Pageblock 28−11−00 page 601
28−11−00 Page 601
Dec 15/2004
 C
AIRCRAFT MAINTENANCE MANUAL
TASK 28−11−00−210−803
General Visual Inspection of the Fuel Access Panels and the Fuel and Water Drain Valves
1. Reason for the Job
Refer to MRB 28−11−00−01.

2. Procedure

Refer to Figure 601 and Figure 602.

Subtask 28−11−00−210−003
A. Do a general visual inspection of the fuel access panels and the fuel drain and water
drain valves for fuel leakage.

Master
EFFECTIVITY: See Pageblock 28−11−00 page 601
28−11−00 Page 602
Aug 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL

192BB

192BR

162AB

610BB 610AB 510BB

640AB 540AB

650FB 550FB

A VIEW LOOKING UP
ram2811006_004.dg, lr , 28/09/04

Fuel Access Panels − General Visual Inspection

Figure 601

Master
EFFECTIVITY: See Pageblock 28−11−00 page 601
28−11−00 Page 603
Dec 15/2004
 C
AIRCRAFT MAINTENANCE MANUAL

VIEW LOOKING UP
OPEN

B WATER DRAIN VALVE

A MAIN−TANK FUEL−DRAIN VALVE

ram2811006_003.dg, lr, 28/09/04

Fuel and Water Drain Valves − General Visual Inspection

Figure 602

Master
EFFECTIVITY: See Pageblock 28−11−00 page 601
28−11−00 Page 604
Dec 15/2004
 C
AIRCRAFT MAINTENANCE MANUAL
TASK 28−11−00−220−801
Detailed Inspection of the Sealant on In−Tank LRUs
1. Reason for the Job
Refer to FSL 28−11−00−603.

2. Job Set_Up Information

Subtask 28−11−00−944−004
A. Consumable Materials
REFERENCE DESIGNATION
09−034 Sealant, fuel tank, low weight

Subtask 28−11−00−946−006
B. Reference Information
REFERENCE DESIGNATION
TASK 28−00−00−910−801 Fuel Safety Precautions
TASK 28−11−01−000−801 Removal of the Honeycomb Access Panel
TASK 28−11−01−000−802 Removal of the Aluminum Access Panel
TASK 28−11−01−400−801 Installation of the Honeycomb Access Panel
TASK 28−11−01−400−802 Installation of the Aluminum Access Panel
TASK 51−23−00−390−804 Bead Seal Sealant Procedure
TASK 51−23−00−390−808 Application of Sealant with Brush

3. Job Set−Up
Subtask 28−11−00−910−006
WARNING: OBEY ALL THE FUEL SAFETY PRECAUTIONS WHEN YOU DO WORK ON
THE FUEL SYSTEM AND/OR A FUEL SYSTEM COMPONENT. IF YOU DO
NOT DO THIS, YOU CAN CAUSE INJURIES TO PERSONS AND/OR
DAMAGE TO EQUIPMENT.
A. Obey all the fuel safety precautions (Ref. TASK 28−00−00−910−801).

Subtask 28−11−00−010−004
B. Remove the access panels that follow (Ref. TASK 28−11−01−000−801 or TASK
28−11−01−000−802):
ACCESS DESIGNATION
510AB Fuel tank access panel
510BB Fuel tank access panel
540AB Fuel tank access panel
540BB Fuel tank access panel
540CB Fuel tank access panel
540DB Fuel tank access panel

Master
EFFECTIVITY: See Pageblock 28−11−00 page 601
28−11−00 Page 605
Aug 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL

ACCESS DESIGNATION
550AB Fuel tank access panel
550BB Fuel tank access panel
550HB Fuel tank access panel
610AB Fuel tank access panel
610BB Fuel tank access panel
640AB Fuel tank access panel
640BB Fuel tank access panel
640CB Fuel tank access panel
640DB Fuel tank access panel
650AB Fuel tank access panel
650BB Fuel tank access panel
650HB Fuel tank access panel

4. Procedure
Subtask 28−11−00−210−002
Refer to Figure 603.
**ON A/C 7003−7031, 7033−7058, 7060−7067, 7069−7124, 7126−7132, 7134−7147, 7149−7204,
7206−7271, 7273−7279, 7282−7287, 7289−7293, 7295−7340, 7342−7345, 7347−7364,
7366−7370, 7372−7401, 7403−7423, 7425−7479, 7481−7489, 7491−7507, 7509−7567,
7570−7581, 7583−7584, 7587−7592, 7594−7602, 7604, 7606−7609, 7611−7718, 7720−7723,
7725−7733, 7735−7743, 7745−7747, 7749−7752, 7754−7765, 7767−7776, 7779−7787,
7789−7803, 7805, 7807−7813, 7815−7817, 7819−7822, 7824−7831, 7833−7834, 7836−7837,
7839−7841, 7843−7853, 7855−7929 Pre SB601R−28−055
Refer to Figure 604.
**ON A/C 7032, 7059, 7125, 7133, 7148, 7205, 7272, 7280−7281, 7288, 7294, 7341, 7346, 7365,
7371, 7402, 7424, 7480, 7490, 7508, 7568−7569, 7582, 7585−7586, 7593, 7603, 7605, 7610,
7719, 7724, 7734, 7744, 7748, 7753, 7766, 7777−7778, 7788, 7804, 7806, 7814, 7818, 7823,
7832, 7835, 7838, 7842, 7854, 7930−7990, 8000−8064, 8066−8068 and ON A/C 7003−7031,
7033−7058, 7060−7067, 7069−7124, 7126−7132, 7134−7147, 7149−7204, 7206−7271,
7273−7279, 7282−7287, 7289−7293, 7295−7340, 7342−7345, 7347−7364, 7366−7370,
7372−7401, 7403−7423, 7425−7479, 7481−7489, 7491−7507, 7509−7567, 7570−7581,
7583−7584, 7587−7592, 7594−7602, 7604, 7606−7609, 7611−7718, 7720−7723, 7725−7733,
7735−7743, 7745−7747, 7749−7752, 7754−7765, 7767−7776, 7779−7787, 7789−7803, 7805,
7807−7813, 7815−7817, 7819−7822, 7824−7831, 7833−7834, 7836−7837, 7839−7841,
7843−7853, 7855−7929 Post SB601R−28−055
Refer to Figure 605.

Master
EFFECTIVITY: See Pageblock 28−11−00 page 601
28−11−00 Page 606
Dec 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C 7003−7031, 7033−7058, 7060−7067, 7069−7124, 7126−7132, 7134−7147, 7149−7204,
7206−7271, 7273−7279, 7282−7287, 7289−7293, 7295−7340, 7342−7345, 7347−7364,
7366−7370, 7372−7401, 7403−7423, 7425−7479, 7481−7489, 7491−7507, 7509−7567,
7570−7581, 7583−7584, 7587−7592, 7594−7602, 7604, 7606−7609, 7611−7718, 7720−7723,
7725−7733, 7735−7743, 7745−7747, 7749−7752, 7754−7765, 7767−7776, 7779−7787,
7789−7803, 7805, 7807−7813, 7815−7817, 7819−7822, 7824−7831, 7833−7834, 7836−7837,
7839−7841, 7843−7853, 7855−7929 Pre SB601R−28−055
Refer to Figure 606.
**ON A/C 7032, 7059, 7125, 7133, 7148, 7205, 7272, 7280−7281, 7288, 7294, 7341, 7346, 7365,
7371, 7402, 7424, 7480, 7490, 7508, 7568−7569, 7582, 7585−7586, 7593, 7603, 7605, 7610,
7719, 7724, 7734, 7744, 7748, 7753, 7766, 7777−7778, 7788, 7804, 7806, 7814, 7818, 7823,
7832, 7835, 7838, 7842, 7854, 7930−7990, 8000−8064, 8066−8068 and ON A/C 7003−7031,
7033−7058, 7060−7067, 7069−7124, 7126−7132, 7134−7147, 7149−7204, 7206−7271,
7273−7279, 7282−7287, 7289−7293, 7295−7340, 7342−7345, 7347−7364, 7366−7370,
7372−7401, 7403−7423, 7425−7479, 7481−7489, 7491−7507, 7509−7567, 7570−7581,
7583−7584, 7587−7592, 7594−7602, 7604, 7606−7609, 7611−7718, 7720−7723, 7725−7733,
7735−7743, 7745−7747, 7749−7752, 7754−7765, 7767−7776, 7779−7787, 7789−7803, 7805,
7807−7813, 7815−7817, 7819−7822, 7824−7831, 7833−7834, 7836−7837, 7839−7841,
7843−7853, 7855−7929 Post SB601R−28−055
Refer to Figure 607.
**ON A/C ALL
A. Do a detailed inspection of the sealant on the in−tank LRU’s (line replaceable unit) as
follows:
(1) Examine the in−tank LRU’s for missing sealant. If necessary, add sealant.
(2) Examine the sealant for cracks, cuts or other damage. If necessary, repair the
sealant.

5. Close Out
Subtask 28−11−00−941−007
A. Remove all tools, equipment, and unwanted materials from the area.

Subtask 28−11−00−410−004
B. Install the applicable access panels that follow (Ref. TASK 28−11−01−400−801) or
(Ref. TASK 28−11−01−400−802):
ACCESS DESIGNATION
510AB Fuel tank access panel
510BB Fuel tank access panel
540AB Fuel tank access panel
540BB Fuel tank access panel
540CB Fuel tank access panel
540DB Fuel tank access panel
550AB Fuel tank access panel
550BB Fuel tank access panel

Master
EFFECTIVITY: See Pageblock 28−11−00 page 601
28−11−00 Page 607
Dec 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL

ACCESS DESIGNATION
550HB Fuel tank access panel
610AB Fuel tank access panel
610BB Fuel tank access panel
640AB Fuel tank access panel
640BB Fuel tank access panel
640CB Fuel tank access panel
640DB Fuel tank access panel
650AB Fuel tank access panel
650BB Fuel tank access panel
650HB Fuel tank access panel

Master
EFFECTIVITY: See Pageblock 28−11−00 page 601
28−11−00 Page 608
Dec 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL

SCUPPER DUCT
DRAIN ASSEMBLY
(REF)
CENTER FUEL
FILLER INSTALLATION
(REF)

LOWER SKIN
(REF)

LOWER
WING SKIN
NOTES
(REF)
Brushcoat sealing.

Fillet sealing. ram2811006_007.dg, rm, 28/04/05

Sealant on In−Tank LRUs − Inspection/Check

Figure 603 (Sheet 1 of 12)

Master
EFFECTIVITY: See Pageblock 28−11−00 page 601
28−11−00 Page 609
Aug 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL

FUEL MAGNETIC
LEVEL INDICATOR
(REF)

LOWER
WING SKIN
(REF)
NOTE
Brushcoat sealing.
ram2811006_008.dg, rm, 20/05/05

TYPICAL

Sealant on In−Tank LRUs − Inspection/Check

Figure 603 (Sheet 2 of 12)

Master
EFFECTIVITY: See Pageblock 28−11−00 page 601
28−11−00 Page 610
Aug 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL

NOTE
Brushcoat sealing.

ram2811006_009.dg, rm, 20/05/05

TYPICAL

Sealant on In−Tank LRUs − Inspection/Check

Figure 603 (Sheet 3 of 12)

Master
EFFECTIVITY: See Pageblock 28−11−00 page 601
28−11−00 Page 611
Aug 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL

NOTE
Brushcoat sealing.

FITTING
(REF)
ram2811006_010.dg, rm, 29/04/05

Sealant on In−Tank LRUs − Inspection/Check

Figure 603 (Sheet 4 of 12)

Master
EFFECTIVITY: See Pageblock 28−11−00 page 601
28−11−00 Page 612
Aug 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL

BL0.00

REAR SPAR
DATUM

WS45.00 WS85.50
WS65.75
WS148.01
FRONT SPAR
DATUM

REAR SPAR
DATUM

WS242.00
WS274.00
WS314.50
WS330.25
FRONT SPAR WS389.00
DATUM

NOTES
ram2811006_011.dg, rm, 04/05/05

The structure is symmetrical

around the aircraft centerline,
unless shown differently.
Brushcoat sealing.

TYPICAL Fillet sealing.

Sealant on In−Tank LRUs − Inspection/Check

Figure 603 (Sheet 5 of 12)

Master
EFFECTIVITY: See Pageblock 28−11−00 page 601
28−11−00 Page 613
Aug 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL

NOTES
Left collector tank is shown.
Right collector tank is opposite.
COLLECTOR
Brushcoat sealing.
TANK
(REF)

COLLECTOR
TANK
(REF)

ram2811006_012.dg, rm, 04/05/05

FITTING
ASSEMBLY
(REF)

Sealant on In−Tank LRUs − Inspection/Check

Figure 603 (Sheet 6 of 12)

Master
EFFECTIVITY: See Pageblock 28−11−00 page 601
28−11−00 Page 614
Aug 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL

NOTES
Brushcoat sealing.

Fillet sealing.

DRAIN
(REF)

ram2811006_013.dg, rm, 06/05/05

Sealant on In−Tank LRUs − Inspection/Check

Figure 603 (Sheet 7 of 12)

Master
EFFECTIVITY: See Pageblock 28−11−00 page 601
28−11−00 Page 615
Aug 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL

NOTES
Brushcoat sealing.

Fillet sealing.

LBL45.00

BOLT
(TYPICAL
4 PLACES) WASHER RBL45.00
(REF) (TYPICAL
4 PLACES)
(REF)
RIB
(REF)

REFUEL
SHUTOFF VALVE
(REF)

PACKING
(REF)

FITTING
(REF) NUT
ram2811006_014.dg, rm, 12/05/05

(REF)

TYPICAL

Sealant on In−Tank LRUs − Inspection/Check

Figure 603 (Sheet 8 of 12)

Master
EFFECTIVITY: See Pageblock 28−11−00 page 601
28−11−00 Page 616
Aug 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL

TRANSFER
EJECTOR PUMP
(REF)

NOTES
Left transfer ejector pump shown,
right transfer ejector pump is opposite.

Brushcoat sealing.

Fillet sealing.

ram2811006_015.dg, rm, 12/05/05

Sealant on In−Tank LRUs − Inspection/Check

Figure 603 (Sheet 9 of 12)

Master
EFFECTIVITY: See Pageblock 28−11−00 page 601
28−11−00 Page 617
Aug 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL

NOTE
Fillet sealing.

REAR SPAR
(REF)

ram2811006_016.dg, rm, 12/05/05

Sealant on In−Tank LRUs − Inspection/Check

Figure 603 (Sheet 10 of 12)

Master
EFFECTIVITY: See Pageblock 28−11−00 page 601
28−11−00 Page 618
Aug 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL

NOTES
Brushcoat sealing. SCAVENGE
EJECTOR
Fillet sealing.
(REF)

TYPICAL
(4 PLACES)

ram2811006_017.dg, rm, 12/05/05

Sealant on In−Tank LRUs − Inspection/Check

Figure 603 (Sheet 11 of 12)

Master
EFFECTIVITY: See Pageblock 28−11−00 page 601
28−11−00 Page 619
Aug 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL

PICKUP COVER
(REF)

GASKET
(REF)

NOTES
Right side is shown,
left side is opposite.

Brushcoat sealing.

BOOST PUMP
CANNISTER
(REF)

ram2811006_018.dg, rm, 12/05/05

TYPICAL
(12 PLACES)

Sealant on In−Tank LRUs − Inspection/Check

Figure 603 (Sheet 12 of 12)

Master
EFFECTIVITY: See Pageblock 28−11−00 page 601
28−11−00 Page 620
Aug 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL

D NOTES
FW
1 Brushcoat sealing.

2 Fillet sealing.

CROSSFLOW
SHUTOFF VALVE
(REF)

TYPICAL
(3 PLACES) 1

D
FW
ram2811006_019.dg, ds/lr, 05/05/05

LEFT SIDE SHOWN

A
RIGHT SIDE OPPOSITE

Sealant on In−Tank LRUs − Inspection/Check

Figure 604

Master
EFFECTIVITY: See Pageblock 28−11−00 page 601
28−11−00 Page 621
Aug 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL

NOTES
1 Brushcoat sealing.

2 Fillet sealing.

D
FW
CROSSFLOW
SHUTOFF VALVE
(REF)

TYPICAL
(3 PLACES) 1
1

D
FW
ram2811006_020.dg, ds/lr, 05/05/05

A LEFT SIDE SHOWN

RIGHT SIDE OPPOSITE

Sealant on In−Tank LRUs − Inspection/Check

Figure 605

Master
EFFECTIVITY: See Pageblock 28−11−00 page 601
28−11−00 Page 622
Aug 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL

D
FW

NOTES
A
1 Brushcoat sealing.

2 Fillet sealing.

TRANSFER
SHUTOFF VALVE
(REF)

TYPICAL
(3 PLACES) 1

D
FW
ram2811006_021.dg, ds/lr, 05/05/05

A RIGHT SIDE SHOWN

LEFT SIDE IS SIMILAR BUT INVERTED

Sealant on In−Tank LRUs − Inspection/Check

Figure 606

Master
EFFECTIVITY: See Pageblock 28−11−00 page 601
28−11−00 Page 623
Aug 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL

D
FW

NOTES
1 Brushcoat sealing.

2 Fillet sealing. A

TRANSFER
SHUTOFF VALVE
(REF)

TYPICAL 1
(3 PLACES) 1

D
FW
ram2811006_022.dg, ds/lr, 05/05/05

A RIGHT SIDE SHOWN

LEFT SIDE IS SIMILAR BUT INVERTED

Sealant on In−Tank LRUs − Inspection/Check

Figure 607

Master
EFFECTIVITY: See Pageblock 28−11−00 page 601
28−11−00 Page 624
Aug 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
TASK 28−11−00−720−801
Functional Check of the Critical Bonding Jumpers
1. Reason for the Job
Refer to FSL 28−11−00−602.

2. Job Set−Up Information

Subtask 28−11−00−943−004
A. Tools and Equipment
REFERENCE DESIGNATION
247001 Digital Low Resistance Ohm Meter (DLRO) −
(120V AC, 50/60Hrz)
M−1 Milliohm Meter, BCD Electronics

Subtask 28−11−00−946−007
B. Reference Information
REFERENCE DESIGNATION
TASK 28−00−00−910−801 Fuel Safety Precautions
TASK 28−11−01−000−801 Removal of the Honeycomb Access Panel
TASK 28−11−01−000−802 Removal of the Aluminum Access Panel
TASK 28−11−01−400−801 Installation of the Honeycomb Access Panel
TASK 28−11−01−400−802 Installation of the Aluminum Access Panel

3. Job Set−Up
Subtask 28−11−00−910−008
WARNING: OBEY ALL THE FUEL SAFETY PRECAUTIONS WHEN YOU DO WORK ON
THE FUEL SYSTEM AND/OR A FUEL SYSTEM COMPONENT. IF YOU DO
NOT DO THIS, YOU CAN CAUSE INJURIES TO PERSONS AND/OR
DAMAGE TO EQUIPMENT.
A. Obey all the fuel safety precautions (Ref. TASK 28−00−00−910−801).

Subtask 28−11−00−010−005
B. Remove the applicable access panels that follow (Ref. TASK 28−11−01−000−801 or
TASK 28−11−01−000−802):
ACCESS DESIGNATION ITEM
510AB Fuel tank access panel L/H Crossflow Check Valve
540AB Fuel tank access panel L/H Wash Filter and Check Valve
610AB Fuel tank access panel R/H Crossflow Check Valve and
APU Fuel Line Check Valve
640AB Fuel tank access panel R/H Wash Filter and Check Valve

Master
EFFECTIVITY: See Pageblock 28−11−00 page 601
28−11−00 Page 625
Aug 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
4. Procedure
Subtask 28−11−00−720−001
Refer to Figure 608
A. Do the functional check of the critical bonding jumpers as follows:
NOTE: When you do a check of resistance values, make sure that the aircraft external
power plug is removed from the aircraft. The readings will not be correct if the
external power plug remains connected.
(1) Connect the ground clip of the bonding tester to a metal surface.
(2) Press the test probe on the metal surface, close to the ground clip. Make sure that
both probe pins make a good electrical contact.
(3) Set the bonding tester to its lowest range and push the TEST switch. See that the
indication reads zero ohms.
(4) Put the ground clip on one end of the bonding jumper and the test probe on the
other end of the bonding jumper.
(5) Read the resistance. The resistance must not be more than 0.01 ohms.

5. Close Out
Subtask 28−11−00−410−005
A. Install the applicable access panels that follow (Ref. TASK 28−11−01−400−801 or TASK
28−11−01−400−802):
ACCESS DESIGNATION ITEM
510AB Fuel tank access panel R/H Crossflow Check Valve
540AB Fuel tank access panel R/H Wash Filter and Check Valve
610AB Fuel tank access panel L/H Crossflow Check Valve and
APU Fuel Line Check Valve
640AB Fuel tank access panel L/H Wash Filter and Check Valve

Subtask 28−11−00−941−008
B. Remove all tools, equipment, and unwanted materials from the area.

Master
EFFECTIVITY: See Pageblock 28−11−00 page 601
28−11−00 Page 626
Aug 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL

BL0.00 LBL22.50 LBL45.00

LEGEND
1. Bonding jumper.
2. Motive flow check−valve.
3. Washfilter.

3
1

A
VIEW LOOKING DOWN ON
LEFT CENTER FUEL TANK
2

ram2811006_005.dg, ds, 23/11/04

NOTE
Left side shown.
Right side opposite.

Critical Bonding Jumper − Inspection/Check

Figure 608 (Sheet 1 of 2)

Master
EFFECTIVITY: See Pageblock 28−11−00 page 601
28−11−00 Page 627
Aug 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL

RBL22.50 BL0.00 LBL22.50

C
REAR SPAR

D
E

LEGEND
1. Bonding jumper.
4. APU feed line check−valve.
5. Crossflow check valve.

C
VIEW LOOKING DOWN ON
CENTER FUEL TANK

LEFT SIDE SHOWN

D
RIGHT SIDE OPPOSITE

1
ram2811006_006.dg, ds, 23/11/04

Critical Bonding Jumper − Inspection/Check

Figure 608 (Sheet 2 of 2)

Master
EFFECTIVITY: See Pageblock 28−11−00 page 601
28−11−00 Page 628
Aug 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
TASK 28−11−00−220−802
Detailed Inspection of the Critical Bonding Jumpers
1. Reason for the Job
Refer to FSL 28−11−00−601.

2. Job Set−Up Information

Subtask 28−11−00−946−008
A. Reference Information
REFERENCE DESIGNATION
TASK 28−00−00−910−801 Fuel Safety Precautions
TASK 28−11−01−000−801 Removal of the Honeycomb Access Panel
TASK 28−11−01−000−802 Removal of the Aluminum Access Panel
TASK 28−11−01−400−801 Installation of the Honeycomb Access Panel
TASK 28−11−01−400−802 Installation of the Aluminum Access Panel

3. Job Set−Up
Subtask 28−11−00−910−009
WARNING: OBEY ALL THE FUEL SAFETY PRECAUTIONS WHEN YOU DO WORK ON
THE FUEL SYSTEM AND/OR A FUEL SYSTEM COMPONENT. IF YOU DO
NOT DO THIS, YOU CAN CAUSE INJURIES TO PERSONS AND/OR
DAMAGE TO EQUIPMENT.
A. Obey all the fuel safety precautions (Ref. TASK 28−00−00−910−801).

Subtask 28−11−00−010−007
B. Remove the applicable access panels that follow: (Ref. TASK 28−11−01−000−801 or
TASK 28−11−01−000−802):
ACCESS DESIGNATION ITEM
510AB Fuel tank access panel L/H Crossflow Check Valve
540AB Fuel tank access panel L/H Wash Filter and Check Valve
610AB Fuel tank access panel R/H Crossflow Check Valve and
APU Fuel Line Check Valve
640AB Fuel tank access panel R/H Wash Filter and Check Valve

4. Procedure
Subtask 28−11−00−220−002
Refer to Figure 609
A. Do the detailed inspection of the critical bonding jumpers as follows:
(1) Examine the critical bonding jumpers for signs of corrosion.
(2) Examine the critical bonding jumpers for damaged or cut strands.

Master
EFFECTIVITY: See Pageblock 28−11−00 page 601
28−11−00 Page 629
Aug 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
(3) Examine both ends of the critical bonding jumpers for missing sealant.

5. Close Out
Subtask 28−11−00−941−009
A. Remove all tools, equipment, and unwanted materials from the area.

Subtask 28−11−00−410−006
B. Install the applicable access panels that follow (Ref. TASK 28−11−01−400−801 or TASK
28−11−01−400−802):
ACCESS DESIGNATION ITEM
510AB Fuel tank access panel R/H Crossflow Check Valve
540AB Fuel tank access panel R/H Wash Filter and Check Valve
610AB Fuel tank access panel L/H Crossflow Check Valve and
APU Fuel Line Check Valve
640AB Fuel tank access panel L/H Wash Filter and Check Valve

Master
EFFECTIVITY: See Pageblock 28−11−00 page 601
28−11−00 Page 630
Aug 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL

BL0.00 LBL22.50 LBL45.00

LEGEND
1. Bonding jumper.
2. Motive flow check−valve.
3. Washfilter.

3
1

A
VIEW LOOKING DOWN ON
LEFT CENTER FUEL TANK
2

ram2811006_005.dg, ds, 23/11/04

NOTE
Left side shown.
Right side opposite.

Critical Bonding Jumper − Inspection/Check

Figure 609 (Sheet 1 of 2)

Master
EFFECTIVITY: See Pageblock 28−11−00 page 601
28−11−00 Page 631
Aug 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL

RBL22.50 BL0.00 LBL22.50

C
REAR SPAR

D
E

LEGEND
1. Bonding jumper.
4. APU feed line check−valve.
5. Crossflow check valve.

C
VIEW LOOKING DOWN ON
CENTER FUEL TANK

LEFT SIDE SHOWN

D
RIGHT SIDE OPPOSITE

1
ram2811006_006.dg, ds, 23/11/04

Critical Bonding Jumper − Inspection/Check

Figure 609 (Sheet 2 of 2)

Master
EFFECTIVITY: See Pageblock 28−11−00 page 601
28−11−00 Page 632
Aug 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
TASK 28−11−00−780−802
Pressurization of the Fuel Tanks Using Shop Air
1. General
A. The procedure that follows is for the pressurization of the fuel tanks with shop air.

2. Job Set−Up Information

Subtask 28−11−00−943−002
A. Tools and Equipment
REFERENCE DESIGNATION
G601R262002−1 Shunt Plug
S601R2811TFIX5 (or equivalent) Fuel Tank Pressurization Test Kit
S601R2821TFIX7 (or equivalent) Dummy Boost Pump
TE−0177−H1 (or equivalent) Air Test Panel

Subtask 28−11−00−946−005
B. Reference Information
REFERENCE DESIGNATION
TASK 12−00−07−861−801 Connect External AC Power
TASK 12−00−07−861−802 Remove External AC Power
TASK 12−11−28−650−804 Suction Defueling
TASK 24−00−00−910−801 Electrical/Electronic Safety Precautions
TASK 26−11−00−710−801 Operational Test of the Engine
Fire/Overheat−Detection System
TASK 26−22−00−710−801 Operational Test of the APU Fire−Extinguishing
System
TASK 28−00−00−910−801 Fuel Safety Precautions

Subtask 28−11−00−910−003
WARNING: OBEY ALL THE FUEL SAFETY PRECAUTIONS WHEN YOU DO WORK ON THE
FUEL SYSTEM AND/OR A FUEL SYSTEM COMPONENT. IF YOU DO NOT DO
THIS, YOU CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO
EQUIPMENT.
C. Obey all the fuel safety precautions (Ref.TASK 28−00−00−910−801).

Subtask 28−11−00−650−003
D. Defuel the aircraft (Ref.TASK 12−11−28−650−804).

Master
EFFECTIVITY: See Pageblock 28−11−00 page 601
28−11−00 Page 633
Aug 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
Subtask 28−11−00−910−005
WARNING: OBEY ALL THE SAFETY PRECAUTIONS WHEN YOU DO MAINTENANCE ON
OR NEAR ELECTRICAL/ELECTRONIC EQUIPMENT. IF YOU DO NOT DO THIS,
YOU CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO THE
EQUIPMENT.
E. Obey all the electrical safety precautions (Ref. TASK 24−00−00−910−801).

3. Job Set−Up
Subtask 28−11−00−865−005
A. Open, safety, and tag the circuit breakers that follow:
CB PANEL CB NO. NAME ZONE
CBP−1 M12 FUEL SYST CONT 221
CBP−1 R5 APU FIRE EXT A 221
CBP−1 R6 APU FIRE EXT B 221
CBP−4 B10 FUEL SYST CONT 222
CBP−5 B6 FUEL DEFL 311
CBP−5 B9 EMERG REFL 311

Subtask 28−11−00−010−003
B. Open the access panels that follow:
ACCESS DESCRIPTION
510AB Center Fuel Tank
510BB Center Fuel Tank
610AB Center Fuel Tank
610BB Center Fuel Tank

Subtask 28−11−00−941−005
C. Prepare the aircraft to do a pressure and leak test of the fuel tanks as follows:
(1) Remove the electrical connector plug from the APU fire−bottle discharge−cartridge.
(2) At the glareshield, push the LH ENG FIRE PUSH and the RH ENG FIRE PUSH to
close the left and right engine fuel feed shut off valves.
(3) At the glareshield, push the APU FIRE PUSH switch/light to close the APU fuel feed
shut off valve.
(4) Remove the external AC power (Ref: TASK 12−00−07−861−802).
NOTE: Make sure that the AC electrical power is OFF at all times when you do
the steps that follow.
(5) Disconnect the NACA scoop fittings (2) at the Wiggins bulkhead fitting on the aft
spar (WS 154).
(6) Install blanking caps at the left and right NACA scoop fittings (2).

Master
EFFECTIVITY: See Pageblock 28−11−00 page 601
28−11−00 Page 634
Aug 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
(7) Make sure that the fuel cap (3) is installed on the gravity refuel adapter.
(8) Blank the left and right boost pump canisters.
NOTE: If the pumps are not installed use the dummy booster pump
(S601R2821TFIX7 or equivalent).
(9) Install the dummy access panel (S601R2811TFIX5 or equivalent) in the center
tank.
(10) Close the shut off valve on the air test panel (TE−0177−H1 or equivalent).
(11) Connect the air test panel (TE−0177−H1 or equivalent) to the shop air.

4. Procedure
Refer to Figure 610.
Subtask 28−11−00−780−001
WARNING: WHEN YOU DO A PRESSURE TEST, KEEP ALL PERSONNEL AWAY FROM
THE AIRCRAFT. THERE IS A RISK OF EXPLOSION OR OTHER INCIDENT. IF
YOU DO NOT DO THIS, YOU CAN CAUSE INJURY TO PERSONS.
CAUTION: DO NOT PRESSURIZE THE FUEL TANKS TO MORE THAN 4.5 PSI (31.0 KPA)
BECAUSE THE FUEL VENT SYSTEM IS CAPPED. IF YOU DO THIS YOU CAN
CAUSE DAMAGE TO THE FUEL TANKS.
A. Do a pressure and leak test of the fuel tanks as follows:
(1) On the air test panel (TE−0177−H1 or equivalent) adjust the regulator to 3.5 psi (24
kPa).
(2) Slowly open the outlet valve on the air test panel (TE−0177−H1 or equivalent) to
pressurize all three tanks to 3.5 psi (24 kPa)
(3) Close the outlet valve on the air test panel (TE−0177−H1 or equivalent).
B. If a leak in the fuel tanks is suspected, do the steps that follow:
(1) Release air pressure from the tank.
(2) Open the input valve to discharge the air pressure from the air test panel
(TE−0177−H1 or equivalent).
(3) Close the input valve on the air test panel (TE−0177−H1 or equivalent).
(4) Open the outlet valve on the air test panel (TE−0177−H1 or equivalent) until the
shop air pressure in the fuel tanks is between 2.5 psi (17 kPa) and 3 psi, (21 kPa).
(5) Close the outlet valve on the air test panel (TE−0177−H1 or equivalent).
(6) Use soap and water to check for leaks in the areas that follow:
(a) all fuel tank exterior surfaces
(b) center fuel tank, rear bulkhead electrical fittings
(c) AHRS flux detector mounting area.
NOTE: All leaks must be noted and repaired.

Master
EFFECTIVITY: See Pageblock 28−11−00 page 601
28−11−00 Page 635
Aug 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
5. Close Out
Subtask 28−11−00−410−001
A. Disconnect the equipment used to leak test the fuel tanks as follows:
(1) De−pressurize the fuel tank.
(2) Turn off the shop air supply and disconnect the bleed air from the tank.
(3) If the dummy booster pump (S601R2821TFIX7 or equivalent) was connected,
disconnect the dummy booster pump.
(4) Disconnect the air test panel (TE−0177−H1 or equivalent).
(5) Remove the dummy access panel (S601R2811TFIX5 or equivalent) and install the
aircraft panel.
(6) At the glareshield, push the LH ENG FIRE PUSH and the RH ENG FIRE PUSH to
open the left and right engine fuel feed shut off valves.
(7) At the glareshield, push the APU FIRE PUSH switch/light to open the APU fuel feed
shut off valve.
(8) Remove the blanking caps at the left and right NACA scoop fittings (2).
(9) Connect the NACA scoops at the Wiggins bulkhead fitting on the aft spar (WS 154).

Subtask 28−11−00−410−003
B. Connect the electrical connector plug to the APU fire−bottle discharge−cartridge.

Subtask 28−11−00−865−006
C. Remove the tags and close the circuit breakers that follow:
CB PANEL CB NO. NAME ZONE
CBP−1 M12 FUEL SYST CONT 221
CBP−1 R5 APU FIRE EXT A 221
CBP−1 R6 APU FIRE EXT B 221
CBP−4 B10 FUEL SYST CONT 222
CBP−5 B6 FUEL DEFL 311
CBP−5 B9 EMERG REFL 311

Subtask 28−11−00−861−001
D. Connect external AC power (Ref. TASK 12−00−07−861−801).

Subtask 28−11−00−710−002
E. Do the operational test of the Engine Fire/Overheat detection system (Ref: TASK
26−11−00−710−801).

Subtask 28−11−00−710−001
F. Do the operational test of the APU Fire−Extinguishing system (Ref. TASK
26−22−00−710−801).

Master
EFFECTIVITY: See Pageblock 28−11−00 page 601
28−11−00 Page 636
Aug 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
Subtask 28−11−00−410−002
G. Close the access panels that follow:
ACCESS DESCRIPTION
510AB Center Fuel Tank
510BB Center Fuel Tank
610AB Center Fuel Tank
610BB Center Fuel Tank

Subtask 28−11−00−941−006
H. Remove all tools, equipment and unwanted materials from the area.

Master
EFFECTIVITY: See Pageblock 28−11−00 page 601
28−11−00 Page 637
Aug 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL

LEGEND
1. Climb vent line.
2. NACA fitting.
3. Fuel cap.
4. Center tank.

1 2

4 2

1
ram2811006_002.dg, rm, 10/07/03

Pressurization of the Fuel Tanks Using Shop Air

Figure 610

Master
EFFECTIVITY: See Pageblock 28−11−00 page 601
28−11−00 Page 638
Aug 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
TASK 28−11−00−790−802
Leak Rate Check of the Fuel Tank
1. General
A. The procedure that follows is for the leak rate check of the fuel tank. Fuel leaks are
divided in four categories: seep, heavy seep, drip and running leak. Each category is
determined by visual examination of wet areas around the leak source.

2. Job Set−Up Information

Subtask 28−11−00−946−004
A. Reference Information
REFERENCE DESIGNATION
TASK 28−00−00−910−801 Fuel Safety Precautions
TASK 12−11−28−650−801 Automatic Pressure Refueling
TASK 51−26−00−910−801 Cleaning Safety Precautions
SRM 51−23−00 Pressure, Environmental and Fuel Tank Sealing

Subtask 28−11−00−944−003
B. Consumable Materials
REFERENCE DESIGNATION
11−018 Solvent, dry cleaning and degreasing
05−073 Powder, talcum
05−001 Cloths, cleaning, low−lint

3. Job Set−Up
Subtask 28−11−00−910−004
WARNING: OBEY ALL THE FUEL SAFETY PRECAUTIONS WHEN YOU DO WORK ON THE
FUEL SYSTEM AND/OR A FUEL SYSTEM COMPONENT. IF YOU DO NOT DO
THIS, YOU CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO
EQUIPMENT.
A. Obey all the fuel safety precautions (Ref. TASK 28−00−00−910−801).
B. Do a check of the amount of the fuel in the tanks and make sure that there is a minimum
of approximately 1000 lb. (453.60 kg.) in each tank.
NOTE: If necessary add fuel to the tanks (Ref. TASK 12−11−28−650−801).

Subtask 28−11−00−110−001
C. Clean the area around the leak source with dry cleaning and degreasing solvent (Ref.
TASK 51−26−00−910−801).
NOTE: Allow one hour for the leak to wet the tank lower surface.

Master
EFFECTIVITY: See Pageblock 28−11−00 page 601
28−11−00 Page 639
Aug 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
4. Procedure
Subtask 28−11−00−790−001
Refer to Figure 611.
A. Carefully examine the lower surface of the tank to find the source of the leak.
B. Carefully blow the talcum powder on the wet area of the leak until the powder clearly
identifies the wet area.
C. Measure the average diameter of the leak area and refer to Table 601 to identify the leak
category:
FUEL LEAKAGE CATEGORY MAXIMUM RATE PERMITTED
SEEP 1.5 inch in any direction.
1.5 inch but not exceeding 3.00 inch in any
HEAVY SEEP
direction.
DRIP Up to four drops per minute.
RUNNING LEAK Exceeding four drops per minute.

Fuel Leakage Category

Table 601

NOTE: The size of the area that is wet from the seep and the heavy seep leaks is
limited by the evaporation of the fuel. This area does not get larger when the
fuel evaporates from the surface at the same rate as the leak rate.

Subtask 28−11−00−360−001
Refer to Table 602 for the repair action.
NOTE: Refer to the SRM, Chapter 51−23−00 for the specific repair procedure.
HEAVY RUNNING
FUEL LEAKAGE LOCATION SEEP DRIP
SEEP LEAK
Exposed, well ventilated locations where
leaking fuel cannot contact an ignition
NOTE 1 NOTE 1 NOTE 2 NOTE 4
source, such as upper and lower wing
surfaces not covered by fairings.
Semi enclosed, partially ventilated
locations such as rear spar at trailing edge NOTE 1 NOTE 2 NOTE 3 NOTE 4
flaps and wheel wells.
Enclosed, unventilated locations such as
wing/body fairings and front spar where NOTE 2 NOTE 3 NOTE 3 NOTE 4
covered by fairings or panels.
Wing leading edge front spar. NOTE 2 NOTE 4 NOTE 4 NOTE 4
Engine pylon. NOTE 4 NOTE 4 NOTE 4 NOTE 4

Fuel Leak Repair Evaluation

Table 602

Master
EFFECTIVITY: See Pageblock 28−11−00 page 601
28−11−00 Page 640
Aug 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL

HEAVY RUNNING
FUEL LEAKAGE LOCATION SEEP DRIP
SEEP LEAK
NOTE: 1. No repair action required. A daily inspection must be made to ensure that leak
category does not change.
NOTE: 2. No immediate repair action required. A daily inspection must be made to ensure leak
category does not change. The leak must be repaired at the next scheduled service
check and within 72 hours of leak discovery.
NOTE: 3. Repair the leak when you get to the operator main facility. Make sure that there is no
structural damage and that it is not possible for the leak to touch an ignition source,
(i.e. very near or above an electrical component, wiring connector, or bleed duct). If it
is possible for the leak to touch or be near an ignition source, repair the leak before
subsequent flight. Daily inspections must be made to ensure leak does not change.
NOTE: 4. Immediate repair action is required.

Fuel Leak Repair Evaluation

Table 602

5. Close−Out
Subtask 28−11−00−941−003
A. Remove all tools, equipment, and unwanted materials from the work area.

Master
EFFECTIVITY: See Pageblock 28−11−00 page 601
28−11−00 Page 641
Aug 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL

1.50 to 3.00 in.

(3.81 to 7.62 cm)

0.750 to 1.50 in.

(1.90 to 3.81 cm) HEAVY SEEP

SEEP

THIS IS THE AREA

WHERE THE FUEL
RUNS OR DRIPS
ram2811006_001.dg, pt, 30/05/94

RUNNING LEAK

Leak Classification of Fuel Tank − Inspection/Check

Figure 611

Master
EFFECTIVITY: See Pageblock 28−11−00 page 601
28−11−00 Page 642
Aug 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C ALL
FUEL TANK − REPAIRS

TASK 28−11−00−390−801
Fuel−Tanks Seal Repair
1. General
A. The procedure that follows is for the repair of the fuel tanks sealant.

2. Procedure
Subtask 28−11−00−390−001
A. To do the repair of the sealant of the fuel tanks, refer to the procedure that is found in
SRM 51−23−00.

Master
EFFECTIVITY: See Pageblock 28−11−00 page 801
28−11−00 Page 801
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C ALL
PANEL, FUEL TANK ACCESS − REMOVAL/INSTALLATION

1. General
A. The maintenance procedures that follow are for the removal and installation of the fuel
tank access panels (written as the "access panels" in this procedure). There are two
types of access panels, the aluminum−honeycomb−core access panels (written as the
"honeycomb access panels" in this procedure) and the aluminum access panels. There
are 5 honeycomb access panels and 27 aluminum access panels installed on the lower
wing skin. A fuel drain valve is found on three of the honeycomb access panels.
B. It is necessary to defuel, drain and remove the fuel fumes from the center tank and the
applicable main tank to remove or install the access panel.

TASK 28−11−01−000−801
Removal of the Honeycomb Access Panel

1. Job Set−Up Information

Subtask 28−11−01−946−001
A. Reference Information
REFERENCE DESIGNATION
TASK 12−11−28−650−804 Suction Defueling
TASK 28−00−00−910−801 Fuel Safety Precautions
TASK 28−11−00−840−801 Prepare Fuel Tank for Access
TASK 28−11−00−840−802 Removal of Fuel Fumes

2. Job Set−Up
Subtask 28−11−01−910−001
WARNING: OBEY ALL THE FUEL SAFETY PRECAUTIONS WHEN YOU DO WORK ON THE
FUEL SYSTEM AND/OR A FUEL SYSTEM COMPONENT. IF YOU DO NOT DO
THIS, YOU CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO
EQUIPMENT.
A. Obey all the fuel safety precautions (Ref. TASK 28−00−00−910−801).

Subtask 28−11−01−650−001
B. Defuel the applicable main tank and the center tank (Ref. TASK 12−11−28−650−804).

Subtask 28−11−01−840−002
C. Prepare the applicable main tank and the center tank for access (Ref. TASK
28−11−00−840−801).
D. Remove the fuel fumes from the applicable main tank and the center tank (Ref. TASK
28−11−00−840−802).

Master
EFFECTIVITY: See Pageblock 28−11−01 page 401
28−11−01 Page 401
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C 7004−7019, 7021−7044, 7046, 7048, 7050, 7052, 7055−7056, 7059, 7061−7064,
7066−7067, 7069−7070, 7072−7073, 7075−7077, 7079−7080, 7085−7086, 7088−7094,
7099−7106, 7108−7111, 7113−7117, 7119, 7121−7123, 7125, 7127−7143, 7145−7152, 7154,
7156−7159, 7162−7163, 7165, 7167−7169, 7171−7176, 7178−7181, 7185−7196, 7199−7200,
7202−7222, 7224−7233, 7235−7236, 7238−7271, 7273−7294 Pre SB601R−24−090

Subtask 28−11−01−865−001
E. Open, safety, and tag the circuit breakers that follow:
CB PANEL CB NO. NAME ZONE
CBP−1 M6 L FUEL PUMP 221
CBP−1 M7 L FUEL PUMP CONT 221
CBP−1 S1 FUEL SOV R ENG 221
CBP−1 S2 FUEL SOV L ENG 221
CBP−1 M12 FUEL SYST CONT 221
CBP−1 N9 XFER/APU XFER SOV 221
CBP−1 N10 XFER/APU FUEL PUMP 221
CBP−1 N11 XFER/APU CONT 221
CBP−1 N12 XFER/APU APU ECU 221
CBP−2 G10 R FUEL PUMP 222
CBP−2 G11 R FUEL PUMP CONT 222
CBP−4 B9 GRAV XFLOW 222
CBP−4 B10 FUEL SYST CONT 222
CBP−5 B14 FUEL DEFL 311
CBP−5 B15 EMRG REFL 311

**ON A/C 7003, 7020, 7045, 7047, 7049, 7051, 7053−7054, 7057−7058, 7060, 7065, 7071, 7074,
7078, 7081−7084, 7087, 7095−7098, 7107, 7112, 7118, 7120, 7124, 7126, 7144, 7153, 7155,
7160−7161, 7164, 7166, 7170, 7177, 7182−7184, 7197−7198, 7201, 7223, 7234, 7237, 7272,
7295−7990, 8000−8064, 8066−8068 and ON A/C 7004−7019, 7021−7044, 7046, 7048, 7050,
7052, 7055−7056, 7059, 7061−7064, 7066−7067, 7069−7070, 7072−7073, 7075−7077,
7079−7080, 7085−7086, 7088−7094, 7099−7106, 7108−7111, 7113−7117, 7119, 7121−7123,
7125, 7127−7143, 7145−7152, 7154, 7156−7159, 7162−7163, 7165, 7167−7169, 7171−7176,
7178−7181, 7185−7196, 7199−7200, 7202−7222, 7224−7233, 7235−7236, 7238−7271,
7273−7294 Post SB601R−24−090

Subtask 28−11−01−865−010
F. Open, safety, and tag the circuit breakers that follow:
CB PANEL CB NO. NAME ZONE
CBP−1 M6 L FUEL PUMP 221
CBP−1 M7 L FUEL PUMP CONT 221
CBP−1 S1 FUEL SOV R ENG 221
CBP−1 S2 FUEL SOV L ENG 221
CBP−1 M12 FUEL SYST CONT 221

Master
EFFECTIVITY: See Pageblock 28−11−01 page 401
28−11−01 Page 402
Dec 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL

CB PANEL CB NO. NAME ZONE

CBP−1 N9 XFER/APU XFER SOV 221
CBP−1 N10 XFER/APU FUEL PUMP 221
CBP−1 N11 XFER/APU CONT 221
CBP−1 N12 XFER/APU APU ECU 221
CBP−2 G10 R FUEL PUMP 222
CBP−2 G11 R FUEL PUMP CONT 222
CBP−4 B9 GRAV XFLOW 222
CBP−4 B10 FUEL SYST CONT 222
CBP−5 B6 FUEL DEFL 311
CBP−5 B7 EMRG REFL 311

**ON A/C 7003−7011, 7013−7021, 7023−7037, 7039, 7041−7049, 7051−7061, 7063−7065, 7069,
7071−7990, 8000−8064, 8066−8068 and ON A/C 7012, 7022, 7038, 7040, 7050, 7062,
7066−7067, 7070 Post SB601R−28−022

Subtask 28−11−01−865−014
G. Also open, safety, and tag the circuit breaker that follows:
CB PANEL CB NO. NAME ZONE
CBP−2 P9 RIGHT FUEL XFER SOV 222

**ON A/C ALL

3. Procedure
Subtask 28−11−01−020−001
Refer to Figure 401.
A. Remove the honeycomb access panel as follows:
(1) Remove the 15 or 19 screws (1), the clamp ring (2) and the knitted wire gasket (3).
NOTE: There are 19 screws (1) installed on the access panel (4) near the
wingtip.
(2) Carefully lift the access panel (4) with the rubber seal (5) and phenolic strip (6). Put
the access panel (4) at an angle and sideways, and lower it through the access
port.

Master
EFFECTIVITY: See Pageblock 28−11−01 page 401
28−11−01 Page 403
Dec 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL

A
6

ACCESS
PORT

4
3

6
1
(TYPICAL
15 PLACES) A 5
RIGHT SIDE IS SHOWN
LEFT SIDE IS OPPOSITE

LEGEND
1. Screw.
2. Clamp ring. 3
ACCESS
3. Knitted wire gasket.
PORT
4. Access panel.
5. Rubber seal. 2
6. Phenolic strip.
ram2811014_001.dg, gw/rm, 29/01/03

1
(TYPICAL B
19 PLACES)
RIGHT SIDE IS SHOWN
LEFT SIDE IS OPPOSITE

Honeycomb Access Panel − Removal/Installation

Figure 401

Master
EFFECTIVITY: See Pageblock 28−11−01 page 401
28−11−01 Page 404
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
TASK 28−11−01−400−801
Installation of the Honeycomb Access Panel

1. Job Set−Up Information

Subtask 28−11−01−943−001
A. Tools and Equipment
REFERENCE DESIGNATION
None specified Torque wrench, torque range 25−30 lbf·in (2.8−3.4
N·m)

Subtask 28−11−01−944−001
B. Consumable Materials
REFERENCE DESIGNATION
05−001A Cloths, cleaning, for aircraft fuel tanks
11−002 Cleaning fluid
06−002 Petrolatum
04−004 Grease, aircraft, helicopter, oscillating bearing,
anti−fretting

Subtask 28−11−01−945−001
C. Parts
REF NAME OF PART QTY IPC SEQUENCE NO.
1 Screw 15 IPC 57−20−00−01−195
1 Screw 19 IPC 57−20−00−01−235
3 Knitted wire gasket 1 IPC 57−20−00−01−220
3 Knitted wire gasket 1 IPC 57−20−00−01−260
5 Rubber seal 1 IPC 57−20−00−01−200
5 Rubber seal 1 IPC 57−20−00−01−250
6 Phenolic strip 1 IPC 57−20−00−01−210
6 Phenolic strip 1 IPC 57−20−00−01−245

Subtask 28−11−01−946−003
D. Reference Information
REFERENCE DESIGNATION
TASK 12−11−28−650−801 Automatic Pressure Refueling
TASK 28−11−01−210−801 Damage Check of the Honeycomb Access Panel
TASK 28−11−01−960−801 Replacement of the Phenolic Strip
TASK 28−11−00−790−802 Leak Rate Check of the Fuel Tank

Master
EFFECTIVITY: See Pageblock 28−11−01 page 401
28−11−01 Page 405
Mar 15/2005
 C
AIRCRAFT MAINTENANCE MANUAL
2. Job Set−Up
Subtask 28−11−01−869−001
A. Make sure that the aircraft is in the same configuration as in the removal task.

Subtask 28−11−01−210−001
B. Examine the access panel for damage (Ref. TASK 28−11−01−210−801).

3. Procedure
Subtask 28−11−01−420−001
Refer to Figure 401.
A. Install the honeycomb access panel as follows:
(1) Remove all of the grease and contamination from the knitted wire gasket (3) with a
clean cloth and cleaning fluid. Discard the gasket (3) if damaged and replace. Apply
a large quantity of grease, (aircraft, helicopter, oscillating bearing, anti−fretting) to
the new or old gasket (3).
(2) Clean the rubber seal (5) with a clean cloth and cleaning fluid. Discard the seal (5) if
damaged and replace. Lubricate the new or old seal (5) with petrolatum.
(3) Clean the phenolic strip (6) with a clean cloth and cleaning fluid. Remove the
phenolic strip (6) if damaged and replace (Ref. TASK 28−11−01−960−801).
(4) Clean the inner and outer surface of the access port with a clean cloth and cleaning
fluid. Make sure that the two surfaces are clean.
(5) Put the access panel (4) with the rubber seal (5) sideways and at an angle, and in
position through the access port.
(6) Install the knitted wire gasket (3) on the clamp ring (2).
(7) Install the clamp ring (2) to the access panel (4) with the 15 or 19 screws (1) and
torque from 25 to 30 lbf·in (2.8 to 3.4 N·m).
NOTE: There are 19 screws (1) installed on the access panel (4) near the
wingtip.

4. Close Out
**ON A/C 7004−7019, 7021−7044, 7046, 7048, 7050, 7052, 7055−7056, 7059, 7061−7064,
7066−7067, 7069−7070, 7072−7073, 7075−7077, 7079−7080, 7085−7086, 7088−7094,
7099−7106, 7108−7111, 7113−7117, 7119, 7121−7123, 7125, 7127−7143, 7145−7152, 7154,
7156−7159, 7162−7163, 7165, 7167−7169, 7171−7176, 7178−7181, 7185−7196, 7199−7200,
7202−7222, 7224−7233, 7235−7236, 7238−7271, 7273−7294 Pre SB601R−24−090

Subtask 28−11−01−865−003
A. Remove the tags and close the circuit breakers that follow:

Master
EFFECTIVITY: See Pageblock 28−11−01 page 401
28−11−01 Page 406
Mar 15/2005
 C
AIRCRAFT MAINTENANCE MANUAL

CB PANEL CB NO. NAME ZONE

CBP−1 M7 L FUEL PUMP CONT 221
CBP−1 M8 FUEL X/FEED CONT 221
CBP−1 S1 FUEL SOV R ENG 221
CBP−1 S2 FUEL SOV L ENG 221
CBP−1 M12 FUEL SYST CONT 221
CBP−1 N9 XFER/APU XFER SOV 221
CBP−1 N10 XFER/APU FUEL PUMP 221
CBP−1 N11 XFER/APU CONT 221
CBP−1 N12 XFER/APU APU ECU 221
CBP−2 G10 R FUEL PUMP 222
CBP−2 G11 R FUEL PUMP CONT 222
CBP−4 B9 GRAV XFLOW 222
CBP−4 B10 FUEL SYST CONT 222
CBP−5 B14 FUEL DEFL 311
CBP−5 B15 EMRG REFL 311

**ON A/C 7003, 7020, 7045, 7047, 7049, 7051, 7053−7054, 7057−7058, 7060, 7065, 7071, 7074,
7078, 7081−7084, 7087, 7095−7098, 7107, 7112, 7118, 7120, 7124, 7126, 7144, 7153, 7155,
7160−7161, 7164, 7166, 7170, 7177, 7182−7184, 7197−7198, 7201, 7223, 7234, 7237, 7272,
7295−7990, 8000−8064, 8066−8068 and ON A/C 7004−7019, 7021−7044, 7046, 7048, 7050,
7052, 7055−7056, 7059, 7061−7064, 7066−7067, 7069−7070, 7072−7073, 7075−7077,
7079−7080, 7085−7086, 7088−7094, 7099−7106, 7108−7111, 7113−7117, 7119, 7121−7123,
7125, 7127−7143, 7145−7152, 7154, 7156−7159, 7162−7163, 7165, 7167−7169, 7171−7176,
7178−7181, 7185−7196, 7199−7200, 7202−7222, 7224−7233, 7235−7236, 7238−7271,
7273−7294 Post SB601R−24−090

Subtask 28−11−01−865−006
B. Remove the tags and close the circuit breakers that follow:
CB PANEL CB NO. NAME ZONE
CBP−1 M7 L FUEL PUMP CONT 221
CBP−1 M8 FUEL X/FEED CONT 221
CBP−1 S1 FUEL SOV R ENG 221
CBP−1 S2 FUEL SOV L ENG 221
CBP−1 M12 FUEL SYST CONT 221
CBP−1 N9 XFER/APU LEFT FUEL SOV 221
CBP−1 N10 XFER/APU FUEL PUMP 221
CBP−1 N11 XFER/APU CONT 221
CBP−1 N12 XFER/APU APU ECU 221
CBP−2 G10 R FUEL PUMP 222
CBP−2 G11 R FUEL PUMP CONT 222
CBP−4 B9 GRAV XFLOW 222

Master
EFFECTIVITY: See Pageblock 28−11−01 page 401
28−11−01 Page 407
Dec 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL

CB PANEL CB NO. NAME ZONE

CBP−4 B10 FUEL SYST CONT 222
CBP−5 B6 FUEL DEFL 311
CBP−5 B7 EMRG REFL 311

**ON A/C 7003−7011, 7013−7021, 7023−7037, 7039, 7041−7049, 7051−7061, 7063−7065, 7069,
7071−7990, 8000−8064, 8066−8068 and ON A/C 7012, 7022, 7038, 7040, 7050, 7062,
7066−7067, 7070 Post SB601R−28−022

Subtask 28−11−01−865−013
C. Also, remove the tag and close the circuit breaker that follows:
CB PANEL CB NO. NAME ZONE
CBP−2 P9 RIGHT FUEL XFER SOV 222

**ON A/C ALL

Subtask 28−11−01−790−001
D. Refuel the applicable main tank and the center tank (Ref. TASK 12−11−28−650−801).

Subtask 28−11−01−790−003
E. Examine the access panel for leaks (Ref. TASK 28−11−00−790−802).

Subtask 28−11−01−941−001
F. Remove all tools, equipment, and unwanted materials from the area.

Master
EFFECTIVITY: See Pageblock 28−11−01 page 401
28−11−01 Page 408
Dec 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
TASK 28−11−01−000−802
Removal of the Aluminum Access Panel

1. Job Set−Up Information

Subtask 28−11−01−946−002
A. Reference Information
REFERENCE DESIGNATION
TASK 12−11−28−650−804 Suction Defueling
TASK 28−00−00−910−801 Fuel Safety Precautions
TASK 28−11−00−840−801 Prepare Fuel Tank for Access
TASK 28−11−00−840−802 Removal of Fuel Fumes

2. Job Set−Up
Subtask 28−11−01−910−002
WARNING: OBEY ALL THE FUEL SAFETY PRECAUTIONS WHEN YOU DO WORK ON THE
FUEL SYSTEM AND/OR A FUEL SYSTEM COMPONENT. IF YOU DO NOT DO
THIS, YOU CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO
EQUIPMENT.
A. Obey all the fuel safety precautions (Ref. TASK 28−00−00−910−801).

Subtask 28−11−01−650−002
B. Defuel the applicable main tank and the center tank (Ref. TASK 12−11−28−650−801).

Subtask 28−11−01−840−003
C. Prepare the applicable main tank and the center tank for access (Ref. TASK
28−11−00−840−801).
D. Remove the fuel fumes from the applicable main tank and the center tank (Ref. TASK
28−11−00−840−802).

**ON A/C 7004−7019, 7021−7044, 7046, 7048, 7050, 7052, 7055−7056, 7059, 7061−7064,
7066−7067, 7069−7070, 7072−7073, 7075−7077, 7079−7080, 7085−7086, 7088−7094,
7099−7106, 7108−7111, 7113−7117, 7119, 7121−7123, 7125, 7127−7143, 7145−7152, 7154,
7156−7159, 7162−7163, 7165, 7167−7169, 7171−7176, 7178−7181, 7185−7196, 7199−7200,
7202−7222, 7224−7233, 7235−7236, 7238−7271, 7273−7294 Pre SB601R−24−090

Subtask 28−11−01−865−002
E. Open, safety, and tag the circuit breakers that follow:
CB PANEL CB NO. NAME ZONE
CBP−1 M6 L FUEL PUMP 221
CBP−1 M7 L FUEL PUMP CONT 221
CBP−1 M8 FUEL X/FEED CONT 221
CBP−1 S1 FUEL SOV R ENG 221

Master
EFFECTIVITY: See Pageblock 28−11−01 page 401
28−11−01 Page 409
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

CB PANEL CB NO. NAME ZONE

CBP−1 S2 FUEL SOV L ENG 221
CBP−1 M12 FUEL SYST CONT 221
CBP−1 N9 XFER/APU XFER SOV 221
CBP−1 N10 XFER/APU FUEL PUMP 221
CBP−1 N11 XFER/APU CONT 221
CBP−1 N12 XFER/APU APU ECU 221
CBP−2 G10 R FUEL PUMP 222
CBP−2 G11 R FUEL PUMP CONT 222
CBP−4 B9 GRAV XFLOW 222
CBP−4 B10 FUEL SYST CONT 222
CBP−5 B14 FUEL DEFL 311
CBP−5 B15 EMRG REFL 311

**ON A/C 7003, 7020, 7045, 7047, 7049, 7051, 7053−7054, 7057−7058, 7060, 7065, 7071, 7074,
7078, 7081−7084, 7087, 7095−7098, 7107, 7112, 7118, 7120, 7124, 7126, 7144, 7153, 7155,
7160−7161, 7164, 7166, 7170, 7177, 7182−7184, 7197−7198, 7201, 7223, 7234, 7237, 7272,
7295−7990, 8000−8064, 8066−8068 and ON A/C 7004−7019, 7021−7044, 7046, 7048, 7050,
7052, 7055−7056, 7059, 7061−7064, 7066−7067, 7069−7070, 7072−7073, 7075−7077,
7079−7080, 7085−7086, 7088−7094, 7099−7106, 7108−7111, 7113−7117, 7119, 7121−7123,
7125, 7127−7143, 7145−7152, 7154, 7156−7159, 7162−7163, 7165, 7167−7169, 7171−7176,
7178−7181, 7185−7196, 7199−7200, 7202−7222, 7224−7233, 7235−7236, 7238−7271,
7273−7294 Post SB601R−24−090

Subtask 28−11−01−865−007
F. Open, safety, and tag the circuit breakers that follow:
CB PANEL CB NO. NAME ZONE
CBP−1 M6 L FUEL PUMP 221
CBP−1 M7 L FUEL PUMP CONT 221
CBP−1 M8 FUEL X/FEED CONT 221
CBP−1 S1 FUEL SOV R ENG 221
CBP−1 S2 FUEL SOV L ENG 221
CBP−1 M12 FUEL SYST CONT 221
CBP−1 N9 XFER/APU LEFT FUEL SOV 221
CBP−1 N10 XFER/APU FUEL PUMP 221
CBP−1 N11 XFER/APU CONT 221
CBP−1 N12 XFER/APU APU ECU 221
CBP−2 G10 R FUEL PUMP 222
CBP−2 G11 R FUEL PUMP CONT 222
CBP−4 B9 GRAV XFLOW 222
CBP−4 B10 FUEL SYST CONT 222
CBP−5 B6 FUEL DEFL 311

Master
EFFECTIVITY: See Pageblock 28−11−01 page 401
28−11−01 Page 410
Dec 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL

CB PANEL CB NO. NAME ZONE

CBP−5 B7 EMRG REFL 311

**ON A/C 7003−7011, 7013−7021, 7023−7037, 7039, 7041−7049, 7051−7061, 7063−7065, 7069,
7071−7990, 8000−8064, 8066−8068 and ON A/C 7012, 7022, 7038, 7040, 7050, 7062,
7066−7067, 7070 Post SB601R−28−022

Subtask 28−11−01−865−015
G. Also open, safety and tag the circuit breaker that follows:
CB PANEL CB NO. NAME ZONE
CBP−2 P9 RIGHT FUEL XFER SOV 222

**ON A/C ALL

3. Procedure
**ON A/C 7003−7031, 7033−7067, 7069−7109, 7111−7114, 7116−7124, 7126−7132, 7134−7141,
7143−7165, 7167−7169, 7171−7255, 7258−7267, 7269−7271, 7273−7279, 7282−7287,
7289−7293, 7295−7321, 7323−7340, 7342−7361, 7363−7364, 7366−7370, 7372−7389,
7391−7395, 7397−7401, 7403−7408 Pre SB601R−57−030

Subtask 28−11−01−020−006
Refer to Figure 402.
A. Remove the aluminum access panel as follows:
(1) Hold the access panel (1) and remove the 14 screws (2). Remove the access panel
(1) with the sealing ring (3) from the access port.
(2) Carefully lift the clamp ring (4) with the rubber seal (5). Put the clamp ring (4) at an
angle and sideways, and lower it through the access port.

**ON A/C 7032, 7110, 7115, 7125, 7133, 7142, 7166, 7170, 7256−7257, 7268, 7272, 7280−7281,
7288, 7294, 7322, 7341, 7362, 7365, 7371, 7390, 7396, 7402, 7409−7990, 8000−8064,
8066−8068 and ON A/C 7003−7031, 7033−7067, 7069−7109, 7111−7114, 7116−7124,
7126−7132, 7134−7141, 7143−7165, 7167−7169, 7171−7255, 7258−7267, 7269−7271,
7273−7279, 7282−7287, 7289−7293, 7295−7321, 7323−7340, 7342−7361, 7363−7364,
7366−7370, 7372−7389, 7391−7395, 7397−7401, 7403−7408 Post SB601R−57−030

Subtask 28−11−01−020−005
Refer to Figure 403.
B. Remove the aluminum access panel as follows:
(1) Hold the access panel (1) and remove the 14 screws (2). Remove the access panel
(1) with the sealing ring (3) and the knitted aluminum gasket (6) from the access
port.
(2) Carefully lift the clamp ring (4) with the rubber seal (5). Put the clamp ring (4) at an
angle and sideways, and lower it through the access port.

Master
EFFECTIVITY: See Pageblock 28−11−01 page 401
28−11−01 Page 411
Dec 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL

LEGEND
1. Access panel.
2. Screw.
3. Sealing ring.
4. Clamp ring.
5. Rubber seal.

NOTE
Right side is shown.
Left side is the opposite.

ACCESS
PORT

2
ram2811014_002(3).dg, cr/gw, 16/06/97

Aluminum Access Panel − Removal/Installation

Figure 402

Master
EFFECTIVITY: See Pageblock 28−11−01 page 401
28−11−01 Page 412
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

LEGEND
1. Access panel.
2. Screw.
3. Sealing ring.
4. Clamp ring.
5. Rubber seal.
6. Knitted aluminum gasket.

ACCESS
PORT

3
6

2
ram2811014_003.dg, cr/gg, 03/12/01

NOTE
Right side is shown.
Left side is the opposite.

Aluminum Access Panel − Removal/Installation

Figure 403

Master
EFFECTIVITY: See Pageblock 28−11−01 page 401
28−11−01 Page 413
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C ALL
TASK 28−11−01−400−802
Installation of the Aluminum Access Panel

1. Job Set−Up Information

Subtask 28−11−01−943−002
A. Tools and Equipment
REFERENCE DESIGNATION
None specified Torque wrench, torque range 18−21 lbf·in
(2.03−2.37 N·m)

**ON A/C 7003−7031, 7033−7067, 7069−7109, 7111−7114, 7116−7124, 7126−7132, 7134−7141,

7143−7165, 7167−7169, 7171−7255, 7258−7267, 7269−7271, 7273−7279, 7282−7287,
7289−7293, 7295−7321, 7323−7340, 7342−7361, 7363−7364, 7366−7370, 7372−7389,
7391−7395, 7397−7401, 7403−7408 Pre SB601R−57−030

Subtask 28−11−01−944−002
B. Consumable Materials
REFERENCE DESIGNATION
04−001A Cloths, cleaning, for aircraft fuel tanks
11−002 Cleaning fluid
06−002 Petrolatum
06−025 Compound, Antiseize

**ON A/C 7003−7031, 7033−7067, 7069−7109, 7111−7114, 7116−7124, 7126−7132, 7134−7141,

7143−7165, 7167−7169, 7171−7255, 7258−7267, 7269−7271, 7273−7279, 7282−7287,
7289−7293, 7295−7321, 7323−7340, 7342−7361, 7363−7364, 7366−7370, 7372−7389,
7391−7395, 7397−7401, 7403−7408 (Post SB601R−57−030 and Pre SB601R−57−030)
C. Consumable Materials
REFERENCE DESIGNATION
04−001A Cloths, cleaning, for aircraft fuel tanks
11−002 Cleaning fluid
06−002 Petrolatum
06−025 Compound, Antiseize
04−004 Grease, aircraft, helicopter, oscillating bearing,
anti−fretting

Master
EFFECTIVITY: See Pageblock 28−11−01 page 401
28−11−01 Page 414
Dec 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C 7003−7031, 7033−7067, 7069−7109, 7111−7114, 7116−7124, 7126−7132, 7134−7141,
7143−7165, 7167−7169, 7171−7255, 7258−7267, 7269−7271, 7273−7279, 7282−7287,
7289−7293, 7295−7321, 7323−7340, 7342−7361, 7363−7364, 7366−7370, 7372−7389,
7391−7395, 7397−7401, 7403−7408 Pre SB601R−57−030

Subtask 28−11−01−945−002
D. Parts
REF NAME OF PART QTY IPC SEQUENCE NO.
2 Screw 14 IPC 57−20−00−01−120
3 Sealing ring 1 IPC 57−20−00−01−125
5 Rubber seal 1 IPC 57−20−00−01−140

**ON A/C 7032, 7110, 7115, 7125, 7133, 7142, 7166, 7170, 7256−7257, 7268, 7272, 7280−7281,
7288, 7294, 7322, 7341, 7362, 7365, 7371, 7390, 7396, 7402, 7409−7990, 8000−8064,
8066−8068 and ON A/C 7003−7031, 7033−7067, 7069−7109, 7111−7114, 7116−7124,
7126−7132, 7134−7141, 7143−7165, 7167−7169, 7171−7255, 7258−7267, 7269−7271,
7273−7279, 7282−7287, 7289−7293, 7295−7321, 7323−7340, 7342−7361, 7363−7364,
7366−7370, 7372−7389, 7391−7395, 7397−7401, 7403−7408 Post SB601R−57−030

Subtask 28−11−01−945−005
E. Parts
REF NAME OF PART QTY IPC SEQUENCE NO.
2 Screw 14 IPC 57−20−00−01−120
3 Sealing ring 1 IPC 57−20−00−01−125
5 Rubber seal 1 IPC 57−20−00−01−140
6 Knitted aluminum gasket 1 IPC 57−20−00−01−127

**ON A/C ALL

Subtask 28−11−01−946−004
F. Reference Information
REFERENCE DESIGNATION
TASK 12−11−28−650−801 Automatic Pressure Refueling
TASK 28−11−01−210−802 Damage Check of the Aluminum Access Panel
TASK 28−11−00−790−802 Leak Rate Check of the Fuel Tank

**ON A/C 7003−7031, 7033−7067, 7069−7109, 7111−7114, 7116−7124, 7126−7132, 7134−7141,

7143−7165, 7167−7169, 7171−7255, 7258−7267, 7269−7271, 7273−7279, 7282−7287,
7289−7293, 7295−7321, 7323−7340, 7342−7361, 7363−7364, 7366−7370, 7372−7389,
7391−7395, 7397−7401, 7403−7408 Pre SB601R−57−030

Master
EFFECTIVITY: See Pageblock 28−11−01 page 401
28−11−01 Page 415
Dec 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
2. Job Set−Up
**ON A/C ALL

Subtask 28−11−01−869−002
A. Make sure that the aircraft is in the same configuration as in the removal task.

Subtask 28−11−01−210−002
B. Examine the access panel for damage (Ref. TASK 28−11−01−210−802).
**ON A/C 7003−7031, 7033−7067, 7069−7109, 7111−7114, 7116−7124, 7126−7132, 7134−7141,
7143−7165, 7167−7169, 7171−7255, 7258−7267, 7269−7271, 7273−7279, 7282−7287,
7289−7293, 7295−7321, 7323−7340, 7342−7361, 7363−7364, 7366−7370, 7372−7389,
7391−7395, 7397−7401, 7403−7408 Pre SB601R−57−030

3. Procedure
Subtask 28−11−01−420−007
Refer to Figure 402.
A. Install the aluminum access panel as follows:
(1) Clean the sealing ring (3) with a clean cloth and cleaning fluid. Discard the sealing
ring (3) if damaged and replace. Lubricate the new or old sealing ring (3) with
petrolatum.
(2) Clean the rubber seal (5) with a clean cloth and cleaning fluid. Discard the seal (5) if
damaged and replace with a serviceable seal. Lubricate the seal (5) with
petrolatum.
(3) Clean the inner and outer surface of the access port with a clean cloth and cleaning
fluid. Make sure that the two surfaces are clean.
(4) Put the clamp ring (4) with the rubber seal (5) sideways and at an angle, and in
position through the access port.
(5) Put antiseize compound on the threads of the screws (2).
(6) Install the access panel (1) with the 14 screws (2) and torque from 18 to 21 lbf·in
(2.03 to 2.37 N·m).

**ON A/C 7032, 7110, 7115, 7125, 7133, 7142, 7166, 7170, 7256−7257, 7268, 7272, 7280−7281,
7288, 7294, 7322, 7341, 7362, 7365, 7371, 7390, 7396, 7402, 7409−7990, 8000−8064,
8066−8068 and ON A/C 7003−7031, 7033−7067, 7069−7109, 7111−7114, 7116−7124,
7126−7132, 7134−7141, 7143−7165, 7167−7169, 7171−7255, 7258−7267, 7269−7271,
7273−7279, 7282−7287, 7289−7293, 7295−7321, 7323−7340, 7342−7361, 7363−7364,
7366−7370, 7372−7389, 7391−7395, 7397−7401, 7403−7408 Post SB601R−57−030

Subtask 28−11−01−420−006
Refer to Figure 403.
B. Install the aluminum access panel as follows:

Master
EFFECTIVITY: See Pageblock 28−11−01 page 401
28−11−01 Page 416
Dec 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
(1) Fully remove all of the grease and contamination from the knitted aluminum gasket
(6) with a clean cloth and cleaning fluid. Discard the gasket (6) if damaged and
replace. If the gasket (6) is to be reused apply a large quantity of grease (04−004)
to the gasket.
NOTE: New knitted aluminum gaskets come pre−greased with grease (04−004).
(2) Clean the sealing ring (3) with a clean cloth and cleaning fluid. Discard the sealing
ring (3) if damaged and replace. Lubricate the new or old sealing ring (3) with
petrolatum.
(3) Clean the rubber seal (5) with a clean cloth and cleaning fluid. Discard the seal (5) if
damaged and replace with a serviceable seal. Lubricate the seal (5) with
petrolatum.
(4) Clean the inner and outer surface of the access port with a clean cloth and cleaning
fluid. Make sure that the two surfaces are clean.
(5) Put the clamp ring (4) with the rubber seal (5) sideways and at an angle, and in
position through the access port.
(6) Install the knitted aluminum gasket (6) on the access panel (1).
(7) Put antiseize compound on the threads of the screws (2).
(8) Install the access panel (1) with the 14 screws (2) and torque to 18−21
pound−inches (2.03−2.37 Newton meter).
**ON A/C 7003−7031, 7033−7067, 7069−7109, 7111−7114, 7116−7124, 7126−7132, 7134−7141,
7143−7165, 7167−7169, 7171−7255, 7258−7267, 7269−7271, 7273−7279, 7282−7287,
7289−7293, 7295−7321, 7323−7340, 7342−7361, 7363−7364, 7366−7370, 7372−7389,
7391−7395, 7397−7401, 7403−7408 Pre SB601R−57−030

4. Close Out
**ON A/C 7004−7019, 7021−7044, 7046, 7048, 7050, 7052, 7055−7056, 7059, 7061−7064,
7066−7067, 7069−7070, 7072−7073, 7075−7077, 7079−7080, 7085−7086, 7088−7094,
7099−7106, 7108−7111, 7113−7117, 7119, 7121−7123, 7125, 7127−7143, 7145−7152, 7154,
7156−7159, 7162−7163, 7165, 7167−7169, 7171−7176, 7178−7181, 7185−7196, 7199−7200,
7202−7222, 7224−7233, 7235−7236, 7238−7271, 7273−7294 Pre SB601R−24−090

Subtask 28−11−01−865−004
A. Remove the tags and close the circuit breakers that follow:
CB PANEL CB NO. NAME ZONE
CBP−1 M6 L FUEL PUMP 221
CBP−1 M7 L FUEL PUMP CONT 221
CBP−1 M8 FUEL X/FEED CONT 221
CBP−1 S1 FUEL SOV R ENG 221
CBP−1 S2 FUEL SOV L ENG 221
CBP−1 M12 FUEL SYST CONT 221
CBP−1 N9 XFER/APU XFER SOV 221
CBP−1 N10 XFER/APU FUEL PUMP 221
CBP−1 N11 XFER/APU CONT 221

Master
EFFECTIVITY: See Pageblock 28−11−01 page 401
28−11−01 Page 417
Dec 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL

CB PANEL CB NO. NAME ZONE

CBP−1 N12 XFER/APU APU ECU 221
CBP−2 G10 R FUEL PUMP 222
CBP−2 G11 R FUEL PUMP CONT 222
CBP−4 B9 GRAV XFLOW 222
CBP−4 B10 FUEL SYST CONT 222
CBP−5 B14 FUEL DEFL 311
CBP−5 B15 EMRG REFL 311

**ON A/C 7003, 7020, 7045, 7047, 7049, 7051, 7053−7054, 7057−7058, 7060, 7065, 7071, 7074,
7078, 7081−7084, 7087, 7095−7098, 7107, 7112, 7118, 7120, 7124, 7126, 7144, 7153, 7155,
7160−7161, 7164, 7166, 7170, 7177, 7182−7184, 7197−7198, 7201, 7223, 7234, 7237, 7272,
7295−7990, 8000−8064, 8066−8068 and ON A/C 7004−7019, 7021−7044, 7046, 7048, 7050,
7052, 7055−7056, 7059, 7061−7064, 7066−7067, 7069−7070, 7072−7073, 7075−7077,
7079−7080, 7085−7086, 7088−7094, 7099−7106, 7108−7111, 7113−7117, 7119, 7121−7123,
7125, 7127−7143, 7145−7152, 7154, 7156−7159, 7162−7163, 7165, 7167−7169, 7171−7176,
7178−7181, 7185−7196, 7199−7200, 7202−7222, 7224−7233, 7235−7236, 7238−7271,
7273−7294 Post SB601R−24−090

Subtask 28−11−01−865−008
B. Remove the tags and close the circuit breakers that follow:
CB PANEL CB NO. NAME ZONE
CBP−1 M6 L FUEL PUMP 221
CBP−1 M7 L FUEL PUMP CONT 221
CBP−1 M8 FUEL X/FEED CONT 221
CBP−1 S1 FUEL SOV R ENG 221
CBP−1 S2 FUEL SOV L ENG 221
CBP−1 M12 FUEL SYST CONT 221
CBP−1 N9 XFER/APU LEFT FUEL SOV 221
CBP−1 N10 XFER/APU FUEL PUMP 221
CBP−1 N11 XFER/APU CONT 221
CBP−1 N12 XFER/APU APU ECU 221
CBP−2 G10 R FUEL PUMP 222
CBP−2 G11 R FUEL PUMP CONT 222
CBP−4 B9 GRAV XFLOW 222
CBP−4 B10 FUEL SYST CONT 222
CBP−5 B6 FUEL DEFL 311
CBP−5 B7 EMRG REFL 311

Master
EFFECTIVITY: See Pageblock 28−11−01 page 401
28−11−01 Page 418
Dec 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C 7003−7011, 7013−7021, 7023−7037, 7039, 7041−7049, 7051−7061, 7063−7065, 7069,
7071−7990, 8000−8064, 8066−8068 and ON A/C 7012, 7022, 7038, 7040, 7050, 7062,
7066−7067, 7070 Post SB601R−28−022

Subtask 28−11−01−865−016
C. Also, remove the tag and close the circuit breaker that follows:
CB PANEL CB NO. NAME ZONE
CBP−2 P9 RIGHT FUEL XFER SOV 222

**ON A/C ALL

Subtask 28−11−01−790−002
D. Refuel the applicable main tank and the center tank (Ref. TASK 12−11−28−650−801).

Subtask 28−11−01−790−004
E. Examine the access panels for leaks (Ref. TASK 28−11−00−790−802).

Subtask 28−11−01−941−002
F. Remove all tools, equipment, and unwanted materials from the area.

Master
EFFECTIVITY: See Pageblock 28−11−01 page 401
28−11−01 Page 419
Dec 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C ALL
PANEL, FUEL TANK ACCESS − INSPECTION/CHECK

1. General
A. The maintenance procedures that follow are for the inspection and check of the fuel tank
access panel (written as the "access panel" in this procedure). These procedures include
the inspections and checks that follow:
± Damage check of the honeycomb access panel
± Damage check of the aluminum access panel
± Visual check of the wing tank fasteners
± Detailed inspection of the wing tank fasteners.
NOTE: It is necessary to remove the access panel to do the damage check.

TASK 28−11−01−210−801
Damage Check of the Honeycomb Access Panel

1. Job Set−Up Information

Subtask 28−11−01−944−006

REFERENCE DESIGNATION
06−002 Petrolatum

Subtask 28−11−01−945−003

REF NAME OF PART QTY IPC SEQUENCE NO.

5 Rubber seal 1 IPC 57−20−00−01−200 or
IPC 57−20−00−01−250
6 Phenolic strip 1 IPC 57−20−00−01−210 or
IPC 57−20−00−01−245
3 Knitted wire gasket 1 IPC 57−20−00−01−220 or
IPC 57−20−00−01−260

Subtask 28−11−01−946−005
A. Reference Information
REFERENCE DESIGNATION
TASK 28−00−00−910−801 Fuel Safety Precautions
TASK 28−11−01−000−801 Removal of the Honeycomb Access Panel
TASK 28−11−01−000−802 Removal of the Aluminum Access Panel
TASK 28−11−00−390−801 Fuel−Tank Seal Repair
TASK 28−11−01−390−801 Repair of the Fuel−Resistant Coating
TASK 28−11−01−960−801 Replacement of the Phenolic Strip
TASK 28−11−01−400−801 Installation of the Honeycomb Access Panel

Master
EFFECTIVITY: See Pageblock 28−11−01 page 601
28−11−01 Page 601
Dec 15/2004
 C
AIRCRAFT MAINTENANCE MANUAL

REFERENCE DESIGNATION
TASK 28−11−01−400−802 Installation of the Aluminum Access Panel
SRM 51−22−34 Attaching Flourosilicone Rubber with Adhesives

2. Job Set−Up
Subtask 28−11−01−910−003
WARNING: OBEY ALL THE FUEL SAFETY PRECAUTIONS WHEN YOU DO WORK ON THE
FUEL SYSTEM AND/OR A FUEL SYSTEM COMPONENT. IF YOU DO NOT DO
THIS, YOU CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO
EQUIPMENT.
A. Obey all the fuel safety precautions (Ref. TASK 28−00−00−910−801).

Subtask 28−11−01−020−003
B. Remove the applicable access panel (Ref. TASK 28−11−01−000−801 or TASK
28−11−01−000−802).

3. Procedure
Subtask 28−11−01−210−003
Refer to Figure 601.
A. Do a damage check of the access panel as follows:
(1) Examine the sealant on the nut plates for cracks. If necessary, repair the sealant
(Ref. TASK 28−11−00−390−801).
(2) Examine the internal side of the access panel for cracks in the fuel−resistant
coating. If necessary, repair the fuel−resistant coating (Ref. TASK
28−11−01−390−801).
(3) Examine the rubber seal for cuts or other damage. If necessary, replace the rubber
seal and lubricate with petrolatum (Ref. SRM 51−22−34).
(4) Examine the phenolic strip for cuts or other damage. If necessary, replace the
phenolic strip (Ref. TASK 28−11−01−960−801).
(5) Examine the knitted wire gasket for damage. Make sure that the gasket makes
good electrical contact. If necessary, replace the gasket.

4. Close Out
Subtask 28−11−01−420−003
A. Install the access panel (Ref. TASK 28−11−01−400−801 or TASK 28−11−01−400−802).

Subtask 28−11−01−941−004
B. Remove all tools, equipment, and unwanted materials from the area.

Master
EFFECTIVITY: See Pageblock 28−11−01 page 601
28−11−01 Page 602
Dec 15/2004
 C
AIRCRAFT MAINTENANCE MANUAL

B B

NOTES
1. Right side is shown.
Left side is the opposite.
A
2. Detail A similar to detail B
Differences are shown.

ACCESS PANEL
NUT PLATE
(TYPICAL)

PHENOLIC STRIP

RUBBER SEAL

ACCESS PORT
(REF)

KNITTED WIRE GASKET

CLAMP RING
(REF)

ram2811016_001.dg, rm, 30/07/97

A
VIEW LOOKING UP

B
VIEW LOOKING UP

Honeycomb Access Panel − Inspection/Check

Figure 601

Master
EFFECTIVITY: See Pageblock 28−11−01 page 601
28−11−01 Page 603
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
TASK 28−11−01−210−802
Damage Check of the Aluminum Access Panel

1. Job Set−Up Information

Subtask 28−11−01−944−005

REFERENCE DESIGNATION
06−002 Petrolatum

Subtask 28−11−01−945−004

REF NAME OF PART QTY IPC SEQUENCE NO.

3 Sealing ring 1 IPC 57−20−00−01−125
5 Rubber seal 1 IPC 57−20−00−01−140

Subtask 28−11−01−946−006
A. Reference Information
REFERENCE DESIGNATION
TASK 28−11−01−000−801 Removal of the Honeycomb Access Panel
TASK 28−11−01−000−802 Removal of the Aluminum Access Panel
TASK 28−11−00−390−801 Fuel−Tank Seal Repair
TASK 28−11−01−390−801 Repair of the Fuel−Resistant Coating
TASK 28−11−01−400−801 Installation of the Honeycomb Access Panel
TASK 28−11−01−400−802 Installation of the Aluminum Access Panel
TASK 28−00−00−910−801 Fuel Safety precautions
SRM 51−22−34 Attaching Flourosilicone Rubber with Adhesives

2. Job Set−Up
Subtask 28−11−01−910−004
WARNING: OBEY ALL THE FUEL SAFETY PRECAUTIONS WHEN YOU DO WORK ON THE
FUEL SYSTEM AND/OR A FUEL SYSTEM COMPONENT. IF YOU DO NOT DO
THIS, YOU CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO
EQUIPMENT.
A. Obey all the fuel safety precautions (Ref. TASK 28−00−00−910−801).

Subtask 28−11−01−020−004
B. Remove the applicable access panel (Ref. TASK 28−11−01−000−801 or TASK
28−11−01−000−802).

Master
EFFECTIVITY: See Pageblock 28−11−01 page 601
28−11−01 Page 604
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
3. Procedure
Subtask 28−11−01−210−004
Refer to Figure 602.
A. Do a damage check of the access panel as follows:
(1) Examine the sealant on the nut plates for cracks. If necessary, repair the sealant
(Ref. TASK 28−11−00−390−801).
(2) Examine the internal side of the access panel for cracks in the fuel−resistant
coating. If necessary, repair the fuel−resistant coating (Ref. TASK
28−11−01−390−801).
(3) Examine the rubber seal of the clamp ring for cuts or other damage. If necessary,
replace the rubber seal and lubricate with petrolatum (Ref. SRM 51−22−34).
(4) Examine the sealing ring of the access panel for cuts or other damage. If
necessary, replace the sealing ring and lubricate with petrolatum.

4. Close Out
Subtask 28−11−01−420−004
A. Install the access panel (Ref. TASK 28−11−01−400−801 or TASK 28−11−01−400−802).

Subtask 28−11−01−941−003
B. Remove all tools, equipment, and unwanted materials from the area.

Master
EFFECTIVITY: See Pageblock 28−11−01 page 601
28−11−01 Page 605
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

A
NOTE
Right side is shown.
Left side is the opposite.

CLAMP RING

NUT PLATE RUBBER SEAL

(TYPICAL)

ACCESS PORT
(REF)

SEALING
RING

ACCESS PANEL
ram2811016_002.dg, rm, 31/07/97

A
VIEW LOOKING UP AND AFT

Aluminum Access Panel − Inspection/Check

Figure 602

Master
EFFECTIVITY: See Pageblock 28−11−01 page 601
28−11−01 Page 606
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
TASK 28−11−01−220−801
Detailed Inspection of the Fuel Access−Panels and the Fuel and Water Drain Valves and
Fasteners
1. Reason for the Job
Refer to MRB 28−11−00−02

2. Procedure
Refer to Figure 603
Subtask 28−11−01−220−001
A. Do a detailed inspection of the fuel access panels and fuel and water drain valves and
fasteners as follows:
(1) Examine all fuel access panels and water drain valves for leakage, condition and
safety of installation.
(2) Examine all rivets and fasteners on the external wing tank structure for leakage,
condition and safety of installation.

3. Close Out
Subtask 28−11−01−869−004
A. Remove all tools, equipment, and unwanted material from the work area.

Master
EFFECTIVITY: See Pageblock 28−11−01 page 601
28−11−01 Page 607
Aug 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL

WING TANK

WING TANK

ram2811016_003.dg, cc, 29/09/04

Fuel Access−Panels and the Fuel and Water Drain Valves and Fasteners − Inspection/Check
Figure 603

Master
EFFECTIVITY: See Pageblock 28−11−01 page 601
28−11−01 Page 608
Aug 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C ALL
PANEL, FUEL TANK ACCESS − REPAIRS

1. General
A. The maintenance procedures that follow are for the repair of the fuel tank access panel
(written as the "access panel" in this procedure). These maintenance procedures are
used to repair the fuel−resistant coating and to replace the phenolic strip.

TASK 28−11−01−390−801
Repair of the Fuel−Resistant Coating

1. Job Set−Up Information

Subtask 28−11−01−944−003
A. Consumable Materials
REFERENCE DESIGNATION
05−001A Cloths, cleaning, for aircraft fuel tanks
05−032 Abrasive paper, no. 60−100 (medium) grit
05−033 Gauze or cheesecloth, oil and lint−free
05−034 Paint brush, natural or synthetic bristle
11−007 Thinner, ethyl acetate
11−011 Solvent, −1,−1,−1 Trichloroethane
15−002 Fuel tank coating

2. Procedure
Subtask 28−11−01−390−001
A. Repair the fuel−resistant coating as follows:
(1) Use abrasive paper to remove all of the old coating that is 1 inch or less from the
damage. Do not cause damage to the surface treatment of the base metal.
WARNING: OBEY ALL OF THE PRECAUTIONS THAT FOLLOW WHEN YOU USE
−1,−1,−1 TRICHLOROETHANE:
± DO NOT USE IN AREAS WHERE THERE IS HIGH HEAT, SPARKS,
OR FLAMES
± DO WORK IN AN AREA THAT HAS A GOOD FLOW OF AIR
± OBEY THE MANUFACTURER’S INSTRUCTIONS
± DO NOT LET THE −1,−1,−1 TRICHLOROETHANE TOUCH YOUR
SKIN, EYES, AND MOUTH
± CLOSE THE CONTAINER WHEN IT IS NOT USED.
−1,−1,−1 TRICHLOROETHANE IS AN IRRITANT AND IS POISONOUS.
(2) Clean the damaged area with a clean cloth and solvent. Put a clean cloth on the
area until the new coating is applied.

Master
EFFECTIVITY: See Pageblock 28−11−01 page 801
28−11−01 Page 801
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
(3) Mix the fuel−resistant coating as follows:
(a) Mix one part base (resin) with four parts catalyst.
(b) Add four parts thinner and mix fully.
(c) Add the dye in a ratio of 1 ounce for each gallon of mixture and mix fully.
(d) After 1 hour, put the mixture through a filter of three layers of gauze or
cheesecloth.
NOTE: The pot life of the mixture at 75 °F (25 °C) is 8 hours. The pot life of
the mixture at 90 °F (30 °C) is 2 hours.
(4) Apply the mixture to the damaged area with a paint brush. Cross−coat the mixture
to a wet−film thickness of 0.06−0.08 inch (1.6−2.4 mm).
NOTE: The film thickness of the mixture will decrease by 50 percent when dry.
Dry−film thickness will be 0.03−0.05 inch (0.8−1.2 mm).
(5) Keep the repair at ambient temperature for 30 minutes, then increase the
temperature of the repair to 200−225 °F (95−105 °C) for 1 hour.

Master
EFFECTIVITY: See Pageblock 28−11−01 page 801
28−11−01 Page 802
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
TASK 28−11−01−960−801
Replacement of the Phenolic Strip

1. Job Set−Up Information

Subtask 28−11−01−943−003
A. Tools and Equipment
REFERENCE DESIGNATION
None specified Scraper, phenolic

Subtask 28−11−01−944−004
B. Consumable Materials
REFERENCE DESIGNATION
05−001A Cloths, cleaning, for aircraft fuel tanks
05−024 Aluminum oxide cloth, 220 grit or finer
05−034 Paint brush, natural or synthetic bristle
05−035 Filler, Cab−O−Sil
08−009 Adhesive, epoxy
11−011 Solvent, −1,−1,−1 Trichloroethane

2. Procedure
Subtask 28−11−01−960−001
A. Remove the phenolic strip as follows:
(1) Remove the phenolic strip and the adhesive with a sharp phenolic scraper.
WARNING: OBEY ALL OF THE PRECAUTIONS THAT FOLLOW WHEN YOU USE
−1,−1,−1 TRICHLOROETHANE:
± DO NOT USE IN AREAS WHERE THERE IS HIGH HEAT, SPARKS,
OR FLAMES
± DO WORK IN AN AREA THAT HAS A GOOD FLOW OF AIR
± OBEY THE MANUFACTURER’S INSTRUCTIONS
± DO NOT LET THE −1,−1,−1 TRICHLOROETHANE TOUCH YOUR
SKIN, EYES, AND MOUTH
± CLOSE THE CONTAINER WHEN IT IS NOT USED.
−1,−1,−1 TRICHLOROETHANE IS AN IRRITANT AND IS POISONOUS.
(2) If necessary, apply solvent to the faying surface to remove the remaining adhesive.
(3) Dry the faying surface with a clean, dry cloth.

Master
EFFECTIVITY: See Pageblock 28−11−01 page 801
28−11−01 Page 803
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
Subtask 28−11−01−960−002
B. Install the phenolic strip as follows:
(1) Make the base of the phenolic strip rough with aluminum oxide cloth until the
surface gloss is removed.
(2) Clean the phenolic strip with solvent and a clean cloth.
(3) Mix the adhesive as follows:
(a) Mix 100 parts by weight of part A with 33 parts by weight of part B. Do not mix
more than 450 grams at one time.
(b) If necessary, add filler to make the adhesive thicker. Do not add more than
4 percent by weight. Mix fully.
(4) Apply a coat of adhesive to the faying surface with the paint brush. Do not apply
adhesive to the phenolic strip.
(5) Install the phenolic strip on the faying surface. Push the two surfaces together with
sufficient, equal hand pressure.
(6) Make sure that the adhesive comes out around the faying surface. Remove
unwanted adhesive with a clean cloth.
NOTE: At ambient temperature, the adhesive becomes hard in less than 6 hours.
A full cure occurs after 7 days at room temperature or after a minimum of
2 hours at 150 °F (65 °C).
(7) Cut the phenolic strip to the correct dimension.

Master
EFFECTIVITY: See Pageblock 28−11−01 page 801
28−11−01 Page 804
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C ALL
TANK, COLLECTOR − REMOVAL/INSTALLATION

1. General
A. The maintenance procedures that follow are for the removal and installation of the
collector tank. There are two collector tanks in the fuel system. They are installed in the
forward section of the center wing box.
B. It is necessary to defuel the aircraft, and drain and remove the fuel fumes from the
center tank to remove or install the collector tank.

TASK 28−11−03−000−801
Removal of the Collector Tank

1. Job Set−Up Information

Subtask 28−11−03−943−001
A. Tools and Equipment
REFERENCE DESIGNATION
None specified Container, fuel, 10 U.S. gallon (38 L)

Subtask 28−11−03−946−001
B. Reference Information
REFERENCE DESIGNATION
TASK 12−11−28−650−804 Suction Defueling
TASK 20−30−00−910−802 Wiggins Couplings − Maintenance Practices
TASK 28−00−00−910−801 Fuel Safety Precautions
TASK 28−11−00−840−801 Prepare Fuel Tank for Access
TASK 28−11−00−840−802 Removal of Fuel Fumes
TASK 28−11−01−000−801 Removal of the Honeycomb Access Panel
TASK 28−11−01−000−802 Removal of the Graphite Access Panel
TASK 28−13−28−000−801 Removal of the Gravity Feed Manifold
TASK 28−21−01−000−801 Removal of the Primary Ejector Pump

Master
EFFECTIVITY: See Pageblock 28−11−03 page 401
28−11−03 Page 401
Sep 10/2004
 C
AIRCRAFT MAINTENANCE MANUAL
2. Job Set−Up
Subtask 28−11−03−910−001
WARNING: OBEY ALL THE FUEL SAFETY PRECAUTIONS WHEN YOU DO WORK ON THE
FUEL SYSTEM AND/OR A FUEL SYSTEM COMPONENT. IF YOU DO NOT DO
THIS, YOU CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO
EQUIPMENT.
A. Obey all the fuel safety precautions (Ref. TASK 28−00−00−910−801).

Subtask 28−11−03−650−001
B. Defuel the aircraft (Ref. TASK 12−11−28−650−804).

Subtask 28−11−03−650−002
C. Drain the fuel from the applicable collector tank as follows:
(1) Put a fuel container below the applicable water drain valve.
(2) Put a screwdriver in the water drain valve.
(3) Push the screwdriver and turn it clockwise.
(4) When the fuel flow stops, put a screwdriver in the water drain valve.
(5) Push the screwdriver and turn it counterclockwise.

Subtask 28−11−03−010−001
D. To remove the left collector tank, remove the access panel that follows (Ref. TASK
28−11−01−000−801):
ACCESS DESCRIPTION
510AB Fuel tank access panel
E. To remove the right collector tank, remove the access panel that follows (Ref. TASK
28−11−01−000−802):
ACCESS DESCRIPTION
610AB Fuel tank access panel

Subtask 28−11−03−840−001
F. Prepare the center tank for access (Ref. TASK 28−11−00−840−801).
G. Remove the fuel fumes from the center tank (Ref. TASK 28−11−00−840−802).

3. Procedure
Subtask 28−11−03−030−001
A. Remove the primary ejector pump (Ref. TASK 28−21−01−000−801).
B. Remove the gravity feed manifold (Ref. TASK 28−13−28−000−801).

Subtask 28−11−03−020−001
Refer to Figure 401.

Master
EFFECTIVITY: See Pageblock 28−11−03 page 401
28−11−03 Page 402
Sep 10/2004
 C
AIRCRAFT MAINTENANCE MANUAL
C. Remove the collector tank as follows:
(1) Disconnect the vent line (2) from the collector tank (1). Put a protective plug in the
vent line.
(2) Disconnect the coupling (3) on the scavenge return manifold (4) (Ref. TASK
20−30−00−910−802) and remove the retainer (5). Put a protective plug in the
scavenge return manifold.
(3) Remove the coupling (7) on the standby−pump feed manifold (8) (Ref. TASK
20−30−00−910−802).
(4) Move the sleeve (9) to the standby−pump feed manifold (8). Remove and discard
the preformed packings (10). Put a protective plug in the scavenge return
manifold (4).
(5) Disconnect the drain line (11) from the collector tank (1). Put a protective plug in the
drain line.
(6) Remove the nuts (12) and disconnect the clamps (13) on the collector tank (1).
(7) Remove the collector tank (1).

Subtask 28−11−03−030−002
Refer to Figure 402.
D. Remove the fittings from the collector tank as follows:
(1) Loosen the jamnut (14) and remove the elbow fitting (15) from the collector tank
(1). Remove and discard the preformed packing (16).
(2) Remove the union (17) and the preformed packing (18) from the collector tank (1).
Discard the preformed packing.
(3) Remove the bolts (19), the washers (20), and the primary ejector bracket (21) from
the collector tank (1).
(4) Remove the bolts (22), the retainers (23), the cover plate (24), and the gasket (25)
from the top of the collector tank (1). Discard the retainers and the gasket.
(5) Remove the bolts (26), the retainers (27), the scavenge return fitting (28), and the
gasket (29) from the collector tank (1). Discard the retainers and the gasket.
(6) Remove the bolts (30) and (31), the retainers (32), the standby−pump feed fitting
(33), and the gasket (34) from the collector tank (1). Discard the retainers and the
gasket.
(7) Remove the bolts (35), the retainers (36), the preformed packings (37), and the
gravity feed fitting (38) from the collector tank (1). Discard the retainers and the
preformed packings.
(8) Remove and discard the preformed packing (39) from the gravity feed fitting (38).

Master
EFFECTIVITY: See Pageblock 28−11−03 page 401
28−11−03 Page 403
Sep 10/2004
 C
AIRCRAFT MAINTENANCE MANUAL

LEGEND.
1. Collector tank.
2. Vent line.
3. Coupling.
4. Scavenge return manifold.
5. Retainer.
6. Preformed packing.
7. Coupling.
8. Standby−pump feed manifold.
9. Sleeve.
10. Preformed packing.
11. Drain line.
12. Nut.
13. Clamp.
14. Not used.
15. Elbow fitting.
16. Not used.
17. Union.
2
28. Scavenge return fitting.
33. Standby−pump feed fitting. 17

1
13
6
5
6
4
3

28
ram2811034_001(1).dc, rs/gd, 11/03/93

33 15
7
11

10 12
NOTE
9 Left side is shown.
Right side is the opposite.
8

Collector Tank − Removal/Installation

Figure 401

Master
EFFECTIVITY: See Pageblock 28−11−03 page 401
28−11−03 Page 404
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

A
LEGEND
1. Collector tank. 26. Bolt.
14. Jamnut. 27. Retainer.
15. Elbow fitting. 28. Scavenge return fitting.
16. Preformed packing. 29. Gasket.
17. Union. 30. Bolt.
18. Preformed packing. 31. Bolt.
19. Bolt. 32. Retainer.
20. Washer. 33. Standby−pump feed fitting.
21. Primary ejector 34. Gasket.
bracket. 35. Bolt.
22. Bolt. 36. Retainer.
NOTES 23. Retainer. 37. Preformed packing.
Left side is shown. 24. Cover plate. 38. Gravity feed fitting.
Right side is the opposite. 25. Gasket. 39. Preformed packing.

1 Apply sealant SAE AMS−S−8802.

22 1

38 17
23

39
18 24
1 35
25
36
37
1

1 19
20
21

1 26

27

16

28 14
ram2811034_002.dg, rs/lr, 11/05/03

34
29 15
33
32

31 1
1 30 32
A

Collector Tank Fittings − Removal/Installation

Figure 402

Master
EFFECTIVITY: See Pageblock 28−11−03 page 401
28−11−03 Page 405
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
TASK 28−11−03−400−801
Installation of the Collector Tank

1. Job Set−Up Information

Subtask 28−11−03−943−002
A. Tools and Equipment
REFERENCE DESIGNATION
None specified Torque wrench, 0−30 lbf in. (0−3.5 N·m)

Subtask 28−11−03−944−002
B. Consumable Materials
REFERENCE DESIGNATION
09−013 Sealant, fuel tank, low weight

Subtask 28−11−03−945−001
C. Parts
REF NAME OF PART QTY IPC SEQUENCE NO.
6 Preformed packing 2 IPC 28−13−00−3A−075
10 Preformed packing 2 IPC 28−23−00−1A−030
12 Nut 2 IPC 28−11−03−1A−025
14 Jamnut 1 IPC 28−11−03−1A−180
15 Elbow fitting 1 IPC 28−11−03−1A−175
16 Preformed packing 1 IPC 28−11−03−1A−185
17 Union 1 IPC 28−11−03−1A−165
18 Preformed packing 1 IPC 28−11−03−1A−170
19 Bolt 2 IPC 28−11−03−1A−155
20 Washer 2 IPC 28−11−03−1A−160
22 Bolt 4 IPC 28−11−03−1A−195
23 Retainer 4 IPC 28−11−03−1A−200
25 Gasket 1 TBD
26 Bolt 4 IPC 28−11−03−1A−135
27 Retainer 4 IPC 28−11−03−1A−140
29 Gasket 1 IPC 28−11−03−1A−145
30 Bolt 2 IPC 28−11−03−1A−105
31 Bolt 2 IPC 28−11−03−1A−110
32 Retainer 4 IPC 28−11−03−1A−115
34 Gasket 1 IPC 28−11−03−1A−120
35 Bolt 2 IPC 28−11−03−1A−050
36 Retainer 2 IPC 28−11−03−1A−055
37 Preformed packing 2 TBD

Master
EFFECTIVITY: See Pageblock 28−11−03 page 401
28−11−03 Page 406
Sep 10/2004
 C
AIRCRAFT MAINTENANCE MANUAL

REF NAME OF PART QTY IPC SEQUENCE NO.

39 Preformed packing 1 IPC 28−11−03−1A−095

Subtask 28−11−03−946−002
D. Reference Information
REFERENCE DESIGNATION
TASK 20−30−00−910−802 Wiggins Couplings − Maintenance Practices
TASK 28−11−01−400−801 Installation of the Honeycomb Access Panel
TASK 28−11−01−400−802 Installation of the Graphite Access Panel
TASK 28−13−28−400−801 Installation of the Gravity Feed Manifold
TASK 28−21−01−400−801 Installation of the Primary Ejector Pump
TASK 28−23−01−710−801 Operational Test of the Electric Boost Pump
TASK 51−23−00−390−808 Application of Sealant with Brush
TASK 51−80−00−760−803 Electrical Bonding Test

2. Procedure
Subtask 28−11−03−869−001
A. Make sure that the aircraft is in the same configuration as in the removal task.

Subtask 28−11−03−430−001
Refer to Figure 402.
B. Install the fittings on the collector tank as follows:
(1) Install the preformed packing (16) and the elbow fitting (15) on the collector tank
(1). Hold the elbow fitting in position and torque the jamnut (14) to 10−15 lbf in.
(1.1−1.7 N·m).
(2) Install the preformed packing (18) and the union (17) on the collector tank (1).
Torque the union to 10−15 lbf in. (1.1−1.7 N·m).
(3) Install the primary ejector bracket (21), the washers (20), and the bolts (19) on the
collector tank (1).
(4) Install the gasket (25), the cover plate (24), the retainers (23), and the bolts (22) on
the top of the collector tank (1).
(5) Install the gasket (29), the scavenge return fitting (28), the retainers (27), and the
bolts (26) on the collector tank (1).
(6) Install the gasket (34), the standby−pump feed fitting (33), the retainers (32), and
the bolts (30) and (31) on the collector tank (1).
(7) Install the preformed packing (39) on the gravity feed fitting (38).
(8) Install the gravity feed fitting (38), the preformed packings (37), the retainers (36),
and the bolts (35) on the collector tank (1).
(9) Apply a layer of sealing compound 09−013 with a brush to all the bolts (19), (22),
(26), (30), (31), and (35). (Ref. TASK 51−23−00−390−808).

Master
EFFECTIVITY: See Pageblock 28−11−03 page 401
28−11−03 Page 407
Sep 10/2004
 C
AIRCRAFT MAINTENANCE MANUAL
Subtask 28−11−03−420−001
Refer to Figure 401.
C. Install the collector tank as follows:
(1) Install the collector tank (1) in the clamps (13). Connect the clamps (13) with the
nuts (12).
(2) Remove the protective plug from the drain line (11). Connect the drain line to the
elbow fitting (15).
(3) Install the preformed packings (10) on the standby−pump feed fitting (33) and the
standby−pump feed manifold (8).
(4) Remove the protective plug from the standby−pump feed manifold (8). Connect the
standby−pump feed manifold to the standby−pump feed fitting (33) with the
sleeve (9).
(5) Install the coupling (7) on the sleeve (9) (Ref. TASK 20−30−00−910−802).
(6) Do the electrical bonding test of the coupling (7) (Ref: TASK 51−80−00−760−803).
(7) Install the preformed packings (6) on the scavenge return fitting (28) and the
scavenge return manifold (4).
(8) Remove the protective plug from the scavenge return manifold (4). Connect the
scavenge return manifold to the scavenge return fitting (28) with the retainer (5).
Connect the coupling (3) (Ref. TASK 20−30−00−910−802).
(9) Remove the protective plug from the vent line (2). Connect the vent line to the
collector tank (1).

Subtask 28−11−03−430−002
D. Install the gravity feed manifold (Ref. TASK 28−13−28−400−801).
E. Install the primary ejector pump (Ref. TASK 28−21−01−400−801).

3. Close Out
Subtask 28−11−03−410−001
A. If the left collector tank is replaced, install the access panel that follows (Ref. TASK
28−11−01−400−801):
ACCESS DESCRIPTION
510AB Fuel tank access panel
B. If the right collector tank is replaced, install the access panel that follows (Ref. TASK
28−11−01−400−802):
ACCESS DESCRIPTION
610AB Fuel tank access panel

Master
EFFECTIVITY: See Pageblock 28−11−03 page 401
28−11−03 Page 408
Sep 10/2004
 C
AIRCRAFT MAINTENANCE MANUAL
Subtask 28−11−03−710−001
C. Do an operational test of the applicable electric boost pump (Ref. TASK
28−23−01−710−801).

Subtask 28−11−03−941−001
D. Remove all tools, equipment, and unwanted materials from the area.

Master
EFFECTIVITY: See Pageblock 28−11−03 page 401
28−11−03 Page 409
Jun 22/2004
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C ALL
CHECK VALVE, COLLECTOR TANK − REMOVAL/INSTALLATION

1. General
A. The maintenance procedures that follow are for the removal and installation of the
collector tank check valve (written as the "check valve" in this procedure). There are two
check valves in the fuel system. There is one check valve installed in each collector tank,
on the gravity feed manifold.
B. It is necessary to defuel, drain, and remove the fuel fumes from the aircraft to remove or
install the check valve.

TASK 28−11−05−000−801
Removal of the Collector Tank Check Valve

1. Job Set−Up Information

Subtask 28−11−05−946−001
A. Reference Information
REFERENCE DESIGNATION
TASK 28−00−00−910−801 Fuel Safety Precautions
TASK 28−13−28−000−801 Removal of the Gravity Feed Manifold
SRM 51−42−10 Structural Repair Manual
TASK 28−11−03−000−801 Removal of the Collector Tank

2. Job Set−Up
Subtask 28−11−05−910−001
WARNING: OBEY ALL THE FUEL SAFETY PRECAUTIONS WHEN YOU DO WORK ON THE
FUEL SYSTEM AND/OR A FUEL SYSTEM COMPONENT. IF YOU DO NOT DO
THIS, YOU CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO
EQUIPMENT.
A. Obey all the fuel safety precautions (Ref. TASK 28−00−00−910−801).

Subtask 28−11−05−010−001
B. Remove the gravity feed manifold (Ref. TASK 28−13−28−000−801).
C. Remove the Collector Tank (Ref. TASK 28−11−03−400−801).

3. Procedure
Subtask 28−11−05−020−001
Refer to Figure 401.

Master
EFFECTIVITY: See Pageblock 28−11−05 page 401
28−11−05 Page 401
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
A. Remove the check valve as follows:
(1) Remove the bolts (1), the preformed packings (2), the washers (3), and the fitting
(4) from the collector tank (5).
(2) Remove the rivets (6) and the tube assembly (7) from the fitting (4) (Ref.SRM
51−42−10).
(3) Remove the preformed packing (8) from the fitting (4).
(4) Remove the nuts (11), the washers (12), the bolts (13), and the check valve (14)
from the fitting (4).

Master
EFFECTIVITY: See Pageblock 28−11−05 page 401
28−11−05 Page 402
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

LEGEND
1. Bolt. 11. Nut.
2. Preformed packing. 12. Washer.
3. Washer. 13. Bolt.
4. Fitting. 14. Check valve.
5. Collector tank.
6. Rivet.
7. Tube assembly.
8. Preformed packing.
9. Split ring.
10. Coupling nut.
9
10

4
8
11
14
12
13
1
3
2

5
6

ram2811054_001(2).dc, rs/kms, 4/07/95

NOTE
Left side is shown.
Right side is the opposite.

Collector Tank Check Valve − Removal/Installation

Figure 401

Master
EFFECTIVITY: See Pageblock 28−11−05 page 401
28−11−05 Page 403
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
TASK 28−11−05−400−801
Installation of the Collector Tank Check Valve

1. Job Set−Up Information

Subtask 28−11−05−944−002
A. Consumable Material
REFERENCE DESIGNATION
06−002 Petrolatum

Subtask 28−11−05−945−001
B. Parts
REF NAME OF PART QTY IPC SEQUENCE NO.
1 Bolt 2 IPC 28−11−03−1A−050
2 Preformed packing 2 TBD
3 Washer 2 IPC 28−11−03−1A−055
6 Rivet 3 TBD
8 Preformed packing 1 IPC 28−11−03−1A−085
11 Nut 2 IPC 28−11−03−1A−070
12 Washer 2 TBD
13 Bolt 2 IPC 28−11−03−1A−065

Subtask 28−11−05−946−002
C. Reference Information
REFERENCE DESIGNATION
TASK 28−13−28−400−801 Installation of the Gravity Feed Manifold
TASK 28−11−03−400−801 Installation of the Collector Tank
SRM 51−42−10 Structural Repair Manual

2. Procedure
Subtask 28−11−05−869−001
A. Make sure that the aircraft is in the same configuration as in the removal task.

Subtask 28−11−05−420−001
Refer to Figure 401.
B. Install the check valve as follows:
(1) Install the check valve (14), the washers (12), the bolts (13), and the nuts (11) on
the fitting (4).
(2) Lubricate the preformed packing (8) with petrolatum and install the preformed
packing (8) on the fitting (4).

Master
EFFECTIVITY: See Pageblock 28−11−05 page 401
28−11−05 Page 404
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
(3) Install the tube assembly (7) to the fitting (4) with the rivets (6) (Ref. SRM
51−42−10).
(4) Install the tube assembly (7) and the fitting (4) in the collector tank (5).
(5) Lubricate the preformed packings (2) with petrolatum and install the preformed
packings (2), the washers (3), and the bolts (1).

3. Close Out
Subtask 28−11−05−410−001
A. Install the collector tank (Ref. TASK 28−11−03−400−801).
B. Install the gravity feed manifold (Ref. TASK 28−13−28−400−801).

Master
EFFECTIVITY: See Pageblock 28−11−05 page 401
28−11−05 Page 405
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C ALL
COLLECTOR TANK CHECK VALVE − ADJUSTMENT/TEST

1. General
A. This is a scheduled maintenance test of the collector tank check valve. There are two
steps to the procedure to check the operation of the collector tank check valve. The first
step makes sure that the collector tank check valve lets the fuel flow into the collector
tank. The second part of the procedure makes sure that the collector tank check valve
prevents the fuel from flowing out of the collector tank.

TASK 28−11−05−720−801
Functional Test of the Collector Tank Check Valve
1. Reason for the Job
Refer to MRB 28−21−00−05

2. Job Set−Up Information

Subtask 28−11−05−943−001
A. Tools and Equipment
REFERENCE DESIGNATION
None specified Funnel, flexible hose
None specified Container, 5 gallons

Subtask 28−11−05−944−003
B. Consumable Materials
REFERENCE DESIGNATION
09−034 Sealant, lightweight fuel tank

Subtask 28−11−05−945−002
C. Parts
REF NAME OF PART QTY IPC SEQUENCE NO.
2 Bolt 4 IPC 28−11−03−01−195
3 Retainer 4 IPC 28−11−03−01−200
5 Gasket 1 IPC 28−11−03−01−205

Subtask 28−11−05−946−003
D. Reference Information

Master
EFFECTIVITY: See Pageblock 28−11−05 page 501
28−11−05 Page 501
Aug 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL

REFERENCE DESIGNATION
TASK 12−11−28−650−804 Suction Defueling
TASK 12−11−28−650−805 Gravity Defueling
TASK 28−00−00−910−801 Fuel Safety Precautions
TASK 28−11−00−840−801 Prepare Fuel Tank for Access
TASK 28−11−00−840−802 Removal of Fuel Fumes
TASK 28−11−01−000−802 Removal of the Aluminum Access Panel
TASK 28−11−01−400−802 Installation of the Aluminum Access Panel
TASK 51−23−00−390−808 Application of Sealant with Brush

3. Job Set−Up
Subtask 28−11−05−910−002
WARNING: OBEY ALL THE FUEL SAFETY PRECAUTIONS WHEN YOU DO WORK ON THE
FUEL SYSTEM AND/OR A FUEL SYSTEM COMPONENT. IF YOU DO NOT DO
THIS, YOU CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO
EQUIPMENT.
A. Obey all the fuel safety precautions (Ref. TASK 28−00−00−910−801).

4. Procedure
Refer to Figure 501.
Subtask 28−11−05−720−001
A. Do the functional test of the collector tank check valves as follows:
NOTE: There must be a minimum of 250 lbs (113 kg) of fuel in each of the main tanks.
This is to make sure that the inlet to the gravity feed line for the collector tank
check valve is below the fuel level.
(1) Put the container under the collector tank water drain valve to catch the drained
fuel.
(2) Drain fuel from the collector tank through the collector tank water drain valve.
NOTE: To make sure that the collector tank check valve is operating correctly,
you must drain more than 10 gallons (38 liters) from the collector tank
drain valve.
(3) Defuel the aircraft (Ref. TASK 12−11−28−650−804 and TASK
12−11−28−650−805).
(4) To gain access to the left collector tank, remove the access panel that follows (Ref.
TASK 28−11−01−000−802):
ACCESS DESIGNATION
510AB Fuel Tank Access Panel
(5) To gain access to the right collector tank, remove the access panel that follows
(Ref. TASK 28−11−01−000−802):

Master
EFFECTIVITY: See Pageblock 28−11−05 page 501
28−11−05 Page 502
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

ACCESS DESIGNATION
610AB Fuel Tank Access Panel
(6) Prepare the center tank for access (Ref. TASK 28−11−00−840−801).
(7) Remove the fuel fumes from the center tank (Ref. TASK 28−11−00−840−802).
(8) Remove the bolts (2) and the retainers (3) from the cover plate (4) on the top of the
collector tank (1).
(9) Remove the cover plate (4) and the gasket (5). Discard the gasket.
(10) Use the funnel to put approximately ten gallons of clean fuel into the collector tank
(1), at the location where the fitting was connected.
NOTE: Make sure the collector tank is full and note the fuel level using a clean
wood stick or a visual check on the tank structure.
(11) Keep the fuel in the collector tank for two hours and make sure that the fuel level
does not change.

5. Close Out
Subtask 28−11−05−650−002
A. Drain the collector tank (Ref. TASK 12−11−28−650−805).

Subtask 28−11−05−420−004
Refer to Figure 501.
B. Connect the fitting to the collector tank (2) as follows:
(1) Install the gasket (5) and the cover plate (4) with the retainers (3) and the bolts (2).
(2) Apply sealant to all the bolts (2) (ref. TASK 51−23−00−390−808).

Subtask 28−11−05−410−002
C. Install the access panels that follow:
(1) For the left collector tank, install the access panel that follows (Ref. TASK
28−11−01−400−802):
ACCESS DESIGNATION
510AB Fuel Tank Access Panel
(2) For the right collector tank, install the access panel that follows (Ref. TASK
28−11−01−400−802):
ACCESS DESIGNATION
610AB Fuel Tank Access Panel

Subtask 28−11−05−941−001
D. Remove all tools, equipment, and unwanted materials from the work area.

Master
EFFECTIVITY: See Pageblock 28−11−05 page 501
28−11−05 Page 503
Aug 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL

LEGEND
1. Collector tank.
2. Bolt.
3. Retainer.
4. Cover plate.
5. Gasket.

A
NOTES
1. Left side is shown.
Right side is the opposite.
2 Brushcoat sealant.
2 2

ram2811055_004.dg, pm/yf, 12/05/05

Collector Tank Check−Valve − Functional Test

Figure 501

Master
EFFECTIVITY: See Pageblock 28−11−05 page 501
28−11−05 Page 504
Aug 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C ALL
VALVE, ONE−WAY FLOW − REMOVAL/INSTALLATION

1. General
A. The maintenance procedures that follow are for the removal and installation of the
one−way flow valve. There are 15 one−way flow valves in each main tank, installed in
the fuel tank ribs at the wing stations that follow:
± Seven one−way flow valves at WS85.5
± Seven one−way flow valves at WS148.0
± One one−way flow valve at WS220.
B. It is necessary to defuel, drain, and remove the fuel fumes from the applicable main tank
to remove or install the one−way flow valves.

TASK 28−11−07−000−801
Removal of the One−Way Flow Valve

1. Job Set−Up Information

Subtask 28−11−07−946−001
A. Reference Information
REFERENCE DESIGNATION
TASK 12−11−28−650−804 Suction Defueling
TASK 28−00−00−910−801 Fuel Safety Precautions
TASK 28−11−00−840−801 Prepare Fuel Tank for Access
TASK 28−11−00−840−802 Removal of Fuel Fumes
TASK 28−11−01−000−802 Removal of the Graphite Access Panel

2. Job Set−Up
Subtask 28−11−07−910−001
WARNING: OBEY ALL THE FUEL SAFETY PRECAUTIONS WHEN YOU DO WORK ON THE
FUEL SYSTEM AND/OR A FUEL SYSTEM COMPONENT. IF YOU DO NOT DO
THIS, YOU CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO
EQUIPMENT.
A. Obey all of the fuel safety precautions (Ref. TASK 28−00−00−910−801).

Subtask 28−11−07−650−001
B. Defuel the applicable main tank (Ref. TASK 12−11−28−650−804).

Subtask 28−11−07−010−001
C. Remove the applicable access panels that follow (Ref. TASK 28−11−01−000−802):

Master
EFFECTIVITY: See Pageblock 28−11−07 page 401
28−11−07 Page 401
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

ACCESS DESIGNATION ITEM

540CB Fuel tank access panel One−way flow valves at WS85.5L
540DB Fuel tank access panel One−way flow valves at WS85.5L
540FB Fuel tank access panel One−way flow valves at WS148.0L
550AB Fuel tank access panel One−way flow valves at WS148.0L
550CB Fuel tank access panel One−way flow valves at WS220L
550DB Fuel tank access panel One−way flow valves at WS220L
640CB Fuel tank access panel One−way flow valves at WS85.5R
640DB Fuel tank access panel One−way flow valves at WS85.5R
640FB Fuel tank access panel One−way flow valves at WS148.0R
650AB Fuel tank access panel One−way flow valves at WS148.0R
650CB Fuel tank access panel One−way flow valves at WS220R
650DB Fuel tank access panel One−way flow valves at WS220R

Subtask 28−11−07−840−001
D. Prepare the applicable main tank for access (Ref. TASK 28−11−00−840−801).
E. Remove the fuel fumes from the applicable main tank (Ref. TASK 28−11−00−840−802).

3. Procedure
Subtask 28−11−07−020−001
Refer to Figure 401.
A. Remove the one−way flow valve as follows:
(1) Remove the nuts (1), the washers (2), and the bolts (3) or (4).
NOTE: The bolts used at WS148.0 (3) are longer than the other bolts (4). If more
than one one−way flow valve is removed, identify the bolts for the
installation procedure.
(2) Remove the one−way flow valve (5).

Master
EFFECTIVITY: See Pageblock 28−11−07 page 401
28−11−07 Page 402
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

WS220.0

WS148.0

WS85.5

NOTE:
Left side is shown.
Right side is the opposite. 2

ram2811074_001(1).dc, ks, 04/01/93

LEGEND.
1. Nut. 3 or 4
2. Washer.
5
3. Bolt (at WS148.0).
4. Bolt (at WS85.5 and WS220).
5. One−way flow valve. TYPICAL

One−Way Flow Valve − Removal/Installation

Figure 401

Master
EFFECTIVITY: See Pageblock 28−11−07 page 401
28−11−07 Page 403
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
TASK 28−11−07−400−801
Installation of the One−Way Flow Valve

1. Job Set−Up Information

Subtask 28−11−07−945−001
A. Parts
REF NAME OF PART QTY IPC SEQUENCE NO.
1 Nut 2 IPC 28−11−07−1A−030
2 Washer 4 IPC 28−11−07−1A−025
3 Bolt 2 IPC 28−11−07−1A−015
4 Bolt 2 IPC 28−11−07−1A−020

Subtask 28−11−07−946−002
B. Reference Information
REFERENCE DESIGNATION
TASK 28−11−01−400−802 Installation of the Graphite Access Panel

2. Procedure
Subtask 28−11−07−869−001
A. Make sure that the aircraft is in the same configuration as in the removal task.

Subtask 28−11−07−420−001
Refer to Figure 401.
B. Install the one−way flow valve as follows:
(1) Hold the one−way flow valve (5) in position and install the washers (2) and the bolts
(3) or (4). Make sure that the one−way flow valve and the heads of the bolts are on
the inboard side of the tank rib.
NOTE: The bolts (4) used at WS148.0 are longer than the bolts (3) used at the
other locations. Use the correct bolts.
(2) Install the nuts (1).

3. Close Out
Subtask 28−11−07−410−001
A. Install the applicable access panels that follow (Ref. TASK 28−11−01−400−802):
ACCESS DESIGNATION ITEM
540CB Fuel tank access panel One−way flow valves at WS85.5L
540DB Fuel tank access panel One−way flow valves at WS85.5L
540FB Fuel tank access panel One−way flow valves at WS148.0L
550AB Fuel tank access panel One−way flow valves at WS148.0L

Master
EFFECTIVITY: See Pageblock 28−11−07 page 401
28−11−07 Page 404
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

ACCESS DESIGNATION ITEM

550CB Fuel tank access panel One−way flow valve at WS220L
550DB Fuel tank access panel One−way flow valve at WS220L
640CB Fuel tank access panel One−way flow valves at WS85.5R
640DB Fuel tank access panel One−way flow valves at WS85.5R
640FB Fuel tank access panel One−way flow valves at WS148.0R
650AB Fuel tank access panel One−way flow valves at WS148.0R
650CB Fuel tank access panel One−way flow valve at WS220R
650DB Fuel tank access panel One−way flow valve at WS220R

Subtask 28−11−07−941−001
B. Remove all tools, equipment, and unwanted materials from the area.

Master
EFFECTIVITY: See Pageblock 28−11−07 page 401
28−11−07 Page 405
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C ALL
VALVE, WATER DRAIN − MAINTENANCE PRACTICES

1. General
A. The maintenance procedure that follows is for the replacement of the primary preformed
packing of the water drain valve. It is not necessary to defuel the applicable fuel tank to
replace the preformed packing.

TASK 28−11−13−960−801
Replacement of the Preformed Packing

1. Job Set−Up Information

Subtask 28−11−13−944−003
A. Consumable Materials
REFERENCE DESIGNATION
06−002 Petrolatum
11−002 Solvent, dry cleaning and degreasing
05−001A Cloths, cleaning, for aircraft fuel tanks

Subtask 28−11−13−945−003
B. Expendable Parts
REF NAME OF PART QTY IPC SEQUENCE NO.
2 Preformed packing 1 IPC 28−11−13−1A−020

2. Procedure
Subtask 28−11−13−960−001
Refer to Figure 201.
A. Replace the preformed packing as follows:
(1) Use a screwdriver to turn the valve poppet (1) of the water drain valve slowly
clockwise until the valve poppet is fully extended.
(2) Remove the preformed packing (2) from the valve poppet (1).
(3) Lubricate a new preformed packing with petrolatum.
(4) Install the new preformed packing (2) on the valve poppet (1).
(5) Use a screwdriver to turn the valve poppet (1) counterclockwise until the valve
poppet is fully locked in the closed position.

Master
EFFECTIVITY: See Pageblock 28−11−13 page 201
28−11−13 Page 201
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
3. Close Out
Subtask 28−11−13−210−002
A. Clean the area around the water drain valve with the solvent and a clean cloth.
B. Examine the area around the water drain valve for leaks.

Subtask 28−11−13−941−002
C. Remove all tools, equipment, and unwanted materials from the area.

Master
EFFECTIVITY: See Pageblock 28−11−13 page 201
28−11−13 Page 202
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

NOTE
Right side is shown.
Left side is the opposite.

LEGEND.
1. Valve poppet.
2. Preformed packing.

ram2811132_001(1).dg, pb/sw, 07/08/95

Water Drain Valve − Maintenance Practices

Figure 201

Master
EFFECTIVITY: See Pageblock 28−11−13 page 201
28−11−13 Page 203
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C ALL
VALVE, WATER DRAIN − REMOVAL/INSTALLATION

1. General
A. The maintenance procedures that follow are for the removal and installation of the water
drain valve and the water drain housing. There are 14 water drain valves in the fuel
system. Six of the water drain valves are on the lower wing skin of the center wing box.
The other eight water drain valves are on the lower wing skin of the main tanks. Each
water drain valve has a water drain housing.
B. It is necessary to defuel and drain the related fuel tank to remove or install the water
drain valve.
C. It is also necessary to remove the fuel fumes from the related fuel tank to remove the
water drain housing.

TASK 28−11−13−000−801
Removal of the Water Drain Valve

1. Job Set−Up Information

Subtask 28−11−13−943−001
A. Tools and Equipment
REFERENCE DESIGNATION
None specified Container, 5−U.S.−gallon (20 L)
G601R281101−1 (2−pins) Tool, Fuel Drain−Valve Removal
or
G601R281101−9 (4−pins)

Subtask 28−11−13−946−001
B. Reference Information
REFERENCE DESIGNATION
TASK 12−11−28−650−804 Suction Defueling
TASK 28−00−00−910−801 Fuel Safety Precautions

Master
EFFECTIVITY: See Pageblock 28−11−13 page 401
28−11−13 Page 401
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
2. Job Set−Up
Subtask 28−11−13−910−001
WARNING: OBEY ALL THE FUEL SAFETY PRECAUTIONS WHEN YOU DO WORK ON THE
FUEL SYSTEM AND/OR A FUEL SYSTEM COMPONENT. IF YOU DO NOT DO
THIS, YOU CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO
EQUIPMENT.
A. Obey all the fuel safety precautions (Ref. TASK 28−00−00−910−801).

Subtask 28−11−13−650−001
B. Defuel the applicable fuel tank (Ref. TASK 12−11−28−650−804).

3. Procedure
Subtask 28−11−13−680−001
Refer to Figure 401.
A. Put a fuel container directly below the water drain valve (1).
B. Push in and turn the core of the water drain valve (1) 1/4 turn counterclockwise with a
screwdriver to open the water drain valve.
C. Drain the unwanted fuel into the container.

Subtask 28−11−13−020−001
D. Remove the water drain valve as follows:
(1) Use the drain−valve tool to remove the water drain valve (1).
(2) Remove and discard the preformed packing (2).

Master
EFFECTIVITY: See Pageblock 28−11−13 page 401
28−11−13 Page 402
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

NOTE:
Right side is shown.
Left side is the opposite.

LOWER WING
SKIN (REF)

LEGEND.
1. Water drain valve.
2. Preformed packing.

1
ram2811134_001.dg, KS, 20/08/92

Water Drain Valve − Removal/Installation

Figure 401

Master
EFFECTIVITY: See Pageblock 28−11−13 page 401
28−11−13 Page 403
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
TASK 28−11−13−400−801
Installation of the Water Drain Valve

1. Job Set−Up Information

Subtask 28−11−13−943−002
A. Tools and Equipment
REFERENCE DESIGNATION
G601R281101−1 (2−pins) Tool, Fuel Drain−Valve Removal
or
G601R281101−9 (4−pins)

Subtask 28−11−13−944−001
B. Consumable Materials
REFERENCE DESIGNATION
06−002 Petrolatum

Subtask 28−11−13−945−001
C. Parts
REF NAME OF PART QTY IPC SEQUENCE NO.
2 Preformed packing 1 IPC 28−11−13−1A−020

Subtask 28−11−13−946−002
D. Reference Information
REFERENCE DESIGNATION
TASK 12−11−28−650−801 Automatic Pressure Refueling

2. Procedure
Subtask 28−11−13−869−001
A. Make sure that the aircraft is in the same configuration as in the removal task.

Subtask 28−11−13−420−001
Refer to Figure 401.
B. Install the water drain valve as follows:
(1) Lubricate the preformed packing (2). Install the preformed packing on the water
drain valve (1).
(2) Install the water drain valve (1). Carefully tighten the water drain valve with the
drain−valve tool.
(3) Turn the core of the water drain valve (1) clockwise with a screwdriver to make sure
that the water drain valve is closed.

Master
EFFECTIVITY: See Pageblock 28−11−13 page 401
28−11−13 Page 404
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
3. Close Out
Subtask 28−11−13−210−001
A. Refuel the applicable fuel tank (Ref. TASK 12−11−28−650−801).
B. Examine the area around the water drain valve for leaks.

Subtask 28−11−13−941−001
C. Remove all the tools, equipment, and unwanted materials from the area.

Master
EFFECTIVITY: See Pageblock 28−11−13 page 401
28−11−13 Page 405
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
TASK 28−11−13−000−802
Removal of the Water Drain Housing

1. Job Set−Up Information

Subtask 28−11−13−943−003
A. Tools and Equipment
REFERENCE DESIGNATION
None specified Scraper, nonmetallic

Subtask 28−11−13−946−003
B. Reference Information
REFERENCE DESIGNATION
TASK 28−00−00−910−801 Fuel Safety Precautions
TASK 28−11−00−840−801 Prepare Fuel Tank for Access
TASK 28−11−00−840−802 Removal of Fuel Fumes
TASK 28−11−01−000−801 Removal of the Honeycomb Access Panel
TASK 28−11−01−000−802 Removal of the Graphite Access Panel
TASK 28−11−13−000−801 Removal of the Water Drain Valve

2. Job Set−Up
Subtask 28−11−13−910−002
WARNING: OBEY ALL THE FUEL SAFETY PRECAUTIONS WHEN YOU DO WORK ON THE
FUEL SYSTEM AND/OR A FUEL SYSTEM COMPONENT. IF YOU DO NOT DO
THIS, YOU CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO
EQUIPMENT.
A. Obey all the fuel safety precautions (Ref. TASK 28−00−00−910−801).

Subtask 28−11−13−010−001
B. Remove the water drain valve (Ref. TASK 28−11−13−000−801).

Subtask 28−11−13−010−002
C. Remove the applicable access panels that follow (Ref. TASK 28−11−01−000−802):
ACCESS DESIGNATION ITEM
540AB Fuel tank access panel Left water drain valve at WS48.0
540CB Fuel tank access panel Left water drain valve at WS69.0
540DB Fuel tank access panel Left water drain valve at WS88.5
550AB Fuel tank access panel Left water drain valve at WS151.0
610AB Fuel tank access panel Water drain valves in the right
center wing box
640AB Fuel tank access panel Right water drain valve at WS48.0

Master
EFFECTIVITY: See Pageblock 28−11−13 page 401
28−11−13 Page 406
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

ACCESS DESIGNATION ITEM

640CB Fuel tank access panel Right water drain valve at WS69.0
640DB Fuel tank access panel Right water drain valve at WS88.5
650AB Fuel tank access panel Right water drain valve at WS151.0

Subtask 28−11−13−010−003
D. Remove the applicable access panels that follow (Ref. TASK 28−11−01−000−801):
ACCESS DESIGNATION ITEM
510AB Fuel tank access panel Water drain valves in the left center
wing box

Subtask 28−11−13−840−001
E. Prepare the applicable fuel tank for access (Ref. TASK 28−11−00−840−801).
F. Remove the fuel fumes from the applicable fuel tank (Ref. TASK 28−11−00−840−802).

3. Procedure
Subtask 28−11−13−020−002
Refer to Figure 402.
A. To remove a water drain housing for the wing tanks, do the steps that follow:
(1) Use a nonmetallic scraper to remove the sealant from the nuts (1) and the
washers (2).
(2) Remove the nuts (1), the washers (2), the uniseal bolts (3), and the water drain
housing (4). Discard the nuts, the washers, and the uniseal bolts.

Subtask 28−11−13−020−003
Refer to Figure 403.
B. To remove a water drain housing for the collector tanks, do the steps that follow:
(1) Disconnect the drain line (5). Put a protective plug in the drain line.
(2) Remove the union (6) and the preformed packing (7). Discard the preformed
packing.
(3) Use a nonmetallic scraper to remove the sealant from the nuts (8) and the
washers (9).
(4) Remove the nuts (8), the washers (9), and the uniseal bolts (10). Discard the nuts,
the washers, and the uniseal bolts.
(5) Remove the water drain housing (11) and the gasket (12).

Subtask 28−11−13−020−004
Refer to Figure 404.

Master
EFFECTIVITY: See Pageblock 28−11−13 page 401
28−11−13 Page 407
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
C. To remove a water drain housing for the boost pumps, do the steps that follow:
(1) Disconnect the pressure line (13) from the boost pump canister. Put a protective
plug in the pressure line.
(2) Remove the union (14) and the preformed packing (15). Discard the preformed
packing.
(3) Remove the bolts (16) and the washers (17) from the pickup assembly (18).
(4) Move the pickup cover (19) and the gasket (20) from the pickup assembly (18) to
remove the water drain housing.
NOTE: You cannot remove the pickup cover and the gasket from the boost pump
canister. Move the pickup cover and the gasket a sufficient distance along
the electrical conduit to permit access to the water drain housing.
(5) Use a nonmetallic scraper to remove the sealant from the nuts (21) and the
washers (22).
(6) Remove the nuts (21), the washers (22), and the uniseal bolts (23). Discard the
nuts, the washers, and the uniseal bolts.
(7) Remove the water drain housing (24) and the gasket (25). Discard the gasket.

Master
EFFECTIVITY: See Pageblock 28−11−13 page 401
28−11−13 Page 408
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

NOTE
Right side is shown.
Left side is the opposite.
3

4
ram2811134_002(2).dg, jp/sw, 07/08/95

LEGEND.
1. Nut.
2. Retainer.
3. Uniseal bolt.
4. Water drain housing.

Wing Tank Water Drain Housing − Removal/Installation

Figure 402

Master
EFFECTIVITY: See Pageblock 28−11−13 page 401
28−11−13 Page 409
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

NOTE
Right side is shown.
Left side is the opposite.
5

6
8 7
9

11
LEGEND.
5. Drain line.
6. Union.
7. Preformed packing.
8. Nut.
9. Washer.
12 10. Uniseal bolt.
11. Water drain housing.
LOWER WING
SKIN (REF) ram2811134_003(2).dg, ks/sw, 07/08/95

10

Collector Tank Water Drain Housing − Removal/Installation

Figure 403

Master
EFFECTIVITY: See Pageblock 28−11−13 page 401
28−11−13 Page 410
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

LEGEND
13. Pressure line.
14. Union.
15. Preformed packing.
16. Bolt.
17. Washer. A
18. Pickup assembly.
19. Pickup cover.
20. Gasket.
21. Nut.
22. Washer.
23. Uniseal bolt. 19 17 16
24. Water drain housing.
25. Gasket. 16
17

NOTE
Right side is shown.
Left side is the opposite. 20

13
21 ELECTRICAL
CONDUIT
22 (REF)
14
15
FULE BOOST
24 PUMP CANNISTER
(REF)

18

25
ram2811134_004.dg, ks/rm, 07/11/00

D
FW TB
D OU
B
A
23
B

Boost Pump Water Drain Housing − Removal/Installation

Figure 404

Master
EFFECTIVITY: See Pageblock 28−11−13 page 401
28−11−13 Page 411
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
TASK 28−11−13−400−802
Installation of the Water Drain Housing

1. Job Set−Up Information

Subtask 28−11−13−944−002
A. Consumable Materials
REFERENCE DESIGNATION
06−002 Petrolatum
09−013 Sealing compound

Subtask 28−11−13−945−002
B. Parts
REF NAME OF PART QTY IPC SEQUENCE NO.
1 Nut 2 IPC 28−11−13−1A−045
2 Washer 2 IPC 28−11−13−1A−040
3 Uniseal bolt 2 IPC 28−11−13−1A−035
6 Union 1 IPC 28−11−13−1A−110
7 Preformed packing 1 IPC 28−11−13−1A−125
8 Nut 2 IPC 28−11−13−1A−105
9 Washer 2 IPC 28−11−13−1A−100
10 Uniseal bolt 2 IPC 28−11−13−1A−095
12 Gasket 1 IPC 28−11−13−1A−135
14 Union 1 IPC 28−23−00−1A−255
15 Preformed packing 1 IPC 28−23−00−1A−260
16 Bolt 28 IPC 28−23−00−1A−240
17 Washer 28 IPC 28−23−00−1A−245
20 Gasket 1 IPC 28−23−00−1A−250
21 Nut 2 IPC 28−23−00−1A−225
22 Washer 2 IPC 28−23−00−1A−220
23 Uniseal bolt 2 IPC 28−23−00−1A−215
25 Gasket 1 IPC 28−23−00−1A−230

Subtask 28−11−13−946−004
C. Reference Information
REFERENCE DESIGNATION
TASK 28−11−01−400−801 Installation of the Honeycomb Access Panel
TASK 28−11−01−400−802 Installation of the Graphite Access Panel
TASK 28−11−13−400−801 Installation of the Water Drain Valve
TASK 51−23−00−390−808 Application of Sealant with Brush

Master
EFFECTIVITY: See Pageblock 28−11−13 page 401
28−11−13 Page 412
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
2. Job Set−Up
Subtask 28−11−13−869−002
A. Make sure that the aircraft is in the same configuration as in the removal task.

3. Procedure
NOTE: To install the valve bodies, there are three different uniseal bolts for the different valve
locations. If more than one water drain housing is removed, use the correct uniseal bolts
to install the valve bodies. Refer to the Illustrated Parts Catalog if necessary.
Subtask 28−11−13−420−002
Refer to Figure 402.
A. If a water drain housing for the wing tanks is removed, install the water drain housing as
follows:
(1) Lubricate the preformed packings on the uniseal bolts (3).
CAUTION: DO NOT TURN THE UNISEAL BOLTS DURING INSTALLATION.
DAMAGE TO THE PREFORMED PACKING ON THE UNISEAL BOLT
CAN OCCUR.
(2) Install the water drain housing (4), the uniseal bolts (3), the washers (2), and the
nuts (1).
(3) Apply the sealant to the washers (2) and the nuts (1).

Subtask 28−11−13−420−003
Refer to Figure 403.
B. If a water drain housing for the collector tanks is removed, install the water drain housing
as follows:
(1) Install the gasket (12) and the water drain housing (11).
(2) Lubricate the preformed packings on the uniseal bolts (10).
CAUTION: DO NOT TURN THE UNISEAL BOLTS DURING INSTALLATION.
DAMAGE TO THE PREFORMED PACKING ON THE UNISEAL BOLT
CAN OCCUR.
(3) Install the uniseal bolts (10), the washers (9), and the nuts (8).
(4) Apply the sealant to the washers (9) and the nuts (8).
(5) Lubricate and install the preformed packing (7) and the union (6) to the water drain
housing (11).
(6) Remove the protective plug from the drain line (5). Connect the drain line to the
union (6).

Subtask 28−11−13−420−004
Refer to Figure 404.
C. If a water drain housing for the boost pump is removed, install the water drain housing as
follows:

Master
EFFECTIVITY: See Pageblock 28−11−13 page 401
28−11−13 Page 413
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
(1) Apply sealing compound to the made to touch surfaces of the water drain housing
(24) and the pickup assembly (18) (Ref. TASK 51−23−00−390−808).
(2) Install the gasket (25) and the water drain housing (24).
(3) Lubricate the preformed packings on the uniseal bolts (23).
CAUTION: DO NOT TURN THE UNISEAL BOLTS DURING INSTALLATION.
DAMAGE TO THE PREFORMED PACKING ON THE UNISEAL BOLT
CAN OCCUR.
(4) Install the uniseal bolts (23), the washers (22), and the nuts (21).
(5) Apply the sealing compound to the washers (22) and the nuts (21).
(6) Connect the gasket (20) and the pickup cover (19) on the pickup assembly (18).
(7) Install the washers (17) and the bolts (16) on the pickup assembly (18).
(8) Install the preformed packing (15) and the union (14) on the boost pump canister.
(9) Remove the protective plug from the pressure line (13). Connect the pressure line
to the union (14).

4. Close Out
Subtask 28−11−13−410−001
A. Install the applicable access panels that follow (Ref. TASK 28−11−01−400−802)):
ACCESS DESIGNATION ITEM
540AB Fuel tank access panel Left water drain valve at WS48.0
540CB Fuel tank access panel Left water drain valve at WS69.0
540DB Fuel tank access panel Left water drain valve at WS88.5
550AB Fuel tank access panel Left water drain valve at WS151.0
610AB Fuel tank access panel Water drain valves in the right
center tank
640AB Fuel tank access panel Right water drain valve at WS48.0
640CB Fuel tank access panel Right water drain valve at WS69.0
640DB Fuel tank access panel Right water drain valve at WS88.5
650AB Fuel tank access panel Right water drain valve at WS151.0

Subtask 28−11−13−410−003
B. Install the applicable access panels that follow (Ref. TASK 28−11−01−400−801):
ACCESS DESIGNATION ITEM
510AB Fuel tank access panel Water drain valves in the left center
tank

Master
EFFECTIVITY: See Pageblock 28−11−13 page 401
28−11−13 Page 414
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
Subtask 28−11−13−410−002
C. Install the water drain valve (Ref. TASK 28−11−13−400−801).

Master
EFFECTIVITY: See Pageblock 28−11−13 page 401
28−11−13 Page 415
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C ALL
VALVE, FUEL DRAIN − REMOVAL/INSTALLATION

1. General
A. The maintenance procedures that follow are for the removal and installation of the fuel
drain valve. The aircraft can has three fuel drain valves in the fuel system. The fuel drain
valves are found on the lower wing skin of each fuel tank.
B. It is necessary to defuel and drain the applicable fuel tank to remove or install the fuel
drain valve.

TASK 28−11−14−000−801
Removal of the Fuel Drain Valve

1. Job Set−Up Information

Subtask 28−11−14−943−001
A. Tools and Equipment
REFERENCE DESIGNATION
None specified Container, 5−U.S.−gallon (20 L)
None specified Scraper, nonmetallic

Subtask 28−11−14−946−001
B. Reference Information
REFERENCE DESIGNATION
TASK 12−11−28−650−804 Suction Defueling
TASK 28−00−00−910−801 Fuel Safety Precautions
TASK 28−11−01−000−801 Removal of the Honeycomb Access Panel

2. Job Set−Up
Subtask 28−11−14−910−001
WARNING: OBEY ALL THE FUEL SAFETY PRECAUTIONS WHEN YOU DO WORK ON THE
FUEL SYSTEM AND/OR A FUEL SYSTEM COMPONENT. IF YOU DO NOT DO
THIS, YOU CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO
EQUIPMENT.
A. Obey all the fuel safety precautions (Ref. TASK 28−00−00−910−801).

Subtask 28−11−14−650−001
B. Defuel the applicable fuel tank (Ref. TASK 12−11−28−650−804).

Master
EFFECTIVITY: See Pageblock 28−11−14 page 401
28−11−14 Page 401
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
Subtask 28−11−14−680−001
C. Put a fuel container directly below the fuel drain valve.
D. Remove the cap from the fuel drain valve.
E. Drain the unwanted fuel into the fuel container with the closest inboard water drain.

Subtask 28−11−14−010−001
F. Remove the applicable access panel that follows (Ref. TASK 28−11−01−000−801):
ACCESS DESIGNATION ITEM
510AB Fuel tank access panel Center tank fuel drain valve
540BB Fuel tank access panel Left main tank fuel drain valve
640BB Fuel tank access panel Right main tank fuel drain valve

3. Procedure
Subtask 28−11−14−020−001
Refer to Figure 401.
A. Remove the fuel drain valve as follows:
(1) Use a nonmetallic scraper to remove the sealant from the nuts (1) and the
washers (2).
(2) Remove the nuts (1), the washers (2), and the uniseal bolts (3). Discard the nuts,
the washers, and the bolts.
(3) Remove the fuel drain valve (4) and the gasket (5). Discard the gasket.

Subtask 28−11−14−410−001
WARNING: INSTALL THE ACCESS PANEL AND A PROTECTIVE PLUG IN THE DRAIN
VALVE HOLE AFTER THE FUEL DRAIN VALVE IS REMOVED. WHILE THE
ACCESS PANEL IS REMOVED, FUEL FUMES FROM THE FUEL TANK CAN
CAUSE AN EXPLOSION.
B. Install the applicable access panel that follows:
NOTE: It is not necessary to install all of the screws on the access panel.
ACCESS DESIGNATION ITEM
510AB Fuel tank access panel Center tank fuel drain valve
540BB Fuel tank access panel Left main tank fuel drain valve
640BB Fuel tank access panel Right main tank fuel drain valve
C. Put a protective plug in the drain valve hole of the access panel.

Master
EFFECTIVITY: See Pageblock 28−11−14 page 401
28−11−14 Page 402
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

LEGEND.
1. Nut.
2. Washer.
3. Uniseal bolt.
4. Fuel drain valve.
5. Gasket.

1
NOTE
Right side shown. 2
Left side is the opposite.

ram2811144_001(1).dc, pb, 11/03/93

ACCESS
PANEL
(REF)

Fuel Drain Valve − Removal/Installation

Figure 401

Master
EFFECTIVITY: See Pageblock 28−11−14 page 401
28−11−14 Page 403
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
TASK 28−11−14−400−801
Installation of the Fuel Drain Valve

1. Job Set−Up Information

Subtask 28−11−14−944−001
A. Consumable Materials
REFERENCE DESIGNATION
06−002 Petrolatum
09−013 Sealing compound

Subtask 28−11−14−945−001
B. Parts
REF NAME OF PART QTY IPC SEQUENCE NO.
1 Nut 4 IPC 28−11−14−1A−020
2 Washer 4 IPC 28−11−14−1A−015
3 Uniseal bolt 4 IPC 28−11−14−1A−010
5 Gasket 1 IPC 28−11−14−1A−025

Subtask 28−11−14−946−002
C. Reference Information
REFERENCE DESIGNATION
TASK 12−11−28−650−801 Automatic Pressure Refueling
TASK 28−11−01−400−801 Installation of the Honeycomb Access Panel
TASK 51−23−00−390−808 Application of Sealant with a Brush

2. Job Set−Up
Subtask 28−11−14−869−001
A. Make sure that the aircraft is in the same configuration as in the removal task.

Subtask 28−11−14−010−003
B. Remove the applicable access panel that follows:
ACCESS DESIGNATION ITEM
510AB Fuel tank access panel Center tank fuel drain valve
540BB Fuel tank access panel Left main tank fuel drain valve
640BB Fuel tank access panel Right main tank fuel drain valve
C. Remove the protective plug from the access panel.

Master
EFFECTIVITY: See Pageblock 28−11−14 page 401
28−11−14 Page 404
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
3. Procedure
Subtask 28−11−14−420−001
Refer to Figure 401.
A. Install the fuel drain valve as follows:
(1) Install the gasket (5) and the fuel drain valve (4).
(2) Lubricate the preformed packings on the uniseal bolts (3).
CAUTION: DO NOT TURN THE UNISEAL BOLTS DURING INSTALLATION.
DAMAGE TO THE PREFORMED PACKING ON THE UNISEAL BOLT
CAN OCCUR.
(3) Install the uniseal bolts (3), the washers (2), and the nuts (1).
(4) Torque the nuts (1) from 20 to 25 lbf in (2.25 to 2.82 N m).
NOTE: The nut shall be turned during torquing whenever possible.
(5) Apply the sealing compound to the nuts (1) and the washers (2) (Ref. TASK
51−23−00−390−808).

4. Close Out
Subtask 28−11−14−410−002
A. Install the applicable access panel that follows (Ref. TASK 28−11−01−400−801):
ACCESS DESIGNATION ITEM
510AB Fuel tank access panel Center tank fuel drain valve
540BB Fuel tank access panel Left main tank fuel drain valve
640BB Fuel tank access panel Right main tank fuel drain valve

Subtask 28−11−14−210−001
B. Refuel the applicable fuel tank (Ref. TASK 12−11−28−650−801).
C. Examine the area around the fuel drain valve for leaks.
D. Install the cap in the fuel drain valve.

Subtask 28−11−14−941−001
E. Remove all the tools, equipment, and unwanted materials from the area.

Master
EFFECTIVITY: See Pageblock 28−11−14 page 401
28−11−14 Page 405
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C ALL
FILLER INSTALLATION, GRAVITY FUEL FEED, CENTER TANK − REMOVAL/INSTALLATION

1. General
A. The maintenance procedure that follows is for the removal and installation of the
center−tank gravity−fuel−feed filler−cap (written as the "filler cap" in this procedure). The
filler cap is installed on the right wing, at WS 58.50.
B. It is necessary to defuel, drain and remove the fumes from the main and center fuel
tanks to remove or install the filler cap.

TASK 28−11−17−000−802
Removal of the Center−Tank Gravity−Fuel−Feed−Filler Installation

1. Job Set−Up Information

Subtask 28−11−17−943−002
A. Tools and Equipment
REFERENCE DESIGNATION
None specified Container, 5 U.S.−gallon (20 L)
None Specified Flat head screwdriver

Subtask 28−11−17−946−004
B. Reference Information
REFERENCE DESIGNATION
TASK 12−11−28−650−804 Suction Defueling
TASK 28−00−00−910−801 Fuel Safety Precautions
TASK 28−11−00−840−801 Prepare Fuel Tank for Access
TASK 28−11−00−840−802 Removal of Fuel Fumes

2. Job Set−Up
Subtask 28−11−17−910−003
WARNING: OBEY ALL THE FUEL SAFETY PRECAUTIONS WHEN YOU DO WORK ON THE
FUEL SYSTEM AND/OR A FUEL SYSTEM COMPONENT. IF YOU DO NOT DO
THIS, YOU CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO
EQUIPMENT.
A. Obey all the fuel safety precautions (Ref. TASK 28−00−00−910−801).

Subtask 28−11−17−650−002
B. Defuel the main and center fuel tanks (Ref. TASK 12−11−28−650−804).

Master
EFFECTIVITY: See Pageblock 28−11−17 page 401
28−11−17 Page 401
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
Subtask 28−11−17−840−002
C. Prepare the fuel tank for access (Ref. TASK 28−11−00−840−801).
D. Remove the fuel fumes from the fuel tanks (Ref. TASK 28−11−00−840−802).

Subtask 28−11−17−010−005
E. Open the applicable access panels that follow (Ref. TASK 28−11−01−000−801):
ACCESS DESIGNATION
640BB Access panel, main fuel tank
610BB Access panel, fuel tank (center)

Subtask 28−11−17−020−004
F. Remove the access door 640DT as follows:
(1) Use a flat head screwdriver and turn the four fasteners (1) counterclockwise to
unlock. Remove the access door 640DT.

3. Procedure
Subtask 28−11−17−020−005
Refer to Figure 401.
A. Remove the filler cap as follows:
(1) Remove the 12 bolts (2), the 12 washers (3) and the 12 nuts (4) from the filler
adapter (5), the scupper (6), the scupper support (7) and the split doubler (8).
Remove the filler adapter (5).
(2) Remove the four bolts (9), the four washers (10) and (11), and the four nuts (12)
from the scupper (6) and the scupper support (7).
(3) Put the container below the drain line (13) and loosen the connector (14). Remove
and discard the two preformed packings (15). Disconnect the drain line (13) from
the scupper (6).
(4) Remove the 12 nuts (16), the 12 washers (17) and the 12 bolts (18) from the duct
assembly (19).
(5) Use a non metallic scraper and remove all of the sealant from the scupper support
(7) and the split doubler (8). Retain the split doubler (8).
(6) Pull the duct assembly (19) away from the scupper (6), the scupper support (7) and
the rib location.
(7) Remove and discard the two gaskets (21) and (22).

Master
EFFECTIVITY: See Pageblock 28−11−17 page 401
28−11−17 Page 402
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

ACCESS DOOR
(640DT)
1

UPPER WING LEGEND

SURFACE
(REF) 1. Fastener. 12. Nut.
5 4
2. Bolt. 13. Drain line.
3 3. Washer. 14. Connector.
4. Nut. 15. Preformed packing.
5. Filler adapter. 16. Nut.
6. Scupper. 17. Washer.
7. Scupper support. 18. Bolt.
8. Split doubler. 19. Duct assembly.
9. Bolt. 20. Preformed packing.
6 10. Washer. 21. Gasket.
B 11. Washer. 22. Gasket.
12
11
13 D
21 RIB LOCATION INB
(REF) FW
D
7
14
10
22
18
9
15

8
ram2811174_002.dg, rm/sw, 18/07/01

13
20

19 2 17
16 B
A

Center−Tank Gravity−Fuel−Feed Filler−Cap − Removal/Installation

Figure 401

Master
EFFECTIVITY: See Pageblock 28−11−17 page 401
28−11−17 Page 403
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
TASK 28−11−17−400−802
Installation of the Center−Tank Gravity−Fuel−Feed−Filler Installation

1. Job Set−Up Information

Subtask 28−11−17−944−002
A. Consumable Materials
REFERENCE DESIGNATION
06−002 Petrolatum
09−013A Sealant

Subtask 28−11−17−945−002
B. Parts
REF NAME OF PART QTY IPC SEQUENCE NO.
1 Fastener 4 IPC 28−11−20−1A−170
2 Bolt 12 IPC 28−11−20−1A−040
3 Washer 12 IPC 28−11−20−1A− 045
4 Nut 12 IPC 28−11−20−1A−050
9 Bolt 4 IPC 28−11−20−1A−215
10 Washer 4 IPC 28−11−20−1A−220
11 Washer 4 IPC 28−11−20−1A−225
12 Nut 4 IPC 28−11−20−1A−230
15 Preformed packing 2 IPC 28−11−20−1A−105
16 Nut 12 IPC 28−11−20−1A−065
17 Washer 12 IPC 28−11−20−1A−060
18 Bolt 12 IPC 28−11−20−1A−055
20 Preformed packing 1 IPC 28−11−20−1A−015
21 Gasket 1 IPC 28−11−20−1A−235
22 Gasket 1 IPC 28−11−20−1A−020

Subtask 28−11−17−946−005
C. Reference Information
REFERENCE DESIGNATION
TASK 28−11−00−210−801 Visual Check of the Fuel Tank Exterior
TASK 12−11−28−650−801 Automatic Pressure Refueling
TASK 51−23−00−390−808 Application of Sealant with Brush

Master
EFFECTIVITY: See Pageblock 28−11−17 page 401
28−11−17 Page 404
Dec 15/2004
 C
AIRCRAFT MAINTENANCE MANUAL
2. Job Set−Up
Subtask 28−11−17−869−002
A. Make sure that the aircraft is in the same configuration as in the removal task.

3. Procedure
Subtask 28−11−17−420−002
Refer to Figure 401.
A. Install the filler cap as follows:
(1) Align the gasket (21) with the scupper (6) and the scupper support (7) and install
with the four bolts (9), the four washers (10) and (11), and the four nuts (12).
(2) Lubricate the preformed packing (20) and align at the rib location with the duct
assembly (19). Install with the 12 bolts (18), the 12 washers (17) and the 12 nuts
(16). Do not tighten the bolts (18) at this time.
(3) Apply the sealant to the top surface of the split doubler (8).
(4) Align the gasket (22) with the scupper support (7), the duct assembly (19), the filler
adapter (5) and the split doubler (8). Install with the twelve bolts (2), the twelve
washers (3), and the twelve nuts (4).
(5) Lubricate the two preformed packings (15) with the petrolatum 06−002 and install in
the retainers of the drain line (13). Connect the drain line (13) to the scupper (6).
Tighten the connector (14).

4. Close Out
Subtask 28−11−17−410−005
A. Install the applicable access panels that follow:
ACCESS DESIGNATION
640BB Access panel, main fuel tank
610BB Access panel, fuel tank (center)

Subtask 28−11−17−410−006
B. Install the access door 640DT as follows:
(1) Use a flat head screwdriver and turn the four fasteners (1) clockwise to lock.

Subtask 28−11−17−210−003
C. Refuel the main and the center tanks (Ref. TASK 12−11−28−650−801).
D. Examine the area around the fuel filler for leaks (Ref. TASK 28−11−00−210−801).

Master
EFFECTIVITY: See Pageblock 28−11−17 page 401
28−11−17 Page 405
Dec 15/2004
 C
AIRCRAFT MAINTENANCE MANUAL
Subtask 28−11−17−941−002
E. Remove all tools, equipment, and unwanted materials from the work area.

Master
EFFECTIVITY: See Pageblock 28−11−17 page 401
28−11−17 Page 406
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C ALL
FUEL FILLER−CAP O RING − INSPECTION/CHECK

1. General
A. This is a scheduled maintenance task for the visual check of the filler cap "o" ring.

TASK 28−11−17−210−801
Visual Check of the Fuel Filler−Cap "O" Ring
1. Reason for the Job
Refer to MRB 28−11−00−07

2. Job Set−Up
Subtask 28−11−17−010−001
A. Remove the gravity fuel filler−cap from the left, right and center fuel tanks.

3. Procedure
Refer to Figure 601.
Subtask 28−11−17−210−001
A. Do a visual check of the filler−cap "O" ring for condition and safety of installation.

4. Close Out
Subtask 28−11−17−941−001
A. Remove all tools, equipment, and unwanted materials from the work area.

Subtask 28−11−17−410−001
B. Install the gravity fuel filler−cap on the left, right and center fuel tanks.

Master
EFFECTIVITY: See Pageblock 28−11−17 page 601
28−11−17 Page 601
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

A
LEGEND
1. Filler cap.
2. O−ring.

2
ram2811176_001.dc, dm/pm, 09/05/96

Fuel Filler−Cap "O" Ring − Visual Check

Figure 601

Master
EFFECTIVITY: See Pageblock 28−11−17 page 601
28−11−17 Page 602
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C ALL
VENT SYSTEM − DESCRIPTION AND OPERATION

1. General
**ON A/C 7008, 7011−7014, 7017−7018, 7022, 7026−7035, 7037−7044, 7046, 7048, 7050, 7052,
7055−7056, 7061−7063, 7066−7067, 7069−7070, 7072, 7075−7077, 7079−7080, 7085, 7088,
7091−7092, 7094, 7099−7103, 7105−7106, 7108−7109 Pre SB601R−28−024
A. The vent system controls the atmospheric pressure in the fuel tanks. It contains the
components that follow:
± Two main−tank relief valves
± One center−tank relief valve
± Two vent−line−purge check valves
± The vent−line tubing
± The vent−line shrouds.
**ON A/C 7003−7007, 7009−7010, 7015−7016, 7019−7021, 7023−7025, 7036, 7045, 7047, 7049,
7051, 7053−7054, 7057−7060, 7064−7065, 7071, 7073−7074, 7078, 7081−7084, 7086−7087,
7089−7090, 7093, 7095−7098, 7104, 7107, 7110−7990, 8000−8064, 8066−8068 and ON A/C
7008, 7011−7014, 7017−7018, 7022, 7026−7035, 7037−7044, 7046, 7048, 7050, 7052,
7055−7056, 7061−7063, 7066−7067, 7069−7070, 7072, 7075−7077, 7079−7080, 7085, 7088,
7091−7092, 7094, 7099−7103, 7105−7106, 7108−7109 Post SB601R−28−024
B. The vent system controls the atmospheric pressure in the fuel tanks. It contains the
components that follow:
± Two main−tank relief valves
± One center−tank relief valve
± Two vent−line−purge check valves
± Two vent−flapper check valves
± The vent−line tubing
± The vent−line shrouds.
**ON A/C ALL
2. Component Details
**ON A/C 7008, 7011−7014, 7017−7018, 7022, 7026−7035, 7037−7044, 7046, 7048, 7050, 7052,
7055−7056, 7061−7063, 7066−7067, 7069−7070, 7072, 7075−7077, 7079−7080, 7085, 7088,
7091−7092, 7094, 7099−7103, 7105−7106, 7108−7109 Pre SB601R−28−024
Refer to Figure 1.
**ON A/C 7003−7007, 7009−7010, 7015−7016, 7019−7021, 7023−7025, 7036, 7045, 7047, 7049,
7051, 7053−7054, 7057−7060, 7064−7065, 7071, 7073−7074, 7078, 7081−7084, 7086−7087,
7089−7090, 7093, 7095−7098, 7104, 7107, 7110−7990, 8000−8064, 8066−8068 and ON A/C
7008, 7011−7014, 7017−7018, 7022, 7026−7035, 7037−7044, 7046, 7048, 7050, 7052,
7055−7056, 7061−7063, 7066−7067, 7069−7070, 7072, 7075−7077, 7079−7080, 7085, 7088,
7091−7092, 7094, 7099−7103, 7105−7106, 7108−7109 Post SB601R−28−024
Refer to Figure 2.

Master
EFFECTIVITY: See Pageblock 28−12−00 page 1
28−12−00 Page 1
Dec 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C ALL
A. Main−Tank Relief Valve
(1) The main−tank relief valves are spring−loaded, poppet−type valves that can
operate automatically or manually. They are installed at the outboard end of each
main tank.
(2) Each main−tank relief valve has a poppet, a spring, a valve body, and a manual
override handle. When pressure in the main tank is more than 4.0 psi (27.6 kPa),
the pressure pushes the poppet down. The relief valve opens fully when the
pressure in the main tank is 6.8 psi (46.9 kPa). When the poppet is down, the port
of the valve body opens. Pressure is then released from the fuel tanks through the
valve body, and to the outside atmosphere. When the pressure in the tanks is less
than 4.0 psi (27.6 kPa), the spring pushes the poppet back into position to close the
valve.
(3) There is a handle installed on the lower wing skin directly below the valve that is
used to open the valve manually. If the operator pulls this handle, the valve opens.
The handle is connected directly to the poppet and pulls the poppet down when the
handle is pulled.
B. Center−Tank Relief Valve
(1) The center−tank relief valve operates in the same way as the main−tank relief
valves. It is installed on the left side of the center tank.
C. Vent−Line−Purge Check Valve
(1) The vent−line−purge check valves are spring−loaded, swing−type valves. These
check valves close the vent lines when the suction ports in the scavenge ejectors
are below the fuel level. The vent−line−purge check valves are connected between
the suction port of the scavenge ejector and the vent line manifolds.
(2) Each vent−line−purge check valve has a swing assembly, a spring, and a valve
body. When fuel drains from the vent line manifold, it pushes against the swing
assembly. The swing assembly then opens the passage in the valve body, which
lets the fuel drain into the fuel tank through the scavenge ejector.
**ON A/C 7003−7007, 7009−7010, 7015−7016, 7019−7021, 7023−7025, 7036, 7045, 7047, 7049,
7051, 7053−7054, 7057−7060, 7064−7065, 7071, 7073−7074, 7078, 7081−7084, 7086−7087,
7089−7090, 7093, 7095−7098, 7104, 7107, 7110−7990, 8000−8064, 8066−8068 and ON A/C
7008, 7011−7014, 7017−7018, 7022, 7026−7035, 7037−7044, 7046, 7048, 7050, 7052,
7055−7056, 7061−7063, 7066−7067, 7069−7070, 7072, 7075−7077, 7079−7080, 7085, 7088,
7091−7092, 7094, 7099−7103, 7105−7106, 7108−7109 Post SB601R−28−024
D. Vent−Flapper Check Valve
(1) The vent−flapper check valves are spring −loaded bipetal valves that permit a one
way flow of fuel to the centre tank.
(2) Each vent−flapper check valve has a spring, a bipetal−flapper assembly, and a
valve seat. The valve seat holds the bipetal−flapper assembly in place in a flange
adaptor, installed in the vent−line tubing. When fuel pressure in the vent line tubing
pushes against the bipetal flapper assembly, it opens the two passages in the valve
seat. When fuel flow in the vent line tubing stops, the spring pushes the bipetal−
flapper assembly back in place, which closes the valve.

Master
EFFECTIVITY: See Pageblock 28−12−00 page 1
28−12−00 Page 2
Dec 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C ALL
E. Vent Line Tubing
(1) The vent line tubing is a series of tubes that connect the two air scoops to the fuel
tanks. The vent line tubing also connects the fuel tanks to each other. The vent line
tubing is open to the suction ports, one in each main tank and two in the center
tank.
(2) Air pressure flows through each main tank from the vent line tubing. This tubing
extends from the outboard section of each main tank to the center section, where it
goes out through the upper wing skin. The tubing then goes into the fuselage to
make an inverted U, goes back down through the wing box. From there, it goes out
through the rear spar and stops below the trailing edge in a flush air scoop. The
inverted U shape of the line prevents fuel transfer through the vent system.
(3) Air pressure flows through the center tank from two vent lines which extend up the
fuselage on either side to make inverted U’s. These lines connect at a junction with
the left and right main−tank manifold junctions. These two manifold junctions are
also connected to each other to connect the left and right sides of the vent system
together.
F. Vent Line Shrouds
(1) The vent line shrouds contain the aft vent lines that are installed in the pressurized
section of the fuselage. These shrouds supply a barrier to prevent fuel leakage from
the vent lines. Any fuel that goes into the shrouds is drained overboard to prevent
fuel pressure buildup in the vent system. The vent shroud drains are installed in the
fuselage above the trailing edge of each wing in the wing fairing.
**ON A/C 7008, 7011−7014, 7017−7018, 7022, 7026−7035, 7037−7044, 7046, 7048, 7050, 7052,
7055−7056, 7061−7063, 7066−7067, 7069−7070, 7072, 7075−7077, 7079−7080, 7085, 7088,
7091−7092, 7094, 7099−7103, 7105−7106, 7108−7109 Pre SB601R−28−024
3. Operation
Refer to Figure 3.
A. The vent system supplies venting with a ram−type air scoop located on the lower surface
of each wing. In flight, the fuel tanks have a small positive pressure, because of the ram
air effect on the air scoop.
B. If the suction ports in the wing tanks are temporarily below the fuel level, fuel can flow
into the vent line manifold. To prevent a buildup of fuel pressure in the vent line
manifolds, a purge line is connected to the vent line manifolds. This purge line is
connected at a low point between the vent line manifolds and the scavenge ejectors.
C. Because the scavenge ejectors are located at the low points of the main tanks, water
collects around the purge line ports of the scavenge ejectors. The vent−line−purge check
valve does not let water go into the vent line when the scavenge ejector is below the fuel
level.
D. In case the fuel tanks are overpressurized, the main−tank relief valves and center−tank
relief valve open to release the pressure. Pressure is released through the relief valves
until the pressure in the tanks decreases below 4.0 psi (27.6 kPa).

Master
EFFECTIVITY: See Pageblock 28−12−00 page 1
28−12−00 Page 3
Dec 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C 7003−7007, 7009−7010, 7015−7016, 7019−7021, 7023−7025, 7036, 7045, 7047, 7049,
7051, 7053−7054, 7057−7060, 7064−7065, 7071, 7073−7074, 7078, 7081−7084, 7086−7087,
7089−7090, 7093, 7095−7098, 7104, 7107, 7110−7990, 8000−8064, 8066−8068 and ON A/C
7008, 7011−7014, 7017−7018, 7022, 7026−7035, 7037−7044, 7046, 7048, 7050, 7052,
7055−7056, 7061−7063, 7066−7067, 7069−7070, 7072, 7075−7077, 7079−7080, 7085, 7088,
7091−7092, 7094, 7099−7103, 7105−7106, 7108−7109 Post SB601R−28−024
4. Operation
Refer to Figure 4.
A. The vent system supplies venting with a ram−type air scoop located on the lower surface
of each wing. In flight, the fuel tanks have a small positive pressure, because of the ram
air effect on the air scoop.
B. If the suction ports in the wing tanks are temporarily below the fuel level, fuel can flow
into the vent line manifold. To prevent a buildup of fuel pressure in the vent line
manifolds, a purge line is connected to the vent line manifolds. This purge line is
connected at a low point between the vent line manifolds and the scavenge ejectors.
C. Because the scavenge ejectors are located at the low points of the main tanks, water
collects around the purge line ports of the scavenge ejectors. The vent−line−purge check
valve does not let water go into the vent line when the scavenge ejector is below the fuel
level.
D. In case the fuel tanks are overpressurized, the main−tank relief valves and center−tank
relief valve open to release the pressure. Pressure is released through the relief valves
until the pressure in the tanks decreases below 4.0 psi (27.6 kPa).
E. Pressure is also released through the vent line tubing and vent−flapper check valves,
with any excess fuel being returned to the centre tank.
**ON A/C ALL
5. Component Location Index
Refer toFigure 5.
**ON A/C 7008, 7011−7014, 7017−7018, 7022, 7026−7035, 7037−7044, 7046, 7048, 7050, 7052,
7055−7056, 7061−7063, 7066−7067, 7069−7070, 7072, 7075−7077, 7079−7080, 7085, 7088,
7091−7092, 7094, 7099−7103, 7105−7106, 7108−7109 Pre SB601R−28−024
COMPONENT NAME QTY ACCESS/ZONE REFERENCE
Check valve, vent line purge 2 510BB, 610BB 28−12−04
Valve, center tank relief 1 510AB 28−12−02
Valve, main tank relief 2 550HB, 650HB 28−12−01
Shroud, vent line 2 Zone 161/162, Zone 311/312 28−12−10 IPC
53−82−00
Fig.2, Item 10
28−12−10

Master
EFFECTIVITY: See Pageblock 28−12−00 page 1
28−12−00 Page 4
Dec 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL

**ON A/C 7003−7007, 7009−7010, 7015−7016, 7019−7021, 7023−7025, 7036, 7045, 7047, 7049,
7051, 7053−7054, 7057−7060, 7064−7065, 7071, 7073−7074, 7078, 7081−7084, 7086−7087,
7089−7090, 7093, 7095−7098, 7104, 7107, 7110−7990, 8000−8064, 8066−8068 and ON A/C
7008, 7011−7014, 7017−7018, 7022, 7026−7035, 7037−7044, 7046, 7048, 7050, 7052,
7055−7056, 7061−7063, 7066−7067, 7069−7070, 7072, 7075−7077, 7079−7080, 7085, 7088,
7091−7092, 7094, 7099−7103, 7105−7106, 7108−7109 Post SB601R−28−024
COMPONENT NAME QTY ACCESS/ZONE REFERENCE
Check valve, vent line purge 2 510BB, 610BB 28−12−04
Valve, center tank relief 1 510AB 28−12−02
Valve, main tank relief 2 550HB, 650HB 28−12−01
Valve, flapper check 2 510AB, 610AB 28−12−06
Shroud, vent line 2 Zone 161/162, Zone 311/312 28−12−10 IPC
53−82−00
Fig.2, Item 10
28−12−10

Master
EFFECTIVITY: See Pageblock 28−12−00 page 1
28−12−00 Page 5
Dec 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL

VENT LINE
TUBING

B
AIR SCOOP
(REF)

C B

MAIN TANK
A
RELIEF VALVE

ram2812000_003.dc, pb, 05/08/92

VENT LINE PURGE CENTER TANK

B C
CHECK VALVE RELIEF VALVE

Vent System − Component Location/Recognition

Figure 1

Master
EFFECTIVITY: See Pageblock 28−12−00 page 1
28−12−00 Page 6
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

A
VENT LINE
TUBING

AIR SCOOP
(REF)
C

C
B

B
VENT LINE PURGE
A CHECK VALVE
MAIN TANK
RELIEF VALVE

ram2812000_007.dg, jp, 10/11/98

C D
VENT−FLAPPER CENTER TANK
CHECK VALVE RELIEF VALVE

Vent System − Component Location/Recognition

Figure 2

Master
EFFECTIVITY: See Pageblock 28−12−00 page 1
28−12−00 Page 7
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

VENT LINE TUBING

CENTER TANK
RELIEF VALVE

MAIN TANK MAIN TANK

RELIEF RELIEF
VALVE VENT VENT VALVE
LINE LINE
PURGE PURGE
CHECK CHECK
VALVE VALVE

SCAVENGER SCAVENGER
EJECTOR EJECTOR ram2812000_001.dg, jp, 16/11/98/98

AIR AIR
SCOOP SCOOP

Vent System − Schematic

Figure 3

Master
EFFECTIVITY: See Pageblock 28−12−00 page 1
28−12−00 Page 8
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

VENT LINE TUBING

VENT−FLAPPER
CHECK VALVE

CENTER TANK
RELIEF VALVE

MAIN TANK MAIN TANK

RELIEF RELIEF
VALVE VENT VENT VALVE
LINE LINE
PURGE PURGE
CHECK CHECK
VALVE VALVE

SCAVENGER SCAVENGER
EJECTOR EJECTOR

ram2812000_008.dg, jp, 16/11/98/98

AIR AIR
SCOOP SCOOP

Vent System−Schematic
Figure 4

Master
EFFECTIVITY: See Pageblock 28−12−00 page 1
28−12−00 Page 9
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

610AB 510AB

610BB 510BB

550HB
650HB

NOTE
500 series panels are on the left side.
600 series panels are on the right side.
ram2812000_002(2).dg, kms/pm, 18/11/98

Vent System − Component Access

Figure 5

Master
EFFECTIVITY: See Pageblock 28−12−00 page 1
28−12−00 Page 10
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C ALL
VALVE, MAIN TANK RELIEF − REMOVAL/INSTALLATION

1. General
A. The maintenance procedures that follow are for the removal and installation of the main
tank relief valve (written as the "relief valve" in this procedure). There are two relief
valves in the main tank fuel system. There is one relief valve at the outboard end of each
main tank, on the lower wing skin.
B. It is necessary to defuel, drain, and remove the fuel fumes from the related main tank to
remove or install the relief valve.

TASK 28−12−01−000−801
Removal of the Main Tank Relief Valve

1. Job Set−Up Information

Subtask 28−12−01−946−001
A. Reference Information
REFERENCE DESIGNATION
TASK 12−11−28−650−804 Suction Defueling
TASK 28−00−00−910−801 Fuel Safety Precautions
TASK 28−11−00−840−801 Prepare Fuel Tank for Access
TASK 28−11−00−840−802 Removal of Fuel Fumes
TASK 28−11−01−000−801 Removal of the Honeycomb Access Panel

2. Job Set−Up
Subtask 28−12−01−910−001
WARNING: OBEY ALL THE FUEL SAFETY PRECAUTIONS WHEN YOU DO WORK ON THE
FUEL SYSTEM AND/OR A FUEL SYSTEM COMPONENT. IF YOU DO NOT DO
THIS, YOU CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO
EQUIPMENT.
A. Obey all the fuel safety precautions (Ref. TASK 28−00−00−910−801).

Subtask 28−12−01−650−001
B. Defuel the applicable main tank (Ref. TASK 12−11−28−650−804).

Subtask 28−12−01−010−001
C. Remove the applicable access panel that follows TASK 28−11−01−000−801):
ACCESS DESIGNATION
550HB Fuel tank access panel
650HB Fuel tank access panel

Master
EFFECTIVITY: See Pageblock 28−12−01 page 401
28−12−01 Page 401
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
Subtask 28−12−01−840−001
D. Prepare the applicable main tank for access (Ref. TASK 28−11−00−840−801).
E. Remove the fuel fumes from the applicable main tank (Ref. TASK 28−11−00−840−802).

3. Procedure
Subtask 28−12−01−020−001
Refer to Figure 401.
A. Remove the relief valve as follows:
(1) Remove the bolts (1) and the washers (2).
(2) Remove the relief valve (3) and the preformed packing (4). Discard the preformed
packing.

Master
EFFECTIVITY: See Pageblock 28−12−01 page 401
28−12−01 Page 402
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

LEGEND.
1. Bolt.
2. Washer.
3. Relief valve.
4. Preformed packing.

1
ram2812014_001(1).dc, ab/ks, 11/03/93

Main Tank Relief Valve − Removal/Installation

Figure 401

Master
EFFECTIVITY: See Pageblock 28−12−01 page 401
28−12−01 Page 403
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
TASK 28−12−01−400−801
Installation of the Main Tank Relief Valve

1. Job Set−Up Information

Subtask 28−12−01−944−001
A. Consumable Materials
REFERENCE DESIGNATION
06−002 Petrolatum

Subtask 28−12−01−945−001
B. Parts
REF NAME OF PART QTY IPC SEQUENCE NO.
1 Bolt 4 IPC 28−12−01−1A−025
2 Washer 4 IPC 28−12−01−1A−030
4 Preformed packing 1 IPC 28−12−01−1A−035

Subtask 28−12−01−946−002
C. Reference Information
REFERENCE DESIGNATION
TASK 12−11−28−650−801 Automatic Pressure Refueling
TASK 28−11−01−400−801 Installation of the Honeycomb Access Panel

2. Procedure
Subtask 28−12−01−869−001
A. Make sure that the aircraft is in the same configuration as in the removal task.

Subtask 28−12−01−420−001
Refer to Figure 401.
B. Install the relief valve as follows:
(1) Lubricate the preformed packing (4) with the petrolatum.
(2) Install the preformed packing (4) on the relief valve (3).
(3) Install the relief valve (3) with the washers (2) and the bolts (1).

3. Close Out
Subtask 28−12−01−410−001
A. Install the applicable access panel that follows (Ref. TASK 28−11−01−400−801):

Master
EFFECTIVITY: See Pageblock 28−12−01 page 401
28−12−01 Page 404
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

ACCESS DESCRIPTION
550HB Fuel tank access panel
650HB Fuel tank access panel

Subtask 28−12−01−210−001
B. Refuel the applicable main tank (Ref.TASK 12−11−28−650−801).
C. Examine the area around the relief valve for leaks.

Master
EFFECTIVITY: See Pageblock 28−12−01 page 401
28−12−01 Page 405
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C ALL
VALVE, MAIN TANK RELIEF − ADJUSTMENT/TEST

1. General
A. The maintenance procedure that follows is a test of the main tank relief valve (written as
the "relief valve" in this procedure).

TASK 28−12−01−710−801
Operational Test of the Main Tank Relief Valve

1. Procedure
Subtask 28−12−01−710−001
A. Pull the handle of the relief valve. Make sure that the valve opens and closes.
B. Do the test again for the other relief valve.

Master
EFFECTIVITY: See Pageblock 28−12−01 page 501
28−12−01 Page 501
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C ALL
VALVE, CENTER TANK RELIEF − REMOVAL/INSTALLATION

1. General
A. The maintenance procedures that follow are for the removal and installation of the center
tank relief valve (written as the "relief valve" in this procedure). The relief valve is
installed through the lower wing skin, in the forward section of the center tank.
B. It is necessary to defuel, drain, and remove the fuel fumes from the center tank to
remove or install the relief valve.

TASK 28−12−02−000−801
Removal of the Center Tank Relief Valve

1. Job Set−Up Information

Subtask 28−12−02−946−001
A. Reference Information
REFERENCE DESIGNATION
TASK 12−11−28−650−804 Suction Defueling
TASK 20−30−00−910−802 Wiggins Couplings − Maintenance Practices
TASK 28−00−00−910−801 Fuel Safety Precautions
TASK 28−11−00−840−801 Prepare Fuel Tank for Access
TASK 28−11−00−840−802 Removal of Fuel Fumes
TASK 28−11−01−000−801 Removal of the Honeycomb Access Panel

2. Job Set−Up
Subtask 28−12−02−910−001
WARNING: OBEY ALL THE FUEL SAFETY PRECAUTIONS WHEN YOU DO WORK ON THE
FUEL SYSTEM AND/OR A FUEL SYSTEM COMPONENT. IF YOU DO NOT DO
THIS, YOU CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO
EQUIPMENT.
A. Obey all the fuel safety precautions (Ref. TASK 28−00−00−910−801).

Subtask 28−12−02−650−001
B. Defuel the center tank (Ref. TASK 12−11−28−650−804).

Subtask 28−12−02−010−001
C. Remove the access panel that follows TASK 28−11−01−000−801:
ACCESS DESIGNATION
510AB Fuel tank access panel

Master
EFFECTIVITY: See Pageblock 28−12−02 page 401
28−12−02 Page 401
Sep 10/2004
 C
AIRCRAFT MAINTENANCE MANUAL
Subtask 28−12−02−840−001
D. Prepare the center tank for access (Ref. TASK 28−11−00−840−801).
E. Remove the fuel fumes from the center tank (Ref. TASK 28−11−00−840−802).

3. Procedure
Subtask 28−12−02−020−001
Refer to Figure 401.
A. Remove the relief valve as follows:
(1) Remove the couplings (1) (Ref. TASK 20−30−00−910−802).
(2) Put the sleeves (2) on the transition tube (3) and loosen the transition tube.
(3) Remove the bolts (4) and the washers (5) and disconnect the relief valve (6) from
the mounting bracket.
(4) Carefully remove the relief valve (6) and the transition tube (3).
(5) Remove the transition tube (3) from the relief valve (6).
(6) Remove and discard the preformed packings (7) from the upper fitting support (8),
the transition tube (3), and the lower fitting support (9).
(7) Remove the bolts (10), the washers (11), and the upper fitting support (9) from the
relief valve (6).
(8) Remove and discard the preformed packing (12) from the relief valve (6).

Master
EFFECTIVITY: See Pageblock 28−12−02 page 401
28−12−02 Page 402
Sep 10/2004
 C
AIRCRAFT MAINTENANCE MANUAL

LEGEND.
1. Coupling. 8. Upper fitting
2. Sleeve. support.
3. Transition tube. 9. Lower fitting
4. Bolt. support.
5. Washer. 10. Bolt.
6. Relief valve. 11. Washer.
7. Preformed packing. 12. Preformed packing.

MOUNTING
BRACKET
(REF)

12 2

3
8

11
7
10

1 7

7 1
ram2812024_001(1).dc, cr/gd, 11/03/93

7
2
9
3

Center Tank Relief Valve − Removal/Installation

Figure 401

Master
EFFECTIVITY: See Pageblock 28−12−02 page 401
28−12−02 Page 403
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
TASK 28−12−02−400−801
Installation of the Center Tank Relief Valve

1. Job Set−Up Information

Subtask 28−12−02−944−001
A. Consumable Materials
REFERENCE DESIGNATION
06−002 Petrolatum

Subtask 28−12−02−945−001
B. Parts
REF NAME OF PART QTY IPC SEQUENCE NO.
4 Bolt 4 IPC 28−12−02−1A−055
5 Washer 4 IPC 28−12−02−1A−060
7 Preformed packing 4 IPC 28−12−02−1A−020
10 Bolt 2 IPC 28−12−02−1A−035
11 Washer 2 IPC 28−12−02−1A−040
12 Preformed packing 1 IPC 28−12−02−1A−045

Subtask 28−12−02−946−002
C. Reference Information
REFERENCE DESIGNATION
TASK 12−11−28−650−801 Automatic Pressure Refueling
TASK 20−30−00−910−802 Wiggins Couplings − Maintenance Practices
TASK 28−11−01−400−801 Installation of the Honeycomb Access Panel
TASK 28−12−02−710−801 Operational Test of the Center Tank Relief Valve
TASK 51−80−00−760−803 Electrical Bonding Test

2. Procedure
Subtask 28−12−02−869−001
A. Make sure that the aircraft is in the same configuration as in the removal task.

Subtask 28−12−02−420−001
Refer to Figure 401.
B. Install the relief valve as follows:
(1) Lubricate the preformed packing (12). Install the preformed packing on the relief
valve (6).
(2) Install the upper fitting support (8), the washers (11), and the bolts (10) on the relief
valve (6).

Master
EFFECTIVITY: See Pageblock 28−12−02 page 401
28−12−02 Page 404
Sep 10/2004
 C
AIRCRAFT MAINTENANCE MANUAL
(3) Make sure that the sleeves (2) are installed on the transition tube (3).
(4) Lubricate and install the preformed packings (7) on the upper fitting support (8), the
transition tube (3), and the lower fitting support (9).
(5) Loosely install the transition tube (3) on the handle of the relief valve (6).
(6) Hold the relief valve (6) and the transition tube (3) in position and install the
washers (5) and the bolts (4).
(7) Connect the sleeves (2) to the upper fitting support (8) and the lower fitting support
(9).
(8) Install the couplings (1) (Ref. TASK 20−30−00−910−802).
(9) Do the electrical bonding test of the coupling (1) (Ref. TASK 51−80−00−760−803).

3. Close Out
Subtask 28−12−02−410−001
A. Install the access panel that follows (Ref. TASK 28−11−01−400−801):
ACCESS DESCRIPTION
510AB Fuel tank access panel

Subtask 28−12−02−710−001
B. Do an operational test of the relief valve (Ref. TASK 28−12−02−710−801).

Subtask 28−12−02−210−001
C. Refuel the center tank (Ref. TASK 12−11−28−650−801).
D. Examine the area around the relief valve for leaks.

Master
EFFECTIVITY: See Pageblock 28−12−02 page 401
28−12−02 Page 405
Sep 10/2004
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C ALL
VALVE, CENTER TANK RELIEF − ADJUSTMENT/TEST

1. General
A. The maintenance procedure that follows is a test of the center tank relief valve (written
as the "relief valve" in this procedure).

TASK 28−12−02−710−801
Operational Test of the Center−Tank Relief Valve

1. Procedure
Subtask 28−12−02−710−002
A. Pull the handle of the relief valve. Make sure that the valve opens and closes.

Master
EFFECTIVITY: See Pageblock 28−12−02 page 501
28−12−02 Page 501
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C ALL
CHECK VALVE, VENT−LINE−PURGE − REMOVAL/INSTALLATION

1. General
A. The maintenance procedures that follow are for the removal and installation of the
vent−line−purge−check valve (written as the "check valve" in this procedure). There are
two check valves in the fuel vent system. They are located in the center tank. The check
valves are installed in the vent lines between the aft−scavenge−ejector pumps and the
main−tank−vent manifolds.
B. It is necessary to defuel, drain, and remove the fuel fumes from the center tank before
you remove or install the check valve.

TASK 28−12−04−000−801
Removal of the Vent−Line−Purge Check Valve

1. Job Set−Up Information

Subtask 28−12−04−946−001
A. Reference Information
REFERENCE DESIGNATION
TASK 12−11−28−650−804 Suction Defueling
TASK 28−00−00−910−801 Fuel Safety Precautions
TASK 28−11−00−840−801 Prepare Fuel Tank for Access
TASK 28−11−01−000−802 Removal of the Aluminum Access Panel
TASK 28−11−00−840−802 Removal of Fuel Fumes

2. Job Set−Up
Subtask 28−12−04−910−001
WARNING: OBEY ALL THE FUEL SAFETY PRECAUTIONS WHEN YOU DO WORK ON THE
FUEL SYSTEM AND/OR A FUEL SYSTEM COMPONENT. IF YOU DO NOT DO
THIS, YOU CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO
EQUIPMENT.
A. Obey all the fuel safety precautions (Ref. TASK 28−00−00−910−801).

Subtask 28−12−04−650−001
B. Defuel the center tank (Ref. TASK 12−11−28−650−804).

Subtask 28−12−04−010−002
C. Remove the access panels that follow (Ref. TASK 28−11−01−000−802):

Master
EFFECTIVITY: See Pageblock 28−12−04 page 401
28−12−04 Page 401
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

ACCESS DESIGNATION
510BB Center Tank Aluminum Access Panel
610BB Center Tank Aluminum Access Panel

Subtask 28−12−04−840−002
D. Prepare the center fuel tank for access (Ref. TASK 28−11−00−840−801).
E. Remove the fuel fumes from the center fuel tank (Ref. TASK 28−11−00−840−802).

3. Procedure
**ON A/C 7008, 7011−7014, 7017−7018, 7022, 7026−7035, 7037−7044, 7046, 7048, 7050, 7052,
7055−7056, 7061−7063, 7066−7067, 7069−7070, 7072, 7075−7077, 7079−7080, 7085, 7088,
7091−7092, 7094, 7099−7103, 7105−7106, 7108−7109 Pre SB601R−28−024

Subtask 28−12−04−020−001
Refer to Figure 401.
A. To remove the left side check valve from the center fuel tank, do the steps that follow:
(1) Remove the nut (1), the washers (2), and the screw (3). Disconnect the bonding
strap (4) from the clamp (5).
(2) Remove the clamp (5).
(3) Disconnect the purge line (6) and remove the check valve (7).
(4) Remove the check valve (7) and the preformed packing (8) from the bulkhead
fitting. Discard the preformed packing.

Subtask 28−12−04−020−003
Refer to Figure 402.
B. To remove the right side check valve from the center fuel tank, do the steps that follow:
(1) Remove the forward purge line (1) from the elbow fitting (2) and the check valve (3).
(2) Remove the check valve (3) from the aft purge line.

**ON A/C 7003−7007, 7009−7010, 7015−7016, 7019−7021, 7023−7025, 7036, 7045, 7047, 7049,
7051, 7053−7054, 7057−7060, 7064−7065, 7071, 7073−7074, 7078, 7081−7084, 7086−7087,
7089−7090, 7093, 7095−7098, 7104, 7107, 7110−7990, 8000−8064, 8066−8068 and ON A/C
7008, 7011−7014, 7017−7018, 7022, 7026−7035, 7037−7044, 7046, 7048, 7050, 7052,
7055−7056, 7061−7063, 7066−7067, 7069−7070, 7072, 7075−7077, 7079−7080, 7085, 7088,
7091−7092, 7094, 7099−7103, 7105−7106, 7108−7109 Post SB601R−28−024

Subtask 28−12−04−020−007
Refer to Figure 403.
C. To remove the left side check valve from the center fuel tank, do the steps that follow:
(1) Disconnect the supply tube assembly (1) from the check valve (2).
(2) Remove the check valve (2) from the aft vent tube assembly (3).

Master
EFFECTIVITY: See Pageblock 28−12−04 page 401
28−12−04 Page 402
Dec 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
(3) Remove the preformed packing (4) from the check valve (2) or aft vent tube
assembly (3), as applicable. Discard the preformed packing (4).

Subtask 28−12−04−020−005
Refer to Figure 403.
D. To remove the right side check valve from the center fuel tank, do the steps that follow:
(1) Disconnect the supply tube assembly (1) from the check valve (2).
(2) Remove the check valve (2) from the aft vent tube assembly (3).
(3) Remove the preformed packing (4) from the check valve (2) or aft vent tube
assembly (3), as applicable. Discard the preformed packing (4).

Master
EFFECTIVITY: See Pageblock 28−12−04 page 401
28−12−04 Page 403
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

LEGEND
1. Nut.
2. Washer.
3. Screw.
4. Bonding strap.
5. Clamp.
6. Purge line.
7. Check valve.
8. Preformed packing.

NOTE
Left side only is shown.

D
FW
3 7
2
C
5
ram2812044_001(2).dg, gd/pm, 07/12/98

4
A

2 6
1

B C

Vent Line Purge Check Valve − Removal/Installation

Figure 401

Master
EFFECTIVITY: See Pageblock 28−12−04 page 401
28−12−04 Page 404
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

LEGEND
1. Forward purge line.
2. Elbow fitting.
3. Check valve.

2
NOTE
Right side only is shown.

D
FW

AFT PURGE LINE

(REF)

1
ram2812044_002(1).dg, br/pm, 18/11/98

Right Vent Line Purge Check Valve − Removal/Installation

Figure 402

Master
EFFECTIVITY: See Pageblock 28−12−04 page 401
28−12−04 Page 405
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

LEGEND
1. Supply tube assembly.
2. Check valve.
3. Vent tube assembly.
4. Preformed packing.

D
ram2812044_004.dg, rm/jc, 15/11/00

FW
1

Left Vent Line Purge Check Valve − Removal/Installation

Figure 403

Master
EFFECTIVITY: See Pageblock 28−12−04 page 401
28−12−04 Page 406
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C ALL
TASK 28−12−04−400−801
Installation of the Vent−Line−Purge Check Valve

1. Job Set−Up Information

**ON A/C 7008, 7011−7014, 7017−7018, 7022, 7026−7035, 7037−7044, 7046, 7048, 7050, 7052,
7055−7056, 7061−7063, 7066−7067, 7069−7070, 7072, 7075−7077, 7079−7080, 7085, 7088,
7091−7092, 7094, 7099−7103, 7105−7106, 7108−7109 Pre SB601R−28−024

Subtask 28−12−04−945−001
A. Parts
REF NAME OF PART QTY IPC SEQUENCE NO.
1 Nut 1 IPC 28−12−00−01−380
2 Washer 2 IPC 28−12−00−01−375
3 Screw 1 IPC 28−12−00−01−370
5 Clamp 1 IPC 28−12−00−01−365
8 Preformed Packing 1 IPC 28−12−00−01−095

**ON A/C 7003−7007, 7009−7010, 7015−7016, 7019−7021, 7023−7025, 7036, 7045, 7047, 7049,
7051, 7053−7054, 7057−7060, 7064−7065, 7071, 7073−7074, 7078, 7081−7084, 7086−7087,
7089−7090, 7093, 7095−7098, 7104, 7107, 7110−7990, 8000−8064, 8066−8068 and ON A/C
7008, 7011−7014, 7017−7018, 7022, 7026−7035, 7037−7044, 7046, 7048, 7050, 7052,
7055−7056, 7061−7063, 7066−7067, 7069−7070, 7072, 7075−7077, 7079−7080, 7085, 7088,
7091−7092, 7094, 7099−7103, 7105−7106, 7108−7109 Post SB601R−28−024

Subtask 28−12−04−945−002
B. Parts
REF NAME OF PART QTY IPC SEQUENCE NO.
8 Preformed Packing 1 IPC 28−12−00−01−095

**ON A/C ALL

Subtask 28−12−04−946−005
C. Reference Information
REFERENCE DESIGNATION
TASK 28−00−00−910−801 Fuel Safety Precautions
TASK 28−11−01−400−802 Installation of the Aluminum Access Panel

Master
EFFECTIVITY: See Pageblock 28−12−04 page 401
28−12−04 Page 407
Dec 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
2. Job Set−Up
Subtask 28−12−04−910−003
WARNING: OBEY ALL THE FUEL SAFETY PRECAUTIONS WHEN YOU DO WORK ON THE
FUEL SYSTEM AND/OR A FUEL SYSTEM COMPONENT. IF YOU DO NOT DO
THIS, YOU CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO
EQUIPMENT.
A. Obey all the fuel safety precautions (Ref. TASK 28−00−00−910−801).

3. Procedure
Subtask 28−12−04−869−001
A. Make sure that the aircraft is in the same configuration as in the removal task.

**ON A/C 7008, 7011−7014, 7017−7018, 7022, 7026−7035, 7037−7044, 7046, 7048, 7050, 7052,
7055−7056, 7061−7063, 7066−7067, 7069−7070, 7072, 7075−7077, 7079−7080, 7085, 7088,
7091−7092, 7094, 7099−7103, 7105−7106, 7108−7109 Pre SB601R−28−024

Subtask 28−12−04−420−001
Refer to Figure 401.
CAUTION: MAKE SURE THAT ALL COMPONENTS ARE CLEAN AND FREE FROM
CONTAMINANTS BEFORE YOU INSTALL THEM IN THE FUEL SYSTEM. IF
YOU DO NOT DO THIS, YOU CAN CAUSE DAMAGE TO EQUIPMENT.
B. To install the left check valve in the center fuel tank, do the steps that follow:
(1) Install the preformed packing (8) and the check valve (7) on the bulkhead fitting.
Make sure that the arrow on the check valve points down.
(2) Connect the purge line (6) to the check valve (7).
(3) Prepare the bonding surface of the clamp (5) and the purge line for electrical bond
(Ref. TASK 51−80−00−100−802).
(4) Install the clamp (5).
(5) Connect the bonding strap (4) to the clamp (5), and install the washers (2), the
screw (3), and the nut (1).

Subtask 28−12−04−420−003
Refer to Figure 402.
CAUTION: MAKE SURE THAT ALL COMPONENTS ARE CLEAN AND FREE FROM
CONTAMINANTS BEFORE YOU INSTALL THEM IN THE FUEL SYSTEM. IF
YOU DO NOT DO THIS, YOU CAN CAUSE DAMAGE TO EQUIPMENT.
C. To install the right check valve in the center fuel tank, do the steps that follow:
(1) Install the check valve (3) on the aft purge line. Make sure that the arrow on the
check valve points to the aft purge line.
(2) Install the forward purge line (1) on the check valve (3) and the elbow fitting (2).

Master
EFFECTIVITY: See Pageblock 28−12−04 page 401
28−12−04 Page 408
Dec 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C 7003−7007, 7009−7010, 7015−7016, 7019−7021, 7023−7025, 7036, 7045, 7047, 7049,
7051, 7053−7054, 7057−7060, 7064−7065, 7071, 7073−7074, 7078, 7081−7084, 7086−7087,
7089−7090, 7093, 7095−7098, 7104, 7107, 7110−7990, 8000−8064, 8066−8068 and ON A/C
7008, 7011−7014, 7017−7018, 7022, 7026−7035, 7037−7044, 7046, 7048, 7050, 7052,
7055−7056, 7061−7063, 7066−7067, 7069−7070, 7072, 7075−7077, 7079−7080, 7085, 7088,
7091−7092, 7094, 7099−7103, 7105−7106, 7108−7109 Post SB601R−28−024

Subtask 28−12−04−420−004
Refer to Figure 403.
CAUTION: MAKE SURE THAT ALL COMPONENTS ARE CLEAN AND FREE FROM
CONTAMINANTS BEFORE YOU INSTALL THEM IN THE FUEL SYSTEM. IF
YOU DO NOT DO THIS, YOU CAN CAUSE DAMAGE TO EQUIPMENT.
D. To install the left check valve in the center fuel tank, do the steps that follow:
(1) Install the preformed packing (4) on the check valve (2).
(2) Install the check valve (2) on the aft vent tube assembly (3). Make sure that the
arrow on the check valve points toward the supply tube assembly (1).
(3) Connect the supply tube assembly (1) to the check valve (2).

Subtask 28−12−04−420−005
Refer to Figure 403.
CAUTION: MAKE SURE THAT ALL COMPONENTS ARE CLEAN AND FREE FROM
CONTAMINANTS BEFORE YOU INSTALL THEM IN THE FUEL SYSTEM. IF
YOU DO NOT DO THIS, YOU CAN CAUSE DAMAGE TO EQUIPMENT.
E. To install the right check valve in the center fuel tank, do the steps that follow:
(1) Install the preformed packing (4) on the check valve (2).
(2) Install the check valve (2) on the aft vent tube assembly (3). Make sure that the
arrow on the check valve points toward the supply tube assembly (1).
(3) Connect the supply tube assembly (1) to the check valve (2).
**ON A/C ALL

4. Close Out
Subtask 28−12−04−410−001
A. Install the applicable access panels that follow (Ref. TASK 28−11−01−400−802):
ACCESS DESIGNATION
510BB Center Tank Aluminum Access Panel
610BB Center Tank Aluminum Access Panel

Master
EFFECTIVITY: See Pageblock 28−12−04 page 401
28−12−04 Page 409
Dec 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C 7003−7007, 7009−7010, 7015−7016, 7019−7021, 7023−7025, 7036, 7045, 7047, 7049,
7051, 7053−7054, 7057−7060, 7064−7065, 7071, 7073−7074, 7078, 7081−7084, 7086−7087,
7089−7090, 7093, 7095−7098, 7104, 7107, 7110−7990, 8000−8064, 8066−8068 and ON A/C
7008, 7011−7014, 7017−7018, 7022, 7026−7035, 7037−7044, 7046, 7048, 7050, 7052,
7055−7056, 7061−7063, 7066−7067, 7069−7070, 7072, 7075−7077, 7079−7080, 7085, 7088,
7091−7092, 7094, 7099−7103, 7105−7106, 7108−7109 Post SB601R−28−024
VALVE, VENT LINE, FLAPPER CHECK − REMOVAL/INSTALLATION

1. General
A. The maintenance procedures that follow are for the removal and installation of the
vent−line flapper check−valves (written as "flapper valve" in this procedure). There are
two flapper valves in the fuel vent system. The two are installed in the center fuel tank.
B. It is necessary to defuel, drain and remove the fuel fumes from the center fuel tank,
before you remove or install the flapper valve.

TASK 28−12−06−000−801
Removal of the Flapper Valve

1. Job Set−Up Information

Subtask 28−12−06−946−001
A. Reference Information
REFERENCE DESIGNATION
TASK 12−11−28−650−804 Suction Defueling
TASK 20−30−00−910−802 Wiggins Couplings − Maintenance Practices
TASK 28−00−00−910−801 Fuel Safety Precautions
TASK 28−11−00−840−801 Prepare Fuel Tank for Access
TASK 28−11−00−840−802 Removal of Fuel Fumes
TASK 28−11−01−000−802 Removal of Aluminum Access Panel

2. Job Set−Up
Subtask 28−12−06−910−001
WARNING: OBEY ALL THE FUEL SAFETY PRECAUTIONS WHEN YOU DO WORK ON THE
FUEL SYSTEM AND/OR A FUEL SYSTEM COMPONENT. IF YOU DO NOT DO
THIS, YOU CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO
EQUIPMENT.
A. Obey all the fuel safety precautions (Ref. TASK 28−00−00−910−801).

Subtask 28−12−06−650−001
B. Defuel the center fuel tank (Ref. TASK 12−11−28−650−804).

Master
EFFECTIVITY: See Pageblock 28−12−06 page 401
28−12−06 Page 401
Dec 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
Subtask 28−12−06−010−001
C. Remove the following access panel, as applicable (Ref. TASK 28−11−01−000−802):
ACCESS DESIGNATION
510AB Aluminum access panel
610AB Aluminum access panel

Subtask 28−12−06−840−001
D. Prepare the center fuel tank for access (Ref. TASK 28−11−00−840−801).
E. Remove the fuel fumes from the center fuel tank (Ref. TASK 28−11−00−840−802).

3. Procedure
**ON A/C 7110−7990, 8000−8064, 8066−8068

Subtask 28−12−06−020−001
Refer to Figure 401.
A. Remove the left or the right side forward vent−tube assembly from the center fuel tank
as follows:
NOTE: Make sure that you put all of the removed fuel components on a clean surface.
(1) Release all three latch pawls of the coupling (1) at the same time.
(2) Remove the coupling (1) from the forward and aft vent−tube assemblies, (2) and (3)
(Ref. TASK 20−30−00−910−802).
(3) Move the sleeve (4) along the aft vent−tube assembly (3) away from the open end.
(4) Hold the forward vent−tube assembly (2) and remove the screw (5), the washer (6)
and the clamp (7) from their forward mounting location.
(5) Continue to hold the forward vent−tube assembly (2) and remove the screw (8), the
washer (9) and the clamp (10) from their center mounting location.
(6) Carefully remove the forward vent−tube assembly (2) from the center tank.
(7) Move the sleeve (4) off of the aft vent−tube assembly (3).
(8) Remove and discard the preformed packing (11) from the open end of the aft
vent−tube assembly (3).
(9) Remove and discard the preformed packing (12) from the open end of the forward
vent−tube assembly (2).
(10) Install a protective cap onto the aft vent−tube assembly (3) to prevent
contamination.

Master
EFFECTIVITY: See Pageblock 28−12−06 page 401
28−12−06 Page 402
Dec 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C 7003−7007, 7009−7010, 7015−7016, 7019−7021, 7023−7025, 7036, 7045, 7047, 7049,
7051, 7053−7054, 7057−7060, 7064−7065, 7071, 7073−7074, 7078, 7081−7084, 7086−7087,
7089−7090, 7093, 7095−7098, 7104, 7107 and ON A/C 7008, 7011−7014, 7017−7018, 7022,
7026−7035, 7037−7044, 7046, 7048, 7050, 7052, 7055−7056, 7061−7063, 7066−7067,
7069−7070, 7072, 7075−7077, 7079−7080, 7085, 7088, 7091−7092, 7094, 7099−7103,
7105−7106, 7108−7109 Post SB601R−28−024

Subtask 28−12−06−020−003
Refer to Figure 402.
B. Remove the left or the right forward vent−tube assembly from the center fuel tank as
follows:
NOTE: Make sure that you put all of the removed fuel components on a clean surface.
(1) Release all three latch pawls of the coupling (1) at the same time.
(2) Remove the coupling (1) from the forward and aft vent−tube assemblies, (2) and (3)
(Ref TASK 20−30−00−910−802).
(3) Move the sleeve (4) along the aft vent−tube assembly (3) away from the open end.
(4) Hold the forward vent−tube assembly (2). Remove the nut (5), washers (6) and (7),
spacer (8), screw (9) and clamps (10 and 11) from the collector−tank tube assembly
(12) and forward vent−tube assembly.
NOTE: Make a visual identification of the clamp positions to help correctly set
when you assemble the components again.
(5) Continue to hold the forward vent−tube assembly (2). Remove nut (13), washers
(14 and 15), spacer (16), screw (17) and clamps (18 and 19) from the cross−flow
SOV−outlet−tube assembly (20) and the forward vent−tube assembly.
NOTE: Make a visual identification of the clamp positions to help correctly set
when you assemble the components again.
(6) Carefully remove the forward vent−tube assembly (2) from the center fuel tank.
(7) Move the sleeve (4) off of the aft vent−tube assembly (3).
(8) Remove and discard the preformed packing (21) from the open end of the aft
vent−tube assembly (3).
(9) Remove and discard the preformed packing (22) from the open end of the forward
vent−tube assembly (2).
(10) Install a protective cap onto the aft vent−tube assembly (3) to prevent
contamination.

**ON A/C 7003−7007, 7009−7010, 7015−7016, 7019−7021, 7023−7025, 7036, 7045, 7047, 7049,
7051, 7053−7054, 7057−7060, 7064−7065, 7071, 7073−7074, 7078, 7081−7084, 7086−7087,
7089−7090, 7093, 7095−7098, 7104, 7107, 7110−7990, 8000−8064, 8066−8068 and ON A/C
7008, 7011−7014, 7017−7018, 7022, 7026−7035, 7037−7044, 7046, 7048, 7050, 7052,
7055−7056, 7061−7063, 7066−7067, 7069−7070, 7072, 7075−7077, 7079−7080, 7085, 7088,
7091−7092, 7094, 7099−7103, 7105−7106, 7108−7109 Post SB601R−28−024

Subtask 28−12−06−020−004
Refer to Figure 403.

Master
EFFECTIVITY: See Pageblock 28−12−06 page 401
28−12−06 Page 403
Dec 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
C. Remove the flapper valve from the forward vent−tube assembly as follows:
NOTE: Make sure that you put all of the removed fuel components on a clean surface.
(1) Release all three latch pawls of the coupling (1) at the same time.
(2) Remove the coupling (1) from the forward vent−tube assembly (2) (Ref TASK
20−30−00−910−802).
(3) Move the adapter (3) out of the sleeve (4).
(4) Move the sleeve (4) off of the forward vent−tube assembly (2).
(5) Remove and discard the preformed packing (5) from the forward vent−tube
assembly (2).
(6) Remove and discard the preformed packing (6) from the adapter (3).
(7) Remove the retainer wire (7), together with the flapper valve (8), from inside of the
adaptor (3).
(8) Remove and discard the preformed packing (9) from the flapper valve (8).
(9) Install a protective cap on each end of the forward vent−tube assembly (2) to
prevent contamination.

Master
EFFECTIVITY: See Pageblock 28−12−06 page 401
28−12−06 Page 404
Sep 10/2004
 C
AIRCRAFT MAINTENANCE MANUAL

A
COLLECTOR TANK
TUBE ASSEMBLY
FLAPPER VALVE
AND ADAPTER

5
6

CROSS FLOW
LEGEND TUBE ASSEMBLY
2
1. Coupling.
2. Forward vent−tube assembly.
3. Aft vent−tube assembly.
4. Sleeve.
5. Screw. 8
6. Washer. 9
7. Clamp.
8. Screw. 10
9. Washer.
10. Clamp.
11. Preformed packing. CROSS FLOW
12. Preformed packing. SHUTOFF VALVE

SCAVENGE EJECTOR
NOTE TUBE ASSEMBLY
LH is shown
RH is opposite.
B

3
3
11
4
1
WS 45.00 WS 22.50
FWD

12
ram2812064_001.dg, rm, 14/12/98

Forward Vent−Tube Assembly − Removal/Installation

Figure 401

Master
EFFECTIVITY: See Pageblock 28−12−06 page 401
28−12−06 Page 405
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

A FLAPPER VALVE
12 AND ADAPTER

LEGEND
1. Coupling. 20
2. Forward vent−tube assembly.
3. Aft vent−tube assembly.
D
4. Sleeve.
5. Nut.
6. Washer. SCAVENGE EJECTOR
7. Washer. TUBE ASSEMBLY
8. Spacer. CROSS FLOW
9. Screw. SHUTOFF VALVE
10. Clamp.
11. Clamp.
12. Collector tank−tube assembly.
13. Nut.
FWD

14. Washer.
15. Washer. B
16. Spacer.
17. Screw.
18. Clamp. 3
19. Clamp.
20. Cross−flow SOV−outlet
tube assembly. NOTE
21. Preformed packing. WS 45.00 WS 22.50
LH is shown
A
22. Preformed packing. RH is opposite.

9 17
11 2 D 18
INB 20
4 (REF)
FW
(REF)
1 7 D
15
22
ram2812064_002.dg, rm, 14/12/98

3 2 8
16
21 2
12 (REF)
10 (REF) 19
6 14
B 5 13
C D

Forward Vent−Tube Assembly − Removal/Installation

Figure 402

Master
EFFECTIVITY: See Pageblock 28−12−06 page 401
28−12−06 Page 406
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

A LEGEND
1. Coupling.
2. Forward vent−tube assembly.
3. Adapter.
4. Sleeve.
5. Preformed packing.
6. Preformed packing.
7. Retainer wire.
A 8. Flapper valve.
9. Preformed packing.

NOTE
RH side is shown
LH side is opposite.

2
D
INB
FW
D

5
9
4
ram2812064_003.dg, rm, 14/11/98

3
1
6
7
A 8

Flapper Valve − Removal/Installation

Figure 403

Master
EFFECTIVITY: See Pageblock 28−12−06 page 401
28−12−06 Page 407
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
TASK 28−12−06−400−801
Installation of the Flapper Valve

1. Job Set−Up Information

Subtask 28−12−06−944−001
A. Consumable Materials
REFERENCE DESIGNATION
06−002 Petrolatum

Subtask 28−12−06−945−001
B. Parts
REF NAME OF PART QTY IPC SEQUENCE NO.
5 Preformed packing 1 IPC 28−12−00−01−TBD
6 Preformed packing 1 IPC 28−12−00−01−TBD
7 Retainer wire 1 IPC 28−12−00−01−TBD
8 Flapper check valve 1 IPC 28−12−00−01−TBD
9 Preformed packing 1 IPC 28−12−00−01−TBD

Subtask 28−12−06−946−002
C. Reference Information
REFERENCE DESIGNATION
TASK 20−30−00−910−802 Wiggins Couplings − Maintenance Practices
TASK 28−00−00−910−801 Fuel Safety Precautions
TASK 28−11−01−400−802 Installation of Aluminum Access Panel

2. Job Set−Up
Subtask 28−12−06−869−001
WARNING: OBEY ALL THE FUEL SAFETY PRECAUTIONS WHEN YOU DO WORK ON THE
FUEL SYSTEM AND/OR A FUEL SYSTEM COMPONENT. IF YOU DO NOT DO
THIS, YOU CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO
EQUIPMENT.
A. Obey all the fuel safety precautions (Ref. TASK 28−00−00−910−801).
B. Make sure that the aircraft is in the same configuration as in the removal task.

3. Procedure
Subtask 28−12−06−420−001
Refer to Figure 403.

Master
EFFECTIVITY: See Pageblock 28−12−06 page 401
28−12−06 Page 408
Sep 10/2004
 C
AIRCRAFT MAINTENANCE MANUAL
CAUTION: MAKE SURE THAT ALL COMPONENTS ARE CLEAN AND FREE FROM
CONTAMINANTS BEFORE YOU INSTALL THEM IN THE FUEL SYSTEM. IF YOU
DO NOT DO THIS, YOU CAN CAUSE DAMAGE TO EQUIPMENT.
A. Install the flapper valve in the forward vent−tube assembly as follows:
(1) Remove the protective cap from each end of the forward vent−tube assembly (2).
(2) Lubricate the preformed packing (5) with Petrolatum and install it in the groove near
the outer end of the forward vent−tube assembly (2).
(3) Lubricate the internal surface of the sleeve (4) with Petrolatum.
(4) Move the sleeve (4) over the forward vent−tube assembly (2) and the preformed
packing (5).
(5) Lubricate the preformed packing (9) with Petrolatum and install it in the groove in
the flapper valve (8).
(6) Put the flapper valve (8) into the adapter (3). Make sure that the flapper opens
outwards, to permit the flow of vented fuel into the center fuel tank. Keep in position
with the retainer wire (7).
(7) Lubricate the preformed packing (6) with Petrolatum and install it in the groove on
the outside of the adapter (3).
(8) Align the adapter (3) with the forward vent−tube assembly (2).
NOTE: The vent−tube assembly and adapter, although aligned, must not touch.
(9) Install the coupling (1) (Ref. TASK 20−30−00−910−802).
NOTE: When all three pawls are engaged the coupling will lock automatically.

**ON A/C 7110−7990, 8000−8064, 8066−8068

Subtask 28−12−06−420−002
Refer to Figure 401.
CAUTION: MAKE SURE THAT ALL COMPONENTS ARE CLEAN AND FREE FROM
CONTAMINANTS BEFORE YOU INSTALL THEM IN THE FUEL SYSTEM. IF YOU
DO NOT DO THIS, YOU CAN CAUSE DAMAGE TO EQUIPMENT.
B. Install the left or right side forward vent−tube assembly into the center fuel tank as
follows:
(1) Remove the protective cover from the aft vent−tube assembly (3).
(2) Lubricate the preformed packing (11) with Petrolatum and install in the groove at
the open end of the aft vent−tube assembly (3).
(3) Lubricate the preformed packing (12) with Petrolatum and install in the groove at
the open end of the forward vent−tube (2).
(4) Lubricate the internal surface of the sleeve (4) with Petrolatum.
(5) Move the sleeve (4) over the aft vent−tube assembly (3) and the preformed
packing (11).
(6) Carefully put the forward vent−tube assembly (2) into the center fuel tank.
(7) Align the forward vent−tube assembly (2) with the aft vent−tube assembly (3) and
hold in position.

Master
EFFECTIVITY: See Pageblock 28−12−06 page 401
28−12−06 Page 409
Dec 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
(8) Put the clamp (10) around the forward vent−tube assembly (2) and loosely install
the screw (8) and the washer (9) at their center mounting location.
NOTE: This will help keep the forward vent−tube assembly (2) in its approximate
position.
(9) Put the clamp (7) around the forward vent−tube assembly (2) and loosely install the
screw (5) and the washer (6) at their forward mounting location.
(10) Make sure that the forward vent−tube assembly (2) is still aligned with the aft
vent−tube assembly (3).
NOTE: The vent−tubes assemblies, although aligned, must not touch.
(11) Move the sleeve (4) back over the end of the aft vent−tube assembly (3) and onto
the forward vent−tube assembly (2). Do this with a gentle to and from motion, until
the preformed packings (11) and (12) are fully enclosed.
(12) Install the coupling (1) over the sleeve (4) (Ref. TASK 20−30−00−910−802).
NOTE: When all three pawls are engaged the coupling will lock automatically.
(13) Tighten the screws (8) and (5) to keep the forward vent−tube assembly (2) in
position.

**ON A/C 7003−7007, 7009−7010, 7015−7016, 7019−7021, 7023−7025, 7036, 7045, 7047, 7049,
7051, 7053−7054, 7057−7060, 7064−7065, 7071, 7073−7074, 7078, 7081−7084, 7086−7087,
7089−7090, 7093, 7095−7098, 7104, 7107 and ON A/C 7008, 7011−7014, 7017−7018, 7022,
7026−7035, 7037−7044, 7046, 7048, 7050, 7052, 7055−7056, 7061−7063, 7066−7067,
7069−7070, 7072, 7075−7077, 7079−7080, 7085, 7088, 7091−7092, 7094, 7099−7103,
7105−7106, 7108−7109 Post SB601R−28−024

Subtask 28−12−06−420−003
Refer to Figure 402.
CAUTION: MAKE SURE THAT ALL COMPONENTS ARE CLEAN AND FREE FROM
CONTAMINANTS BEFORE YOU INSTALL THEM IN THE FUEL SYSTEM. IF YOU
DO NOT DO THIS, YOU CAN CAUSE DAMAGE TO EQUIPMENT.
C. Install the left or right side forward vent−tube assembly into the center fuel tank as
follows:
(1) Remove the protective cover from the aft vent−tube assembly (3).
(2) Lubricate the preformed packing (21) with Petrolatum and install in the groove at
the open end of the aft vent−tube assembly (3).
(3) Lubricate the preformed packing (22) with Petrolatum and install in the groove at
the open end of the forward vent−tube (2).
(4) Lubricate the internal surface of the sleeve (4) with Petrolatum.
(5) Move the sleeve (4) over the aft vent−tube assembly (3) and the preformed
packing (21).
(6) Carefully put the forward vent−tube assembly (2) into the center fuel tank.
(7) Align the forward vent−tube assembly (2) with the aft vent−tube assembly (3) and
hold in position.
(8) Put the clamp (18) around the cross−flow SOV−outlet−tube assembly (20) and the
clamp (19) around the forward vent−tube assembly (2). Loosely install the screw

Master
EFFECTIVITY: See Pageblock 28−12−06 page 401
28−12−06 Page 410
Dec 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
(17), washers (14) and (15), spacer (16) and nut (13).
NOTE: This will help keep the forward vent−tube assembly (2) in its approximate
position.
(9) Put the clamp (10) around the collector−tank tube assembly (12) and the clamp (11)
around the forward vent−tube assembly (2). Loosely install the screw (9), washers
(6) and (7), spacer (8) and nut (5).
(10) Make sure that the forward vent−tube assembly (2) is still aligned with the aft
vent−tube assembly (3).
NOTE: The vent−tubes assemblies, although aligned, must not touch.
(11) Move the sleeve (4) back over the end of the aft vent−tube assembly (3) and onto
the forward vent−tube assembly (2). Do this with a gentle to and from motion, until
the preformed packings (21) and (22) are fully enclosed.
(12) Install the coupling (1) over the sleeve (4) (Ref. TASK 20−30−00−910−802).
NOTE: When all three pawls are engaged the coupling will lock automatically.
(13) Tighten the nuts (5) and (13) onto the screws (9) and (17) to keep the forward
vent−tube assembly (2) in position.
**ON A/C 7003−7007, 7009−7010, 7015−7016, 7019−7021, 7023−7025, 7036, 7045, 7047, 7049,
7051, 7053−7054, 7057−7060, 7064−7065, 7071, 7073−7074, 7078, 7081−7084, 7086−7087,
7089−7090, 7093, 7095−7098, 7104, 7107, 7110−7990, 8000−8064, 8066−8068 and ON A/C
7008, 7011−7014, 7017−7018, 7022, 7026−7035, 7037−7044, 7046, 7048, 7050, 7052,
7055−7056, 7061−7063, 7066−7067, 7069−7070, 7072, 7075−7077, 7079−7080, 7085, 7088,
7091−7092, 7094, 7099−7103, 7105−7106, 7108−7109 Post SB601R−28−024

4. Close Out
Subtask 28−12−06−941−001
A. Remove all tools, equipment, and unwanted materials from the center fuel tank and work
area.

Subtask 28−12−06−410−001
B. Install the following access panel, as applicable (Ref. TASK 28−11−01−400−802):
ACCESS DESIGNATION
510AB Aluminum access panel
610AB Aluminum access panel

Master
EFFECTIVITY: See Pageblock 28−12−06 page 401
28−12−06 Page 411
Dec 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C ALL
FUEL TANK VENT AND FUEL LINE SHROUDS − LEAK TEST

1. General
A. This is a scheduled maintenance pressure leak test of the fuel tank vent and fuel line
shrouds.

TASK 28−12−10−790−801
Pressure Leak Test of the Fuel Tank Vent and Fuel Line Shrouds
1. Reason for the Job
Refer to MRB 28−12−00−03

2. Job Set−Up Information

Subtask 28−12−10−943−001
A. Tools and Equipment
REFERENCE DESIGNATION
G601R121605−1 Air test panel
G601R282001−1 Kit − fuel/vent line shrouds leak test
AN815−4 or equivalent Union flared tube
B. Reference Information
REFERENCE DESIGNATION
TASK 53−83−01−000−801 Remove MLG wheel bins
TASK 53−83−01−400−801 Install MLG wheel bins

3. Job Set−Up
Subtask 28−12−10−010−002
A. Remove the MLG wheel bins (Ref. TASK 53−83−01−000−801).

Subtask 28−12−10−010−003
B. It is possible to have a leak between the air test panel and the shroud drain fittings. If
necessary, remove the panels that follow:
REFERENCE DESIGNATION
161EL Overwing to Fuselage Fairing (Center)
162EL Overwing to Fuselage Fairing (Center)

Master
EFFECTIVITY: See Pageblock 28−12−10 page 501
28−12−10 Page 501
Mar 15/2005
 C
AIRCRAFT MAINTENANCE MANUAL
Subtask 28−12−10−840−001
C. Use the union flared tube to connect the air test panel to the shroud drain fitting on the
overwing fairing at FS 506.4 LBL 47.0 (10).
D. Use the adapter assembly (G601R282001−7 from the Kit) to block the fuel shroud drains
at the locations that follow:
± FS 502.4 RBL 45.0 (1)
± FS 502.4 LBL 45.0 (2).
E. Use the adapter assembly (G601R282001−3 from the Kit) to block the fuel shroud drains
at the locations that follow:
± FS 559.0+20 RBL 11.63 (3)
± FS 572.35 RBL 3.35 (4)
± FS 572.35 LBL 3.35 (5)
± FS 608.0 RBL 29.49 (6)
± FS 608.0 LBL 29.49 (7).

4. Procedure
Refer to Figure 501.
Subtask 28−12−10−790−001
CAUTION: DO NOT PRESSURIZE THE FUEL LINE SHROUD TO MORE THAN 9 PSI
(62 KPA). YOU CAN CAUSE DAMAGE TO THE FUEL LINE SHROUD.
A. Do a pressure leak test of the fuel line shrouds as follows:
(1) Set the air test panel to 9 psi (62 KPa).
(2) Open the outlet valve on the air test panel and pressurize the shroud to 9 psi
(62 KPa).
(3) Close the outlet valve on the air test panel.
(4) Make sure that the pressure does not leak more than 1.0 psi over 10 minutes.
(5) Remove pressure from the shroud.
(6) Disconnect the air test panel and pressure adapter from the shroud drain fitting on
the pressure box assembly.

Subtask 28−12−10−790−002
B. Do the pressure leak test of the main tank vent shrouds as follows:
(1) Connect the air test panel and adapter assembly (G601R282001−9 from the Kit) to
shroud drain fitting at FS 504.9 RBL 45.0 (8).
(2) Set the air test panel to 8 psi (55 KPa).
(3) Open the outlet valve on the air test panel and pressurize the shroud to 8 psi
(55 KPa).
(4) Close the outlet valve on the air test panel.
(5) Make sure that there is no loss of pressure over a 10 minute period.

Master
EFFECTIVITY: See Pageblock 28−12−10 page 501
28−12−10 Page 502
Mar 15/2005
 C
AIRCRAFT MAINTENANCE MANUAL
(6) Remove pressure from the shroud.
(7) Remove the hose assembly from shroud drain fitting at FS 504.9 RBL 45.0 (8).
(8) Connect the hose assembly to shroud drain fitting at FS 504.9 LBL 45.0 (9).
(9) Set the air test panel to 8 psi (55 KPa).
(10) Open the outlet valve on the air test panel and pressurize the shroud to 8 psi
(55 KPa).
(11) Close the outlet valve on the air test panel.
(12) Make sure that the pressure no loss of pressure over 10 minutes.
(13) Remove pressure from the shroud.

5. Close Out
Subtask 28−12−10−400−001
A. Install the MLG wheel bins (Ref. TASK 53−83−01−400−801).

Subtask 28−12−10−840−002
B. Remove the hose assembly from shroud drain fitting at FS 504.9 LBL 45.0 (8).
C. Remove the drain plugs from the fuel shroud drains at the locations that follow:
± FS 502.4 RBL 45.0 (1)
± FS 502.4 LBL 45.0 (2)
± FS 559.0+20 RBL 11.63 (3)
± FS 572.35 RBL 3.35 (4)
± FS 572.35 LBL 3.35 (5)
± FS 608.0 RBL 29.49 (6)
± FS 608.0 LBL 29.49 (7).

Subtask 28−12−10−410−001
D. If necessary, install the panels that follow:
REFERENCE DESIGNATION
161EL Overwing to Fuselage Fairing (Center)
162EL Overwing to Fuselage Fairing (Center)

Subtask 28−12−10−941−002
E. Remove all tools, equipment, and unwanted materials from the work area.

Master
EFFECTIVITY: See Pageblock 28−12−10 page 501
28−12−10 Page 503
Mar 15/2005
 C
AIRCRAFT MAINTENANCE MANUAL

B FS502.40 FS504.90
LBL45.0 LBL45.0

C
2
9
A
14
12

FS504.90 FS502.40
1 RBL45.0 RBL45.0 10
8

FS501.40 FS503.90 FS506.40

13 LBL47.0 LBL47.0 LBL47.0

A LEFT SIDE
11

15

RBL11.63 3
FS506.40 FS503.90 FS501.40
RBL47.0 RBL47.0 RBL47.0 FS559.00
+20.00
RBL3.35
B RIGHT SIDE
LBL3.35
LEGEND
1. Fuel shroud drain. 4 5
2. Fuel shroud drain.
3. Fuel shroud drain. FS572.35
4. Fuel shroud drain.
5. Fuel shroud drain.
6. Fuel shroud drain.
7. Fuel shroud drain. FS608.00
ram2812105_001.dg, pm/lr, 3/03/03

8. Shroud drain fitting.

9. Shroud drain fitting.
10. Shroud drain fitting.
11. Shroud drain fitting.
12. Shroud drain fitting.
13. Shroud drain fitting. 6 RBL29.49 LBL29.49 7
14. Shroud drain fitting.
15. Shroud drain fitting. C

Fuel Line Shrouds − Pressure Leak Test

Figure 501

Master
EFFECTIVITY: See Pageblock 28−12−10 page 501
28−12−10 Page 504
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C ALL
TRANSFER SYSTEM − DESCRIPTION AND OPERATION

1. General
A. The transfer system controls fuel flow and fuel balance between all of the fuel tanks. The
transfer system has the components that follow:
± Two transfer ejector pumps
± Two transfer ejector screens
± Two aft scavenge−ejector pumps
± Two scavenge ejector screens
± Two gravity−feed check valves
± Two fuel−transfer shutoff valves
± One gravity−crossflow shutoff valve
± Two crossflow check valves
± Two fuel−crossflow shutoff valves
± Two fuel crossflow restrictors
± One GRAVITY XFLOW switch/light
± Two XFLOW L and R switch/lights
± One AUTO OVERRIDE switch/light.
The auxiliary power unit (APU) fuel pump (28−24−00) is also used in the transfer
system.
2. Component Details
A. Transfer Ejector Pump
Refer to Figure 1.
(1) The transfer ejector pumps are venturi−type ejector tubes that are operated by the
motive flow system (28−22−00). They are located in the aft section of the center
tank, connected to the transfer manifolds.
(2) Each transfer ejector pump has a motive flow port, a venturi tube, a pickup port, an
output port, and a flapper−type check valve. When motive flow pressure is supplied
to the motive flow port, it causes a venturi effect in the venturi tube. This causes
fuel at the pickup port to move through the pump to the output port, and to be
pumped through the transfer manifold.
(3) The flapper−type check valve is installed in the pickup port of the transfer ejector
pump. The check valve keeps fuel pressure in the transfer manifold when the
transfer ejector pump does not operate. When the transfer ejector pump operates,
fuel suction at the pickup port causes the flapper to open. With the flapper open,
fuel goes into the transfer ejector pump. If the transfer ejector pump stops, the
flapper closes the transfer manifold and does not let fuel flow back into the center
tank.
B. Transfer Ejector Screen
(1) The transfer ejector screens are metal−mesh screens that make a box around the
pickup port of the transfer ejector pumps. These screens keep unwanted material
out of the transfer ejector pumps. They also prevent ice formation around the

Master
EFFECTIVITY: See Pageblock 28−13−00 page 1
28−13−00 Page 1
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
pickup port of the transfer ejector pump.
C. Aft Scavenge−Ejector Pump
(1) The aft scavenge−ejector pumps are venturi−type ejector tubes that are operated
by the motive flow system. They are located at the lowest point of the aft inboard
section of each main tank, connected to the scavenge manifolds.
(2) Each aft scavenge−ejector pump has a motive flow port, a venturi tube, a pickup
port, an output port, and a suction port. When motive flow pressure is supplied to
the motive flow port, it causes a venturi effect in the venturi tube. This causes fuel
at the pickup port to move through the pump to the output port, and to be moved
through the scavenge manifold.
(3) The suction port is connected to the vent system, and lets fuel in the vent line drain
into the fuel tank. For more information, refer to the vent system (28−12−00).
D. Scavenge Ejector Screen
(1) The scavenge ejector screens are metal−mesh screens that make a box around the
pickup port of the aft scavenge−ejector pumps. These screens keep unwanted
material out of the aft scavenge−ejector pumps. They also prevent ice formation
around the pickup port of the aft scavenge−ejector pump.
E. Gravity−Feed Check Valve
(1) The gravity−feed check valves are flapper−type valves. They are located in the
collector tanks, installed on the ends of the gravity feed manifolds.
(2) Each gravity−feed check valve has a swing assembly and a bracket. The bracket
holds the swing assembly in place on the open port of the gravity feed manifold.
Fuel in the main tank pushes against the swing assembly, which lets the fuel flow
into the gravity feed manifold. In case of reverse flow, the fuel in the gravity feed
manifold pushes the swing assembly closed, and closes the gravity feed manifold.
F. Fuel−Transfer Shutoff Valve
(1) The fuel−transfer shutoff valves are electrically−operated plunger−type valves.
They are located in the aft center wing box, connected to the motive flow lines of
the transfer ejector pumps.
(2) Each fuel−transfer shutoff valve has a 28−volt−dc solenoid, a status circuit, a
plunger, and a valve body. When a close−valve signal is supplied to the solenoid,
the solenoid pushes the plunger into the passage of the valve body. This closes the
valve and stops fuel pressure in the motive flow line to the transfer ejector pump.
When the plunger has closed the valve, the status circuit sends a valve−closed
status signal.
(3) When an open−valve signal is supplied to the solenoid, the solenoid pulls the
plunger out of the passage of the valve body, which opens the valve. Motive flow
pressure is then supplied through the valve to the transfer ejector pump. This also
causes the status circuit to supply a valve−open status signal.
G. Gravity−Crossflow Shutoff Valve
Refer to Figure 2.
(1) The gravity−crossflow shutoff valve is an electrically−operated butterfly valve. It is
located in the center wing box, connected to the center of the gravity crossflow
manifold.

Master
EFFECTIVITY: See Pageblock 28−13−00 page 1
28−13−00 Page 2
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
(2) The gravity−crossflow shutoff valve has a 28−volt−dc motor, a status switch, a
butterfly flapper, and a valve body. When an open−valve signal is supplied to the
valve motor, the motor turns the butterfly flapper, which opens the passage in the
valve body. This lets fuel flow in either direction through the gravity crossflow
manifold. When the butterfly flapper is open, the status switch closes the contacts in
the open−valve−position circuit to supply a valve−open status signal.
(3) When a close−valve signal is supplied to the valve motor, the motor turns the
butterfly flapper in the other direction, which closes the valve. This also causes the
status switch to close the contacts in the closed−valve−position circuit to supply a
valve−closed status signal.
H. Crossflow Check Valve
(1) The crossflow check valves are spring−loaded, poppet−type valves. They are
installed in the center wing box, in the APU feed/crossflow manifold.
(2) Each crossflow check valve has a poppet, a spring, and a valve body. When
pressure in the APU feed/crossflow manifold decreases, fuel pressure in the main
tanks pushes the poppet. This opens the passage in the valve body. When fuel flow
in the APU feed/crossflow manifold stops, the spring pushes the poppet back into
position, and the valve closes.
I. Fuel−Crossflow Shutoff Valve
(1) The fuel−crossflow shutoff valves are electrically−operated, plunger−type valves.
They are located in the aft center wing box, connected to the APU fuel pump
through the power crossflow manifold.
(2) Each fuel−crossflow shutoff valve has a 28−volt−dc solenoid, a status circuit, a
plunger, a spring, and a valve body. When an open−valve signal is supplied to the
solenoid, the solenoid pulls the plunger out of the passage of the valve body. This
opens the valve and lets fuel flow from the APU fuel pump into the power crossflow
manifold. This also causes the status circuit to supply a valve−open status signal.
(3) When the open−valve signal is disconnected, the spring pushes the plunger into the
passage of the valve body, which closes the valve. This stops the fuel flow in the
power crossflow manifold. When the plunger has closed the valve, the status circuit
sends a valve−closed status signal.
J. Fuel Crossflow Restrictor
(1) The fuel crossflow restrictors are bulkhead−mounted flow restrictors. They are
mounted on the inboard rib of each main tank, connected to the output end of the
power crossflow manifold.
(2) Each fuel crossflow restrictor has a rib mounting plate and a restrictor union. The
open diameter of the restrictor union is smaller than the output end of the power
crossflow manifold.
K. GRAVITY XFLOW Switch/Light
Refer to Figure 3.
(1) The GRAVITY XFLOW switch/light is an illuminated, split−legend pushbutton. It is
located on the FUEL control panel on the overhead panel in the flight compartment.
(2) The GRAVITY XFLOW switch/light is used to control and monitor the status of the
gravity−crossflow shutoff valve. When the switch/light is off, the gravity−crossflow
shutoff valve is closed. If the operator pushes the switch/light, the gravity−crossflow
shutoff valve is opened. This sends a signal back to the switch/light which makes

Master
EFFECTIVITY: See Pageblock 28−13−00 page 1
28−13−00 Page 3
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
the OPEN legend come on.
(3) When the operator pushes the switch/light again, the gravity−crossflow shutoff
valve closes. This sends a signal back to the switch/light which makes the OPEN
legend go off.
(4) If the gravity−crossflow shutoff valve does not operate, a signal is sent to the
XFLOW switch/light which makes the FAIL legend come on.
L. XFLOW L and R Switch/Lights
(1) The XFLOW L and R switch/lights are illuminated, split−legend pushbuttons. They
are located on the FUEL control panel on the overhead panel in the flight
compartment. One switch/light is for the right side and one switch/light is for the left
side.
(2) The XFLOW L and R switch/lights are used to control and monitor the status of the
applicable fuel−crossflow shutoff valve. When the switch/light is off, the
fuel−crossflow shutoff valve is closed. When the operator pushes the switch/light,
the fuel−crossflow shutoff valve opens. This sends a signal back to the switch/light
which makes the ON legend come on.
(3) When the operator pushes the switch/light again, the fuel−crossflow shutoff valve
closes. This sends a signal back to the switch/light which makes the ON legend go
off.
(4) If the fuel−crossflow shutoff valve does not operate, a signal is sent to the XFLOW
switch/light which makes the FAIL legend come on.
M. AUTO OVERRIDE Switch/Light
(1) The AUTO OVERRIDE switch/light is an illuminated, single−legend pushbutton. It is
located on the FUEL control panel on the overhead panel in the flight compartment.
(2) The AUTO OVERRIDE switch/light is used to permit override of auto transfer and
also to allow the XFLOW SOV (L and R) to be operated manually. The APU fuel
pump operates in manual mode when one of the XFLOW SOV push buttons is
depressed. This sends a signal back to the switch/light which makes the MAN
legend come on.
(3) If the operator pushes the switch/light again, the operator sets the APU fuel pump
to the automatic mode. This sends a signal back to the switch/light which makes the
MAN legend go off.
3. Operation
Refer to Figure 4.
A. The transfer system controls the crossflow and transfer of fuel in the fuel system. The
transfer system has the functions that follow:
± Fuel scavenge from the main tanks to the collector tanks
± Gravity fuel transfer from the main tanks to the collector tanks
± Power fuel crossflow between the main tanks
± Gravity fuel crossflow between the main tanks
± Fuel transfer from the center tank to the main tanks.
B. Fuel scavenge from the main tanks to the collector tanks is supplied by the aft
scavenge−ejector pumps. The motive flow system supplies fuel pressure to the motive
flow port of the aft scavenge−ejector pumps. This causes the aft scavenge−ejector

Master
EFFECTIVITY: See Pageblock 28−13−00 page 1
28−13−00 Page 4
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
pumps to operate. The aft scavenge−ejector pumps move fuel from the main tanks
through the scavenge ejector screens, through the scavenge manifold, and to the
collector tanks. The aft scavenge−ejector pumps are at the lowest point of the main
tanks and behind a baffle. The baffle has check valves installed in the base to help
ensure a positive fuel level at the pickup port.
C. Fuel transfer from the main tanks to the collector tanks is supplied by gravity feed
through the gravity feed lines. Reverse flow in these gravity feed lines is prevented by
the gravity−feed check valves.
Refer to Figure 5.
D. Power fuel crossflow is automatically controlled between the two main tanks when a fuel
imbalance occurs. For power fuel crossflow, the APU fuel pump is used to move fuel
through the APU feed/crossflow manifold and the power crossflow manifold.
E. If there is a fuel imbalance of more than 200 pounds (91 kg), the fuel system computer
supplies a ground signal to the APU−pump control relay. When the relay closes, it
supplies 28−volt−dc power to the APU fuel pump. The fuel system computer also
supplies a ground signal to the applicable fuel−crossflow shutoff valve. The 28−volt−dc
power is supplied to the shutoff valve through the auto mode relay. These signals cause
the shutoff valve to open and to send the status signal to the fuel system computer.
F. When the APU fuel pump operates, fuel is supplied at the APU inlet screens in each
main tank. The fuel then goes through the crossflow check valves which prevent reverse
flow in the manifold. From there, the fuel flows into the APU fuel pump. The APU fuel
pump moves the fuel into the power crossflow manifold, through the open fuel−crossflow
shutoff valve, and into the applicable main tank. Fuel flow is controlled at the outlet of the
power crossflow manifold by the fuel crossflow restrictors. Power fuel crossflow
continues until the less full of the two main tanks has 50 pounds more fuel than the other
main tank.
G. If the fuel system computer does not operate, the operator can control power fuel
crossflow manually. When the AUTO OVERRIDE switch/light on the FUEL control panel
is pushed, it disconnects the ground signal from the auto mode relay. When the relay
opens, it disconnects the fuel−crossflow shutoff valves from the fuel system computer.
The operator then pushes the XFLOW R or L switch/light. When this switch/light is
closed, it supplies a ground signal through the AUTO OVERRIDE switch to the
applicable fuel−crossflow shutoff valve and to the APU−pump control relay. The shutoff
valve then opens and fuel flows into the appropriate main tank.
Refer to Figure 6.
H. Gravity fuel crossflow is manually operated and is used when the power fuel−crossflow
function does not operate. Gravity fuel crossflow is controlled by the gravity−crossflow
shutoff valve in the gravity crossflow manifold. If the GRAVITY XFLOW switch/light on
the FUEL control panel is pushed, the switch/light supplies 28−volt−dc power to the
OPEN circuit of the shutoff valve. This signal causes the valve to open. Fuel then flows
through the gravity crossflow manifold between the two main tanks until the two fuel
levels are equal. If the operator pushes the switch/light again, the switch/light supplies
28−volt−dc power to the CLOSE circuit of the shutoff valve, and the valve closes.
I. Fuel transfer from the center tank to the main tanks is fully controlled by the fuel system
computer. This function uses the transfer−ejector shutoff valves and the transfer ejector
pumps.

Master
EFFECTIVITY: See Pageblock 28−13−00 page 1
28−13−00 Page 5
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
J. When either of the main tanks is less than 93 percent full, the fuel system computer
removes a ground signal to the applicable transfer−ejector shutoff valve. This signal
causes the transfer−ejector shutoff valve to open and to send the status signal to the fuel
system computer. When the shutoff valve is open, fuel pressure from the motive flow
system moves to the motive flow port of the transfer ejector pump. Motive flow pressure
causes the transfer ejector pump to operate. The transfer ejector pump moves fuel from
the center tank through the transfer ejector screen, through the transfer manifold, and to
the main tank.
K. When the fuel level in the main fuel tank increases to 97 percent full, the fuel system
computer closes the applicable transfer−ejector shutoff valve. This stops motive flow
pressure to the transfer ejector pump, which causes the transfer ejector pump to stop. If
a failure occurs in the transfer−ejector shutoff valve, the shutoff valve stays open and
fuel transfer continues until the center tank is empty.
4. Component Location Index
Refer to Figure 7.
COMPONENT NAME QTY ACCESS/ZONE REFERENCE
Check valve, crossflow 2 510AB, 610AB 28−13−19
Check valve, gravity feed 2 510AB, 610AB 28−13−28
Circuit breakers:
XFLOW SOV, M8 1 CBP−1/221 −
FUEL GRAVITY XFLOW, B9 1 CBP−4/221 −
XFER/APU APU ECU, N12 1 CBP−1/221 −
XFER/APU CONT, N11 1 CBP−1/221 −
XFER/APU FUEL PUMP, N10 1 CBP−1/221 −
Pump, aft scavenge ejector 2 540AB, 640AB 28−13−22
Pump, transfer ejector 2 510AB, 610AB 28−13−01
Restrictor, fuel crossflow 2 540AB, 640AB −
Screen, scavenge ejector 2 540AB, 640AB −
Screen, transfer ejector 2 510AB, 610AB −
Switch/light, XFLOW L 1 Flight compartment −
Switch/light, XFLOW R 1 Flight compartment −
Switch/light, GRAVITY XFLOW 1 Flight compartment 28−13−31
Switch/light, AUTO OVERRIDE 1 Flight compartment −
Valve, gravity crossflow shutoff 1 510AB, 610AB 28−13−16
Valve, fuel crossflow shutoff 2 510BB, 610BB 28−13−45
Valve, fuel transfer shutoff 2 510AB, 610AB 28−13−43

Master
EFFECTIVITY: See Pageblock 28−13−00 page 1
28−13−00 Page 6
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

A C
D

B A
B
D

FUEL TRANSFER
B
SHUTOFF VALVE

TRANSFER EJECTOR
A
PUMP

ram2813000_003(1).dc, ks, 04/01/93

GRAVITY FEED AFT SCAVENGE

C D
CHECK VALVE EJECTOR PUMP

Transfer System − Component Location/Recognition

Figure 1

Master
EFFECTIVITY: See Pageblock 28−13−00 page 1
28−13−00 Page 7
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

B
A
D
B

C D
C

GRAVITY CROSSFLOW
A
SHUTOFF VALVE

FUEL CROSSFLOW
B
SHUTOFF VALVE

C CROSSFLOW
CHECK VALVE ram2813000_004(1).dc, ks, 04/01/93

FUEL CROSSFLOW
D RESTRICTOR

Transfer System Crossflow − Component Location/Recognition

Figure 2

Master
EFFECTIVITY: See Pageblock 28−13−00 page 1
28−13−00 Page 8
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

GRAVITY XFLOW
SWITCH/LIGHT

L BOOST GRAVITY R BOOST

PUMP XFLOW PUMP

ON FAIL ON
F INOP OPEN INOP
U
E XFLOW
L AUTO OVERRIDE R
L
ON ON
MAN ram2813000_005(2).dg, gd/sw, 08/08/95
FAIL FAIL

XFLOW L AUTO OVERRIDE XFLOW R

SWITCH/LIGHT SWITCH/LIGHT SWITCH/LIGHT

Transfer System Controls − Component Location/Recognition

Figure 3

Master
EFFECTIVITY: See Pageblock 28−13−00 page 1
28−13−00 Page 9
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

GRAVITY
CROSSFLOW
GRAVITY FEED SHUTOFF GRAVITY FEED
CHECK VALVE VALVE CHECK VALVE

AFT AFT
SCAVENGE SCAVENGE
EJECTOR EJECTOR
PUMP COLLECTOR COLLECTOR PUMP
TANK FROM TANK
MOTIVE
FLOW

FUEL FUEL
TRANSFER TRANSFER TRANSFER TRANSFER
SCAVENGE SHUTOFF SCAVENGE
EJECTOR SHUTOFF EJECTOR
EJECTOR VALVE VALVE EJECTOR
PUMP PUMP
SCREEN SCREEN
APU
FUEL
FUEL PUMP FUEL
CROSSFLOW CROSSFLOW
RESTRICTOR RESTRICTOR

FROM FROM
MOTIVE MOTIVE
FLOW FLOW

TRANSFER TRANSFER
EJECTOR EJECTOR
SCREEN SCREEN

CROSSFLOW CROSSFLOW
CHECK CHECK
FUEL CROSSFLOW FUEL CROSSFLOW
VALVE VALVE
SHUTOFF VALVE SHUTOFF VALVE
ram2813000_001(1).dg, pb, 04/01/93

Transfer System − Schematic

Figure 4

Master
EFFECTIVITY: See Pageblock 28−13−00 page 1
28−13−00 Page 10
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

+28V
BATTERY
BUS
NOTE XFER/ APU PUMP
AUTO PWR FUEL XFLOW OCCURS
WHEN THERE IS A FUEL IMBALANCE XFER/ APU PUMP FUEL SYSTEM
OF MORE THAN 200 LBS (91 KG) CONTROL RELAY COMPUTER
BETWEEN L & R MAIN TANKS.

ON APU PUMP
FAIL
+28V LEFT RIGHT
XFLOW SOV SWITCH XFLOW SOV
BATTERY
BUS RIGHT XFLOW
AUTO SOV SIGNAL
OVERRIDE
AUTO

GRND RTN

OPEN MAN

RIGHT XFLOW
SOV RTN
ON
FAIL
GRND RTN
RIGHT MAN
XFLOW SOV SWITCH
LEFT XFLOW
SOV SIGNAL
LEFT
XFLOW SOV
MANUAL/AUTO
XFLOW
OPEN
AUTO LEFT XFLOW
MODE SOV RTN
RELAY AUTO

ram2813000_007(2).dg, gd/sw, 18/08/95

MAN

STATE
RELAYS DE−ENERGIZED
L & R XFLOW SOV SWs.
IN CLOSED POS. & AUTO
OVERRIDE SW. IN AUTO POSITION.

Auto/Manual Power Fuel Crossflow Function − Electrical Schematic

Figure 5

Master
EFFECTIVITY: See Pageblock 28−13−00 page 1
28−13−00 Page 11
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

STATE
GRAVITY X FLOW
MANUAL/X−FLOW GRAVITY
30V CLOSED
LEFT FUEL SWITCH/LIGHT XFLOW SOV
XFER SOV
CLOSED

CLOSE
+ 28 VDC CLOSE
DC ESSENTIAL DC
BUS OPEN MOTOR

OPEN GRND
FAIL
OPEN

EICAS
PRIMARY DCU
1

GRAV X FLOW X FLOW OPEN OPEN

OPEN
STATUS
GRAV XFLOW X FLOW FAIL SW
FAIL X FER SOV
FAIL
CLOSED
X FER GRAV
SOV X FLOW
POS POS
2 NOTE
GRAVITY X FLOW 3 NOTE
SOV & LEFT FUEL TOTAL FUEL FUEL FUEL USED

L (R) X FER X FER SOV

12100 LBS
1060 KG
3900 LBS
LEFT X FER SOV
SHOWN IN THE IS SHOWN RIGHT
SOV P AUTO
BAL
IS SIMILAR
CLOSED POSITION
P P

FUEL SYSTEM
4870 LBS 4890 LBS

3 LEFT FUEL
COMPUTER 2 35 C 36 C X FER SOV
APU
LO PRESS LO PRESS
FUEL CH 1/2 FAIL

LEFT X FER EICAS FUEL SYNOPTIC

SOV OPEN/CLOSE
28 VDC SOLENOID
+ 28 VDC GRND
DC ESSENTIAL
1 NOTE BUS
GRAV X FLOW
ram2813000_008.dg, sw, 18/08/95

CLOSED CLOSED
FAIL CAUTION STATUS
MESSAGE WILL OPEN OPEN
BE DISPLAYED
ON EICAS WHEN
GRAVITY X FLOW
SOV POSITION
IS NOT CONFIRMED
AFTER 5 SECOND
TIME DELAY.

Gravity Fuel Crossflow and Fuel Transfer Functions − Electrical Schematic

Figure 6

Master
EFFECTIVITY: See Pageblock 28−13−00 page 1
28−13−00 Page 12
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

610AB 510AB

610BB 510BB

640AB 540AB

NOTE
500 series panels are on the left side.
600 series panels are on the right side.

ram2813000_002(1).dg, pb/rm, 29/07/97

Transfer System − Component Access

Figure 7

Master
EFFECTIVITY: See Pageblock 28−13−00 page 1
28−13−00 Page 13
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C ALL
TRANSFER SYSTEM − ADJUSTMENT/TEST

1. General
A. The maintenance procedure that follows is for the test of the fuel manual−crossflow
system.

TASK 28−13−00−710−801
Operational Test of the Fuel Manual−Crossflow System

1. Reason for Job

Refer to CMR C28−00−142−01.

2. Job Set−Up Information

Subtask 28−13−00−946−001
A. Reference Information
REFERENCE DESIGNATION
TASK 12−11−28−650−802 Manual Pressure Refueling
TASK 12−00−07−861−801 Connect External AC Power
TASK 12−00−07−861−802 Remove External AC Power

3. Job Set−Up
Subtask 28−13−00−865−001
A. Make sure that the circuit breakers that follow are closed:
CB PANEL CB NO. NAME ZONE
CBP−1 M8 XFLOW SOV 221
CBP−1 M12 FUEL SYST CONT 221
CBP−1 N10 XFER/APU FUEL PUMP 221
CBP−1 N11 XFER/APU CONT 221
CBP−1 N12 XFER/APU APU ECU 221
CBP−4 B9 FUEL GRAV XFLOW 222
CBP−4 B10 FUEL SYST CONT 222

Subtask 28−13−00−010−001
B. Open the access door that follows:

Master
EFFECTIVITY: See Pageblock 28−13−00 page 501
28−13−00 Page 501
Sep 10/2004
 C
AIRCRAFT MAINTENANCE MANUAL

ACCESS DESIGNATION
811 Main avionics compartment door

Subtask 28−13−00−650−001
C. Connect the external AC power to the aircraft (Ref. TASK 12−00−07−861−801).

Subtask 28−13−00−650−002
D. Refuel the aircraft if necessary (Ref. TASK 12−11−28−650−802).

4. Procedure
Subtask 28−13−00−710−001
A. Push the RESET button on the fuel system computer, which is installed in the right side
of the main avionics compartment.
B. Push the FUEL push−button on the engine indication and crew alerting system (EICAS)
control panel to show the FUEL synoptic display.
C. Do an operational test of the fuel manual crossflow system as follows:
(1) Make sure the switch/lights on the refuel/defuel control panel that follow are not on:
± XFLOW AUTO OVERRIDE switch/light
± L BOOST PUMP switch/light
± R BOOST PUMP switch/light
± XFLOW L switch/light
± XFLOW R switch/light
± GRAVITY XFLOW switch/light.
(2) Make sure that the MAN XFLOW status indication is not shown on the status page
of the FUEL synoptic display.
(3) Make sure the EICAS indications on the FUEL synoptic display are shown as
follows:
± The APU fuel−pump outline is shown in white
± The left and the right fuel−crossflow shutoff−valve outlines are shown in white
± The left and right fuel crossflow shutoff valves are shown in the closed position
and the green flow lines are not shown.
(4) Push in the GRAVITY XFLOW switch/light on the refuel/defuel control panel.
(5) Make sure the results that follow occur:
± The OPEN light comes on and the FAIL light does not come on
± The shutoff valve outline is shown in white on the FUEL synoptic display of the
EICAS
± The shutoff valve is shown in the open position and the flow line is shown in
green
± The GRAV XFLOW OPEN advisory indication is shown on the status page of
the secondary EICAS display.

Master
EFFECTIVITY: See Pageblock 28−13−00 page 501
28−13−00 Page 502
Sep 10/2004
 C
AIRCRAFT MAINTENANCE MANUAL
(6) Push out the GRAVITY XFLOW switch/light on the refuel/defuel control panel.
(7) Make sure the results that follow occur:
± The OPEN light goes off
± The shutoff valve outline is shown in the closed position
± The green flow line is not shown on the FUEL synoptic display
± Make sure the GRAV XFLOW OPEN advisory indication is not shown on the
status page of the FUEL synoptic display.

5. Close−Out
Subtask 28−13−00−861−002
A. Remove the external AC power from the aircraft (Ref. TASK 12−00−07−861−802).

Subtask 28−13−00−941−001
B. Remove all tools, equipment, and unwanted materials from the work area.

Subtask 28−13−00−410−001
C. Close the access doors that follow:
ACCESS DESIGNATION
811 Main avionics compartment door

Master
EFFECTIVITY: See Pageblock 28−13−00 page 501
28−13−00 Page 503
Sep 10/2004
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C ALL
PUMP, TRANSFER EJECTOR − REMOVAL/INSTALLATION

1. General
A. The maintenance procedures that follow are for the removal and installation of the
transfer ejector pump. There are two transfer ejector pumps in the fuel system. They are
found in the aft end of the center tank. The transfer ejector pumps are connected to the
transfer manifold between the center tank and the main tanks.
B. It is necessary to defuel, drain, and remove the fuel fumes from the center tank to
remove or install the transfer ejector pump.

TASK 28−13−01−000−801
Removal of the Transfer Ejector Pump

1. Job Set−Up Information

Subtask 28−13−01−946−001
A. Reference Information
REFERENCE DESIGNATION
TASK 12−11−28−650−804 Suction Defueling
TASK 20−30−00−910−802 Wiggins Couplings − Maintenance Practices
TASK 28−00−00−910−801 Fuel Safety Precautions
TASK 28−11−00−840−801 Prepare Fuel Tank for Access
TASK 28−11−00−840−802 Removal of Fuel Fumes
TASK 28−11−01−000−801 Removal of the Honeycomb Access Panel
TASK 28−11−01−000−802 Removal of the Graphite Access Panel

2. Job Set−Up
Subtask 28−13−01−910−001
WARNING: OBEY ALL THE FUEL SAFETY PRECAUTIONS WHEN YOU DO WORK ON THE
FUEL SYSTEM AND/OR A FUEL SYSTEM COMPONENT. IF YOU DO NOT DO
THIS, YOU CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO
EQUIPMENT.
A. Obey all the fuel safety precautions (Ref. TASK 28−00−00−910−801).

Subtask 28−13−01−650−001
B. Defuel the center tank (Ref. TASK 12−11−28−650−804).

Subtask 28−13−01−010−001
C. To remove the left transfer ejector pump, remove the access panel that follows (Ref.
TASK 28−11−01−000−801):

Master
EFFECTIVITY: See Pageblock 28−13−01 page 401
28−13−01 Page 401
Sep 10/2004
 C
AIRCRAFT MAINTENANCE MANUAL

ACCESS DESCRIPTION
510AB Fuel tank access panel
D. To remove the right transfer ejector pump, remove the access panel that follows (Ref.
TASK 28−11−01−000−802):
ACCESS DESCRIPTION
610AB Fuel tank access panel

Subtask 28−13−01−840−001
E. Prepare the center tank for access (Ref. TASK 28−11−00−840−801).
F. Remove the fuel fumes from the center tank (Ref. TASK 28−11−00−840−802).

3. Procedure
Subtask 28−13−01−020−001
Refer to Figure 401.
A. Remove the transfer ejector pump as follows:
(1) Remove the lockwire from the motive line (1). Discard the lockwire.
(2) Disconnect the motive line (1). Put a protective plug in the motive line.
(3) Remove the coupling (2) (Ref. TASK 20−30−00−910−802).
(4) Remove the bolts (3), the washers (4), and the tab (5).
(5) Remove the transfer ejector pump (6) the shim (7), and the sleeve (8).
(6) Remove and discard the preformed packings (9).
(7) Put a protective plug in the transfer manifold.

Master
EFFECTIVITY: See Pageblock 28−13−01 page 401
28−13−01 Page 402
Sep 10/2004
 C
AIRCRAFT MAINTENANCE MANUAL

1 3
4
6

7 TRANSFER
9 MANIFOLD
(REF)
8

2
9

LEGEND
1. Motive line. A
2. Coupling.
3. Bolt.
4. Washer.
5. Tab. FILLET SEAL
6. Transfer ejector pump. AROUND EDGES
7. Shim.
8. Sleeve.
9. Preformed packing.
ram2813014_001.dg, ks/lr, 29/01/04

NOTES
0.25 TO 0.30 in.
1. Left transfer ejector pump shown, BOTTOM TUBE (6.35 TO 7.62 mm) WING
right transfer ejector pump is opposite. OF TRANSFER GAP
EJECTOR PLANK
Apply sealant SAE AMS−S−8802.
B

Transfer Ejector Pump − Removal/Installation

Figure 401

Master
EFFECTIVITY: See Pageblock 28−13−01 page 401
28−13−01 Page 403
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
TASK 28−13−01−400−801
Installation of the Transfer Ejector Pump

1. Job Set−Up Information

Subtask 28−13−01−944−001
A. Consumable Materials
REFERENCE DESIGNATION
05−004 Lockwire
06−002 Petrolatum
09−013 Sealant, fuel tank, low weight

Subtask 28−13−01−945−001
B. Parts
REF NAME OF PART QTY IPC SEQUENCE NO.
3 Bolt 4 IPC 28−13−01−1A−020
4 Washer 4 IPC 28−13−01−1A−025
5 Tab 1 IPC 28−13−01−1A−045
7 Shim AR IPC 28−13−01−1A−030
9 Preformed packing 2 IPC 28−13−01−2A−050

Subtask 28−13−01−946−002
C. Reference Information
REFERENCE DESIGNATION
TASK 20−30−00−910−802 Wiggins Couplings − Maintenance Practices
TASK 28−11−01−400−801 Installation of the Honeycomb Access Panel
TASK 28−11−01−400−802 Installation of the Graphite Access Panel
TASK 28−13−01−710−801 Operational Test of the Transfer Ejector Pump
TASK 51−23−00−390−804 Bead Seal Sealant Procedure
TASK 51−23−00−390−808 Application of Sealant with a Brush
TASK 51−80−00−760−803 Electrical Bonding Test

2. Procedure
Subtask 28−13−01−869−001
A. Make sure that the aircraft is in the same configuration as in the removal task.

Subtask 28−13−01−420−001
Refer to Figure 401.

Master
EFFECTIVITY: See Pageblock 28−13−01 page 401
28−13−01 Page 404
Sep 10/2004
 C
AIRCRAFT MAINTENANCE MANUAL
B. Install the transfer ejector pump as follows:
(1) Remove the protective plug from the transfer manifold.
(2) Install the shim (7) and the transfer ejector pump (6).
(3) Measure the clearance between the bottom tube of the transfer ejector pump and
the wing plank. Make sure that the clearance is 0.25−0.30 inch (6.35−7.62 mm).
NOTE: If the clearance is not correct, the transfer ejector pump will not operate
correctly.
(4) Remove or install more shims (7) as necessary to correct the clearance between
the bottom tube of the transfer ejector pump and the wing plank.
(5) Lubricate the preformed packings (9) and install the preformed packings (9) on the
transfer manifold and the transfer ejector pump (6).
(6) Connect the transfer manifold to the transfer ejector pump (6) with the sleeve (8)
and the coupling (2) (Ref. TASK 20−30−00−910−802).
(7) Install the washers (4), the tab (5), and the bolts (3).
NOTE: Make sure that the tab washer is installed on the bolt adjacent to the
motive line (1).
(8) Apply the sealant 09−013B to all the bolts (3) (Ref. TASK 51−23−00−390−808).
(9) Fillet seal around the edges of the ejector pump (6) (Ref. TASK
51−23−00−390−804).
(10) Do the electrical bonding test of the coupling (2) (Ref. TASK 51−80−00−760−803).
(11) Remove the protective plug from the motive line (1). Connect the motive line to the
transfer ejector pump (6).
(12) Safety the motive line to the tab washer (5) with lockwire.

3. Close Out
Subtask 28−13−01−410−001
A. If the left transfer ejector pump was replaced, install the access panel that follows (Ref.
TASK 28−11−01−400−801):
ACCESS DESCRIPTION
510AB Fuel tank access panel
B. If the right transfer ejector pump was replaced, install the access panel that follows (Ref.
TASK 28−11−01−400−802):
ACCESS DESCRIPTION
610AB Fuel tank access panel

Subtask 28−13−01−710−001
C. Do an operational test of the transfer ejector pump (Ref. TASK 28−13−01−710−801).

Master
EFFECTIVITY: See Pageblock 28−13−01 page 401
28−13−01 Page 405
Sep 10/2004
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C ALL
PUMP, TRANSFER EJECTOR − ADJUSTMENT/TEST

1. General
A. The maintenance procedure that follows is for the test of the transfer ejector pump.

TASK 28−13−01−710−801
Operational Test of the Transfer Ejector Pump

1. Job Set−Up Information

Subtask 28−13−01−946−003
A. Reference Information
REFERENCE DESIGNATION
TASK 12−00−07−861−801 Connect External AC Power
TASK 12−00−07−861−802 Remove External AC Power
TASK 12−11−28−650−802 Manual Pressure Refueling
TASK 71−00−00−868−806 Engine Start
TASK 71−00−00−868−807 Engine Shutdown (Normal)

2. Job Set−Up
Subtask 28−13−01−650−002
A. Refuel the center tank (Ref. TASK 12−11−28−650−802).
B. Make sure that the applicable main tank does not have more than 4000 pounds
(1814 kg) of fuel.

Subtask 28−13−01−861−001
C. Connect the external AC power to the aircraft (Ref. TASK 12−00−07−861−801).
D. Push the FUEL pushbutton on the engine indication and crew alerting system (EICAS)
control panel to get the FUEL synoptic display.

3. Procedure
Subtask 28−13−01−710−002
A. If the left transfer ejector pump was replaced, do a test as follows:
(1) On the fuel synoptic display of the EICAS, make sure that the left transfer ejector
pump is shown in white.
(2) Start the left engine (Ref. TASK 71−00−00−868−806).
(3) On the fuel synoptic display, make sure that the left transfer ejector pump is shown
in green.

Master
EFFECTIVITY: See Pageblock 28−13−01 page 501
28−13−01 Page 501
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
(4) Do a shutdown of the left engine (Ref. TASK 71−00−00−868−807).
NOTE: When the fuel level in the main tank is more than 4560 ±100 pounds
(2060 ±45 kg), the fuel transfer will stop.

Subtask 28−13−01−710−003
B. If the right transfer ejector pump was replaced, do a test as follows:
(1) On the fuel synoptic display of the EICAS, make sure that the right transfer ejector
pump is shown in white.
(2) Start the right engine (Ref. TASK 71−00−00−868−806).
(3) On the fuel synoptic display, make sure that the right transfer ejector pump is
shown in green.
(4) Do a shutdown of the right engine (Ref. TASK 71−00−00−868−807).
NOTE: When the fuel level in the main tank is more than 4560 ±100 pounds
(2060 ±45 kg), the fuel transfer will stop.

Subtask 28−13−01−861−002
C. Remove the external AC power from the aircraft (Ref. TASK 12−00−07−861−802).

Master
EFFECTIVITY: See Pageblock 28−13−01 page 501
28−13−01 Page 502
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C ALL
VALVE, GRAVITY CROSSFLOW SHUTOFF − REMOVAL/INSTALLATION

1. General
A. The maintenance procedures that follow are for the removal and installation of the
gravity crossflow shutoff valve (written as the "shutoff valve" in this procedure) and the
electrical actuator of the gravity crossflow shutoff valve. There is one shutoff valve in the
fuel system. It is found in the wing box connected to the balance line manifold.
B. It is necessary to defuel the aircraft to remove or install the shutoff valve or the electrical
actuator. It is also necessary to drain and remove the fuel fumes from the center tank.

TASK 28−13−16−000−801
Removal of the Gravity Crossflow Shutoff Valve

1. Job Set−Up Information

Subtask 28−13−16−946−001
A. Reference Information
REFERENCE DESIGNATION
TASK 12−11−28−650−804 Suction Defueling
TASK 20−30−00−910−802 Wiggins Couplings − Maintenance Practices
TASK 28−00−00−910−801 Fuel Safety Precautions
TASK 28−11−00−840−801 Prepare Fuel Tank for Access
TASK 28−11−00−840−802 Removal of Fuel Fumes
TASK 28−11−01−000−801 Removal of the Honeycomb Access Panel
TASK 28−11−01−000−802 Removal of the Graphite Access Panel
TASK 53−83−01−000−801 Removal of the MLG Wheel Bin
WM 20−12−00 Wiring − Installation
WM 20−17−10 Wiring Manual

2. Job Set−Up
Subtask 28−13−16−865−001
A. Open, safety, and tag the circuit breakers that follow:
CB PANEL CB NO. NAME ZONE
CBP−1 S1 FUEL SOV R ENG 221
CBP−1 S2 FUEL SOV L ENG 221
CBP−1 S3 FUEL SOV APU 221
CBP−4 B9 GRAV XFLOW 222

Master
EFFECTIVITY: See Pageblock 28−13−16 page 401
28−13−16 Page 401
Mar 15/2005
 C
AIRCRAFT MAINTENANCE MANUAL
Subtask 28−13−16−910−001
WARNING: OBEY ALL THE FUEL SAFETY PRECAUTIONS WHEN YOU DO WORK ON THE
FUEL SYSTEM AND/OR A FUEL SYSTEM COMPONENT. IF YOU DO NOT DO
THIS, YOU CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO
EQUIPMENT.
B. Obey all the fuel safety precautions (Ref. TASK 28−00−00−910−801).

Subtask 28−13−16−650−001
C. Defuel the aircraft (Ref. TASK 12−11−28−650−804).

Subtask 28−13−16−010−001
D. Remove the left wheel bin from the main wheel well (Ref. TASK 53−83−01−000−801).
E. Remove the access panel that follows (Ref. TASK 28−11−01−000−801):
ACCESS DESIGNATION
510AB Fuel tank honeycomb
F. Remove the access panel that follows (Ref. TASK 28−11−01−000−802):
ACCESS DESIGNATION
610AB Fuel tank access panel

Subtask 28−13−16−840−001
G. Prepare the center tank for access (Ref. TASK 28−11−00−840−801).
H. Remove the fuel fumes from the center tank (Ref. TASK 28−11−00−840−802).

**ON A/C 7003−7067, 7069−7175, 7177−7183 Pre SB601R−28−031

3. Procedure
Subtask 28−13−16−030−001
Refer to Figure 401.
A. Disconnect the electrical connections (Ref. WM 20−17−10).
B. Remove the wires from the electrical conduit as follows:
CAUTION: USE TWO WRENCHES WHEN YOU REMOVE THE ELECTRICAL
CONDUIT FROM THE SOLENOID. USE ONE WRENCH TO HOLD THE
FITTING ON THE SOLENOID AND THE OTHER WRENCH TO LOOSEN
THE COUPLING NUT ON THE CONDUIT. DAMAGE TO THE
ELECTRICAL WIRES CAN OCCUR IF YOU DO NOT USE TWO
WRENCHES.
(1) Disconnect the electrical conduit (1) from the shutoff valve (2).
CAUTION: DO NOT PULL THE VALVE BODY WHEN YOU REMOVE THE WIRES
FROM THE ELECTRICAL CONDUIT. IF YOU DO THIS, YOU CAN
DAMAGE THE VALVE AND ITS SOLENOID.
(2) Remove the wires from the electrical conduit (Ref. WM 20−12−00).

Master
EFFECTIVITY: See Pageblock 28−13−16 page 401
28−13−16 Page 402
Mar 15/2005
 C
AIRCRAFT MAINTENANCE MANUAL
Subtask 28−13−16−020−001
C. Remove the shutoff valve as follows:
(1) Disconnect the couplings (3) (Ref. TASK 20−30−00−910−802).
(2) Remove the retainers (4) (Ref. TASK 20−30−00−910−802).
(3) Remove the split rings (5) and the coupling nuts (6).
CAUTION: HOLD THE SHUTOFF VALVE WHILE THE BOLTS ARE REMOVED. IF
THE SHUTOFF VALVE FALLS, IT WILL CAUSE DAMAGE TO THE
ADJACENT STRUCTURE.
(4) Remove the nuts (7), the washers (8), the bolts (9), and the shutoff valve (2).
(5) Remove the preformed packings (10) from the shutoff valve (2) and the balance line
manifold. Discard the preformed packings.
(6) Put protective plugs in the balance line manifolds.

**ON A/C 7176, 7184−7990, 8000−8064, 8066−8068 and ON A/C 7003−7067, 7069−7175,
7177−7183 Post SB601R−28−031
4. Procedure
Subtask 28−13−16−030−002
Refer to Figure 402.
A. Disconnect the electrical connections (Ref. WM 20−17−10).
B. Remove the wires from the electrical conduit as follows:
CAUTION: USE TWO WRENCHES WHEN YOU REMOVE THE ELECTRICAL
CONDUIT FROM THE SOLENOID. USE ONE WRENCH TO HOLD THE
FITTING ON THE SOLENOID AND THE OTHER WRENCH TO LOOSEN
THE COUPLING NUT ON THE CONDUIT. DAMAGE TO THE
ELECTRICAL WIRES CAN OCCUR IF YOU DO NOT USE TWO
WRENCHES.
(1) Disconnect the electrical conduit (2) from the shutoff valve (1).
CAUTION: DO NOT PULL THE VALVE BODY WHEN YOU REMOVE THE WIRES
FROM THE ELECTRICAL CONDUIT. IF YOU DO THIS, YOU CAN
DAMAGE THE VALVE AND ITS SOLENOID.
(2) Remove the wires from the electrical conduit (Ref. WM 20−12−00).

Subtask 28−13−16−020−002
C. Remove the shutoff valve as follows:
(1) Disconnect the electrical conduit (2) from the shutoff valve (1).
(2) Disconnect the electrical harness (8) from the shutoff valve (1).
(3) Disconnect the couplings (6) (Ref. TASK 20−30−00−910−802).
CAUTION: HOLD THE SHUTOFF VALVE WHILE THE BOLTS ARE REMOVED. IF
THE SHUTOFF VALVE FALLS, IT WILL CAUSE DAMAGE TO THE
ADJACENT STRUCTURE.
(4) Remove the nuts (3), the washers (4), the bolts (7), and the shutoff valve (1).

Master
EFFECTIVITY: See Pageblock 28−13−16 page 401
28−13−16 Page 403
Dec 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
(5) Remove the preformed packings (5) from the shutoff valve (1) and the balance line
manifold. Discard the preformed packings.
(6) Put protective plugs in the balance line manifolds.

Master
EFFECTIVITY: See Pageblock 28−13−16 page 401
28−13−16 Page 404
Mar 15/2005
 C
AIRCRAFT MAINTENANCE MANUAL

3
BALANCE LINE
MANIFOLD (REF)
5
10

4
10
5 LEGEND.
1. Electrical conduit.
6
2. Shutoff valve.
3. Coupling.
4. Retainer.
5. Split ring.
6. Coupling nut.
7. Nut.
BULKHEAD 8. Washer.
(REF) 9. Bolt.
10. Preformed packing.

8
7
ram2813164_001(1).dg, gg, 21/09/95

10
4
6
10 5

BALANCE LINE 5
MANIFOLD (REF)
3

Gravity Crossflow Shutoff Valve − Removal/Installation

Figure 401

Master
EFFECTIVITY: See Pageblock 28−13−16 page 401
28−13−16 Page 405
Mar 15/2005
 C
AIRCRAFT MAINTENANCE MANUAL

5
6

5
BALANCE LINE
MANIFOLD (REF)

LEGEND
1. Shutoff valve
2. Electrical conduit.
3. Nut.
4. Washer.
BULKHEAD
(REF) 5. Packing.
6. Coupling assembly
7. Bolt.

1
7

4
3
5
ram2813164_002.dg, gv/kms, 02/10/02

BALANCE LINE
MANIFOLD (REF)

Gravity Crossflow Shutoff Valve − Removal/Installation

Figure 402

Master
EFFECTIVITY: See Pageblock 28−13−16 page 401
28−13−16 Page 406
Mar 15/2005
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C ALL
TASK 28−13−16−400−801
Installation of the Gravity Crossflow Shutoff Valve

1. Job Set−Up Information

**ON A/C 7003−7067, 7069−7175, 7177−7183 Pre SB601R−28−031

Subtask 28−13−16−945−001
A. Parts
REF NAME OF PART QTY IPC SEQUENCE NO.
7 Nut 4 IPC 28−13−16−1A−020
8 Washer 4 IPC 28−13−16−1A−015
9 Bolt 4 IPC 28−13−16−1A−010
10 Preformed packing 4 IPC 28−13−00−4A−095

**ON A/C 7176, 7184−7990, 8000−8064, 8066−8068 and ON A/C 7003−7067, 7069−7175,
7177−7183 Post SB601R−28−031

Subtask 28−13−16−945−002
B. Parts
REF NAME OF PART QTY IPC SEQUENCE NO.
7 Nut 4 IPC 28−13−16−1A−020
8 Washer 4 IPC 28−13−16−1A−015
9 Bolt 4 IPC 28−13−16−1A−010
10 Preformed packing 4 IPC 28−13−00−4A−096

**ON A/C ALL

Subtask 28−13−16−640−001
C. Consumable Materials
REFERENCE DESIGNATION
06−002 Petrolatum

Subtask 28−13−16−946−002
D. Reference Information
REFERENCE DESIGNATION
TASK 20−30−00−910−802 Wiggins Couplings − Maintenance Practices
TASK 28−11−01−400−801 Installation of the Honeycomb Access Panel
TASK 28−11−01−400−802 Installation of the Graphite Access Panel
TASK 28−13−16−710−801 Operational Test of the Gravity Crossflow Shutoff
Valve

Master
EFFECTIVITY: See Pageblock 28−13−16 page 401
28−13−16 Page 407
Dec 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL

REFERENCE DESIGNATION
TASK 51−80−00−100−802 Preparation of Bonding Surfaces
TASK 51−80−00−760−803 Electrical Bonding Test
TASK 53−83−01−400−801 Installation of the MLG Wheel Bin
WM 20−12−00 Wiring − Installation
WM 20−17−10 Wiring Manual

**ON A/C 7003−7067, 7069−7175, 7177−7183 Pre SB601R−28−031

2. Procedure
Subtask 28−13−16−869−001
A. Make sure that the aircraft is in the same configuration as in the removal task.

Subtask 28−13−16−420−001
Refer to Figure 401.
B. Install the shutoff valve as follows:
(1) Prepare the mating surfaces of the bolts (9), the shutoff valve (2), and the bulkhead
for electrical bonding (Ref. TASK 51−80−00−100−802).
(2) Install the shutoff valve (2), the bolts (9), the washers (8), and the nuts (7).
(3) Install the coupling nuts (6) and the split rings (5) on the shutoff valve (2).
(4) Do the electrical bonding test on the coupling nuts (6) (Ref. TASK
51−80−00−760−803).
(5) Remove the protective caps from the balance line manifolds.
(6) Lubricate the preformed packings (10) with petrolatum. Install the preformed
packings (10) and the retainers (4).
(7) Connect the couplings (3) (Ref. TASK 20−30−00−910−802).

Subtask 28−13−16−430−001
C. Install the wires in the electrical conduit as follows:
(1) Install the wires in the electrical conduit (Ref. WM 20−12−00).
CAUTION: USE TWO WRENCHES WHEN YOU TIGHTEN THE ELECTRICAL
CONDUIT TO THE SOLENOID. USE ONE WRENCH TO HOLD THE
FITTING ON THE SOLENOID AND THE OTHER WRENCH TO
TIGHTEN THE COUPLING NUT ON THE CONDUIT. DAMAGE TO THE
ELECTRICAL WIRES CAN OCCUR IF YOU DO NOT USE TWO
WRENCHES.
(2) Connect the conduit (1) to the shutoff valve (2).
D. Connect the electrical connections to the valve which is located at BL 0.00 (Ref. WM
20−17−10).

Master
EFFECTIVITY: See Pageblock 28−13−16 page 401
28−13−16 Page 408
Mar 15/2005
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C 7176, 7184−7990, 8000−8064, 8066−8068 and ON A/C 7003−7067, 7069−7175,
7177−7183 Post SB601R−28−031
3. Procedure
Subtask 28−13−16−869−002
A. Make sure that the aircraft is in the same configuration as in the removal task.

Subtask 28−13−16−420−002
Refer to Figure 402.
B. Install the shutoff valve as follows:
(1) Prepare the mating surfaces of the bolts (7), the shutoff valve (1), and the bulkhead
for electrical bonding (Ref. TASK 51−80−00−100−802).
(2) Install the shutoff valve (1), the bolts (7), the washers (4), and the nuts (3).
(3) Remove the protective caps from the balance line manifolds.
(4) Lubricate the preformed packings (5) with petrolatum.
(5) Install the preformed packings (5) on the flanges of the shutoff valve (1) and the
balance line manifolds.
(6) Install the coupling (6) over the packings (5) (Ref. TASK 20−30−00−910−802).
NOTE: When all three pawls are engaged the coupling locks.
(7) Do the electrical bonding test on the coupling assembly (6) (Ref. TASK
51−80−00−760−803).

Subtask 28−13−16−430−002
C. Install the wires in the electrical conduit as follows:
(1) Install the wires in the electrical conduit (Ref. WM 20−12−00).
CAUTION: USE TWO WRENCHES WHEN YOU TIGHTEN THE ELECTRICAL
CONDUIT TO THE SOLENOID. USE ONE WRENCH TO HOLD THE
FITTING ON THE SOLENOID AND THE OTHER WRENCH TO
TIGHTEN THE COUPLING NUT ON THE CONDUIT. DAMAGE TO THE
ELECTRICAL WIRES CAN OCCUR IF YOU DO NOT USE TWO
WRENCHES.
(2) Connect the conduit (2) to the shutoff valve (1).
D. Connect the electrical connections to the valve which is located at BL 0.00 (Ref. WM
20−17−10).
**ON A/C ALL

4. Close Out
Subtask 28−13−16−410−001
A. Install the access panel that follows (Ref. TASK 28−11−01−400−801):

Master
EFFECTIVITY: See Pageblock 28−13−16 page 401
28−13−16 Page 409
Dec 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL

ACCESS DESIGNATION
510AB Fuel tank access panel
B. Install the access panel that follows (Ref. TASK 28−11−01−400−802):
ACCESS DESIGNATION
610AB Fuel tank access panel

Subtask 28−13−16−710−001
C. Do an operational test of the shutoff valve (Ref. TASK 28−13−16−710−801).

Subtask 28−13−16−410−002
D. Install the right wheel bin in the main wheel well (Ref. TASK 53−83−01−400−801).

Subtask 28−13−16−865−005
E. Make sure that the circuit breakers that follow are closed:
CB PANEL CB NO. NAME ZONE
CBP−1 S1 FUEL SOV R ENG 221
CBP−1 S2 FUEL SOV L ENG 221
CBP−1 S3 FUEL SOV APU 221
CBP−4 B9 GRAV XFLOW 222

Master
EFFECTIVITY: See Pageblock 28−13−16 page 401
28−13−16 Page 410
Mar 15/2005
 C
AIRCRAFT MAINTENANCE MANUAL
TASK 28−13−16−000−802
Removal of the Gravity Crossflow Shutoff Valve Electrical Actuator.

1. Job Set−Up Information

Subtask 28−13−16−946−004
A. Reference Information
REFERENCE DESIGNATION
TASK 12−11−28−650−804 Suction Defueling
TASK 28−00−00−910−801 Fuel Safety Precautions
TASK 28−11−00−840−801 Prepare Fuel Tank for Access
TASK 28−11−00−840−802 Removal of Fuel Fumes
TASK 28−11−01−000−801 Removal of the Honeycomb Access Panel
TASK 28−11−01−000−802 Removal of the Graphite Access Panel
TASK 53−83−01−000−801 Removal of the MLG Wheel Bin
WM 20−12−00 Wiring − Installation
WM 20−17−10 Wiring Manual

2. Job Set−Up
Subtask 28−13−16−865−002
A. Open, safety, and tag the circuit breakers that follow:
CB PANEL CB NO. NAME ZONE
CBP−1 S1 FUEL SOV R ENG 221
CBP−1 S2 FUEL SOV L ENG 221
CBP−1 S3 FUEL SOV APU 221
CBP−4 B9 GRAV XFLOW 222

Subtask 28−13−16−910−002
WARNING: OBEY ALL THE FUEL SAFETY PRECAUTIONS WHEN YOU DO WORK ON THE
FUEL SYSTEM AND/OR A FUEL SYSTEM COMPONENT. IF YOU DO NOT DO
THIS, YOU CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO
EQUIPMENT.
B. Obey all the fuel safety precautions (Ref. TASK 28−00−00−910−801).

Subtask 28−13−16−650−002
C. Defuel the aircraft (Ref. TASK 12−11−28−650−804).

Subtask 28−13−16−010−002
D. Remove the left wheel bin from the main wheel well (Ref. TASK 53−83−01−000−801).
E. Remove the access panel that follows (Ref. TASK 28−11−01−000−801):

Master
EFFECTIVITY: See Pageblock 28−13−16 page 401
28−13−16 Page 411
Mar 15/2005
 C
AIRCRAFT MAINTENANCE MANUAL

ACCESS DESIGNATION
510AB Fuel tank honeycomb
F. Remove the access panel that follows (Ref. TASK 28−11−01−000−802):
ACCESS DESIGNATION
610AB Fuel tank access panel

Subtask 28−13−16−840−002
G. Prepare the center tank for access (Ref. TASK 28−11−00−840−801).
H. Remove the fuel fumes from the center tank (Ref. TASK 28−11−00−840−802).

3. Procedure
Refer to Figure 403
Subtask 28−13−16−030−003
A. Disconnect the electrical connections (Ref: WM 20−17−10).
B. Remove the wires from the electrical conduit as follows:
CAUTION: USE TWO WRENCHES WHEN YOU REMOVE THE ELECTRICAL
CONDUIT FROM THE SOLENOID. USE ONE WRENCH TO HOLD THE
FITTING ON THE SOLENOID AND THE OTHER WRENCH TO LOOSEN
THE COUPLING NUT ON THE CONDUIT. DAMAGE TO THE
ELECTRICAL WIRES CAN OCCUR IF YOU DO NOT USE TWO
WRENCHES.
(1) Disconnect the electrical conduit (1) from the electrical actuator (2).
CAUTION: DO NOT PULL THE VALVE BODY WHEN YOU REMOVE THE WIRES
FROM THE ELECTRICAL CONDUIT. IF YOU DO THIS, YOU CAN
DAMAGE THE VALVE AND ITS SOLENOID.
(2) Remove the wires from the electrical conduit (Ref: WM 20−12−10).

Subtask 28−13−16−020−004
C. Remove the electrical actuator (2) as follows:
(1) Remove the screws (5) and the washers (6) from the half−clamps (4).
(2) Remove the half−clamps (4) from the electrical actuator (2).
(3) Remove the electrical actuator (2).

Master
EFFECTIVITY: See Pageblock 28−13−16 page 401
28−13−16 Page 412
Mar 15/2005
 C
AIRCRAFT MAINTENANCE MANUAL

LEGEND
1. Electrical conduit.
2. Electrical actuator.
3. Valve body.
4. Half−clamp.
A 5. Screw.
BULKHEAD 6. Washer.
(REF) BALANCE
LINE MANIFOLD
(REF)

BALANCE
LINE MANIFOLD 1
(REF)
ram2813164_003.dg, lr/rm, 29/10/04

Gravity Crossflow Shutoff Valve Electrical Actuator − Removal/Installation

Figure 403

Master
EFFECTIVITY: See Pageblock 28−13−16 page 401
28−13−16 Page 413
Mar 15/2005
 C
AIRCRAFT MAINTENANCE MANUAL
TASK 28−13−16−400−802
Installation of the Gravity Crossflow Shutoff Valve Electrical Actuator

1. Job Set−Up Information

Subtask 28−13−16−944−002
A. Consumable Materials
REFERENCE DESIGNATION
08−001A Sealing Compound, threadlocking, low strength,
anaerobic, single compound, (Locktite 221)

Subtask 28−13−16−945−003
B. Parts
REF NAME OF PART QTY IPC SEQUENCE NO.
4 Half−Clamp 2 IPC 28−13−16−1A−020
5 Screw 2 IPC 28−13−16−1A−015
6 Washer 2 IPC 28−13−16−1A−010

Subtask 28−13−16−946−005
C. Reference Information
REFERENCE DESIGNATION
TASK 28−11−01−400−801 Installation of the Honeycomb Access Panel
TASK 28−11−01−400−802 Installation of the Graphite Access Panel
TASK 28−13−16−710−801 Operational Test of the Gravity Crossflow Shutoff
Valve
TASK 53−83−01−400−801 Installation of the MLG Wheel Bin
WM 20−12−00 Wiring − Installation
WM 20−17−10 Wiring Manual

2. Job Set Up
Subtask 28−13−16−869−003
A. Make sure that the aircraft is in the same configuration as in the removal task.

3. Procedure
Refer to Figure 403
Subtask 28−13−16−420−003
A. Install the shutoff valve electrical actuator (2) to the valve body (3) as follows:
(1) Make sure that the key slot on the control shaft is correctly aligned with the key that
is inside the electrical actuator. Both must be in the fully opened or fully closed
position.

Master
EFFECTIVITY: See Pageblock 28−13−16 page 401
28−13−16 Page 414
Mar 15/2005
 C
AIRCRAFT MAINTENANCE MANUAL
(2) Put the electrical actuator (2) in position on the valve body (3).
(3) Make sure that the pin on the flange of the valve body (3) is correctly aligned with
the hole in the flange of the electrical actuator (2).
(4) Install the two half−clamps (4).
(5) Apply a layer of 08−001A threadlock compound to the threads of the screws (5).
(6) Install the screws (5) and the washers (6).
(7) Tighten the screws (5).
NOTE: Make sure the space between the two half−clamps is the same on both
sides.

Subtask 28−13−16−430−003
B. Install the wires in the electrical conduit (1) as follows:
(1) Install the wires in the electrical conduit (1) (Ref: WM 20−12−00).
CAUTION: USE TWO WRENCHES WHEN YOU TIGHTEN THE ELECTRICAL
CONDUIT TO THE SOLENOID. USE ONE WRENCH TO HOLD THE
FITTING ON THE SOLENOID AND THE OTHER WRENCH TO
TIGHTEN THE COUPLING NUT ON THE CONDUIT. DAMAGE TO THE
ELECTRICAL WIRES CAN OCCUR IF YOU DO NOT USE TWO
WRENCHES.
(2) Connect the electrical conduit (1) to the electrical actuator (2).
(3) Connect the electrical connections to the valve which is located at BL 0.00 (Ref:
WM 20−17−10).

4. Close Out
Subtask 28−13−16−410−003
A. Install the access panel that follows (Ref. TASK 28−11−01−400−801):
ACCESS DESIGNATION
510AB Fuel tank access panel
B. Install the access panel that follows (Ref. TASK 28−11−01−400−802):
ACCESS DESIGNATION
610AB Fuel tank access panel

Subtask 28−13−16−710−003
C. Do an operational test of the shutoff valve (Ref. TASK 28−13−16−710−801).

Subtask 28−13−16−410−004
D. Install the right wheel bin in the main wheel well (Ref. TASK 53−83−01−400−801).

Master
EFFECTIVITY: See Pageblock 28−13−16 page 401
28−13−16 Page 415
Mar 15/2005
 C
AIRCRAFT MAINTENANCE MANUAL
Subtask 28−13−16−865−006
E. Make sure that the circuit breakers that follow are closed:
CB PANEL CB NO. NAME ZONE
CBP−1 S1 FUEL SOV R ENG 221
CBP−1 S2 FUEL SOV L ENG 221
CBP−1 S3 FUEL SOV APU 221
CBP−4 B9 GRAV XFLOW 222

Master
EFFECTIVITY: See Pageblock 28−13−16 page 401
28−13−16 Page 416
Mar 15/2005
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C ALL
VALVE, GRAVITY CROSSFLOW SHUTOFF − ADJUSTMENT/TEST

1. General
A. The maintenance procedure that follows is for the test of the gravity crossflow shutoff
valve (written as the "shutoff valve" in this procedure).

TASK 28−13−16−710−801
Operational Test of the Gravity Crossflow Shutoff Valve

1. Job Set−Up Information

Subtask 28−13−16−946−003
A. Reference Information
REFERENCE DESIGNATION
TASK 12−00−07−861−801 Connect External AC Power
TASK 12−00−07−861−802 Remove External AC Power

2. Job Set−Up
Subtask 28−13−16−865−003
A. Make sure that the circuit breakers that follow are closed:
CB PANEL CB NO. NAME ZONE
CBP−1 M12 FUEL SYST CONT 221
CBP−4 B9 GRAV XFLOW 222
CBP−4 B10 FUEL SYST CONT 222

Subtask 28−13−16−861−001
B. Connect the external AC power to the aircraft (Ref. TASK 12−00−07−861−801).
C. Push the FUEL pushbutton on the engine indication and crew alerting system (EICAS)
control panel to get the fuel synoptic display.

3. Procedure
Subtask 28−13−16−710−002
A. Do a test of the shutoff valve as follows:
(1) On the fuel synoptic display of the EICAS, make sure that the shutoff valve is
shown in white and in the closed position.
NOTE: Make sure the aircraft has fuel in one or both tanks with an imbalance, or
enough fuel to have a transfer. The suggested amount is 500 lb.
(2) At the FUEL control panel, push the GRAVITY XFLOW switch/light. Make sure that
the OPEN light comes on and that the FAIL light does not come on.

Master
EFFECTIVITY: See Pageblock 28−13−16 page 501
28−13−16 Page 501
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
(3) On the fuel synoptic display, make sure that the shutoff valve is shown in green and
in the open position.
NOTE: Make sure the fuel quantity increases in one tank, and decreases in the
other.
(4) At the FUEL control panel, push the GRAVITY XFLOW switch/light. Make sure that
the OPEN light goes off.

Subtask 28−13−16−861−002
B. Remove the external AC power from the aircraft (Ref. TASK 12−00−07−861−802).

Master
EFFECTIVITY: See Pageblock 28−13−16 page 501
28−13−16 Page 502
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C ALL
CHECK VALVE, CROSSFLOW − REMOVAL/INSTALLATION

1. General
A. The maintenance procedures that follow are for the removal and installation of the
crossflow check valve. There are two crossflow check valves in the fuel system. They
are found in the center wing box connected to the auxiliary power unit (APU) crossflow
feed lines.
B. It is necessary to defuel the aircraft, and drain and remove the fuel fumes from the
center tank to remove or install the crossflow check valve.

TASK 28−13−19−000−801
Removal of the Crossflow Check Valve

1. Job Set−Up Information

Subtask 28−13−19−946−001
A. Reference Information
REFERENCE DESIGNATION
TASK 12−11−28−650−804 Suction Defueling
TASK 28−00−00−910−801 Fuel Safety Precautions
TASK 28−11−00−840−801 Prepare Fuel Tank for Access
TASK 28−11−00−840−802 Removal of Fuel Fumes
TASK 28−11−01−000−801 Removal of the Honeycomb Access Panel
TASK 28−11−01−000−802 Removal of the Graphite Access Panel

2. Job Set−Up
Subtask 28−13−19−910−001
WARNING: OBEY ALL THE FUEL SAFETY PRECAUTIONS WHEN YOU DO WORK ON THE
FUEL SYSTEM AND/OR A FUEL SYSTEM COMPONENT. IF YOU DO NOT DO
THIS, YOU CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO
EQUIPMENT.
A. Obey all the fuel safety precautions (Ref. TASK 28−00−00−910−801).

Subtask 28−13−19−650−001
B. Defuel the aircraft (Ref. TASK 12−11−28−650−804).

Subtask 28−13−19−010−001
C. To remove the left crossflow check valve, remove the access panel that follows (Ref.
TASK 28−11−01−000−801).

Master
EFFECTIVITY: See Pageblock 28−13−19 page 401
28−13−19 Page 401
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

ACCESS DESIGNATION
510AB Fuel tank access panel
D. To remove the right crossflow check valve, remove the access panel that follows (Ref.
TASK 28−11−01−000−802):
ACCESS DESIGNATION
610AB Fuel tank access panel

Subtask 28−13−19−840−001
E. Prepare the center tank for access (Ref. TASK 28−11−00−840−801).
F. Remove the fuel fumes from the center tank (Ref. TASK 28−11−00−840−802).

3. Procedure
Subtask 28−13−19−020−001
Refer to Figure 401.
A. Remove the crossflow check valve as follows:
(1) Hold the check valve and loosen the jamnut (10).
(2) Remove the screw (3) and the washer (4) from the clamp (5). Remove the clamp.
(3) Disconnect the check valve (6) from the fuel line (2).
(4) Disconnect the check valve (6) from the adaptor (7).
(5) Remove the retainer (9) and the preformed packing (8). Discard the preformed
packing.
(6) Put protective plugs in the fuel line (2) and the adaptor (7).

Master
EFFECTIVITY: See Pageblock 28−13−19 page 401
28−13−19 Page 402
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

LEGEND
1. Fuel line.
2. Fuel line.
3. Screw.
4. Washer.
5. Tube clamp.
6. Check valve.
7. Adaptor.
8. Preformed packing.
9. Retainer.
10. Jam nut.
11. Reducer tee.

11
3

5
2

8
9
10
7
1

NOTE
ram2813194_001.dg, pt/om, 16/05/03

Left hand side is shown

Right hand side is opposite.

Crossflow Check Valve − Removal/Installation

Figure 401

Master
EFFECTIVITY: See Pageblock 28−13−19 page 401
28−13−19 Page 403
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
TASK 28−13−19−400−801
Installation of the Crossflow Check Valve

1. Job Set−Up Information

Subtask 28−13−19−945−001
A. Parts
REF NAME OF PART QTY IPC SEQUENCE NO.
8 Preformed packing 1 IPC 28−24−00−01−215

Subtask 28−13−19−946−002
B. Reference Information
REFERENCE DESIGNATION
TASK 28−11−01−400−801 Installation of the Honeycomb Access Panel
TASK 28−11−01−400−802 Installation of the Graphite Access Panel

2. Procedure
Subtask 28−13−19−869−001
A. Make sure that the aircraft is in the same configuration as in the removal task.

Subtask 28−13−19−420−001
Refer to Figure 401.
B. Install the crossflow check valve as follows:
(1) Remove the protective plugs from the fuel lines (2) and the adaptor (7).
(2) Lubricate the preformed packing (8).
(3) Install the preformed packing (8) and the retainer (9) on the check valve (6).
(4) Connect the check valve (6) to the adaptor (7).
NOTE: Make sure the arrow on the crossflow check valve points inboard.
(5) Connect the fuel line (2) to the check valve (6).
(6) Attach the clamp (5) with the screw (3) and the washer (4).
(7) Hold the check valve and tighten the jamnut (10).

3. Close Out
Subtask 28−13−19−410−001
A. If the left crossflow check valve was replaced, install the access panel that follows
(Ref.TASK 28−11−01−400−801):

Master
EFFECTIVITY: See Pageblock 28−13−19 page 401
28−13−19 Page 404
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

ACCESS DESCRIPTION
510AB Fuel tank access panel
B. If the right crossflow check valve was replaced, install the access panel that follows (Ref.
TASK 28−11−01−400−802):
ACCESS DESCRIPTION
610AB Fuel tank access panel

Subtask 28−13−19−941−001
C. Remove all tools, equipment, and unwanted materials from the work area.

Master
EFFECTIVITY: See Pageblock 28−13−19 page 401
28−13−19 Page 405
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C ALL
PUMP, AFT SCAVENGE EJECTOR − REMOVAL/INSTALLATION

1. General
A. The maintenance procedures that follow are for the removal and installation of the aft
scavenge ejector pump (written as the "scavenge ejector" in this procedure). There are
two scavenge ejectors in the fuel system. There is one scavenge ejector found in each
inboard end of the main tanks. The scavenge ejectors are connected to the
collector−tank fill lines.
B. It is necessary to defuel, drain, and remove the fuel fumes from the related main fuel
tank to remove or install the scavenge ejector.

TASK 28−13−22−000−801
Removal of the Aft Scavenge Ejector Pump

1. Job Set−Up Information

Subtask 28−13−22−943−001
A. Tools and Equipment
REFERENCE DESIGNATION
None specified Scraper, nonmetallic

Subtask 28−13−22−946−001
B. Reference Information
REFERENCE DESIGNATION
TASK 12−11−28−650−804 Suction Defueling
TASK 20−30−00−910−802 Wiggins Couplings − Maintenance Practices
TASK 28−00−00−910−801 Fuel Safety Precautions
TASK 28−11−00−840−801 Prepare Fuel Tank for Access
TASK 28−11−00−840−802 Removal of Fuel Fumes
TASK 28−11−01−000−802 Removal of the Graphite Access Panel

2. Job Set−Up
Subtask 28−13−22−910−001
WARNING: OBEY ALL THE FUEL SAFETY PRECAUTIONS WHEN YOU DO WORK ON THE
FUEL SYSTEM AND/OR A FUEL SYSTEM COMPONENT. IF YOU DO NOT DO
THIS, YOU CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO
EQUIPMENT.
A. Obey all the fuel safety precautions (Ref. TASK 28−00−00−910−801).

Master
EFFECTIVITY: See Pageblock 28−13−22 page 401
28−13−22 Page 401
Sep 10/2004
 C
AIRCRAFT MAINTENANCE MANUAL
Subtask 28−13−22−650−001
B. Defuel the applicable main tank (Ref. TASK 12−11−28−650−804).

Subtask 28−13−22−010−001
C. Remove the applicable access panel that follows (Ref. TASK 28−11−01−000−802:
ACCESS DESCRIPTION
540AB Fuel tank access panel
640AB Fuel tank access panel

Subtask 28−13−22−840−001
D. Prepare the applicable main tank for access (Ref. TASK 28−11−00−840−801).
E. Remove the fuel fumes from the applicable main tank (Ref. TASK 28−11−00−840−802).

3. Procedure
Subtask 28−13−22−020−001
Refer to Figure 401.
A. Remove the scavenge ejector as follows:
(1) Disconnect the vent line (1) from the scavenge ejector (2). Put a protective plug in
the vent line.
(2) Disconnect the motive line (3) from the scavenge ejector (2). Put a protective plug
in the motive line.
(3) Remove the coupling (4) (Ref. TASK 20−30−00−910−802).
(4) Remove the screws (5), the washers (6), the scavenge ejector (2), and the shim (7).
(5) Remove the sleeve (8) and the preformed packings (9). Discard the preformed
packings.
(6) Put a protective plug in the scavenge manifold.

Master
EFFECTIVITY: See Pageblock 28−13−22 page 401
28−13−22 Page 402
Sep 10/2004
 C
AIRCRAFT MAINTENANCE MANUAL

NOTE
Right side is shown.
Left side is opposite.

BOTTOM TUBE OF
SCAVENGE EJECTOR

0.25 TO 0.30 INCH GAP 4 SCAVENGE

(6.35 TO 7.62 mm GAP) MANIFOLD
8 (REF)
WING PLANK

1 9

LEGEND. 2
1. Vent line.
2. Scavenge ejector. 5
3. Motive line. 6
4. Coupling.
5. Screw. 3 7
6. Washer.
7. Shim.
8. Sleeve.
9. Preformed packing.

ram2813224_001(1).dc, ks, 15/12/92

Aft Scavenge Ejector Pump − Removal/Installation

Figure 401

Master
EFFECTIVITY: See Pageblock 28−13−22 page 401
28−13−22 Page 403
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
TASK 28−13−22−400−801
Installation of the Aft Scavenge Ejector Pump

1. Job Set−Up Information

Subtask 28−13−22−944−001
A. Consumable Materials
REFERENCE DESIGNATION
Petrolatum None specified

Subtask 28−13−22−945−001
B. Parts
REF NAME OF PART QTY IPC SEQUENCE NO.
5 Screw 4 IPC 28−13−22−1A−010
6 Washer 4 IPC 28−13−22−1A−015
7 Shim AR IPC 28−13−22−1A−020
9 Preformed packing 2 IPC 28−13−00−3A−008

Subtask 28−13−22−946−002
C. Reference Information
REFERENCE DESIGNATION
TASK 20−30−00−910−802 Wiggins Couplings − Maintenance Practices
TASK 28−11−01−400−802 Installation of the Graphite Access Panel
TASK 28−13−22−710−801 Operational Test of the Aft Scavenge Ejector
Pump
TASK 51−23−00−390−804 Bead Seal Sealant Procedure
TASK 51−23−00−390−808 Application of Sealant with Brush
TASK 51−80−00−100−802 Preparation of Bonding Surfaces
TASK 51−80−00−760−803 Electrical Bonding Test

2. Procedure
Subtask 28−13−22−869−001
A. Make sure that the aircraft is in the same configuration as in the removal task.

Subtask 28−13−22−420−001
Refer to Figure 401.
B. Install the scavenge ejector as follows:
(1) Remove the protective plug from the scavenge manifold.
(2) Install the shim (7) and the scavenge ejector (2).

Master
EFFECTIVITY: See Pageblock 28−13−22 page 401
28−13−22 Page 404
Aug 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
(3) Measure the clearance between the bottom tube of the scavenge ejector (2) and
the wing plank. Make sure that the clearance is 0.25−0.30 inch (6.35−7.62 mm).
NOTE: If the clearance is not correct, the scavenge ejector will not operate
correctly.
(4) Remove or install more shims (7) as necessary to correct the clearance between
the bottom tube of the scavenge ejector (2) and the wing plank.
(5) Lubricate the preformed packings (9) with petrolatum and install the preformed
packings (9) on the scavenge manifold and the scavenge ejector (2).
(6) Connect the scavenge manifold to the scavenge ejector (2) with the sleeve (8).
(7) Install the coupling (4) (Ref. TASK 20−30−00−910−802).
(8) Do the electrical bonding test on the coupling (4) (Ref. TASK 51−80−00−760−803).
(9) Install the washers (6) and the screws (5).
(10) Do an electrical bonding test of the scavenge ejector (2) (Ref. TASK
51−80−00−760−803).
(11) Apply a brushcoat of sealant to the screws (5) and washers (6).
(12) Apply a bead of sealant around the scavenge ejector (2).
(13) Remove the protective plug from the motive line (3). Connect the motive line to the
scavenge ejector (2).
(14) Remove the protective plug from the vent line (1). Connect the vent line to the
scavenge ejector (2).

3. Close Out
Subtask 28−13−22−410−001
A. Install the applicable access panel that follows (Ref. TASK 28−11−01−400−802):
ACCESS DESCRIPTION
540AB Fuel tank access panel
640AB Fuel tank access panel

Subtask 28−13−22−710−001
B. Do an operational test of the scavenge ejector (Ref. TASK 28−13−22−710−801).

Subtask 28−13−22−941−001
C. Remove all the tools, equipment, and unwanted materials from the area.

Master
EFFECTIVITY: See Pageblock 28−13−22 page 401
28−13−22 Page 405
Aug 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C ALL
PUMP, AFT SCAVENGE EJECTOR − ADJUSTMENT/TEST

1. General
A. The maintenance procedure that follows is for the test of the aft scavenge ejector pump
(written as the "scavenge ejector" in this procedure).

TASK 28−13−22−710−801
Operational Test of the Aft Scavenge Ejector Pump

1. Job Set−Up Information

Subtask 28−13−22−946−003
A. Reference Information
REFERENCE DESIGNATION
TASK 12−00−07−861−801 Connect External AC Power
TASK 12−00−07−861−802 Remove External AC Power
TASK 12−11−28−650−802 Manual Pressure Refueling
TASK 71−00−00−868−806 Engine Start
TASK 71−00−00−868−807 Engine Shutdown (Normal)

2. Job Set−Up
Subtask 28−13−22−650−002
A. Refuel the applicable main tank (Ref. TASK 12−11−28−650−802).

Subtask 28−13−22−861−001
B. Connect the external AC power to the aircraft (Ref. TASK 12−00−07−861−801).
C. Push the FUEL pushbutton on the engine indication and crew alerting system (EICAS)
control panel to get the FUEL synoptic display.

3. Procedure
Subtask 28−13−22−710−002
A. If the left scavenge ejector was replaced, do a test as follows:
(1) On the fuel synoptic display of the EICAS, make sure that the left scavenge ejector
is shown in white.
(2) Start the left engine (Ref. TASK 71−00−00−868−806).
(3) On the fuel synoptic display, make sure that the left scavenge ejector is shown in
green.
(4) Do a shutdown of the left engine (Ref. TASK 71−00−00−868−807).

Master
EFFECTIVITY: See Pageblock 28−13−22 page 501
28−13−22 Page 501
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
Subtask 28−13−22−710−003
B. If the right scavenge ejector was replaced, do a test as follows:
(1) On the fuel synoptic display of the EICAS, make sure that the right scavenge
ejector is shown in white.
(2) Start the right engine (Ref. TASK 71−00−00−868−806).
(3) On the fuel synoptic display, make sure that the right scavenge ejector is shown in
green.
(4) Do a shutdown of the right engine (Ref. TASK 71−00−00−868−807.

Subtask 28−13−22−861−002
C. Remove the external AC power from the aircraft (Ref. TASK 12−00−07−861−802).

Master
EFFECTIVITY: See Pageblock 28−13−22 page 501
28−13−22 Page 502
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C ALL
MANIFOLD, GRAVITY FEED − REMOVAL/INSTALLATION

1. General
A. The maintenance procedures that follow are for the removal and installation of the
gravity feed manifold which contains the gravity−feed check valve. There are two gravity
feed manifolds in the fuel system. There is one gravity feed manifold connected between
each collector tank and the related main tank bulkhead.
B. It is necessary to defuel the aircraft, and drain and remove the fuel fumes from the
center tank to remove or install the gravity feed manifold.

TASK 28−13−28−000−801
Removal of the Gravity Feed Manifold

1. Job Set−Up Information

Subtask 28−13−28−946−001
A. Reference Information
REFERENCE DESIGNATION
TASK 12−11−28−650−804 Suction Defueling
TASK 20−30−00−910−802 Wiggins Couplings − Maintenance Practices
TASK 28−00−00−910−801 Fuel Safety Precautions
TASK 28−11−00−840−801 Prepare Fuel Tank for Access
TASK 28−11−00−840−802 Removal of Fuel Fumes
TASK 28−11−01−000−801 Removal of the Honeycomb Access Panel
TASK 28−11−01−000−802 Removal of the Graphite Access Panel

2. Job Set−Up
Subtask 28−13−28−910−001
WARNING: OBEY ALL THE FUEL SAFETY PRECAUTIONS WHEN YOU DO WORK ON THE
FUEL SYSTEM AND/OR A FUEL SYSTEM COMPONENT. IF YOU DO NOT DO
THIS, YOU CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO
EQUIPMENT.
A. Obey all the fuel safety precautions (Ref. TASK 28−00−00−910−801).

Subtask 28−13−28−650−001
B. Defuel the aircraft (Ref. TASK 12−11−28−650−804).

Subtask 28−13−28−010−001
C. To remove the left gravity feed manifold, remove the access panel that follows (Ref.
TASK 28−11−01−000−801):

Master
EFFECTIVITY: See Pageblock 28−13−28 page 401
28−13−28 Page 401
Sep 10/2004
 C
AIRCRAFT MAINTENANCE MANUAL

ACCESS DESCRIPTION
510AB Fuel tank access panel
D. To remove the right gravity feed manifold, remove the access panel that follows (Ref.
TASK 28−11−01−000−802):
ACCESS DESCRIPTION
610AB Fuel tank access panel

Subtask 28−13−28−840−001
E. Prepare the center tank for access (Ref. TASK 28−11−00−840−801.
F. Remove the fuel fumes from the center tank (Ref. TASK 28−11−00−840−802).

3. Procedure
Subtask 28−13−28−020−001
Refer to Figure 401.
A. Remove the gravity feed manifold as follows:
(1) Disconnect the venturi tube (1) from the gravity feed manifold (2). Put a protective
plug in the venturi tube.
(2) Disconnect the couplings (3) and remove the retainers (4) (Ref. TASK
20−30−00−910−802).
(3) Remove the preformed packings (5) and (6) from the gravity feed manifold (2), the
gravity crossflow manifold, the collector tank fitting, and the main tank fitting.
Discard the preformed packings.
(4) Remove the gravity feed manifold (2). Put protective plugs in the gravity crossflow
manifold, the collector tank fitting, and the main tank fitting.
(5) Remove the split rings (7) and the couplings (3) from the gravity feed manifold (2).

Master
EFFECTIVITY: See Pageblock 28−13−28 page 401
28−13−28 Page 402
Sep 10/2004
 C
AIRCRAFT MAINTENANCE MANUAL

LEGEND
1. Venturi tube.
2. Gravity feed manifold.
3. Coupling.
4. Retainer.
5. Preformed packing.
6. Preformed packing.
7. Split ring.
8. Gravity feed check valve.

COLLECTOR
TANK FITTING
(REF)

1
3
7
2
6
4
8
6
3
P
D
TO

FW

3
3
GRAVITY
7 7
CROSSFLOW
MANIFOLD
ram2813284_001(2).dc, rs/kms, 4/06/95

(REF) 5
4
4

5
NOTE 3
Right side is shown. 3 MAIN TANK
Left side is the opposite. FITTING
(REF)

Gravity Feed Manifold − Removal/Installation

Figure 401

Master
EFFECTIVITY: See Pageblock 28−13−28 page 401
28−13−28 Page 403
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
TASK 28−13−28−400−801
Installation of the Gravity Feed Manifold

1. Job Set−Up Information

Subtask 28−13−28−945−001
A. Parts
REF NAME OF PART QTY IPC SEQUENCE NO.
5 Preformed packing 4 IPC 28−13−00−4A−095
6 Preformed packing 2 IPC 28−13−00−4A−085

Subtask 28−13−28−946−002
B. Reference Information
REFERENCE DESIGNATION
TASK 20−30−00−910−802 Wiggins Couplings − Maintenance Practices
TASK 28−11−01−400−801 Installation of the Honeycomb Access Panel
TASK 28−11−01−400−802 Installation of the Graphite Access Panel

2. Procedure
Subtask 28−13−28−869−001
A. Make sure that the aircraft is in the same configuration as in the removal task.

Subtask 28−13−28−420−001
Refer to Figure 401.
B. Install the gravity feed manifold as follows:
(1) Install the couplings (3) and the split rings (7) on the gravity feed manifold (2) (Ref.
TASK 20−30−00−910−802).
(2) Remove the protective plugs from the collector tank fitting, the main tank fitting, and
the gravity crossflow manifold.
(3) Lubricate the preformed packings (5) and (6) with petrolatum and install the
preformed packings (5) and (6) on the gravity feed manifold (2), the collector tank
fitting, the main tank fitting, and the gravity crossflow manifold.
(4) Install the gravity feed manifold (2) and the retainers (4). Make sure that the TOP
placard is on the top of the gravity−feed check valve (8).
(5) Connect the couplings (3) (Ref. TASK 20−30−00−910−802).
(6) Remove the protective plug from the venturi tube (1). Connect the venturi tube to
the gravity feed manifold (2).

Master
EFFECTIVITY: See Pageblock 28−13−28 page 401
28−13−28 Page 404
Sep 10/2004
 C
AIRCRAFT MAINTENANCE MANUAL
3. Close Out
Subtask 28−13−28−410−001
A. If the left gravity feed manifold was replaced, install the access panel that follows (Ref.
TASK 28−11−01−400−801):
ACCESS DESCRIPTION
510AB Fuel tank access panel
B. If the right gravity feed manifold was replaced, install the access panel that follows (Ref.
TASK 28−11−01−400−802):
ACCESS DESCRIPTION
610AB Fuel tank access panel

Master
EFFECTIVITY: See Pageblock 28−13−28 page 401
28−13−28 Page 405
Sep 10/2004
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C ALL
SWITCH/LIGHT, FUEL CROSSFLOW − REMOVAL/INSTALLATION

1. General
A. The maintenance procedures that follow are for the removal and installation of the fuel
crossflow switch/lights. There are four fuel crossflow switch/lights. They are installed on
the FUEL control panel, on the overhead panel in the flight compartment. The
switch/lights removed and installed in this procedure are as follows:
± GRAVITY XFLOW switch/light
± AUTO OVERRIDE switch/light
± XFLOW L and R switch/lights.

TASK 28−13−31−000−801
Removal of the Fuel Crossflow Switch/Light

1. Job Set−Up Information

Subtask 28−13−31−946−001
A. Reference Information
REFERENCE DESIGNATION
TASK 24−00−00−910−801 Electrical/Electronic Safety Precautions

2. Job Set−Up
Subtask 28−13−31−910−001
A. Obey all of the electrical and electrical safety precautions reef. TASK
24−00−00−910−801).

Subtask 28−13−31−865−001
B. Open, safety, and tag the circuit breakers that follow:
CB PANEL CB NO. NAME ZONE
CBP−1 H5 EICAS LDU L 221
CBP−1 M7 L FUEL PUMP CONT 221
CBP−1 M8 XFLOW SOV 221
CBP−1 M12 FUEL SYST CONT 221
CBP−1 N10 XFER/APU FUEL PUMP 221
CBP−1 N11 XFER/APU CONT 221
CBP−1 N12 XFER/APU APU ECU 221
CBP−2 G11 FUEL PUMP CONT 222
CBP−2 Q8 EICAS CONT PNL 222
CBP−4 B9 FUEL GRAV XFLOW 222
CBP−4 B10 FUEL SYST CONT 222

Master
EFFECTIVITY: See Pageblock 28−13−31 page 401
28−13−31 Page 401
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
3. Procedure
Subtask 28−13−31−020−001
Refer to Figure 401.
A. Remove the fuel crossflow switch/light as follows:
(1) Remove the screws (1), the rubber washers (2), and the plastic panel (3).
(2) Release the captive fasteners (4) and carefully pull the control panel (5) out of the
overhead panel.
(3) Disconnect the electrical connector (6) from the switch/light (7), and remove the
switch/light.
(4) Put protective covers on all the electrical connectors.
(5) Remove the switch cap (8) and the cap lens (9) from the switch/light (7). Keep the
cap lens for installation.
(6) Install the switch cap (8) on the switch/light (7).

Master
EFFECTIVITY: See Pageblock 28−13−31 page 401
28−13−31 Page 402
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

A
B

L BOOST GRAVITY R BOOST

PUMP XFLOW PUMP

ON FAIL ON
F INOP OPEN INOP
U
E XFLOW
L AUTO OVERRIDE R
L
ON ON
MAN
FAIL FAIL

B B
A
LEGEND
1. Screw nuts.
2. Rubber washer.
3. Plastic panel.
4. Captive fastener. OVERHEAD
5. Control panel. 6 CONSOLE (REF)
6. Electrical connector.
7. Swit.ch/light.
8. Switch cap.
9. Cap lens.

7
9
8

B TYPICAL
4
5 ram2823044_001(1).dc, pb/kms, 5/07/95

1 2 3

Fuel Crossflow Switch/Light − Removal/Installation

Figure 401

Master
EFFECTIVITY: See Pageblock 28−13−31 page 401
28−13−31 Page 403
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
TASK 28−13−31−400−801
Installation of the Fuel Crossflow Switch/Light

1. Job Set−Up Information

Subtask 28−13−31−945−001
A. Parts
REF NAME OF PART QTY IPC SEQUENCE NO.
1 Screw 4 IPC 28−13−00−05−010
2 Washer, rubber 4 IPC 28−13−00−05−015

Subtask 28−13−31−946−002
B. Reference Information
REFERENCE DESIGNATION
TASK 31−52−00−710−801 Operational Test of the Warning Lights System

2. Procedure
Subtask 28−13−31−869−001
A. Make sure that the aircraft is in the same configuration as in the removal task.

Subtask 28−13−31−420−001
Refer to Figure 401.
B. Install the fuel crossflow switch/light as follows:
(1) Remove the switch cap (8) from the switch/light (7).
(2) Install the cap lens (9) and the switch cap (8) on the switch/light (7).
(3) Remove the protective caps from the electrical connectors.
(4) Install the switch/light (7) in the control panel (5). Connect the electrical connector
(6).
(5) Carefully push the control panel (7) into the overhead panel. Tighten the captive
fasteners (4).
(6) Install the plastic panel (3), the rubber washers (2), and the screws (1).

3. Close Out
Subtask 28−13−31−865−002
A. Remove the tags and close the circuit breakers that follow:
CB PANEL CB NO. NAME ZONE
CBP−1 H5 EICAS LDU L 221
CBP−1 M7 L FUEL PUMP CONT 221
CBP−1 M8 XFLOW SOV 221

Master
EFFECTIVITY: See Pageblock 28−13−31 page 401
28−13−31 Page 404
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

CB PANEL CB NO. NAME ZONE

CBP−1 M12 FUEL SYST CONT 221
CBP−1 N10 XFER/APU FUEL PUMP 221
CBP−1 N11 XFER/APU CONT 221
CBP−1 N12 XFER/APU APU ECU 221
CBP−2 G11 L FUEL PUMP CONT 222
CBP−2 Q8 EICAS CONT PNL 222
CBP−4 B9 FUEL GRAV XFLOW 222
CBP−4 B10 FUEL SYST CONT 222

Subtask 28−13−31−710−001
B. Do a lamp test of the FUEL control panel reef. TASK 31−52−00−710−801).

Master
EFFECTIVITY: See Pageblock 28−13−31 page 401
28−13−31 Page 405
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C ALL
VALVE, FUEL TRANSFER SHUTOFF − REMOVAL/INSTALLATION

1. General
A. The maintenance procedures that follow are for the removal and installation of the
fuel−transfer shutoff valve (written as the "shutoff valve" in this procedure). There are
two shutoff valves in the fuel system. They are found in the center tank connected to the
motive line of the transfer ejector pump.
B. It is necessary to defuel the aircraft to remove or install the shutoff valve. It is also
necessary to drain and remove the fuel fumes from the center tank.

TASK 28−13−43−000−801
Removal of the Fuel−Transfer Shutoff Valve

1. Job Set−Up Information

Subtask 28−13−43−946−001
A. Reference Information
REFERENCE DESIGNATION
TASK 12−11−28−650−804 Suction Defueling
TASK 28−00−00−910−801 Fuel Safety Precautions
TASK 28−11−00−840−801 Prepare Fuel Tank for Access
TASK 28−11−00−840−802 Removal of Fuel Fumes
TASK 28−11−01−000−801 Removal of the Honeycomb Access Panel
TASK 28−11−01−000−802 Removal of the Aluminum Access Panel
TASK 53−83−01−000−801 Removal of the MLG Wheel Bin
WM 20−12−00 Wiring Manual
WM 20−17−10 Wiring Manual

2. Job Set−Up
Subtask 28−13−43−910−001
WARNING: OBEY ALL THE FUEL SAFETY PRECAUTIONS WHEN YOU DO WORK ON
THE FUEL SYSTEM AND/OR A FUEL SYSTEM COMPONENT. IF YOU DO
NOT DO THIS, YOU CAN CAUSE INJURIES TO PERSONS AND/OR
DAMAGE TO EQUIPMENT.
A. Obey all the fuel safety precautions (Ref. TASK 28−00−00−910−801).
WARNING: OBEY ALL THE SAFETY PRECAUTIONS WHEN YOU DO MAINTENANCE
ON OR NEAR ELECTRICAL/ELECTRONIC EQUIPMENT. IF YOU DO NOT
DO THIS, YOU CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE
TO THE EQUIPMENT.
B. Obey all the electrical/electronic safety precautions (Ref. TASK 24−00−00−910−801).

Master
EFFECTIVITY: See Pageblock 28−13−43 page 401
28−13−43 Page 401
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
Subtask 28−13−43−650−001
C. Defuel the aircraft (Ref. TASK 12−11−28−650−804).

Subtask 28−13−43−010−001
D. For the left shutoff valve, remove the left wheel bin from the main wheel well (Ref. TASK
53−83−01−000−801).
E. For the right shutoff valve, remove the right wheel bin from the main wheel well (Ref.
TASK 53−83−01−000−801).
F. To remove the left shutoff valve, remove the access panel that follows (Ref. TASK
28−11−01−000−801):
ACCESS DESCRIPTION
510AB Center−fuel−tank access panel
G. To remove the right shutoff valve, remove the access panel that follows (Ref. TASK
28−11−01−000−802):
ACCESS DESCRIPTION
610AB Center−fuel−tank access panel

Subtask 28−13−43−840−001
H. Prepare the center tank for access (Ref. TASK 28−11−00−840−801).
I. Remove the fuel fumes from the center tank (Ref. TASK 28−11−00−840−802).

**ON A/C 7012, 7022, 7038, 7040, 7050, 7062, 7066−7067, 7070 Pre SB601R−28−022

Subtask 28−13−43−865−006
J. Open, safety, and tag the circuit breaker that follows:
CB PANEL CB NO. NAME ZONE
CBP−1 N9 XFER/APU XFER SOV 221

**ON A/C 7003−7011, 7013−7021, 7023−7037, 7039, 7041−7049, 7051−7061, 7063−7065, 7069,
7071−7990, 8000−8064, 8066−8068 and ON A/C 7012, 7022, 7038, 7040, 7050, 7062,
7066−7067, 7070 Post SB601R−28−022

Subtask 28−13−43−865−003
K. Open, safety, and tag the circuit breakers that follow:
CB PANEL CB NO. NAME ZONE
CBP−1 N9 XFER/APU LEFT FUEL SOV 221
CBP−2 P9 RIGHT FUEL XFER SOV 222

**ON A/C ALL

Master
EFFECTIVITY: See Pageblock 28−13−43 page 401
28−13−43 Page 402
Dec 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
3. Procedure
**ON A/C 7003−7067, 7069−7299

Subtask 28−13−43−030−001
Refer to Figure 401.
A. Disconnect the electrical connections (Ref. WM 20−17−10).
B. Remove the wires from the electrical conduit as follows:
CAUTION: USE TWO WRENCHES WHEN YOU REMOVE THE ELECTRICAL
CONDUIT FROM THE SOLENOID. USE ONE WRENCH TO HOLD THE
FITTING ON THE SOLENOID AND THE OTHER WRENCH TO LOOSEN
THE COUPLING NUT ON THE CONDUIT. DAMAGE TO THE
ELECTRICAL WIRES CAN OCCUR IF YOU DO NOT USE TWO
WRENCHES.
(1) Disconnect the electrical conduit (1) from the control solenoid (2) of the shutoff
valve (3).
CAUTION: DO NOT PULL THE VALVE BODY WHEN YOU REMOVE THE WIRES
FROM THE ELECTRICAL CONDUIT. IF YOU DO THIS, YOU CAN
DAMAGE THE VALVE AND ITS SOLENOID.
(2) Remove the wires from the electrical conduit (1) (Ref. WM 20−12−00).

Subtask 28−13−43−020−001
Refer to Figure 401.
C. Remove the shutoff valve as follows:
(1) Remove the lockwire and disconnect the fuel pressure lines (4) from the shutoff
valve (3). Put protective plugs in the fuel pressure lines (4).
(2) Hold the shutoff valve (3) and remove the three screws (5) and the three washers
(6) from the two mounting brackets (7). Remove the shutoff valve.

**ON A/C 7300−7990, 8000−8064, 8066−8068

Subtask 28−13−43−030−002
Refer to Figure 402.
D. Disconnect the electrical connections (Ref. WM 20−17−10).
E. Remove the wires from the electrical conduit as follows:
(1) Disconnect the electrical conduit (1) from the control solenoid (2), of the shutoff
valve (3).
CAUTION: DO NOT PULL THE VALVE BODY WHEN YOU REMOVE THE WIRES
FROM THE ELECTRICAL CONDUIT. IF YOU DO THIS, YOU CAN
DAMAGE THE VALVE AND ITS SOLENOID.
(2) Remove the wires from the electrical conduit (1) (Ref. WM 20−12−00).

Subtask 28−13−43−020−002
Refer to Figure 402.

Master
EFFECTIVITY: See Pageblock 28−13−43 page 401
28−13−43 Page 403
Dec 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
F. Remove the shutoff valve as follows:
(1) Remove the screw (4), together with three washers (5) and two bonding jumpers
(6).
(2) Remove the lockwire and disconnect the fuel pressure lines (7) from the shutoff
valve (3). Put protective plugs in the fuel pressure lines.
(3) Hold the shutoff valve (3) and remove the two screws (8) and the two washers (9)
from the mounting bracket (10). Remove the shutoff valve.

Master
EFFECTIVITY: See Pageblock 28−13−43 page 401
28−13−43 Page 404
Dec 15/2004
 C
AIRCRAFT MAINTENANCE MANUAL

D
FW

B
LEGEND. A
1. Electrical conduit.
2. Control solenoid.
3. Shutoff valve.
4. Fuel pressure lines.
5. Screw.
6. Washer.
7. Mounting brackets.

4
7

6
5

4
3

A
ram2813434_001(2).dg, rt, 14/06/95

NOTE

A Right side is shown.

B Left side is similar but inverted.

Fuel−Transfer Shutoff Valve − Removal/Installation

Figure 401

Master
EFFECTIVITY: See Pageblock 28−13−43 page 401
28−13−43 Page 405
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

LEGEND D
FW
1. Electrical conduit.
2. Control solenoid.
3. Shutoff valve.
4. Screw.
5. Washer.
6. Bonding jumper.
7. Fuel pressure lines.
8. Screw.
9. Washer.
10. Mounting brackets.

1 A

NOTE
Right side shown, left side
is similar but inverted.

10

3
9 5
8
5
7
4
ram2813434_002.dg, jp, 11/05/99

6
A

Fuel−Transfer Shutoff Valve − Removal/Installation

Figure 402

Master
EFFECTIVITY: See Pageblock 28−13−43 page 401
28−13−43 Page 406
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C ALL
TASK 28−13−43−400−801
Installation of the Fuel−Transfer Shutoff Valve

1. Job Set−Up Information

Subtask 28−13−43−944−001
A. Consumable Materials
REFERENCE DESIGNATION
05−004 Lockwire

**ON A/C 7003−7067, 7069−7299

Subtask 28−13−43−945−001
B. Parts
REF NAME OF PART QTY IPC SEQUENCE NO.
5 Screw 3 IPC 28−13−43−1A−010
6 Washer 3 IPC 28−13−43−1A−015

**ON A/C 7300−7990, 8000−8064, 8066−8068

Subtask 28−13−43−945−002
C. Parts
REF NAME OF PART QTY IPC SEQUENCE NO.
4 Screw 1 IPC 28−13−43−1A−040
5 Washer 3 IPC 28−13−43−1A−045
8 Screw 2 IPC 28−13−43−1A−010
9 Washer 2 IPC 28−13−43−1A−015

**ON A/C ALL

Subtask 28−13−43−946−002
D. Reference Information
REFERENCE DESIGNATION
TASK 24−00−00−910−801 Electrical/Electronic Safety Precautions
TASK 28−00−00−910−801 Fuel Safety Precautions
TASK 28−11−01−400−801 Installation of the Honeycomb Access Panel
TASK 28−11−01−400−802 Installation of the Aluminum Access Panel
TASK 28−13−43−710−801 Operational Test of the Fuel−Transfer Shutoff
Valve
TASK 51−23−00−390−804 Bead Seal Sealant Procedure

Master
EFFECTIVITY: See Pageblock 28−13−43 page 401
28−13−43 Page 407
Dec 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL

REFERENCE DESIGNATION
TASK 51−23−00−390−808 Application of Sealant with Brush
TASK 51−80−00−100−802 Preparation of Bonding Surfaces
TASK 51−80−00−760−803 Electrical Bonding Test
TASK 51−80−00−910−801 Electrical Bonding Precautions
TASK 53−83−01−400−801 Installation of the MLG Wheel Bin
WM 20−12−00 Wiring Manual
WM 20−17−10 Wiring Manual

2. Job Set−Up
Subtask 28−13−43−910−003
WARNING: OBEY ALL THE FUEL SAFETY PRECAUTIONS WHEN YOU DO WORK ON
THE FUEL SYSTEM AND/OR A FUEL SYSTEM COMPONENT. IF YOU DO
NOT DO THIS, YOU CAN CAUSE INJURIES TO PERSONS AND/OR
DAMAGE TO EQUIPMENT.
A. Obey all the fuel safety precautions (Ref. TASK 28−00−00−910−801).
WARNING: OBEY ALL THE SAFETY PRECAUTIONS WHEN YOU DO MAINTENANCE
ON OR NEAR ELECTRICAL/ELECTRONIC EQUIPMENT. IF YOU DO NOT
DO THIS, YOU CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE
TO THE EQUIPMENT.
B. Obey all the electrical/electronic safety precautions (Ref. TASK 24−00−00−910−801).
C. Obey all of the electrical bonding precautions (Ref. TASK 51−80−00−910−801).

Subtask 28−13−43−869−001
D. Make sure that the aircraft is in the same configuration as in the removal task.

3. Procedure
**ON A/C 7003−7067, 7069−7299

Subtask 28−13−43−420−001
Refer to Figure 401.
A. Install the shutoff valve as follows:
(1) Prepare the mating surfaces of the three screws (5), the shutoff valve (3), and the
mounting brackets (7) for electrical bonding (Ref. TASK 51−80−00−100−802).
(2) Position the shutoff valve (3) on the two mounting brackets (7) and install with three
washers (6) and three screws (5).
NOTE: When installed, the control solenoid (2) of the left shutoff valve (3) points
down. The control solenoid (2) of the right shutoff valve (3) points up.
NOTE: Make sure that the arrow on the shutoff valve (3) body points in the flow
direction.

Master
EFFECTIVITY: See Pageblock 28−13−43 page 401
28−13−43 Page 408
Aug 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
(3) Do an electrical bonding test of the shutoff valve (3).
(4) Apply a brushcoat of sealant to the screws (5) and the washers (6).
(5) Apply a bead of sealant around the shutoff valve (3).
(6) Remove the protective plugs from the fuel pressure lines (4). Connect the fuel
pressure lines (4) to the shutoff valve (3). Safety the fuel pressure lines (4) to each
other with lockwire.

Subtask 28−13−43−430−001
Refer to Figure 401.
B. Install the wires in the electrical conduit as follows:
(1) Install the wires in the electrical conduit (1) (Ref. WM 20−12−00).
CAUTION: USE TWO WRENCHES WHEN YOU TIGHTEN THE ELECTRICAL
CONDUIT TO THE SOLENOID. USE ONE WRENCH TO HOLD THE
FITTING ON THE SOLENOID AND THE OTHER WRENCH TO
TIGHTEN THE COUPLING NUT ON THE CONDUIT. DAMAGE TO THE
ELECTRICAL WIRES CAN OCCUR IF YOU DO NOT USE TWO
WRENCHES.
(2) Connect the electrical conduit (1) to the control solenoid (2).
C. Connect the electrical connections (Ref. WM 20−17−10).

**ON A/C 7300−7990, 8000−8064, 8066−8068

Subtask 28−13−43−420−002
Refer to Figure 402.
D. Install the shutoff valve as follows:
(1) Prepare the mating surfaces of the three screws (4) and (8), the shutoff valve (3),
and the two mounting brackets (10) for electrical bonding (Ref. TASK
51−80−00−100−802).
(2) Position the shutoff valve (3) on the two mounting brackets (10) and install with two
washers (9) and two screws (8).
NOTE: When installed, the control solenoid (2) of the left shutoff valve (3) points
down. The control solenoid (2) of the right shutoff valve (3) points up.
NOTE: Make sure that the arrow on the shutoff valve (3) body points in the flow
direction.
(3) Remove the protective plugs from the fuel pressure lines (7). Connect the fuel
pressure lines to the shutoff valve (3). Safety the fuel pressure lines to each other
with lockwire.
(4) Assemble the two bonding jumpers (6) with one washer (5) on either side of the
bonding jumpers and one washer between. Insert the screw (4).
(5) Install the screw (4), complete with the bonding jumpers (6) and washers (5), into
the mounting bracket (10).
(6) Do an electrical bonding test of the shutoff valve (3).
(7) Apply a brushcoat of sealant to the screws (4) and (8), and the washers (5) and (9).

Master
EFFECTIVITY: See Pageblock 28−13−43 page 401
28−13−43 Page 409
Dec 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
(8) Apply a bead of sealant around the shutoff valve (3).

Subtask 28−13−43−430−002
Refer to Figure 402.
E. Install the wires in the electrical conduit as follows:
(1) Install the wires in the electrical conduit (1) (Ref. WM 20−12−00).
(2) Connect the electrical conduit (1) to the control solenoid (2).
F. Connect the electrical connections (Ref. WM 20−17−10).
**ON A/C ALL

4. Close Out
Subtask 28−13−43−410−001
A. If the left shutoff valve was replaced, install the access panel that follows (Ref. TASK
28−11−01−400−801):
ACCESS DESCRIPTION
510AB Center−fuel−tank access panel
B. If the right shutoff valve was replaced, install the access panel that follows (Ref. TASK
28−11−01−400−802):
ACCESS DESCRIPTION
610AB Center−fuel−tank access panel

**ON A/C 7012, 7022, 7038, 7040, 7050, 7062, 7066−7067, 7070 Pre SB601R−28−022

Subtask 28−13−43−865−004
C. Remove the tags and close the circuit breaker that follows:
CB PANEL CB NO. NAME ZONE
CBP−1 N9 XFER/APU LEFT FUEL SOV 221

**ON A/C 7003−7011, 7013−7021, 7023−7037, 7039, 7041−7049, 7051−7061, 7063−7065, 7069,
7071−7990, 8000−8064, 8066−8068 and ON A/C 7012, 7022, 7038, 7040, 7050, 7062,
7066−7067, 7070 Post SB601R−28−022

Subtask 28−13−43−865−007
D. Remove the tags and close the circuit breakers that follow:
CB PANEL CB NO. NAME ZONE
CBP−1 N9 XFER/APU LEFT FUEL SOV 221
CBP−2 P9 RIGHT FUEL XFER SOV 222

Master
EFFECTIVITY: See Pageblock 28−13−43 page 401
28−13−43 Page 410
Dec 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C ALL

Subtask 28−13−43−710−001
E. Do an operational test of the shutoff valve (Ref. TASK 28−13−43−710−801).

Subtask 28−13−43−410−002
F. For the left shutoff valve, install the left wheel bin in the main wheel well (Ref. TASK
53−83−01−400−801).
G. For the right shutoff valve, install the right wheel bin in the main wheel well (Ref. TASK
53−83−01−400−801).

Master
EFFECTIVITY: See Pageblock 28−13−43 page 401
28−13−43 Page 411
Aug 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C ALL
VALVE, FUEL TRANSFER SHUTOFF − ADJUSTMENT/TEST

1. General
A. The maintenance procedure that follows is for the operational test of the fuel−transfer
shutoff valve (written as the "shutoff valve" in this procedure).

TASK 28−13−43−710−801
Operational Test of the Fuel−Transfer Shutoff Valve

1. Job Set−Up Information

Subtask 28−13−43−946−003
A. Reference Information
REFERENCE DESIGNATION
TASK 12−00−07−861−801 Connect External AC Power
TASK 12−00−07−861−802 Remove External AC Power
TASK 12−11−28−650−802 Manual Pressure Refueling
FIM 28−40−00 Fault Isolation Manual indicating system

2. Job Set−Up
Subtask 28−13−43−650−002
A. Refuel each main tank to a minimum of 4700 pounds (2131.88 kg) (Ref. TASK
12−11−28−650−802).
B. Make sure that the center tank is refuelled to a minimum of 200 pounds (90.71 kg) of
fuel.

**ON A/C 7012, 7022, 7038, 7040, 7050, 7062, 7066−7067, 7070 Pre SB601R−28−022

Subtask 28−13−43−865−005
C. Make sure that the circuit breaker that follows is closed:
CB PANEL CB NO. NAME ZONE
CBP−1 N9 FUEL XFER 221

**ON A/C 7003−7011, 7013−7021, 7023−7037, 7039, 7041−7049, 7051−7061, 7063−7065, 7069,
7071−7990, 8000−8064, 8066−8068 and ON A/C 7012, 7022, 7038, 7040, 7050, 7062,
7066−7067, 7070 Post SB601R−28−022

Subtask 28−13−43−865−008
D. Make sure that the circuit breakers that follow are closed:

Master
EFFECTIVITY: See Pageblock 28−13−43 page 501
28−13−43 Page 501
Dec 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL

CB PANEL CB NO. NAME ZONE

CBP−1 N9 FUEL XFER 221
CBP−2 P9 RIGHT FUEL XFER SOV 222

**ON A/C ALL

Subtask 28−13−43−861−001
E. Connect the external AC power to the aircraft (Ref. TASK 12−00−07−861−801).
F. Push the FUEL pushbutton on the engine indication and crew alerting system (EICAS)
control panel to get the FUEL synoptic display.
**ON A/C 7008, 7011−7014, 7017−7018, 7020, 7022, 7026−7031, 7034−7035, 7037−7038, 7040,
7042−7051, 7053−7058, 7060, 7062, 7065−7067, 7069−7072, 7074, 7076−7085, 7087−7088,
7091−7092, 7095−7098, 7100−7102, 7105−7109, 7111−7112, 7115−7118, 7120, 7123−7124,
7126−7127, 7129, 7131−7132, 7137, 7139, 7141, 7143−7147, 7150−7151, 7153−7164, 7166,
7168−7175, 7177−7179, 7181−7188, 7191−7192, 7194−7199, 7201−7204, 7206−7219,
7221−7225, 7227−7246, 7249−7265, 7267−7281, 7284−7297, 7300−7328, 7330−7350,
7352−7364, 7366−7370, 7372, 7374−7377, 7379−7385, 7387−7390, 7392−7393, 7395−7402,
7404−7406, 7408−7412, 7414−7418, 7420−7430, 7432−7435, 7437−7438, 7440−7441,
7443−7448, 7450−7463, 7465−7477, 7479, 7481−7485, 7487−7493, 7495−7498, 7500−7566,
7568−7569, 7571−7572, 7574−7582, 7584−7604, 7606, 7608−7616, 7618, 7620−7624,
7626−7628, 7631−7737, 7739−7845, 7847−7861, 7863, 7865−7900, 7903−7909, 7911−7972,
7974−7989, 8000−8045, 8047−8059, 8061−8064 and ON A/C 7226 Pre SB601R−28−034
(1) Make sure that the refuel/defuel control panel is off and the guard of the POWER
toggle switch is down.
**ON A/C 7003−7007, 7009−7010, 7015−7016, 7019, 7021, 7023−7025, 7032−7033, 7036, 7039,
7041, 7052, 7059, 7061, 7063−7064, 7073, 7075, 7086, 7089−7090, 7093−7094, 7099,
7103−7104, 7110, 7113−7114, 7119, 7121−7122, 7125, 7128, 7130, 7133−7136, 7138, 7140,
7142, 7148−7149, 7152, 7165, 7167, 7176, 7180, 7189−7190, 7193, 7200, 7205, 7220,
7247−7248, 7266, 7282−7283, 7298−7299, 7329, 7351, 7365, 7371, 7373, 7378, 7386, 7391,
7394, 7403, 7407, 7413, 7419, 7431, 7436, 7439, 7442, 7449, 7464, 7478, 7480, 7486, 7494,
7499, 7567, 7570, 7573, 7583, 7605, 7607, 7617, 7619, 7625, 7629−7630, 7738, 7846, 7862,
7864, 7901−7902, 7910, 7973, 7990, 8046, 8060, 8066−8068 and ON A/C 7226 Post
SB601R−28−034
(2) Make sure that the two refuel/defuel control panels are off and the guard of each
POWER toggle switch is down.
**ON A/C ALL

3. Procedure
Subtask 28−13−43−710−002
A. Do an operational test of the left and right shutoff valve as follows:
(1) On the FUEL synoptic display of the EICAS, make sure that the left and right
shutoff−valve outlines are shown in white and in the closed position.

Master
EFFECTIVITY: See Pageblock 28−13−43 page 501
28−13−43 Page 502
Dec 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C 7008, 7011−7014, 7017−7018, 7020, 7022, 7026−7031, 7034−7035, 7037−7038, 7040,
7042−7051, 7053−7058, 7060, 7062, 7065−7067, 7069−7072, 7074, 7076−7085, 7087−7088,
7091−7092, 7095−7098, 7100−7102, 7105−7109, 7111−7112, 7115−7118, 7120, 7123−7124,
7126−7127, 7129, 7131−7132, 7137, 7139, 7141, 7143−7147, 7150−7151, 7153−7164, 7166,
7168−7175, 7177−7179, 7181−7188, 7191−7192, 7194−7199, 7201−7204, 7206−7219,
7221−7225, 7227−7246, 7249−7265, 7267−7281, 7284−7297, 7300−7328, 7330−7350,
7352−7364, 7366−7370, 7372, 7374−7377, 7379−7385, 7387−7390, 7392−7393, 7395−7402,
7404−7406, 7408−7412, 7414−7418, 7420−7430, 7432−7435, 7437−7438, 7440−7441,
7443−7448, 7450−7463, 7465−7477, 7479, 7481−7485, 7487−7493, 7495−7498, 7500−7566,
7568−7569, 7571−7572, 7574−7582, 7584−7604, 7606, 7608−7616, 7618, 7620−7624,
7626−7628, 7631−7737, 7739−7845, 7847−7861, 7863, 7865−7900, 7903−7909, 7911−7972,
7974−7989, 8000−8045, 8047−8059, 8061−8064 and ON A/C 7226 Pre SB601R−28−034
(2) On the refuel/defuel control panel, lift the guard off the POWER toggle switch. Set
the POWER toggle switch to on. Make sure that the POWER ON indicator light
comes on.
**ON A/C 7003−7007, 7009−7010, 7015−7016, 7019, 7021, 7023−7025, 7032−7033, 7036, 7039,
7041, 7052, 7059, 7061, 7063−7064, 7073, 7075, 7086, 7089−7090, 7093−7094, 7099,
7103−7104, 7110, 7113−7114, 7119, 7121−7122, 7125, 7128, 7130, 7133−7136, 7138, 7140,
7142, 7148−7149, 7152, 7165, 7167, 7176, 7180, 7189−7190, 7193, 7200, 7205, 7220,
7247−7248, 7266, 7282−7283, 7298−7299, 7329, 7351, 7365, 7371, 7373, 7378, 7386, 7391,
7394, 7403, 7407, 7413, 7419, 7431, 7436, 7439, 7442, 7449, 7464, 7478, 7480, 7486, 7494,
7499, 7567, 7570, 7573, 7583, 7605, 7607, 7617, 7619, 7625, 7629−7630, 7738, 7846, 7862,
7864, 7901−7902, 7910, 7973, 7990, 8046, 8060, 8066−8068 and ON A/C 7226 Post
SB601R−28−034
(3) On one of the two refuel/defuel control panels, lift the guard off the POWER toggle
switch. Set the POWER toggle switch to on. Make sure that the POWER ON
indicator light comes on.
NOTE: Make sure that the FAULT ANNUNC. indicator light is not on. If the light is
on, refer to the Fault Isolation Manual (Ref. FIM28−40−00).
**ON A/C ALL
(4) On the FUEL synoptic display of the EICAS, make sure that the left and right
shutoff−valve outlines are shown in white and in the open position.
(5) On the refuel/defuel control panel, set the POWER toggle switch to off and lower
the guard. Make sure that the POWER ON indicator light goes off.
(6) On the FUEL synoptic display of the EICAS, make sure that the left and right
shutoff−valve outlines are shown in white and in the closed position.

4. Close Out
Subtask 28−13−43−861−002
A. Remove the external AC power from the aircraft (Ref. TASK 12−00−07−861−802).

Master
EFFECTIVITY: See Pageblock 28−13−43 page 501
28−13−43 Page 503
Dec 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C ALL
VALVE, FUEL CROSSFLOW SHUTOFF − REMOVAL/INSTALLATION

1. General
A. The maintenance procedures that follow are for the removal and installation of the fuel
crossflow shutoff valve (written as the "shutoff valve" in this procedure). There are two
shutoff valves in the fuel system. They are found in the center wing box at the two ends
of the crossflow manifold.
B. It is necessary to defuel the aircraft to remove or install the shutoff valve. It is also
necessary to drain and remove the fuel fumes from the center tank.

TASK 28−13−45−000−801
Removal of the Fuel Crossflow Shutoff Valve

1. Job Set−Up Information

Subtask 28−13−45−946−001
A. Reference Information
REFERENCE DESIGNATION
TASK 12−11−28−650−804 Suction Defueling
TASK 28−00−00−910−801 Fuel Safety Precautions
TASK 28−11−00−840−801 Prepare Fuel Tank for Access
TASK 28−11−00−840−802 Removal of Fuel Fumes
TASK 28−11−01−000−802 Removal of the Aluminum Access Panel
TASK 53−83−01−000−801 Removal of the MLG Wheel Bin
WM 20−12−00 Wiring − Installation
WM 20−17−10 Wiring Manual

2. Job Set−Up
Subtask 28−13−45−910−001
WARNING: OBEY ALL THE FUEL SAFETY PRECAUTIONS WHEN YOU DO WORK ON
THE FUEL SYSTEM AND/OR A FUEL SYSTEM COMPONENT. IF YOU DO
NOT DO THIS, YOU CAN CAUSE INJURIES TO PERSONS AND/OR
DAMAGE TO EQUIPMENT.
A. Obey all the fuel safety precautions (Ref. TASK 28−00−00−910−801).
WARNING: OBEY ALL THE SAFETY PRECAUTIONS WHEN YOU DO MAINTENANCE
ON OR NEAR ELECTRICAL/ELECTRONIC EQUIPMENT. IF YOU DO NOT
DO THIS, YOU CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE
TO THE EQUIPMENT.
B. Obey all the electrical/electronic safety precautions (Ref. TASK 24−00−00−910−801).

Master
EFFECTIVITY: See Pageblock 28−13−45 page 401
28−13−45 Page 401
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
Subtask 28−13−45−650−001
C. Defuel the aircraft (Ref. TASK 12−11−28−650−804).

Subtask 28−13−45−010−001
D. For the left shutoff valve, remove the left main wheel well (Ref. TASK
53−83−01−000−801).
E. For the right shutoff valve, remove the right wheel bin from the main wheel well (Ref.
TASK 53−83−01−000−801).
F. Remove the applicable access panel that follows (Ref. TASK 28−11−01−000−802):
ACCESS DESIGNATION
510BB Fuel tank access panel
610BB Fuel tank access panel

Subtask 28−13−45−840−001
G. Prepare the center tank for access (Ref. TASK 28−11−00−840−801).
H. Remove the fuel fumes from the center tank (Ref. TASK 28−11−00−840−802).

Subtask 28−13−45−865−003
I. Open, safety and tag the circuit beaker that follows:
CB PANEL CB NO. NAME ZONE
CBP−1 M8 XFLOW SOV 221

3. Procedure
**ON A/C 7003−7067, 7069−7299

Subtask 28−13−45−030−001
Refer to Figure 401.
A. Disconnect the electrical connections (Ref. WM 20−17−10).
B. Remove the wires from the conduit as follows:
(1) Disconnect the electrical conduit (1) from the control solenoid (2) of the shutoff
valve (3).
CAUTION: DO NOT PULL THE VALVE BODY WHEN YOU REMOVE THE WIRES
FROM THE ELECTRICAL CONDUIT. IF YOU DO THIS, YOU CAN
DAMAGE THE VALVE AND ITS SOLENOID.
(2) Remove the wires from the electrical conduit (Ref. TASK WM 20−12−00).

Subtask 28−13−45−020−001
C. Remove the shutoff valve as follows:

Master
EFFECTIVITY: See Pageblock 28−13−45 page 401
28−13−45 Page 402
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
(1) Disconnect the fuel pressure lines (4) from the shutoff valve (3). Put protective
plugs in the pressure lines.
(2) Hold the shutoff valve (3) and remove the screws (4), the washers (5) from the
mounting bracket (6). Remove the shutoff valve.

**ON A/C 7300−7990, 8000−8064, 8066−8068

Subtask 28−13−45−030−002
Refer to Figure 402
D. Disconnect the electrical connections (Ref. WM 20−17−10).
E. Remove the wires from the electrical conduit as follows:
(1) Disconnect the electrical conduit (1) from the control solenoid (2) of the shutoff
valve (3).
CAUTION: DO NOT PULL THE VALVE BODY WHEN YOU REMOVE THE WIRES
FROM THE ELECTRICAL CONDUIT. IF YOU DO THIS, YOU CAN
DAMAGE THE VALVE AND ITS SOLENOID.
(2) Remove the wires from the electrical conduit (1) (Ref. WM 20−12−00).

Subtask 28−13−45−020−002
Refer to Figure 402
F. Remove the shutoff valve as follows:
(1) Remove the screw (4), together with three washers (5) and two bonding jumpers
(6).
(2) Disconnect the fuel pressure lines (7) from the shutoff valve (3). Put protective
plugs in the fuel pressure lines.
(3) Hold the shutoff valve (3) and remove the two screws (8) and the two washers (9)
from the mounting bracket (10). Remove the shutoff valve.

Master
EFFECTIVITY: See Pageblock 28−13−45 page 401
28−13−45 Page 403
Dec 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL

LEGEND
1. Electrical conduit.
2. Control solenoid.
3. Shutoff valve.
4. Fuel pressure line.
5. Screw.
6. Washer.
7. Mounting bracket.

3 4

6
5
ram2813454_001(2).dc, ks/rm, 18/05/99

NOTE
LH side is shown
RH side is opposite.

Fuel Crossflow Shutoff Valve − Removal/Installation

Figure 401

Master
EFFECTIVITY: See Pageblock 28−13−45 page 401
28−13−45 Page 404
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

LEGEND
1. Electrical conduit.
2. Control solenoid.
3. Shutoff valve.
4. Screw.
5. Washer.
6. Bonding jumper.
7. Fuel pressure lines.
8. Screw.
9. Washer.
10. Mounting bracket.

10 9
8
7

7
5
6

ram2813454_002(2).dc, ks/rm, 31/05/99

5
NOTE
4
LH side is shown
RH side is opposite.

Fuel Crossflow Shutoff Valve − Removal/Installation

Figure 402

Master
EFFECTIVITY: See Pageblock 28−13−45 page 401
28−13−45 Page 405
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C ALL
TASK 28−13−45−400−801
Installation of the Fuel Crossflow Shutoff Valve

1. Job Set−Up Information

**ON A/C 7003−7067, 7069−7299

Subtask 28−13−45−945−001
A. Parts
REF NAME OF PART QTY IPC SEQUENCE NO.
5 Screw 3 IPC 28−13−45−1A−010
6 Washer 3 IPC 28−13−45−1A−015

Subtask 28−13−45−945−002

REF NAME OF PART QTY IPC SEQUENCE NO.

4 Screw 1 IPC 28−13−45−1A−040
5 Washer 3 IPC 28−13−45−1A−045
8 Screw 2 IPC 28−13−45−1A−010
9 Washer 2 IPC 28−13−45−1A−015

**ON A/C ALL

Subtask 28−13−45−946−002
B. Reference Information
REFERENCE DESIGNATION
TASK 24−00−00−910−801 Electrical/Electronic Safety Precautions
TASK 28−00−00−910−801 Fuel Safety Precautions
TASK 28−11−01−400−802 Installation of the Aluminum Access Panel
TASK 28−13−45−710−801 Operational Test of the Fuel Crossflow Shutoff
Valve
TASK 51−23−00−390−804 Bead Seal Sealant Procedure
TASK 51−23−00−390−808 Application of Sealant with Brush
TASK 51−80−00−100−802 Preparation of Bonding Surfaces
TASK 51−80−00−760−803 Electrical Bonding Test
TASK 53−83−01−400−801 Installation of the MLG Wheel Bin
WM 20−12−00 Wiring − Installation
WM 20−17−10 Wiring Manual

Master
EFFECTIVITY: See Pageblock 28−13−45 page 401
28−13−45 Page 406
Aug 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
Subtask 28−13−45−910−002
WARNING: OBEY ALL THE FUEL SAFETY PRECAUTIONS WHEN YOU DO WORK ON
THE FUEL SYSTEM AND/OR A FUEL SYSTEM COMPONENT. IF YOU DO
NOT DO THIS, YOU CAN CAUSE INJURIES TO PERSONS AND/OR
DAMAGE TO EQUIPMENT.
C. Obey all the fuel safety precautions (Ref. TASK 28−00−00−910−801).
WARNING: OBEY ALL THE SAFETY PRECAUTIONS WHEN YOU DO MAINTENANCE
ON OR NEAR ELECTRICAL/ELECTRONIC EQUIPMENT. IF YOU DO NOT
DO THIS, YOU CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE
TO THE EQUIPMENT.
D. Obey all the electrical/electronic safety precautions (Ref. TASK 24−00−00−910−801).

Subtask 28−13−45−869−001
E. Make sure that the aircraft is in the same configuration as in the removal task.

2. Procedure
**ON A/C 7003−7067, 7069−7299

Subtask 28−13−45−420−001
Refer to Figure 401.
A. Install the shutoff valve as follows:
(1) Prepare the mating surfaces of the screws (5), the shutoff valve (3), and the
mounting bracket (7) for electrical bond (Ref. TASK 51−80−00−100−802).
(2) Install the shutoff valve (3), the washers (6), and the screws (5).
NOTE: When installed, the control solenoid of the left shutoff valve is below the
valve body. The control solenoid of the right shutoff valve is above the
valve body.
NOTE: Make sure that the arrow on the shutoff valve (3) body points in the flow
direction.
(3) Do an electrical bonding test of the shutoff valve (3).
(4) Apply a brushcoat of sealant to the screws (5) and washers (6).
(5) Apply a bead of sealant around the shutoff valve (3).
(6) Remove the protective caps from the pressure lines (4). Connect the fuel pressure
lines to the shutoff valve (3).

Subtask 28−13−45−430−001
Refer to Figure 401
B. Install the wires in the electrical conduit as follows:
(1) Install the wires in the electrical conduit (Ref. WM 20−12−00).
(2) Connect the conduit (1) to the control solenoid (2).
C. Connect the electrical connections (Ref. WM 20−17−10).

Master
EFFECTIVITY: See Pageblock 28−13−45 page 401
28−13−45 Page 407
Aug 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C 7300−7990, 8000−8064, 8066−8068

Subtask 28−13−45−420−002
Refer to Figure 402
D. Install the shutoff valve as follows:
(1) Prepare the mating surfaces of the screws (4) and (8), the shutoff valve (3), and the
mounting bracket (10) for electrical bonding (Ref. TASK 51−80−00−100−802).
(2) Position the shutoff valve (3) on the mounting bracket (10) and install with two
washers (9) and two screws (8).
NOTE: When installed, the control solenoid of the left shutoff valve is below the
valve body. The control solenoid of the right shutoff valve is above the
valve body.
NOTE: Make sure that the arrow on the shutoff valve (3) body points in the flow
direction.
(3) Remove the protective plugs from the fuel pressure lines (7). Connect the fuel
pressure lines to the shutoff valve (3).
(4) Assemble the two bonding jumpers (6) with one washer (5) on either side of the
bonding jumpers and one washer between. Insert the screw (4).
(5) Install the screw (4), complete with the bonding jumpers (6) and washers (5), into
the mounting bracket (10).
(6) Do an electrical bonding test of the shutoff valve (3).
(7) Apply a brushcoat of sealant to the screws (4) and (8), and the washers (5) and (9).
(8) Apply a bead of sealant around the shutoff valve (3).

Subtask 28−13−45−430−002
Refer to Figure 402
E. Install the wires in the electrical conduit as follows:
(1) Install the wires in the electrical conduit (Ref. WM 20−12−00).
(2) Connect the conduit (1) to the control solenoid (2).
F. Connect the electrical connections (Ref. WM 20−17−10).
**ON A/C ALL

3. Close Out
Subtask 28−13−45−410−001
A. Install the applicable access panel that follows (Ref. TASK 28−11−01−400−802):
ACCESS DESIGNATION
510BB Fuel tank access panel
610BB Fuel tank access panel

Master
EFFECTIVITY: See Pageblock 28−13−45 page 401
28−13−45 Page 408
Dec 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
Subtask 28−13−45−865−004
B. Remove the tag and close the circuit beaker that follows:
CB PANEL CB NO. NAME ZONE
CBP−1 M8 XFLOW SOV 221

Subtask 28−13−45−710−001
C. Do an operational test of the shutoff valve (Ref. TASK 28−13−45−710−801).

Subtask 28−13−45−410−002
D. For the left shutoff valve, install the left wheel bin in the main wheel well (Ref. TASK
53−83−01−400−801).
E. For the right shutoff valve, install the right wheel bin in the main wheel well (Ref. TASK
53−83−01−400−801).

Master
EFFECTIVITY: See Pageblock 28−13−45 page 401
28−13−45 Page 409
Aug 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C ALL
VALVE, FUEL CROSSFLOW SHUTOFF − ADJUSTMENT/TEST

1. General
A. The maintenance procedure that follows is for the test of the fuel crossflow shutoff valve
(written as the "shutoff valve" in this procedure).

TASK 28−13−45−710−801
Operational Test of the Fuel Crossflow Shutoff Valve

1. Job Set−Up Information

Subtask 28−13−45−946−003
A. Reference Information
REFERENCE DESIGNATION
TASK 12−00−07−861−801 Connect External AC Power
TASK 12−00−07−861−802 Remove External AC Power
TASK 12−11−28−650−801 Automatic Pressure Refueling

2. Job Set−Up
Subtask 28−13−45−650−002
A. Refuel the aircraft (Ref. TASK 12−11−28−650−801).

Subtask 28−13−45−861−001
B. Connect the external AC power to the aircraft (Ref. TASK 12−00−07−861−801).
C. Push the FUEL pushbutton on the engine indication and crew alerting system (EICAS)
control panel to get the FUEL synoptic display.

3. Procedure
Subtask 28−13−45−710−002
A. Do an operational test of the shutoff valves as follows:
(1) On the fuel synoptic display of the EICAS, make sure that the left and right shutoff
valves are shown in white.
(2) On the FUEL control panel, do the steps that follow:
(a) Push the AUTO OVERRIDE switch/light.
(b) Make sure that the MAN light comes on.
(c) Push the XFLOW L switch/light.
(d) Make sure that the ON light comes on and that the FAIL light does not come
on.
(3) On the fuel synoptic display, make sure that the left shutoff valve is shown in green
and in the open position. Make sure that the right shutoff valve is shown in white

Master
EFFECTIVITY: See Pageblock 28−13−45 page 501
28−13−45 Page 501
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
and in the closed position.
(4) On the FUEL control panel, do the steps that follow:
(a) Push the XFLOW L switch/light.
(b) Make sure that the ON light goes off.
(c) Push the XFLOW R switch/light.
(d) Make sure that the ON light comes on and that the FAIL light does not come
on.
(5) On the fuel synoptic display, make sure that the right shutoff valve is shown in
green and in the open position. Make sure that the left shutoff valve is shown in
white and in the closed position.
(6) On the FUEL control panel, do the steps that follow:
(a) Push the XFLOW R switch/light.
(b) Make sure that the ON light goes off.
(c) Push the AUTO OVERRIDE switch/light.
(d) Make sure that the MAN light goes off.

Subtask 28−13−45−861−002
B. Remove the external AC power from the aircraft (Ref. TASK 12−00−07−861−802).

Master
EFFECTIVITY: See Pageblock 28−13−45 page 501
28−13−45 Page 502
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C ALL
DISTRIBUTION SYSTEM − DESCRIPTION AND OPERATION

1. General
A. The distribution system controls the movement of fuel into and out of the fuel tanks. The
distribution system includes the systems that follow:
± Engine fuel−feed system (28−21−00)
± Motive flow system (28−22−00)
± Standby fuel−feed system (28−23−00)
± Auxiliary power unit (APU) fuel−feed system (28−24−00)
± Pressure refuel/defuel system (28−25−00).
2. Description
A. Engine Fuel−Feed System
(1) The engine fuel−feed system controls the flow of fuel from the main tanks to the
engines. This system includes ejector pumps, check valves, and firewall shutoff
valves.
B. Motive Flow System
(1) The motive flow system controls the motive flow pressure in the fuel system. Motive
flow pressure is used to operate the ejector pumps and the venturi tubes. The
motive flow system includes the fuel filters, check valves, and venturi.
C. Standby Fuel−Feed System
(1) The standby fuel−feed system is used to supply fuel to the engines during the
engine start sequence. The standby fuel−feed system also controls the flow of fuel
to the engines in case of a failure of the engine fuel−feed system. The standby
fuel−feed system includes electric boost pumps and check valves.
D. APU Fuel−Feed System
(1) The APU fuel−feed system controls the flow of fuel from the main tanks to the APU.
This system includes an electric fuel pump, check valves, and a firewall shutoff
valve. The electric fuel pump is also used for automatic power crossflow to move
fuel during a fuel imbalance.
E. Pressure Refuel/Defuel System
(1) The pressure refuel/defuel system controls the flow of fuel from the pressure
refueling equipment to the fuel tanks. It also controls the flow of fuel during
defueling. This system includes a single−point refuel adapter, a two−way check
valve, shutoff valves, restrictors, fuel sensors, and a control panel.
3. Operation
Refer to Figure 1.
A. Engine Fuel−Feed System
(1) Fuel is supplied to each engine from the related main fuel tank. Motive pressure is
supplied to the primary ejector pumps which move fuel from the collector tanks to
the engine feed manifolds. Fuel flows out of the fuel tanks through these manifolds,
and into the engine feed lines which are connected to the engines.

Master
EFFECTIVITY: See Pageblock 28−20−00 page 1
28−20−00 Page 1
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
(2) In case of an engine fire, the engine feed lines are installed with engine−fuel−feed
shutoff valves. A switch/light in the flight compartment lets the operator close this
valve and stop the flow of fuel to the engine.
B. Motive Flow System
(1) Motive pressure is used to operate the ejector pumps in the engine fuel−feed
system and the transfer system (28−13−00). Motive pressure also helps the gravity
flow of fuel to the collector tanks. To make motive pressure, an engine−driven fuel
pump supplies fuel pressure to a filter which prevents the flow of ice crystals to the
smaller ejector pumps. From the filter, motive pressure flows through the motive
flow system to supply motive pressure.
(2) A venturi with two pressure ports is also installed in the motive flow lines. The
pressure ports are connected to a differential pressure switch which lets the
warning system (28−42−00) monitor the motive pressure.
C. Standby Fuel−Feed System
(1) A switch/light in the flight compartment lets the operator operate the boost pumps
that move fuel from the collector tanks to the engine feed manifold for engine start.
During a failure of the engine fuel−feed system, fuel is supplied to the engines by
the standby fuel−feed system.
D. APU Fuel−Feed System
(1) Fuel is supplied to the APU from the two main tanks. A switch/light in the flight
compartment lets the operator operate the APU fuel pump which moves fuel from
the main tanks to the APU feed manifold. Fuel flows out of the fuel tanks through
this manifold, and into the APU feed line which is connected to the APU.
(2) In case of an APU fire, the APU feed line is installed with an APU−fuel−feed shutoff
valve. A switch/light in the flight compartment lets the operator close this valve and
stop the flow of fuel to the APU.
(3) In case of a failure of the APU fuel−feed system, the APU feed manifold is installed
with a relief valve connected to the right engine feed manifold. If the pressure in the
APU feed manifold is less than the pressure in the right engine feed manifold, fuel
flows through the relief valve. This fuel is supplied to the APU.
E. Pressure Refuel/Defuel System
(1) The fuel system is pressure refueled through a single−point adapter behind the right
wing−to−fuselage fairing. The refuel operation is controlled and monitored by the
operator at the refuel/defuel control panel. When the operator sets the necessary
fuel quantity and starts the refuel operation, fuel flows through the refuel/defuel
manifold. When the refuel shutoff valves open, the fuel flows into the selected fuel
tanks.
(2) As fuel flows into the fuel tanks, fuel quantity is monitored by the fuel−quantity
gauging system (28−41−00). If the operator does an automatic refuel operation, the
fuel system computer closes the refuel shutoff valves when the correct amount of
fuel is supplied. If the operator does a manual refuel operation, the operator closes
each refuel shutoff valve with a switch at the refuel/defuel control panel.
(3) When any of the fuel tanks are full, the related high−level sensor sends a signal to
the fuel system computer to stop the flow of fuel to that tank. The fuel system
computer closes the applicable refuel shutoff valve to prevent a fuel spill.

Master
EFFECTIVITY: See Pageblock 28−20−00 page 1
28−20−00 Page 2
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
(4) The aircraft is also suction defueled through the single−point adapter. The operator
controls the defuel operation at the refuel/defuel control panel. The refuel shutoff
valves are opened and closed by the operator as necessary to remove the fuel.

Master
EFFECTIVITY: See Pageblock 28−20−00 page 1
28−20−00 Page 3
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

FUEL
QUANTITY
GAUGING
SYSTEM RIGHT MAIN
(28−41−00) TANK
STANDBY
FUEL
FEED
ENGINE
PRESSURE FUEL ENGINE
REFUEL/ FEED
DEFUEL
MOTIVE
FLOW

CENTER
WING
BOX

TRANSFER APU
SYSTEM FUEL APU
(28−13−00) FEED

LEFT MAIN
TANK
MOTIVE
FLOW

ENGINE
FUEL ENGINE
FEED
STANDBY
ram2820000_001(2).dg, ks, 11/07/95

FUEL
FUEL
FEED
WARNING
SYSTEM
(28−42−00)

Distribution System − Block Diagram

Figure 1

Master
EFFECTIVITY: See Pageblock 28−20−00 page 1
28−20−00 Page 4
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C ALL
SHROUD, FUEL LINES − REMOVAL/INSTALLATION

1. General
A. Refer to Figure 401.
The maintenance procedures that follow are for the removal and installation of the fuel
lines shroud (written as shroud in this procedure). The shroud is found below the cabin
floor and between FS559.00 and FS621.00. It contains the left and right engine fuel feed
lines, the left and right motive flow lines and the APU fuel feed line. If a fuel leak occurs,
the fuel will be contained by the shroud and vented overboard. When a fuel leak occurs,
it is possible to remove only part of the shroud to find the leak.
The shroud has been divided into five assemblies. These are the common fuel−feed
assembly, the left engine fuel−feed assembly, the right engine fuel−feed assembly and
the aft APU fuel−feed assembly. The four fuel−feed assemblies are connected by the
cross adapter assembly at FS559.00 +112.

TASK 28−20−01−000−801
Removal of the Fuel Lines Shroud (FS559.00 to FS621.00)

1. Job Set−Up Information

Subtask 28−20−01−943−007
A. Tools and Equipment
REFERENCE DESIGNATION
None Specified Fuel Container

Subtask 28−20−01−946−004
B. Reference Information
REFERENCE DESIGNATION
TASK 12−11−28−650−804 Suction Defueling
TASK 20−30−00−910−802 Wiggins Couplings − Maintenance Practices
TASK 21−22−01−000−801 Removal of the Mainfeed Manifold
TASK 28−00−00−910−801 Fuel Safety Precautions
TASK 53−01−01−000−802 Removal of the Passenger Compartment Floor
Panels (FS559.00 to 559+80)
TASK 53−01−01−000−804 Removal of the Cargo Compartment Floor Panels
(FS559+80 to 621.00)

Master
EFFECTIVITY: See Pageblock 28−20−01 page 401
28−20−01 Page 401
Sep 10/2004
 C
AIRCRAFT MAINTENANCE MANUAL
2. Job Set−Up
Subtask 28−20−01−910−004
WARNING: OBEY ALL THE FUEL SAFETY PRECAUTIONS WHEN YOU DO WORK ON THE
FUEL SYSTEM AND/OR A FUEL SYSTEM COMPONENT. IF YOU DO NOT DO
THIS, YOU CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO
EQUIPMENT.
A. Obey all the fuel safety precautions (Ref. TASK 28−00−00−910−801).

Subtask 28−20−01−650−007
B. Defuel the aircraft (Ref. TASK 12−11−28−650−804).

Subtask 28−20−01−865−009
C. Open, safety, and tag the circuit breakers that follow:
CB PANEL CB NO. NAME ZONE
CBP−1 M6 L FUEL PUMP 221
CBP−1 M7 L FUEL PUMP CONT 221
CBP−1 M12 FUEL SYST CONT 221
CBP−1 N10 XFER/APU FUEL PUMP 221
CBP−2 G10 R FUEL PUMP 222
CBP−2 G11 R FUEL PUMP CONT 222
CBP−4 B10 FUEL SYST CONT 222

Subtask 28−20−01−010−009
D. When applicable, remove the passenger compartment center floor panels between
FS559.00 and FS559+80. This to get access to the pressure−box installation,
under−floor fuel shroud and the common fuel feed subassembly (Ref. TASK
53−01−01−000−802).

Subtask 28−20−01−010−010
E. When applicable, remove the cargo compartment floor panels between FS559+80 and
FS621.00. This to get access to the left and right engine fuel−feed shroud
subassemblies, the cross adapter subassembly and the APU fuel−feed sub assembly
(Ref. TASK 53−01−01−000−804).

Subtask 28−20−01−010−011
F. When applicable, remove the center cross beam at FS589, between LBL9.0 and
RBL9.0. This to let the removal and installation of the left and right engine fuel−feed
shroud subassemblies (Ref. TASK 21−22−01−000−801). Keep all the hardware.
G. When applicable, remove the mainfeed manifold (Ref. TASK 21−22−01−000−801). The
mainfeed manifold (also referred to as the air conditioning distribution manifold) is
installed below the cargo compartment floor.

Master
EFFECTIVITY: See Pageblock 28−20−01 page 401
28−20−01 Page 402
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
3. Procedure
NOTE: Some of the steps in the procedures that follow are repeated. This is because it is
possible to remove only a part of the shroud and fuel line.
NOTE: For the procedures for the removal and installation of Wiggins couplings, refer to
Wiggins Couplings − Maintenance Practices (Ref. TASK 20−30−00−910−802)
Subtask 28−20−01−020−001
Refer to Figure 402.
**ON A/C ALL
A. When applicable, remove the aft APU fuel−feed assembly, as follows:
(1) Remove the two screws (1), the two washers (2) and the two clamps (3) from the
APU line assembly (4).
(2) Unscrew the slider assembly (5) cap and lift up.
(3) Move the body of the slider assembly (5) down.
(4) Remove the clamshell assembly (6) from the APU fuel−feed tube (7), as follows:
(a) Release the latch and remove the clamshell (6).
(b) Remove and discard the preformed packing (8) from the APU fuel−feed
tube (7).
(5) Remove the retainer ring (9) from under the slider assembly (5) cap, then remove
the cap.
(6) Remove the retainer ring (9) from inside the slider assembly (5) body, then remove
the body.
(7) Remove and discard the two preformed packings (10) from the APU line
assembly (4).
(8) Remove the clamshell assembly (11) from the cross adaptor (12) and the APU line
assembly (4), as follows:
(a) Release the latch and remove the clamshell (11).
NOTE: Use a suitable container to catch any residual fuel inside the
disconnected fuel tube.
(9) Do the steps that follow to disconnect the slider assembly (13) from the cross
adaptor assembly (12):
(a) Remove the coupling assembly (14) from the cross adaptor (12) and the slider
assembly (13), as follows:
1 Release the latch and remove the retainer.
2 Move the sleeve over the cross adaptor (12) to expose the preformed
packings (15) and open the connection.
(b) Loosen the nut assembly (16) that is screwed into the slider assembly (13).
Move the slider assembly forward.
NOTE: Use a suitable container to catch any residual fuel inside the
disconnected shroud assembly.
(10) Remove the clamshell assembly (17) from the APU fuel−feed tube (7) connection,
as follows:

Master
EFFECTIVITY: See Pageblock 28−20−01 page 401
28−20−01 Page 403
Aug 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
(a) Release the latch and remove the clamshell (17).
(b) Remove and discard the two preformed packings (18) from the APU fuel−feed
tube (7).
(11) Carefully pull the spacer (19), along the fuel tubes and out of the cross
adaptor (12).
(12) Carefully withdraw the APU fuel−feed tube (7) out of the cross adaptor (12).
(13) Remove the APU line assembly (4) from the fuselage.
(14) Remove and discard the preformed packing (20) from the APU line assembly (4).
(15) Remove the jam nut (21), shroud cup (22) and sealing washer (23) to disconnect
the APU line assembly (4) at the bulkhead fitting.
(16) Install blanking caps on the APU line assembly (4) and the APU fuel feed tube (7)
to prevent the ingress of foreign objects.

Subtask 28−20−01−020−002
Refer to Figure 403.
B. When applicable, remove the cross adaptor assembly, as follows:
(1) Do the steps that follow to disconnect the cross adaptor assembly from the
common shroud assembly:
(a) Remove the coupling assembly (1) from the cross adaptor (2), as follows:
1 Release the latch and remove the retainer.
2 Move the sleeve away from the flanges to expose the preformed packings
(3) and open the connection.
(b) Loosen the nut assembly (4) and move the slider assembly (5) forward.
(c) Disconnect and remove the unions (6) from the motive−flow tubes (7).
NOTE: Use a suitable container to catch any residual fuel inside the
disconnected fuel tube.
(2) Remove the clamshell assembly (8) from the APU fuel−feed tube (9) connection, as
follows:
(a) Release the latch and remove the clamshell (8).
(b) Remove and discard the preformed packing (10) from the APU fuel−feed
tube (9).
(c) Remove the coupling assemblies (11) from the engine fuel−feed tubes (12), as
follows:
1 Release the latches and remove the retainers.
2 Move the sleeves off of the engine fuel−feed tubes (12).
NOTE: Use a suitable container to catch any residual fuel inside the
disconnected fuel tubes.
(d) Remove and discard the four preformed packings (13), one at each open end
of the engine fuel−feed tubes (12).
(e) Remove and keep the sleeves with their coupling assemblies (11).
(f) Remove and discard the preformed packings (3) from the cross adaptor (2)
and the slider assembly (5).

Master
EFFECTIVITY: See Pageblock 28−20−01 page 401
28−20−01 Page 404
Sep 10/2004
 C
AIRCRAFT MAINTENANCE MANUAL
(3) Do the steps that follow to disconnect the APU line assembly from the cross
adaptor assembly:
(a) Remove the clamshell assembly (14) from the cross adaptor (2) and the APU
line assembly (15), as follows:
1 Release the latch and remove the clamshell (14).
NOTE: Use a suitable container to catch any residual fuel inside the
disconnected fuel tube.
(b) Unscrew the slider assembly (16) cap and lift up.
(c) Move the body of the slider assembly (16) down.
(d) Remove the clamshell assembly (17) from the APU fuel−feed tube (9), as
follows:
1 Release the latch and remove the clamshell (17).
2 Remove and discard the preformed packing (18) from the APU fuel−feed
tube (9).
(e) Remove the retainer ring (19) from under the slider assembly (16) cap, then
remove the cap.
(f) Remove the retainer ring (19) from inside the slider assembly (16) body, then
remove the body.
(g) Remove and discard the two preformed packings (20) from the APU line
assembly (15).
(4) Do the steps that follow to disconnect the slider tube assemblies and fuel lines from
the cross adaptor assembly:
NOTE: The procedure that follows is for the slider tube and fuel lines on the left
side. The procedure for the slider tube on the right side is the same.
(a) Remove the coupling assembly (21) from the elbow assembly (22) and the
slider assembly (23), as follows:
1 Release the latch and remove the retainer.
2 Move the sleeve over the elbow assembly (23) to expose the preformed
packings (24) and open the connection.
(b) Loosen the nut assembly (25) that is screwed into the slider assembly (23).
Move the slider assembly inboard over the slider tube (26).
(c) Disconnect and remove the union (27) from the left motive−flow tube (7).
NOTE: Use a suitable container to catch any residual fuel inside the
disconnected fuel tube.
(d) Remove the coupling assembly (28) from the left engine fuel−feed tube (12),
as follows:
1 Release the latch and remove the retainer.
2 Move the sleeve off of the engine fuel−feed tube (12).
NOTE: Use a suitable container to catch any residual fuel inside the
disconnected fuel tube.
(e) Remove and discard the two preformed packings (29) from each open end of
the engine fuel−feed tube (12).

Master
EFFECTIVITY: See Pageblock 28−20−01 page 401
28−20−01 Page 405
Sep 10/2004
 C
AIRCRAFT MAINTENANCE MANUAL
(f) Remove and keep the sleeves with their coupling assemblies (21 and 28).
(g) Remove and discard the two preformed packings (24) from the elbow
assembly (22) and slider assembly (23).
(h) Disconnect the LH drain line (30) union at the cross adaptor (2) and fuselage
fitting.
(i) Do these steps again for the right side.
(j) Remove two screws (31) and two washers (32) from the cross adaptor (2) and
bracket assembly (33).
(5) Lift out the cross adaptor assembly from the fuselage, through the opening at
FS559+112 and FS574. Be careful not to damage the APU fuel−feed tube (9),
when you remove the cross adaptor assembly. Place the cross adaptor assembly
on a clean dry work surface.
(6) Install blanking caps on the open fuel tubes at FS559+112 to prevent the ingress of
foreign objects.
(7) Do the steps that follow to complete removal of the cross adaptor:
(a) Remove the two coupling assemblies (34) from the cross adaptor (2) and two
slider tube assemblies (26), as follows:
1 Release the latch and remove the retainer.
2 Move the sleeve over the slider tube to expose the two preformed
packings (35).
(b) Remove the two slider tube assemblies (26) from the cross adaptor (2).
(c) Remove the fuel tubes out of the spacer (36) and the spacer out of the cross
adaptor (2).
(d) Remove the two motive flow tubes (7) and the two engine fuel−feed tubes (12)
from the cross adaptor (2).
(e) Remove and keep the sleeves with their coupling assembly (34).
(f) Remove the APU fuel−feed tube (9) from the cross adaptor (2).
(g) Remove and discard the preformed packing (37) from the APU line
assembly (15).
(h) Remove the nut assembly (25) from the slider assembly (23).
(i) Remove the washer assembly (38), preformed packing (39) and one more
washer assembly (38) from inside the slider assembly (23).

Subtask 28−20−01−020−003
Refer to Figure 404.
C. When applicable, remove the left or the right engine fuel−feed assembly, as follows:
NOTE: The procedure to remove the right engine fuel−feed assembly is the same as
that for the left engine fuel−feed assembly.
(1) Remove the four screws (1), the four washers (2), and the two saddle clamps (3)
that hold the LH shroud assembly (4) to the fuselage mounts.
(2) Remove the two screws (5), the two washers (6) and the saddle clamp (7) that hold
LH shroud assembly (4) to the fuselage mounts.

Master
EFFECTIVITY: See Pageblock 28−20−01 page 401
28−20−01 Page 406
Sep 10/2004
 C
AIRCRAFT MAINTENANCE MANUAL
(3) Remove two screws (8), the two washers (9) and the saddle clamp (10) that hold
the heat shield (11) and the elbow assembly (12) to the fuselage mount. Remove
the heat shield.
(4) Remove the coupling assembly (13) from the forward end of the LH shroud
assembly (4) and the elbow assembly (12) as follows:
(a) Release the latch and remove the retainer.
(b) Move the sleeve away from the ferrule to expose the two preformed
packings (14).
(5) Remove the coupling assembly (15) from the elbow assembly (12) and the slider
assembly (16), as follows:
(a) Release the latch and remove the retainer.
(b) Move the sleeve away from the ferrule to expose the two preformed
packings (17) and open the connection.
(6) Unscrew the nut assembly (18) from the slider assembly (16).
(7) Move the slider assembly (16) over the slider tube assembly (19).
(8) Disconnect and remove the union (20) from the motive flow fuel−feed tube (21).
NOTE: Use a suitable container to catch any residual fuel inside the
disconnected fuel tube.
(9) Remove the coupling assembly (22) from the engine fuel−feed tube (23), as follows:
(a) Release the latch and remove the retainer.
(b) Move the sleeve from the engine fuel−feed tube (23).
(10) Remove and discard the two preformed packings (24) from each open end of the
engine fuel−feed tube (23).
NOTE: Use a suitable container to catch any residual fuel inside the
disconnected fuel tube.
(11) Remove and keep the sleeves with their coupling assemblies (13) and (22).
(12) Remove and discard the preformed packings (17) from the elbow assembly (12)
and the slider assembly (16).
**ON A/C 7003−7067, 7069−7334
(13) Remove the spacer (25), inside the LH shroud assembly (4), from around the
motive flow fuel−feed tube (21) and the engine fuel−feed tube (23).
**ON A/C 7335−7990, 8000−8064, 8066−8068
(14) Cut the tie wrap (34) from inside the elbow assembly (12), then remove and
discard.
(15) Cut the second tie wrap (34), behind the spacer (25), inside the elbow
assembly (12), then remove and discard.
(16) Remove the spacer (25), inside the elbow assembly (12), from around the motive
flow fuel−feed tube (21) and the engine fuel−feed tube (23).
**ON A/C ALL
(17) Remove the elbow assembly (12) from around the motive flow fuel−feed tube (21)
and engine fuel−feed tube (23).

Master
EFFECTIVITY: See Pageblock 28−20−01 page 401
28−20−01 Page 407
Dec 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
(18) Remove the insulation material from around and under the drain line (26) at FS608.
(19) Disconnect the drain line (26) from the fitting (27).
(20) Disconnect the drain line (26) from the elbow fitting (28).
(21) Remove the aft coupling assembly (29) from the flange assembly (30) at FS621, as
follows:
(a) Release the latch and remove the retainer.
(b) Move the sleeve over the flange assembly (30) towards the bulkhead to
expose the preformed packings (31).
(22) Disconnect the motive flow fuel−feed tube (21) from the fitting inside the flange
assembly (30).
NOTE: Use a suitable container to catch any residual fuel inside the
disconnected fuel tube.
(23) Remove the coupling assembly (32) from the engine fuel−feed tubes (23), as
follows:
(a) Release the latch and remove the retainer.
(b) Move the sleeve from the engine fuel−feed tube (23).
(24) Remove and discard the two preformed packings (33) from each open end of the
engine fuel−feed tube (33).
NOTE: Use a suitable container to catch any residual fuel inside the
disconnected fuel tube.
(25) Remove and keep the sleeves with their coupling assemblies (29) and (32).
(26) Remove and discard the preformed packings (31).
(27) Remove the left engine fuel−feed shroud assembly from the fuselage through the
opening at FS559+112 and FS574.
(28) Install blanking caps on the open fuel tubes at FS621 and FS574 to prevent the
ingress of foreign objects.

Subtask 28−20−01−020−004
**ON A/C 7003−7067, 7069−7990, 8000−8026
Refer to Figure 405.
**ON A/C 8027−8064, 8066−8068
Refer to Figure 406.
**ON A/C ALL
D. When applicable, remove the common fuel feed assembly, as follows:
(1) Remove the screws (1), the washers (2), the spacers (3) and the saddle clamp (4)
that hold the common shroud assembly to the fuselage mounts.
(2) Remove the screws (5), the washers (6), the spacers (7) and the three saddle
clamps (8) that hold the common shroud assembly to the fuselage mounts.
(3) Remove the insulation material from around and under the drain line (9).
(4) Disconnect the drain line (9) at the shroud assembly drain union (10) and the
fuselage drain union (11). Remove the drain line from the aircraft.

Master
EFFECTIVITY: See Pageblock 28−20−01 page 401
28−20−01 Page 408
Dec 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
(5) Do the steps that follow to disconnect the slider assembly from the cross adaptor
assembly:
(a) Remove the coupling assembly (12) from the cross adaptor (13) and the slider
assembly (14), as follows:
1 Release the latch and remove the retainer.
2 Move the sleeve over the cross adaptor (13) to expose the preformed
packings (15) and open the connection.
(b) Loosen the nut assembly (16) that is screwed into the slider assembly (14).
Move the slider assembly forward.
NOTE: Use a suitable container to catch any residual fuel inside the
disconnected shroud assembly.
(6) Do the steps that follow to disconnect the slider assembly from the shroud
assembly:
(a) Remove the coupling assembly (17) from the shroud assembly (18) and the
slider assembly (19), as follows:
1 Release the latch and remove the retainer.
2 Move the sleeve over the shroud assembly (18) to expose the preformed
packings (20) and open the connection.
(b) Loosen the nut assembly (21) that is screwed into the slider assembly (19).
Move the slider assembly aft.
(7) Remove the coupling assembly (22) from the tube assembly (23) and the shroud
assembly (18), as follows:
(a) Release the latch and remove the retainer.
(b) Move the sleeve over the shroud assembly (18) to expose the preformed
packings (24) and open the connection.
(8) Remove the coupling assembly (25) from the transition shroud (26) and the tube
assembly (23), as follows:
(a) Release the latch and remove the retainer.
(b) Move the sleeve over the tube assembly (23) to expose the preformed
packings (27) and open the connection.
(9) Disconnect the transition shroud (26) from the pressure box (28), as follows:
(a) Remove the five screws (29), the five washers (30) and the bottom flange plate
(31) from the flange of the transition shroud (26).
(b) Remove the five screws (29), the five washers (30) and the top flange plate
(32) from the flange of the transition shroud (26).
(c) Pull the transition shroud (26), together with the gasket (33) from the pressure
box (28).
(10) Cut and remove the tie wrap (34), installed in the transition shroud (26), which
keeps the forward fuel tubes in place.
(11) Place a suitable container under the fuel feed tubes, close to the cross adaptor
assembly (13). This to collect the fuel in the fuel feed tubes, when the tubes are
disconnected.

Master
EFFECTIVITY: See Pageblock 28−20−01 page 401
28−20−01 Page 409
Aug 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
(12) Disconnect the fuel feed tubes closest to the cross adaptor assembly, as follows:
(a) Disconnect the two motive flow fuel−feed tubes (35).
(b) Remove the coupling assemblies (36) from the engine fuel−feed tubes (37), as
follows:
1 Release the latches and remove the retainers.
2 Move the sleeves from the engine fuel−feed tubes (37).
(c) Remove and discard the four preformed packings (38) from each open end of
the engine fuel−feed tubes (37).
(d) Remove and keep the three sleeves with their coupling assemblies (36)
and (12).
(e) Remove the coupling assembly (39) from the APU fuel−feed tube (40), as
follows:
1 Release the latch and remove the retainer.
2 Move the sleeve from the APU fuel−feed tube (40).
(f) Remove and discard the two preformed packings (41) from each open end of
the APU fuel−feed tube (40).
(g) Remove and keep the sleeve with the coupling assembly (39).
(13) Disconnect the fuel feed tubes at the shroud assembly to slider assembly
connection, as follows:
(a) Disconnect the two motive flow tubes (35).
(b) Remove the coupling assemblies (42) from the engine fuel−feed tubes (37), as
follows:
1 Release the latches and remove the retainers.
2 Move the sleeves from the engine fuel−feed tubes (37).
(c) Remove and discard the four preformed packings (43) from each open end of
the engine fuel−feed tubes (37).
(d) Remove and keep the three sleeves with their coupling assemblies (42)
and (17).
(e) Remove the coupling assembly (44) from the APU fuel−feed tube (40), as
follows:
1 Release the latch and remove the retainer.
2 Move the sleeve from the APU fuel−feed tube (40).
(f) Remove and discard the two preformed packings (45) from each open end of
the APU fuel−feed tube (40).
(g) Remove and keep the sleeve with the coupling assembly (44).
(14) Disconnect the fuel tubes at the pressure box, as follows:
(a) Disconnect the two motive flow fuel−feed tubes (35).
(b) Remove the two coupling assemblies (46) from the engine fuel−feed
tubes (37), as follows:
1 Release the two latches and remove the two retainers.
2 Move the two sleeves from the two engine fuel−feed tubes (37).

Master
EFFECTIVITY: See Pageblock 28−20−01 page 401
28−20−01 Page 410
Aug 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
(c) Remove and discard the four preformed packings (47) from the ends of the
two engine fuel−feed tubes (37).
(d) Remove and keep the two sleeves with their coupling assemblies (46).
(e) Remove the coupling assembly (48) from the APU fuel−feed tube (40), as
follows:
1 Release the latch and remove the retainer.
2 Move the sleeve from the APU fuel−feed tube (40).
(f) Remove and discard the two preformed packings (49) from the ends of the
APU fuel−feed tube (40).
(g) Remove and keep the sleeve with the coupling assembly (48).
(15) Remove and discard the gasket (33) from the transition shroud (26), or pressure
box (28) flange, as applicable.
**ON A/C 8027−8064, 8066−8068
(16) Remove the spacer (57).
**ON A/C ALL
(17) Remove all of the common shroud assembly components through the floor cross
members and out of the aircraft.
(18) Disassemble the two slider assemblies, as follows:
(a) Unscrew and remove the nut assemblies (16) and (21) from both slider
assemblies (14) and (19).
(b) Remove the two washer assemblies (50) and (51).
(c) Remove and discard the two preformed packings (52) and (53).
(d) Remove two more washer assemblies (50) and (51).
(19) Remove the spacer (54) from the tube assembly (23).
(20) Remove the spacer (55) from the shroud assembly (18).
(21) Install blanking caps on the ends of all of the open fuel tubes and the drains to
prevent the ingress of foreign objects.
(22) Install blanking caps on the pressure box fuel−feed tubes.

Master
EFFECTIVITY: See Pageblock 28−20−01 page 401
28−20−01 Page 411
Dec 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL

LEGEND
1. Common fuel−feed assrmbly.
2. Left/Rght engine fuel feed assembly.
3. APU fuel−feed assembly.
4. Cross adapter assembly.
FS621.00

2
FS559.00
3

2
ram2820014_001.dg, gg/rm, 16/12/99

Fuel Shroud and Fuel Lines Assembly

Figure 401

Master
EFFECTIVITY: See Pageblock 28−20−01 page 401
28−20−01 Page 412
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

LEGEND
1. Screw. 12. Cross adapter.
2. Washer. 13. Slider assembly.
3. Clamp. 14. Coupling assembly.
4. APU line assembly. 15. Preformed packing.
5. Slider assembly. 16. Nut assembly.
6. Clamshell. 17. Clamshell.
D
7. Fuel feed tube. 18. Preformed packing.
C E 8. Preformed packing. 19. Spacer.
A 9. Retainer ring. 20. Preformed packing.
10. Preformed packing 21. Jam nut.
11. Clamshell. 22. Shroud cup.
23. Sealing washer.
14
15
19

16 18 12

13
7
15
5 17 18 7 4
A
4

9 20
11 B
10
7
8 4
6 12

10

B
4
BULKHEAD
621.00
9 (REF)
2
ram2820014_002.dg, jp/rm, 14/12/99

23 1
22
5
4 21
3

C D E

APU Fuel−Feed Assembly

Figure 402

Master
EFFECTIVITY: See Pageblock 28−20−01 page 401
28−20−01 Page 413
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

LEGEND
1. Coupling. 11. Coupling assembly.
2. Cross adapter. 12. Engine fuel−feed tube.
3. Preformed packing. 13. Preformed packing.
4. Nut assembly. 14. Clamshell.
5. Slider assembly. 15. APU line assembly.
6. Union. 16. Slider assembly
7. Motive flow fuel− 17. Clamshell.
feed tube. 18. Preformed packing.
G 8. Clamshell. 19. Retainer ring.
9. APU fuel−feed tube. 20. Preformed packing.
F
10. Preformed packing. 37. Preformed packing.

12

16
4
7
13 15
3 6 11
13
19

5 11 20

18 9
3
12 13
1 9 13 17

3 20
8
10

15

19
ram2820014_004.dg, jp/rm, 16/12/99

2
15
16

9
37
14 G
F

Cross Adaptor Assembly

Figure 403 (Sheet 1 of 2)

Master
EFFECTIVITY: See Pageblock 28−20−01 page 401
28−20−01 Page 414
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

LEGEND
2. Cross adapter. 25. Nut assembly.
7. Motive flow fuel− 26. Slider tube assembly.
feed tube. 27. Union.
12. Engine fuel−feed 28. Coupling assembly.
tube. 29. Preformed packing.
21. Coupling assembly. 30. Drain line.
22. Elbow assembly. 31. Screw.
23. Slider assembly. 32. Washer.
24. Preformed packing. 33. Bracket assembly.
34. Coupling assembly.
34
35. Preformed packing.
H 35 36. Spacer.
36 37. Preformed packing.
2
38. Washer assembly.
39. Preformed packing.
40. Cushion.
35
34
NOTE
35 LH side is shown
26 RH side is opposite.
31
25 32

30

23
27 30
40
38
7
39
38 33
29
28
29
D
INB
12 ram2820014_005.dg, jp/rm, 16/12/99

24
7
21
24
22 FS559.00 +112
12 H (REF)

Cross Adaptor Assembly

Figure 403 (Sheet 2 of 2)

Master
EFFECTIVITY: See Pageblock 28−20−01 page 401
28−20−01 Page 415
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

L LEGEND
1. Screw.
K 2. Washer.
J 3. Saddle clamp.
D 4. LH shroud assembly.
INB
5. Screw.
21 6. Washer.
16 7. Saddle clamp.
FS 559.00
L 20 8. Screw.
+112 K 17 9. Washer.
(REF) J 10. Saddle clamp.
11 24 11. Heat shield.
17 12. Elbow assembly.
12 22
24 13. Coupling assembly.
14. Preformed packing.
23 15. Coupling assembly.
16. Slider assembly.
17. Preformed packing.
15 18. Nut assembly.
19. Slider tube assembly.
9 20. Union.
8 19 21. Motive flow fuel− feed tube.
10
34 18 22. Coupling assembly.
23. Engine fuel−feed tube.
12 5 24. Preformed packing.
6 25. Spacer.
7
26. Drain line.
WL 58.87 27. Fitting.
(REF) 28. Elbow fitting.
NOTE 4 29. Coupling assembly.
LH side is shown 25 30. Flange assembly.
RH side is opposite. 14 31. Preformed packing.
1 13 32. Coupling assembly.
14 33. Preformed packing.
2 34. Tie wrap.
7
3 33
LBL 31.11
(REF) J 31
FS
621.00
31 (REF)
ram2820014_006.dg, jp/rm, 16/12/99

4
3
30
4 32
26 23

27 28 29
K L

Left/Right Engine Fuel−Feed Assembly

Figure 404

Master
EFFECTIVITY: See Pageblock 28−20−01 page 401
28−20−01 Page 416
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

LEGEND
1. Screw. 8. Saddle clamp.
2. Washer. 9. Drain line.
3. Spacer. 10. Shroud assembly
4. Saddle clamp. drain union.
5. Screw. 11. Fuselage drain union.
6. Washer. 18. Shroud assembly.
7. Spacer.

3 1
2
3
4

N
M
P

SHROUD
ASSEMBLY
(REF) 18
4

8
5
7 6 10
7

11 9
ram2820014_007.dg, gg/rm, 16/12/99

SLIDER D
4 INB
ASSEMBLY
(REF)

RBL 9.12
N (REF) P

Common Fuel−Feed Assembly − Removal/Installation

Figure 405 (Sheet 1 of 3)

Master
EFFECTIVITY: See Pageblock 28−20−01 page 401
28−20−01 Page 417
Aug 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL

LEGEND
10. Shroud assembly
drain union.
R NOTE 14. Slider assembly.
Left side is shown, 16. Nut assembly.
right side is opposite. 17. Coupling assembly.
18. Shroud assembly.
19. Slider assembly.
20. Preformed packing.
32 30 29 34
25 21. Nut assembly.
22. Coupling assembly.
33 23. Tube assembly.
24. Preformed packing.
25. Coupling assembly.
26. Transition shroud.
27. Preformed packing.
28. Pressure box.
29. Screw.
26 27 30. Washer.
31 31. Bottom flange plate.
32. Top flange plate.
33. Gasket.
22 34. Tie wrap.
28 50. Washer assembly.
24 51. Washer assembly.
52. Preformed packing.
53. Preformed packing.
27 54. Spacer.
54 55. Spacer.
23
INB 24 56. Shroud assembly.
D

51

19

20 14
17
ram2820014_008.dg, gg/rm, 16/12/99

20
55 50
51 52
18 53 50
10 16
56

R 21

Common Fuel−Feed Assembly − Removal/Installation

Figure 405 (Sheet 2 of 3)

Master
EFFECTIVITY: See Pageblock 28−20−01 page 401
28−20−01 Page 418
Aug 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL

LEGEND
12. Coupling assembly
U 13. Cross adapter
V 14. Slider assembly.
15. Preformed packing.
19. Slider assembly.
26. Transition shroud.
28. Pressure box.
35. Motive flow fuel−
feed tube.
T 37 36. Coupling assembly.
35
37. Engine fuel− feed tube.
38. Preformed packing.
38 39. Coupling assembly.
36 40. APU fuel−feed tube.
38
41. Preformed packing.
14 42. Coupling assembly.
43. Preformed packing.
41
39 44. Coupling assembly.
41 37
40 45. Preformed packing.
46. Coupling assembly.
47. Preformed packing.
48. Coupling assembly.
37 49. Preformed packing.
35
38
36
15
38
12
15
40
37
13
35 37
37 35 40 26
45
43 T
42
43
37 46 47
47
35
19 37

40
ram2820014_009.dg, jp/rm, 16/12/99

37
43
35 37
42
40 47
44 43 48 49 47 46
40 45 49
35
37 U 28 V

Common Fuel−Feed Assembly − Removal/Installation

Figure 405 (Sheet 3 of 3)

Master
EFFECTIVITY: See Pageblock 28−20−01 page 401
28−20−01 Page 419
Aug 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL

LEGEND
1. Screw. 8. Saddle clamp.
2. Washer. 9. Drain line.
3. Spacer. 10. Shroud assembly
4. Saddle clamp. drain union.
5. Screw. 11. Fuselage drain union.
6. Washer. 18. Shroud assembly.
7. Spacer.
1
3
2

3
4

SHROUD
ASSEMBLY
(REF) 18

8 5
7 6
10
7

11 9

D
INB
ram2820014_011.dg, rm, 26/05/05

4 SLIDER
ASSEMBLY
(REF)
RBL 9.12
(REF)

Common Fuel−Feed Assembly − Removal/Installation

Figure 406 (Sheet 1 of 3)

Master
EFFECTIVITY: See Pageblock 28−20−01 page 401
28−20−01 Page 420
Aug 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL

LEGEND
10. Shroud assembly
drain union.
NOTE 14. Slider assembly.
Left side is shown, 16. Nut assembly.
right side is opposite. 17. Coupling assembly.
18. Shroud assembly.
29 19. Slider assembly.
30 20. Preformed packing.
32 34
25 21. Nut assembly.
22. Coupling assembly.
33 23. Tube assembly.
24. Preformed packing.
25. Coupling assembly.
26. Transition shroud.
27. Preformed packing.
28. Pressure box.
29. Screw.
26 27 30. Washer.
31 31. Bottom flange plate.
32. Top flange plate.
33. Gasket.
22 34. Tie wrap.
28 50. Washer assembly.
24 51. Washer assembly.
52. Preformed packing.
53. Preformed packing.
27 54. Spacer.
54 55. Spacer.
23
INB 24 56. Shroud assembly.
D

51

19

20 14
20 17
ram2820014_012.dg, rm, 26/05/05

55 50
51 52
18 53 50
10 16
56
21

Common Fuel−Feed Assembly − Removal/Installation

Figure 406 (Sheet 2 of 3)

Master
EFFECTIVITY: See Pageblock 28−20−01 page 401
28−20−01 Page 421
Aug 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL

LEGEND
12. Coupling assembly
13. Cross adapter
14. Slider assembly.
15. Preformed packing.
19. Slider assembly.
26. Transition shroud.
28. Pressure box.
35. Motive flow fuel−
feed tube.
37 36. Coupling assembly.
35
37. Engine fuel− feed tube.
38. Preformed packing.
38 39. Coupling assembly.
36 40. APU fuel−feed tube.
38
41. Preformed packing.
14 42. Coupling assembly.
43. Preformed packing.
41
39 44. Coupling assembly.
41 37
40 45. Preformed packing.
46. Coupling assembly.
47. Preformed packing.
48. Coupling assembly.
37 49. Preformed packing.
35 57. Spacer.
38
36
15
38
12
15
40
37
37 40 13
35
37 35 40 26
45
43
42
43
37
46 47
35 47
19
28 37

37
ram2820014_013.dg, rm, 26/05/05

43
42 37
35 47
43 57 46
44
45 48 49 47
40
40 49
37 35

Common Fuel−Feed Assembly − Removal/Installation

Figure 406 (Sheet 3 of 3)

Master
EFFECTIVITY: See Pageblock 28−20−01 page 401
28−20−01 Page 422
Aug 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
TASK 28−20−01−400−801
Installation of the Fuel Lines Shroud (FS559 to 621)

1. Job Set−Up Information

Subtask 28−20−01−944−005
A. Consumable Materials
REFERENCE DESIGNATION
06−002 Petrolatum
B0816024−003 Tie wrap
11−028A DS−108 Wipe solvent
11−009 Alcohol
None specified Lint−free cloth

Subtask 28−20−01−945−003
B. Parts
Refer to Figure 402 for the parts required to install the APU fuel−feed assembly.
REF NAME OF PART QTY IPC SEQUENCE NO.
2 Screw 2 IPC 28−20−00−02−410
2 Washer 2 IPC 28−20−00−02−415
8 Packing. preformed 1 IPC 28−20−00−02−400
9 Ring, retainer 2 IPC 28−20−00−02−TBD
10 Packing, preformed 2 IPC 28−20−00−02−390
15 Packing, preformed 2 IPC 28−20−00−02−115
18 Packing, preformed 2 IPC 28−20−00−02−TBD
20 Packing, preformed 1 IPC 28−20−00−02−360
21 Nut, jam 1 IPC 28−20−00−02−430
22 Cup, shroud 1 IPC 28−20−00−02−425
23 Washer, sealing 1 IPC 28−20−00−02−420
C. Refer to Figure 403 for the parts required to install the cross adaptor assembly.
REF NAME OF PART QTY IPC SEQUENCE NO.
3 Packing, preformed 2 IPC 28−20−00−02−115
6 Union 2 IPC 28−20−00−02−225
10 Packing, preformed 2 IPC 28−20−00−02−TBD
13 Packing, preformed 4 IPC 28−20−00−02−040
18 Packing. preformed 1 IPC 28−20−00−02−400
19 Ring, retainer 2 IPC 28−20−00−02−TBD
20 Packing, preformed 2 IPC 28−20−00−02−390
24 Packing, preformed 4 IPC 28−20−00−02−205
27 Union 2 IPC 28−20−00−02−225

Master
EFFECTIVITY: See Pageblock 28−20−01 page 401
28−20−01 Page 423
Aug 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL

REF NAME OF PART QTY IPC SEQUENCE NO.

29 Packing, preformed 4 IPC 28−20−00−02−235
31 Screw 2 IPC 28−20−00−02−440
32 Washer 2 IPC 28−20−00−02−445
35 Packing, preformed 4 IPC 28−20−00−02−190
37 Packing, preformed 1 IPC 28−20−00−02−360
38 Washer assembly 4 IPC 28−20−00−02−220
39 Packing, preformed 2 IPC 28−20−00−02−215
40 Cushion 1 IPC 28−20−00−02−450
D. Refer to Figure 404 for the parts required to install the left or right engine fuel−feed
assembly.
REF NAME OF PART QTY IPC SEQUENCE NO.
1 Screw 4 IPC 28−20−00−02−340
2 Washer 4 IPC 28−20−00−02−345
5 Screw 4 IPC 28−20−00−02−340
6 Washer 4 IPC 28−20−00−02−345
8 Screw 4 IPC 28−20−00−02−245
9 Washer 4 IPC 28−20−00−02−250
14 Packing, preformed 4 IPC 28−20−00−02−205
17 Packing, preformed 4 IPC 28−20−00−02−205
20 Union 2 IPC 28−20−00−02−225
24 Packing, preformed 4 IPC 28−20−00−02−235
31 Packing, preformed 4 IPC 28−20−00−02−290
33 Packing, preformed 4 IPC 28−20−00−02−300
**ON A/C 7003−7067, 7069−7990, 8000−8026
E. Refer to Figure 405 for the parts required to install the common fuel−feed assembly.
REF NAME OF PART QTY IPC SEQUENCE NO.
1 Screw 6 IPC 28−20−00−02−155
2 Washer 6 IPC 28−20−00−02−160
5 Screw 1 IPC 28−20−00−02−155
6 Washer 1 IPC 28−20−00−02−160
15 Packing, preformed 2 IPC 28−20−00−02−115
20 Packing, preformed 2 IPC 28−20−00−02−115
24 Packing, preformed 2 IPC 28−20−00−02−055
27 Packing, preformed 2 IPC 28−20−00−02−055
29 Screw 10 IPC 28−20−00−02−010
30 Washer 10 IPC 28−20−00−02−015
33 Gasket 1 IPC 28−20−00−02−020
38 Packing, preformed 4 IPC 28−20−00−02−040

Master
EFFECTIVITY: See Pageblock 28−20−01 page 401
28−20−01 Page 424
Aug 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL

REF NAME OF PART QTY IPC SEQUENCE NO.

41 Packing, preformed 2 IPC 28−20−00−02−TBD
43 Packing, preformed 4 IPC 28−20−00−02−235
45 Packing, preformed 2 IPC 28−20−00−02−030
47 Packing, preformed 4 IPC 28−20−00−02−040
49 Packing, preformed 2 IPC 28−20−00−02−030
50 Washer Assembly 2 IPC 28−20−00−02−135
51 Washer Assembly 2 IPC 28−20−00−02−135
52 Packing, preformed 1 IPC 28−20−00−02−130
53 Packing, preformed 1 IPC 28−20−00−02−130
**ON A/C 8027−8064, 8066−8068
F. Refer to Figure 406 for the parts required to install the common fuel−feed assembly.
REF NAME OF PART QTY IPC SEQUENCE NO.
1 Screw 6 IPC 28−20−00−02−155
2 Washer 6 IPC 28−20−00−02−160
5 Screw 1 IPC 28−20−00−02−155
6 Washer 1 IPC 28−20−00−02−160
15 Packing, preformed 2 IPC 28−20−00−02−115
20 Packing, preformed 2 IPC 28−20−00−02−115
24 Packing, preformed 2 IPC 28−20−00−02−055
27 Packing, preformed 2 IPC 28−20−00−02−055
29 Screw 10 IPC 28−20−00−02−010
30 Washer 10 IPC 28−20−00−02−015
33 Gasket 1 IPC 28−20−00−02−020
38 Packing, preformed 4 IPC 28−20−00−02−040
41 Packing, preformed 2 IPC 28−20−00−02−TBD
43 Packing, preformed 4 IPC 28−20−00−02−235
45 Packing, preformed 2 IPC 28−20−00−02−030
47 Packing, preformed 4 IPC 28−20−00−02−040
49 Packing, preformed 2 IPC 28−20−00−02−030
50 Washer Assembly 2 IPC 28−20−00−02−135
51 Washer Assembly 2 IPC 28−20−00−02−135
52 Packing, preformed 1 IPC 28−20−00−02−130
53 Packing, preformed 1 IPC 28−20−00−02−130
57 Spacer 1 IPC 28−20−00−02−TBD

Master
EFFECTIVITY: See Pageblock 28−20−01 page 401
28−20−01 Page 425
Dec 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C ALL

Subtask 28−20−01−946−005
G. Reference Information
REFERENCE DESIGNATION
TASK 20−30−00−910−802 Wiggins Couplings − Maintenance Practices
TASK 21−22−01−400−801 Installation of the Mainfeed Manifold
TASK 28−00−00−710−801 Operational Test of The Fuel System
TASK 28−20−01−780−801 Pressure and Blockage Test of The Fuel Lines
Shroud
TASK 28−20−01−780−802 Pressure and Blockage Test of The Fuel Feed
Lines
TASK 28−20−01−780−803 Pressure and Blockage Test of the Motive
Flow−Fuel Line
TASK 28−20−01−780−804 Pressure and Blockage Test of the APU
Fuel−Feed Line
TASK 53−01−01−400−802 Installation of the Passenger Compartment Floor
Panels (FS559.00 to 559+80)
TASK 53−01−01−400−804 Removal of the Cargo Compartment Floor Panels
(FS559+80 to 621.00)

2. Job Set−Up
Subtask 28−20−01−910−005
WARNING: OBEY ALL THE FUEL SAFETY PRECAUTIONS WHEN YOU DO WORK ON THE
FUEL SYSTEM AND/OR A FUEL SYSTEM COMPONENT. IF YOU DO NOT DO
THIS, YOU CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO
EQUIPMENT.
A. Obey all the fuel safety precautions (Ref. TASK 28−00−00−910−801).

Subtask 28−20−01−869−001
B. Make sure that the aircraft is in the same configuration as in the removal task.

3. Procedure
NOTE: Some of the steps in the following procedures are repeated. This is because it is
possible that only a part of the shroud and fuel line was removed.
NOTE: For the procedures for the removal and installation of Wiggins couplings, refer to
Wiggins Couplings − Maintenance Practices (Ref. TASK 20−30−00−910−802)
Subtask 28−20−01−420−001
**ON A/C 7003−7067, 7069−7990, 8000−8026
Refer to Figure 405.

Master
EFFECTIVITY: See Pageblock 28−20−01 page 401
28−20−01 Page 426
Aug 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C 8027−8064, 8066−8068
Refer to Figure 406.
**ON A/C ALL
A. When applicable, install the common fuel feed assembly, as follows:
(1) Do the steps that follow to assemble the forward part of the common fuel feed
assembly, when necessary:
NOTE: The following steps may be done outside the aircraft.
(a) Remove the blanking caps from the engine fuel−feed tubes (37).
(b) Apply petrolatum to four preformed packings (47) and (43). Then install them
in the grooves in the engine fuel−feed tubes (37) at the transition shroud (26)
and the slider assembly (19) connections.
(c) Remove the blanking caps from the APU fuel−feed tube (40).
(d) Apply petrolatum to two preformed packings (49) and (45) and install in the
grooves in the APU fuel−feed tube (40) at the transition shroud (26) and slider
assembly (19) connections.
(e) Remove the blanking caps from the motive flow fuel−feed tubes (35).
(f) Apply petrolatum to the union threads on the motive flow fuel−feed tube (35)
unions at the transition shroud (26) and slider assembly (19) connections.
(g) Apply petrolatum to two preformed packings (27) and (24) and install in the
grooves at both ends of the tube assembly (23).
(h) Apply petrolatum to the preformed packing (27) and install in the groove in the
transition shroud (26).
(i) Apply petrolatum to two preformed packings (24) and (20) and install in the
grooves at both ends of the shroud assembly (18).
(j) Position the gasket (33) against the wrong side of the flange of the transition
shroud (26).
(k) Apply petrolatum to the spacers (54) and (55).
(l) Put the forward ends of the forward motive flow fuel−feed tubes (35) in the
spacer (54). Make sure they are placed in the correct sized cut outs.
NOTE: The ends of the motive flow fuel−feed tubes that have a double bend
must be near the spacer.
(m) Put the forward ends of the forward engine fuel−feed tubes (37) in the spacer
(54). Make sure they are placed in the correct sized cut outs.
NOTE: The ends of the engine fuel−feed tubes that have a double bend
must be near the spacer.
(n) Put the forward end of the forward APU fuel−feed tube (40) in the spacer (54).
Make sure it is placed in the correct sized cut out.
NOTE: The ends of the APU fuel−feed tube that has a double bend must be
near the spacer.
(o) Make sure that the two forward motive flow fuel−feed tubes (35) are on top (at
the 11 and one O’clock positions). Then put the forward fuel−feed tubes
through the tube assembly (23) and the transition shroud (26).

Master
EFFECTIVITY: See Pageblock 28−20−01 page 401
28−20−01 Page 427
Dec 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
(p) Apply a thin layer of petrolatum inside the three coupling assembly (25), (22),
and (17) sleeve. Put the sleeves over the shroud assembly (18).
(q) Put the shroud assembly (18) over the forward fuel−feed tubes. Make sure that
the drain union (10) connector is at the bottom and the fuel feed tubes are
parallel to each other.
(r) Put the aft ends of the forward motive flow fuel−feed tubes (35) in the
spacer (55). Make sure they are placed in the correct sized cut outs.
NOTE: The curved ends of the motive flow fuel−feed tubes will be near the
spacer.
(s) Put the aft ends of the forward engine fuel−feed tubes (37) in the spacer (55).
Make sure they are placed in the correct sized cut outs.
NOTE: The curved ends of the engine fuel−feed tubes will be near the
spacer.
(t) Put the aft end of the forward APU fuel−feed tube (40) in the spacer (55).
Make sure it is placed in the correct sized cut out.
NOTE: The curved end of the APU fuel−feed tube will be near the spacer.
(u) Push the spacer (55) inside the shroud assembly (18).
(v) Push the spacer (54) inside the tube assembly (23).
NOTE: Make sure the motive flow fuel−feed tubes (35) are on top and all
fuel feed tubes are parallel to each other.
(2) Do the steps that follow to assemble the aft part of the common fuel feed assembly,
when necessary:
NOTE: The following steps may be done outside the aircraft.
(a) Remove the blanking caps from the fuel−feed tubes inside the shroud
assembly (56).
(b) Inspect the threads of the motive flow fuel−feed tubes (35) and the ends of the
engine and APU fuel−feed tubes (40) for damage.
(c) Apply petrolatum to the preformed packings (45) and (41) and install in the
grooves at both ends of the APU fuel−feed tube (40).
(d) Apply petrolatum to the preformed packings (43) and (38) and install in the
grooves at both ends of the two engine fuel−feed tubes (37).
(e) Put the nut assembly (21) onto the forward end of the shroud assembly (56)
with the threaded end forward.
NOTE: The APU fuel−feed tube (40) protrudes further at the forward end of
the shroud assembly than it does at the aft end.
(f) Put the washer assembly (51) onto the forward end of the shroud
assembly (56). Be careful not to displace or damage the retainer wire.
(g) Apply petrolatum to the preformed packing (53) and put onto the forward end
of the shroud assembly (56).
(h) Put a second washer assembly (51) onto the forward end of the shroud
assembly (56). Be careful not to displace or damage the retainer wire.
(i) Apply petrolatum to the preformed packing (20) and put into the groove in the
slider assembly (19).

Master
EFFECTIVITY: See Pageblock 28−20−01 page 401
28−20−01 Page 428
Aug 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
(j) Put the slider assembly (19) onto the shroud assembly (56). Make sure the
threaded end goes on first.
(k) Put the nut assembly (16) onto the aft end of the shroud assembly (56) with
the threaded end aft.
(l) Put the washer assembly (50) onto the aft end of the shroud assembly (56). Be
careful not to displace or damage the retainer wire.
(m) Apply petrolatum to the preformed packing (52) and put onto the aft end of the
shroud assembly (56).
(n) Put a second washer assembly (50) onto the aft end of the shroud
assembly (56). Be careful not to displace or damage the retainer wire.
(o) Apply petrolatum to the preformed packing (15) and put into the groove in the
slider assembly (14).
(p) Put the slider assembly (14) onto the shroud assembly (56). Make sure the
threaded end goes on first.
(3) Do the following steps to install the common fuel feed assembly in the aircraft,
when necessary:
(a) Clean the pressure box (28) flange with DS 108, Burgundy. Then wipe off
residual traces of the cleaner with alcohol.
(b) Apply a thin layer of petrolatum inside the coupling assembly (25). Put the
coupling assembly sleeve over the transition shroud (26).
(c) Remove the blanking caps from the pressure box (28) fuel−feed tubes.
(d) Apply petrolatum to the two preformed packings (47) and install in the grooves
at the ends of the pressure box, engine−fuel−feed tubes (37)
(e) Apply petrolatum to the preformed packing (49) and install in the groove at the
end of the pressure box, APU−fuel−feed tube (40).
(f) Apply petrolatum to the threads of the pressure box, motive flow fuel−feed
tube (35) unions. Wipe off any excess petrolatum.
(g) Apply petrolatum to preformed packing (15) and install in the groove in the
cross adaptor (13).
(h) Remove the blanking caps from the fuel−feed tubes nearest to the cross
adaptor (13).
(i) Apply petrolatum to the preformed packings (38) and install in the grooves at
the ends of the engine−fuel−feed tubes (37), nearest to the cross adaptor (13).
(j) Apply petrolatum to the preformed packing (41) and install in the groove at the
end of the APU−fuel−feed tube (40), nearest to the cross adaptor (13).
(k) Apply petrolatum to the threads of the motive flow fuel−feed tubes (35) at the
cross adaptor (13). Wipe off any excess petrolatum.
(l) Carefully put the common shroud assembly between the fuselage cross
members and into position. Make sure that the end with the APU fuel−feed
tube (40) protruding the most, points forward.
**ON A/C 8027−8064, 8066−8068
(m) Install the spacer (57). Make sure that the tubes are installed in the correct cut
out.

Master
EFFECTIVITY: See Pageblock 28−20−01 page 401
28−20−01 Page 429
Dec 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C ALL
(n) Apply petrolatum to the threads of the motive flow fuel−feed tubes (35) at both
ends of the shroud assembly (56). Wipe off any excess petrolatum.
(o) Align the fuel−feed tubes in the shroud assembly (56) with those in the shroud
assembly (18) and cross adaptor (13).
NOTE: If fuel−feed tubes do not meet they can be pulled through the shroud
assemblies.
(p) Connect the motive flow fuel−feed tubes (35) between the shroud
assembly (56) and the cross adaptor (13). These should be connected finger
tight only.
(q) Connect the motive flow fuel−feed tubes (35) between the shroud
assembly (56) and the shroud assembly (18). These should be connected
finger tight only.
(r) Install the coupling (48) to connect the APU fuel−feed tube (40) between the
pressure box (28) and the transition shroud (26), as follows:
1 Apply a thin layer of petrolatum inside the coupling assembly (25) sleeve.
Move the sleeve over the APU−fuel−feed tube (40) and preformed
packing (49).
2 Gently rock the coupling assembly (48) sleeve over the two preformed
packings (49).
3 Install the coupling assembly (48) retainer over the sleeve and snap the
latch closed, with pawls fully engaged. The coupling is locked
automatically. Make sure the coupling can be turned by hand.
(s) Install the two couplings (46) to connect the engine fuel−feed tubes (37)
between the pressure box (28) and the transition shroud (26), as follows:
1 Apply a thin layer of petrolatum inside both of the coupling assembly (46)
sleeves. Move the sleeves over the engine fuel−feed tubes (37) and
preformed packings (47).
2 Gently rock each of coupling assemblies (46) sleeves over two preformed
packings (47).
3 Install both coupling assembly (46) retainers over the sleeves and snap the
latches closed, with pawls fully engaged. The couplings are locked
automatically. Make sure the couplings can be turned by hand.
(t) Install the coupling (44) to connect the APU fuel−feed tube (40) between the
shroud assembly (18) and the shroud assembly (56), as follows:
1 Apply a thin layer of petrolatum inside the coupling assembly (44) sleeve.
Move the sleeve over the APU−fuel−feed tube (40) and preformed
packing (45).
2 Gently rock the coupling assembly (44) sleeve over the two preformed
packings (45).
3 Install the coupling assembly (44) retainer over the sleeve and snap the
latch closed, with pawls fully engaged. The coupling is locked
automatically. Make sure the coupling can be turned by hand.
(u) Install the two coupling assemblies (42) to connect the engine fuel−feed
tubes (37) between the shroud assembly (18) and the shroud assembly (56),

Master
EFFECTIVITY: See Pageblock 28−20−01 page 401
28−20−01 Page 430
Aug 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
as follows:
1 Apply a thin layer of petrolatum inside both of the coupling assembly (42)
sleeves. Move the sleeves over the engine fuel−feed tubes (37) and
preformed packings (43).
2 Gently rock the sleeve of each coupling assembly (42) over the two
preformed packings (43).
3 Install both coupling assembly (42) retainers over the sleeves and snap the
latches closed, with pawls fully engaged. The couplings are locked
automatically. Make sure the couplings can be turned by hand.
(v) Install the coupling assembly (39) to connect the APU fuel−feed tube (40)
between the shroud assembly (56) and the cross adaptor (13), as follows:
1 Move the sleeve over the APU−fuel−feed tube (40) and preformed
packing (41).
2 Gently rock the coupling assembly (39) sleeve over the two preformed
packings (41).
3 Install the coupling assembly (39) retainer over the sleeve and snap the
latch closed, with pawls fully engaged. The coupling is locked
automatically. Make sure the coupling can be turned by hand.
(w) Install the two coupling assemblies (36) to connect the engine fuel−feed
tubes (37) between the shroud assembly (56) and the cross adaptor (13), as
follows:
1 Apply a thin layer of petrolatum inside both of the coupling assembly (36)
sleeves. Move the sleeves over the engine fuel−feed tubes (37) and the
preformed packings (38).
2 Gently rock the sleeve of each coupling assembly (39) over the two
preformed packings (38).
3 Install both the coupling assembly (36) retainers over the sleeves and snap
the latches closed, with pawls fully engaged. The couplings are locked
automatically. Make sure the couplings can be turned by hand.
(x) Make sure there is no stress on the engine fuel−feed tubes (37). That they are
parallel to each other. That the motive flow fuel−feed tubes (35) are still in
the 11 and one O’clock positions.
(y) Torque the motive flow fuel−feed tubes (35) at their union connectors to
between 300 to 400 inch pounds (35 to 45 N·m). Make sure that the motive
flow fuel−feed tubes have not twisted during the torque loading procedure.
(z) Install a tie wrap (34) around the fuel−feed tubes inside the transition
shroud (26).
(4) Do a pressure and blockage test of the fuel−feed (Ref. TASK 28−20−01−780−802),
motive flow (Ref. TASK 28−20−01−780−803), and APU tubes (Ref. TASK
28−20−01−780−804).
(5) Do the steps that follow to close the common fuel−feed−shroud assembly, when
applicable:
(a) Wipe the gasket (33) with a clean, dry and lint−free cloth.
(b) Position the gasket (33) between the transition shroud (26) and the pressure
box (28) flanges.

Master
EFFECTIVITY: See Pageblock 28−20−01 page 401
28−20−01 Page 431
Aug 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
(c) Align the transition shroud (26), gasket (33) and pressure box (28) and hold in
position.
(d) Put the top half of the flange plate (32) against the transition shroud (26) and
install five screws (29) with five washers (30). Hand tighten the screws.
NOTE: The cut out in the flange plate must be to the left of center, when
viewed from aft.
(e) Put the bottom half of the flange plate (31) against the transition shroud (26)
and install five screws (29) with five washers (30). Hand tighten the screws.
(f) Tighten the ten screws (29) to a torque value of 18 inch pounds (2.1 N·m). in
the given sequence. Refer to Figure 407.
(g) Move the tube assembly (23) until it contacts the transition shroud (26).
(h) Install the coupling assembly (25) to connect the tube assembly (23) to the
transition shroud (26), as follows:
1 Gently rock the coupling assembly (25) sleeve over the two preformed
packings (27).
2 Install the coupling assembly (25) retainer over the sleeve and snap the
latch closed, with pawls fully engaged. The coupling is locked
automatically. Make sure the coupling can be turned by hand.
(i) Move the shroud assembly (18) until it contacts the tube assembly (23). Make
sure that the drain union (10) connector is at the bottom.
(j) Install the coupling assembly (22) to connect the shroud assembly (18) to the
tube assembly (23), as follows:
1 Gently rock the coupling assembly (22) sleeve over the two preformed
packings (24).
2 Install the coupling assembly (22) retainer over the sleeve and snap the
latch closed, with pawls fully engaged. The coupling is locked
automatically. Make sure the coupling can be turned by hand.
(k) Connect the drain line (9) to the shroud assembly (18) at the drain union (10)
and to the fuselage drain union (11).
NOTE: Make sure the arrow on the drain line points in the direction of flow.
The longer straight section of the line will be closer to the fuselage.
(l) Torque the drain line (9) connectors to 120 to 140 inch pounds (13.6 to 15.8
N·m).
(m) Replace the insulation material, against the fuselage, around the drain line (9).
(n) Move the slider assembly (19) until it contacts the shroud assembly (18).
(o) Move the washer assembly (51) from the forward end of the shroud
assembly (56) into the slider assembly (19). Do not push the washer assembly
too far into the slider assembly. Be careful not to displace or damage the
retainer wire.
(p) Move the preformed packing (53) from the forward end of the shroud
assembly (56) into the slider assembly (19). Do this until it touches the washer
assembly (51).
(q) Move the second washer assembly (51) from the forward end of the shroud
assembly (56) into the slider assembly (19). Do this until it touches the

Master
EFFECTIVITY: See Pageblock 28−20−01 page 401
28−20−01 Page 432
Aug 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
preformed packing (53). Be careful not to displace or damage the retainer
wire.
(r) Move the nut assembly (21) along the forward end of the shroud
assembly (56) and screw loosely onto the slider assembly (19).
(s) Install the coupling assembly (17) to connect the slider assembly (19) to the
shroud assembly (18), as follows:
1 Gently rock the coupling assembly (17) sleeve from the shroud
assembly (18) over the two preformed packings (20).
2 Install the coupling assembly (17) retainer over the sleeve and snap the
latch closed, with pawls fully engaged. The coupling is locked
automatically. Make sure the coupling can be turned by hand.
(t) Make sure that all of the fuel tube assemblies run parallel to each other at the
cross adaptor (13). This to reduce the risk of fuel leaks.
(u) Move the slider assembly (14) until it contacts the cross adaptor (13).
(v) Move the washer assembly (50) from the aft end of the shroud assembly (56)
into the slider assembly (14). Do not push the washer assembly too far into the
slider assembly. Be careful not to displace or damage the retainer wire.
(w) Move the preformed packing (52) from the aft end of the shroud assembly (56)
into the slider assembly (14). Do this until it touches the washer assembly (50).
(x) Move the second washer assembly (50) from the aft end of the shroud
assembly (56) into the slider assembly (14). Do this until it touches the
preformed packing (52). Be careful not to displace or damage the retainer wire.
(y) Move the nut assembly (16) along the aft end of the shroud assembly (56) and
screw loosely onto the slider assembly (14).
(z) Install the coupling assembly (12) to connect the slider assembly (14) to the
cross adaptor (13), as follows:
1 Gently rock the coupling assembly (12) sleeve from the cross adaptor (13)
over the two preformed packings (15).
2 Install the coupling assembly (12) retainer over the sleeve and snap the
latch closed, with pawls fully engaged. The coupling is locked
automatically. Make sure the coupling can be turned by hand.
(aa) Tighten the nut assemblies (16) and (21) into the slider assemblies (14)
and (19).
(ab) Loosely attach the slider assembly (19) to the fuselage mounting bracket with
the saddle clamp (8), as follows:
1 Put the smaller part of the saddle clamp (8) under the slider assembly (19)
and on top of the related mounting bracket.
2 Position the larger part of the saddle clamp (8) over the slider
assembly (19) and align with the mounting bracket.
3 Position two L−shaped spacers (7) on top of the saddle clamp (8). Keep
the saddle clamp in position with two screws (5) and two washers (6).
(ac) Loosely attach the shroud assembly (56) to a fuselage mounting bracket in
three positions with three saddle clamps (4), as follows:

Master
EFFECTIVITY: See Pageblock 28−20−01 page 401
28−20−01 Page 433
Aug 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
1 Put the smaller part of the first saddle clamp (4) under the forward end of
the shroud assembly (56) and on top of the related mounting bracket.
2 Position the larger part of the first saddle clamp (4) over the forward end of
the shroud assembly (56) and align with the mounting bracket.
3 Position two L−shaped spacers (3) on top of the first saddle clamp (4).
Keep the saddle clamp in position with two screws (1) and two washers (2).
4 Put the smaller part of a second saddle clamp (4) under the middle section
of the shroud assembly (56) and on top of the related mounting bracket.
5 Position the larger part of the second saddle clamp (4) over the middle
section of the shroud assembly (56) and align with the mounting bracket.
6 Position two L−shaped spacers (3) on top of the second saddle clamp (4).
Keep the saddle clamp in position with two screws (1) and two washers (2).
7 Put the smaller part of the third saddle clamp (4) under the aft end of the
shroud assembly (56) and on top of the related mounting bracket.
8 Position the larger part of the third saddle clamp (4) over the aft end of the
shroud assembly (56) and align with the mounting bracket.
9 Position two L−shaped spacers (3) on top of the third saddle clamp (4).
Keep the saddle clamp in position with two screws (1) and two washers (2).
(ad) Tighten the eight screws (1) that keep the four saddle clamps (4) and (8)
attached to their related fuselage mounting brackets.

Subtask 28−20−01−420−002
Refer to Figure 404.
B. When applicable, install the left or right engine fuel−feed assembly, as follows:
NOTE: The procedure to install the right engine fuel−feed assembly is the same as
that for the left engine fuel−feed assembly.
(1) Remove the blanking caps from the LH shroud assembly (4).
(2) Apply petrolatum to preformed packing (14) and install in the groove at the flared
end of the LH shroud assembly (4).
(3) Apply petrolatum to the preformed packing (14) and install in groove at the forward
end of the LH shroud assembly (4).
(4) Remove blanking caps from the engine fuel−feed tube (23).
(5) Apply petrolatum to the preformed packing (33) and install in the groove at the aft
end of the engine fuel−feed tube (23).
(6) Apply petrolatum to the preformed packing (33) and install in the groove in the
engine fuel−feed tube (23) inside the flange assembly (30).
(7) Apply petrolatum to the preformed packing (31) and install in the groove in the LH
flange assembly (30).
(8) Apply a thin layer of petrolatum inside the coupling assembly (29) sleeve. Move the
sleeve over the flange assembly (30).
(9) Carefully put the LH shroud assembly (4) into the fuselage through the opening at
FS559+112 and FS574. Place under the bleed air tube so that it runs parallel to the
fuselage and aligns with the bulkhead connector on the left side. The flared end
must face aft.

Master
EFFECTIVITY: See Pageblock 28−20−01 page 401
28−20−01 Page 434
Aug 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
(10) Loosely install two saddle clamps (3) and cushions at FS589 and FS605 to position
the LH shroud assembly (4). This with two screws (1) and two washers (2).
(11) Loosely install the saddle clamp (7) and cushion at FS574 to position the LH shroud
assembly (4). This with one screw (5) and one washer (6).
(12) Make sure that the fuel tubes at the forward end of the LH shroud assembly (4) are
parallel to each other. The motive flow fuel−feed tube (21) must be on top.
(13) Connect the motive flow fuel−feed tube (21) at the motive flow bulkhead connector,
inside the flange assembly (30). Torque the connector to 300 to 400 pound−inches
(34 to 45 N·m).
(14) Apply a thin layer of petrolatum inside the coupling assembly (32) sleeve. Move the
sleeve over the aft engine fuel−feed tube (23) and preformed packing (33).
(15) Bring both engine fuel−feed tubes (23) into contact.
(16) Use a gentle rocking movement to move the coupling assembly (32) sleeve over
the two preformed packings (33).
(17) Install the coupling assembly (32) retainer over the sleeve and snap the latch
closed, with pawls fully engaged. The coupling is locked automatically. Make sure
the coupling can be turned by hand.
(18) Close the distance between the LH shroud assembly (4) and the flange
assembly (30).
(19) Use a gentle rocking movement to move the coupling assembly (29) sleeve away
from the bulkhead and over the two preformed packings (31).
(20) Install the coupling assembly (29) retainer over the sleeve and snap the latch
closed, with pawls fully engaged. The coupling is locked automatically. Make sure
the coupling can be turned by hand.
(21) Connect the drain line (26) at the fuselage fitting (27).
(22) Connect the drain line (26) to the elbow fitting (28).
(23) Apply petrolatum to the preformed packing (14) and install in the groove at the
forward end of the LH shroud assembly (4).
(24) Apply a thin layer of petrolatum inside the coupling assembly (13) sleeve. Move the
sleeve over the forward end of the LH shroud assembly (4) and the preformed
packing (14).
(25) Apply petrolatum to the preformed packings (14) and (17) and install in the grooves
at each end of the elbow assembly (12).
(26) Carefully place the elbow assembly (12) over the motive flow fuel−feed tube (21)
and engine fuel−feed tube (23).
(27) Install the spacer (25) in the open end of the elbow assembly (12) with the smaller
receptacle up. The spacer puts the motive flow fuel−feed tube (21) and the engine
fuel−feed tube (23) in their correct positions.
(28) Install a tie wrap (34) aft of the spacer (25). Push the spacer along the motive flow
fuel−feed tube (21) and the engine fuel−feed tube (23). Install a second tie
wrap (34) forward of the spacer (25).
(29) Move the elbow assembly (12) against the LH shroud assembly (4).
(30) Gently rock the coupling assembly (13) sleeve over the two preformed
packings (14).

Master
EFFECTIVITY: See Pageblock 28−20−01 page 401
28−20−01 Page 435
Aug 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
(31) Install the coupling assembly (13) retainer over the sleeve and snap the latch
closed, with pawls fully engaged. The coupling is locked automatically. Make sure
the coupling can be turned by hand.
(32) Apply petrolatum to the preformed packing (17) and install in the groove at outboard
end of the end of the slider assembly (16).
(33) Apply a thin layer of petrolatum inside the coupling assembly (15) sleeve. Move the
sleeve over the outboard end of the slider assembly (16) and preformed
packing (17).
(34) Connect the motive flow fuel−feed tubes (21) with the motive flow union (20).
Torque the connector to 300 to 400 pound−inches (34 to 45 N·m).
(35) Apply petrolatum to the two preformed packing (24) and install in the grooves at the
ends of both engine fuel−feed tubes (23).
(36) Apply a thin layer of petrolatum inside the coupling assembly (22) sleeve. Move the
sleeve over the forward engine fuel−feed tube (23) and preformed packing (24).
(37) Bring both engine fuel feed−tubes (22) into contact.
(38) Use a gentle rocking movement to move the coupling assembly (22) sleeve over
the two preformed packings (24).
(39) Install the coupling assembly (22) retainer over the sleeve and snap the latch
closed, with pawls fully engaged. The coupling is locked automatically. Make sure
the coupling can be turned by hand.
(40) Move the slider assembly (16) until it contacts the elbow assembly (12).
(41) Gently rock the coupling assembly (15) sleeve over the two preformed
packings (17), installed in the slider assembly (16) and elbow assembly (12).
(42) Install the coupling assembly (15) retainer over the sleeve and snap the latch
closed, with pawls fully engaged. The coupling is locked automatically. Make sure
the coupling can be turned by hand.
(43) Tighten the nut assembly (18) into the slider tube assembly (19).
(44) Attach the elbow assembly (12) and heat shield (11) to the fuselage mount at
FS574. This with the saddle clamp and cushion (10), the two screws (8) and the
two washers (9).
(45) Install two more screws (1) with two more washers (2) to the two saddle clamps (3)
to keep the LH shroud assembly (4) in position. Tighten the four screws.
(46) Install one more screw (5) with one more washers (6) to the saddle clamp (7) to
keep the LH shroud assembly (4) in position. Tighten the two screws.
(47) Do a pressure and blockage test of the engine fuel−feed (Ref. TASK
28−20−01−780−802), motive flow fuel−feed (Ref. TASK 28−20−01−780−803), and
APU fuel−feed tubes (Ref. TASK 28−20−01−780−804).

Subtask 28−20−01−420−003
Refer to Figure 403.
C. When applicable, do the steps that follow to install the cross adaptor assembly, as
follows:

Master
EFFECTIVITY: See Pageblock 28−20−01 page 401
28−20−01 Page 436
Aug 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
(1) Do the steps that follow to connect the slider tube assemblies to the cross adaptor
assembly:
NOTE: The procedure that follows is for the slider tube on the left side. The
procedure for the slider tube on the right side is the same.
NOTE: The following steps may be done outside the aircraft.
(a) Apply petrolatum to the preformed packing (35) and install in the groove in left
side of the cross adaptor assembly (2).
(b) Apply petrolatum to the preformed packing (35) and install in the inboard
groove in the slider tube assembly (26).
(c) Put the motive flow fuel−feed tube (7) and the engine fuel−feed tube (12)
through the cross adaptor (2). These tubes are part of the slider tube assembly
(26). Place the slider tube assembly against the cross adaptor.
(d) Apply a thin layer of petrolatum inside the coupling assembly (34) sleeve.
(e) Gently rock the coupling assembly (34) sleeve over the two preformed
packings (35) installed on the slider tube assembly (26) and cross adaptor (2).
(f) Install the coupling assembly (34) retainer over the sleeve and snap the latch
closed, with pawls fully engaged. The coupling is locked automatically. Make
sure the coupling can be turned by hand.
(g) Place the nut assembly (25) over the slider tube assembly (26).
(h) Install the washer assembly (38) inside the slider assembly (23) at the inboard
end. Take care not to displace or damage the retaining wire inside the washer
assembly.
(i) Apply petrolatum to the preformed packing (39) and install inside the slider
assembly (23) at the inboard end.
(j) Install one more washer assembly (38) inside the slider assembly (23) at the
inboard end.
(k) Apply petrolatum to the preformed packing (24) and install in the outboard
groove of the slider assembly (23).
(l) Place the slider assembly (23) over the motive flow fuel−feed tube (7) and the
engine fuel−feed tube (12). Then loosely screw the nut assembly (25) into the
slider assembly.
(m) Install the union (27) onto the motive flow fuel−feed tube (7). Tighten the union
to a torque value of 300 to 400 pound−inches (34 to 45 N·m).
(n) Do again these steps for the right side cross adaptor assembly.
(2) Put the cross adaptor (2) assembly into the fuselage, through the opening at
FS559+112 and FS574.
(3) Do the steps that follow to connect the aft APU line assembly to the cross adaptor
assembly:
(a) Apply petrolatum to the preformed packing (37) and install in the groove in the
forward end of the APU line assembly (15).
(b) Carefully put the APU fuel−feed tube (9) through the cross adaptor (2). Do this
until the APU line assembly (15) touches the cross adaptor fitting.
(c) Install the clamshell assembly (14) over the cross adaptor (2) fitting and the
APU line assembly (15). Make sure the preformed packing (37) is correctly

Master
EFFECTIVITY: See Pageblock 28−20−01 page 401
28−20−01 Page 437
Aug 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
installed. Then snap the latch closed, with pawls fully engaged. The clamshell
is locked automatically.
(4) Do the steps that follow to connect the fuel feed tubes between the slider assembly
the cross adaptor assembly:
(a) Apply petrolatum to the threads of the motive flow fuel−feed tubes (6) at the
cross adaptor (2). Wipe off any excess petrolatum.
(b) Apply petrolatum to the preformed packings (13) and install in the grooves at
the ends of the engine−fuel−feed tubes (12), nearest to the cross adaptor (2).
(c) Apply petrolatum to the two preformed packings (10). Install one in the groove
at each end of the APU fuel−feed tubes (9) nearest to the cross adaptor (2).
(d) Install the coupling assembly (8) to connect the APU fuel−feed tube (9)
between the slider assembly (5) and the cross adaptor (2), as follows:
1 Apply a thin layer of petrolatum inside the coupling assembly (8) sleeve.
Move the sleeve over the APU−fuel−feed tube (9) and preformed packings
(10).
2 Install the coupling assembly (8) retainer over the sleeve and snap the
latch closed, with pawls fully engaged. The coupling is locked
automatically. Make sure the coupling can be turned by hand.
(e) Install the two coupling assemblies (11) to connect the engine fuel−feed
tubes (12) between the shroud assembly (5) and the cross adaptor (2), as
follows:
1 Apply a thin layer of petrolatum inside both of the coupling assembly (11)
sleeves. Move the sleeves over the engine fuel−feed tubes (12) and the
preformed packings (13).
2 Gently rock the sleeve of each coupling assembly (11) over the two
preformed packings (13).
3 Install both the coupling assembly (11) retainers over the sleeves and snap
the latches closed, with pawls fully engaged. The couplings are locked
automatically. Make sure the couplings can be turned by hand.
(f) Make sure there is no stress on the engine fuel−feed tubes (12). That they are
parallel to each other. That the motive flow fuel−feed tubes (7) are in the 11
and one O’clock positions.
(g) Torque the motive flow fuel−feed tubes (7) at their union connectors (6) to
between 300 to 400 inch pounds (35 to 45 N·m). Make sure that the motive
flow fuel−feed tubes have not twisted during the torque loading procedure.
(5) Do the steps that follow to connect the aft APU Line assembly:
(a) Apply petrolatum to the preformed packing (20) and install in the groove at the
top end of the APU line assembly (15).
(b) Apply petrolatum to the preformed packing (20) and install in the groove at the
bottom end of the APU line assembly (15).
(c) Apply petrolatum to the preformed packing (18) and install in the groove in the
aft end of the APU fuel−feed tube (9).
(d) Put the slider assembly (16) body onto the bottom APU line assembly (15).

Master
EFFECTIVITY: See Pageblock 28−20−01 page 401
28−20−01 Page 438
Aug 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
(e) Install a retainer ring (19) inside the slider assembly (16) body.
(f) Put the slider assembly (16) cap onto the top APU line assembly (15).
(g) Install a retainer ring (19) inside the cap of the slider assembly (16).
(h) Install the coupling assembly (17) over the preformed packing (18) and snap
the latch closed, with pawls fully engaged. The coupling is locked
automatically.
(i) Move up the body of the slider assembly (16).
(j) Screw the cap of the slider assembly (16) onto the body of the slider assembly.
(6) Do the steps that follow to connect the cross adaptor assembly and the left or the
right engine fuel−feed shroud assembly:
NOTE: The procedure that follows is to connect the engine fuel−feed shroud
assembly on the left side. The procedure to connect the engine fuel−feed
shroud assembly on the right side is the same.
(a) Install the spacer (36) around the two motive flow fuel−feed tubes (7), the two
engine fuel−feed tubes (12) and the APU fuel−feed tube (9) in the cross
adaptor (2). Make sure the two motive flow fuel−feed tubes are put into the two
smaller receptacles.
(b) Push the spacer (36) into the cross adaptor (2). The two motive flow fuel−feed
tubes (7) must be at the 10 O’clock and two o’clock positions.
(c) Apply petrolatum to the preformed packing (24) and install in the groove in the
elbow assembly (22).
(d) The cross adaptor assembly keeps the motive flow fuel−feed tube (7) and the
engine fuel−feed tube (12). The left engine fuel−feed shroud assembly keeps
the continued motive flow fuel−feed tube (7) and the continued engine
fuel−feed tube (12). Align these tubes.
(e) Apply petrolatum to the two preformed packings (29) and install in the grooves
at the ends of both engine fuel−feed tubes (12).
(f) Connect the motive flow fuel−feed tubes (7) with the motive flow union (27).
Torque the connector to 300 to 400 pound−inches (34 to 45 N·m).
(g) Apply a thin layer of petrolatum inside the coupling assembly (28) sleeve.
Move the sleeve over the engine fuel−feed tube (12) and preformed
packing (29).
(h) Bring both engine fuel feed−tubes (12) into contact.
(i) Gently rock the coupling assembly (28) sleeve over the two preformed
packings (29).
(j) Install the coupling assembly (28) retainer over the sleeve and snap the latch
closed, with pawls fully engaged. The coupling is locked automatically. Make
sure the coupling can be turned by hand.
(k) Move the slider assembly (23) until it contacts the elbow assembly (22).
(l) Gently rock the coupling assembly (21) sleeve over the two preformed
packings (24). These are installed in the slider assembly (23) and the elbow
assembly (22).
(m) Install the coupling assembly (21) retainer over the sleeve and snap the latch
closed, with pawls fully engaged. The coupling is locked automatically. Make

Master
EFFECTIVITY: See Pageblock 28−20−01 page 401
28−20−01 Page 439
Aug 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
sure the coupling can be turned by hand.
(n) Tighten the nut assembly (25) into the slider assembly (23).
(o) Install the LH drain line (30) union at the cross adaptor (2) and fuselage fitting.
(p) Tighten the drain line (30) connectors to a torque value of 120 to 140 inch
pounds (13.6 to 15.8 N·m).
(q) Replace the insulation material around the drain line (30).
(r) Attach the cross adaptor (2) to the bracket assembly (33) with the two screws
(31) and the two washers (32). Make sure the cushion (40) is correctly
positioned.
(7) Do a pressure and blockage test of the fuel−feed (Ref. TASK 28−20−01−780−802),
motive flow (Ref. TASK 28−20−01−780−803), and APU tubes (Ref. TASK
28−20−01−780−804).

Subtask 28−20−01−420−004
Refer to Figure 402.
D. When applicable, install the APU fuel−feed assembly, as follows:
(1) Apply petrolatum to the preformed packing (20) and install in the groove at the
forward end of the APU line assembly (4).
(2) Put the APU fuel−feed tube (7) through the cross adaptor (12). Do this until the
APU line assembly (4) touches the cross adaptor fitting.
(3) Put the APU fuel−feed tube (7) into the bottom receptacle of the spacer (19).
(4) Apply petrolatum to the two preformed packings (18). Install one in the grooves at
each end of the APU fuel−feed tubes (7).
(5) Install the coupling assembly (17) over the APU fuel−feed tubes (7) and the
preformed packing (18). Snap the latch closed, with pawls fully engaged. The
coupling is locked automatically.
(6) Install the clamshell assembly (11) over the cross adaptor (12) fitting and the APU
line assembly (4). Make sure the preformed packing (20) is correctly installed. Then
snap the latch closed, with pawls fully engaged. The clamshell is locked
automatically.
(7) Apply petrolatum to the preformed packing (10) and install in the groove at the end
of the forward APU line assembly (4).
(8) Apply petrolatum to the preformed packing (10) and install in the groove at the end
of the aft APU line assembly (4).
(9) Apply petrolatum to the preformed packing (8) and install in the groove in the aft
end of the forward APU fuel−feed tube (7).
(10) Put the slider assembly (5) body onto the APU line assembly (4).
(11) Install a retainer ring (9) inside the slider assembly (4) body.
(12) Put the slider assembly (5) cap onto the APU line assembly (4).
(13) Install a retainer ring (9) inside the cap of the slider assembly (5).
(14) Install the coupling assembly (6) over the preformed packing (8) and snap the latch
closed, with pawls fully engaged. The coupling is locked automatically.

Master
EFFECTIVITY: See Pageblock 28−20−01 page 401
28−20−01 Page 440
Aug 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
(15) Move up the body of the slider assembly (5).
(16) Screw the cap of the slider assembly (5) onto the body of the slider assembly.
(17) Connect the aft APU line assembly (4) at the bulkhead fitting, using a sealing
washer (23), shroud cup (22) and jam nut (21).
(18) Attach the APU line assembly (4) to the fuselage brackets with the two clamps (3)
the two washers (2) and the two screws (1).
(19) Visually inspect the preformed packings (15) for condition. When serviceable,
continue with this procedure. When unserviceable, the procedures for removal and
installation of the common shroud assembly should be followed. This, to renew the
preformed packings.
(20) Do a pressure and blockage test of the fuel−feed, Ref. TASK 28−20−01−780−802),
motive flow (Ref. TASK 28−20−01−780−803), and APU tubes (Ref. TASK
28−20−01−780−804).
(21) Apply petrolatum to the installed preformed packings (15) and inside of the coupling
assembly (14) sleeve.
(22) Move the slider assembly (13) until it contacts the cross adaptor (12).
(23) Install the coupling assembly (14) to connect the slider assembly (13) to the cross
adaptor (12), as follows:
(a) Gently rock the coupling assembly (14) sleeve from the cross adaptor (12)
over the two preformed packings (15).
(b) Install the coupling assembly (14) retainer over the sleeve and snap the latch
closed, with pawls fully engaged. The coupling is locked automatically. Make
sure the coupling can be turned by hand.
(24) Tighten the nut assembly (16) into the slider assembly (13).

4. Close Out
Subtask 28−20−01−780−006
A. Do a pressure and blockage test of the fuel line shroud (Ref. TASK
28−20−01−780−801).

Subtask 28−20−01−865−010
B. Remove the tags and close the circuit breakers that follow:
CBP−1 M6 L FUEL PUMP 221
CBP−1 M7 L FUEL PUMP CONT 221
CBP−1 M12 FUEL SYST CONT 221
CBP−1 N10 XFER/APU FUEL PUMP 221
CBP−2 G10 R FUEL PUMP 222
CBP−2 G11 R FUEL PUMP CONT 222
CBP−4 B10 FUEL SYST CONT 222

Master
EFFECTIVITY: See Pageblock 28−20−01 page 401
28−20−01 Page 441
Aug 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
Subtask 28−20−01−710−002
C. Do an operational test of the fuel system (Ref. TASK 28−00−00−710−801)

Subtask 28−20−01−410−009
D. When applicable, install the mainfeed manifold (Ref. TASK 21−22−01−000−801).
E. When applicable, install the center cross beam at FS589, between LBL9.0 and RBL9.0.
This with the hardware retained from the set−up procedure (Ref TASK
21−22−01−400−801).

Subtask 28−20−01−410−010
F. When applicable, install the cargo compartment floor panels between FS559+80 and
FS621.00 (Ref. TASK 53−01−01−400−804).

Subtask 28−20−01−410−011
G. When applicable, install the passenger compartment center floor panels between
FS559.00 and FS559+80 (Ref TASK 53−01−01−400−802).

Subtask 28−20−01−941−005
H. Remove all tools, equipment, and unwanted materials from the work area.

Master
EFFECTIVITY: See Pageblock 28−20−01 page 401
28−20−01 Page 442
Aug 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL

FS559.00

NOTE
Tighten screws in given
sequence to 18 inch pounds W
(2.1 Nm).

10 8 9

3 1

2 4
ram2820014_010.dg, rm, 15/12/99

6 5 7
X
VIEW LOOKING FORWARD

Tightening Sequence for Transition Shroud Screws

Figure 407

Master
EFFECTIVITY: See Pageblock 28−20−01 page 401
28−20−01 Page 443
Aug 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C ALL
SHROUD, FUEL LINE−ADJUSTMENT/TEST

1. General
A. The maintenance procedures that follow are for the pressure and blockage tests of the
fuel line shrouds. The fuel line shroud contains the fuel lines from the aft bulkhead of the
main wheel well to the aft pressure bulkhead.
B. It is not necessary to defuel the aircraft to do a test of the fuel line shroud.

TASK 28−20−01−780−801
Pressure and Blockage Test of the Fuel Line Shroud Forward of FS 621.00

1. Job Set−Up Information

Subtask 28−20−01−944−001
A. Consumable Materials
REFERENCE DESIGNATION
05−036 Fluid, leak detector

Subtask 28−20−01−943−001
B. Tools and Equipment
REFERENCE DESIGNATION
G601R121605−1 Gaseous test panel
G601R282001−1 Leak test kit − fuel and vent line shroud

2. Procedure
Subtask 28−20−01−480−001
Refer to Figure 501.
A. Connect the test equipment as follows:
NOTE: No fuel has to be drained to perform this procedure.
(1) Close all of the shutoff valves on the gaseous test panel.
(2) Connect the hose assembly to the shroud drain fitting (1) at FS506.40 on the over
wing fairing.
(3) Connect the gaseous test panel to the hose assembly.
(4) Connect the gaseous test panel to pressurized air.
(5) Install a plug assembly in the shroud drain fittings (2) at FS 504.90 on the over wing
fairing.
(6) Install a plug assembly in each of the other shroud drain fittings (3), (4), and (5),
between the main wheel well and the aft pressure bulkhead FS 621.00.

Master
EFFECTIVITY: See Pageblock 28−20−01 page 501
28−20−01 Page 501
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
Subtask 28−20−01−780−001
B. Do a blockage test of the fuel line shroud as follows:
CAUTION: DO NOT PRESSURIZE THE FUEL LINE SHROUD TO MORE THAN
9 PSI (62 KPA). YOU CAN CAUSE DAMAGE TO THE FUEL LINE
SHROUD.
(1) Make sure that the pressure on the gaseous test panel is 9 psi (62 kPa) or less.
(2) Slowly open the outlet valve on the gaseous test panel to pressurize the fuel line
shroud.
(3) For each of the shroud drain fittings with a plug assembly, do the steps that follow:
(a) Remove the plug assembly from the shroud drain fitting.
(b) Make sure that air flows out of the shroud drain fitting.
(c) Install the plug assembly in the shroud drain fitting.
(4) Close the outlet valve on the gaseous test panel and release the pressure.

Subtask 28−20−01−780−002
C. Do a pressure test of the fuel line shroud as follows:
CAUTION: DO NOT PRESSURIZE THE FUEL LINE SHROUD TO MORE THAN
9 PSI (62 KPA). YOU CAN CAUSE DAMAGE TO THE FUEL LINE
SHROUD.
(1) Set the gaseous test panel to 9 psi (62 kPa).
(2) Slowly open the outlet valve on the gaseous test panel to pressurize the fuel line
shroud to 9PSI (62 kPa).
(3) Close the outlet valve on the gaseous test panel.
(4) After 10 minutes, examine the shroud pressure on the gaseous test panel. Make
sure that the maximum shroud pressure loss is 1.0 psi (6.89 kPa).
(5) If the shroud pressure loss is more than 1.0 psi (6.89 kPa), use leak detector fluid to
find the leak and repair it. Do the test again after the repair is completed.

3. Close Out
Subtask 28−20−01−080−001
A. Disconnect the test equipment as follows:
(1) Disconnect the pressurized air from the gaseous test panel.
(2) Disconnect the gaseous test panel from the hose assembly.
(3) Remove the hose assembly from the shroud drain fitting.
(4) Remove all of the plug assemblies from the shroud drain fittings.

Subtask 28−20−01−941−001
B. Remove all the tools, equipment, and unwanted materials from the area.

Master
EFFECTIVITY: See Pageblock 28−20−01 page 501
28−20−01 Page 502
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

LEGEND
1. Shroud drain fitting
(at FS506).
2. Shroud drain fitting
(at FS 504.90).
B
3. Shroud drain fitting
(at FS 502.40).
4. Shroud drain fitting
C (at FS 608.00).
5. Shroud drain fitting
A (at FS 572.35).
6. Shroud drain fitting
(at FS 559+20).

3 2

6
5
4 4

LEFT SIDE

2 3

1 ram2820015_001.dg, pb/sm, 24/09/01

B C
RIGHT SIDE

Fuel Line Shroud − Adjustment/Test

Figure 501

Master
EFFECTIVITY: See Pageblock 28−20−01 page 501
28−20−01 Page 503
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
TASK 28−20−01−780−802
Pressure and Blockage Test of the Engine Fuel−Feed Line

1. Job Set−Up Information

Subtask 28−20−01−944−002
A. Consumable Materials
REFERENCE DESIGNATION
05−036 Fluid, leak detector

Subtask 28−20−01−943−002
B. Tools and Equipment
REFERENCE DESIGNATION
G601R121605−1 Gaseous test panel
AN919−24D Reducer
AN929−20 Cap assembly
None specified Fuel container

Subtask 28−20−01−945−001
C. Reference Information
REFERENCE DESIGNATION
TASK 12−11−28−650−804 Suction Defueling
TASK 12−11−28−650−801 Automatic Pressure Refueling
TASK 12−11−28−650−802 Manual Pressure Refueling
TASK 28−00−00−910−801 Fuel Safety Precautions
TASK 53−83−01−000−801 Removal of the MLG Wheel Bin
TASK 53−83−01−400−801 Installation of the MLG Wheel Bin
TASK 54−60−01−000−808 Removal of the Lines Disconnect
Outboard−Access−Panels (412DB and 422DB)
TASK 54−60−01−400−808 Installation of the Lines Disconnect
Outboard−Access−Panels (412DB and 422DB)
TASK 71−00−00−868−812 Engine Wet Motor Cycle

Subtask 28−20−01−910−001
WARNING: OBEY ALL THE FUEL SAFETY PRECAUTIONS WHEN YOU DO WORK ON
THE FUEL SYSTEM AND/OR A FUEL SYSTEM COMPONENT. IF YOU DO
NOT DO THIS, YOU CAN CAUSE INJURIES TO PERSONS AND/OR
DAMAGE TO EQUIPMENT.
D. Obey all the fuel safety precautions (Ref. TASK 28−00−00−910−801).

Master
EFFECTIVITY: See Pageblock 28−20−01 page 501
28−20−01 Page 504
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
Subtask 28−20−01−650−001
E. Defuel the aircraft (Ref. TASK 12−11−28−650−804).

Subtask 28−20−01−010−001
F. Remove the access panels that follow, as applicable (Ref. TASK 54−60−01−000−808):
ACCESS DESIGNATION
412DB Power Plant Lines Disconnect (Left)
422DB Power Plant Lines Disconnect (Right)

Subtask 28−20−01−865−001
G. Open, safety, and tag the circuit breakers that follow:
CB PANEL CB NO. NAME ZONE
CBP−1 M6 L FUEL PUMP 221
CBP−1 M7 L FUEL PUMP CONT 221
CBP−1 M12 FUEL SYST CONT 221
CBP−1 N10 XFER/APU FUEL PUMP 221
CBP−2 G10 R FUEL PUMP 222
CBP−2 G11 R FUEL PUMP CONT 222
CBP−4 B10 FUEL SYST CONT 222

Subtask 28−20−01−010−002
H. For the left side engine fuel−feed tube remove the left main landing gear (MLG) wheel
bin (Ref. TASK 53−83−01−000−801).

Subtask 28−20−01−010−003
I. For the right side engine fuel−feed tube remove the left main landing gear (MLG) wheel
bin (Ref. TASK 53−83−01−000−801).

2. Procedure
Subtask 28−20−01−480−002
Refer to Figure 502 and Figure 503.

A. Connect the test equipment to the engine fuel−feed tubes, as follows:

NOTE: The procedure that follows is to connect the test equipment to the left side
engine fuel−feed tube. The procedure for the right side engine fuel−feed tube
is the same.
(1) Close the shutoff valve on the gaseous test panel.
(2) Connect the gaseous test panel to the shop air supply.
(3) Put the fuel container below the engine fuel−feed tube at the pylon connection to
collect fuel spillage.

Master
EFFECTIVITY: See Pageblock 28−20−01 page 501
28−20−01 Page 505
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
(4) Disconnect the left engine fuel−feed tube from the engine at the engine pylon
connector.
(5) Install a protective cover on the engine side of the engine fuel−feed tube.
(6) Put the fuel container near the left engine fuel−feed tube at the center fuel tank
connection to collect any fuel spillage. This is inside the main landing gear wheel
well (FS499).
(7) Disconnect the left engine fuel−feed tube at the center fuel tank connector. Remove
any fuel spillage with suitable cloths.
(8) Install a protective cap on the center fuel tank fitting.
(9) Connect the reducer to the left engine fuel−feed tube (FS499).
(10) Connect the gaseous test panel to the reducer.
(11) Make sure the left engine shutoff valve is in the open position. This will be shown by
the visual indicator on the shutoff valve body.
(12) Set the regulator on the gaseous test panel to 10.0 psi (69.0 kPa).

Subtask 28−20−01−780−003
CAUTION: DO NOT PRESSURIZE THE ENGINE FUEL−FEED LINE TO MORE THAN 45
PSI (310 KPA). IF YOU DO, YOU CAN CAUSE DAMAGE TO THE FUEL
FEED TUBES, COUPLING ASSEMBLIES AND PREFORMED PACKINGS.
B. Do a pressure test of the engine fuel−feed line, between the center tank and the engine
pylon, as follows:
NOTE: The procedure that follows is to test the left side engine fuel−feed tube. The
procedure for the right side engine fuel−feed tube is the same.
(1) Slowly open the gaseous test panel shutoff valve. Air should flow from the fuel−feed
tube at the left engine pylon connector.
(2) Close the left engine fuel−feed shutoff valve. No air should flow from the fuel−feed
tube at the left engine pylon connector.
(3) Open the fuel shutoff valve. Air should flow from the fuel−feed tube at the left
engine pylon connector.
(4) Close the test panel shutoff valve.
(5) Blank the left engine fuel−feed tube at the engine pylon connector with cap
assembly.
(6) Set the regulator on the gaseous test panel to 45 psi (310 kPa).
(7) Slowly open the gaseous test panel shutoff valve and let the fuel−feed line
pressurize. The gauge must show 45 psi (310 kPa).
(8) Close the gaseous test panel shutoff valve.
(9) After 10 minutes read the gaseous test panel pressure gauge. There should be no
drop in pressure. A pressure drop shows leakage, which must be corrected.
(10) Release the air pressure in the left engine fuel−feed line.
(11) When necessary use leak detector fluid to find the fuel leak. Then repair the leak
(Ref. TASK 28−20−01−000−801 and TASK 28−20−01−400−801). Do the test
again after the leak has been repaired.

Master
EFFECTIVITY: See Pageblock 28−20−01 page 501
28−20−01 Page 506
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
3. Close Out
Subtask 28−20−01−080−002
A. Disconnect the equipment used to test the engine fuel−feed line as follows:
(1) Turn off the shop air supply and disconnect the gaseous test panel.
(2) Disconnect the gaseous test panel from the reducer.
(3) Remove the cap assembly from the left engine fuel−feed tube at the engine pylon.
(4) Remove the protective cover from the left engine fuel−feed tube at the engine
pylon.
(5) Connect the left engine fuel−feed tube at the engine pylon. Tighten the connector to
a torque value of 1200 to 1450 inch pounds (135.58 to 163.71 Nm).
(6) Remove the reducer from the engine fuel−feed tube inside the main landing gear
wheel well (FS499).
(7) Remove the protective cover from the center fuel tank connector.
(8) Connect the left engine fuel−feed tube to the center fuel tank fitting. Tighten the
connector to a torque value of 1200 to 1450 inch pounds (135.58 to 163.71 Nm).

Subtask 28−20−01−865−002
B. Remove the tags and close the circuit breakers that follow:
CB PANEL CB NO. NAME ZONE
CBP−1 M6 L FUEL PUMP 221
CBP−1 M7 L FUEL PUMP CONT 221
CBP−1 M12 FUEL SYST CONT 221
CBP−1 N10 XFER/APU FUEL PUMP 221
CBP−2 G10 R FUEL PUMP 222
CBP−2 G11 R FUEL PUMP CONT 222
CBP−4 B10 FUEL SYST CONT 222

Subtask 28−20−01−650−002
C. Refuel the aircraft (Ref. TASK 12−11−28−650−801 or TASK 12−11−28−650−802).

Subtask 28−20−01−868−001
D. For the left side of the engine fuel−feed tube, do a left engine wet motor cycle (Ref.
TASK 71−00−00−868−812).

Subtask 28−20−01−210−001
E. Do a check for fuel leaks from the engine fuel feed−tube, as follows:
NOTE: The procedure that follows is to check the left side engine fuel−feed tube. The
procedure for the right side engine fuel−feed tube is the same.
(1) Visually inspect the left engine fuel−feed tube at the engine pylon connector for
traces of fuel leakage. There must be no leakage.

Master
EFFECTIVITY: See Pageblock 28−20−01 page 501
28−20−01 Page 507
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
(2) Visually inspect the left engine fuel−feed tube at the center fuel tank connector for
traces of fuel leakage. There must be no leakage.
(3) When a leak is found, do the steps that follow:
(a) Open, safety, and tag the circuit breakers referred to in para. 1G.
(b) Disconnect the left engine fuel−feed tube at the end that leaks.
(c) Inspect both connector parts for foreign objects or damage.
(d) Reconnect the left engine fuel−feed tube. Tighten the connector to a torque
value of 1200 to 1450 inch pounds (135.58 to 163.71 Nm).
(e) Remove the tags and close the circuit breakers referred to in para. 3B.
(f) Do again an engine wet motor cycle (Ref. TASK 71−00−00−868−812).
(g) Do again a check for fuel leaks from the engine fuel feed−tube.

Subtask 28−20−01−410−001
F. For the left side engine fuel−feed tube install the left main landing gear (MLG) wheel bin
(Ref. TASK 53−83−01−400−801).

Subtask 28−20−01−410−003
G. For the right side engine fuel−feed tube install the left main landing gear (MLG) wheel
bin (Ref. TASK 53−83−01−400−801).

Subtask 28−20−01−410−002
H. Install the access panels that follow, as applicable (Ref. TASK 54−60−01−400−808):
ACCESS DESIGNATION
412DB Power Plant Lines Disconnect (Left)
422DB Power Plant Lines Disconnect (Right)

Subtask 28−20−01−941−002
I. Remove all tools, equipment, and unwanted materials from the area.

Master
EFFECTIVITY: See Pageblock 28−20−01 page 501
28−20−01 Page 508
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

LEGEND
A 1. Engine fuel−feed tube.
2. Engine fuel−feed connector.
3. Motive flow fuel−feed tube.
4. Motive flow fuel−feed connector.
5. APU fuel−feed tube.
6. APU fuel−feed connector.

FW 3
D
4

6
5

FW
D
ram2820015_003.dg, jp, 30/11/99

Center Tank Fuel − Feed Tubes

Figure 502

Master
EFFECTIVITY: See Pageblock 28−20−01 page 501
28−20−01 Page 509
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

LEGEND
1. Engine fuel−feed tube.
2. Engine fuel−feed connector.
3. Motive flow fuel−feed tube.
4. Motive flow fuel−feed connector.

ram2820015_004.dg, jp, 29/11/99

Engine Pylon Fuel − Feed Tubes

Figure 503

Master
EFFECTIVITY: See Pageblock 28−20−01 page 501
28−20−01 Page 510
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
TASK 28−20−01−780−803
Pressure and Blockage Test of the Motive Flow−Fuel Feed Line

1. Job Set−Up Information

Subtask 28−20−01−944−003
A. Consumable Materials
REFERENCE DESIGNATION
05−036 Fluid, Leak Detector
05−022 Nitrogen, gaseous

Subtask 28−20−01−943−003
B. Tools and Equipment
REFERENCE DESIGNATION
S601R2822TFIX1 Nitrogen control panel
AN919−10D Reducer
AN929−8 Cap assembly
None specified Fuel container

Subtask 28−20−01−946−001
C. Reference Information
REFERENCE DESIGNATION
TASK 12−11−28−650−804 Suction Defueling
TASK 12−11−28−650−801 Automatic Pressure Refueling
TASK 12−11−28−650−802 Manual Pressure Refueling
TASK 28−00−00−910−801 Fuel Safety Precautions
TASK 53−83−01−000−801 Removal of the MLG Wheel Bin
TASK 53−83−01−400−801 Installation of the MLG Wheel Bin
TASK 54−60−01−000−808 Removal of the Lines Disconnect
Outboard−Access−Panels (412DB and 422DB)
TASK 54−60−01−400−801 Installation of the Lines Disconnect
Outboard−Access−Panels (412DB and 422DB)
TASK 71−00−00−868−806 Engine Start
TASK 71−00−00−868−807 Engine Stop (Normal)

Master
EFFECTIVITY: See Pageblock 28−20−01 page 501
28−20−01 Page 511
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
Subtask 28−20−01−910−002
WARNING: OBEY ALL THE FUEL SAFETY PRECAUTIONS WHEN YOU DO WORK ON THE
FUEL SYSTEM AND/OR A FUEL SYSTEM COMPONENT. IF YOU DO NOT DO
THIS, YOU CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO
EQUIPMENT.
D. Obey all the fuel safety precautions (Ref. TASK 28−00−00−910−801).

Subtask 28−20−01−650−003
E. Defuel the aircraft (Ref. TASK 12−11−28−650−804).

Subtask 28−20−01−010−004
F. Remove the access panels that follow, as applicable (Ref. TASK 54−60−01−000−808):
ACCESS DESIGNATION
412DB Power Lines Disconnect (Left)
422DB Power Lines Disconnect (Right)

Subtask 28−20−01−865−003
G. Open, safety, and tag the circuit breakers that follow:
CB PANEL CB NO. NAME ZONE
CBP−1 M6 L FUEL PUMP 221
CBP−1 M7 L FUEL PUMP CONT 221
CBP−1 M12 FUEL SYST CONT 221
CBP−1 N10 XFER/APU FUEL PUMP 221
CBP−2 G10 R FUEL PUMP 222
CBP−2 G11 R FUEL PUMP CONT 222
CBP−4 B10 FUEL SYST CONT 222

Subtask 28−20−01−010−005
H. For the left side motive fuel−feed tube remove the left main landing gear (MLG) wheel
bin (Ref. TASK 53−83−01−000−801).

Subtask 28−20−01−010−006
I. For the right side motive fuel−feed tube remove the right main landing gear (MLG) wheel
bin (Ref. TASK 53−83−01−000−801).

2. Procedure
Subtask 28−20−01−480−003
Refer to Figure 502 and Figure 503.

Master
EFFECTIVITY: See Pageblock 28−20−01 page 501
28−20−01 Page 512
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
A. Connect the test equipment to the motive fuel−feed tubes, as follows:
NOTE: The procedure that follows is to connect the test equipment to the left side
motive fuel−feed tube. The procedure for the right side motive fuel−feed tube
is the same.
(1) Put the fuel container below the motive flow fuel−feed tube at the pylon connection
to collect fuel spillage.
(2) Disconnect the left motive flow fuel−feed tube from the engine at the engine pylon
connector.
(3) Install a protective cover on the engine side of the motive flow fuel−feed tube.
(4) Put the fuel container near the left motive flow fuel−feed tube at the center fuel tank
connection to collect any fuel spillage. This is inside the main landing gear wheel
well (FS499).
(5) Disconnect the left motive flow fuel−feed tube at the center fuel tank connector.
Remove any fuel spillage with suitable cloths.
(6) Install a protective cap on the center fuel tank fitting.
(7) Connect the nitrogen control panel to the reducer.
(8) Connect the reducer to the left motive flow fuel−feed tube (FS502).
(9) Close the outlet valve on the nitrogen control panel.
(10) Connect the nitrogen control panel to the gaseous nitrogen bottle.
(11) Set the regulator on the nitrogen control panel to 10 psi (69.0kPa).

Subtask 28−20−01−780−004
WARNING: WHEN YOU DO A PRESSURE TEST, KEEP ALL PERSONNEL AWAY
FROM THE AIRCRAFT. THERE IS A RISK OF EXPLOSION OR OTHER
INCIDENT. IF YOU DO NOT DO THIS, YOU CAN CAUSE INJURY TO
PERSONS.
CAUTION: DO NOT PRESSURIZE THE MOTIVE FLOW FUEL−FEED LINE TO MORE
THAN 525 PSI (3620 KPA). IF YOU USE A HIGHER PRESSURE, YOU CAN
CAUSE DAMAGE TO THE MOTIVE FLOW FUEL−FEED LINE, THE FUEL
LINE SHROUD AND ADJACENT COMPONENTS.
B. Do a pressure test of the motive flow fuel−feed line, between the center tank and the
engine pylon, as follows:
NOTE: The procedure that follows is to test the left side motive flow fuel−feed tube.
The procedure for the right side motive flow fuel−feed tube is the same.
(1) Slowly open the outlet valve on the nitrogen control panel. Nitrogen should flow
from the motive flow fuel−feed tube at the left engine pylon connector.
(2) Close the outlet valve on the nitrogen control panel.
(3) Blank the left motive flow fuel−feed tube at engine pylon connector with the cap
assembly.
(4) Slowly open the outlet valve on the nitrogen control panel and let the motive flow
fuel−feed line pressurize.
(5) Gradually increase the pressure as shown on the nitrogen control panel to 525 psi
(3620 kPa).

Master
EFFECTIVITY: See Pageblock 28−20−01 page 501
28−20−01 Page 513
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
(6) Close the outlet valve on the nitrogen control panel.
(7) After 10 minutes read the nitrogen control panel pressure gauge. There should be
no drop in pressure. A pressure drop shows leakage, which must be corrected.
(8) Release the nitrogen pressure in the left motive flow fuel−feed line.
(9) When necessary use leak detector fluid to find the fuel leak. Then repair the leak
(Ref. TASK 28−20−01−000−801 and TASK 28−20−01−400−801). Do the test again
after the leak has been repaired.

3. Close Out
Subtask 28−20−01−080−003
A. Disconnect the equipment used to test the motive flow fuel−feed line, as follows:
(1) Turn the gaseous nitrogen bottle and disconnect the gaseous test panel.
(2) Remove the cap assembly from the left motive flow fuel−feed tube at the engine
pylon.
(3) Remove the protective cover from the left motive flow fuel−feed tube at the engine
pylon.
(4) Connect the left motive flow fuel−feed tube at the engine pylon. Tighten the
connector to a torque value of 300 to 400 inch pounds (33.87 to 45.16 Nm).
(5) Remove the reducer from the motive flow fuel−feed tube (FS502).
(6) Remove the protective cover from the center fuel tank connector.
(7) Connect the left motive flow fuel−feed tube to the center fuel tank fitting. Tighten the
connector to a torque value of 300 to 400 inch pounds (33.87 to 45.16 Nm).

Subtask 28−20−01−865−004
B. Remove the tags and close the circuit breakers that follow:
CB PANEL CB NO. NAME ZONE
CBP−1 M6 L FUEL PUMP 221
CBP−1 M7 L FUEL PUMP CONT 221
CBP−1 M12 FUEL SYST CONT 221
CBP−1 N10 XFER/APU FUEL PUMP 221
CBP−2 G10 R FUEL PUMP 222
CBP−2 G11 R FUEL PUMP CONT 222
CBP−4 B10 FUEL SYST CONT 222

Subtask 28−20−01−650−004
C. Refuel the aircraft (Ref. TASK 12−11−28−650−801 or TASK 12−11−28−650−802).

Master
EFFECTIVITY: See Pageblock 28−20−01 page 501
28−20−01 Page 514
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
Subtask 28−20−01−868−002
D. For the left side motive flow fuel−feed tube, do a left engine start (Ref. TASK
71−00−00−868−806).

Subtask 28−20−01−868−003
E. For the left side motive flow fuel−feed tube, do a left engine stop (Ref. TASK
71−00−00−868−807).

Subtask 28−20−01−210−002
F. Do a check for fuel leaks from the motive flow fuel feed−tube, as follows:
NOTE: The procedure that follows is to check the left side motive flow fuel−feed tube.
The procedure for the right side motive flow fuel−feed tube is the same.
(1) Visually inspect the left motive flow fuel−feed tube at the engine pylon connector for
traces of fuel leakage. There must be no leakage.
(2) Visually inspect the left motive flow fuel−feed tube at the center fuel tank connector
for traces of fuel leakage. There must be no leakage.
(3) When a leak is found, do the steps that follow:
(a) Open, safety, and tag the circuit breakers referred to in para. 1G.
(b) Disconnect the left motive flow fuel−feed tube at the end that leaks.
(c) Inspect both connector parts for foreign objects or damage.
(d) Reconnect the left motive flow fuel−feed tube. Tighten the connector to a
torque value of 300 to 400 inch pounds (33.87 to 45.16 Nm).
(e) Remove the tags and close the circuit breakers referred to in para. 3B.
(f) Do again and engine start (Ref. TASK 71−00−00−868−806).
(g) Do again an engine stop (Ref. TASK 71−00−00−868−807).
(h) Do again a check for fuel leaks from the motive flow fuel feed−tube.

Subtask 28−20−01−410−004
G. For the left side motive flow fuel−feed tube install the left main landing gear (MLG) wheel
bin (Ref. TASK 53−83−01−400−801).

Subtask 28−20−01−410−005
H. For the right side motive flow fuel−feed tube install the left main landing gear (MLG)
wheel bin (Ref. TASK 53−83−01−400−801).

Subtask 28−20−01−410−006
I. Install the access panels that follow, as applicable (Ref. TASK 54−60−01−400−808):
ACCESS DESIGNATION
412DB Power Lines Disconnect (Left)
422DB Power Lines Disconnect (Right)

Master
EFFECTIVITY: See Pageblock 28−20−01 page 501
28−20−01 Page 515
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
Subtask 28−20−01−941−003
J. Remove all tools, equipment, and unwanted materials from the area.

Master
EFFECTIVITY: See Pageblock 28−20−01 page 501
28−20−01 Page 516
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
TASK 28−20−01−780−804
Pressure and Blockage Test of the APU Fuel−Feed Line

1. Job Set−Up Information

Subtask 28−20−01−944−004
A. Consumable Materials
REFERENCE DESIGNATION
05−036 Fluid, Leak Detector

Subtask 28−20−01−945−002
B. Parts
REF NAME OF PART QTY IPC SEQUENCE NO.
4 Union 1 IPC 49−15−00−01−317
5 Preformed packing 1 IPC 49−15−00−01−318

Subtask 28−20−01−943−005
C. Tools and Equipment
REFERENCE DESIGNATION
G601R121605−1 Gaseous test panel
AN919−10D Reducer
AN929−8 Cap assembly
None specified Fuel container

Subtask 28−20−01−946−003
D. Reference Information
REFERENCE DESIGNATION
TASK 12−11−28−650−804 Suction Defueling
TASK 12−11−28−650−801 Automatic Pressure Refueling
TASK 12−11−28−650−802 Manual Pressure Refueling
TASK 28−00−00−910−801 Fuel Safety Precautions
TASK 53−83−01−000−801 Removal of the MLG Wheel Bin
TASK 53−83−01−400−801 Installation of the MLG Wheel Bin
TASK 49−31−01−000−801 Removal of the APU Fuel Control Unit
TASK 49−31−01−400−801 Installation of the APU Fuel Control Unit
TASK 49−31−01−710−801 Operational Test of the APU Fuel Control Unit

Master
EFFECTIVITY: See Pageblock 28−20−01 page 501
28−20−01 Page 517
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
Subtask 28−20−01−910−003
WARNING: OBEY ALL THE FUEL SAFETY PRECAUTIONS WHEN YOU DO WORK ON
THE FUEL SYSTEM AND/OR A FUEL SYSTEM COMPONENT. IF YOU DO
NOT DO THIS, YOU CAN CAUSE INJURIES TO PERSONS AND/OR
DAMAGE TO EQUIPMENT.
E. Obey all the fuel safety precautions (Ref. TASK 28−00−00−910−801).
F. At the APU control panel, make sure that the PWR FUEL switch/light is off. When the
PWR FUEL switch/light is not off, push out the PWR FUEL switch/light.

Subtask 28−20−01−650−005
G. Defuel the aircraft (Ref. TASK 12−11−28−650−804).

Subtask 28−20−01−010−007
H. Open/remove the access doors/panels that follow:
ACCESS DESIGNATION
311BB Aft equipment−component door
311BZ APU access panel

Subtask 28−20−01−865−007
I. Open, safety, and tag the circuit breakers that follow:
CB PANEL CB NO. NAME ZONE
CBP−1 N10 XFER/APU FUEL PUMP 221
CBP−1 N12 XFER/APU ECU 221
CBP−1 S3 FUEL SOV APU 221
CBP−5 A1 APU ACT 311

2. Procedure
Subtask 28−20−01−010−008
Refer to Figure 502 and Figure 504.

A. Remove the right main landing gear (MLG) wheel bin (Ref. TASK 53−83−01−000−801).

Subtask 28−20−01−480−004
B. Connect the test equipment to the auxiliary power unit (APU) fuel−feed tube, as follows:
(1) Go inside the APU enclosure and put the fuel container below the fuel control unit
(FCU) fuel inlet port, to collect fuel spillage.
(2) Disconnect the APU fuel inlet hose from the FCU inlet port union (Ref. TASK
49−31−01−000−801).
(3) Install a protective cover on the FCU fuel inlet port.
(4) Close the shutoff valve on the gaseous test panel.

Master
EFFECTIVITY: See Pageblock 28−20−01 page 501
28−20−01 Page 518
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
(5) Connect the gaseous test panel to the shop air supply.
(6) Disconnect the APU fuel feed tube at the center tank connection inside the right
(MLG) wheel well.
(7) Install a protective cover on the fuel feed tube.
(8) Connect the gaseous test panel to the APU fuel−feed tube with the reducer.
(9) Make sure the APU fuel−feed shutoff valve is in the open position. This will be
shown by the visual indicator on the shutoff valve body.
(10) Set the regulator on the gaseous test panel to 10.0 psi (69.0 kPa).

Subtask 28−20−01−780−005
CAUTION: DO NOT PRESSURIZE THE APU FUEL−FEED LINE TO MORE THAN 45
PSI (310 KPA). IF YOU DO, YOU CAN CAUSE DAMAGE TO THE
FUEL−FEED TUBES, COUPLING ASSEMBLIES AND PREFORMED
PACKINGS.
C. Do a pressure test of the APU fuel−feed line, between the center tank and the APU fuel
control unit (FCU), as follows:
(1) Slowly open the gaseous test panel shutoff valve. Air should flow from the APU
fuel−feed tube at the APU enclosure connection.
(2) Close the APU shutoff valve. No air should flow from the APU fuel−feed tube at the
APU enclosure connection.
(3) Open the APU fuel shutoff valve.
(4) Blank the APU fuel inlet hose with the cap assembly.
(5) Set the regulator on the gaseous test panel to 45 psi (310 kPa).
(6) Slowly open the gaseous test panel shutoff valve and let the APU fuel−feed line
pressurize. The gauge must show 45 psi (310 kPa).
(7) Close the gaseous test panel shutoff valve.
(8) After 10 minutes read the gaseous test panel pressure gauge. There should be no
drop in pressure. A pressure drop shows leakage, which must be corrected.
(9) Release the air pressure in the APU fuel−feed line.
(10) When necessary use leak detector fluid to find the fuel leak. Then repair the leak
(Ref. TASK 28−20−01−000−801 and TASK 28−20−01−400−801). Do the test again
after the leak has been repaired.

3. Close Out
Subtask 28−20−01−080−004
A. Disconnect the equipment used to test the APU fuel−feed line, as follows:
(1) Turn off the shop air supply and disconnect the gaseous test panel.
(2) Disconnect the gaseous test panel from the reducer.
(3) Connect the fuel inlet hose, as follows (Ref. TASK 49−31−01−400−801).
(a) Remove the cap assembly fro the APU fuel inlet hose inside the APU
enclosure.

Master
EFFECTIVITY: See Pageblock 28−20−01 page 501
28−20−01 Page 519
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
(b) Remove the protective cover from the fuel inlet port of the FCU.
(c) Reconnect the aft APU fuel inlet hose to the inlet port of the FCU.
(4) Remove the protective cover from the APU center fuel−tank fitting inside the right
(MLG) wheel well.
(5) Reconnect the forward APU fuel−feed tube at center tank fitting. Tighten the
connector to a torque of 210 to 420 inch pounds (23.71 to 47.72 Nm).

Subtask 28−20−01−865−008
B. Remove the tags and close the circuit breakers that follow:
CB PANEL CB NO. NAME ZONE
CBP−1 N10 XFER/APU FUEL PUMP 221
CBP−1 N12 XFER/APU APU ECU 221
CBP−1 S3 FUEL SOV APU 221
CBP−5 A1 APU ACT 311

Subtask 28−20−01−650−006
C. Refuel the aircraft (Ref. TASK 12−11−28−650−801 or TASK 12−11−28−650−802).

Subtask 28−20−01−710−001
D. Do the operational test of the FCU (Ref. TASK 49−31−01−710−801).

Subtask 28−20−01−210−003
E. Do check for fuel leaks from the APU fuel−feed line, as follows:
(1) Visually inspect APU fuel inlet hose at the FCU connector for traces of fuel leakage.
There must be no leakage.
(2) Visually inspect the APU fuel−feed tube at the center tank connector for traces of
fuel leakage. There must be no leakage.
(3) When a leak is found, do the steps that follow:
(a) Open, safety, and tag the circuit breakers referred to in para. 1I.
(b) Disconnect the APU fuel inlet hose to the FCU inlet port, when fuel leaks at
this connection (Ref. TASK 49−31−01−991−802). Or, disconnect the APU fuel
feed tube at the center tank connector, when fuel leaks at this connection.
(c) Inspect both applicable connector parts for foreign objects or damage.
(d) Reconnect the APU fuel inlet hose to the FCU inlet port, when applicable (Ref.
TASK 49−31−01−400−801). Or, reconnect the APU fuel−feed tube at the
center tank connector. Tighten the connector to 210 to 420 inch pounds (23.71
to 47.42 Nm).
(e) Remove the tags and close the circuit breakers referred to in para. 3B.
(f) Do again the operational test of the FCU (Ref. TASK 49−31−01−710−801).

Master
EFFECTIVITY: See Pageblock 28−20−01 page 501
28−20−01 Page 520
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
Subtask 28−20−01−410−008
F. Install the right (MLG) wheel bin (Ref. TASK 53−83−01−400−801).

Subtask 28−20−01−410−007
G. Close/install the access doors/panels that follow:
ACCESS DESIGNATION
311BB Aft equipment−component door
311BZ APU access panel

Subtask 28−20−01−941−004
H. Remove all tools, equipment, and unwanted materials from the area.

Master
EFFECTIVITY: See Pageblock 28−20−01 page 501
28−20−01 Page 521
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

LEGEND
1. Auxillary Power Unit (APU).
2. Fuel Control Unit (FCU).
3. Fuel inlet hose.
4. Union fitting.
5. Preformed packing.

3
ram2820015_005(0).dg, rt/rm, 07/12/99

5
2
4

APU Fuel − Feed to FCU Connection

Figure 504

Master
EFFECTIVITY: See Pageblock 28−20−01 page 501
28−20−01 Page 522
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C ALL
TUBE, SHROUD DRAIN, PRESSURE BOX − REMOVAL/INSTALLATION

1. General
A. The maintenance procedures that follow are for the removal and installation of the
pressure−box−shroud−drain tube (written as the shroud−drain tube in these
procedures). The shroud−drain tube is routed from the bottom of the pressure box to an
overboard vent. The pressure box is installed under the cabin floor between FS 499 and
FS 559. The overboard vent is installed in the fuselage, above the left wing at FS 506.

TASK 28−20−05−000−801
Removal of the Pressure−Box−Shroud−Drain Tube

1. Job Set−Up Information

Subtask 28−20−05−946−001
A. Tools and Equipment
REFERENCE DESIGNATION
None specified Container, fuel
B. Reference Information
REFERENCE DESIGNATION
TASK 28−00−00−910−801 Fuel Safety Precautions
TASK 53−83−01−000−801 Removal of the MLG Wheel Bin

2. Job Set−Up
Subtask 28−20−05−910−001
WARNING: OBEY ALL THE FUEL SAFETY PRECAUTIONS WHEN YOU DO WORK ON THE
FUEL SYSTEM AND/OR A FUEL SYSTEM COMPONENT. IF YOU DO NOT DO
THIS, YOU CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO
EQUIPMENT.
A. Obey all the fuel safety precautions (Ref. TASK 28−00−00−910−801).

Subtask 28−20−05−010−001
B. Remove the left wheel bin (163AZ) from the main wheel well (Ref. TASK
53−83−01−000−801).
C. Put the fuel container below the pressure−box−shroud−drain tube.

Master
EFFECTIVITY: See Pageblock 28−20−05 page 401
28−20−05 Page 401
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
3. Procedure
**ON A/C 7003−7067, 7069−7288

Subtask 28−20−05−020−001
Refer to Figure 401.
A. Remove the pressure−box−shroud−drain tube, as follows:
(1) Loosen the hose clamp (1) from the shroud−drain tube (2).
NOTE: The use of a mirror will make it easier to find the pressure−box fitting (3)
and the hose clamp (1).
(2) Disconnect the shroud−drain tube (2) from the pressure−box fitting (3).
(3) Remove the hose clamp (1) from the shroud−drain tube (2).
(4) Loosen the hose clamp (4) from the shroud−drain tube (2).
(5) Disconnect the shroud−drain tube (2) from the overboard−vent fitting (5).
(6) Remove the hose clamp (4) from the shroud−drain tube (2).
(7) Hold the shroud−drain tube (2) and remove the screw (6) and the washer (7).
(8) Remove the clamp (8) from the sleeve (9).
(9) Remove the sleeve (9) from the shroud−drain tube (2).
(10) Put a protective plug in each end of the shroud−drain tube (2).

**ON A/C 7289−7990, 8000−8064, 8066−8068

Subtask 28−20−05−020−002
Refer to Figure 402.
B. Remove the pressure−box−shroud−drain tube, as follows:
(1) Loosen the hose clamp (1) from the shroud−drain tube (2).
NOTE: The use of a mirror will make it easier to find the pressure−box fitting (3)
and the hose clamp (1).
(2) Disconnect the shroud−drain tube (2) from the pressure−box fitting (3).
(3) Remove the hose clamp (1) from the shroud−drain tube (2).
(4) Loosen the hose clamp (4) from the shroud−drain tube (2).
(5) Disconnect the shroud−drain tube (2) from the overboard−vent fitting (5).
(6) Remove the hose clamp (4) from the shroud−drain tube (2).
(7) Hold the shroud−drain tube (2) and remove the screw (6) and the washer (7).
(8) Remove the clamp (8) from the shroud−drain tube (2).
(9) Put a protective plug in each end of the shroud−drain tube (2).

Master
EFFECTIVITY: See Pageblock 28−20−05 page 401
28−20−05 Page 402
Dec 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL

A 2

9 8

2
3
6

2
B

LEGEND
4
1. Hose clamp.
5 2. Shroud drain tube.
C 3. Pressure box fitting.
4. Hose clamp.
ram2820054_001.dg, pt/rm, 29/04/99

5. Overboard vent fitting.

2 6. Screw.
7. Washer.
8. Clamp.
9. Sleeve.
D

Pressure−Box−Shroud−Drain Tube − Removal/Installation

Figure 401

Master
EFFECTIVITY: See Pageblock 28−20−05 page 401
28−20−05 Page 403
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

A 2

2
3
6

2
B

LEGEND
4
1. Hose clamp.
5 2. Shroud drain tube.
C 3. Pressure box fitting.
4. Hose clamp.
ram2820054_002.dg, pt/rm, 29/04/99

5. Overboard vent fitting.

2 6. Screw.
7. Washer.
8. Clamp.

Pressure−Box−Shroud−Drain Tube − Removal/Installation

Figure 402

Master
EFFECTIVITY: See Pageblock 28−20−05 page 401
28−20−05 Page 404
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C ALL
TASK 28−20−05−400−801
Installation of the Pressure−Box−Shroud−Drain Tube

1. Job Set−Up Information

Subtask 28−20−05−944−001
A. Consumable Materials
REFERENCE DESIGNATION
06−002 Petrolatum

Subtask 28−20−05−945−001
B. Parts
REF NAME OF PART QTY IPC SEQUENCE NO.
1 Clamp, hose 1 IPC 28−30−01−01−015
4 Clamp, hose 1 IPC 28−30−01−01−015
6 Screw 1 IPC 28−30−01−01−025
7 Washer 1 IPC 28−30−01−01−030

Subtask 28−20−05−946−002
C. Reference Information
REFERENCE DESIGNATION
TASK 28−20−01−780−801 Pressure and Blockage Test of the Fuel Line
Shroud
TASK 53−83−01−400−801 Installation of the MLG Wheel Bin

2. Job Set−Up
Subtask 28−20−05−910−002
WARNING: OBEY ALL THE FUEL SAFETY PRECAUTIONS WHEN YOU DO WORK ON THE
FUEL SYSTEM AND/OR A FUEL SYSTEM COMPONENT. IF YOU DO NOT DO
THIS, YOU CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO
EQUIPMENT.
A. Obey all the fuel safety precautions (Ref. TASK 28−00−00−910−801).

Subtask 28−20−05−869−001
B. Make sure that the aircraft is in the same configuration as in the removal task.

Master
EFFECTIVITY: See Pageblock 28−20−05 page 401
28−20−05 Page 405
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
3. Procedure
**ON A/C 7003−7067, 7069−7288

Subtask 28−20−05−420−001
Refer to Figure 401.
A. Install the pressure−box−shroud−drain tube, as follows:
(1) Remove the plug from each end of the pressure−box−shroud−drain tube (2).
(2) Apply petrolatum internally to both ends of the shroud−drain tube (2).
(3) Slide the sleeve (9) over the shroud−drain tube (2) to its approximate right of center
position.
(4) Put the shroud−drain tube (2) in position.
(5) Put the clamp (8) around the sleeve (9) and loosely install the screw (6) together
with washer (7).
(6) Put the hose clamp (4) around the shroud−drain tube (2).
(7) Slide the shroud−drain tube (2) onto the overboard−vent fitting (5).
(8) Put the hose clamp (4) in position and tighten.
(9) Put the hose clamp (1) around the shroud−drain tube (2).
(10) Slide the shroud−drain tube (2) onto the pressure−box fitting (3).
(11) Put the hose clamp (1) in position and tighten.
NOTE: The use of a mirror will make it easier to find the pressure−box fitting (3).
(12) Move the clamp (8) to its correct position and tighten the screw (6).

**ON A/C 7289−7990, 8000−8064, 8066−8068

Subtask 28−20−05−420−002
Refer to Figure 402.
B. Install the pressure−box−shroud−drain tube, as follows:
(1) Remove the plug from each end of the pressure−box−shroud−drain tube (2).
(2) Apply petrolatum internally to both ends of the shroud−drain tube (2).
(3) Put the shroud−drain tube (2) in position.
(4) Put the hose clamp (4) around the shroud−drain tube (2).
(5) Slide the shroud−drain tube (2) onto the overboard−vent fitting (5).
(6) Put the hose clamp (4) in position and tighten.
(7) Put the hose clamp (1) around the shroud−drain tube (2).
(8) Slide the shroud−drain tube (2) onto the pressure−box fitting (3).
(9) Put the hose clamp (1) in position and tighten.
NOTE: The use of a mirror will make it easier to find the pressure box fitting (3).

Master
EFFECTIVITY: See Pageblock 28−20−05 page 401
28−20−05 Page 406
Dec 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C ALL

Subtask 28−20−05−780−001
C. Do a pressure and blockage test of the fuel−line shroud (Ref. TASK
28−20−01−780−801).

Subtask 28−20−05−410−001
D. Install the left wheel bin (163AZ) in the main wheel well (Ref. TASK
53−83−01−400−801).

4. Close Out
Subtask 28−20−05−941−001
A. Remove all tools, equipment, and unwanted materials from the work area.

Master
EFFECTIVITY: See Pageblock 28−20−05 page 401
28−20−05 Page 407
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C ALL
ENGINE FUEL FEED SYSTEM − DESCRIPTION AND OPERATION

1. General
A. The engine fuel−feed system supplies fuel to the engines. The engine fuel−feed system
has the components that follow:
± Two primary ejector pumps
± Two fuel−feed check valves
± Two engine−fuel−feed shutoff valves
± Two fuel line shrouds.
2. Component Details
A. Primary Ejector Pump
Refer to Figure 1.
(1) The primary ejector pumps are venturi−type ejector tubes that are operated by the
motive flow system. These pumps move fuel from the collector tanks to the engine
feed manifold. The primary ejector pumps are installed on top of the collector tanks
in the center wing box.
(2) Each primary ejector pump has a motive flow port, a venturi tube, a pickup port, and
an output port. When motive flow pressure is supplied to the motive flow port, it
causes a venturi effect in the venturi tube. This causes fuel at the pickup port to
move through the pump to the output port, and to move through the engine feed
manifold.
B. Fuel−Feed Check Valve
(1) The fuel−feed check valves are spring−loaded bipetal−flapper valves that prevent
reverse fuel flow in the engine feed manifold. They are in the engine feed manifold
downstream of the primary ejector pump.
(2) Each fuel−feed check valve has a spring, a bipetal−flapper assembly, and a valve
seat. The valve seat holds the bipetal−flapper assembly in place in the fuel feed
manifold. When pressure in the fuel feed manifold pushes the bipetal flapper
assembly, it opens the two passages in the valve seat. When fuel flow in the engine
feed manifold stops, the spring pushes the bipetal−flapper assembly back in place,
which closes the valve.
C. Engine−Fuel−Feed Shutoff Valve
(1) The engine−fuel−feed shutoff valves are electrically−operated butterfly valves that
stop the flow of fuel to the engines during an engine fire. They are located above
the center wing box, connected to the fuel feed lines.
(2) Each engine−fuel−feed shutoff valve has a 28−volt−dc motor, a status switch, a
butterfly flapper, and a valve body. When a close−valve signal is supplied to the
valve motor, the motor turns the butterfly flapper and closes the passage in the
valve body. This stops fuel flow in the engine feed line. When the butterfly valve is
closed, the status switch closes the contacts in the closed−valve−position circuit to
supply a valve−closed status signal.
(3) When an open−valve signal is supplied to the valve motor, the motor turns the
butterfly flapper in the other direction and opens the passage in the valve body.
This also causes the status switch to close the contacts in the open−valve−position

Master
EFFECTIVITY: See Pageblock 28−21−00 page 1
28−21−00 Page 1
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
circuit to supply a valve−open status signal.
D. Fuel Line Shroud
(1) The fuel line shrouds contain the engine feed lines that are installed outside of the
center wing box. These shrouds collect fuel leakage from the engine feed lines. Any
fuel that goes into the shrouds is drained overboard.
3. Operation
Refer to Figure 2.
A. The engine fuel−feed system supplies fuel to the engines during normal operation. When
the engines operate, motive pressure is supplied by the motive flow system (28−22−00)
to the primary ejector pumps. This causes the primary ejector pumps to move fuel from
the collector tanks to the engine feed manifold. The fuel−feed check valve controls the
direction of flow in this manifold.
B. If there is a fire in the engine, the operator can push the applicable LH or RH ENG FIRE
PUSH switch/light on the left or right glareshield. This sends a signal to the
engine−fuel−feed shutoff valve which closes the valve. When the valve is closed, the fuel
supply to the engine is stopped.
4. Component Location Index
Refer to Figure 3.
COMPONENT NAME QTY ACCESS/ZONE REFERENCE
Check valve, fuel feed line 2 510AB, 610AB 28−21−04
Circuit breakers:
FUEL SOV R ENG, S1 1 CBP−1/221 −
FUEL SOV L ENG, S2 1 CBP−1/221 −
Pump, primary ejector 2 510AB, 610AB 28−21−01
Shroud, fuel line − 163AZ, 164AZ 28−21−13
Valve, engine fuel feed shutoff 2 163AZ, 164AZ 28−21−07

Master
EFFECTIVITY: See Pageblock 28−21−00 page 1
28−21−00 Page 2
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

C B
C

A
A

A FUEL FEED LINE PRIMARY EJECTOR

CHECK VALVE B
PUMP

ram2821000_003(2).dc, pb/ks, 11/07/95

ENGINE FUEL FEED

C SHUTOFF VALVE

Engine Fuel Feed System − Component Location/Recognition

Figure 1

Master
EFFECTIVITY: See Pageblock 28−21−00 page 1
28−21−00 Page 3
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

FROM FROM
PRIMARY
MOTIVE MOTIVE
EJECTOR
FLOW FLOW
PUMP
COLLECTOR COLLECTOR
TANK TANK

FUEL FEED
LINE CHECK
VALVE

ENGINE
FUEL FEED
SHUTOFF
VALVE
TO TO
ENGINE ENGINE
ram2821000_001.dg, PB, 08/05/91

Engine Fuel Feed System − Schematic

Figure 2

Master
EFFECTIVITY: See Pageblock 28−21−00 page 1
28−21−00 Page 4
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

610AB 510AB

NOTE
500 series panels are on the left side.
600 series panels are on the right side.

ram2821000_002.dg, PB, 08/05/91

Engine Fuel Feed System − Component Access

Figure 3

Master
EFFECTIVITY: See Pageblock 28−21−00 page 1
28−21−00 Page 5
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C ALL
ENGINE FUEL FEED SYSTEM − ADJUSTMENT/TEST

1. General
A. The maintenance procedure that follows is for the leak test of the engine fuel−feed
tubes. The engine fuel−feed tubes are installed in the center fuel tank.

TASK 28−21−00−790−801
Leak Test of the Engine Fuel−Feed Tubes

1. Job Set−Up Information

Subtask 28−21−00−946−001
A. Reference Information
REFERENCE DESIGNATION
TASK 12−11−28−650−801 Automatic Pressure Refueling
TASK 12−11−28−650−802 Manual Pressure Refueling
TASK 12−11−28−650−804 Suction Defueling
TASK 12−11−28−650−805 Gravity Defueling
TASK 24−00−00−910−801 Electrical/Electronic Safety Precautions
TASK 28−00−00−910−801 Fuel Safety Precautions
TASK 28−11−00−840−801 Prepare Fuel Tank For Access
TASK 28−11−01−000−802 Removal of the Aluminum Access Panel
TASK 28−11−01−400−802 Installation of the Aluminum Access Panel
TASK 71−00−00−868−806 Engine Start
TASK 71−00−00−868−807 Engine Shutdown (Normal)

2. Job Set−Up
Subtask 28−21−00−910−001
WARNING: OBEY ALL THE FUEL SAFETY PRECAUTIONS WHEN YOU DO WORK ON
THE FUEL SYSTEM AND/OR A FUEL SYSTEM COMPONENT. IF YOU DO
NOT DO THIS, YOU CAN CAUSE INJURIES TO PERSONS AND/OR
DAMAGE TO EQUIPMENT.
A. Obey all the fuel safety precautions (Ref. TASK 28−00−00−910−801).

Subtask 28−21−00−910−002
WARNING: OBEY ALL THE SAFETY PRECAUTIONS WHEN YOU DO MAINTENANCE
ON OR NEAR ELECTRICAL/ELECTRONIC EQUIPMENT. IF YOU DO NOT
DO THIS, YOU CAN CAUSE INJURIES TO PERSONS AND DAMAGE TO
EQUIPMENT.
B. Obey all the electrical/electronic safety precautions (Ref. TASK 24−00−00−910−801).

Master
EFFECTIVITY: See Pageblock 28−21−00 page 501
28−21−00 Page 501
Dec 15/2004
 C
AIRCRAFT MAINTENANCE MANUAL
Subtask 28−21−00−860−001
C. Make sure of the conditions that follow:
(1) The fuel load of each of the left and right main fuel tank is 1700 ±200 lbs (771 ±91
kg).
(2) The fuel quantity of the center fuel tank is zero.
D. If necessary, adjust the fuel tank quantities as follows:
(1) Do an automatic pressure refueling (Ref: TASK 12−11−28−650−801) or a manual
pressure refueling (Ref. TASK 12−11−28−650−802).
(2) Do a suction defueling (Ref: TASK 12−11−28−650−804) or a gravity defueling
(Ref. TASK 12−11−28−650−805).

Subtask 28−21−00−860−002
E. Open all the water drains under the center fuel tank and make sure that you do not get
more than 1 drop per second at the water drains.
NOTE: If you get more than 1 drop per second at the water drains, make sure that the
fuel quantity of the left and right main tanks is less than 50% of the tank
capacity. This will prevent fuel transfer from the fuel transfer system.

Subtask 28−21−00−860−003
F. Close all the water drain valves under the center fuel tank .

3. Procedure
Subtask 28−21−00−790−001
A. Do the leak test of the engine fuel−feed tubes as follows:
(1) Start both engines (Ref. TASK 71−00−00−868−806).
(a) Operate the engines at 10% N1 below normal take−off power for 10 minutes.
(2) Shutdown both engine (Ref. TASK 71−00−00−868−807).
(3) Open the forward water drains under the center fuel tank
(4) If there is no fuel leakage from the water drains, the leak test is satisfactory.
(5) If there is fuel leakage from the water drains, do the steps that follow:
(a) Measure the total fuel leakage from the forward center tank water drains.
(b) Make sure that the quantity of the fuel leakage from the water drains is less
than 0.02 L (0.0052 US Gallons) for each minute of engine operation.
NOTE: This leakage is acceptable through the transfer ejector only.
(c) Remove the applicable access panels that follow: (Ref. TASK
28−11−01−000−802)
ACCESS DESCRIPTION
510AB Aluminum Access Panel (Center Fuel Tank)
610AB Aluminum Access Panel (Center Fuel Tank)

Master
EFFECTIVITY: See Pageblock 28−21−00 page 501
28−21−00 Page 502
Dec 15/2004
 C
AIRCRAFT MAINTENANCE MANUAL
(d) Prepare the fuel tank for access (Ref. TASK 28−11−00−840−801).
(e) Examine the engine fuel−feed tubes as follows:
1 Examine the area around the couplings. No leaks are permitted.
(f) Install the applicable access panels that follow: (Ref. TASK
28−11−01−400−802)
ACCESS DESCRIPTION
510AB Aluminum Access Panel (Center Fuel Tank)
610AB Aluminum Access Panel (Center Fuel Tank)
(g) Close the forward water drain valves under the center fuel tank .

4. Close Out
Subtask 28−21−00−941−001
A. Remove all tools, equipment, and unwanted materials from the work area.

Master
EFFECTIVITY: See Pageblock 28−21−00 page 501
28−21−00 Page 503
Dec 15/2004
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C ALL
PUMP, PRIMARY EJECTOR − REMOVAL/INSTALLATION

1. General
A. The maintenance procedures that follow are for the removal and installation of the
primary ejector pump. There are two primary ejector pumps in the fuel system. They are
found on the top of each collector tank connected to the engine feed lines.
B. It is necessary to defuel the center tank and the related main tank to remove or install
the primary ejector pump. It is also necessary to drain and remove the fuel fumes from
the center tank and to drain the related collector tank.

TASK 28−21−01−000−801
Removal of the Primary Ejector Pump

1. Job Set−Up Information

Subtask 28−21−01−946−001
A. Reference Information
REFERENCE DESIGNATION
TASK 12−11−28−650−804 Suction Defueling
TASK 28−00−00−910−801 Fuel Safety Precautions
TASK 28−11−00−840−801 Prepare Fuel Tank for Access
TASK 28−11−00−840−802 Removal of Fuel Fumes
TASK 28−11−01−000−801 Removal of the Honeycomb Access Panel
TASK 28−11−01−000−802 Removal of the Graphite Access Panel

2. Job Set−Up
Subtask 28−21−01−910−001
WARNING: OBEY ALL THE FUEL SAFETY PRECAUTIONS WHEN YOU DO WORK ON THE
FUEL SYSTEM AND/OR A FUEL SYSTEM COMPONENT. IF YOU DO NOT DO
THIS, YOU CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO
EQUIPMENT.
A. Obey all the fuel safety precautions (Ref. TASK 28−00−00−910−801).

Subtask 28−21−01−650−001
B. Defuel the center tank and the related main tank, and drain the applicable collector tank
(Ref. TASK 12−11−28−650−804).

Subtask 28−21−01−010−001
C. To remove the left primary ejector pump, remove the access panel that follows (Ref.
TASK 28−11−01−000−801):

Master
EFFECTIVITY: See Pageblock 28−21−01 page 401
28−21−01 Page 401
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

ACCESS DESCRIPTION
510AB Fuel tank access panel
D. To remove the right primary ejector pump, remove the access panel that follows (Ref.
TASK 28−11−01−000−802):
ACCESS DESCRIPTION
610AB Fuel tank access panel

Subtask 28−21−01−840−001
E. Prepare the center tank for access (Ref. TASK 28−11−00−840−801).
F. Remove the fuel fumes from the center tank (Ref. TASK 28−11−00−840−802).

3. Procedure
Subtask 28−21−01−020−001
Refer to Figure 401.
A. Remove the primary ejector pump as follows:
(1) Disconnect the engine feed line (1). Put a protective plug in the engine feed line.
(2) Disconnect the motive line (2). Put a protective plug in the motive line.
(3) Remove the bolts (3) and the washers (4) from the support bracket.
(4) Remove the bolts (5), the washers (6), the primary ejector pump (7), and the seal
(8). Discard the washers and the seal.

Master
EFFECTIVITY: See Pageblock 28−21−01 page 401
28−21−01 Page 402
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

2
5

1 NOTE
Left side is shown
Right side is the opposite.

3 COLLECTOR
TANK
4 (REF)
LEGEND.
1. Engine feed line.
2. Motive line.
3. Bolt.
4. Washer.
5. Bolt.
6. Washer.
7. Primary ejector pump.
ram2821014_001(2).dc, ks 11/07/95

8. Seal.

SUPPORT BRACKET
(REF)

Primary Ejector Pump − Removal/Installation

Figure 401

Master
EFFECTIVITY: See Pageblock 28−21−01 page 401
28−21−01 Page 403
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
TASK 28−21−01−400−801
Installation of the Primary Ejector Pump

1. Job Set−Up Information

Subtask 28−21−01−945−001
A. Parts
REF NAME OF PART QTY IPC SEQUENCE NO.
3 Bolt 2 IPC 28−11−03−1A−155
4 Washer 2 IPC 28−11−03−1A−160
5 Bolt 4 IPC 28−21−01−1A−015
6 Washer 4 IPC 28−21−01−1A−020
8 Seal 1 IPC 28−21−01−1A−025

Subtask 28−21−01−946−002
B. Reference Information
REFERENCE DESIGNATION
TASK 28−11−01−400−801 Installation of the Honeycomb Access Panel
TASK 28−11−01−400−802 Installation of the Graphite Access Panel
TASK 28−21−01−710−801 Operational Test of the Primary Ejector Pump

2. Procedure
Subtask 28−21−01−869−001
A. Make sure that the aircraft is in the same configuration as in the removal task.

Subtask 28−21−01−420−001
Refer to Figure 401.
B. Install the primary ejector pump as follows:
(1) Install the seal (8), the primary ejector pump (7), the washers (6), and the bolts (5).
Do not tighten the bolts.
(2) Connect the primary ejector pump (7) to the support bracket with the washers (4)
and the bolts (3).
(3) Tighten the bolts (5) that attach the primary ejector pump (7) to the collector tank.
(4) Remove the protective plug from the motive line (2). Connect the motive line (2) to
the primary ejector pump (7).
(5) Remove the protective plug from the engine feed line (1). Connect the engine feed
line (1) to the primary ejector pump (7).

Master
EFFECTIVITY: See Pageblock 28−21−01 page 401
28−21−01 Page 404
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
3. Close Out
Subtask 28−21−01−410−001
A. If the left primary ejector pump was replaced, install the access panel that follows (Ref.
TASK 28−11−01−400−801):
ACCESS DESCRIPTION
510AB Fuel tank access panel
B. If the right primary ejector pump was replaced, install the access panel that follows (Ref.
TASK 28−11−01−400−802):
ACCESS DESCRIPTION
610AB Fuel tank access panel

Subtask 28−21−01−710−001
C. Do an operational test of the primary ejector pump (Ref. TASK 28−21−01−710−801).

Subtask 28−21−01−941−001
D. Remove all the tools, equipment, and unwanted materials from the area.

Master
EFFECTIVITY: See Pageblock 28−21−01 page 401
28−21−01 Page 405
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C ALL
PUMP, PRIMARY EJECTOR − ADJUSTMENT/TEST

1. General
A. The maintenance procedure that follows is for the test of the primary ejector pump.

TASK 28−21−01−710−801
Operational Test of the Primary Ejector Pump

1. Job Set−Up Information

Subtask 28−21−01−946−003
A. Reference Information
REFERENCE DESIGNATION
TASK 12−00−07−861−801 Connect External AC Power
TASK 12−00−07−861−802 Remove External AC Power
TASK 12−11−28−650−802 Manual Pressure Refueling
TASK 28−21−04−710−801 Operational Test of the Engine−Fuel−Feed−Line
Check Valve
TASK 71−00−00−868−806 Engine Start
TASK 71−00−00−868−807 Engine Stop (Normal)

2. Job Set−Up
Subtask 28−21−01−650−002
A. Refuel the left and right main tanks (Ref. TASK 12−11−28−650−802).

Subtask 28−21−01−861−001
B. Connect the external AC power to the aircraft (Ref. TASK 12−00−07−861−801).
C. Push the FUEL pushbutton on the engine indication and crew alerting system (EICAS)
control panel to get the FUEL synoptic display.

3. Procedure
Subtask 28−21−01−710−002
A. If the left primary ejector pump was replaced, do a test as follows:
(1) On the fuel synoptic display of the EICAS, make sure that the left primary ejector
pump is shown in white.
(2) Start the left engine only (Ref. TASK 71−00−00−868−806).
(3) On the fuel synoptic display, make sure that the left primary ejector pump is shown
in green. Make sure that the left and right electric boost pumps are not shown in
green.

Master
EFFECTIVITY: See Pageblock 28−21−01 page 501
28−21−01 Page 501
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
(4) Do a shutdown of the left engine (Ref. TASK 71−00−00−868−807).

Subtask 28−21−01−710−003
B. If the right primary ejector pump was replaced, do a test as follows:
(1) On the fuel synoptic display of the EICAS, make sure that the right primary ejector
pump is shown in white.
(2) Start the right engine only (Ref. TASK 71−00−00−868−806).
(3) On the fuel synoptic display, make sure that the right primary ejector pump is
shown in green. Make sure that the left and right electric boost pumps are not
shown in green.
(4) Do a shutdown of the right engine (Ref. TASK 71−00−00−868−807.

Subtask 28−21−01−861−002
C. Remove the external AC power from the aircraft (Ref. TASK 12−00−07−861−802).

Master
EFFECTIVITY: See Pageblock 28−21−01 page 501
28−21−01 Page 502
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C ALL
CHECK VALVE, FUEL FEED LINE − REMOVAL/INSTALLATION

1. General
A. The maintenance procedures that follow are for the removal and installation of the fuel
feed line check valve (written as the "check valve" in this procedure). There are four
check valves in the fuel system. They are found in the center wing box. Two of the
check valves are connected to the fuel−feed manifolds, downstream of the primary
ejectors. The other two check valves are connected to the standby fuel−feed manifolds,
downstream of the fuel boost pumps.
B. It is necessary to defuel, drain, and remove the fuel fumes from the center tank and the
applicable main tank to remove or install the check valve.

TASK 28−21−04−000−801
Removal of the Fuel Feed Line Check Valve

1. Job Set−Up Information

Subtask 28−21−04−946−001
A. Reference Information
REFERENCE DESIGNATION
TASK 12−11−28−650−804 Suction Defueling
TASK 28−00−00−910−801 Fuel Safety Precautions
TASK 28−11−00−840−801 Prepare Fuel Tank for Access
TASK 28−11−00−840−802 Removal of Fuel Fumes
TASK 28−11−01−000−801 Removal of the Honeycomb Access Panel
TASK 28−11−01−000−802 Removal of the Graphite Access Panel

2. Job Set−Up
Subtask 28−21−04−910−001
WARNING: OBEY ALL THE FUEL SAFETY PRECAUTIONS WHEN YOU DO WORK ON THE
FUEL SYSTEM AND/OR A FUEL SYSTEM COMPONENT. IF YOU DO NOT DO
THIS, YOU CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO
EQUIPMENT.
A. Obey all the fuel safety precautions (Ref. TASK 28−00−00−910−801).

Subtask 28−21−04−650−001
B. Defuel the center tank and the applicable main tank (Ref. TASK 12−11−28−650−804).

Master
EFFECTIVITY: See Pageblock 28−21−04 page 401
28−21−04 Page 401
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
Subtask 28−21−04−010−001
C. To remove the left check valve, remove the access panel that follows (Ref. TASK
28−11−01−000−801):
ACCESS DESCRIPTION
510AB Fuel tank access panel
D. To remove the right check valve, remove the access panel that follows (Ref. TASK
28−11−01−000−802):
ACCESS DESCRIPTION
610AB Fuel tank access panel

Subtask 28−21−04−840−001
E. Prepare the center tank for access (Ref. TASK 28−11−00−840−801).
F. Remove the fuel fumes from the center tank and the applicable main tank (Ref. TASK
28−11−00−840−802).

3. Procedure
Subtask 28−21−04−020−001
Refer to Figure 401.
A. Remove the check valve as follows:
(1) For the right tube assembly, disconnect the pressure line (1) from the reducer (15).
Install a protective plug in the pressure line.
(2) Remove the couplings (2) at the check valve ferrules (3).
(3) Slide the sleeve (10) back over the ferrule (3).
(4) Disconnect the coupling (4) from the engine feed manifold and remove the retainer
(5).
(5) Remove the screw (6), the washer (7), and the clamp (8).
(6) Remove the tube assembly (9).
(7) Remove the sleeves (10) from the check valve ferrules (3).
(8) Remove and discard the preformed packings (13).
(9) Remove the circlip (18) and the check valves (11)
(10) Remove and discard the preformed packings (12) and (17) from the tube assembly
(9), the engine feed manifold, and the fuel manifolds.
(11) Install protective caps on the fuel manifolds and the engine feed manifold.
(12) Remove the split ring (14) and the coupling (4) from the tube assembly (9).
(13) For the right tube assembly, remove the reducer (15) and the preformed packing
(16). Discard the preformed packing.

Master
EFFECTIVITY: See Pageblock 28−21−04 page 401
28−21−04 Page 402
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

FUEL
MANIFOLD
(REF)

ram2821044_003.dc, rs/rm, 01/12/00

FUEL
MANIFOLD
(REF)

Fuel Feed Line Check Valve − Removal/Installation

Figure 401

Master
EFFECTIVITY: See Pageblock 28−21−04 page 401
28−21−04 Page 403
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
TASK 28−21−04−400−801
Installation of the Fuel Feed Line Check Valve

1. Job Set−Up Information

Subtask 28−21−04−945−001
A. Parts
REF NAME OF PART QTY IPC SEQUENCE NO.
12 Preformed packing 2 28−23−00−1A−63
13 Preformed packing 4 28−21−00−1A−025
16 Preformed packing 1 28−13−00−2A−20

Subtask 28−21−04−946−002
B. Reference Information
REFERENCE DESIGNATION
TASK 28−11−01−400−801 Installation of the Honeycomb Access Panel
TASK 28−11−01−400−802 Installation of the Graphite Access Panel
TASK 28−21−01−710−801 Operational Test of the Primary Ejector Pump
TASK 28−23−01−710−801 Operational Test of the Electric Boost Pump

2. Procedure
Subtask 28−21−04−869−001
A. Make sure that the aircraft is in the same configuration as in the removal task.

Subtask 28−21−04−420−001
Refer to Figure 401.
B. Install the check valve as follows:
(1) For the right tube assembly, lubricate the preformed packing (16) and install the
preformed packing and the reducer (15).
(2) Remove the protective caps from the fuel manifolds and the engine feed manifold.
(3) Install the coupling (4) and the split ring (14) on the tube assembly (9).
(4) Lubricate and install the vendor−supplied preformed packings (17) on the check
valves (11).
(5) Install the check valves (11) and circlip (18) in the check valve ferrules (3). Make
sure that the check valve flappers open in the direction of the arrows on the check
valve ferrules.
(6) Lubricate and install the vendor−supplied preformed packings (13) on the check
valves (11).
(7) Install the sleeves (10) on the check valve ferrules (3).
(8) Hold the tube assembly (9) in position. Install the clamp (8), the washer (7), and
the screw (6).

Master
EFFECTIVITY: See Pageblock 28−21−04 page 401
28−21−04 Page 404
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
(9) Lubricate and install the preformed packings (12) and (13) on the tube assembly
(9), the engine feed manifold, and the fuel manifolds.
(10) Install the retainer (5) and connect the coupling (4) at the engine feed manifold.
(11) Connect the check valve ferrules (3) to the fuel manifolds with the sleeves (10).
(12) Install the couplings (2) on the sleeves (10).
(13) For the right tube assembly, remove the protective plug from the pressure line (1).
Connect the pressure line (1) to the reducer (15).

3. Close Out
Subtask 28−21−04−410−001
A. If the left check valve was replaced, install the access panel that follows (Ref. TASK
28−11−01−400−801):
ACCESS DESCRIPTION
510AB Fuel tank access panel
B. If the right check valve was replaced, install the access panel that follows (Ref. TASK
28−11−01−400−802):
ACCESS DESCRIPTION
610AB Fuel tank access panel

Subtask 28−21−04−710−003
C. Do an operational test of the fwd check valves as follows:
(1) If the left hand check valve is to be tested, make sure there is fuel in the right hand
tank and no fuel in the left hand tank.
(2) Open the circuit breaker that follows:
CB PANEL CB NO. NAME ZONE
CBP1 M6 L FUEL PUMP 221
CBP1 M7 L FUEL PUMP CONT 221
(3) Open the left hand collector tank water drain valve.
(4) Start the right hand booster pump. The flow from the drain valve should not change,
or return to what it was before the pump operation.
(5) Shut down the right hand booster pump when test is completed.
(6) Close the circuit breakers M6 and M7 on CBP1.
(7) Close the left hand collector tank drain valve.
(8) Carry out the opposite procedure if the right hand check valve is to be tested.

Master
EFFECTIVITY: See Pageblock 28−21−04 page 401
28−21−04 Page 405
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
Subtask 28−21−04−710−001
D. Do a test of the aft check valves as follows:
(1) Do an operational test of the aft check valve (Ref. TASK 28−21−01−710−002).

Master
EFFECTIVITY: See Pageblock 28−21−04 page 401
28−21−04 Page 406
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C ALL
CHECK VALVE, ENGINE−FUEL−FEED LINE − ADJUSTMENT/TEST

1. General
A. The maintenance procedure that follows is for the test of the engine−fuel−feed−line
check valve (written as the "check valve" in this procedure). There are two check valves
in the engine−fuel−feed line. They are installed in the center wing box.

TASK 28−21−04−710−801
Operational Test of the Engine−Fuel−Feed−Line Check Valve

1. Job Set−Up Information

Subtask 28−21−04−943−002
A. Tools and Equipment
REFERENCE DESIGNATION
None specified Container, fuel

Subtask 28−21−04−946−003
B. Reference Information
REFERENCE DESIGNATION
TASK 12−11−28−650−801 Automatic Pressure Refueling
TASK 12−11−28−650−802 Manual Pressure Refueling
TASK 12−11−28−650−804 Suction Defueling
TASK 12−11−28−650−805 Gravity Defueling
TASK 12−00−07−861−801 Connect External AC Power
TASK 12−00−07−861−802 Remove External AC Power

2. Job Set−Up
Subtask 28−21−04−865−003
A. If the right check valve is to be tested, open the circuit breakers that follow:
CB PANEL CB NO. NAME ZONE
CBP−1 M6 L FUEL PUMP 221
CBP−1 M7 L FUEL PUMP CONT 221
B. If the left check valve is to be tested, open the circuit breakers that follow:
CB PANEL CB NO. NAME ZONE
CBP−2 G10 R FUEL PUMP 222
CBP−2 G11 R FUEL PUMP CONT 222

Master
EFFECTIVITY: See Pageblock 28−21−04 page 501
28−21−04 Page 501
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
Subtask 28−21−04−861−003
C. Connect the external AC power (Ref. TASK 12−00−07−861−801).

3. Procedure
Subtask 28−21−04−710−004
A. Do the operational test of the left check valve as follows:
(1) Make sure that the right main tank has a minimum of 200 pounds (90.8 kg) of fuel.
Refuel if necessary (Ref. TASK 12−11−28−650−801 or TASK 12−11−28−650−802).
(2) Make sure that the left main tank is fully defueled. Defuel if necessary (Ref. TASK
12−11−28−650−804 or TASK 12−11−28−650−805).
(3) Open the left−collector−tank water−drain valve as follows:
(a) Put a fuel container directly below the drain valve.
(b) Use a screwdriver to turn the valve poppet slowly counterclockwise until fully
extended.
(4) Fully drain the remaining fuel into the fuel container.
(5) On the FUEL control panel in the flight compartment, push in the R BOOST PUMP
switch/light. Make sure that the R BOOST PUMP ON light comes on and that the
L BOOST PUMP INOP light comes on.
(6) Make sure that no fuel comes from the drain valve.
(7) On the FUEL control panel, push in the R BOOST PUMP switch/light. Make sure
that the R BOOST PUMP ON light goes off and that the INOP light comes on.
(8) Close the left−collector−tank water−drain valve as follows:
(a) Use a screwdriver to turn the valve poppet of the drain valve clockwise until
the valve poppet is fully locked in the closed position.
(b) Remove the fuel container.

Subtask 28−21−04−710−005
B. Do the operational test of the right check valve as follows:
(1) Make sure that the left main tank has a minimum of 200 pounds (90.8 kg) of fuel.
Refuel if necessary (Ref. TASK 12−11−28−650−801 or TASK 12−11−28−650−802).
(2) Make sure that the right main tank is fully defueled. Defuel if necessary TASK
12−11−28−650−804 or TASK 12−11−28−650−805).
(3) Open the right−collector−tank water−drain valve as follows:
(a) Put a fuel container directly below the drain valve.
(b) Use a screwdriver to turn the valve poppet slowly counterclockwise until fully
extended.
(4) Fully drain the remaining fuel into the fuel container.
(5) On the FUEL control panel in the flight compartment, push in the L BOOST PUMP
switch/light. Make sure that the L BOOST PUMP ON light comes on and that the R
BOOST PUMP INOP light comes on.

Master
EFFECTIVITY: See Pageblock 28−21−04 page 501
28−21−04 Page 502
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
(6) Make sure that no fuel comes from the drain valve.
(7) On the FUEL control panel, push in the L BOOST PUMP switch/light. Make sure
that the L BOOST PUMP ON light goes off and that the INOP light comes on.
(8) Close the right−collector−tank water−drain valve as follows:
(a) Use a screwdriver to turn the valve poppet of the drain valve clockwise until
the valve poppet is fully locked in the closed position.
(b) Remove the fuel container.

4. Close Out
Subtask 28−21−04−865−004
A. If the right check valve was tested, close the circuit breakers that follow:
CB PANEL CB NO. NAME ZONE
CBP−1 M6 L FUEL PUMP 221
CBP−1 M7 L FUEL PUMP CONT 221
B. If the left check valve was tested, close the circuit breakers that follow:
CB PANEL CB NO. NAME ZONE
CBP−2 G10 R FUEL PUMP 222
CBP−2 G11 R FUEL PUMP CONT 222

Subtask 28−21−04−861−002
C. Remove the external AC power from the aircraft (Ref. TASK 12−00−07−861−802).

Subtask 28−21−04−941−007
D. Remove all tools, equipment, and unwanted materials from the work area.

Master
EFFECTIVITY: See Pageblock 28−21−04 page 501
28−21−04 Page 503
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C ALL
VALVE, ENGINE FUEL FEED SHUTOFF − REMOVAL/INSTALLATION

1. General
A. The maintenance procedures that follow are for the removal and installation TASKs for
the engine−fuel−feed shutoff valves (written as the "shutoff valve" in this procedure) and
the removal and installation TASKs for the removal and installation of the electrical
actuator from the valve assembly of the firewall shutoff valve.
B. There are two shutoff valves in the fuel system. They are found above the center tank.
Each shutoff valve is connected to the engine feed line from the collector tanks. There
are two shutoff valve actuators (written as the "SOV actuator" in this procedure) in the
fuel system. Each SOV actuator is installed on the shutoff valve body.
C. It is not necessary to defuel the fuel tanks to remove the shutoff valves.

TASK 28−21−07−000−801
Removal of the Engine−Fuel−Feed Shutoff Valve

1. Job Set−Up Information

Subtask 28−21−07−943−001
A. Tools and Equipment
REFERENCE DESIGNATION
None specified Fuel Container

Subtask 28−21−07−946−001
B. Reference Information
REFERENCE DESIGNATION
TASK 28−00−00−910−801 Fuel Safety Precautions
TASK 53−83−01−000−801 Removal of the MLG Wheel Bin

2. Job Set−Up
Subtask 28−21−07−910−001
WARNING: OBEY ALL THE FUEL SAFETY PRECAUTIONS WHEN YOU DO WORK ON THE
FUEL SYSTEM AND/OR A FUEL SYSTEM COMPONENT. IF YOU DO NOT DO
THIS, YOU CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO
EQUIPMENT.
A. Obey all the fuel safety precautions (Ref. TASK 28−00−00−910−801).

Master
EFFECTIVITY: See Pageblock 28−21−07 page 401
28−21−07 Page 401
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
Subtask 28−21−07−865−001
B. Open, safety, and tag the circuit breakers that follow:
CB PANEL CB NO. NAME ZONE
CBP−1 S1 FUEL SOV R ENG 221
CBP−1 S2 FUEL SOV L ENG 221
CBP−1 M12 FUEL SYST CONT 221
CBP−4 B10 FUEL SYST CONT 222

Subtask 28−21−07−010−001
C. For the left shutoff valve, remove the left wheel bin (163AZ) from the main wheel well
(Ref. TASK 53−83−01−000−801).
D. For the right shutoff valve, remove the right wheel bin (164AZ) from the main wheel well
(Ref. TASK 53−83−01−000−801).

3. Procedure
Subtask 28−21−07−020−001
Refer to Figure 401.
A. Remove the shutoff valve as follows:
(1) Disconnect the electrical connector (1) from the control solenoid (2) of the shutoff
valve (3). Put a protective cap on the electrical connector (1).
(2) Put the fuel container below the shutoff valve (3). Remove the lockwire from the cap
(4) and fastener (6).
(3) Remove the cap (4) from the bulkhead fitting (5). Drain the fuel into the fuel
container.
(4) Connect the cap (4) to the bulkhead fitting (5). Wirelock the cap (4) to the fastener
(6).
(5) Loosen the clamp (7) and disconnect the drain line (8) from the shroud (9).
(6) Loosen the clamp (10) and disconnect the shroud (9) from the shutoff valve (3).
(7) Disconnect the fuel pressure line (11) from the shutoff valve (3). Put a protective
plug in the fuel pressure line (11).
(8) Loosen the clamp (12) and disconnect the shroud (13) from the shutoff valve (3).
(9) Disconnect the fuel hose (14) from the shutoff valve (3). Put a protective plug in the
fuel hose (14).
(10) Remove the four screws (15), the four washers (16), and remove the shutoff
valve (3).

Master
EFFECTIVITY: See Pageblock 28−21−07 page 401
28−21−07 Page 402
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

LEGEND
1. Electrical connector.
2. Control solenoid.
3. Shutoff valve.
4. Cap.
5. Bulkhead fitting.
6. Fastener.
7. Clamp.
8. Drain line.
9. Shroud.
10. Clamp.
11. Fuel pressure line.
12. Clamp.
13. Shroud.
14. Fuel hose.
15. Screw.
16. Washer.
3
2

14
13 12

16
15

8
4
TO ENGINE

5
ram2821074_001(1).dc, pb/pm, 12/06/95

6 10

FROM
BOOSTER
9
PUMP
NOTE 7
Left side is shown. 11
Right side is the opposite. 8

Engine−Fuel−Feed Shutoff Valve − Removal/Installation

Figure 401

Master
EFFECTIVITY: See Pageblock 28−21−07 page 401
28−21−07 Page 403
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
TASK 28−21−07−400−801
Installation of the Engine−Fuel−Feed Shutoff Valve

1. Job Set−Up Information

Subtask 28−21−07−945−001
A. Parts
REF NAME OF PART QTY IPC SEQUENCE NO.
7 Clamp 1 IPC 28−21−00−1A−225
10 Clamp 1 IPC 28−21−00−1A−190
15 Screw 4 IPC 28−21−07−1A−010
16 Washer 4 IPC 28−21−07−1A−015

Subtask 28−21−07−946−002
B. Reference Information
REFERENCE DESIGNATION
TASK 28−21−07−710−801 Operational Test of the Engine−Fuel−Feed Shutoff
Valve
TASK 28−21−13−780−801 Pressure and Blockage Test of the Engine Feed
Shroud
TASK 53−83−01−400−801 Installation of the MLG Wheel Bin

2. Procedure
Subtask 28−21−07−869−001
A. Make sure that the aircraft is in the same configuration as in the removal task.

Subtask 28−21−07−420−001
Refer to Figure 401.
B. Install the shutoff valve as follows:
(1) Put the shutoff valve (3) in position and install with the four screws (15) and four
washers (16).
(2) Remove the protective plug and connect the fuel hose (14) to the shutoff valve (3).
(3) Connect the shroud (13) to the shutoff valve (3) with the clamp (12).
(4) Remove the protective plug and connect the fuel pressure line (11) to the shutoff
valve (3).
(5) Connect the shroud (9) to the shutoff valve (3) with the clamp (10).
(6) Connect the drain line (8) to the shroud (9) with the clamp (7).
(7) Remove the protective cap and connect the electrical connector (1) to the control
solenoid (2) of the shutoff valve (3).

Master
EFFECTIVITY: See Pageblock 28−21−07 page 401
28−21−07 Page 404
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
3. Close Out
Subtask 28−21−07−865−002
A. Remove the tags and close the circuit breakers that follow:
CB PANEL CB NO. NAME ZONE
CBP−1 S1 FUEL SOV R ENG 221
CBP−1 S2 FUEL SOV L ENG 221
CBP−1 M12 FUEL SYST CONT 221
CBP−4 B10 FUEL SYST CONT 222

Subtask 28−21−07−710−001
B. Do an operational test of the shutoff valve (Ref. TASK 28−21−07−710−801).

Subtask 28−21−07−780−001
C. Do a pressure and blockage test of the engine feed shroud (Ref.TASK
28−21−13−780−801).

Subtask 28−21−07−410−001
D. For the left shutoff valve, install the left wheel bin (163AZ) in the main wheel well (Ref.
TASK 53−83−01−400−801).
E. For the right shutoff valve, install the right wheel bin (164AZ) in the main wheel well (Ref.
TASK 53−83−01−400−801).

Subtask 28−21−07−941−001
F. Remove all the tools, equipment, and unwanted materials from the area.

Master
EFFECTIVITY: See Pageblock 28−21−07 page 401
28−21−07 Page 405
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
TASK 28−21−07−000−802
Removal of the Engine−Fuel−Feed Shutoff Valve Electrical Actuator

1. Job Set−Up Information

Subtask 28−21−07−946−004
A. Reference Information
REFERENCE DESIGNATION
TASK 28−00−00−910−801 Fuel Safety Precautions
TASK 53−83−01−000−801 Removal of the MLG Wheel Bin

2. Job Set−Up
Subtask 28−21−07−910−002
WARNING: OBEY ALL THE FUEL SAFETY PRECAUTIONS WHEN YOU DO WORK ON THE
FUEL SYSTEM AND/OR A FUEL SYSTEM COMPONENT. IF YOU DO NOT DO
THIS, YOU CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO
EQUIPMENT.
A. Obey all the fuel safety precautions (Ref. TASK 28−00−00−910−801).

Subtask 28−21−07−865−004
B. Open, safety, and tag the circuit breakers that follow:
CB PANEL CB NO. NAME ZONE
CBP−1 S1 FUEL SOV R ENG 221
CBP−1 S2 FUEL SOV L ENG 221
CBP−1 M12 FUEL SYST CONT 221
CBP−4 B10 FUEL SYST CONT 222

Subtask 28−21−07−010−002
C. For the left SOV actuator, remove the left wheel bin (163AZ) from the main wheel well
(Ref. TASK 53−83−01−000−801).
D. For the right SOV actuator, remove the right bin (164AZ) from the main wheel well (Ref.
TASK 53−83−01−000−801).

3. Procedure
Subtask 28−21−07−020−002
Refer to Figure 402.
A. Remove the electrical actuator (2) from the body assembly (3) of the engine fuel feed
shutoff valve as follows:
NOTE: This procedure is the same for both of the engine fuel feed shutoff valves.

Master
EFFECTIVITY: See Pageblock 28−21−07 page 401
28−21−07 Page 406
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
(1) Disconnect the electrical connector (1) from the electrical actuator (2).
(2) Put protective caps on the electrical connector and on the receptacle of the
electrical actuator.
(3) Remove the screws (4) and the washers (5) that attach the two half−clamps (6).
(4) Remove the two half−clamps (6) that secure the electrical actuator (2) to the body
assembly (3).
(5) Remove the electrical actuator (2) from the body assembly (3).

Master
EFFECTIVITY: See Pageblock 28−21−07 page 401
28−21−07 Page 407
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

LEGEND
1. Electrical connector.
2. Electrical actuator.
A 3. Body assembly.
4. Screw.
5. Washer.
6. Clamp.

6 3
1

5
4 ram2821074_002.dg, yf, 09/04/03

Engine Fuel Feed Shutoff Valve Electrical Actuator − Removal/Installation

Figure 402

Master
EFFECTIVITY: See Pageblock 28−21−07 page 401
28−21−07 Page 408
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
TASK 28−21−07−400−802
Installation of the Engine−Fuel−Feed Shutoff Valve Electrical Actuator

1. Job Set−Up Information

Subtask 28−21−07−943−004
A. Consumable Materials
REFERENCE DESIGNATION
08−001 Sealing Compound, threadlocking, low strength,
anaerobic, single component, (Locktite 222MS)
08−001A Sealing Compound, threadlocking, low strength,
anaerobic, single component, (Locktite 221)
B. Parts
REF NAME OF PART QTY IPC SEQUENCE NO.
1 Screw 2 IPC 29−11−36−02−020
2 Washer 2 IPC 29−11−36−02−025

Subtask 28−21−07−946−006
C. Reference Information
REFERENCE DESIGNATION
TASK 28−21−07−710−801 Operational Test of the Engine−Fuel−Feed Shutoff
Valve
TASK 53−83−01−400−801 Installation of the MLG Wheel Bin

2. Procedure
Subtask 28−21−07−869−002
A. Make sure that the aircraft is in the same configuration as in the removal task.

Subtask 28−21−07−420−002
Refer to Figure 402.
B. Install the electrical actuator (2) to the body assembly (3) of the engine−fuel−feed shutoff
valve as follows:
NOTE: This procedure is the same for both of the engine fuel−feed shutoff valves.
(1) Install the two washers (5) on the two screws (4).
(2) Apply a layer of 08−001A threadlock on the threads of the two screws (4).
NOTE: 08−001 threadlocker is similar to 08−001A threadlocker and can be used
as an alternate.
(3) Make sure that the keyslot on the control shaft is correctly aligned with the key that
is inside the electrical actuator (2). Both are in the fully open or the fully closed
position.

Master
EFFECTIVITY: See Pageblock 28−21−07 page 401
28−21−07 Page 409
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
(4) Put the electrical actuator (2) in position on the body assembly (3). Make sure that
the pin on the flange of the body assembly (2) is correctly aligned with the hole in
the flange of the electrical actuator (2).
NOTE: With the keyslot on the control shaft correctly engaged with the key of the
electrical actuator (2), it is possible that the electrical actuator (2) will need
to be turned slightly to align the pin and the hole.
(5) Secure the electrical actuator (2) to the body assembly (3) with the two half−clamps
(6).
(6) Secure the two half−clamps (6) together with the two screws (4).
(7) Tighten the two screws (4).
NOTE: Make sure that the space between the joints of the half−clamps (6) is the
same when you tighten the two screws (4).
(8) Remove the protective caps from the electrical connector (1) and from the
receptacle of the electrical actuator (2).
(9) Connect the electrical connector (1) to the electrical actuator (2).

3. Close Out
Subtask 28−21−07−865−005
A. Remove the tags and close the circuit breakers that follow:
CB PANEL CB NO. NAME ZONE
CBP−1 S1 FUEL SOV R ENG 221
CBP−1 S2 FUEL SOV L ENG 221
CBP−1 M12 FUEL SYST CONT 221
CBP−4 B10 FUEL SYST CONT 222

Subtask 28−21−07−710−005
B. Do an operational test of the engine fuel−feed shutoff valve (Ref. TASK
28−21−07−710−801).

Subtask 28−21−07−410−002
C. For the left shutoff valve actuator, install left wheel bin 163AZ in the main wheel well
(Ref. TASK 53−83−01−400−801).

Subtask 28−21−07−410−005
D. For the right shutoff valve actuator, install the right wheel bin (164AZ) in the main wheel
well (Ref. TASK 53−83−01−400−801).

Subtask 28−21−07−941−002
E. Remove all tools, equipment, and unwanted materials from the work area.

Master
EFFECTIVITY: See Pageblock 28−21−07 page 401
28−21−07 Page 410
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C ALL
VALVE, ENGINE FUEL FEED SHUTOFF − ADJUSTMENT/TEST

1. General
A. The maintenance procedure that follows is for the test of the engine−fuel−feed shutoff
valve (written as the "shutoff valve" in this procedure).

TASK 28−21−07−710−801
Operational Test of the Engine−Fuel−Feed Shutoff Valve

1. Job Set−Up Information

Subtask 28−21−07−943−003
A. Tools and Equipment
REFERENCE DESIGNATION
None specified Container, fuel

Subtask 28−21−07−946−003
B. Reference Information
REFERENCE DESIGNATION
TASK 12−00−07−861−801 Connect External AC Power
TASK 12−00−07−861−802 Remove External AC Power
TASK 53−83−01−000−801 Removal of the MLG Wheel Bin
TASK 53−83−01−400−801 Installation of the MLG Wheel Bin
TASK 12−11−28−650−802 Manual Pressure Refueling

2. Job Set−Up
Subtask 28−21−07−010−003
A. If the wheel bins are installed, remove the applicable wheel bin from the main wheel well
(Ref. TASK 53−83−01−000−801).

Subtask 28−21−07−865−003
B. Make sure that the circuit breakers that follow are closed:
CB PANEL CB NO. NAME ZONE
CBP−1 M6 L FUEL PUMP 221
CBP−1 M7 L FUEL PUMP CONT 221
CBP−1 S1 FUEL SOV R ENG 221
CBP−1 S2 FUEL SOV L ENG 221
CBP−1 M12 FUEL SYST CONT 221
CBP−2 G10 R FUEL PUMP 222

Master
EFFECTIVITY: See Pageblock 28−21−07 page 501
28−21−07 Page 501
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

CB PANEL CB NO. NAME ZONE

CBP−2 G11 R FUEL PUMP CONT 222
CBP−4 B10 FUEL SYST CONT 222

Subtask 28−21−07−010−004
C. Open the access doors that follow:
ACCESS DESIGNATION
162AB Fuel/defuel control panel door

Subtask 28−21−07−650−001
D. Make sure that each main tank has a minimum of 200 pounds (90.8 kg) of fuel. Refuel if
necessary (Ref. TASK 12−11−28−650−802).

Subtask 28−21−07−861−001
E. Connect the external AC power to the aircraft (Ref. TASK 12−00−07−861−801).
F. Push the FUEL pushbutton on the engine indication and crew alerting system (EICAS)
control panel to get the FUEL synoptic display.

3. Procedure
Subtask 28−21−07−710−002
A. Do an operational test of the left shutoff valve as follows:
(1) On the FUEL synoptic display of the EICAS, make sure that the left shutoff valve
outline is shown in white and in the open position.
(2) In the main wheel well, at the shutoff valve, make sure that the visual position
indicator is at the OPEN position.
(3) On the FUEL control panel, push in the L BOOST PUMP switch/light. Make sure
that the L and R BOOST PUMP ON lights come on and that the two INOP lights do
not come on.
NOTE: When the L BOOST PUMP switch/light is pushed, the left and the right
boost pump come on line.
(4) On the FUEL synoptic display, make sure that the left shutoff valve outline is shown
in white and in the open position, and its flow line in green.
WARNING: DO NOT PUSH THE "BOTTLE 1 ARMED PUSH TO DISCH"
SWITCH/LIGHT OR THE "BOTTLE 2 ARMED PUSH TO DISCH"
SWITCH/LIGHT DURING THE REMAINING STEPS OF THIS TEST.
THE HALON CAN COME OUT OF THE FIREX BOTTLE AND CAUSE
INJURIES.
(5) On the pilot’s glareshield panel, push in the LH ENG FIRE PUSH switch/light.
(6) Make sure the conditions that follow occur:

Master
EFFECTIVITY: See Pageblock 28−21−07 page 501
28−21−07 Page 502
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
(a) On the primary EICAS display, make sure that the L ENG SOV CLSD caution
indication is shown.
(b) On the pilot’s and copilot’s glareshield panels, the two MASTER CAUTION
pushbutton−annunciators start to flash followed by an audible chime.
(c) On the FUEL synoptic display, make sure that the left shutoff valve outline is
shown in amber and in the closed position, and its green flow line is not
shown.
(d) In the main wheel well, at the shutoff valve, make sure that the visual position
indicator is at the CLOSED position.
(7) On the pilot’s glareshield panel, push out the LH ENG FIRE PUSH switch/light.
(8) Make sure the conditions that follow occur:
(a) On the primary EICAS display, make sure that the L ENG SOV CLSD caution
indication is not shown.
(b) On the pilot’s and copilot’s glareshield panels, the two MASTER CAUTION
pushbutton−annunciators go off and the chime is not heard.
(c) On the FUEL synoptic display, make sure that the left shutoff valve outline is
shown in white and in the open position, and its flow line in green.
(d) In the main wheel well, at the shutoff valve, make sure that the visual position
indicator is at the OPEN position.
(9) On the FUEL control panel, push out the L BOOST PUMP switch/light. Make sure
that the L and R BOOST PUMP ON lights go off and the two INOP lights come on.
NOTE: When the L BOOST PUMP switch/light is pushed out, the left and the
right boost pump stop.

Subtask 28−21−07−710−003
B. Do an operational test of the right shutoff valve as follows:
(1) On the FUEL synoptic display of the EICAS, make sure that the right shutoff valve
outline is shown in white and in the open position.
(2) In the main wheel well, at the shutoff valve, make sure that the visual position
indicator is at the OPEN position.
(3) On the FUEL control panel, push in the R BOOST PUMP switch/light. Make sure
that the L and R BOOST PUMP ON lights come on and that the two INOP lights do
not come on.
NOTE: When the R BOOST PUMP switch/light is pushed, the left and the right
boost pump come on line.
(4) On the FUEL synoptic display, make sure that the right shutoff valve outline is
shown in white and in the open position, and its flow line in green.
WARNING: DO NOT PUSH THE "BOTTLE 1 ARMED PUSH TO DISCH"
SWITCH/LIGHT OR THE "BOTTLE 2 ARMED PUSH TO DISCH"
SWITCH/LIGHT DURING THE REMAINING STEPS OF THIS TEST.
THE HALON CAN COME OUT OF THE FIREX BOTTLE AND CAUSE
INJURIES.
(5) On the copilot’s glareshield panel, push in the RH ENG FIRE PUSH switch/light.

Master
EFFECTIVITY: See Pageblock 28−21−07 page 501
28−21−07 Page 503
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
(6) Make sure the conditions that follow occur:
(a) On the primary EICAS display, make sure that the R ENG SOV CLSD caution
indication is shown.
(b) On the pilot’s and copilot’s glareshield panels, the two MASTER CAUTION
pushbutton−annunciators start to flash followed by an audible chime.
(c) On the FUEL synoptic display, make sure that the right shutoff valve outline is
shown in amber and in the closed position, and its green flow line is not
shown.
(d) In the main wheel well, at the shutoff valve, make sure that the visual position
indicator is at the CLOSED position.
(7) On the copilot’s glareshield panel, push out the RH ENG FIRE PUSH switch/light.
(8) Make sure the conditions that follow occur:
(a) On the primary EICAS display, make sure that the R ENG SOV CLSD caution
indication is not shown.
(b) On the pilot’s and copilot’s glareshield panels, the two MASTER CAUTION
pushbutton−annunciators go off and the chime is not heard.
(c) On the FUEL synoptic display, make sure that the right shutoff valve outline is
shown in white and in the open position, and its flow line in green.
(d) In the main wheel well, at the shutoff valve, make sure that the visual position
indicator is at the OPEN position.
(9) On the FUEL control panel, push out the R BOOST PUMP switch/light. Make sure
that the L and R BOOST PUMP ON lights go off and the two INOP lights come on.
NOTE: When the R BOOST PUMP switch/light is pushed out, the left and the
right boost pump stop.

4. Close Out
Subtask 28−21−07−861−002
A. Remove the external AC power from the aircraft (Ref. TASK 12−00−07−861−802).

Subtask 28−21−07−210−001
Refer to Figure 501.
B. Check for leaks around the shutoff valve as follow:
(1) Put the fuel container below the shutoff valve. Loosen the clamp (1) and disconnect
the drain line (2).
(2) Examine the area around the applicable shutoff valve for leaks. Tighten all loose
connections, if necessary.
(3) Connect the drain line (2) with the clamp (1).

Subtask 28−21−07−410−003
C. Install the applicable wheel bin in the main wheel well (Ref. TASK 53−83−01−400−801).

Master
EFFECTIVITY: See Pageblock 28−21−07 page 501
28−21−07 Page 504
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
Subtask 28−21−07−941−004
D. Remove all the tools, equipment, and unwanted materials form the area.

Master
EFFECTIVITY: See Pageblock 28−21−07 page 501
28−21−07 Page 505
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

LEGEND
1. Clamp.
2. Drain line.

TO ENGINE

ram2821075_002.dc, pb/pm, 12/06/95

FROM
BOOSTER
PUMP

NOTE
Left side is shown.
Right side is the opposite.

Engine−fuel−feed Shutoff Valve − Adjustment/Test

Figure 501

Master
EFFECTIVITY: See Pageblock 28−21−07 page 501
28−21−07 Page 506
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
TASK 28−21−07−710−802
Operation Test of the Engine−Fuel−Shutoff−Valve Position Indicators
1. Reason for the Job
Refer to MRB 28−21−00−03

2. Job Set−Up Information

Subtask 28−21−07−946−005
A. Reference Information
REFERENCE DESIGNATION
TASK 12−00−07−861−801 Connect External AC Power
TASK 12−00−07−861−802 Remove External AC Power
TASK 53−83−01−000−801 Removal of the MLG Wheel Bin
TASK 53−83−01−400−801 Installation of the MLG Wheel Bin

3. Job Set−Up
Subtask 28−21−07−010−005
A. Remove the wheel bins from the main wheel well (Ref. TASK 53−83−01−000−801).

Subtask 28−21−07−861−005
B. Connect the external AC power to the aircraft (Ref. TASK 12−00−07−861−801).

4. Procedure
Subtask 28−21−07−710−004
A. Do an operational test of the shutoff valve position indicators as follows:
(1) In the main wheel well, on the shutoff valves, make sure that the visual position
indicators are at the OPEN position.
WARNING: DO NOT PUSH THE "BOTTLE 1 ARMED PUSH TO DISCH"
SWITCH/LIGHT OR THE "BOTTLE 2 ARMED PUSH TO DISCH"
SWITCH/LIGHT DURING THE REMAINING STEPS OF THIS TEST.
THE HALON CAN COME OUT OF THE FIREX BOTTLE AND CAUSE
INJURIES.
(2) On the pilot’s glareshield panel, push in the LH ENG FIRE PUSH switch/light.
(3) In the main wheel well, on the left shutoff valve, make sure that the visual position
indicator is at the CLOSED position.
(4) On the pilot’s glareshield panel, push out the LH ENG FIRE PUSH switch/light.
(5) In the main wheel well, on the left shutoff valve, make sure that the visual position
indicator is at the OPEN position.
(6) On the pilot’s glareshield panel, push in the RH ENG FIRE PUSH switch/light.
(7) In the main wheel well, on the right shutoff valve, make sure that the visual position
indicator is at the CLOSED position.

Master
EFFECTIVITY: See Pageblock 28−21−07 page 501
28−21−07 Page 507
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
(8) On the pilot’s glareshield panel, push out the RH ENG FIRE PUSH switch/light.
(9) In the main wheel well, on the right shutoff valve, make sure that the visual position
indicator is at the OPEN position.

5. Close Out
Subtask 28−21−07−861−006
A. Remove the external AC power from the aircraft (Ref. TASK 12−00−07−861−802).

Subtask 28−21−07−410−004
B. Install the applicable wheel bin in the main wheel well (Ref. TASK 53−83−01−400−801).

Subtask 28−21−07−941−005
C. Remove all the tools, equipment, and unwanted materials from the area.

Master
EFFECTIVITY: See Pageblock 28−21−07 page 501
28−21−07 Page 508
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C ALL
SHROUD, ENGINE FUEL FEED − REMOVAL/INSTALLATION

1. General
A. The maintenance procedure that follows is for the removal and installation of the engine
fuel−feed shroud (written as the "shroud" in this procedure). The shrouds are installed in
the aft cargo compartment between FS621.00 and the engine pylon firewalls at
FS656.20, between WL62.72 and WL111.09. This procedure is applicable to the left side
and the right side. The procedure for the left side is given. Differences for the right side
are identified.

TASK 28−21−13−000−801
Removal of the Shroud and Engine−Fuel−Feed Tube from FS621.00 to the Engine Pylon
Firewall

1. Job Set−Up Information

Subtask 28−21−13−943−003
A. Tools and Equipment
REFERENCE DESIGNATION
Commercially Available Container − Non−static Fuel

Subtask 28−21−13−944−003
B. Consumable Materials
REFERENCE DESIGNATION
05−001A Cloth, cleaning, for aircraft fuel tanks

Subtask 28−21−13−946−001
C. Reference Information
REFERENCE DESIGNATION
TASK 20−30−00−910−802 Wiggins Couplings − Maintenance Practices
TASK 24−00−00−910−801 Electrical/Electronic Safety Precautions
TASK 24−00−00−910−802 Electrostatic Discharge Safety Precautions
TASK 28−00−00−910−801 Fuel Safety Precautions
TASK 73−10−00−910−802 Close the Fuel−Feed Shutoff Valve

Master
EFFECTIVITY: See Pageblock 28−21−13 page 401
28−21−13 Page 401
Sep 10/2004
 C
AIRCRAFT MAINTENANCE MANUAL
2. Job Set−Up
Subtask 28−21−13−910−002
WARNING: OBEY ALL THE FUEL SAFETY PRECAUTIONS WHEN YOU DO WORK ON THE
FUEL SYSTEM AND/OR A FUEL SYSTEM COMPONENT. IF YOU DO NOT DO
THIS, YOU CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO
EQUIPMENT.
A. Obey all the fuel safety precautions (Ref. TASK 28−00−00−910−801).

Subtask 28−21−13−910−003
B. Obey all the electrostatic discharge precautions (Ref. TASK 24−00−00−910−802).

Subtask 28−21−13−910−007
C. Obey all the electrical/electronic safety precautions (Ref. TASK 24−00−00−910−801).

Subtask 28−21−13−940−001
D. Close the fuel−feed shutoff valve (Ref. TASK 73−10−00−910−802).

Subtask 28−21−13−010−002
E. Open the access door that follows:
ACCESS DESIGNATION
311BB Aft Equipment Bay Door

Subtask 28−21−13−010−003
F. Open the access panels that follow:
ACCESS DESIGNATION
412DB/422DB Power−Plant Line Disconnect

3. Procedure
Refer to Figure 401.
Subtask 28−21−13−020−001
NOTE: For the procedures for the removal and installation of Wiggins couplings, refer to
Wiggins Couplings − Maintenance Practices (Ref. TASK 20−30−00−910−802).
A. Remove the lower section of the engine fuel−feed shroud from FS621.00 to FS632.50
(FS633.70 for the right side) as follows:
(1) Put the fuel container below the shroud coupling (1) at FS621.00.
(2) Remove the insulation material from around and under the drain line (2).
(3) Disconnect the drain line (2) from the vent fitting (3) at FS639.9.
(4) Disconnect the drain line (2) from the coupling fitting (4).
(5) Remove the clamps (5) from the shroud coupling (6) at FS632.50 (FS633.70 for the
right side).

Master
EFFECTIVITY: See Pageblock 28−21−13 page 401
28−21−13 Page 402
Sep 10/2004
 C
AIRCRAFT MAINTENANCE MANUAL
(6) Remove the aft clamp (7) from the shroud coupling (1) at FS621.00.
(7) Remove the clamshell assembly (8) from the bulkhead fitting (9) at FS621.00 and
expose the preformed packings (10).
(8) Discard the preformed packings (10).
(9) Remove the two screws (11), the two washers (12), and the saddle clamp (13) that
hold the tube assembly (14) to the fuselage mount at FS625.3.
(10) Slide the tube assembly (14) away from the shroud (15) to access the clamshell
assembly (16) of the fuel line (17).
(11) Remove the clamshell assembly (16) from the fuel line (17) and expose the
preformed packings (18).
(12) Discard the preformed packings (18).
(13) Remove the screw (19), the washer (20), and the loop clamp (21) that hold the
shroud (15) to the fuselage mount at FS632.50 (FS633.70 for the right side).
(14) Slide the shroud (22) down to access the clamshell assembly (23) of the fuel
line (24).
(15) Remove the clamshell assembly (23) from the fuel line (24) and expose the
preformed packings (18).
(16) Discard the preformed packings (18).
(17) Remove the shroud (15) from the aircraft.
(18) Install a blanking cap on the fuel line of the bulkhead fitting (9) at FS621.00.
(19) Install a blanking cap on the fuel line (24) of the upper shroud coupling (6) at
FS632.50 (FS633.70 for the right side).
(20) Install blanking caps on both ends of the fuel line (17) of the removed shroud
assembly (15).

Subtask 28−21−13−020−002
B. Remove the center section of the engine fuel−feed shroud from FS632.50 to FS648.5 as
follows:
(1) Put the fuel container below the shroud coupling (6) at FS632.50.
(2) Remove the clamps (5) from the shroud coupling (6) at FS632.50 (FS633.70 for the
right side).
(3) Remove the clamp (25) from the shroud coupling (26) at FS648.5.
(4) Remove the two screws (19), the two washers (20), and the loop clamp (21) that
hold the shroud (27) to the fuselage mount at FS625.3.
(5) Slide the tube assembly (22) down to access the clamshell assembly (23) of the
fuel line (24).
(6) Remove the clamshell assembly (23) from the fuel line (24) and expose the
preformed packings (18).
(7) Discard the preformed packings (18).
(8) Remove the two screws (19), the two washers (20), and the loop clamp (21) that
hold the shroud (27) to the fuselage mount at FS640.
(9) Slide the shroud (27) away to access the clamshell assembly (28) of the fuel
line (24).

Master
EFFECTIVITY: See Pageblock 28−21−13 page 401
28−21−13 Page 403
Sep 10/2004
 C
AIRCRAFT MAINTENANCE MANUAL
(10) Remove the heat shrinkable tubing from clamshell assembly (28).
(11) Remove the clamshell assembly (28) from the fuel line (24) and expose the
preformed packings (29).
(12) Discard the preformed packings (29).
(13) Remove the shroud (27) from the aircraft.
(14) Install a blanking cap on the fuel line (17) of the shroud coupling (6) at FS632.50
(FS633.70 for the right side).
(15) Install a blanking cap on the fuel line (30) of the shroud coupling (26) at FS648.5.
(16) Install blanking caps on both ends of the fuel line (24) of the removed shroud
assembly (27).

Subtask 28−21−13−020−003
C. Remove the upper section of the engine fuel−feed shroud from FS648.5 to FS656.2 as
follows:
(1) Put the fuel container below the shroud coupling (26) at FS648.5.
(2) Remove the clamp (25) from the shroud coupling (26) at FS648.5.
(3) Remove the screw (19), the washer (20), and the loop clamp (21) that hold the
shroud (31) to the fuselage mount at FS656.2.
(4) Slide the shroud (27) away to access the clamshell assembly (28) of the fuel line
(24).
(5) Remove the clamshell assembly (28) from the fuel line (30) and expose the
preformed packings (29).
(6) Discard the preformed packings (29).
(7) Remove the two screws (32), the two washers (33), the two nuts (34) and the
bonding jumper (35) from the shroud (30) and the shroud coupling (36).
(8) Remove the clamp (37) from the shroud (31).
(9) Remove the clamp (38) from the shroud coupling (36).
(10) Remove the clamshell assembly (39) from the shroud coupling (36) and the pylon
coupling (40) and expose the preformed packings (41).
(11) Discard the preformed packings (41).
(12) Slide the shroud coupling (36) back to access the clamshell assembly (42) of the
fuel line (30).
(13) Remove the clamshell assembly (42) from the fuel line (30) and expose the
preformed packings (43).
(14) Discard the preformed packings (43).
(15) Remove the shroud (31) from the aircraft.
(16) Install a blanking cap on the fuel line (24) of the shroud coupling (6) at FS632.50
(FS633.70 for the right side).
(17) Install a blanking cap on the engine pylon firewall fuel−line coupling (44) at
FS656.2.
(18) Install blanking caps on both ends of the fuel line (30) of the removed shroud
assembly (31).

Master
EFFECTIVITY: See Pageblock 28−21−13 page 401
28−21−13 Page 404
Sep 10/2004
 C
AIRCRAFT MAINTENANCE MANUAL

LEGEND A
1. Coupling.
2. Drain line.
3. Drain vent.
4. Coupling fitting.
6. Shroud coupling.
15. Shroud. E
26. Shroud coupling.
27. Shroud.
31. Shroud. 26 31
F

D
31
26
D
27

4 27
15

1 2
B
3 6

RH SIDE 15 C
1

D
ram2821134_001.dg, gg, 13/03/02

LH SIDE

Shroud, Engine Fuel−Feed Line − Removal/Installation

Figure 401 (Sheet 1 of 3)

Master
EFFECTIVITY: See Pageblock 28−21−13 page 401
28−21−13 Page 405
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

11 7
12

4 15
13

2
1
17
18
16
18
45
5
13
14
10 B
8
10
9 27

LEGEND
1. Coupling.
2. Drain line.
3. Drain vent. 22
4. Coupling fitting.
5. Clamp.
7. Clamp. 24
8. Clamshell.
9. Bulkhead fitting.
18
10. Preformed packing.
11. Screw. 23
12. Washer.
13. Saddle clamp.
14. Tube assembly. 18
15. Shroud.
16. Clamshell. 17
17. Fuel line. 20
18. Preformed packing. 19
19. Screw.
ram2821134_002.dg, gg, 14/03/02

20. Washer. 15
21. Loop clamp. 21
22. Shroud coupling. 5
15
23. Clamshell.
24. Fuel line.
27. Shroud.
45. Fuel line.
TYPICAL 2 PLACES

Shroud, Engine Fuel−Feed Line − Removal/Installation

Figure 401 (Sheet 2 of 3)

Master
EFFECTIVITY: See Pageblock 28−21−13 page 401
28−21−13 Page 406
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

40
44
43
42
41
39
43
36
38

41
31
37
LEGEND
19. Screw.
20. Washer. 30 30
21. Loop clamp.
23. Clamshell.
24. Fuel line. 34
25. Preformed packing. 33
27. Shroud.
28. Clamshell.
29. Preformed packing. 35 32
30. Fuel line.
31. Shroud.
32. Screw.
33. Washer.
34. Nut.
35. Bonding jumper.
36. Shroud coupling.
37. Clamp.
38. Clamp.
39. Clamshell.
28
40. Pylon coupling.
41. Preformed packing.
42. Clamshell.
43. Preformed packing.
44. Pylon fuel−line coupling. 24
27
25
30
ram2821134_003.dg, gg, 14/03/02

29

Shroud, Engine Fuel−Feed Line − Removal/Installation

Figure 401 (Sheet 3 of 3)

Master
EFFECTIVITY: See Pageblock 28−21−13 page 401
28−21−13 Page 407
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
TASK 28−21−13−400−801
Installation of the Shroud and the Engine Fuel−Feed Line from FS621.00 to the Engine
Pylon Firewall

1. Job Set−up Information

Subtask 28−21−13−944−004
A. Consumable Materiels
REFERENCE DESIGNATION
06−002 Petrolatum
B0816024−003 Tie wrap
11−028A DS−108 Wipe solvent
11−009 Alcohol
None specified Lint−free cloth
05−052 Heat shrinkable tubing

Subtask 28−21−13−943−004
B. Tools and Equipment
REFERENCE DESIGNATION
None specified Heat gun

Subtask 28−21−13−945−001
C. Parts
REF NAME OF PART QTY IPC SEQUENCE NO.
5 Clamp 4 IPC 28−20−00−03−070
7 Clamp 2 IPC 28−20−00−03−015
10 Packing, preformed 4 IPC 28−20−00−03−010
11 Screw 4 IPC 28−20−00−03−030
12 Washer 4 IPC 28−20−00−03−035
13 Saddle clamp 2 IPC 28−20−00−03−025
18 Packing, preformed 8 IPC 28−20−00−03−065
19 Screw 10 IPC 28−20−00−03−315
20 Washer 10 IPC 28−20−00−03−320
21 Loop Clamp 10 IPC 28−20−00−03−305
25 Clamp 2 IPC 28−20−00−03−125
29 Packing, preformed 4 IPC 28−20−00−03−135
32 Screw 4 IPC 28−20−00−03−345
33 Washer 4 IPC 28−20−00−03−310
34 Nut 4 IPC 28−20−00−03−335
35 Bonding Jumper 2 IPC 28−20−00−03−325
37 Clamp 2 IPC 28−20−00−03−340

Master
EFFECTIVITY: See Pageblock 28−21−13 page 401
28−21−13 Page 408
Sep 10/2004
 C
AIRCRAFT MAINTENANCE MANUAL

REF NAME OF PART QTY IPC SEQUENCE NO.

38 Clamp 2 IPC 28−20−00−03−335
41 Packing, preformed 4 IPC 28−20−00−03−160
43 Packing, preformed 4 IPC 28−20−00−03−170

Subtask 28−21−13−946−002
D. Reference Information
REFERENCE DESIGNATION
TASK 20−30−00−910−802 Wiggins Couplings − Maintenance Practices
TASK 24−00−00−910−801 Electrical/Electronic Safety Precautions
TASK 24−00−00−910−802 Electrostatic Discharge Safety Precautions
TASK 28−00−00−910−801 Fuel Safety Precautions
TASK 28−00−00−710−801 Operational Test of the Fuel System
TASK 28−21−13−780−801 Pressure and Blockage Test of the Engine
Fuel−Feed Shroud, FS621.00 to the Engine Pylon
Firewall
TASK 28−20−01−780−802 Pressure and Blockage Test of the Engine
Fuel−Feed Line
TASK 20−21−00−910−801 Torque Procedure for Threaded Fasteners
TASK 73−10−00−910−801 Open the Fuel−Feed Shutoff Valve

2. Job Set−up
Subtask 28−21−13−910−004
WARNING: OBEY ALL THE FUEL SAFETY PRECAUTIONS WHEN YOU DO WORK ON THE
FUEL SYSTEM AND/OR A FUEL SYSTEM COMPONENT. IF YOU DO NOT DO
THIS, YOU CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO
EQUIPMENT.
A. Obey all the fuel safety precautions (Ref. TASK 28−00−00−910−801).

Subtask 28−21−13−910−005
B. Obey all the electrostatic discharge precautions (Ref. TASK 24−00−00−910−802).

Subtask 28−21−13−910−006
C. Obey all the electrical/electronic safety precautions (Ref. TASK 24−00−00−910−801).

Subtask 28−21−13−869−001
D. Make sure that the aircraft is in the same configuration as in the removal task.

Master
EFFECTIVITY: See Pageblock 28−21−13 page 401
28−21−13 Page 409
Sep 10/2004
 C
AIRCRAFT MAINTENANCE MANUAL
3. Procedure
Refer to Figure 401.
NOTE: It may be necessary to remove only a section of the shroud and fuel line assembly after
a fuel leak. For this reason some of the steps in the procedures that follow are repeated.
NOTE: For the procedures for the removal and installation of Wiggins couplings, refer to
Wiggins Couplings − Maintenance Practices (Ref. TASK 20−30−00−910−802).
Subtask 28−21−13−420−001
A. Install the lower section of the engine fuel−feed shroud from FS621.00 to FS632.50
(FS633.70 for the right side) as follows:
(1) Remove the blanking caps from the bulkhead fitting (9) at FS621.00.
(2) Remove the blanking cap from the fuel line (24) at FS632.50 (FS633.70 for the right
side).
(3) Remove the blanking caps from each end of the fuel line (17) of the shroud
assembly (15).
(4) Apply petrolatum to the preformed packing (10) and install on the shroud (14).
(5) Apply petrolatum to the preformed packing (10) and install on the bulkhead
fitting (9).
(6) Apply petrolatum to the preformed packing (18) and install on each end of the fuel
line (17).
(7) Apply petrolatum to the preformed packing (18) and install on the fuel line (45).
(8) Apply petrolatum to the preformed packing (18) and install on the fuel line (24).
(9) Carefully place the shroud (15) into position in the aircraft.
(10) Bring the two fuel feed lines (17) and (45) together at FS621.00.
(11) Connect the fuel lines (17) and (45) at the bulkhead fitting (9).
(12) Install the clamshell assembly (16) around the fuel line connection and snap the
latch closed, with pawls fully engaged.
(13) Connect the sliding tube assembly (14) to the bulkhead fitting (9).
(14) Install the clamshell assembly (8) around the fuel line connection and snap the latch
closed, with pawls fully engaged.
(15) Gently rock the shroud (15) over the tube assembly (14).
(16) Install and tighten the clamp (7) around the shroud connection (1).
(17) Torque the clamp (7) to 25 pound inches (2.82 N m).
(18) Loosely install the saddle clamp (13) at FS625.3 with two screws (11) and two
washers (12).
(19) Connect the fuel lines (17) and (24) together at FS632.50 (FS633.70 for the right
side).
(20) Install the clamshell (23) around the fuel line connection and snap the latch closed,
with pawls fully engaged.
(21) Slide the coupling shroud (22) over the fuel line connection.
(22) Gently rock the shrouds (15) and (27) over the coupling shroud (22).

Master
EFFECTIVITY: See Pageblock 28−21−13 page 401
28−21−13 Page 410
Sep 10/2004
 C
AIRCRAFT MAINTENANCE MANUAL
(23) Install and tighten the two clamps (5) over the shroud connection.
(24) Torque the clamp (5) to 25 pound inches (2.82 N m).
(25) Install and tighten the loop clamp (21) with the screw (19) and the washer (20) to
the fuselage mount at FS632.50 (FS633.70 for the right side).
(26) Tighten the screws (11) of the saddle clamp (13) at FS625.3.

Subtask 28−21−13−420−002
B. Install the center section engine fuel−feed shroud from FS632.50 (FS633.70 for the right
side) to FS648.5 as follows:
(1) Remove the blanking caps from the fuel line (17) at FS632.50 (FS633.70 for the
right side).
(2) Remove the blanking cap from the fuel line (30) at FS648.5.
(3) Remove the blanking caps from each end of the fuel line (24) of the shroud
assembly (27).
(4) Apply petrolatum to the preformed packing (18) and install on the fuel line (17).
(5) Apply petrolatum to the preformed packing (18) and install on the forward end of the
fuel line (24).
(6) Apply petrolatum to the preformed packing (29) and install on the aft end of the fuel
line (24).
(7) Apply petrolatum to the preformed packing (29) and install on the fuel line (30).
(8) Carefully place the shroud (27) into position in the aircraft.
(9) Bring the two fuel lines (17) and (24) together at FS632.50 (FS633.70 for the right
side).
(10) Connect the fuel lines (17) and (24) at FS632.50 (FS633.70 for the right side).
(11) Install the clamshell assembly (23) around the fuel line connection and snap the
latch closed, with pawls fully engaged.
(12) Slide the connecting shroud (22) over the fuel line connection.
(13) Gently rock the shrouds (15) and (27) over the coupling shroud (22).
(14) Install and tighten the clamps (5) around the shroud coupling (6).
(15) Torque the clamp (5) to 25 pound inches (2.82 N m).
(16) Install and tighten the loop clamp (21) with the screw (19) and the washer (20) to
the fuselage mount at FS632.50 (FS633.70 for the right side).
(17) Connect the fuel lines (17) and (30) together at FS648.5.
(18) Install the clamshell (28) around the fuel line connection and snap the latch closed,
with pawls fully engaged.
(19) Install the heat shrinkable tubing on the clamshell (28).
(20) Gently rock the shrouds (27) and (31) into each other.
(21) Install and tighten the clamp (25) over the shroud coupling (26).
(22) Torque the clamp (25) to 25 pound inches (2.82 N m).
(23) Install and tighten the loop clamp (21) with the screw (19) and the washer (20) to
the fuselage mount at FS640.

Master
EFFECTIVITY: See Pageblock 28−21−13 page 401
28−21−13 Page 411
Sep 10/2004
 C
AIRCRAFT MAINTENANCE MANUAL
Subtask 28−21−13−420−003
C. Install the upper section of the engine fuel−feed shroud from FS648.5 to FS656.2 as
follows:
(1) Remove the blanking cap from the fuel line (24) at FS648.5.
(2) Remove the blanking cap from the pylon fuel−line coupling (44) at FS656.2.
(3) Remove the blanking caps from each end of the fuel line (30) of the shroud
assembly (31).
(4) Apply petrolatum to the preformed packing (29) and install on the fuel line (30).
(5) Apply petrolatum to the preformed packing (29) and install on the fuel line (24).
(6) Apply petrolatum to the preformed packing (43) and install on the pylon fuel line
coupling (44).
(7) Apply petrolatum to the preformed packing (43) and install on the fuel line (30).
(8) Apply petrolatum to the preformed packing (41) and install on the shroud (31).
(9) Apply petrolatum to the preformed packing (41) and install on the shroud coupling
(36).
(10) Carefully place the shroud (31) into position in the aircraft.
(11) Bring the two fuel lines (24) and (30) together at FS648.5.
(12) Connect the fuel lines (24) and (30) at FS648.5.
(13) Install the clamshell assembly (28) around the fuel line connection and snap the
latch closed, with pawls fully engaged.
(14) Install the heat shrinkable tubing on the clamshell (28).
(15) Gently rock the shrouds (27) and (31) into each other.
(16) Install and tighten the clamp (25) around the shroud coupling (26).
(17) Torque the clamp (25) to 25 pound inches (2.82 N m).
(18) Connect the fuel lines (30) and (44) together at FS656.2.
(19) Install the clamshell (42) around the fuel line connection and snap the latch closed,
with pawls fully engaged.
(20) Slide the shroud coupling (36) over the fuel line connection against the pylon
coupling (40).
(21) Install the clamshell assembly (39) around the shroud coupling (36) and the pylon
coupling (40) and snap the latch closed, with pawls fully engaged.
(22) Slide the shroud (31) against the shroud coupling (36) and tighten the coupling
connector.
(23) Install the shroud clamp (37) around the shroud (31).
(24) Torque the clamp (37) to 25 pound inches (2.82 N m).
(25) Install the bonding jumper (35) with two screws (32), two washers (33), and two
nuts (34) between the shroud clamp (37) and the shroud coupling clamp (38).
(26) Install and tighten the loop clamp (21) with the screw (19) and the washer (20) to
the fuselage mount at FS640.
(27) Make sure there is a minimum clearance of 0.25 in. (6.35 mm) between the shroud

Master
EFFECTIVITY: See Pageblock 28−21−13 page 401
28−21−13 Page 412
Sep 10/2004
 C
AIRCRAFT MAINTENANCE MANUAL
(31) and the adjacent hydraulic hose.
NOTE: If the clearance is less than 0.25 in. (6.35 mm), contact the Bombardier
Technical help desk for aid.

4. Close−Out
Subtask 28−21−13−910−008
A. After two hours, torque the shroud clamps (5), (7), and (25).
B. After the torque is applied, mark the clamp screws with a dot of white lacquer.

Subtask 28−21−13−780−004
C. Do a pressure and blockage test of the fuel line shroud (Ref. TASK
28−21−13−780−801).

Subtask 28−21−13−780−005
D. Do a pressure and blockage test of the engine fuel−feed shroud, FS621.00 to the engine
pylon firewall (Ref. TASK 28−21−13−780−801).

Subtask 28−21−13−780−006
E. Do a pressure and blockage test of fuel feed lines (Ref. TASK 28−20−01−780−802).

Subtask 28−21−13−940−002
F. Open the fuel−feed shutoff valve (Ref. TASK 73−10−00−910−801).

Subtask 28−21−13−710−001
G. Do an operational test of the fuel system (Ref. TASK 28−00−00−710−801).

Subtask 28−21−13−410−002
H. Close the access door that follows:
ACCESS DESIGNATION
311BB Aft Equipment Bay Door

Subtask 28−21−13−410−003
I. Close the access panels that follow:
ACCESS DESIGNATION
412DB/422DB Power−Plant Line Disconnect

Subtask 28−21−13−941−003
J. Remove all tools, equipment and unwanted materials from the area.

Master
EFFECTIVITY: See Pageblock 28−21−13 page 401
28−21−13 Page 413
Sep 10/2004
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C ALL
SHROUDS, ENGINE FEED AND ABOVE WING− ADJUSTMENT/TEST

1. General
A. The maintenance procedures that follow are for the pressure and blockage tests of the
engine fuel−feed shroud, the motive flow shroud and the APU shroud. They are all
written as "the shroud" in this procedure. There are two engine fuel−feed shrouds found
between the aft pressure bulkhead at FS 621.00 and the engine pylon firewall. There are
two above wing fuel−feed shrouds at FS 501.4 and two above wing motive flow shrouds
at FS 503.9. The APU shroud is found at FS 506.4 on the right side drain panel.
B. The procedures are the same for the left and right fuel shrouds.
C. It is not necessary to defuel the aircraft to do the test of the shrouds.

TASK 28−21−13−780−801
Pressure and Blockage Test of the Engine Fuel−Feed Shroud, FS 621.00 to the Engine
Pylon Firewall

1. Job Set−Up Information

Subtask 28−21−13−943−001
A. Tools and Equipment
REFERENCE DESIGNATION
G601R282101−1 Check Kit, Fuel Flow
G601R121605−1 Gaseous Test Panel

Subtask 28−21−13−944−001
B. Consumable Materials
REFERENCE DESIGNATION
05−036 Fluid, leak detector

2. Procedure
Subtask 28−21−13−010−001
A. Remove the applicable access panels that follow:
ACCESS DESIGNATION
412DB/422DB Power−Plant Line Disconnect
434AB/444AB Lower Translating Cowl
434BB/444BB Thrust/Reverser Pylon−Tracks Lower

Subtask 28−21−13−480−001
Refer to Figure 501.

Master
EFFECTIVITY: See Pageblock 28−21−13 page 501
28−21−13 Page 501
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
B. Install the test equipment as follows:
(1) To do a test of the left shroud, connect the hose assembly of the fuel−flow check kit
to the left drain fitting (1).
(2) To do a test of the right shroud, connect the hose assembly of the fuel−flow check
kit to the right drain fitting (2).
(3) Connect the gaseous test panel to the hose assembly of the fuel−flow check kit.
(4) Close all the shut off valves on the gaseous test panel.
(5) Connect the pressurized air to the gaseous test panel.

Subtask 28−21−13−780−001
C. Do a blockage test of the engine fuel−feed shroud as follows:
(1) Slowly disconnect the shroud coupling body (3) from the nut (4) at the engine pylon
firewall. Remove the split retainer (5) from the engine feed−line coupling (6).
(2) Set the gaseous test panel to 20 psi (140 kPa).
(3) Slowly open the outlet valve on the gaseous test panel. Make sure that the air flows
out of the coupling body (3).
(4) Close the outlet valve on the gaseous test panel.
(5) Clean and lubricate the two preformed packings (7).
(6) Put the two halves of the split retainer (5) together over the two ferrules (8) and hold
in position.
(7) Install the two preformed packings (7) against the flanges (9).
(8) Connect the body (3) to the nut (4).

Subtask 28−21−13−780−002
D. Do a pressure test of the shroud as follows:
(1) Make sure that the gaseous test panel is set to 20 psi (140 kPa).
WARNING: KEEP ALL PERSONS AWAY FROM THE SHROUDS WHILE THEY ARE
PRESSURIZED. THE SHROUDS CAN CAUSE AN EXPLOSION.
(2) Slowly open the outlet valve on the gaseous test panel to pressurize the shroud (3).
Let the system become stable at 20 psi (140 kPa) for two minutes.
(3) Close the outlet valve on the gaseous test panel and let the system become stable
for three minutes. Make sure that there is no loss of pressure in the system.
NOTE: If there is a loss of pressure in the system, use a leak detector fluid to find
the leak. Repair the leak and do the pressure test of the shroud (3) again.
(4) Disconnect the shroud body (3) from the nut (4) and release the pressure. Connect
the shroud (3) to the fitting (4).

Master
EFFECTIVITY: See Pageblock 28−21−13 page 501
28−21−13 Page 502
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
3. Close Out
Subtask 28−21−13−080−001
A. Disconnect the test equipment as follows:
(1) Disconnect the pressurized air from the gaseous test panel of the fuel−flow check
kit.
(2) If the test of the left shroud was done, remove the hose assembly of the fuel−flow
check kit from the drain fitting (1).
(3) If the test of the right shroud was done, remove the hose assembly of the fuel−flow
check kit from the drain fitting (2).

Subtask 28−21−13−410−001
B. Install the applicable access panels that follow:
ACCESS DESIGNATION
412DB/422DB Power−Plant Line Disconnect
434AB/444AB Lower Translating Cowl
434BB/444BB Thrust/Reverser Pylon−Tracks Lower

Subtask 28−21−13−941−001
C. Remove all tools, equipment, and unwanted materials from the area.

Master
EFFECTIVITY: See Pageblock 28−21−13 page 501
28−21−13 Page 503
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

PRESSURE 1
2
BULKHEAD B
FS621.00

ENGINE PYLON
FIREWALL
A
A
5

4
7
8

8
7

9
B

LEGEND
1. Left drain fitting.
ram2821135_001(2).dg, db/gw, 16/06/97

2. Right drain fitting. MOTIVE FLOW

3. Shroud coupling body. SHROUD
4. Nut. (REF)
5. Split retainer.
6. Engine feed−line coupling.
7. Preformed packing.
8. Ferrule.
9. Flange.

Engine Fuel−Feed Shroud − Adjustment/Test

Figure 501

Master
EFFECTIVITY: See Pageblock 28−21−13 page 501
28−21−13 Page 504
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
TASK 28−21−13−780−802
Pressure and Leak Test of the Above Wing Fuel−Feed Shrouds at FS 501.4, the Motive Flow
Shrouds at FS 503.9 and the APU Shroud at FS 506.4

1. Job Set−Up Information

Subtask 28−21−13−943−002
A. Tools and Equipment
REFERENCE DESIGNATION
G601R282101−1 Check Kit, Fuel Flow
G601R121605−1 Gaseous Test Panel
G601R282001−1 Leak Test Kit − Fuel and Vent Lines Shroud

Subtask 28−21−13−944−002
B. Consumable Materials
REFERENCE DESIGNATION
05−036 Fluid, leak detector

2. Job Set−Up
Subtask 28−21−13−480−002
Refer to Figure 502.
A. To do the procedure for the above−wing fuel−feed shrouds, connect the test equipment
as follows:
(1) Make sure the fuel−feed drain shroud is free from FOD.
(2) Make sure that all shut off valves on the gaseous air test panel are closed.
(3) Connect the gaseous air test panel to the left drain fitting (1) with the pressure
adapter assembly (G601R282001−1).

Subtask 28−21−13−480−003
B. To do the procedure for the above−wing motive flow shrouds, connect the test
equipment as follows:
(1) Make sure the motive flow drain shroud is free from FOD.
(2) Make sure that all shut off valves on the gaseous air test panel are closed.
(3) Connect the gaseous air test panel to the left drain fitting (2) with the pressure
adapter assembly (G601R282001−1).

Subtask 28−21−13−480−004
C. To do the procedure for the above−wing APU fuel shroud, connect the test equipment as
follows:
(1) Make sure the APU fuel drain shroud is free from FOD.
(2) Make sure that all shut off valves on the gaseous air test panel are closed.

Master
EFFECTIVITY: See Pageblock 28−21−13 page 501
28−21−13 Page 505
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
(3) Connect the gaseous air test panel to the right drain fitting (4) with the pressure
adapter assembly (G601R282001−1).

3. Procedure
Subtask 28−21−13−780−003
A. Do a pressure test of the left above−wing fuel−feed shroud (1), the left motive flow
shroud (2), and the APU (4) shroud as follows:
NOTE: The procedure is the same for the left and right above−wing fuel−feed shroud,
the left and right motive flow shroud and the APU shroud.
WARNING: KEEP ALL PERSONS AWAY FROM THE SHROUDS WHILE THEY ARE
PRESSURIZED. THE SHROUDS CAN CAUSE AN EXPLOSION.
(1) Set the pressure on the gaseous air test panel to 20 psi (140 KPa).
(2) Slowly open the outlet valve on the gaseous air test panel to pressurize the line to
20 psi (140 Kpa).
(3) Let the system become stable at 20 psi (140 kPa) for two minutes.
(4) Close the gaseous air test panel outlet valve.
(5) Wait for a period of 10 minutes.
(6) Read the gauge on the air test panel. The maximum allowable pressure loss is 1.0
psi (6.9 KPa).
(7) If the pressure loss was more than 1.0 psi (6.9 KPa), use the leak detector solution
to find the source of the leakage.
(8) Release the pressure from the air test panel.
(9) If there was a leak, repair the leak and do the pressure test of the above−wing
shroud again.

4. Close Out
Subtask 28−21−13−941−002
A. Remove all tools, equipment and unwanted materials from the work area.

Master
EFFECTIVITY: See Pageblock 28−21−13 page 501
28−21−13 Page 506
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

B LEGEND
1. Engine drain fitting.
2. Motive flow fitting.
3. Pressure box drain fitting.
4. APU drain fitting.
A

FS501.40 FS503.90 FS506.40

FWD

1
2
A
3
LEFT SIDE

FS506.40 FS503.90 FS501.40

FWD
ram2821135_002.dg, jp/yf, 06/03/03

1
2 B
4
RIGHT SIDE

Engine Fuel Feed Drain − Adjustment/Test

Figure 502

Master
EFFECTIVITY: See Pageblock 28−21−13 page 501
28−21−13 Page 507
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C ALL
MOTIVE FLOW SYSTEM − DESCRIPTION AND OPERATION

1. General
A. The motive flow system supplies motive pressure from the engines to the venturi tubes
in the fuel system. The motive flow system contains the components that follow:
± Two wash filters
± Two motive−flow check valves
± Two venturi
± Four venturi tubes.
2. Component Details
Refer to Figure 1.
A. Wash Filter
(1) The wash filters are tee−unions with 70−micron filters which do not let ice crystals
go into the aft scavenge−ejector pumps. The wash filters are installed in the aft
inboard section of each main tank, connected at a junction in the motive flow line.
(2) Each wash filter has an input port, a filter element, and two output ports. As fuel
flows into the input port, it can go into the filter element. Fuel that flows through the
filter element flows through the output port that is connected to the aft
scavenge−ejector pump. Unfiltered fuel and ice crystals flow through the output port
that is connected to the primary ejector pump.
B. Motive−Flow Check Valve
(1) The motive−flow check valves are spring−loaded, poppet−type valves. These check
valves prevent reverse fuel flow in the motive flow lines from the primary ejector
pumps and the scavenge−ejector pump. The check valves are installed in the aft
inboard section of each main tank, connected to the input port of the wash filter.
(2) Each motive−flow check valve has a poppet, a spring, and a valve body. When the
engine operates, fuel pressure in the motive flow line pushes the poppet which
opens the passage in the valve body. When fuel flow stops, the spring pushes the
poppet back in place and closes the valve.
C. Venturi
(1) The venturi are venturi tubes with two pressure ports that supply pressure
connections to the fuel warning system (28−42−00). They are installed in the aft
inboard section of each main tank, connected between the wash filter and the aft
scavenge−ejector pumps.
(2) Each venturi has an input port, an output port, a venturi tube, an input−pressure
port, and an output−pressure port. Fuel flows through the input port, through the
venturi tube, and out of the output port. The effect of the venturi tube causes a
higher pressure at the input port than at the output port. The fuel warning system
monitors the two pressures to make sure that there is between 2.0 and 3.3 pounds
per square inch difference (13.8 to 22.8 ∆kPa).

Master
EFFECTIVITY: See Pageblock 28−22−00 page 1
28−22−00 Page 1
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
D. Venturi Tube
(1) The venturi tubes are small−diameter lines installed in the gravity flow manifolds to
cause a venturi effect. They are installed in the center wing box, connected to the
gravity feed manifold of the collector tanks.
(2) Each venturi connects a motive flow line from the output of the primary ejector
pump to the gravity feed manifold of the collector tank. The venturi effect supplied in
the gravity feed manifold helps to cause fuel pressure in the manifold.
3. Operation
Refer to Figure 2.
A. The motive flow system supplies motive flow pressure to all of the venturi tubes in the
fuel system. When the engine operates, the engine−driven fuel pump supplies fuel
pressure to the motive flow line, through the motive−flow check valve, and into the wash
filter. The wash filter does not let ice crystals in the fuel flow to the aft scavenge−ejector
pump.
B. The filtered fuel flows from the wash filter to the venturi where pressure in the scavenge
motive−flow line is monitored by the fuel warning system (28−42−00). From the venturi,
the fuel flow supplies motive pressure to the aft scavenge−ejector pump in the transfer
system (28−13−00).
C. The unfiltered fuel flows through the primary motive−flow line to the primary ejector. The
fuel flow supplies motive pressure to the primary ejector pump in the engine fuel−feed
system (28−21−00).
D. At the output of the primary ejector pump, there are two other motive flow lines, the
transfer motive−flow line and the gravity motive−flow line. The transfer motive−flow line
supplies motive flow to the transfer ejector pump of the transfer system. The gravity
motive−flow line supplies motive pressure to the venturi in the gravity feed manifold. The
venturi supply positive fuel pressure in the gravity feed manifold of the fuel tank system
(28−11−00).
4. Component Location Index
Refer to Figure 3.
COMPONENT NAME QTY ACCESS/ZONE REFERENCE
Check valve, motive flow 2 540AB, 640AB 28−22−04
Filter, wash 2 540AB, 640AB 28−22−01
Tube, venturi 4 510BB, 610BB −
Venturi 2 540BB, 640BB 28−22−07

Master
EFFECTIVITY: See Pageblock 28−22−00 page 1
28−22−00 Page 2
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

B
C

B
C

B MOTIVE FLOW CHECK VALVE

A VENTURI

ram2822000_003(1).dc, sw/ks, 15/06/95

C WASH FILTER

Motive Flow System − Component Location/Recognition

Figure 1

Master
EFFECTIVITY: See Pageblock 28−22−00 page 1
28−22−00 Page 3
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

TO AFT SCAVENGE TO AFT SCAVENGE

EJECTOR PUMP EJECTOR PUMP

TO FUEL TO FUEL
WARNING FOR GRAVITY WARNING
SYSTEM CROSSFLOW SYSTEM
VENTURI VENTURI
PRIMARY PRIMARY
EJECTOR PUMP EJECTOR PUMP
WASH WASH
FILTER FILTER

MOTIVE FLOW VENTURI VENTURI MOTIVE FLOW

CHECK VALVE TUBES TUBES CHECK VALVE
COLLECTOR COLLECTOR
TANK TANK

TO TRANSFER TO TRANSFER
FROM FROM
EJECTOR EJECTOR
ENGINE ENGINE
PUMP PUMP

TO ENGINES
ram2822000_001(2).dg, ks, 15/06/95

Motive Flow System − Schematic

Figure 2

Master
EFFECTIVITY: See Pageblock 28−22−00 page 1
28−22−00 Page 4
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

610BB 510BB

640AB 540AB

NOTE
500 series panels are on the left side.
600 series panels are on the right side.

ram2822000_002(2).dg, ks, 15/06/95

Motive Flow System − Component Access

Figure 3

Master
EFFECTIVITY: See Pageblock 28−22−00 page 1
28−22−00 Page 5
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C ALL
FILTER, WASH − REMOVAL/INSTALLATION

1. General
A. The maintenance procedures that follow are for the removal and installation of the wash
filter. There are two wash filters in the fuel system. They are found above the scavenge
ejectors, attached to the inboard bulkhead of each main tank. The wash filters are
connected to the motive flow lines of the scavenge ejectors.
B. It is necessary to defuel, drain, and remove the fuel fumes from the applicable main tank
to remove or install the wash filter.

TASK 28−22−01−000−801
Removal of the Wash Filter

1. Job Set−Up Information

Subtask 28−22−01−946−001
A. Reference Information
REFERENCE DESIGNATION
TASK 12−11−28−650−804 Suction Defueling
TASK 28−00−00−910−801 Fuel Safety Precautions
TASK 28−11−00−840−801 Prepare Fuel Tank for Access
TASK 28−11−00−840−802 Removal of Fuel Fumes
TASK 28−11−01−000−802 Removal of the Graphite Access Panel

2. Job Set−Up
Subtask 28−22−01−910−001
WARNING: OBEY ALL THE FUEL SAFETY PRECAUTIONS WHEN YOU DO WORK ON THE
FUEL SYSTEM AND/OR A FUEL SYSTEM COMPONENT. IF YOU DO NOT DO
THIS, YOU CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO
EQUIPMENT.
A. Obey all the fuel safety precautions (Ref. TASK 28−00−00−910−801).

Subtask 28−22−01−650−001
B. Defuel the applicable main tank (Ref. TASK 12−11−28−650−804).

Subtask 28−22−01−010−001
C. Remove the applicable access panel that follows (Ref. TASK 28−11−01−000−802):
ACCESS DESIGNATION
540AB Fuel tank access panel
640AB Fuel tank access panel

Master
EFFECTIVITY: See Pageblock 28−22−01 page 401
28−22−01 Page 401
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
Subtask 28−22−01−840−001
D. Prepare the applicable main tank for access (Ref. TASK 28−11−00−840−801).
E. Remove the fuel fumes from the applicable main tank (Ref. TASK 28−11−00−840−802).

3. Procedure
Subtask 28−22−01−020−001
Refer to Figure 401.
A. Remove the wash filter as follows:
(1) Remove the baffle (14).
(2) Remove the nut (1), the screw (2), and the washer (3) and disconnect the jumper
assembly (4) from the clamp (5).
(3) Discard the nut (1), the screw (2) and the washer (3).
(4) Remove the clamp (5) from the pressure line (6).
(5) Disconnect the pressure lines (6) from the check valve (7) and the wash filter (8).
(6) Remove the nut (9), the screw (10), the washer (11), and the clamp (12) from the
mounting bracket.
(7) Remove the check valve (7) and the wash filter (8).
(8) Remove the lockwire from the check valve (7) and the wash filter (8).
(9) Disassemble the wash filter (7) and the check valve (8). Remove and discard the
preformed packing (13).

Master
EFFECTIVITY: See Pageblock 28−22−01 page 401
28−22−01 Page 402
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

LEGEND.
1. Nut. 8. Wash filter.
2. Screw. 9. Nut.
3. Washer. 10. Screw.
4. Jumper assembly. 11. Washer.
5. Clamp. 12. Clamp.
6. Pressure line. 13. Preformed packing.
7. Check valve. 14. Baffle.

NOTE 14 3
Right side is shown.
Left side is the opposite.
5

FWD 6

MOUNTING
10
BRACKET
(REF) 7

11
13

4
9

6
12
8
ram2822014_001(2).dc, jp/ks, 11/07/95

Wash Filter − Removal/Installation

Figure 401

Master
EFFECTIVITY: See Pageblock 28−22−01 page 401
28−22−01 Page 403
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
TASK 28−22−01−400−801
Installation of the Wash Filter

1. Job Set−Up Information

Subtask 28−22−01−944−001
A. Consumable Materials
REFERENCE DESIGNATION
05−004 Lockwire
1422 Petrolatum Sealant

Subtask 28−22−01−945−001
B. Parts
REF NAME OF PART QTY IPC SEQUENCE NO.
1 Nut 1 TBD
2 Screw 1 TBD
3 Washer 1 IPC 28−21−00−1A−050
4 Jumper assembly 1 TBD
5 Clamp 1 TBD
9 Nut 1 IPC 28−22−00−1A−235
10 Screw 1 IPC 28−22−00−1A−225
11 Washer 1 IPC 28−22−00−1A−230
12 Clamp 1 IPC 28−22−00−1A−215
13 Preformed packing 1 IPC 28−22−00−1A−155

Subtask 28−22−01−946−002
C. Reference Information
REFERENCE DESIGNATION
TASK 28−11−01−400−802 Installation of the Graphite Access Panel
TASK 28−13−22−710−801 Operational Test of the Aft Scavenge Ejector
Pump

2. Procedure
Subtask 28−22−01−869−001
A. Make sure that the aircraft is in the same configuration as in the removal task.

Subtask 28−22−01−420−001
Refer to Figure 401.

Master
EFFECTIVITY: See Pageblock 28−22−01 page 401
28−22−01 Page 404
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
B. Install the wash filter as follows:
(1) Install the preformed packing (13) in the check valve (7) with lubrication.
(2) Assemble the check valve (7) and the wash filter (8). Make sure that the arrow on
the check points to the wash filter. Safety the check valve to the wash filter with
safety wire.
(3) Hold the wash filter (8) and the check valve (7) in position. Make sure that the arrow
on the check valve points aft.
(4) Install the clamp (12) on the wash filter (8).
(5) Install the clamp (12), the washer (11), the screw (10), and the nut (9) on the
mounting bracket.
(6) Connect the pressure lines (6) to the wash filter (8) and the check valve (7).
(7) Install the clamp (5) on the pressure line (6).
(8) Connect the jumper assembly (4) and install the washer (3), the screw (2), and the
nut (1).
(9) Apply sealant to the screw (2), the washer (3) and the nut (9).
(10) Install the baffle (14).

3. Close Out
Subtask 28−22−01−410−001
A. Install the applicable access panel that follows (Ref. TASK 28−11−01−400−802):
ACCESS DESIGNATION
540AB Fuel tank access panel
640AB Fuel tank access panel

Subtask 28−22−01−710−001
B. Do an operational test of the wash filter (Ref. TASK 28−13−22−710−801).

Master
EFFECTIVITY: See Pageblock 28−22−01 page 401
28−22−01 Page 405
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C ALL
CHECK VALVE, MOTIVE FLOW − REMOVAL/INSTALLATION

1. General
A. The maintenance procedures that follow are for the removal and installation of the
motive flow check valve (written as the "check valve" in this procedure). There are two
check valves in the fuel system. They are found above the scavenge ejectors, attached
to the inboard bulkhead of each main tank. The check valves are connected to the
motive flow lines of the scavenge ejectors.
B. It is necessary to defuel, drain, and remove the fuel fumes from the applicable main tank
to remove or install the check valve.

TASK 28−22−04−000−801
Removal of the Motive Flow Check Valve

1. Job Set−Up Information

Subtask 28−22−04−946−001
A. Reference Information
REFERENCE DESIGNATION
TASK 12−11−28−650−804 Suction Defueling
TASK 28−00−00−910−801 Fuel Safety Precautions
TASK 28−11−00−840−801 Prepare Fuel Tank for Access
TASK 28−11−00−840−802 Removal of Fuel Fumes
TASK 28−11−01−000−802 Removal of the Graphite Access Panel

2. Job Set−Up
Subtask 28−22−04−910−001
WARNING: OBEY ALL THE FUEL SAFETY PRECAUTIONS WHEN YOU DO WORK ON THE
FUEL SYSTEM AND/OR A FUEL SYSTEM COMPONENT. IF YOU DO NOT DO
THIS, YOU CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO
EQUIPMENT.
A. Obey all the fuel safety precautions (Ref. TASK 28−00−00−910−801).

Subtask 28−22−04−650−001
B. Defuel the applicable main tank (Ref. TASK 12−11−28−650−804).

Subtask 28−22−04−010−001
C. Remove the applicable access panel that follows (Ref. TASK 28−11−01−000−802):

Master
EFFECTIVITY: See Pageblock 28−22−04 page 401
28−22−04 Page 401
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

ACCESS DESIGNATION
540AB Fuel tank access panel
640AB Fuel tank access panel

Subtask 28−22−04−840−001
D. Prepare the applicable main tank for access (Ref. TASK 28−11−00−840−801).
E. Remove the fuel fumes from the applicable main tank (Ref. TASK 28−11−00−840−802).

3. Procedure
Subtask 28−22−04−020−001
Refer to Figure 401.
A. Remove the check valve as follows:
(1) Remove the baffle (14).
(2) Remove the nut (1), the screw (2), and the washer (3) and disconnect the jumper
assembly (4) from the clamp (5).
(3) Discard the nut (1), the screw (2) and the washer (3).
(4) Remove the clamp (5) from the pressure line (6).
(5) Disconnect the pressure line (6) from the check valve (7).
(6) Remove the nut (9), the screw (10), the washer (11), and the clamp (12) from the
mounting bracket.
(7) Remove the lockwire from the check valve (7) and the wash filter (8). Remove the
check valve (6) from the wash filter (7).
(8) Remove and discard the preformed packing (13).

Master
EFFECTIVITY: See Pageblock 28−22−04 page 401
28−22−04 Page 402
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

LEGEND.
1. Nut. 8. Wash filter.
2. Screw. 9. Nut.
3. Washer. 10. Screw.
4. Jumper assembly. 11. Washer.
5. Clamp. 12. Clamp.
6. Pressure line. 13. Preformed packing.
7. Check valve. 14. Baffle.

14 2

NOTE 3
Right side is shown.
Left side is the opposite.
5

FWD 6

MOUNTING
10
BRACKET
(REF) 7

11
13

4
9

12
8
ram2822044_001(2).dc, jp/ks, 11/07/95

Motive Flow Check Valve − Removal/Installation

Figure 401

Master
EFFECTIVITY: See Pageblock 28−22−04 page 401
28−22−04 Page 403
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
TASK 28−22−04−400−801
Installation of the Motive Flow Check Valve

1. Job Set−Up Information

Subtask 28−22−04−944−001
A. Consumable Materials
REFERENCE DESIGNATION
05−004 Lockwire
1422 Petrolatum
TBD Sealant

Subtask 28−22−04−945−001
B. Parts
REF NAME OF PART QTY IPC SEQUENCE NO.
1 Nut 1 TBD
2 Screw 1 TBD
3 Washer 1 TBD
4 Jumper assembly 1 TBD
5 Clamp 1 TBD
9 Nut 1 IPC 28−22−00−1A−235
10 Screw 1 IPC 28−22−00−1A−225
11 Washer 1 IPC 28−22−00−1A−230
12 Clamp 1 IPC 28−22−00−1A−215
13 Preformed packing 1 IPC 28−22−00−1A−082

Subtask 28−22−04−946−002
C. Reference Information
REFERENCE DESIGNATION
TASK 28−11−01−400−802 Installation of the Graphite Access Panel
TASK 28−13−22−710−801 Operational Test of the Aft Scavenge Ejector
Pump

2. Procedure
Subtask 28−22−04−869−001
A. Make sure that the aircraft is in the same configuration as in the removal task.

Subtask 28−22−04−420−001
Refer to Figure 401.

Master
EFFECTIVITY: See Pageblock 28−22−04 page 401
28−22−04 Page 404
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
B. Install the check valve as follows:
(1) Install the preformed packing (13) in the check valve (7) using lubrication.
(2) Install the check valve (7) on the wash filter (8). Make sure that the arrow on the
check valve points to the wash filter. Safety the check valve to the wash filter with
lockwire.
(3) Install the clamp (12) on the wash filter (8).
(4) Install the clamp (12), the washer (11), the screw (10), and the nut (9) on the
mounting bracket.
(5) Connect the pressure line (6) to the check valve (7).
(6) Install the clamp (5) on the pressure line (6).
(7) Connect the jumper assembly (4) and install the washer (3), the screw (2), and the
nut (1).
(8) Apply sealant to the washer (3), the screw (2) and the nut (1).
(9) Install the baffle (14).

3. Close Out
Subtask 28−22−04−410−001
A. Install the applicable access panel that follows (Ref. TASK 28−11−01−400−802):
ACCESS DESIGNATION
540AB Fuel tank access panel
640AB Fuel tank access panel

Subtask 28−22−04−710−001
B. Do an operational test of the check valve (Ref. TASK 28−13−22−710−801).

Master
EFFECTIVITY: See Pageblock 28−22−04 page 401
28−22−04 Page 405
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C ALL
VENTURI − REMOVAL/INSTALLATION

1. General
A. The maintenance procedures that follow are for the removal and installation of the
venturi. There are two venturi in the fuel system. They are connected to the motive flow
lines, above the scavenge ejectors.
B. It is necessary to defuel, drain, and remove the fuel fumes from the applicable main tank
to remove or install the venturi.

TASK 28−22−07−000−801
Removal of the Venturi

1. Job Set−Up Information

Subtask 28−22−07−946−001
A. Reference Information
REFERENCE DESIGNATION
TASK 12−11−28−650−804 Suction Defueling
TASK 28−00−00−910−801 Fuel Safety Precautions
TASK 28−11−00−840−801 Prepare Fuel Tank for Access
TASK 28−11−00−840−802 Removal of Fuel Fumes
TASK 28−11−01−000−802 Removal of the Graphite Access Panel

2. Job Set−Up
Subtask 28−22−07−910−001
WARNING: OBEY ALL THE FUEL SAFETY PRECAUTIONS WHEN YOU DO WORK ON THE
FUEL SYSTEM AND/OR A FUEL SYSTEM COMPONENT. IF YOU DO NOT DO
THIS, YOU CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO
EQUIPMENT.
A. Obey all the fuel safety precautions (Ref. TASK 28−00−00−910−801).

Subtask 28−22−07−650−001
B. Defuel the applicable main tank (Ref. TASK 12−11−28−650−804).

Subtask 28−22−07−010−001
C. Remove the applicable access panel that follows (Ref. TASK 28−11−01−000−802):
ACCESS DESIGNATION
540AB Fuel tank access panel
640AB Fuel tank access panel

Master
EFFECTIVITY: See Pageblock 28−22−07 page 401
28−22−07 Page 401
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
Subtask 28−22−07−840−001
D. Prepare the applicable main tank for access (Ref. TASK 28−11−00−840−801).
E. Remove the fuel fumes from the applicable main tank (Ref. TASK 28−11−00−840−802).

3. Procedure
Subtask 28−22−07−020−001
Refer to Figure 401.
A. Remove the venturi as follows:
(1) Remove the baffle (7).
(2) Disconnect the tube assembly (2) that is connected between the fuel filter and the
venturi (3).
(3) Disconnect the pressure lines (1). Put protective plugs in the pressure lines.
(4) Disconnect the motive flow line (4) and remove the venturi (3). Put a protective plug
in the motive flow line.
(5) Remove the unions (5) and the preformed packings (6) from the venturi (3). Discard
the preformed packings.

Master
EFFECTIVITY: See Pageblock 28−22−07 page 401
28−22−07 Page 402
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

LEGEND.
1. Pressure line.
2. Tube assembly.
3. Venturi.
4. Motive flow line.
5. Union.
6. Preformed packing. 7
7. Baffle.

FUEL FILTER
(REF)

5
6

5
6

3 ram2822074_001(1).dc, ks, 11/07/95

NOTE:
Left side is shown.
4
Right side is opposite.

Venturi − Removal/Installation
Figure 401

Master
EFFECTIVITY: See Pageblock 28−22−07 page 401
28−22−07 Page 403
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
TASK 28−22−07−400−801
Installation of the Venturi

1. Job Set−Up Information

Subtask 28−22−07−945−001
A. Parts
REF NAME OF PART QTY IPC SEQUENCE NO.
6 Preformed packing 2 IPC 28−22−00−1A−110
5 Union 2 IPC 28−22−00−1A−105

Subtask 28−22−07−946−002
B. Reference Information
REFERENCE DESIGNATION
TASK 28−11−01−400−802 Installation of the Graphite Access Panel
TASK 28−13−22−710−801 Operational Test of the Aft Scavenge Ejector
Pump

2. Procedure
Subtask 28−22−07−869−001
A. Make sure that the aircraft is in the same configuration as in the removal task.

Subtask 28−22−07−420−001
Refer to Figure 401.
B. Install the venturi as follows:
(1) Install the preformed packings (6) and the unions (5) on the venturi (3). Use
lubrication.
(2) Remove the protective plug from the motive flow line (4). Connect the venturi (3) to
the motive flow line. Make sure that the arrow on the venturi points aft.
(3) Install the tube assembly (2) between the fuel filter and the venturi (3).
(4) Remove the protective plugs from the pressure lines (1). Connect the pressure lines
to the unions (5).
(5) Install the baffle (7).

3. Close Out
Subtask 28−22−07−410−001
A. Install the applicable access panel that follows (Ref. TASK 28−11−01−400−802):

Master
EFFECTIVITY: See Pageblock 28−22−07 page 401
28−22−07 Page 404
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

ACCESS DESIGNATION
540AB Fuel tank access panel
640AB Fuel tank access panel

Subtask 28−22−07−710−001
B. Do an operational test of the applicable venturi (Ref. TASK 28−13−22−710−801).

Master
EFFECTIVITY: See Pageblock 28−22−07 page 401
28−22−07 Page 405
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C ALL
LINES, MOTIVE FLOW − REMOVAL/INSTALLATION

1. General
A. The maintenance procedures that follow are for the removal and installation of the
motive flow lines. There are four motive flow lines in the fuel system. The motive flow
lines are in the rear sections of the tank and are connected to the check valve, and to the
venturi.
B. It is necessary to defuel the aircraft. Remove the fuel and the fuel fumes from the tank to
remove or install the motive flow lines.

TASK 28−22−09−000−801
Removal of the Motive Flow Lines

1. Job Set−Up Information

Subtask 28−22−09−943−001
A. Tools and Equipment
REFERENCE DESIGNATION
None specified Container, fuel, 10 U.S. gallons (38 L)

Subtask 28−22−09−946−001
B. Reference Information
REFERENCE DESIGNATION
TASK 12−11−28−650−804 Suction Defueling
TASK 28−00−00−910−801 Fuel Safety Precautions
TASK 28−11−00−840−801 Prepare Fuel Tank for Access
TASK 28−11−00−840−802 Removal of Fuel Fumes
TASK 28−11−01−000−802 Removal of the Aluminum Access Panel

2. Job Set−Up
Subtask 28−22−09−910−001
WARNING: OBEY ALL THE FUEL SAFETY PRECAUTIONS WHEN YOU DO WORK ON THE
FUEL SYSTEM AND/OR A FUEL SYSTEM COMPONENT. IF YOU DO NOT DO
THIS, YOU CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO
EQUIPMENT.
A. Obey all the fuel safety precautions (Ref. TASK 28−00−00−910−801).

Master
EFFECTIVITY: See Pageblock 28−22−09 page 401
28−22−09 Page 401
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
Subtask 28−22−09−650−001
B. Defuel the applicable tank and the center tank (Ref. TASK 12−11−28−650−804).

Subtask 28−22−09−010−001
C. Remove the aluminum access panels that follows (as applicable) (Ref. TASK
28−11−01−000−802):
ACCESS DESIGNATION
540AB Fuel tank access panel
640AB Fuel tank access panel

Subtask 28−22−09−840−001
D. Prepare the applicable tank and the center tank for access (Ref. TASK
28−11−00−840−801).
E. Remove the fuel fumes from the applicable tank and the center tank (Ref. TASK
28−11−00−840−802).

3. Procedure
Subtask 28−22−09−020−001
Refer to Figure 401.
A. Remove the motive flow lines (1), (2), (3), and (4) as follows:
(1) Remove the baffle (10).
(2) Disconnect the motive flow line (1) that is connected to the motive flow line (2). Put
a protective cap on the motive flow line (1) to prevent contamination.
(3) Disconnect the motive flow line (2). Put a protective cap on the motive flow line (2)
to prevent contamination.
(4) Disconnect the motive flow line (3) that is connected to the motive flow line (4). Put
a protective cap on the motive flow line (3) to prevent contamination.
(5) Disconnect the motive flow line (4). Put a protective cap on the motive flow line (4)
to prevent contamination.
(6) Loosen and remove the nuts (5). Remove the unions (7), the washers (6) and (8).
Discard the washers (6) and (8).

Master
EFFECTIVITY: See Pageblock 28−22−09 page 401
28−22−09 Page 402
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

LEGEND
1. Tube assembly.
2. Tube assembly.
3. Tube assembly.
4. Tube assembly.
5. Nut.
6. Washer.
7. Union.
8. Washer.
10 9. Stop bar.
10. Baffle.

NOTE
Right side equipment is shown.
10 Left side equipment is opposite.

5
6

1
3

7
8
9
9
ram2822094_002.dg, rm, 08/07/03

5
2

Motive Flow Lines − Removal/Installation

Figure 401

Master
EFFECTIVITY: See Pageblock 28−22−09 page 401
28−22−09 Page 403
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
TASK 28−22−09−400−801
Installation of the Motive Flow Lines

1. Job Set−Up Information

Subtask 28−22−09−946−002
A. Reference Information
REFERENCE DESIGNATION
TASK 28−11−01−400−802 Installation of the Aluminum Access Panel
TASK 28−13−22−710−801 Operational Test of the Aft Scavenge Ejector
Pump
TASK 28−22−09−780−801 Pressure Blockage and Leak Test of the Motive
Flow Lines

2. Procedure
Subtask 28−22−09−869−001
A. Make sure that the aircraft is in the same configuration as in the removal task.

Subtask 28−22−09−420−001
Refer to Figure 401.
B. Install the motive flow lines (1), (2), (3) and (4) as follows:
(1) Install the unions (7) with the washers (8), the washers (6) and the nuts (5).
(2) Remove the protective plugs from the motive flow lines (1), (2), (3) and (4).
(3) Install the motive flow lines (1), (2), (3) and (4).
(4) Install the baffle (10).

3. Close Out
Subtask 28−22−09−410−001
A. Install the aluminum access panel that follows (as applicable) (Ref. TASK
28−11−01−400−802):
ACCESS DESIGNATION
540AB Fuel tank access panel
640AB Fuel tank access panel

Subtask 28−22−09−780−003
B. Do the pressure blockage test and leak test of the motive flow lines (Ref. TASK
28−22−09−780−801).

Master
EFFECTIVITY: See Pageblock 28−22−09 page 401
28−22−09 Page 404
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
Subtask 28−22−09−710−002
C. Do the operational test of the aft scavenge ejector pump (Ref. TASK
28−13−22−710−801).

Subtask 28−22−09−941−002
D. Remove all tools, equipment, and unwanted materials from the area.

Master
EFFECTIVITY: See Pageblock 28−22−09 page 401
28−22−09 Page 405
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C ALL
LINES, MOTIVE FLOW − ADJUSTMENT/TEST

1. General
A. The maintenance procedures that follow are for the pressure blockage test and the leak
test of the motive flow lines. There are two sets of the motive flow lines.
B. It is not necessary to defuel the aircraft to do a test of the motive flow lines.

TASK 28−22−09−780−801
Pressure Blockage Test and Leak Test of the Motive Flow Lines

1. Job Set−Up Information

Subtask 28−22−09−943−002
A. Tools and Equipment
REFERENCE DESIGNATION
G601R282101−1 Check Kit, Fuel Flow
G601R121605−1 Gaseous Test Panel

Subtask 28−22−09−944−001
B. Consumable Materials
REFERENCE DESIGNATION
05−036 Fluid, leak detector

2. Procedure
Subtask 28−22−09−010−002
A. Remove the applicable access panels that follow:
ACCESS DESIGNATION
412DB/422DB Power−Plant Line Disconnect
434AB/444AB Lower Translating Cowl
434BB/444BB Thrust/Reverser Pylon−Tracks Lower

Subtask 28−22−09−480−001
Refer to Figure &
B. Install the test equipment as follows:
(1) For the test of the left shroud, connect the hose assembly of the fuel−flow check kit
to the fitting (1).
(2) For the test of the right shroud, connect the hose assembly of the fuel−flow check
kit to the fitting (2).

Master
EFFECTIVITY: See Pageblock 28−22−09 page 501
28−22−09 Page 501
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
(3) Connect the gaseous test panel to the hose assembly of the fuel−flow check kit.
(4) Close all of the valves on the gaseous test panel.
(5) Connect a supply of clean compressed air to the gaseous test panel.

Subtask 28−22−09−780−001
C. Do a blockage test of the motive flow shroud as follows:
(1) Slowly disconnect the shroud coupling body (3) from the nut (4) at the engine pylon
firewall. Remove the retainer (5) from the motive flow coupling (6).
(2) Set the gaseous test panel to 20 psi (140 kPa).
(3) Slowly open the outlet valve on the gaseous test panel. Make sure that the air flows
out of the coupling body (3).
(4) Close the outlet valve on the gaseous test panel.
(5) Lubricate the packings (7).
(6) Put the both sections of the retainer (5) together above the two ferrules (8).
(7) Over the two ferrules (8), assemble the both sections of the retainer (5).
(8) Install the two packings (7) against the flanges (9).
(9) Connect the body (3) to the nut (4).

Subtask 28−22−09−780−002
D. Do a pressure test of the shroud as follows:
(1) Make sure that the gaseous test panel is set to 20 psi (140 kPa).
WARNING: KEEP ALL PERSONS AWAY FROM THE SHROUDS WHILE THEY ARE
PRESSURIZED. THE SHROUDS CAN CAUSE AN EXPLOSION.
(2) Slowly open the outlet valve on the gaseous test panel to pressurize the shroud (3).
Let the system become stable at 20 psi (140 kPa) for two minutes.
(3) Close the outlet valve on the gaseous test panel. Let the system become stable for
3 minutes. Make sure that the pressure stays the same in the system.
NOTE: If the pressure goes down in the system, use a 05−036 leak detector fluid
to find the leak. Repair the leak and do the pressure test (3) again.
(4) Disconnect the shroud body (3) from the nut (4). Release the pressure. Connect the
shroud (3) to the nut (4).

3. Close Out
Subtask 28−22−09−080−001
A. Disconnect the test equipment as follows:
(1) Disconnect the compressed air supply from the gaseous test panel.
(2) When the test of the left shroud is complete, remove the hose assembly of the
fuel−flow check kit from the fitting (1).
(3) When the test of the right shroud is complete, remove the hose assembly of the
fuel−flow check kit from the fitting (2).

Master
EFFECTIVITY: See Pageblock 28−22−09 page 501
28−22−09 Page 502
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
(4) Disconnect the hose assembly from the fuel−flow check kit that is attached to the
gaseous test panel.

Subtask 28−22−09−410−002
B. Install the applicable access panels that follow:
ACCESS DESIGNATION
412DB/422DB Power−Plant Line Disconnect
434AB/444AB Lower Translating Cowl
434BB/444BB Thrust/Reverser Pylon−Tracks Lower

Subtask 28−22−09−941−001
C. Remove all tools, equipment, and unwanted materials from the area.

Master
EFFECTIVITY: See Pageblock 28−22−09 page 501
28−22−09 Page 503
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

PRESSURE 2 1
BULKHEAD B
FS621.00

A
A
ENGINE PYLON
FIREWALL
ENGINE FEED
SHROUD
(REF)

6
4
7 8
8 7
LEGEND
1. Left drain fitting.
ram2822115_002(2).dg, db/gw, 16/06/97

2. Right drain fitting. 3

3. Shroud coupling body.
4. Nut. 9 5
5. Split retainer.
B
6. Motive flow coupling.
7. Preformed packing.
8. Ferrule.
9. Flange.

Motive Flow Lines − Adjustment/Test

Figure 501

Master
EFFECTIVITY: See Pageblock 28−22−09 page 501
28−22−09 Page 504
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C ALL
SHROUD, MOTIVE FLOW − ADJUSTMENT/TEST

1. General
A. The maintenance procedures that follow are for the pressure and blockage tests of the
motive flow shroud (written as "the shroud" in this procedure). There are two shrouds
between the aft pressure bulkhead at FS 621.00 and the engine pylon firewall.
B. It is not necessary to defuel the aircraft to do a test of the shrouds.

TASK 28−22−11−780−801
Pressure and Blockage Test of the Motive Flow Shroud, FS 621.00 to the Engine Pylon
Firewall

1. Job Set−Up Information

Subtask 28−22−11−943−001
A. Tools and Equipment
REFERENCE DESIGNATION
G601R282101−1 Check Kit, Fuel Flow
G601R121605−1 Gaseous Test Panel

Subtask 28−22−11−944−001
B. Consumable Materials
REFERENCE DESIGNATION
05−036 Fluid, leak detector

2. Procedure
Subtask 28−22−11−010−001
A. Remove the applicable access panels that follow:
ACCESS DESIGNATION
412DB/422DB Power−Plant Line Disconnect
434AB/444AB Lower Translating Cowl
434BB/444BB Thrust/Reverser Pylon−Tracks Lower

Subtask 28−22−11−480−001
Refer to Figure 501.
B. Install the test equipment as follows:
(1) To do a test of the left shroud, connect the hose assembly of the fuel−flow check kit
to the left drain fitting (1).

Master
EFFECTIVITY: See Pageblock 28−22−11 page 501
28−22−11 Page 501
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
(2) To do a test of the right shroud, connect the hose assembly of the fuel−flow check
kit to the right drain fitting (2).
(3) Connect the gaseous test panel to the hose assembly of the fuel−flow check kit.
(4) Close all of the shutoff valves on the gaseous test panel.
(5) Connect the pressurized air to the gaseous test panel.

Subtask 28−22−11−780−001
C. Do a blockage test of the motive flow shroud as follows:
(1) Slowly disconnect the shroud coupling body (3) from the nut (4) at the engine pylon
firewall. Remove the split retainer (5) from the motive flow coupling (6).
(2) Set the gaseous test panel to 20 psi (140 kPa).
(3) Slowly open the outlet valve on the gaseous test panel. Make sure that the air flows
out of the coupling body (3).
(4) Close the outlet valve on the gaseous test panel.
(5) Clean and lubricate the two preformed packings (7).
(6) Put the two halves of the split retainer (5) together over the two ferrules (8) and hold
in position.
(7) Install the two preformed packings (7) against the flanges (9).
(8) Connect the body (3) to the nut (4).

Subtask 28−22−11−780−002
D. Do a pressure test of the shroud as follows:
(1) Make sure that the gaseous test panel is set to 20 psi (140 kPa).
WARNING: KEEP ALL PERSONS AWAY FROM THE SHROUDS WHILE THEY ARE
PRESSURIZED. THE SHROUDS CAN CAUSE AN EXPLOSION.
(2) Slowly open the outlet valve on the gaseous test panel to pressurize the shroud (3).
Let the system become stable at 20 psi (140 kPa) for two minutes.
(3) Close the outlet valve on the gaseous test panel and let the system become stable
for three minutes. Make sure that there is no loss of pressure in the system.
NOTE: If there is a loss of pressure in the system, use a leak detector fluid to find
the leak. Repair the leak and do the pressure test of the shroud (3) again.
(4) Disconnect the shroud body (3) from the nut (4) and release the pressure. Connect
the shroud (3) to the fitting (4).

3. Close Out
Subtask 28−22−11−080−001
A. Disconnect the test equipment as follows:
(1) Disconnect the pressurized air from the gaseous test panel of the fuel−flow check
kit.
(2) If the test of the left shroud was done, remove the hose assembly of the fuel−flow
check kit from the drain fitting (1).

Master
EFFECTIVITY: See Pageblock 28−22−11 page 501
28−22−11 Page 502
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
(3) If the test of the right shroud was done, disconnect the hose assembly of the
fuel−flow check kit from the right drain fitting (2).

Subtask 28−22−11−410−001
B. Install the applicable access panels that follow:
ACCESS DESIGNATION
412DB/422DB Power−Plant Line Disconnect
434AB/444AB Lower Translating Cowl
434BB/444BB Thrust/Reverser Pylon−Tracks Lower

Subtask 28−22−11−941−001
C. Remove all tools, equipment, and unwanted materials from the area.

Master
EFFECTIVITY: See Pageblock 28−22−11 page 501
28−22−11 Page 503
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

PRESSURE 2 1
BULKHEAD B
FS621.00

A
A
ENGINE PYLON
FIREWALL
ENGINE FEED
SHROUD
(REF)

6
4
7 8
8 7
LEGEND
1. Left drain fitting.
ram2822115_002(2).dg, db/gw, 16/06/97

2. Right drain fitting. 3

3. Shroud coupling body.
4. Nut. 9 5
5. Split retainer.
B
6. Motive flow coupling.
7. Preformed packing.
8. Ferrule.
9. Flange.

Motive Flow Shroud − Adjustment/Test

Figure 501

Master
EFFECTIVITY: See Pageblock 28−22−11 page 501
28−22−11 Page 504
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C ALL
STANDBY FUEL FEED SYSTEM − DESCRIPTION AND OPERATION

1. General
A. The standby fuel−feed system supplies fuel to the engines for engine start up and during
failure of the engine fuel−feed system (28−21−00). The standby fuel−feed system has
the components that follow:
± Two electric boost pumps
± Two boost pump canisters
± Two standby−fuel−feed check valves
± Two boost pump switch/lights.
2. Component Details
A. Electric Boost Pump
Refer to Figure 1.
(1) The electric boost pumps are electrically−operated impeller−type pumps that move
fuel from the collector tanks to the standby fuel−feed manifold. The electric boost
pumps are on the aft lower wing skin of the center wing box, installed in the boost
pump canister.
(2) Each electric boost pump has a 28−volt−dc motor, an impeller, and a drain plug.
When a pump−on signal is supplied to the pump motor, the pump motor turns the
impeller which causes fuel to move. The pump impeller causes fuel to move from
the inlet screen of the boost pump canister to the pump outlet port.
(3) The drain plug lets the operator drain fuel out of the electric boost pump. When the
electric boost pump is removed after it is drained, it is not necessary to defuel the
aircraft.
B. Boost Pump Canister
(1) The boost pump canisters are containers for the electric boost pumps. The boost
pump canisters permit the operator to remove the electric boost pumps while there
is fuel in the fuel tanks. The boost pump canisters are in the aft center wing box.
(2) Each boost pump canister has an inlet screen, an output port, a check valve, a
spring−loaded canister poppet, and an electrical feedthrough. When the electric
boost pump operates, it causes fuel to move from the pump feed manifold, through
the inlet screen, and to the output port. The output port has a check valve that
prevents reverse flow and also closes the output port when the electric boost pump
is removed.
(3) The spring−loaded canister poppet is a container in the boost pump canister that
closes the inlet screen when the electric boost pump is removed. As the electric
boost pump is removed, the spring pushes the canister poppet between the electric
boost pump and the inlet screen.
(4) The electrical feedthrough supplies electrical connections to the electric boost pump
through the top of the boost pump canister.

Master
EFFECTIVITY: See Pageblock 28−23−00 page 1
28−23−00 Page 1
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
C. Standby−Fuel−Feed Check Valve
(1) The standby−fuel−feed check valves are spring−loaded bipetal−flapper valves that
prevent reverse flow in the standby fuel−feed manifold. The standby−fuel−feed
check valves are located in the standby fuel−feed manifold, downstream of the
electric boost pumps.
(2) Each standby−fuel−feed check valve has a spring, a bipetal−flapper assembly, and
a valve seat. The valve seat holds the bipetal−flapper assembly in place in the fuel
feed manifold. When pressure in the fuel feed manifold pushes the bipetal−flapper
assembly, it opens the two passages in the valve seat. When fuel flow in the engine
feed manifold stops, the spring pushes the bipetal−flapper assembly back in place,
which closes the valve.
D. Boost Pump Switch/Light
Refer to Figure 2.
(1) The boost pump switch/lights are illuminated split−legend pushbuttons. They are
located on the FUEL control panel on the overhead panel in the flight compartment.
There is one switch/light for the right side and one switch/light for the left side.
(2) Each boost pump switch/light is used to control and monitor the status of the
applicable electric boost pump. When the switch/light is off, the electric boost pump
is off. When the operator pushes the switch/light, the electric boost pump comes on.
This sends a signal back to the switch/light which makes the ON legend come on.
(3) When the operator pushes the switch/light again, the electric boost pump goes off.
This sends a signal back to the switch/light which makes the ON legend go off and
the INOP legend come on.
(4) If the electric boost pump does not operate, a signal is sent to the boost pump
switch/light which makes the INOP legend come on.
3. Operation
Refer to Figure 3.
A. The standby fuel−feed system supplies fuel to the engines during engine−startup and
engine−fuel−feed−system failures. When the electric boost pumps operate, they move
fuel from the related collector tank to the engine feed manifold in the engine fuel−feed
system (28−21−00). The standby−fuel−feed check valve controls the direction of flow
from the electric boost pumps. The installation of the standby−fuel−feed check valves
also lets fuel from each electric boost pump supply the two engine feed manifolds.
B. During an engine start, the operator pushes the boost pump switch/light to operate the
boost pumps and supplies the engines with fuel. When the engines operate, the
engine−driven fuel pumps in the engines supply the motive flow system (28−22−00) with
motive flow pressure. The motive flow system then supplies motive pressure to the
engine feed system (28−24−00) which causes the primary ejector pumps to operate. As
the primary ejector pumps operate, the fuel pressure from the primary ejector pumps is
monitored by the fuel warning system (28−42−00). When the pressure from the primary
ejector pumps is sufficient to supply the engines, the fuel warning system disconnects
the 28−volt−dc power from the electric boost pumps. When the electric boost pumps
stop, the ON legend on the boost pump switch/light goes off.
C. If there is a failure in the engine feed system, the fuel warning system detects the failure
and connects the 28−volt−dc power to the electric boost pumps again. This signal
causes the ON legend comes on and the electric boost pumps to operate and supply
fuel to the engines.

Master
EFFECTIVITY: See Pageblock 28−23−00 page 1
28−23−00 Page 2
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
4. Component Location Index
Refer to Figure 4.
COMPONENT NAME QTY ACCESS/ZONE REFERENCE
Canister, boost pump 2 510AB, 610AB 28−23−03
Check valve, standby fuel feed 2 510AB, 610AB 28−23−07
Circuit breakers:
L FUEL PUMP, M6 1 CBP−1/221 −
L FUEL PUMP CONT, M7 1 CBP−1/221 −
R FUEL PUMP, G10 1 CBP−2/221 −
R FUEL PUMP CONT, G11 1 CBP−2/221 −
Pump, electric boost 2 510CB, 610CB 28−23−01
Switch/light, LEFT PUMP 1 221, Flight compartment 28−23−04
Switch/light, RIGHT PUMP 1 221, Flight compartment 28−23−04

Master
EFFECTIVITY: See Pageblock 28−23−00 page 1
28−23−00 Page 3
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

A ELECTRIC
BOOST PUMP

STANDBY FUEL FEED

B CHECK VALVE

A
ram2823000_003.dc, KS, 10/07/91

BOOST PUMP
C
CANISTER

Standby Fuel Feed System − Component Location/Recognition

Figure 1

Master
EFFECTIVITY: See Pageblock 28−23−00 page 1
28−23−00 Page 4
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

LEFT PUMP RIGHT PUMP

SWITCH/LIGHT SWITCH/LIGHT

L BOOST GRAVITY R BOOST

PUMP XFLOW PUMP

ON FAIL ON
F INOP OPEN INOP
U
ram2823000_004(1).dg, pb/ks, 15/06/95
E XFLOW
L AUTO OVERRIDE R
L
ON ON
MAN
FAIL FAIL

Standby Fuel Feed System Controls − Component Location/Recognition

Figure 2

Master
EFFECTIVITY: See Pageblock 28−23−00 page 1
28−23−00 Page 5
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

COLLECTOR COLLECTOR
TANK FROM PRIMARY TANK
EJECTOR
PUMPS

STANDBY
ELECTRIC ELECTRIC
FUEL
BOOST BOOST
FEED CHECK
PUMP PUMP
VALVE
TO TO
ENGINE ENGINE

ram2823000_001.dg, PB, 08/05/91

Standby Fuel Feed System − Schematic

Figure 3

Master
EFFECTIVITY: See Pageblock 28−23−00 page 1
28−23−00 Page 6
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

610AB 510AB

610CB 510CB

NOTE
500 series panels are on the left side.
600 series panels are on the right side.

ram2823000_002.dg, PB, 08/07/91

Standby Fuel Feed System − Component Access

Figure 4

Master
EFFECTIVITY: See Pageblock 28−23−00 page 1
28−23−00 Page 7
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C ALL
PUMP, ELECTRIC BOOST − REMOVAL/INSTALLATION

1. General
A. The maintenance procedures that follow are for the removal and installation of the
electric boost pump. There are two electric boost pumps in the fuel system. They are
found in the aft section of the center wing box. It is not necessary to defuel the aircraft to
remove or install the electric boost pumps.

TASK 28−23−01−000−801
Removal of the Electric Boost Pump

1. Job Set−Up Information

Subtask 28−23−01−943−001
A. Tools and Equipment
REFERENCE DESIGNATION
None specified Container, 5−U.S. gallon (20 L)

Subtask 28−23−01−946−001
B. Reference Information
REFERENCE DESIGNATION
TASK 28−00−00−910−801 Fuel Safety Precautions

2. Job Set−Up
Subtask 28−23−01−910−001
WARNING: OBEY ALL THE FUEL SAFETY PRECAUTIONS WHEN YOU DO WORK ON THE
FUEL SYSTEM AND/OR A FUEL SYSTEM COMPONENT. IF YOU DO NOT DO
THIS, YOU CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO
EQUIPMENT.
A. Obey all the fuel safety precautions (Ref. TASK 28−00−00−910−801).

Subtask 28−23−01−865−001
B. Open, safety, and tag the circuit breakers that follow:
CB PANEL CB NO. NAME ZONE
CBP−1 M6 L FUEL PUMP 221
CBP−1 M7 L FUEL PUMP CONT 221
CBP−1 M12 FUEL SYST CONT 221
CBP−2 G10 R FUEL PUMP 222
CBP−2 G11 R FUEL PUMP CONT 222
CBP−4 B10 FUEL SYST CONT 222

Master
EFFECTIVITY: See Pageblock 28−23−01 page 401
28−23−01 Page 401
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
Subtask 28−23−01−010−001
C. Remove the applicable access panels that follow:
ACCESS DESIGNATION
510CB Boost pump cover
610CB Boost pump cover

3. Procedure
Subtask 28−23−01−680−001
Refer to Figure 401.
A. Remove the electric boost pumps as follows:
(1) Put a fuel container directly below the electric boost pump.
(2) Remove the screws (4) and the washers (5). Hold the boost pump up to prevent
downward movement of the boost pump as you remove the last screw (4).
(3) Hold the handle on the electric boost pump and pull it quickly half way down out of
the boost pump canister and hold it there. Be prepared for a small amount of fuel
that will come out as you do this. Hold the pump at this position until no more fuel
comes out.
NOTE: There is a check valve above the pressure port that keeps fuel in the fuel
line above the check valve when the pump is removed. Some of the fuel
below the check valve comes out as the pressure port of the pump is
removed from its receptacle in the top of the boost pump canister.
(4) Remove the electric boost pump and drain the fuel in the top of the pump into the
container.
(5) Remove and discard the preformed packings (6), (7) and (8).

Master
EFFECTIVITY: See Pageblock 28−23−01 page 401
28−23−01 Page 402
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

BOOST PUMP
CANISTER
(REF) LEGEND
1. Drain plug.
2. Washer.
3. Preformed packing.
4. Screw.
PRESSURE 5. Washer.
PORT 6. Preformed packing.
(REF) 7. Preformed packing.
8 8. Preformed packing.

BOOST PUMP
(REF)
7

HANDLE
(REF) ram2823014_001(2).dg, kms/pm, 01/06/98

3
5
2

4
1
B
B

Electric Boost Pump − Removal/Installation

Figure 401

Master
EFFECTIVITY: See Pageblock 28−23−01 page 401
28−23−01 Page 403
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
TASK 28−23−01−400−801
Installation of the Electric Boost Pump

1. Job Set−Up Information

Subtask 28−23−01−944−001
A. Consumable Materials
REFERENCE DESIGNATION
06−002 Petrolatum

Subtask 28−23−01−945−001
B. Parts
REF NAME OF PART QTY IPC SEQUENCE NO.
4 Screw 4 IPC 28−23−00−01−180
5 Washer 4 IPC 28−23−00−01−181
6 Preformed packing 1 IPC 28−23−00−01−185
7 Preformed packing 1 IPC 28−23−00−01−190
8 Preformed packing 1 IPC 28−23−00−01−195

Subtask 28−23−01−946−002
C. Reference Information
REFERENCE DESIGNATION
TASK 28−23−01−710−801 Operational Test of the Electric Boost Pump

2. Procedure
Subtask 28−23−01−869−001
A. Make sure that the aircraft is in the same configuration as in the removal task.

Subtask 28−23−01−420−001
Refer to Figure 401.
B. Install the electric boost pump as follows:
(1) Apply a layer of petrolatum to the preformed packings (6), (7) and (8).
(2) Install the preformed packings (6), (7) and (8) on the boost pump.
(3) Move the boost pump into position and align the pressure port on the top of the
electric boost pump with its mating receptacle at the top of the boost pump canister.
(4) Carefully move the boost pump up into the housing until you can feel the pressure
port on the top of the boost pump start to engage its receptacle in the canister.
Have one of the screws (4) and washers (5) ready in your hand as you do this.
(5) When you are sure that correct engagement of the boost pump pressure port has
started, quickly push the boost pump all the way up and hold it there. Do not let it

Master
EFFECTIVITY: See Pageblock 28−23−01 page 401
28−23−01 Page 404
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
go until you have installed the first screw.
NOTE: If you do not hold the pump up until the screw is installed, it can move
down and let fuel leak from the pressure inlet at the top of the canister.
(6) Install the screws (4) with the washers (5).

3. Close Out
Subtask 28−23−01−865−002
A. Remove the tags and close the circuit breakers that follow:
CB PANEL CB NO. NAME ZONE
CBP−1 M6 L FUEL PUMP 221
CBP−1 M7 L FUEL PUMP CONT 221
CBP−1 M12 FUEL SYST CONT 221
CBP−2 G10 R FUEL PUMP 222
CBP−2 G11 R FUEL PUMP CONT 222
CBP−4 B10 FUEL SYST CONT 222

Subtask 28−23−01−710−001
B. Do an operational test of the electric boost pump (Ref. TASK 28−23−01−710−801).

Subtask 28−23−01−210−001
C. Examine the area around the electric boost pump and the drain plug for leaks.

Subtask 28−23−01−410−001
D. Install the applicable access panels that follow:
ACCESS DESIGNATION
510CB Boost pump cover
610CB Boost pump cover

Subtask 28−23−01−941−001
E. Remove all tools, equipment and unwanted materials from the work area.

Master
EFFECTIVITY: See Pageblock 28−23−01 page 401
28−23−01 Page 405
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C ALL
PUMP, ELECTRIC BOOST − ADJUSTMENT/TEST

1. General
A. The maintenance procedure that follows is for the test of the electric boost pump and the
boost pump canister.

TASK 28−23−01−710−801
Operational Test of the Electric Boost Pump

1. Job Set-Up Information

Subtask 28−23−01−946−003
A. Reference Information
REFERENCE DESIGNATION
TASK 12−00−07−861−801 Connect External AC Power
TASK 12−00−07−861−802 Remove External AC Power
TASK 12−11−28−650−802 Manual Pressure Refueling

2. Job Set−Up
Subtask 28−23−01−861−001
A. Connect the external AC power to the aircraft (Ref. TASK 12−00−07−861−801).
B. Push the FUEL pushbutton on the engine indication and crew alerting system (EICAS)
control panel to get the FUEL synoptic display.

3. Procedure
Subtask 28−23−01−710−002
A. If the left boost pump was replaced, do a test as follows:
(1) At the FUEL control panel, push in the L BOOST PUMP switch/light. Make sure that
the ON light comes on and that the INOP light does not come on.
(2) Make sure that the left boost pump operates. Examine the area around the left
boost pump. Make sure that there is sound or vibration.
(3) At the FUEL control panel, push out the L BOOST PUMP switch/light. Make sure
that the ON light goes off and the INOP light comes on.

Subtask 28−23−01−710−003
B. If the right boost pump was replaced, do a test as follows:
(1) At the FUEL control panel, push in the R BOOST PUMP switch/light. Make sure
that the ON light comes on and that the INOP light does not come on.
(2) Make sure that the right boost pump operates. Examine the area around the right
boost pump. Make sure that there is sound or vibration.

Master
EFFECTIVITY: See Pageblock 28−23−01 page 501
28−23−01 Page 501
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
(3) At the FUEL control panel, push out the R BOOST PUMP switch/light. Make sure
that the ON light goes off and that the INOP light comes on.

Subtask 28−23−01−869−002
CAUTION: MAKE SURE THAT THERE IS A MINIMUM OF 200 POUNDS (90KG) OF FUEL IN
BOTH MAIN TANKS BEFORE YOU OPERATE THE ELECTRIC BOOST PUMPS.
WHEN YOU SELECT EITHER THE L OR R BOOST PUMP SWITCH/LIGHT,
BOTH PUMPS WILL OPERATE. IF YOU DO NOT DO THIS, YOU WILL DAMAGE
THE EQUIPMENT.
C. If either of the main tanks has less than 200 pounds (90 kg) of fuel, refuel one or both
main tanks, as required (Ref. TASK 12−11−28−650−802).

Subtask 28−23−01−710−004
D. If the left electric boost pump was replaced, do a test as follows:
(1) On the fuel synoptic display of the EICAS, make sure that the left electric boost
pump is shown in amber.
(2) At the FUEL control panel, push in the L BOOST PUMP switch/light. Make sure that
the ON light comes on and that the INOP light does not come on.
(3) On the fuel synoptic display, make sure that the left electric boost pump is shown in
green.
(4) At the FUEL control panel, push out the L BOOST PUMP switch/light. Make sure
that the ON light goes off and that the INOP light comes on.

Subtask 28−23−01−710−005
E. If the right electric boost pump was replaced, do a test as follows:
(1) On the fuel synoptic display of the EICAS, make sure that the right electric boost
pump is shown in amber.
(2) At the FUEL control panel, push in the R BOOST PUMP switch/light. Make sure
that the ON light comes on and that the INOP light does not come on.
(3) On the fuel synoptic display, make sure that the right electric boost pump is shown
in green.
(4) At the FUEL control panel, push out the R BOOST PUMP switch/light. Make sure
that the ON light goes off and that the INOP light comes on.

Subtask 28−23−01−861−002
F. Remove the external AC power from the aircraft (Ref. TASK 12−00−07−861−802).

Master
EFFECTIVITY: See Pageblock 28−23−01 page 501
28−23−01 Page 502
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C ALL
CANISTER, BOOST PUMP − REMOVAL/INSTALLATION

1. General
A. The maintenance procedures that follow are for the removal and installation of the boost
pump canister. There are two boost pump canisters in the fuel system. They are found in
the aft section of the center wing box.
B. It is necessary to defuel, drain, and remove the fuel fumes from the center tank and the
main tank that corresponds to the applicable booster pump. You must perform this step if
you want to remove or install the boost pump canister or the electric boost pump.

TASK 28−23−03−000−801
Removal of the Boost Pump Canister

1. Job Set−Up Information

Subtask 28−23−03−946−001
A. Reference Information
REFERENCE DESIGNATION
TASK 12−11−28−650−804 Suction Defueling
TASK 28−00−00−910−801 Fuel Safety Precautions
TASK 28−11−00−840−801 Prepare Fuel Tank for Access
TASK 28−11−00−840−802 Removal of Fuel Fumes
TASK 28−11−01−000−801 Removal of the Honeycomb Access Panel
TASK 28−11−01−000−802 Removal of the Aluminum Access Panel
TASK 28−23−01−000−801 Removal of the Electric Boost Pump
TASK 53−83−01−000−801 Removal of the MLG Wheel Bin
WM 20−12−00 Wiring − Installation
WM 20−17−10 Wiring Manual

2. Job Set−Up
Subtask 28−23−03−910−001
WARNING: OBEY ALL THE FUEL SAFETY PRECAUTIONS WHEN YOU DO WORK ON THE
FUEL SYSTEM AND/OR A FUEL SYSTEM COMPONENT. IF YOU DO NOT DO
THIS, YOU CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO
EQUIPMENT.
A. Obey all the fuel safety precautions (Ref. TASK 28−00−00−910−801).

Subtask 28−23−03−865−001
B. Open, safety, and tag the circuit breakers that follow:

Master
EFFECTIVITY: See Pageblock 28−23−03 page 401
28−23−03 Page 401
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

CB PANEL CB NO. NAME ZONE

CBP−1 M6 L FUEL PUMP 221
CBP−1 M7 L FUEL PUMP CONT 221
CBP−1 M12 FUEL SYST CONT 221
CBP−2 G10 R FUEL PUMP 222
CBP−2 G11 R FUEL PUMP CONT 222
CBP−4 B10 FUEL SYST CONT 222

Subtask 28−23−03−010−001
C. Remove the electric boost pump (Ref. TASK 28−23−01−000−801).

Subtask 28−23−03−650−001
D. Defuel the center tank and the left or the right main tank related to the booster pump that
is to be removed (Ref. TASK 12−11−28−650−804).

Subtask 28−23−03−010−002
E. For the left boost pump canister, remove the left wheel bin from the main wheel well
(Ref. TASK 53−83−01−000−801).
F. For the right boost pump canister, remove the right wheel bin from the main wheel well
(Ref. TASK 53−83−01−000−801).
G. To remove the left boost pump canister, remove the access panel that follows (Ref.
TASK 28−11−01−000−801).
ACCESS DESCRIPTION
510AB Fuel tank access panel
H. To remove the right boost pump canister, remove the access panel that follows (Ref.
TASK 28−11−01−000−802).
ACCESS DESCRIPTION
610AB Fuel tank access panel

Subtask 28−23−03−840−001
I. Prepare the center tank for access (Ref. TASK 28−11−00−840−801).
J. Remove the fuel fumes from the center tank and the applicable main tank (Ref. TASK
28−11−00−840−802).

3. Procedure
Subtask 28−23−03−030−001
A. Disconnect the electrical connections (Ref. WM 20−17−10).
B. Remove the wires from the electrical conduit as follows:

Master
EFFECTIVITY: See Pageblock 28−23−03 page 401
28−23−03 Page 402
Dec 15/2004
 C
AIRCRAFT MAINTENANCE MANUAL
(1) Disconnect the electrical conduit (1) from the boost pump canister (2).
(2) Remove the wires from the electrical conduit (1) (Ref. WM 20−12−00).

**ON A/C 7003−7067, 7069−7939 Pre SB601R−57−032

Subtask 28−23−03−020−001
Refer to Figure 401
C. Remove the boost pump canister as follows:
(1) Remove the drain valve (3) and the preformed packing (4). Discard the preformed
packing.
(2) Disconnect the pump discharge tube assembly (5) from the boost pump canister
(2).
(3) Disconnect the pressure pickup line (6) and then remove the reducer (7), and the
preformed packing (8) from the boost pump canister (2). Discard the preformed
packing.
(4) Disconnect the collector tank tube assembly from the container inlet (9).
(5) Remove the bolts (10) and the washers (11) from the container cover (12).
(6) Remove the container cover (12) and the gasket (13) from the container assembly
(14). Discard the gasket.
(7) Remove the uniseal bolts (15) and lift out the boost pump canister (2) from the
container assembly (14). Discard the uniseal bolts.
(8) Remove and discard the preformed packing (16) from the boost pump canister (2).
(9) Remove the nuts (17), the washers (18) and the uniseal bolts (19) from the
container assembly (14). Discard the uniseal bolts.
(10) Remove the drain valve housing (20) from the container assembly (14).
(11) Remove the container assembly (14) from the lower wing skin.
(12) Remove and discard the gaskets (21) and (22), which were between the container
assembly (14) and the lower wing skin.
(13) Remove any sealant from the bottom of the container assembly (14) and external
wing skin, when applicable.

**ON A/C 7003−7067, 7069−7939 Post SB601R−57−032

Subtask 28−23−03−020−003
Refer to Figure 402
D. Remove the boost pump canister as follows:
(1) Remove the drain valve (3) and the preformed packing (4). Discard the preformed
packing.
(2) Disconnect the pump discharge tube assembly (5) from the boost pump canister
(2).
(3) Disconnect the pressure pickup line (6) and then remove the reducer (7), and the
preformed packing (8) from the boost pump canister (2). Discard the preformed
packing.

Master
EFFECTIVITY: See Pageblock 28−23−03 page 401
28−23−03 Page 403
Dec 15/2004
 C
AIRCRAFT MAINTENANCE MANUAL
(4) Disconnect the collector tank tube assembly from the container inlet (9).
(5) Remove the bolts (10) and the washers (11) from the container cover (12).
(6) Remove the container cover (12) and the gasket (13) from the container assembly
(14). Discard the gasket.
(7) Remove the uniseal bolts (15) from the plate assembly (24). Discard the uniseal
bolts (15).
(8) Lift out the boost pump canister (2) from the container (14).
(9) Remove and discard the uniseal bolts (23)
(10) Remove the nuts (17), washers (18), and the uniseal bolts (19) from the drain valve
housing (20).
(11) Remove the drain valve housing (20).
(12) Remove the container assembly (14) from the lower wing.
(13) Remove and discard the gasket (25), which was between the container assembly
(14) and the lower wing skin.
(14) Remove any sealant from the bottom of the container assembly (14) and external
wing skin, when applicable.

**ON A/C 7940−7990, 8000−8064, 8066−8068

Subtask 28−23−03−020−004
Refer to Figure 403
E. Remove the boost pump canister as follows:
(1) Remove the drain valve (3) and the preformed packing (4). Discard the preformed
packing.
(2) Disconnect the pump discharge tube assembly (5) from the boost pump canister
(2).
(3) Disconnect the pressure pickup line (6) and then remove the reducer (7), and the
preformed packing (8) from the boost pump canister (2). Discard the preformed
packing.
(4) Disconnect the collector tank tube assembly from the container inlet (9).
(5) Remove the bolts (10) and the washers (11) from the container cover (12).
(6) Remove the container cover (12) and the gasket (13) from the container assembly
(14). Discard the gasket.
(7) Remove the uniseal bolts (23) from the lower wing skin. Discard the uniseal bolts
(23).
(8) Remove the plate (22) and the container assembly (14) from the lower wing.
(9) Remove and discard the gasket (21).
(10) Remove the uniseal bolts (15) from the boost pump canister (2). Discard the uniseal
bolts (15).
(11) Remove the canister (2) from the container assembly (14).
(12) Remove the nuts (17), washers (18), and the uniseal bolts (19) from the drain valve
housing (20). Discard the uniseal bolts (19).

Master
EFFECTIVITY: See Pageblock 28−23−03 page 401
28−23−03 Page 404
Dec 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
(13) Remove the drain valve housing (20).
(14) Remove the plate assembly (22) from the container assembly (14).
(15) Remove any sealant from the bottom of the container assembly (14) and the wing
skin.

Master
EFFECTIVITY: See Pageblock 28−23−03 page 401
28−23−03 Page 405
Dec 15/2004
 C
AIRCRAFT MAINTENANCE MANUAL

10 11
12
11

13

1 5

6
LEGEND
7
1. Electrical conduit. 2
2. Boost pump canister.
3. Drain valve. 9 17
4. Preformed packing.
5. Pump discharge tube assembly.
6. Pressure pickup line. 18
7. Reducer. 16
8. Preformed packing.
20
9. Container inlet.
10. Bolt.
11. Washer.
12. Container cover.
13. Gasket. 14
14. Container assembly.
15. Uniseal bolt.
16. Preformed packing.
17. Nut.
18. Washer.
19. Uniseal bolt. 21
20. Drain valve housing.
21. Gasket.
22. Gasket.
LOWER
WING SKIN
(REF)
NOTE 22 19
ram2823034_001.dg, pm/lr, 27/10/04

Left side shown,

right side opposite.
4

15 3

Boost Pump Canister − Removal/Installation

Figure 401

Master
EFFECTIVITY: See Pageblock 28−23−03 page 401
28−23−03 Page 406
Dec 15/2004
 C
AIRCRAFT MAINTENANCE MANUAL

10 11
12
11

13

5
1
8

6
7
2
LEGEND
17
1. Electrical conduit. 9
2. Boost pump canister.
18
3. Drain valve.
4. Preformed packing.
5. Pump discharge tube assembly. 20
6. Pressure pickup line.
7. Reducer. 16
8. Preformed packing.
9. Container inlet. 14
10. Bolt.
11. Washer.
12. Container cover.
13. Gasket.
14. Container assembly.
25
15. Uniseal bolt.
16. Preformed packing.
17. Nut.
18. Washer.
19. Uniseal bolt. LOWER
20. Drain valve housing. WING SKIN
21. Gasket. (REF)
22. Gasket.
19
23. Uniseal bolt.
24. Plate assembly.
25. Gasket. 4 ram2823034_003.dg, rm/lr, 26/10/04

NOTE 3
24 23
Left side shown,
right side opposite.

15
A

Boost Pump Canister

Figure 402

Master
EFFECTIVITY: See Pageblock 28−23−03 page 401
28−23−03 Page 407
Dec 15/2004
 C
AIRCRAFT MAINTENANCE MANUAL

10 11 B 12
11

A
13
LEGEND

1. Electrical conduit. 5
1
2. Boost pump canister.
3. Drain valve. 8
4. Preformed packing.
5. Pump discharge tube assembly. 6
6. Pressure pickup line.
7. Reducer. 2 7
8. Preformed packing. 17
9. Container inlet. 9
10. Bolt. 18
11. Washer.
12. Container cover.
13. Gasket. 20
14. Container assembly.
15. Uniseal bolt.
16. Preformed packing. 16
17. Nut.
18. Washer.
19. Uniseal bolt.
20. Drain valve housing.
21. Gasket. 14
22. Plate assembly.
23. Uniseal bolt.
NOTES
1. Left side shown,
right side opposite.
19
2 Apply sealant to fill the gap
all around the perimeter of CONTAINER
ASSEMBLY 22
the gasket and plate.
(REF)
15
PLATE
CL ASSEMBLY 2
(REF) 21
GASKET
(REF)
ram2823034_004.dg, pm/lr, 27/10/04

LOWER
WING SKIN
(REF) B
LOWER
4
WING SKIN
(REF)
23 3
B B SHOWN ASSEMBLED A

Boost Pump Canister − Removal/Installation

Figure 403

Master
EFFECTIVITY: See Pageblock 28−23−03 page 401
28−23−03 Page 408
Dec 15/2004
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C ALL
TASK 28−23−03−400−801
Installation of the Boost Pump Canister

1. Job Set−Up Information

Subtask 28−23−03−944−002
A. Consumable Materials
REFERENCE DESIGNATION
05−034 Paint Brush
06−002 Petrolatum
09−013 Sealant, fuel tank, low weight
09−034 Sealant, fuel tank, low weight

**ON A/C 7003−7031, 7033−7058, 7060, 7062, 7064−7067, 7069−7093, 7095−7102, 7104−7109,
7111−7124, 7126−7132, 7134−7141, 7143−7147, 7149−7165, 7168−7169, 7171−7204,
7206−7271, 7273−7277, 7279−7345, 7347−7364, 7366−7370, 7372−7383, 7385−7395,
7397−7399 Pre SB601R−28−048

Subtask 28−23−03−945−001
B. Parts
REF NAME OF PART QTY IPC SEQUENCE NO.
3 Drain valve 1 IPC 28−23−00−1A−200
4 Preformed packing 1 IPC 28−23−00−1A−205
7 Reducer 1 IPC 28−23−00−1A−255A
8 Preformed packing 1 IPC 28−23−00−1A−260
10 Bolt 28 IPC 28−23−00−1A−240
11 Washer 28 IPC 28−23−00−1A−245
12 Container cover 1 IPC 28−23−00−1A−235
13 Gasket 1 IPC 28−23−00−1A−250
15 Uniseal bolt 12 IPC 28−23−00−1A−270
16 Preformed packing 1 IPC 28−23−00−1A−272
17 Nut 2 IPC 28−23−00−1A−225
18 Washer 2 IPC 28−23−00−1A−220
19 Uniseal bolt 2 IPC 28−23−00−1A−215
20 Drain valve housing 1 IPC 28−23−00−1A−210
21 Gasket 1 IPC 28−23−00−1A−230
22 Gasket 1 IPC 28−23−00−1A−275

Master
EFFECTIVITY: See Pageblock 28−23−03 page 401
28−23−03 Page 409
Aug 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C 7032, 7059, 7061, 7063, 7094, 7103, 7110, 7125, 7133, 7142, 7148, 7166−7167, 7170,
7205, 7272, 7278, 7346, 7365, 7371, 7384, 7396, 7400−7990, 8000−8064, 8066−8068 and ON
A/C 7003−7031, 7033−7058, 7060, 7062, 7064−7067, 7069−7093, 7095−7102, 7104−7109,
7111−7124, 7126−7132, 7134−7141, 7143−7147, 7149−7165, 7168−7169, 7171−7204,
7206−7271, 7273−7277, 7279−7345, 7347−7364, 7366−7370, 7372−7383, 7385−7395,
7397−7399 Post SB601R−28−048

Subtask 28−23−03−945−002
C. Parts
REF NAME OF PART QTY IPC SEQUENCE NO.
3 Drain valve 1 IPC 28−23−00−1A−200
4 Preformed packing 1 IPC 28−23−00−1A−205
7 Reducer 1 IPC 28−23−00−1A−255A
8 Preformed packing 1 IPC 28−23−00−1A−260
10 Bolt 28 IPC 28−23−00−1A−240
11 Washer 28 IPC 28−23−00−1A−245
12 Container cover 1 IPC 28−23−00−1A−235
13 Gasket 1 IPC 28−23−00−1A−250
15 Uniseal bolt 12 IPC 28−23−00−1A−270
16 Preformed packing 1 IPC 28−23−00−1A−272
17 Nut 2 IPC 28−23−00−1A−225
18 Washer 2 IPC 28−23−00−1A−220
19 Uniseal bolt 2 IPC 28−23−00−1A−215
20 Drain valve housing 1 IPC 28−23−00−1A−210
21 Gasket 1 IPC 28−23−00−1A−230
22 Gasket 1 IPC 28−23−00−1A−275A

**ON A/C 7940−7990, 8000−8064, 8066−8068

Subtask 28−23−03−945−003
D. Parts
REF NAME OF PART QTY IPC SEQUENCE NO.
3 Drain valve 1 IPC 28−23−00−1A−200
4 Preformed packing 1 IPC 28−23−00−1A−205
7 Reducer 1 IPC 28−23−00−1A−255A
8 Preformed packing 1 IPC 28−23−00−1A−260
10 Bolt 28 IPC 28−23−00−1A−240
11 Washer 28 IPC 28−23−00−1A−245
12 Container cover 1 IPC 28−23−00−1A−235
13 Gasket 1 IPC 28−23−00−1A−250
15 Uniseal bolt 12 IPC 28−23−00−1A−270

Master
EFFECTIVITY: See Pageblock 28−23−03 page 401
28−23−03 Page 410
Dec 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL

REF NAME OF PART QTY IPC SEQUENCE NO.

16 Preformed packing 1 IPC 28−23−00−1A−272
17 Nut 2 IPC 28−23−00−1A−225
18 Washer 2 IPC 28−23−00−1A−220
19 Uniseal bolt 2 IPC 28−23−00−1A−215
20 Drain valve housing 1 IPC 28−23−00−1A−210
21 Gasket 1 IPC 28−23−00−1A−282
22 Plate 1 IPC 28−23−00−1A−288
23 Uniseal Bolt 7 IPC 28−23−00−1A−289

**ON A/C ALL

Subtask 28−23−03−946−002
E. Reference Information
REFERENCE DESIGNATION
TASK 12−00−07−861−801 Connect External AC Power
TASK 12−00−07−861−802 Remove External AC Power
TASK 12−11−28−650−801 Automatic Pressure Refueling
TASK 28−11−01−400−801 Installation of the Honeycomb Access Panel
TASK 28−11−01−400−802 Installation of the Aluminum Access Panel
TASK 28−23−01−400−801 Installation of the Electric Boost Pump
TASK 53−83−01−400−801 Installation of the MLG Wheel Bin
WM 20−12−00 Wiring − Installation
WM 20−17−10 Wiring Manual

2. Procedure
Subtask 28−23−03−869−001
A. Make sure that the aircraft is in the same configuration as in the removal task.

**ON A/C 7003−7031, 7033−7058, 7060, 7062, 7064−7067, 7069−7093, 7095−7102, 7104−7109,
7111−7124, 7126−7132, 7134−7141, 7143−7147, 7149−7165, 7168−7169, 7171−7204,
7206−7271, 7273−7277, 7279−7345, 7347−7364, 7366−7370, 7372−7383, 7385−7395,
7397−7399 Pre SB601R−28−048

Subtask 28−23−03−420−001
Refer to Figure 401.
B. Install the boost pump canister as follows:
(1) Apply sealing compound as follows:
(a) Turn the container assembly (14) upside down.
(b) Put the gasket (22) in position on the outside of the container assembly (14).

Master
EFFECTIVITY: See Pageblock 28−23−03 page 401
28−23−03 Page 411
Mar 15/2005
 C
AIRCRAFT MAINTENANCE MANUAL
(c) Apply a 0.25 inch (6−7 mm) bead of sealing compound externally to the base
of the container assembly (14). Make sure the sealing compound surrounds
the gasket (22), but does not touch the gasket.
NOTE: A clearance of approximately 0.25 inch (6−7 mm) should be allowed
between the gasket and the sealing compound.
(d) Remove the gasket (22) from the container assembly (14).
(2) Put the gasket (22) in position on the lower wing skin. Make sure that the holes in
the gasket (22) align with the holes in the wing skin.
(3) Put the gasket (21) in position on the lower wing skin. Make sure that the holes in
the gasket (21) align with the holes in the wing skin.
(4) Carefully put the container assembly (14) above the lower wing skin. Make sure
that the bolt holes in the container assembly (14) align with the holes in the gaskets
(21) and (22) and in the wing skin. Lower the container assembly (14) onto the
lower wing skin.
(5) Put the drain valve housing (20) inside the container assembly (14), directly above
the gasket (21).
(6) Lubricate the seal on the two uniseal bolts (19) with petrolatum.
(7) Put the uniseal bolts (19) through the lower wing skin, the gasket (21), the container
assembly (14), and the drain valve housing (20). Make sure that the heads of the
uniseal bolts are adjacent to the lower wing skin.
(8) Install the washers (18) and the nuts (17) on the uniseal bolts (19). Torque the nuts
(17) from 30−40 lbf·in (3.39−4.52 N·m).
(9) Apply a layer of sealing compound with a brush on the uniseal bolts (19) and nuts
(17).
NOTE: Apply sealant (09−013) on the nut side only (Ref. SRM 51−23−00).
(10) Lubricate the preformed packing (16) with petrolatum and install it into the groove in
the base of the boost pump canister (2).
(11) Apply a layer of sealing compound with a brush on the dome nuts that are installed
on the lower flange of the boost pump canister (2).
(12) Put the boost pump canister (2) in position inside the container assembly (14).
Make sure that the pressure port on the boost pump canister (2) is adjacent to the
pressure pickup line (6) and the captive nuts align with the two holes in the gasket
(22) and the lower wing skin.
(13) Lubricate the seal on the uniseal bolts (15) with petrolatum.
(14) Install the uniseal bolts (15) through the lower wing skin and the gasket (22) into the
boost pump canister (2) captive nuts. Torque the uniseal bolts (15) from 30 to 40
lbf·in (3.39 to 4.52 N·m).
NOTE: These uniseal bolts can be turned to tighten.
(15) Apply a brushcoat of sealant (09−034) to the nutplates of the the uniseal bolts (15).
(16) Put the gasket (13) in position on the container assembly (14).
(17) Install the container cover (12) with the bolts (10) and the washers (11).
(18) Lubricate the preformed packing (8) with petrolatum, then put the preformed
packing on the reducer (7).

Master
EFFECTIVITY: See Pageblock 28−23−03 page 401
28−23−03 Page 412
Aug 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
(19) Install the reducer (7) in the boost pump canister (2).
(20) Connect the pressure pickup line (6) to the reducer (7).
(21) Torque the nut on the pressure pickup line (6) from 70 to 120 lbf·in (7.90 to 13.55
N·m).
(22) Connect the pump discharge tube assembly (5) to the boost pump canister (2).
(23) Torque the nut on the pump discharge tube assembly (5) from 900 to 1100 lbf·in
(101.7 to 124.3 N·m).
(24) Connect the collector tank tube assembly to the container inlet (9).
(25) Lubricate the preformed packing (4) with petrolatum, then put the preformed
packing on the drain valve (3).
(26) Put the drain valve (3) through the lower wing skin and install it in the drain valve
housing (20).

**ON A/C 7032, 7059, 7061, 7063, 7094, 7103, 7110, 7125, 7133, 7142, 7148, 7166−7167, 7170,
7205, 7272, 7278, 7346, 7365, 7371, 7384, 7396, 7400−7939 and ON A/C 7003−7031,
7033−7058, 7060, 7062, 7064−7067, 7069−7093, 7095−7102, 7104−7109, 7111−7124,
7126−7132, 7134−7141, 7143−7147, 7149−7165, 7168−7169, 7171−7204, 7206−7271,
7273−7277, 7279−7345, 7347−7364, 7366−7370, 7372−7383, 7385−7395, 7397−7399 Post
SB601R−28−048

Subtask 28−23−03−420−002
Refer to Figure 401.
C. Install the boost pump canister as follows:
(1) Put the gasket (22) in position on the lower wing skin. Make sure that the holes in
the gasket (22) align with the holes in the wing skin.
(2) Put the gasket (21) in position on the lower wing skin. Make sure that the holes in
the gasket (21) align with the holes in the wing skin.
(3) Carefully put the container assembly (14) above the lower wing skin. Make sure
that the bolt holes in the container assembly (14) align with the holes in the gaskets
(21) and (22) and in the wing skin. Lower the container assembly (14) onto the
lower wing skin.
(4) Apply sealant (09−013) on the mating surface between the drain valve housing (20)
and the container assembly (14).
(5) Put the drain valve housing (20) inside the container assembly (14), directly above
the gasket (21).
(6) Lubricate the seal on the two uniseal bolts (19) with petrolatum.
(7) Put the uniseal bolts (19) through the lower wing skin, the gasket (21), the container
assembly (14), and the drain valve housing (20). Make sure that the heads of the
uniseal bolts are adjacent to the lower wing skin.
(8) Install the two washers (18) and the two nuts (17) on the uniseal bolts (19). Torque
the nuts (17) from 20 to 25 lbf·in (2.26 to 2.82 N·m).
(9) Apply a layer of sealing compound with a brush on the uniseal bolts (19) and nuts
(17).
NOTE: Apply sealant (09−013) on the nut side only (Ref. SRM 51−23−00).

Master
EFFECTIVITY: See Pageblock 28−23−03 page 401
28−23−03 Page 413
Aug 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
(10) Lubricate the preformed packing (16) with petrolatum and install it into the groove in
the base of the boost pump canister (2).
(11) Apply a layer of sealing compound with a brush on the dome nuts that are installed
on the lower flange of the boost pump canister (2).
(12) Put the boost pump canister (2) in position inside the container assembly (14).
Make sure that the pressure port on the boost pump canister (2) is adjacent to the
pressure pickup line (6).
(13) Lubricate the seal on the uniseal bolts (15) with petrolatum.
(14) Install the uniseal bolts (15) through the lower wing skin and the gasket (22) into the
boost pump canister (2) captive nuts. Torque the uniseal bolts (15) from 50 to 70
lbf·in (5.65 to 7.91 N·m).
NOTE: These uniseal bolts can be turned to tighten.
(15) Apply a brushcoat of sealant (09−034) to the nutplates of the the uniseal bolts (15).
(16) Put the gasket (13) in position on the container assembly (14).
(17) Install the container cover (12) with the bolts (10) and the washers (11).
(18) Torque the bolts (10) from 20 to 25 lbf·in (2.26 to 2.82 N·m)
(19) Lubricate the preformed packing (8) with petrolatum.
(20) Put the preformed packing (8) on the reducer (7).
(21) Install the reducer (7) in the boost pump canister (2).
(22) Connect the pressure pickup line (6) to the reducer (7).
(23) Torque the nut on the pressure pickup line (6) from 70 to 120 lbf·in (7.90 to 13.55
N·m).
(24) Connect the pump discharge tube assembly (5) to the boost pump canister (2).
(25) Torque the nut on the pump discharge tube assembly (5) to 900−1100 lbf·in
(101.7−124.3 N·m).
(26) Connect the collector tank tube assembly to the container inlet (9).
(27) Lubricate the preformed packing (4) with petrolatum, then put the preformed
packing on the drain valve (3).
(28) Put the drain valve (3) through the lower wing skin and install it in the drain valve
housing (20).

**ON A/C 7003−7067, 7069−7939 Post SB601R−57−032

Subtask 28−23−03−420−003
Refer to Figure 402
D. Install the boost pump canister as follows:
(1) Carefully put the gasket (25) and the container assembly (14) in position on the
lower wing plank.
(2) Make sure that the holes in the gasket (25) align with the holes in the wing plank.
(3) Make sure that the holes in the container assembly (14) align with the holes in the
gasket (25) and the wing plank.

Master
EFFECTIVITY: See Pageblock 28−23−03 page 401
28−23−03 Page 414
Aug 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
(4) Lubricate the seal on the uniseal bolts (23) with petrolatum.
(5) Install the uniseal bolts (23) through the lower wing skin and the gasket (25) into the
container assembly (14).
NOTE: Do not tighten the uniseal bolts (23).
(6) Apply sealant (09−013) to the mating surface between the drain valve housing (20)
and the container assembly (14).
(7) Put the drain valve housing (20) inside the container assembly (14).
(8) Lubricate the seal on the uniseal bolts (19) with petrolatum.
(9) Put the uniseal bolts (19) through the lower wing skin, the container assembly (14),
and the drain valve housing (20). Make sure that the heads of the uniseal bolts are
adjacent to the lower wing skin.
(10) Install the washers (18) and the nuts (17) on the uniseal bolts (19).
(11) Torque the nuts (17) from 20 to 25 lbf·in (2.26 to 2.82 N·m).
(12) Make sure that the heads of the uniseal bolts (17) are flush or below the surface of
the lower wing plank.
(13) Apply a layer of sealing compound with a brush on the nuts (17).
(14) Torque the uniseal bolts (23) from 50 to 60 lbf·in (5.65 to 6.78 N·m).
(15) Make sure that the heads of the uniseal bolts (23) are flush or below the surface of
the lower wing plank.
(16) Lubricate the preformed packing (16) with petrolatum and install it into the groove in
the base of the boost pump canister (2).
(17) Apply a layer of sealing compound with a brush on the dome nuts that are installed
on the lower flange of the boost pump canister (2).
(18) Put the boost pump canister (2) in position inside the container assembly (14).
Make sure that the pressure port on the boost pump canister (2) is adjacent to the
pressure pickup line (6).
(19) With a roller, apply sealant (09−013) on the mating surfaces of the plate assembly
(24) and the container (14).
NOTE: Make sure that you do not put sealant on the mating surface of the plate
assembly (24) and the wing plank.
(20) Put the plate assembly (24) on the lower surface of the wing plank.
(21) Lubricate the seal on the uniseal bolts (15) with petrolatum.
(22) Install the uniseal bolts (15) through the lower wing skin and the gasket (25) into the
boost pump canister (2) captive nuts.
(23) Torque the uniseal bolts (15) from 50 to 60 lbf·in (5.65 to 6.78 N·m).
(24) Make sure the heads of the uniseal bolts (15) are flush or below the surface of the
surface of the plate assembly.
(25) Apply a brushcoat of sealant (09−034) to the nutplates of the the uniseal bolts (15).
(26) Put the gasket (13) in position on the container assembly (14).
(27) Install the container cover (12) with the bolts (10) and the washers (11).
(28) Torque the bolts (10) from 20 to 25 lbf·in (2.26 to 2.82 N·m)

Master
EFFECTIVITY: See Pageblock 28−23−03 page 401
28−23−03 Page 415
Aug 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
(29) Lubricate the preformed packing (8) with petrolatum.
(30) Put the preformed packing (8) on the reducer (7).
(31) Install the reducer (7) in the boost pump canister (2).
(32) Connect the pressure pickup line (6) to the reducer (7).
(33) Torque the nut on the pressure pickup line (6) from 70 to 120 lbf·in (7.90 to 13.55
N·m).
(34) Connect the pump discharge tube assembly (5) to the boost pump canister (2).
(35) Torque the nut on the pump discharge tube assembly (5) from 900 to 1100 lbf·in
(101.7 to 124.3 N·m).
(36) Connect the collector tank tube assembly to the container inlet (9).
(37) Lubricate the preformed packing (4) with petrolatum, then put the preformed
packing on the drain valve (3).
(38) Put the drain valve (3) through the lower wing skin and install it in the drain valve
housing (20).
(39) Apply a 0.25 inch (6−7 mm) bead of sealing compound externally to the base of the
container assembly (14) and the lower wing skin.

**ON A/C 7940−7990, 8000−8064, 8066−8068

Subtask 28−23−03−420−004
Refer to Figure 403
E. Install the boost pump canister as follows:
(1) Put the drain valve housing (20) into the container assembly (14).
(2) Lubricate the seal on the uniseal bolts (19) with petrolatum.
(3) Install the uniseal bolts (19), through the plate assembly (22) the container
assembly (14), and into the drain valve housing (20).
(4) Install the washers (18) and the nuts (17) on the uniseal bolts (19).
(5) Torque the nuts (17) from 25 to 30 lbf·in (2.82 to 3.39N·m).
(6) Apply a layer of sealing compound with a brush on the nuts (17).
(7) Lubricate the preformed packing (16) with petrolatum and install it into the groove in
the base of the boost pump canister (2).
(8) Apply a layer of sealing compound with a brush on the dome nuts that are installed
on the lower flange of the boost pump canister (2).
(9) Put the boost pump canister (2) in position inside the container assembly (14).
Make sure that the pressure port on the boost pump canister (2) is adjacent to the
pressure pickup line (6).
(10) Lubricate the seal on the uniseal bolts (15) with petrolatum.
(11) Install the uniseal bolts (15) through the plate assembly (22) into the boost pump
canister (2) captive nuts.
(12) Torque the uniseal bolts (15) from 50 to 70 lbf·in (5.65 to 7.91 N·m).
(13) Apply a layer of sealing compound with a brush on the uniseal bolts (15).

Master
EFFECTIVITY: See Pageblock 28−23−03 page 401
28−23−03 Page 416
Dec 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
(14) Put the gasket (21) in position on the lower wing skin. Make sure that the holes in
the gasket (21) align with the holes in the lower wing skin.
(15) Carefully put the plate assembly (22) above the lower wing skin. Make sure that the
bolt holes in the container assembly (22) align with the holes in the gasket (21) and
the lower wing skin. Lower the plate assembly (22) onto the lower wing skin.
(16) Apply a layer of sealing compound with a brush on the dome nuts that are installed
on the container assembly (14).
(17) Lubricate the seal on the uniseal bolts (23) with petrolatum.
(18) Install the uniseal bolts (23) through the lower wing skin and the gasket (21) into the
container assembly (14) captive nuts.
(19) Torque the uniseal bolts (23) from 50 to 70 lbf·in (5.65 to 7.91 N·m).
NOTE: These uniseal bolts can be turned to tighten.
(20) Apply a brushcoat of sealant (09−034) to the nutplates of the the uniseal bolts (15).
(21) Put the gasket (13) in position on the container assembly (14).
(22) Install the container cover (12) with the bolts (10) and the washers (11).
(23) Torque the bolts (10) from 20 to 25 lbf·in (2.26 to 2.82 N·m).
(24) Lubricate the preformed packing (8) with petrolatum.
(25) Install the reducer (7) in the boost pump canister (2).
(26) Connect the pressure pickup line (6) to the reducer (7).
(27) Torque the nut on the pressure pickup line (6) from 70 to 120 lbf·in (7.90 to 13.55
N·m).
(28) Connect the pump discharge tube assembly (5) to the boost pump canister (2).
(29) Torque the nut on the pump discharge tube assembly (5) from 900 to 1100 lbf·in
(101.7 to 124.3 N·m).
(30) Connect the collector tank tube assembly to the container inlet (9).
(31) Lubricate the preformed packing (4) with petrolatum, then put the preformed
packing on the drain valve (3).
(32) Put the drain valve (3) through the lower wing skin and install it in the drain valve
housing (20).
(33) Apply a 0.25 inch (6−7 mm) bead of sealing compound externally to the base of the
container assembly (14). Make sure the sealing compound surrounds the plate
assembly (22) and the gasket (21).

**ON A/C ALL

Subtask 28−23−03−430−001
F. Install the wires in the electrical conduit as follows:
(1) Install the wires in the electrical conduit (1) (Ref. WM 20−12−00).
(2) Connect the electrical conduit (1) to the boost pump canister (2).
G. Connect the electrical connections (Ref. WM 20−17−10).

Master
EFFECTIVITY: See Pageblock 28−23−03 page 401
28−23−03 Page 417
Aug 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
3. Close Out
Subtask 28−23−03−410−004
A. Install the electric fuel boost pump (Ref.TASK 28−23−01−400−801).

Subtask 28−23−03−865−003
B. Remove the tags and close the circuit breakers that follow:
CB PANEL CB NO. NAME ZONE
CBP−1 M6 L FUEL PUMP 221
CBP−1 M7 L FUEL PUMP CONT 221
CBP−1 M12 FUEL SYST CONT 221
CBP−2 G10 R FUEL PUMP 222
CBP−2 G11 R FUEL PUMP CONT 222
CBP−4 B10 FUEL SYST CONT 222

Subtask 28−23−03−210−003
C. Do the operational integrity visual leak check of the boost pump canister as follows:
(1) Connect external AC power to the aircraft (Ref.TASK 12−00−07−861−801).
(2) Fill the left main fuel tank and the right main fuel tanks (Ref.TASK
12−11−28−650−801).
CAUTION: MAKE SURE THAT THERE IS A MINIMUM OF 200 POUNDS (90KG) OF
FUEL IN BOTH MAIN TANKS BEFORE YOU OPERATE THE ELECTRIC
BOOST PUMPS. WHEN YOU SELECT EITHER THE L OR R BOOST
PUMP SWITCH/LIGHT, BOTH PUMPS WILL OPERATE. IF YOU DO
NOT DO THIS, YOU WILL DAMAGE THE EQUIPMENT.
(3) Make sure that both engine power levers are in the cut−off position.
(4) If the left boost pump canister was replaced, on the FUEL control panel, push in the
L BOOST PUMP switch/light. Make sure that the ON light goes on and that the
INOP light does not come on.
(5) If the right boost pump canister was replaced, on the FUEL control panel, push in
the R BOOST PUMP switch/light. Make sure that the ON light goes on and the
INOP light does not come on.
(6) After 15 minutes, push out the selected BOOST PUMP switch/light.
(7) Remove external AC power from the aircraft (Ref.TASK 12−00−07−861−802).
(8) Do a visual inspection for any fuel leaks at the boost pump canister.

Subtask 28−23−03−280−001
D. Do the electrical connection installation integrity test as follows:
(1) Remove the boost pump cartridge from the fuel boost pump canister (Ref.TASK
28−23−01−000−801).
(2) Inspect the canister electrical connector and make sure that there is no fuel
leakage.

Master
EFFECTIVITY: See Pageblock 28−23−03 page 401
28−23−03 Page 418
Mar 15/2005
 C
AIRCRAFT MAINTENANCE MANUAL
(3) Fill the center fuel tank to maximum capacity (Ref.TASK 12−11−28−650−801).
(4) Monitor the boost pump canister installation and the electrical receptacle for fuel
leakage/seepage for a minimum of six hours.
NOTE: If leakage/seepage is observed at the electrical connector, replace the
canister.

Subtask 28−23−03−410−001
E. If the left boost pump canister was replaced, install the access panel that follows (Ref.
TASK 28−11−01−400−801).
ACCESS DESCRIPTION
510AB Fuel tank access panel
F. For the left boost pump canister, install the left wheel bin in the main wheel well
(Ref.TASK 53−83−01−400−801).
G. If the right boost pump canister was replaced, install the access panel that follows (Ref.
TASK 28−11−01−400−802).
ACCESS DESCRIPTION
610AB Fuel tank access panel
H. For the right boost pump canister, install the right wheel bin in the main wheel well
(Ref.TASK 53−83−01−400−801).

Subtask 28−23−03−941−001
I. Remove all the tools, equipment, and unwanted materials from the work area.

Master
EFFECTIVITY: See Pageblock 28−23−03 page 401
28−23−03 Page 419
Mar 15/2005
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C ALL
SWITCH/LIGHT, BOOST PUMP − REMOVAL/INSTALLATION

1. General
A. The maintenance procedures that follow are for the removal and installation of the left
and right boost pump switch/lights. There are two boost pump switch/lights. They are
installed on the FUEL control panel, on the overhead panel in the flight compartment.
The switch/lights removed and installed in this procedure are as follows:
± R BOOST PUMP switch/light
± L BOOST PUMP switch/light.

TASK 28−23−04−000−801
Removal of the Boost Pump Switch/Light

1. Job Set−Up Information

Subtask 28−23−04−946−001
A. Reference Information
REFERENCE DESIGNATION
TASK 24−00−00−910−801 Electrical/Electronic Safety Precautions

2. Job Set−Up
Subtask 28−23−04−910−001
A. Obey all of the electrical and electronic safety precautions (Ref. TASK
24−00−00−910−801).

Subtask 28−23−04−865−001
B. Open, safety, and tag the circuit breakers that follow:
CB PANEL CB NO. NAME ZONE
CBP−1 H5 EICAS LDU L 221
CBP−1 M6 L FUEL PUMP 221
CBP−1 M7 L FUEL PUMP CONT 221
CBP−1 M8 XFLOW SOV 221
CBP−1 M12 FUEL SYST CONT 221
CBP−1 N11 XFER/APU CONT 221
CBP−2 G10 R FUEL PUMP 222
CBP−2 G11 R FUEL PUMP CONT 222
CBP−2 Q9 EICAS LDU R 222
CBP−4 B10 FUEL SYST CONT 222

Master
EFFECTIVITY: See Pageblock 28−23−04 page 401
28−23−04 Page 401
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
3. Procedure
Subtask 28−23−04−020−001
Refer to Figure 401.
A. Remove the boost pump switch/light as follows:
(1) Release the DZUS captive fasteners (4) and carefully pull the fuel control panel (5)
out of the overhead panel.
(2) Disconnect the two electrical connectors (6) from the fuel control panel (5).
(3) Put protective covers on both of the electrical connectors.
(4) Remove the four screws (1) and four rubber washers (2) from the fuel control
panel (5).
(5) Carefully remove the plastic integral lighting panel (3) from the fuel control
panel (5).
(6) Carefully remove the left and right boost pump switch/light lens cap assembly (7).
Retain the lens/cap assembly for later re−installation.
(7) Locate the switch light mounting screw, installed in the base of the switch/light
module (7).
(8) Turn the mounting screw (10) approximately half a turn clockwise to unlock the
mounting CAM (11).
(9) Pull the switch/light module (7) out of the mounting sleeve (12). Retain the rubber
gasket (9) for later reuse.

Master
EFFECTIVITY: See Pageblock 28−23−04 page 401
28−23−04 Page 402
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

A
B

L BOOST GRAVITY R BOOST

PUMP XFLOW PUMP

ON FAIL ON
F INOP OPEN INOP
U
E XFLOW
L AUTO OVERRIDE R
L
ON ON
MAN
FAIL FAIL

LEGEND
A
1. Screw nuts.
2. Rubber washer.
3. Plastic integral lighting panel.
4. Captive fastener.
5. Fuel control panel. OVERHEAD
6. Electrical connector. 6 CONSOLE (REF)
7. Switch/light module.
8. Switch/light. 9
9. Rubber gasket.
10. Mounting screw.
11. Mounting cam.
12. Switch cap. 8
7

B TYPICAL 4
11
10
5
ram2813314_001(1).dc, pb/ks, 20/06/95

12

1 2 3

Boost Pump Switch/Light − Removal/Installation

Figure 401

Master
EFFECTIVITY: See Pageblock 28−23−04 page 401
28−23−04 Page 403
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
TASK 28−23−04−400−801
Installation of the Boost Pump Switch/Light

1. Job Set−Up Information

Subtask 28−23−04−945−001
A. Parts
REF NAME OF PART QTY IPC SEQUENCE NO.
1 Screw 4 IPC 28−25−16−1A−010
2 Washer, rubber 4 IPC 28−25−16−1A−015

Subtask 28−23−04−946−002
B. Reference Information
REFERENCE DESIGNATION
TASK 31−52−00−710−801 Operational Test of the Warning Lights System
TASK 28−23−01−710−801 Operational Test of the Electrical Boost Pump

2. Procedure
Subtask 28−23−04−869−001
A. Make sure that the aircraft is in the same configuration as in the removal task.

Subtask 28−23−04−420−001
Refer to Figure 401.
B. Install the boost pump switch/light as follows:
(1) Re−install the rubber gasket (9).
(2) Install the switch/light module (7) in the mounting sleeve.
(3) Turn the mounting screw (10) approximately half a turn counter−clockwise to lock
the mounting CAM (11).
(4) Locate the switch light mounting screw, installed in the base of the switch/light
module (7).
(5) Carefully install the left and right boost pump switch/light lens cap assembly (7).
(6) Carefully install the plastic integral lighting panel (3) on the fuel control panel (5).
(7) Install the four screws (1) and four rubber washers (2) to the fuel control panel (5).
(8) Remove the protective covers on all of the electrical connectors.
(9) Connect the two electrical connectors (6) to the fuel control panel (5).
(10) Fasten the DZUS captive fasteners (4) and carefully install the fuel control panel (5)
in the to middle compartment of the overhead panel.

Master
EFFECTIVITY: See Pageblock 28−23−04 page 401
28−23−04 Page 404
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
3. Close Out
Subtask 28−23−04−865−002
A. Remove the tags and close the circuit breakers that follow:
CB PANEL CB NO. NAME ZONE
CBP−1 H5 EICAS LDU L 221
CBP−1 M6 L FUEL PUMP 221
CBP−1 M7 L FUEL PUMP CONT 221
CBP−1 M8 XFLOW SOV 221
CBP−1 M12 FUEL SYST CONT 221
CBP−1 N11 XFER/APU CONT 221
CBP−2 G10 R FUEL PUMP 222
CBP−2 G11 R FUEL PUMP CONT 222
CBP−2 Q9 EICAS LDU R 222
CBP−4 B10 FUEL SYST CONT 222

Subtask 28−23−04−710−001
B. Do a lamp test of the FUEL control panel (Ref. TASK 31−52−00−710−801).

Subtask 28−23−04−710−002
C. Do an operational test of the left and right Electrical Boost Pump (Ref. TASK
28−23−01−710−801).

Master
EFFECTIVITY: See Pageblock 28−23−04 page 401
28−23−04 Page 405
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C ALL
CHECK VALVE, STANDBY FUEL−FEED LINE − REMOVAL/INSTALLATION

1. General
A. The maintenance procedures that follow are for the removal and installation of the
standby−fuel−feed−line check valve (written as the "check valve" in this procedure).
There are two check valves in the fuel system. They are found in the center wing box
and are connected to the standby fuel−feed manifolds, downstream of the electric boost
pumps.
B. It is necessary to defuel, drain and remove the fuel fumes from the center tank and the
applicable main tank to remove or install the check valve.

TASK 28−23−07−000−801
Removal of the Standby−Fuel−Feed−Line Check Valve

1. Job Set−Up Information

Subtask 28−23−07−946−001
A. Reference Information
REFERENCE DESIGNATION
TASK 12−11−28−650−804 Suction Defueling
TASK 20−30−00−910−802 Wiggins Couplings − Maintenance Practices
TASK 28−00−00−910−801 Fuel Safety Precautions
TASK 28−11−00−840−801 Prepare Fuel Tank for Access
TASK 28−11−00−840−802 Removal of Fuel Fumes
TASK 28−11−01−000−801 Removal of the Honeycomb Access Panel
TASK 28−11−01−000−802 Removal of the Aluminum Access Panel

2. Job Set−Up
Subtask 28−23−07−910−001
WARNING: OBEY ALL THE FUEL SAFETY PRECAUTIONS WHEN YOU DO WORK ON THE
FUEL SYSTEM AND/OR A FUEL SYSTEM COMPONENT. IF YOU DO NOT DO
THIS, YOU CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO
EQUIPMENT.
A. Obey all the fuel safety precautions (Ref. TASK 28−00−00−910−801).

Subtask 28−23−07−650−001
B. Defuel the center tank and the applicable main tank (Ref. TASK 12−11−28−650−804).

Master
EFFECTIVITY: See Pageblock 28−23−07 page 401
28−23−07 Page 401
Sep 10/2004
 C
AIRCRAFT MAINTENANCE MANUAL
Subtask 28−23−07−010−001
C. To remove the left check valve, remove the honeycomb access panel that follows (Ref.
TASK 28−11−01−000−801):
ACCESS DESCRIPTION
510AB Fuel−tank access panel
D. To remove the right check valve, remove the aluminum access panel that follows (Ref.
TASK 28−11−01−000−802):
ACCESS DESCRIPTION
610AB Fuel tank access panel

Subtask 28−23−07−840−001
E. Prepare the center tank and applicable tank for access (Ref. TASK
28−11−00−840−801).
F. Remove the fuel fumes from the center tank and the applicable main tank (Ref. TASK
28−11−00−840−802).

3. Procedure
Subtask 28−23−07−020−001
Refer to Figure 401.
NOTE: For the procedures for the removal and installation of Wiggins couplings, refer to
Wiggins Couplings − Maintenance Practices (Ref. TASK 20−30−00−910−802).
A. If it is necessary to remove the tube assembly (1) from the aircraft, remove the check
valve (2) as follows:
(1) Disconnect the auxiliary−power−unit (APU) fuel−feed line (3) from the
union/reducer (4). Install a protective plug on the line (3).
NOTE: The line (3) and union/reducer (4) are available only on the right tube
assembly (1).
(2) Remove the coupling (5) and move the sleeve (6) away from the two ferrules (7).
(3) Remove the coupling (8) and move the sleeve (9) away from the two ferrules (10).
(4) Remove the coupling (11) and move the sleeve (12) away from the two the ferrules
(13).
(5) Remove the screw (14) and washer (15), and remove the tube assembly (1) from
the aircraft. Keep the clamp (16) on the tube assembly (1).
(6) Remove and discard the six preformed packings (17), (18) and (19) from the related
ferrules (7), (10) and (13).
(7) Install a protective cap on the engine fuel−feed manifold (20), the fuel manifold (21)
and standby fuel−feed manifold (22).
(8) Remove the retainer wire (23) and the check valve (2) from the ferrule (13) of the
tube assembly (1).

Master
EFFECTIVITY: See Pageblock 28−23−07 page 401
28−23−07 Page 402
Sep 10/2004
 C
AIRCRAFT MAINTENANCE MANUAL
(9) Remove and discard the preformed packing (24) from the check valve (2).
B. If it is not necessary to remove the tube assembly (1), remove the check valve (2) as
follows:
(1) Remove the coupling (11) and move the sleeve (12) away from the two ferrules
(13).
(2) Loosen the screw (14) to loosen the tube assembly (1).
(3) Lightly disconnect the two ferrules (13) to gain access to the check valve (2).
(4) Remove the retainer wire (23) and remove the check valve (2) from the ferrule (13)
of the tube assembly (1).
(5) Remove and discard the preformed packing (24) from the check valve (2).
(6) Remove and discard the two preformed packings (19) from the two ferrules (13).
(7) Install a protective cap on the fuel manifold (21) and tube assembly (1).

Master
EFFECTIVITY: See Pageblock 28−23−07 page 401
28−23−07 Page 403
Sep 10/2004
 C
AIRCRAFT MAINTENANCE MANUAL

LEGEND
1. Tube assembly. 10. Ferrule. 19. Preformed packing.
2. Check valve. 11. Coupling. 20. Engine fuel−feed manifold.
3. APU fuel−feed line. 12. Sleeve. 21. Fuel manifold.
4. Union/reducer. 13. Ferrule. 22. Standby fuel−feed manifold.
5. Coupling. 14. Screw. 23. Retainer wire.
6. Sleeve. 15. Washer. 24. Preformed packing.
7. Ferrule. 16. Clamp.
8. Coupling. 17. Preformed packing.
9. Sleeve. 18. Preformed packing.

TO ENGINE
FEED
(REF) FLAPPERS
20 24 B
A
7
PREFORMED
17 PACKING
(TYPICAL SIX
6 PLACES)

5
2
17

10 22
7 8 18
9 FERRULE
23 18
10 24 (TYPICAL SIX
FROM PLACES)
2
ELECTRIC
BOOST PUMP
(REF)

13 19 12 11
13
19
1 21
FROM
ram2823074_001.dg, rs/gw, 12/06/97

PRIMARY
15 16
14 4 EJECTOR
PUMP
3 (REF)
A
TO APU
NOTE FEED
Right side only shown. (REF)

Standby−Fuel−Feed−Line Check Valve − Removal/Installation

Figure 401 (Sheet 1 of 2)

Master
EFFECTIVITY: See Pageblock 28−23−07 page 401
28−23−07 Page 404
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

LEGEND
1. Tube assembly. 11. Coupling. 19. Preformed packing.
2. Check valve. 12. Sleeve. 20. Engine fuel−feed manifold.
5. Coupling. 13. Ferrule. 21. Fuel manifold.
6. Sleeve. 14. Screw. 22. Standby fuel−feed manifold.
7. Ferrule. 15. Washer. 23. Retainer wire.
8. Coupling. 16. Clamp. 24. Preformed packing.
9. Sleeve. 17. Preformed packing.
10. Ferrule. 18. Preformed packing.

TO ENGINE
FEED
(REF)
20
7

17

17

10 22
7 8 18
9
23 18
10 24
FROM
2
ELECTRIC
BOOST PUMP
(REF)

13 19 12 11
13
19
1 21
FROM
PRIMARY
15 16
14 EJECTOR
ram2823074_002.dg, rs/kms, 17/01/01

PUMP
(REF)

B
NOTE
Left side only shown.

Standby−Fuel−Feed−Line Check Valve − Removal/Installation

Figure 401 (Sheet 2 of 2)

Master
EFFECTIVITY: See Pageblock 28−23−07 page 401
28−23−07 Page 405
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
TASK 28−23−07−400−801
Installation of the Standby−Fuel−Feed−Line Check Valve

1. Job Set−Up Information

Subtask 28−23−07−944−001
A. Consumable Materials
REFERENCE DESIGNATION
06−002 Petrolatum

Subtask 28−23−07−945−001
B. Parts
REF NAME OF PART QTY IPC SEQUENCE NO.
2 Check valve 1 IPC 28−23−00−1A−075
14 Screw 1 IPC 28−21−00−1A−045
15 Washer 1 IPC 28−21−00−1A−050
17 Preformed packing 2 TBD
18 Preformed packing 2 IPC 28−13−00−1A−025
19 Preformed packing 2 IPC 28−23−00−1A−070
24 Preformed packing 1 Manufacturer supplied

Subtask 28−23−07−946−002
C. Reference Information
REFERENCE DESIGNATION
TASK 20−30−00−910−802 Wiggins Couplings − Maintenance Practices
TASK 28−11−01−400−801 Installation of the Honeycomb Access Panel
TASK 28−11−01−400−802 Installation of the Aluminum Access Panel
TASK 28−23−07−710−801 Operational Test of the Standby−Fuel−Feed
Check Valve

2. Procedure
Subtask 28−23−07−869−001
A. Make sure that the aircraft is in the same configuration as in the removal task.

Subtask 28−23−07−420−001
Refer to Figure 401.
NOTE: For the procedures for the removal and installation of Wiggins couplings, refer to
Wiggins Couplings − Maintenance Practices (Ref. TASK 20−30−00−910−802).

Master
EFFECTIVITY: See Pageblock 28−23−07 page 401
28−23−07 Page 406
Sep 10/2004
 C
AIRCRAFT MAINTENANCE MANUAL
B. If the tube assembly (1) was removed, Install the check valve (2) as follows:
(1) Lubricate the preformed packing (24) with petrolatum and install on the check valve
(2).
(2) Install the check valve (2) in the ferrule (13) of the tube assembly (1) and lock in
position with the retainer wire (23).
NOTE: Make sure that the check valve (2) flappers open in the direction of the
arrow as shown on the ferrule (13).
(3) Remove the protective caps from the manifolds (20), (21) and (22). Lubricate with
petrolatum and install the six preformed packings (17), (18) and (19) in the grooves
of the related ferrules (7) (10) and (13).
(4) Hold the tube assembly (1) in position and install the washer (15) and the screw
(14) to the clamp (16). Do not tighten the screw (14) at this time.
(5) Move the sleeve (6) over the two preformed packings (17) of the two ferrules (7),
and lock with the coupling (5).
(6) Move the sleeve (9) over the two preformed packings (18) of the two ferrules (10),
and lock with the coupling (8).
(7) Move the sleeve (12) over the two preformed packings (19) of the two ferrules (13),
and lock with the coupling (11).
(8) Remove the protective plug and install the line (3) to the union/reducer (4).
NOTE: The line (2) and union/reducer (3) are available only on the right tube
assembly (1).
(9) Tighten the screw (14).
C. If the tube assembly (1) was not removed, install the check valve (2) as follows:
(1) Lubricate the preformed packing (24) with petrolatum and install on the check
valve (2).
(2) Install the check valve (2) in the ferrule (13) of the tube assembly (1) and lock the
check valve (2) in position with the retainer wire (23).
NOTE: Make sure that the check valve (2) flappers open in the direction of the
arrow as shown on the ferrule (13).
(3) Remove the protective cap from the manifold (21) and install the two preformed
packings (19) in the grooves of the two ferrules (13).
(4) Move the sleeve (12) over the two preformed packings (19) of the two ferrules (13),
and lock with the coupling (11).
(5) Tighten the screw (14).

3. Close Out
Subtask 28−23−07−410−001
A. If the left check valve was replaced, install the aluminum−honeycomb−core access panel
that follows (Ref. TASK 28−11−01−400−801):

Master
EFFECTIVITY: See Pageblock 28−23−07 page 401
28−23−07 Page 407
Sep 10/2004
 C
AIRCRAFT MAINTENANCE MANUAL

ACCESS DESCRIPTION
510AB Fuel−tank access panel
B. If the right check valve was replaced, install the aluminum access panel that follows
(Ref. TASK 28−11−01−400−802):
ACCESS DESCRIPTION
610AB Fuel tank access panel

Subtask 28−23−07−710−003
C. Do the operational test of the left or right check valve (2) (Ref. TASK
28−23−07−710−801).

Master
EFFECTIVITY: See Pageblock 28−23−07 page 401
28−23−07 Page 408
Sep 10/2004
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C ALL
CHECK VALVE, STANDBY FUEL FEED − ADJUSTMENT/TEST

1. General
A. The maintenance procedure that follows is for the test of the standby−fuel−feed check
valve (written as the "check valve" in this procedure). There are two check valves in the
standby−fuel feed system. They are installed in the center wing box.

TASK 28−23−07−710−801
Operational Test of the Standby−Fuel−Feed Check Valve

1. Job Set−Up Information

Subtask 28−23−07−943−002
A. Tools and Equipment
REFERENCE DESIGNATION
None specified Container, fuel

Subtask 28−23−07−946−003
B. Reference Information
REFERENCE DESIGNATION
TASK 12−00−07−861−801 Connect External AC Power
TASK 12−00−07−861−802 Remove External AC Power
TASK 12−11−28−650−801 Automatic Pressure Refueling
TASK 12−11−28−650−802 Manual Pressure Refueling
TASK 71−00−00−868−806 Engine Start
TASK 71−00−00−868−807 Engine Stop (Normal)

2. Job Set−Up
Subtask 28−23−07−650−004
A. Make sure that the aircraft has a minimum of 200 pounds (90.8 kg) of fuel. Refuel if
necessary (Ref.TASK 12−11−28−650−801 or TASK 12−11−28−650−802).

Subtask 28−23−07−861−001
B. Connect the external AC power to the aircraft (Ref. TASK 12−00−07−861−801).
C. Push the FUEL push−button on the engine indication and crew alerting system (EICAS)
control panel to get the FUEL synoptic display.

Master
EFFECTIVITY: See Pageblock 28−23−07 page 501
28−23−07 Page 501
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
3. Procedure
Subtask 28−23−07−710−004
A. If the right check valve was replaced, do a test as follows:
(1) Start the left engine (Ref. TASK 71−00−00−868−806).
(2) On the FUEL synoptic display, make sure that the left and right electric boost
pumps are not shown in green.
NOTE: Left and right boost pumps set to off.
(3) Wait for up to two minutes. Make sure that the caution message R LO FUEL
PRESS is shown in amber on the EICAS primary page.
NOTE: When the R LO FUEL PRESS message is not shown, the left
fuel−feed−line−check valve has possibly failed in the open position.
(4) When necessary, do an engine dry motor cycle (Ref. TASK 71−00−00−868−811) to
find if the left fuel−feed−line−check valve is serviceable.
NOTE: When the R LO FUEL PRESS caution does not show, the left
fuel−feed−line−check valve must be replaced.
(5) Do a shut down of the left engine (Ref. TASK 71−00−00−868−807).
(6) When necessary, replace the left fuel−feed−line−check valve (Ref. TASK
28−21−04−000−801 and TASK 28−21−04−400−801) and do this test again.

Subtask 28−23−07−710−005
B. If the left check valve was replaced, do a test as follows:
(1) Start the right engine (Ref. TASK 71−00−00−868−806).
(2) On the FUEL synoptic display, make sure that the left and right electric boost
pumps are not shown in green.
NOTE: Left and right boost pumps set to off.
(3) Wait for up to two minutes. Make sure that the caution message L LO FUEL
PRESS is shown in amber on the EICAS primary page.
NOTE: When the L LO FUEL PRESS message is not shown, the right
fuel−feed−line−check valve has possibly failed in the open position.
(4) When necessary, do an engine dry motor cycle (Ref. TASK 71−00−00−868−811) to
find if the right fuel−feed−line−check valve is serviceable.
NOTE: When the L LO FUEL PRESS caution does not show, the right
fuel−feed−line−check valve must be replaced.
(5) Do a shutdown of the right engine (Ref. TASK 71−00−00−868−807).
(6) When necessary, replace the right fuel−feed−line−check valve (Ref. TASK
28−21−04−000−801 and TASK 28−21−04−400−801) and do this test again.

Master
EFFECTIVITY: See Pageblock 28−23−07 page 501
28−23−07 Page 502
Jun 22/2004
 C
AIRCRAFT MAINTENANCE MANUAL
4. Close Out
Subtask 28−23−07−861−002
A. Remove the external AC power from the aircraft (Ref. TASK 12−00−07−861−802).

Subtask 28−23−07−941−001
B. Remove all tools, equipment, and unwanted materials from the work area.

Master
EFFECTIVITY: See Pageblock 28−23−07 page 501
28−23−07 Page 503
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C ALL
AUXILIARY POWER UNIT (APU) FUEL FEED SYSTEM − DESCRIPTION AND OPERATION

1. General
A. The auxiliary power unit (APU) fuel−feed system supplies fuel to the APU. The APU
fuel−feed system has the components that follow:
± One APU fuel pump
± One APU−feed−line check valve
± Two APU−pump inlet screens
± One APU negative−gravity−feed valve
± One APU−fuel−feed shutoff valve
± One APU fuel−line shroud.
2. Component Details
Refer to Figure 1.
A. APU Fuel Pump
(1) The APU fuel pump is an electrically−operated impeller−type pump that moves fuel
through the APU feed/crossflow manifold. It is on the right side of the aft bulkhead
of the center wing box in the main wheel well. The APU fuel pump has two parts. It
has a pump cartridge and a pump canister.
(2) The pump cartridge has a 28−volt−dc motor, an impeller, an inlet port, and a
delivery port. When a pump−on signal is supplied to the pump motor, the pump
motor turns the impeller which causes fuel to move. Fuel moves from the inlet port
to the delivery port.
(3) The pump canister lets the operator remove the pump cartridge while there is fuel in
the fuel tanks. The pump canister has an input port with a plunger valve, an output
port with a nonreturn valve, a pressure port, and a housing. When the pump
cartridge is installed in the pump canister housing, the structure of the pump
canister pushes the plunger valve open. When the plunger valve is open, fuel flows
through the input port to supply the APU fuel pump.
(4) When the APU fuel pump is on, fuel pressure in the canister pushes the nonreturn
valve open. When the nonreturn valve is open, fuel flows through the output port to
the APU feed manifold. Fuel pressure is also supplied to the pressure port to
measure the pressure.
B. APU−Feed−Line Check Valve
(1) The APU−feed−line check valve is a spring−loaded poppet−type valve that
prevents reverse fuel flow in the APU feed manifold. It is installed in the center wing
box connected to the APU feed manifold.
(2) The APU−feed−line check valve has a poppet, a spring, and a valve body. When
the APU feed manifold is pressurized, fuel pressure pushes on the poppet which
opens the passage in the valve body. Fuel then flows through the valve and through
the APU feed manifold. When fuel flow stops, the spring pushes the poppet back in
place and closes the valve.

Master
EFFECTIVITY: See Pageblock 28−24−00 page 1
28−24−00 Page 1
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
C. APU−Pump Inlet Screen
(1) The APU−pump inlet screens are metal−mesh screens that make a box around the
pickup port of the APU feed/crossflow manifold. These screens are in the main
tanks on the inboard bulkhead. The APU−pump inlet screens keep unwanted
material out of the APU fuel pump.
D. APU Negative−Gravity−Feed Valve
(1) The APU negative−gravity−feed valve is a spring−loaded poppet−type valve that
lets fuel flow from the right engine feed manifold to the APU feed manifold. It is
installed in the center wing box in a line connected between the APU feed manifold
and the right engine feed manifold.
(2) The APU negative−gravity−feed valve has a poppet, a spring, and a valve body.
When the pressure on the output side of the valve is 6.5 to 10 psi (45 to 69 kPa)
less than the pressure on the input side, the larger pressure pushes the poppet.
The poppet then opens the valve passage in the valve body and fuel flows through
the valve. When the pressure difference on the two sides of the valve is less than 8
to 10 psi (55 to 69 kPa), the spring pushes the poppet back in place and closes the
valve.
E. APU−Fuel−Feed Shutoff Valve
(1) The APU−fuel−feed shutoff valve is an electrically−operated butterfly valve that is
used to stop the flow of fuel during an APU fire. It is located above the center wing
box, connected to the APU feed lines.
(2) Each APU−fuel−feed shutoff valve has a 28−volt−dc motor, a status switch, a
butterfly flapper, and a valve body. When a close−valve signal is supplied to the
valve motor, the motor turns the butterfly flapper and closes the passage in the
valve body. This stops fuel flow in the APU feed line. When the butterfly valve is
closed, the status switch closes the contacts in the closed−valve−position circuit to
supply a valve−closed status signal.
(3) When an open−valve signal is supplied to the valve motor, the motor turns the
butterfly flapper in the other direction and opens the passage in the valve body.
This also causes the status switch to close the contacts in the open−valve−position
circuit to supply a valve−open status signal.
F. APU Fuel−Line Shroud
(1) The APU fuel−line shroud contains the APU feed line that is installed outside of the
center wing box. This shroud collects fuel leakage from the APU feed line. Any fuel
that goes into the shroud can be drained overboard.
3. Operation
Refer to Figure 2.
A. The APU fuel−feed system supplies fuel to the APU. When the operator pushes the
PWR FUEL switch/light, a signal is supplied to the APU fuel pump which causes the
APU fuel pump to operate. The APU fuel pump moves fuel from the APU feed/crossflow
manifold to the APU feed manifold. The fuel then flows through the APU feed manifold,
through the APU−fuel−feed check valve, and the APU−fuel−feed shutoff valve to the
APU fuel feed line and the APU.
B. In case of a negative−gravity condition in flight when the APU fuel pump does not get
enough fuel, pressure decreases in the APU feed manifold. This causes fuel pressure in
the right engine feed line to open the APU negative−gravity−feed valve. Fuel is then

Master
EFFECTIVITY: See Pageblock 28−24−00 page 1
28−24−00 Page 2
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
supplied to the APU through the feed valve from the right engine feed manifold.
C. If there is a fire in the APU, the operator can push the APU FIRE PUSH switch/light on
the right glareshield. This sends a signal to the APU−fuel−feed shutoff valve which
closes the valve and shuts down the APU fuel pump.
D. The APU fuel pump is also used in the transfer system (28−13−00) in the power
fuel−crossflow function.
4. Component Location Index
Refer to Figure 3.
COMPONENT NAME QTY ACCESS/ZONE REFERENCE
Check valve, APU feed line 1 610AB 28−24−07
Circuit breakers:
XFER/APU FUEL PUMP, N10 1 CBP−1/221 −
XFER/APU CONT, N11 1 CBP−1/221 −
XFER/APU APU ECU, N12 1 CBP−1/221 −
Pump, APU fuel 1 164AZ, 610AB 28−24−01
Screen, APU pump inlet 2 540AB, 640AB 28−24−20
Shrouds, APU fuel line − Main wheel well 28−24−23
Valve, APU fuel feed shutoff 1 164AZ 28−24−25
Valve, APU negative−gravity feed 1 610AB 28−24−10

Master
EFFECTIVITY: See Pageblock 28−24−00 page 1
28−24−00 Page 3
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

B D

A C

A APU FUEL PUMP

APU FUEL FEED
B
SHUTOFF VALVE

ram2824000_003(2).dc, ks/gg, 18/07/95

APU FEED LINE APU NEGATIVE−GRAVITY

C D
CHECK VALVE FEED VALVE

APU Fuel Feed System − Component Location/Recognition

Figure 1

Master
EFFECTIVITY: See Pageblock 28−24−00 page 1
28−24−00 Page 4
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

CROSSFLOW CROSSFLOW
CHECK VALVE CHECK VALVE

APU PUMP APU PUMP

INLET INLET
SCREEN SCREEN

APU
FUEL
APU PUMP
FEED
LINE RIGHT
CHECK ENGINE
VALVE FEED
MANIFOLD

APU
FUEL FEED APU NEGATIVE−
SHUTOFF GRAVITY
VALVE RELIEF VALVE

TO
APU ram2824000_001.dg, PB, 08/05/91

APU Fuel Feed System − Schematic

Figure 2

Master
EFFECTIVITY: See Pageblock 28−24−00 page 1
28−24−00 Page 5
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

640BB 610AB 540BB

164AZ

ram2824000_002.dg, pb, 20/08/92

NOTE
500 series panels are on the left side.
600 series panels are on the right side.

APU Fuel Feed System − Component Access

Figure 3

Master
EFFECTIVITY: See Pageblock 28−24−00 page 1
28−24−00 Page 6
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C ALL
PUMP, AUXILIARY POWER UNIT (APU) FUEL − REMOVAL/INSTALLATION

1. General
A. The maintenance procedures that follow are for the removal and installation of the
auxiliary power unit (APU) fuel pump. The APU fuel pump has two parts, the pump
cartridge and the pump canister. There is one APU fuel pump in the fuel system. It is
attached to the right rear bulkhead of the center tank.
B. It is necessary to remove the pump pressure switch to remove the pump cartridge.
C. It is necessary to clean the APU pump inlet screen when FOD is suspected to block the
APU pump.
D. It is necessary to remove the pump cartridge to remove the pump canister.
E. It is necessary to defuel the aircraft to remove or install the pump canister. It is also
necessary to drain and remove the fuel fumes from the center tank.
F. It is not necessary to defuel the center tank to remove or install the pump cartridge.

TASK 28−24−01−000−801
Removal of the APU Fuel Pump Cartridge

1. Job Set−Up Information

Subtask 28−24−01−943−001
A. Tools and Equipment
REFERENCE DESIGNATION
None specified Container, fuel

Subtask 28−24−01−946−001
B. Reference Information
REFERENCE DESIGNATION
TASK 28−00−00−910−801 Fuel Safety Precautions
TASK 28−42−10−000−801 Removal of the APU Fuel Pump Pressure Switch
TASK 53−83−01−000−801 Removal of the MLG Wheel Bin

Master
EFFECTIVITY: See Pageblock 28−24−01 page 401
28−24−01 Page 401
Sep 10/2004
 C
AIRCRAFT MAINTENANCE MANUAL
2. Job Set−Up
Subtask 28−24−01−910−001
WARNING: OBEY ALL THE FUEL SAFETY PRECAUTIONS WHEN YOU DO WORK ON THE
FUEL SYSTEM AND/OR A FUEL SYSTEM COMPONENT. IF YOU DO NOT DO
THIS, YOU CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO
EQUIPMENT.
A. Obey all the fuel safety precautions (Ref. TASK 28−00−00−910−801).

Subtask 28−24−01−865−001
B. Open, safety, and tag the circuit breakers that follow:
CB PANEL CB NO. NAME ZONE
CBP−1 M12 FUEL SYST CONT 221
CBP−1 N10 XFER/APU FUEL PUMP 221
CBP−4 B10 FUEL SYST CONT 222

Subtask 28−24−01−010−001
C. Remove the right wheel bin (164AZ) from the main wheel well (Ref. TASK
53−83−01−000−801).
D. Remove the pressure switch (Ref. TASK 28−42−10−000−801).
E. Put the fuel container below the APU fuel pump.

3. Procedure
Subtask 28−24−01−020−001
Refer to Figure 401.
A. Remove the pump cartridge as follows:
(1) Disconnect the electrical connector (1) from the pump cartridge (2). Put a protective
cap on the electrical connector (1).
(2) Loosen the jamnut (3) and remove the fitting (4). Remove the retainer (5) from the
pump cartridge (2). Remove and discard the preformed packing (6).
(3) Remove the three bolts (7), the three washers (8), and the pump cartridge (2).
Remove and discard the preformed packing (9).
(4) Check for visible FOD in the pump inlet area. If FOD is detected, get access to the
APU pump inlet screen and clean the area.

Master
EFFECTIVITY: See Pageblock 28−24−01 page 401
28−24−01 Page 402
Sep 10/2004
 C
AIRCRAFT MAINTENANCE MANUAL

LEGEND.
1. Electrical connector.
2. Pump cartridge.
3. Jamnut.
4. Fitting.
5. Retainer.
6. Preformed packing.
7. Bolt.
8. Washer.
9. Preformed packing.

A FUEL TANK
BULKHEAD
(REF)

D
FW
9

ram2824014_001(3).dc, gg/rm, 24/02/97

4 6 8
7
5
3
A

APU Fuel−Pump Cartridge − Removal/Installation

Figure 401

Master
EFFECTIVITY: See Pageblock 28−24−01 page 401
28−24−01 Page 403
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
TASK 28−24−01−400−801
Installation of the APU Fuel Pump Cartridge

1. Job Set−Up Information

Subtask 28−24−01−943−004
A. Tools and Equipment
REFERENCE DESIGNATION
None specified Torque wrench − 12 to 15 lbf·in (1.356 to 1.695
N·m) torque range

Subtask 28−24−01−944−001
B. Consumable Materials
REFERENCE DESIGNATION
06−002 Petrolatum

Subtask 28−24−01−945−001
C. Parts
REF NAME OF PART QTY IPC SEQUENCE NO.
5 Retainer 1 IPC 28−24−00−3−060
6 Preformed packing 1 IPC 28−24−00−3−055
7 Bolt 3 IPC 28−24−00−3−015
8 Washer 3 IPC 28−24−00−3−025
9 Preformed packing 1 IPC 28−24−00−3−030

Subtask 28−24−01−946−002
D. Reference Information
REFERENCE DESIGNATION
TASK 28−24−01−710−801 Operational Test of the APU Fuel Pump
TASK 28−42−10−400−801 Installation of the APU Fuel Pump Pressure
Switch
TASK 51−80−00−100−802 Preparation of Bonding Surfaces
TASK 53−83−01−400−801 Installation of the MLG Wheel Bin

2. Procedure
Subtask 28−24−01−869−001
A. Make sure that the aircraft is in the same configuration as in the removal task.

Subtask 28−24−01−420−001
Refer to Figure 401.

Master
EFFECTIVITY: See Pageblock 28−24−01 page 401
28−24−01 Page 404
Jun 22/2004
 C
AIRCRAFT MAINTENANCE MANUAL
B. Install the pump cartridge as follows:
(1) Prepare the mating surfaces of the pump cartridge (2), the bolts (7), and the fuel
tank bulkhead for electrical bonding (Ref. TASK 51−80−00−100−802).
(2) Lubricate the preformed packing (9) and install on the pump cartridge (2).
(3) Install the pump cartridge (2), the three washers (8) and the three bolts (7).
(4) Torque the bolts (7) from 12 to 15 lbf·in (1.356 to 1.695 N·m).
(5) Install the jamnut (3) and the retainer (5) on the fitting (4).
(6) Lubricate the preformed packing (6) and install on the fitting (4). Install the fitting (4)
on the pump cartridge (2) and tighten the jamnut (3).
(7) Remove the protective cap from the electrical connector (1). Connect the electrical
connector (1) to the pump cartridge (2).

3. Close Out
Subtask 28−24−01−410−001
A. Install the pump pressure switch (Ref. TASK 28−42−10−400−801).

Subtask 28−24−01−865−002
B. Remove the tags and close the circuit breakers that follow:
CB PANEL CB NO. NAME ZONE
CBP−1 M12 FUEL SYST CONT 221
CBP−1 N10 XFER/APU FUEL PUMP 221
CBP−4 B10 FUEL SYST CONT 222

Subtask 28−24−01−710−001
C. Do an operational test of the APU fuel pump (Ref. TASK 28−24−01−710−801) and
examine the area around the APU fuel pump for leaks.

Subtask 28−24−01−410−002
D. Install the right wheel bin (164AZ) in the main gear well (Ref. TASK
53−83−01−400−801).

Subtask 28−24−01−941−001
E. Remove all the tools, equipment, and unwanted materials from the area.

Master
EFFECTIVITY: See Pageblock 28−24−01 page 401
28−24−01 Page 405
Jun 22/2004
 C
AIRCRAFT MAINTENANCE MANUAL
TASK 28−24−01−000−802
Removal of the APU Fuel Pump Canister

1. Job Set−Up Information

Subtask 28−24−01−943−002
A. Tools and Equipment
REFERENCE DESIGNATION
None specified Scraper, nonmetallic

Subtask 28−24−01−946−003
B. Reference Information
REFERENCE DESIGNATION
TASK 12−11−28−650−804 Suction Defueling
TASK 28−00−00−910−801 Fuel Safety Precautions
TASK 28−11−00−840−801 Prepare Fuel Tank for Access
TASK 28−11−00−840−802 Removal of Fuel Fumes
TASK 28−11−01−000−802 Removal of the Graphite Access Panel
TASK 28−24−01−000−801 Removal of the APU Fuel Pump Cartridge
TASK 53−83−01−000−801 Removal of the MLG Wheel Bin

2. Job Set−Up
Subtask 28−24−01−910−002
WARNING: OBEY ALL THE FUEL SAFETY PRECAUTIONS WHEN YOU DO WORK ON THE
FUEL SYSTEM AND/OR A FUEL SYSTEM COMPONENT. IF YOU DO NOT DO
THIS, YOU CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO
EQUIPMENT.
A. Obey all the fuel safety precautions (Ref. TASK 28−00−00−910−801).

Subtask 28−24−01−650−001
B. Defuel the aircraft (Ref. TASK 12−11−28−650−804).

Subtask 28−24−01−010−004
C. Remove the right wheel bin (164AZ) from the main wheel well (Ref.TASK
53−83−01−000−801).

Subtask 28−24−01−010−002
D. Remove the access panel that follows (Ref. TASK 28−11−01−000−802):

Master
EFFECTIVITY: See Pageblock 28−24−01 page 401
28−24−01 Page 406
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

ACCESS DESIGNATION
610AB Fuel tank access panel

Subtask 28−24−01−840−001
E. Prepare the center tank for access (Ref. TASK 28−11−00−840−801).
F. Remove the fuel fumes from the center tank (Ref. TASK 28−11−00−840−802).

Subtask 28−24−01−010−003
G. Remove the pump cartridge (Ref. TASK 28−24−01−000−801).

3. Procedure
Subtask 28−24−01−020−002
Refer to Figure 402.
A. Remove the pump canister as follows:
(1) Remove the lockwire and disconnect the inlet tube (1) from the pump canister (2).
Remove and discard the preformed packing (3). Put a protective plug in the inlet
tube.
(2) Remove the lockwire and disconnect the outlet tube (4) from the pump canister (2).
(3) Remove the retainer (5) and the preformed packings (6). Discard the preformed
packings.
(4) Put a protective plug in the outlet tube (4).
(5) Use a nonmetallic scraper to remove the sealant around the pump canister (2) and
the fuel tank bulkhead.
CAUTION: HOLD THE PUMP CANISTER WHILE THE BOLTS ARE REMOVED. IF
THE PUMP CANISTER FALLS, IT WILL CAUSE DAMAGE TO THE
ADJACENT STRUCTURE.
(6) Remove the bolts (7), the washers (8), and the pump canister (2). Remove and
discard the preformed packing (9).
NOTE: The bolts for the pump cartridge are longer than the bolts for the pump
canister. Examine the bolts to help in the installation.
(7) Remove the split ring (10) and the coupling (11) from the pump canister (2).

Master
EFFECTIVITY: See Pageblock 28−24−01 page 401
28−24−01 Page 407
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

LEGEND
1. Inlet tube.
2. Pump canister.
3. Preformed packing.
4. Outlet tube.
5. Retainer.
6. Preformed packing.
7. Bolt.
8. Washer.
9. Preformed packing.
10. Split ring.
11. Coupling.
12. Coupling.
13. Split ring.

FUEL TANK
BULKHEAD 9
(REF)

8 3

13
12
1

D
FW
ram2824014_002(2).dc, ks/gg, 18/07/95

11
10
6
5
6
13
12
4

APU Fuel Pump Canister − Removal/Installation

Figure 402

Master
EFFECTIVITY: See Pageblock 28−24−01 page 401
28−24−01 Page 408
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
TASK 28−24−01−400−802
Installation of the APU Fuel Pump Canister

1. Job Set−Up Information

Subtask 28−24−01−943−003
A. Tools and Equipment
REFERENCE DESIGNATION
None specified Flow gun, sealant
None specified Torque wrench − 12 to 15 lbf·in (1.356 to 1.695
N·m) torque range

Subtask 28−24−01−944−002
B. Consumable Materials
REFERENCE DESIGNATION
06−002 Petrolatum
MS20995 C 32 Lockwire
09−001 Sealing compound

Subtask 28−24−01−945−002
C. Parts
REF NAME OF PART QTY IPC SEQUENCE NO.
3 Preformed packing 1 IPC 28−24−00−01−090
6 Preformed packing 2 IPC 28−24−00−01−105
9 Preformed packing 1 IPC 28−24−00−03−035

Subtask 28−24−01−946−004
D. Reference Information
REFERENCE DESIGNATION
TASK 28−11−01−400−802 Installation of the Graphite Access Panel
TASK 28−24−01−400−801 Installation of the APU Fuel Pump Cartridge
TASK 51−80−00−100−802 Preparation of Bonding Surfaces
TASK 53−83−01−400−801 Installation of the MLG Wheel Bin

2. Procedure
Subtask 28−24−01−869−002
A. Make sure that the aircraft is in the same configuration as in the removal task.

Subtask 28−24−01−420−002
Refer to Figure 402.

Master
EFFECTIVITY: See Pageblock 28−24−01 page 401
28−24−01 Page 409
Jun 22/2004
 C
AIRCRAFT MAINTENANCE MANUAL
B. Install the pump canister as follows:
(1) Prepare the mating surfaces of the fuel tank bulkhead and the pump canister (2) for
electrical bonding (Ref. TASK 51−80−00−100−802).
(2) Install the coupling (11) and the split ring (10) on the pump canister (2).
(3) Lubricate the preformed packing (9) and install on the pump canister (2).
(4) Install the pump canister (2), the washers (8), and the bolts (7).
NOTE: The bolts for the pump cartridge are longer than the bolts for the pump
canister. Use the correct bolts to install the pump canister.
(5) Torque the bolts (7) from 12 to 15 lbf·in (1.356 to 1.695 N·m).
(6) Apply a fillet seal at the joint between the pump canister (2) and the fuel tank
bulkhead.
(7) Remove the protective cap from the outlet tube (4).
(8) Lubricate the preformed packings (6) and install the preformed packings and the
retainer (5).
(9) Connect the outlet tube (4) to the pump canister (2). Lockwire the coupling (12) to
the pump canister (2).
(10) Lubricate the preformed packing (3) and install on the inlet tube (1).
(11) Remove the protective cap from the inlet tube (1). Connect the inlet tube to the
pump canister (2). Lockwire the coupling (12) to the pump canister (2).

3. Close Out
Subtask 28−24−01−210−002
A. Make sure that there is fuel in the center tank and examine the area around the APU fuel
canister for leaks.

Subtask 28−24−01−410−006
B. Install the fuel pump cartridge (Ref.TASK 28−24−01−400−801).

Subtask 28−24−01−410−003
C. Install the access panel that follows (Ref. TASK 28−11−01−400−802).
ACCESS DESIGNATION
610AB Fuel tank access panel

Subtask 28−24−01−410−005
D. Install the right wheel bin (164AZ) in the main wheel well (Ref. TASK
53−83−01−400−801).

Subtask 28−24−01−710−003
E. Do an operational test of the APU fuel pump (Ref. TASK 28−24−01−710−801).

Master
EFFECTIVITY: See Pageblock 28−24−01 page 401
28−24−01 Page 410
Jun 22/2004
 C
AIRCRAFT MAINTENANCE MANUAL
Subtask 28−24−01−941−002
F. Remove all the tools, equipment, and unwanted materials from the area.

Master
EFFECTIVITY: See Pageblock 28−24−01 page 401
28−24−01 Page 411
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C ALL
PUMP, AUXILIARY POWER UNIT (APU) FUEL − ADJUSTMENT/TEST

1. General
A. The maintenance procedure that follows is for the test of the auxiliary power unit (APU)
fuel pump.

TASK 28−24−01−710−801
Operational Test of the APU Fuel Pump

1. Job Set−Up Information

Subtask 28−24−01−946−005
A. Reference Information
REFERENCE DESIGNATION
TASK 12−00−07−861−801 Connect External AC Power
TASK 12−00−07−861−802 Remove External AC Power

2. Job Set−Up
Subtask 28−24−01−861−001
A. Connect the external AC power to the aircraft (Ref. TASK 12−00−07−861−801).
B. Push the FUEL pushbutton on the engine indication and crew alerting system (EICAS)
control panel to get the FUEL synoptic display.

3. Procedure
Subtask 28−24−01−710−002
A. Do a test of the APU fuel pump as follows:
(1) On the fuel synoptic display of the EICAS, make sure that the APU fuel pump is
shown in white.
(2) At the APU control panel, push in the PWR FUEL switch/light. Make sure that the
PUMP FAIL light does not come on.
(3) On the fuel synoptic display, make sure that the APU fuel pump is shown in green.
(4) At the APU control panel, push out the PWR FUEL switch/light.
(5) On the fuel synoptic display, make sure that the APU fuel pump is shown in white.

Subtask 28−24−01−861−002
B. Remove the external AC power from the aircraft (Ref. TASK 12−00−07−861−802).

Master
EFFECTIVITY: See Pageblock 28−24−01 page 501
28−24−01 Page 501
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C ALL
CHECK VALVE, AUXILIARY POWER UNIT (APU) FEED LINE − REMOVAL/INSTALLATION

1. General
A. The maintenance procedures that follow are for the removal and installation of the
auxiliary power unit (APU) feed line check valve (written as the "check valve" in this
procedure). There is one check valve in the fuel system. It is found in the center tank
connected to the APU feed line.
B. It is necessary to defuel the aircraft to remove or install the check valve. It is also
necessary to drain and remove the fuel fumes from the center tank.

TASK 28−24−07−000−801
Removal of the APU Feed Line Check Valve

1. Job Set−Up Information

Subtask 28−24−07−946−001
A. Reference Information
REFERENCE DESIGNATION
TASK 12−11−28−650−804 Suction Defueling
TASK 28−00−00−910−801 Fuel Safety Precautions
TASK 28−11−00−840−801 Prepare Fuel Tank for Access
TASK 28−11−00−840−802 Removal of Fuel Fumes
TASK 28−11−01−000−802 Removal of the Graphite Access Panel

2. Job Set−Up
Subtask 28−24−07−910−001
WARNING: OBEY ALL THE FUEL SAFETY PRECAUTIONS WHEN YOU DO WORK ON THE
FUEL SYSTEM AND/OR A FUEL SYSTEM COMPONENT. IF YOU DO NOT DO
THIS, YOU CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO
EQUIPMENT.
A. Obey all the fuel safety precautions (Ref. TASK 28−00−00−910−801).

Subtask 28−24−07−650−001
B. Defuel the aircraft (Ref. TASK 12−11−28−650−804).

Subtask 28−24−07−010−001
C. Remove the access panel that follows (Ref. TASK 28−11−01−000−802):
ACCESS DESIGNATION
610AB Fuel tank access panel

Master
EFFECTIVITY: See Pageblock 28−24−07 page 401
28−24−07 Page 401
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
Subtask 28−24−07−840−001
D. Prepare the center tank for access (Ref. TASK 28−11−00−840−801).
E. Remove the fuel fumes from the center tank (Ref. TASK 28−11−00−840−802).

3. Procedure
Subtask 28−24−07−020−001
Refer to Figure 401.
A. Remove the check valve as follows:
(1) Hold the check valve and loosen the jamnut (10).
(2) Disconnect the check valve (6) from the fuel line (1).
(3) Disconnect the check valve (6) from the adaptor (7).
(4) Remove the retainer (9) and the preformed packing (8). Discard the preformed
packing (8).
(5) Put protective plugs in the fuel line (1) and the adaptor (7).

Master
EFFECTIVITY: See Pageblock 28−24−07 page 401
28−24−07 Page 402
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

LEGEND
1. Fuel line.
2. Fuel line.
3. Screw.
4. Washer.
5. Tube clamp.
6. Check valve.
7. Adaptor.
2
8. Preformed packing.
9. Retainer.
10. Jamnut.

1 10

ram2824074_001(2).dg, gg/yf, 23/01/03

4
5 3

APU Feed Line Check Valve − Removal/Installation

Figure 401

Master
EFFECTIVITY: See Pageblock 28−24−07 page 401
28−24−07 Page 403
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
TASK 28−24−07−400−801
Installation of the APU Feed Line Check Valve

1. Job Set−Up Information

Subtask 28−24−07−945−001
A. Parts
REF NAME OF PART QTY IPC SEQUENCE NO.
8 Preformed packing 1 IPC 28−24−00−01−215

Subtask 28−24−07−946−002
B. Reference Information
REFERENCE DESIGNATION
TASK 28−11−01−400−802 Installation of the Graphite Access Panel

2. Procedure
Subtask 28−24−07−869−001
A. Make sure that the aircraft is in the same configuration as in the removal task.

Subtask 28−24−07−420−001
Refer to Figure 401.
B. Install the check valve as follows:
(1) Remove the protective plugs from the fuel line (1) and the adaptor (7).
(2) Lubricate the preformed packing (8).
(3) Install the preformed packing (8) and the retainer (9) on the adaptor (7).
(4) Turn the check valve (6) on the adaptor (7).
NOTE: Make sure that the arrow on the check valve points forward.
(5) Connect the fuel line (1) to the check valve (6).
(6) Hold the check valve and tighten the jamnut (10).

3. Close Out
Subtask 28−24−07−410−001
A. Install the access panel that follows (Ref. TASK 28−11−01−400−802).
ACCESS DESIGNATION
610AB Fuel tank access panel

Master
EFFECTIVITY: See Pageblock 28−24−07 page 401
28−24−07 Page 404
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
Subtask 28−24−07−941−001
B. Remove all tools, equipment, and unwanted materials from the work area.

Master
EFFECTIVITY: See Pageblock 28−24−07 page 401
28−24−07 Page 405
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C ALL
CHECK VALVE, AUXILIARY POWER UNIT (APU) NEGATIVE−GRAVITY FEED −
REMOVAL/INSTALLATION

1. General
A. The maintenance procedures that follow are for the removal and installation of the
auxiliary power unit (APU) negative−gravity feed check valve (written as the "check
valve" in this procedure). There is one check valve in the fuel system. It is in the center
wing box connected between the right engine feed manifold and the APU feed line.
B. It is necessary to defuel, drain, and remove the fuel fumes from the center tank and the
right main tank to remove or install the check valve.

TASK 28−24−10−000−801
Removal of the APU Negative−Gravity Feed Check Valve

1. Job Set−Up Information

Subtask 28−24−10−946−001
A. Reference Information
REFERENCE DESIGNATION
TASK 12−11−28−650−804 Suction Defueling
TASK 28−00−00−910−801 Fuel Safety Precautions
TASK 28−11−00−840−801 Prepare Fuel Tank for Access
TASK 28−11−00−840−802 Removal of Fuel Fumes
TASK 28−11−01−000−802 Removal of the Graphite Access Panel

2. Job Set−Up
Subtask 28−24−10−910−001
WARNING: OBEY ALL THE FUEL SAFETY PRECAUTIONS WHEN YOU DO WORK ON THE
FUEL SYSTEM AND/OR A FUEL SYSTEM COMPONENT. IF YOU DO NOT DO
THIS, YOU CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO
EQUIPMENT.
A. Obey all the fuel safety precautions (Ref. TASK 28−00−00−910−801).

Subtask 28−24−10−650−001
B. Defuel the center tank and the right main tank (Ref. TASK 12−11−28−650−804).

Subtask 28−24−10−010−001
C. Remove the access panel that follows (Ref. TASK 28−11−01−000−802):

Master
EFFECTIVITY: See Pageblock 28−24−10 page 401
28−24−10 Page 401
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

ACCESS DESIGNATION
610AB Fuel tank access panel

Subtask 28−24−10−840−001
D. Prepare the center tank for access (Ref. TASK 28−11−00−840−801).
E. Remove the fuel fumes from the center tank and the right main tank (Ref. TASK
28−11−00−840−802).

3. Procedure
Subtask 28−24−10−020−001
Refer to Figure 401.
A. Remove the check valve as follows:
(1) Disconnect the fuel line (1) from the reducer (2).
(2) Disconnect the check valve (3) from the tube assembly.
(3) Remove the fuel line (1) from the check valve (3).
(4) Remove the check valve (3) from the tube assembly.
(5) Install protective plugs in the tube assembly and the reducer.

Master
EFFECTIVITY: See Pageblock 28−24−10 page 401
28−24−10 Page 402
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

LEGEND.
1. Fuel line.
2. Reducer.
3. Check valve.

ENGINE FEED
MANIFOLD
(REF)

3
TUBE
ASSEMBLY
(REF)
ram2824104_001(2).dc, cr/gg, 18/07/95

APU Negative−Gravity Feed Check Valve − Removal/Installation

Figure 401

Master
EFFECTIVITY: See Pageblock 28−24−10 page 401
28−24−10 Page 403
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
TASK 28−24−10−400−801
Installation of the APU Negative−Gravity Feed Check Valve

1. Job Set−Up Information

Subtask 28−24−10−946−002
A. Reference Information
REFERENCE DESIGNATION
TASK 28−11−01−400−802 Installation of the Graphite Access Panel

2. Procedure
Subtask 28−24−10−869−001
A. Make sure that the aircraft is in the same configuration as in the removal task.

Subtask 28−24−10−420−001
Refer to Figure 401.
B. Install the check valve as follows:
(1) Install the check valve (3) on the APU feed line. Make sure that the arrow on the
check valve points aft.
(2) Remove the protective plugs from the tube assembly and the reducer (2).
(3) Connect the check valve (3) to the tube assembly.
(4) Connect the fuel line (1) to the reducer (2).

3. Close Out
Subtask 28−24−10−410−001
A. Install the access panel that follows (Ref. TASK 28−11−01−400−802):
ACCESS DESIGNATION
610AB Fuel tank access panel

Master
EFFECTIVITY: See Pageblock 28−24−10 page 401
28−24−10 Page 404
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C ALL
SHROUD, AUXILIARY POWER UNIT (APU) FEED − REMOVAL/INSTALLATION

1. General
A. The maintenance procedures that follow are for the removal and installation of the
auxiliary power unit (APU) feed shroud. The APU feed shroud is installed between the
aft pressure bulkhead at FS 621.00 and the APU enclosure.

TASK 28−24−23−000−801
Removal of the APU Feed Shroud

1. Job Set−Up Information

Subtask 28−24−23−943−002
A. Tools and Equipment
REFERENCE DESIGNATION
Commercially Available Container − Non−static Fuel

Subtask 28−24−23−946−003
B. Reference Information
REFERENCE DESIGNATION
TASK 24−00−00−910−801 Electrical/Electronic Safety Precautions
TASK 24−00−00−910−802 Electrostatic Discharge Safety Precautions
TASK 28−00−00−910−801 Fuel Safety Precautions

2. Job Set−Up
Subtask 28−24−23−910−013
WARNING: OBEY ALL THE FUEL SAFETY PRECAUTIONS WHEN YOU DO WORK ON THE
FUEL SYSTEM AND/OR A FUEL SYSTEM COMPONENT. IF YOU DO NOT DO
THIS, YOU CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO
EQUIPMENT.
A. Obey all the fuel safety precautions (Ref. TASK 28−00−00−910−801).

Subtask 28−24−23−910−014
B. Obey all the electrostatic discharge precautions (Ref.TASK 24−00−00−910−802).

Subtask 28−24−23−910−015
C. Obey all the electrical/electronic safety precautions (Ref. TASK 24−00−00−910−801).

Master
EFFECTIVITY: See Pageblock 28−24−23 page 401
28−24−23 Page 401
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
Subtask 28−24−23−865−001
D. Open, safety and tag the circuit breakers that follow:
CB PANEL CB NO. NAME ZONE
CBP−1 R5 APU FIRE EXT A 221
CBP−1 R6 APU FIRE EXT B 221
CBP−1 N10 XFER/APU FUEL PUMP 221
CBP−1 N11 XFER/APU CONT 221
CBP−1 N12 XFER/APU APU ECU 221
CBP−1 S3 FUEL SOV APU 221
CBP−5 A1 APU ACT 221

Subtask 28−24−23−010−002
E. Open the access doors that follow:
ACCESS DESIGNATION
311BB Aft Equipment − Bay Door

3. Procedure
Refer to Figure 401.
Subtask 28−24−23−000−001
A. Remove the APU feed shroud assembly as follows:
(1) Disconnect the fuel feed line from the APU enclosure, and from the aft pressure
bulkhead at FS621.00 as follows:
(a) Remove the clam shell (3) from the shroud cup (9) and (10).
(b) Remove and discard the preformed packings (2) and (5).
(c) Disconnect the slider assembly (1) from the shroud cup (9) and (10) to get
access to the fuel tube (6).
(d) Remove the clam shell (8).
(e) Disconnect the fuel tube (6) from bulkhead fitting on the APU enclosure, and
from the pressure bulkhead at FS621.00.
(f) Remove and discard the preformed packing (7).
(g) Install the protective covers on the shroud tube (4), fuel tube (6), and the
bulkhead fitting that is attached to the APU enclosure.
(h) Install the protective covers on the shroud tube (4), fuel tube (6), and the
bulkhead fitting that is attached to the pressure bulkhead at FS621.00.
CAUTION: ALWAYS USE TWO WRENCHES WHEN YOU REMOVE HOSES
AND TUBES. USE ONE WRENCH TO HOLD THE FITTING, AND
THE OTHER WRENCH TO LOOSEN THE COUPLING NUT. IF
THESE PRECAUTIONS ARE NOT USED, DAMAGE TO THE
COMPONENTS CAN BE A RESULT.
(i) Remove the nut and the two washers that attach the shroud cup (9) and the

Master
EFFECTIVITY: See Pageblock 28−24−23 page 401
28−24−23 Page 402
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
bulkhead fitting to the APU enclosure.
(j) Remove the nut and the two washers that attach the shroud cup (10) and the
bulkhead fitting to the pressure bulkhead at FS621.00.
(k) Remove the screw (11), washer (12), and clamp (13).
(l) Remove the bulkhead fitting.

Master
EFFECTIVITY: See Pageblock 28−24−23 page 401
28−24−23 Page 403
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

B
1

FS621.00

A
1

2 D
APU
3 C ENCLOSURE
(REF)

A
4
LEGEND
5
1. Shroud assembly.
2. Packing (preformed).
3. Clam shell. 6
4. Shroud tube. 7
5. Packing (preformed). 8
6. Fuel tube.
7. Packing (preformed).
8. Clam shell.
9. Shroud cup. 10 B
10. Shroud cup.
11. Screw.
12. Washer. 8 9
13. Clamp.
7
5

4 3

6
2
12
1
ram2824234_001.dg, lr, 17/07/03

11
C

13
D

APU Feed Shroud − Removal/Installation

Figure 401

Master
EFFECTIVITY: See Pageblock 28−24−23 page 401
28−24−23 Page 404
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
TASK 28−24−23−400−801
Installation of the APU Feed Shroud

1. Job Set−Up Information

Subtask 28−24−23−946−004
A. Reference Information
ACCESS DESIGNATION
TASK 20−21−00−910−801 Torque Procedure for Threaded Fasteners
TASK 24−00−00−910−801 Electrical/Electronic Safety Precautions
TASK 24−00−00−910−802 Electrostatic Discharge Safety Precautions
TASK 28−00−00−910−801 Fuel Safety Precautions
TASK 28−24−23−780−801 Pressure and Blockage Test of the APU Feed
Shroud

Subtask 28−24−23−944−002
B. Consumable Materials
REFERENCE DESIGNATION
06−002 Petrolatum

Subtask 28−24−23−945−001
C. Expendable Parts
REF NAME OF PART QTY IPC SEQUENCE NO.
2 Preformed packing 2 IPC 28−24−00−04−025
5 Preformed packing 5 IPC 28−24−00−04−015
7 Preformed packing 2 IPC 28−24−00−04−035
11 Screw 1 IPC 28−24−00−04−045
12 Washer 1 IPC 28−24−00−04−050
13 Clamp 1 IPC 28−24−00−04−40

2. Job Set−Up
Subtask 28−24−23−869−001
A. Make sure that the aircraft is in the same configuration as in the removal task.

Master
EFFECTIVITY: See Pageblock 28−24−23 page 401
28−24−23 Page 405
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
Subtask 28−24−23−910−016
WARNING: OBEY ALL THE FUEL SAFETY PRECAUTIONS WHEN YOU DO WORK ON THE
FUEL SYSTEM AND/OR A FUEL SYSTEM COMPONENT. IF YOU DO NOT DO
THIS, YOU CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO
EQUIPMENT.
B. Obey all the fuel safety precautions (Ref. TASK 28−00−00−910−801).

Subtask 28−24−23−910−017
C. Obey all the electrostatic discharge precautions (Ref. TASK 24−00−00−910−802).

Subtask 28−24−23−910−018
D. Obey all the electrical/electronic safety precautions (Ref. TASK 24−00−00−910−801).

3. Procedure
Refer to Figure 401.
Subtask 28−24−23−400−001
A. Connect the fuel feed line to the APU enclosure and to the aft pressure bulkhead at
FS621.00 as follows:
(1) Remove the protective covers from the shroud tube (4), the fuel tube (6), and the
bulkhead fitting.
(2) Apply petrolatum on the new preformed packing (7).
(3) Install the preformed packing (7) on the fuel tube (6).
(4) Install the clam shell (8) that connects the fuel tube (6) to the bulkhead fitting on the
APU enclosure.
(5) Install the clam shell (8) that connects the fuel tube (6) to fitting at the aft pressure
bulkhead at FS 621.00.
(6) Apply petrolatum on the new preformed packing (5).
(7) Install the preformed packing (5) on the shroud tube (4).
(8) Apply petrolatum on the new preformed packing (2).
(9) Install the preformed packing (2) on the slider (1).
(10) Connect the shroud tube (4) to the shroud cup (9) and (10).
(11) Position the slider (1) over the shroud tube (4) and install the clam shell (3) that
connects the shroud cup (9) and (10) and the slider (1).

4. Close Out
Subtask 28−24−23−941−002
A. Remove all tools, equipment, and unwanted materials from the area.

Master
EFFECTIVITY: See Pageblock 28−24−23 page 401
28−24−23 Page 406
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
Subtask 28−24−23−410−002
B. Close the access doors that follow:
ACCESS DESIGNATION
311BB Aft Equipment−Bay Door

Subtask 28−24−23−865−002
C. Remove the tag and close the circuit breakers that follow:
CB PANEL CB NO. NAME ZONE
CBP−1 R5 APU FIRE EXT A 221
CBP−1 R6 APU FIRE EXT B 221
CBP−1 N10 XFER/APU FUEL PUMP 221
CBP−1 N11 XFER/APU CONT 221
CBP−1 N12 XFER/APU APU ECU 221
CBP−1 S3 FUEL SOV APU 221
CBP−5 A1 APU ACT 221

Subtask 28−24−23−780−005
D. Do the Adjustment/Test of the APU feed shroud (Ref. TASK 28−24−23−780−801).

Master
EFFECTIVITY: See Pageblock 28−24−23 page 401
28−24−23 Page 407
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C ALL
SHROUD, AUXILIARY POWER UNIT (APU) FEED − ADJUSTMENT/TEST

1. General
A. The maintenance procedures that follow are for the pressure and blockage tests of the
auxiliary power unit (APU) feed shroud. The APU feed shroud is installed between the
aft pressure bulkhead and the APU enclosure.
B. It is not necessary to defuel the aircraft to do a test of the APU feed shrouds.

TASK 28−24−23−780−801
Pressure and Blockage Test of the APU Feed Shroud

1. Job Set−Up Information

Subtask 28−24−23−943−001
A. Tools and Equipment
REFERENCE DESIGNATION
F601R2820TFIX2−1 Hose assembly
G601R121605−1 Gaseous test panel

Subtask 28−24−23−944−001
B. Consumable Materials
REFERENCE DESIGNATION
05−036 Fluid, leak detector

Subtask 28−24−23−946−002
C. Reference Information
REFERENCE DESIGNATION
TASK 28−20−01−780−801 Pressure and Blockage Test of the Fuel Line
Shroud

2. Procedure
Subtask 28−24−23−010−001
A. Open the access door that follows:
ACCESS DESIGNATION
311BB Aft equipment compartment door

Master
EFFECTIVITY: See Pageblock 28−24−23 page 501
28−24−23 Page 501
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
Subtask 28−24−23−480−003
B. Install the test equipment as follows:
(1) Close all of the shutoff valves on the gaseous test panel.
(2) Connect the hose assembly to the shroud drain fitting at FS506.
(3) Connect the gaseous test panel to the hose assembly.
(4) Connect the gaseous test panel to pressurized air.
(5) Install a plug assembly in each of the other shroud drain fittings between the main
wheel well and the aft pressure bulkhead.

Subtask 28−24−23−780−003
Refer to Figure 502
C. Do a blockage test of the APU feed shroud as follows:
(1) Disconnect the slider assembly (2) from the shroud cup (7) at the APU enclosure
(8).
(2) Set the air test panel to 20 psi (149 kPa).
(3) Slowly open the outlet valve on the gaseous test panel.
(4) Make sure that air flows out of the shroud tube assembly (5).
(5) Close the outlet valve on the gaseous test panel.
(6) Connect the shroud tube assembly (5) to the shroud cup (7).
(7) Position the slider (2) over the shroud tube assembly (5) and install the clam shell
assembly (4).

Subtask 28−24−23−780−004
D. Do a pressure test of the APU feed shroud (Ref. TASK 28−20−01−780−801).
NOTE: There is no drain on the APU feed shroud, therefore the procedure for the
engine fuel feed line must be used.

3. Close Out
Subtask 28−24−23−080−001
A. Disconnect the test equipment as follows:
(1) Disconnect the pressurized air from the gaseous test panel.
(2) Disconnect the gaseous test panel from the hose assembly.
(3) Remove the hose assembly from the drain fitting.

Subtask 28−24−23−941−001
B. Remove all tools, equipment, and unwanted materials from the area.

Master
EFFECTIVITY: See Pageblock 28−24−23 page 501
28−24−23 Page 502
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
Subtask 28−24−23−410−001
C. Close the access door that follows:
ACCESS DESIGNATION
811 Aft equipment compartment door

Master
EFFECTIVITY: See Pageblock 28−24−23 page 501
28−24−23 Page 503
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

APU PRESSURE
ENCLOSURE BULKHEAD
(REF) FS621.00

LEGEND
1. Shroud clamp.
2. Shroud.
3. Shroud fitting.

1 3
ENGINE 2
FEED

FS637.00
FS635.00
ram2824235_001.dg, db/rm, 07/03/03

MOTIVE
FLOW

APU Feed Shroud − Adjustment/Test

Figure 501

Master
EFFECTIVITY: See Pageblock 28−24−23 page 501
28−24−23 Page 504
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

APU
ENCLOSURE
(REF) A

FS621.00
LEGEND
1. Shroud assembly.
2. Slider assembly.
3. Preformed packing.
4. Clam shell assembly.
5. Shroud tube assembly.
6. Preformed packing.
7. Shroud cup.
A 8. APU enclosure.

2 6

7
3
8
4
ram2824235_002.dg, gg, 09/08/95

APU Feed Shroud − Adjustment/Test

Figure 502

Master
EFFECTIVITY: See Pageblock 28−24−23 page 501
28−24−23 Page 505
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C ALL
VALVE, AUXILIARY POWER UNIT (APU) FUEL FEED SHUTOFF − REMOVAL/INSTALLATION

1. General
A. The maintenance procedures that follow are for the removal and installation of the
auxiliary power unit (APU) fuel feed shutoff valve (written as the "shutoff valve" in this
procedure) and the removal and installation of the electrical actuator from the fuel feed
shutoff valve assembly. There is one shutoff valve in the fuel system. It is found above
the center tank. The shutoff valve is connected to the APU feed line from the main fuel
tanks.
B. It is not necessary to defuel the fuel tanks to remove the shutoff valve.

TASK 28−24−25−000−801
Removal of the APU Fuel Feed Shutoff Valve

1. Job Set−Up Information

Subtask 28−24−25−943−001
A. Tools and Equipment
REFERENCE DESIGNATION
None specified Container, fuel

Subtask 28−24−25−946−001
B. Reference Information
REFERENCE DESIGNATION
TASK 28−00−00−910−801 Fuel Safety Precautions
TASK 53−83−01−000−801 Removal of the MLG Wheel Bin

2. Job Set−Up
Subtask 28−24−25−910−001
WARNING: OBEY ALL THE FUEL SAFETY PRECAUTIONS WHEN YOU DO WORK ON THE
FUEL SYSTEM AND/OR A FUEL SYSTEM COMPONENT. IF YOU DO NOT DO
THIS, YOU CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO
EQUIPMENT.
A. Obey all the fuel safety precautions (Ref. TASK 28−00−00−910−801).

Subtask 28−24−25−865−001
B. Open, safety, and tag the circuit breakers that follow:

Master
EFFECTIVITY: See Pageblock 28−24−25 page 401
28−24−25 Page 401
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

CB PANEL CB NO. NAME ZONE

CBP−1 M12 FUEL SYST CONT 221
CBP−1 N10 XFER/APU FUEL PUMP 221
CBP−1 N11 XFER/APU CONT 221
CBP−1 N12 XFER/APU APU ECU 221
CBP−4 B10 FUEL SYST CONT 222

Subtask 28−24−25−010−001
C. Remove the right wheel bin (164AZ) from the main wheel well (Ref. TASK
53−83−01−000−801).
D. Put a fuel container below the shutoff valve.

3. Procedure
Subtask 28−24−25−020−001
Refer to Figure 401.
A. Remove the shutoff valve as follows:
(1) Disconnect the electrical connector (1) from the shutoff valve (2). Put a protective
cap on the electrical connector.
(2) Loosen the hose clamp (3) and disconnect the drain tube (4) from the fuel
shroud (5).
(3) Loosen the hose clamps (6) and disconnect the fuel shrouds (5) from the shutoff
valve (2).
(4) Put a container under fitting (12). Remove cap (11) to empty the shutoff valve.
(5) Disconnect the pressure line (7) from the shutoff valve (2). Put a protective plug in
the pressure line. Put the cap (11) on the fitting (12).
(6) Disconnect the hose (8) from the shutoff valve (2). Put a protective plug in the hose.
(7) Remove the screws (9), the washers (10), and the shutoff valve (2).

Master
EFFECTIVITY: See Pageblock 28−24−25 page 401
28−24−25 Page 402
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

LEGEND.
1. Electrical connector.
2. Shutoff valve.
3. Hose clamp.
4. Drain tube.
5. Fuel shroud.
6. Hose clamp.
7. Pressure line.
8. Hose.
9. Screw.
10. Washer.
11. Cap.
12. Fitting.

1
2

7
6
5 10
9

ram2824254_001(2).dc, pb, 15/08/95

12 11
8 6 3

APU Fuel Feed Shutoff Valve − Removal/Installation

Figure 401

Master
EFFECTIVITY: See Pageblock 28−24−25 page 401
28−24−25 Page 403
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
TASK 28−24−25−400−801
Installation of the APU Fuel Feed Shutoff Valve

1. Job Set−Up Information

Subtask 28−24−25−946−002
A. Reference Information
REFERENCE DESIGNATION
TASK 28−24−25−710−801 Operational Test of the APU Fuel Feed Shutoff
Valve

2. Procedure
Subtask 28−24−25−869−001
A. Make sure that the aircraft is in the same configuration as in the removal task.

Subtask 28−24−25−420−001
Refer to Figure 401.
B. Install the shutoff valve as follows:
(1) Install the shutoff valve (2), the washers (10), and the screws (9).
(2) Remove the protective plug from the hose (8). Connect the hose to the shutoff
valve (2).
(3) Remove the protective plug from the pressure line (7). Connect the pressure line to
the shutoff valve (2).
(4) Connect the fuel shrouds (5) to the shutoff valve (2) and tighten the hose
clamps (6).
(5) Connect the drain tube (4) to the fuel shroud (5) and tighten the hose clamp (3).
(6) Remove the protective cap from the electrical connector (1). Connect the electrical
connector to the shutoff valve (2).

3. Close Out
Subtask 28−24−25−865−002
A. Remove the tags and close the circuit breakers that follow:
CB PANEL CB NO. NAME ZONE
CBP−1 M12 FUEL SYST CONT 221
CBP−1 N10 XFER/APU FUEL PUMP 221
CBP−1 N11 XFER/APU CONT 221
CBP−1 N12 XFER/APU APU ECU 221
CBP−4 B10 FUEL SYST CONT 222

Master
EFFECTIVITY: See Pageblock 28−24−25 page 401
28−24−25 Page 404
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
Subtask 28−24−25−710−001
B. Do an operational test of the shutoff valve (Ref. TASK 28−24−25−710−801.

Subtask 28−24−25−941−001
C. Remove all the tools, equipment, and unwanted materials from the area.

Master
EFFECTIVITY: See Pageblock 28−24−25 page 401
28−24−25 Page 405
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
TASK 28−24−25−000−802
Removal of the APU Fuel Feed Shutoff Valve Electrical Actuator

1. Job Set−Up Information

Subtask 28−24−25−946−007
A. Reference Information
REFERENCE DESIGNATION
TASK 28−00−00−910−801 Fuel Safety Precautions
TASK 53−83−01−000−801 Removal of the MLG Wheel Bin

2. Job Set−Up
Subtask 28−24−25−910−004
WARNING: OBEY ALL THE FUEL SAFETY PRECAUTIONS WHEN YOU DO WORK ON THE
FUEL SYSTEM AND/OR A FUEL SYSTEM COMPONENT. IF YOU DO NOT DO
THIS, YOU CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO
EQUIPMENT.
A. Obey all the fuel safety precautions (Ref.TASK 28−00−00−910−801).

Subtask 28−24−25−865−006
B. Open, safety, and tag the circuit breakers that follow:
CB PANEL CB NO. NAME ZONE
CBP−1 M12 FUEL SYST CONT 221
CBP−1 N10 XFER/APU FUEL PUMP 221
CBP−1 N11 XFER/APU CONT 221
CBP−1 N12 XFER/APU APU ECU 221
CBP−4 B10 FUEL SYST CONT 222

Subtask 28−24−25−010−007
C. Remove the right wheel bin (164AZ) from the main wheel well (Ref. TASK
53−83−01−000−801).

3. Procedure
Subtask 28−24−25−020−003
Refer to Figure 402.
A. Remove the electrical actuator (2) from the body assembly (3) of the APU fuel feed valve
as follows:
NOTE: This procedure is the same for both of the engine fuel feed shutoff valves.
(1) Disconnect the electrical connector (1) from the electrical actuator (2).
(2) Put protective caps on the electrical connector and on the receptacle of the
electrical actuator.

Master
EFFECTIVITY: See Pageblock 28−24−25 page 401
28−24−25 Page 406
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
(3) Remove the screws (4) and the washers (5) that attach the two half−clamps (6).
(4) Remove the two half−clamps (6) that secure the electrical actuator (2) to the body
assembly (3).
(5) Remove the electrical actuator (2) from the body assembly (3).

Master
EFFECTIVITY: See Pageblock 28−24−25 page 401
28−24−25 Page 407
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

LEGEND
A
1. Electrical connector.
2. Electrical actuator.
3. Body assembly.
4. Screw.
5. Washer.
6. Clamp.

6 3
1

5
4 ram2824254_002.dg, yf, 09/04/03

APU Fuel Feed Shutoff Valve Electrical Actuator − Removal/Installation

Figure 402

Master
EFFECTIVITY: See Pageblock 28−24−25 page 401
28−24−25 Page 408
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
TASK 28−24−25−400−802
Installation of the APU Fuel Feed Shutoff Valve Electrical Actuator

1. Job Set−Up Information

Subtask 28−24−25−943−003
A. Consumable Materials
REFERENCE DESIGNATION
08−001 Sealing Compound, threadlocking, low strength,
anaerobic, single component, (Locktite 222MS)
08−001A Sealing Compound, threadlocking, low strength,
anaerobic, single component, (Locktite 221)
B. Parts
REF NAME OF PART QTY IPC SEQUENCE NO.
1 Screw 2 IPC 29−11−36−02−020
2 Washer 2 IPC 29−11−36−02−025

Subtask 28−24−25−946−008
C. Reference Information
REFERENCE DESIGNATION
TASK 28−24−25−710−801 Operational Test of the APU Fuel Feed Shutoff
Valve
TASK 53−83−01−400−801 Installation of the MLG Wheel Bin

Subtask 28−24−25−869−002
D. Make sure that the aircraft is in the same configuration as in the removal task.

2. Procedure
Subtask 28−24−25−420−002
Refer to Figure 402.
A. Install the electrical actuator (2) to the body assembly (3) of the APU fuel feed shutoff
valve as follows:
(1) Install the washers (5) on the two screws (4).
(2) Apply a layer of 08−001A threadlocker on the threads of the two screws (4).
NOTE: 08−001 threadlocker is similar to 08−001A threadlocker and can be used
as an alternative.
(3) Make sure that the key slot on the control shaft is correctly aligned with the key that
is inside the electrical actuator (2). Both must be in the fully opened or the fully
closed position.
(4) Put the electrical actuator (2) in position on the body assembly (3). Make sure that
the pin on the flange of the body assembly (3) is correctly aligned with the hole in

Master
EFFECTIVITY: See Pageblock 28−24−25 page 401
28−24−25 Page 409
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
the flange of the electrical actuator (2).
NOTE: With the keyslot on the control shaft correctly engaged with the key of the
electrical actuator (2), it is possible that the electrical actuator (2) will need
to be turned slightly to align the pin and the hole.
(5) Secure the two electrical actuator (2) to the body assembly (3) with the two
half−clamps (6).
(6) Secure the two half−clamps (6) with the two screws (4).
(7) Tighten the two screws (4).
NOTE: Make sure that the spaces between the joints of the half−clamps (6) are
the same when you tighten the two screws.
(8) Remove the protective caps from the electrical connector (1) and from the
receptacle of the electrical actuator (2).
(9) Connect the electrical connector (1) to the electrical connector (2).

3. Close Out
Subtask 28−24−25−865−007
A. Remove the tags and close the circuit breakers that follow:
CB PANEL CB NO. NAME ZONE
CBP−1 M12 FUEL SYST CONT 221
CBP−1 N10 XFER/APU FUEL PUMP 221
CBP−1 N11 XFER/APU CONT 221
CBP−1 N12 XFER/APU APU ECU 221
CBP−4 B10 FUEL SYST CONT 222

Subtask 28−24−25−710−004
B. Do an operational test of the APU fuel feed shutoff valve (Ref. TASK
28−24−25−710−801).

Subtask 28−24−25−410−001
C. Install the right wheel bin 164AZ in the main wheel well (Ref. TASK
53−83−01−400−801).

Subtask 28−24−25−941−004
D. Remove all tools, equipment, and unwanted materials from the work area.

Master
EFFECTIVITY: See Pageblock 28−24−25 page 401
28−24−25 Page 410
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C ALL
VALVE, AUXILIARY POWER UNIT (APU) FUEL FEED SHUTOFF − ADJUSTMENT/TEST

1. General
A. The maintenance procedure that follows is for the test of the auxiliary power unit (APU)
fuel−feed shutoff−valve (written as the "shutoff valve" in this procedure).

TASK 28−24−25−710−801
Operational Test of the APU Fuel−Feed Shutoff−Valve

1. Job Set−Up Information

Subtask 28−24−25−946−003
A. Reference Information
REFERENCE DESIGNATION
TASK 12−00−07−861−801 Connect External AC Power
TASK 12−00−07−861−802 Remove External AC Power
TASK 28−20−01−780−801 Pressure and Blockage Test of The Fuel Line
Shroud
TASK 53−83−01−000−801 Removal of the MLG Wheel Bin
TASK 53−83−01−400−801 Installation of the MLG Wheel Bin

2. Job Set−Up
Subtask 28−24−25−010−003
A. If the wheel bins are installed, remove the right wheel bin (164AZ) from the main wheel
well (Ref. TASK 53−83−01−000−801).

Subtask 28−24−25−865−003
B. Make sure that the circuit breakers that follow are closed:
CB PANEL CB NO. NAME ZONE
CBP−1 M12 FUEL SYST CONT 221
CBP−1 N10 XFER/APU FUEL PUMP 221
CBP−1 N11 XFER/APU CONT 221
CBP−1 N12 XFER/APU APU ECU 221
CBP−4 B10 FUEL SYST CONT 222

Subtask 28−24−25−861−001
C. Connect the external AC power to the aircraft (Ref. TASK 12−00−07−861−801).
D. Push the FUEL pushbutton on the engine indication and crew alerting system (EICAS)
control panel to get the FUEL synoptic display.

Master
EFFECTIVITY: See Pageblock 28−24−25 page 501
28−24−25 Page 501
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
3. Procedure
Subtask 28−24−25−710−002
A. Do a test of the APU fuel−feed shutoff−valve as follows:
(1) On the fuel synoptic display of the EICAS, make sure that the shutoff valve is
shown in white and in the CLOSED position.
(2) In the main wheel well, at the shutoff valve, make sure that the position indicator is
at the CLOSED position.
(3) At the APU control panel, push in the PWR FUEL switch/light. Make sure that the
PUMP FAIL light does not come on.
(4) On the fuel synoptic display, make sure that the shutoff valve is shown in green and
in the OPEN position.
(5) In the main wheel well, at the shutoff valve, make sure the position indicator is at
the OPEN position.
WARNING: DO NOT PUSH THE "BOTTLE ARMED PUSH TO DISCH"
SWITCH/LIGHT DURING THE REMAINING STEPS OF THIS TEST.
THE HALON CAN COME OUT OF THE FIREX BOTTLE AND CAUSE
INJURIES.
(6) On the glareshield, push in the APU FIRE PUSH switch/light.
(7) On the fuel synoptic display, make sure that the shutoff valve is shown in white and
in the closed position.
(8) In the main wheel well, at the shutoff valve, make sure that the position indicator is
at the CLOSED position.
(9) On the glareshield, push out the APU FIRE PUSH switch/light.
(10) On the FUEL synoptic display, make sure that the shutoff valve is shown in green
and in the open position.
(11) In the main wheel well, at the shutoff valve, make sure that the position indicator is
at the OPEN position.
(12) On the APU control panel, push out the PWR FUEL switch/light.

4. Close Out
Subtask 28−24−25−861−002
A. Remove the external AC power from the aircraft (Ref. TASK 12−00−07−861−802).

Subtask 28−24−25−210−001
B. Check the following areas for a sign of fuel leakage.
(1) Examine the area around the shutoff valve for leaks.
(2) Remove one end of the drain tube and check inside the tube for a sign of leaks.
(3) Do a pressure and blockage test of the fuel line shroud (Ref. TASK
28−20−01−780−801).

Master
EFFECTIVITY: See Pageblock 28−24−25 page 501
28−24−25 Page 502
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
Subtask 28−24−25−410−003
C. Install the right wheel bin (164AZ) in the main wheel well (Ref. TASK
53−83−01−400−801).

Master
EFFECTIVITY: See Pageblock 28−24−25 page 501
28−24−25 Page 503
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
TASK 28−24−25−710−802
Operation Test of APU Fuel−Feed Shutoff−Valve Position−Indicator
1. Reason for the Job
Refer to MRB 28−24−00−03

2. Job Set−Up Information

Subtask 28−24−25−946−006
A. Reference Information
REFERENCE DESIGNATION
TASK 12−00−07−861−801 Connect External AC Power
TASK 12−00−07−861−802 Remove External AC Power
TASK 53−83−01−000−801 Removal of the MLG Wheel Bin
TASK 53−83−01−400−801 Installation of the MLG Wheel Bin

3. Job Set−Up
Subtask 28−24−25−010−005
A. Remove the right wheel bin (164AZ) from the main wheel well (Ref. TASK
53−83−01−000−801).

Subtask 28−24−25−861−007
B. Connect the external AC power to the aircraft (Ref. TASK 12−00−07−861−801).

4. Procedure
Subtask 28−24−25−710−003
A. Do a test of the APU fuel−feed shutoff−valve as follows:
(1) In the flight compartment, on the APU control panel, push the FUEL SOV switch.
(2) In the main wheel well, at the shutoff valve, make sure that the position indicator is
at the OPEN position.
WARNING: DO NOT PUSH THE "BOTTLE ARMED PUSH TO DISCH"
SWITCH/LIGHT DURING THE REMAINING STEPS OF THIS TEST.
THE HALON CAN COME OUT OF THE FIREX BOTTLE AND CAUSE
INJURIES.
(3) On the glareshield, push in the APU FIRE PUSH switch/light.
(4) In the main wheel well, at the shutoff valve, make sure that the position indicator is
at the CLOSED position.
(5) On the glareshield, push out the APU FIRE PUSH switch/light.
(6) In the main wheel well, at the shutoff valve, make sure that the position indicator is
at the OPEN position.
(7) In the flight compartment, on the APU control panel, push out the FUEL SOV
switch.

Master
EFFECTIVITY: See Pageblock 28−24−25 page 501
28−24−25 Page 504
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
5. Close Out
Subtask 28−24−25−861−008
A. Remove the external AC power from the aircraft (Ref. TASK 12−00−07−861−802).

Subtask 28−24−25−410−005
B. Install the right wheel bin (164AZ) in the main wheel well (Ref. TASK
53−83−01−400−801).

Master
EFFECTIVITY: See Pageblock 28−24−25 page 501
28−24−25 Page 505
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
TASK 28−24−25−790−801
Leak Test of the APU Fuel−Feed Shutoff−Valve
1. Reason for the Job
Refer to CMR C28−20−131−01.

2. Job Set−up Information

Subtask 28−24−25−946−005
A. Reference Information
REFERENCE DESIGNATION
TASK 12−00−07−861−801 Connect External AC Power
TASK 12−00−07−861−802 Remove External AC Power

3. Job Set−up
Subtask 28−24−25−865−005
A. Open, safety and tag the circuit breaker that follows:
CB PANEL CB NO. NAME ZONE
CBP−1 S3 FUEL SOV APU 221

Subtask 28−24−25−010−004
B. Open the access doors that follow:
ACCESS DESCRIPTION
311BB Aft equipment compartment door
311BZ APU enclosure door

Subtask 28−24−25−861−005
C. Connect the external AC power to the aircraft (Ref. TASK 12−00−07−861−801).
D. Push the FUEL pushbutton on the engine indication and crew alerting system (EICAS)
control panel to get the FUEL synoptic display.

4. Procedure
Subtask 28−24−25−790−001
A. Do a leak test of the APU fuel−feed shutoff−valve as follows:
(1) Disconnect the main pressure−fuel line from the APU fuel−control unit.
(2) On the APU control panel, push the PWR FUEL switch/light. On the FUEL synoptic
display, make sure that the green fuel line stops at the APU shutoff valve.
(3) Make sure that no fuel leaks from the APU main pressure−fuel line.
(4) On the APU control panel, push the PWR FUEL switch/light. On the FUEL synoptic
display, make sure that the green fuel line goes out of view.

Master
EFFECTIVITY: See Pageblock 28−24−25 page 501
28−24−25 Page 506
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
(5) Connect the main pressure fuel−line to the APU fuel−control unit.
(6) Remove the tag and close the circuit breaker that follows:
CB PANEL CB NO. NAME ZONE
CBP−1 S3 FUEL SOV APU 221
(7) On the APU control panel, push the PWR FUEL switch/light. On the FUEL synoptic
display of the EICAS, make sure that the green fuel line goes to the APU.
(8) Make sure that no fuel leaks between the main pressure−fuel line and the APU
fuel−control unit.
(9) On the APU control panel, push the PWR FUEL switch/light. On the FUEL synoptic
display, make sure the green fuel line goes out of view.

5. Close Out
Subtask 28−24−25−410−004
A. Close the access doors that follow:
ACCESS DESCRIPTION
311BB Aft equipment compartment door
311BZ APU enclosure door

Subtask 28−24−25−861−006
B. Remove the external AC power from the aircraft (Ref. TASK 12−00−07−861−802).

Master
EFFECTIVITY: See Pageblock 28−24−25 page 501
28−24−25 Page 507
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C ALL
VALVE, AUXILIARY POWER UNIT (APU) FUEL FEED SHUTOFF − INSPECTION/CHECK

1. General
A. The maintenance procedure that follows is for the internal leak check of the auxiliary
power unit (APU) fuel feed shutoff valve (written as the "shutoff valve" in this procedure).
B. It is not necessary to defuel the fuel tanks to do a leak check of the shutoff valve.

TASK 28−24−25−200−801
Internal Leak Check

1. Job Set−Up Information

Subtask 28−24−25−943−002
A. Tools and Equipment
REFERENCE DESIGNATION
None specified Container, fuel
None specified Stopwatch
None specified Graduated cylinder, 10 cc

Subtask 28−24−25−945−002
B. Parts
REF NAME OF PART QTY IPC SEQUENCE NO.
4 Hose clamp 1 IPC 28−24−00−095
7 Hose clamp 1 IPC 28−24−00−005

Subtask 28−24−25−946−004
C. Reference Information
REFERENCE DESIGNATION
TASK 12−00−07−861−801 Connect External AC Power
TASK 12−00−07−861−802 Remove External AC Power
TASK 28−00−00−910−801 Fuel Safety Precautions
TASK 53−83−01−000−801 Removal of the MLG Wheel Bin
TASK 53−83−01−400−801 Installation of the MLG Wheel Bin

Master
EFFECTIVITY: See Pageblock 28−24−25 page 601
28−24−25 Page 601
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
2. Job Set−Up
Subtask 28−24−25−910−002
WARNING: OBEY ALL THE FUEL SAFETY PRECAUTIONS WHEN YOU DO WORK ON THE
FUEL SYSTEM AND/OR A FUEL SYSTEM COMPONENT. IF YOU DO NOT DO
THIS, YOU CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO
EQUIPMENT.
A. Obey all the fuel safety precautions (Ref. TASK 28−00−00−910−801).

Subtask 28−24−25−010−002
B. Remove the right wheel bin (164AZ) from the main wheel well (Ref. TASK
53−83−01−000−801).

Subtask 28−24−25−865−004
C. Make sure that the circuit breakers that follow are closed:
CB PANEL CB NO. NAME ZONE
CBP−1 N10 XFER/APU FUEL PUMP 221
CBP−1 N11 XFER/APU CONT 221
CBP−1 N12 XFER/APU APU ECU 221

Subtask 28−24−25−861−003
D. Connect the external AC power to the aircraft (Ref. TASK 12−00−07−861−801).

Subtask 28−24−25−941−002
E. Close the shutoff valve as follows:
WARNING: DO NOT PUSH THE "BOTTLE ARMED PUSH TO DISCH"
SWITCH/LIGHT DURING THE REMAINING STEPS OF THIS TEST.
THE HALON CAN COME OUT OF THE FIREX BOTTLE AND CAUSE
INJURIES.
(1) In the flight compartment, on the glareshield, push in the APU FIRE PUSH
switch/light.
(2) In the right wheel well, at the shutoff valve, make sure that the position indicator is
at the closed position.

3. Procedure
Subtask 28−24−25−030−001
Refer to Figure 601.
A. Disconnect the fuel hose from the shutoff valve as follows:
(1) Remove the cap (1) from the bulkhead fitting (2) and drain the fuel into the fuel
container.
(2) Install the cap (1) on the bulkhead fitting (2).

Master
EFFECTIVITY: See Pageblock 28−24−25 page 601
28−24−25 Page 602
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
(3) Put the fuel container below the shutoff valve (3).
(4) Loosen the hose clamp (4) on the drain line (5). Disconnect the drain line from the
fuel hose shroud (6). Drain the remaining fuel into the fuel container.
(5) Loosen the hose clamp (7) on the fuel hose shroud (6). Disconnect the fuel hose
shroud from the shutoff valve (3).
(6) Disconnect the fuel hose (8) from the shutoff valve (3). Drain the remaining fuel into
the fuel container.

Subtask 28−24−25−210−002
B. Do an internal leak check of the shutoff valve as follows:
(1) Put the graduated cylinder below the open port of the shutoff valve (3).
(2) In the flight compartment at the APU control panel, do the steps the follow:
(a) Push in the PWR FUEL switch/light to operate the APU fuel pump.
(b) Make sure that the PUMP FAIL light does not come on.
(c) Use a stopwatch to measure the time that the APU fuel pump operates.
Operate the APU fuel pump for a minimum of 1 minute. Do not operate the
APU fuel pump for more than 5 minutes.
(d) Push out the PWR FUEL switch/light.
(3) At the graduated cylinder, measure the fuel leakage from the open port of the
shutoff valve (3). With the time from the stopwatch, calculate the leakage rate.
Make sure that the leakage rate is not more than 0.5 cc per minute.

Subtask 28−24−25−430−001
C. Connect the fuel hose to the shutoff valve as follows:
(1) Connect the fuel hose (8) to the shutoff valve (3).
(2) Connect the fuel hose shroud (6) to the shutoff valve (3). Tighten the hose clamp
(7) on the fuel hose shroud.
(3) Connect the drain line (5) to the fuel hose shroud (6). Tighten the hose clamp (4) on
the drain line.

Subtask 28−24−25−210−003
D. Do an external leak check of the shutoff valve as follows:
(1) At the glareshield, push out the APU FIRE PUSH switch/light.
(2) At the shutoff valve, make sure that the position indicator is at the open position.
(3) At the APU control panel, push in the PWR FUEL switch/light. Make sure that the
PUMP FAIL light does not come on.
(4) Examine the area around the shutoff valve for leaks.
(5) In the flight compartment, at the APU control panel, push out the PWR FUEL
switch/light.

Master
EFFECTIVITY: See Pageblock 28−24−25 page 601
28−24−25 Page 603
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
4. Close Out
Subtask 28−24−25−861−004
A. Disconnect the external AC power from the aircraft (Ref. TASK 12−00−07−861−802).

Subtask 28−24−25−410−002
B. Install the right wheel bin (164AZ) in the main wheel well (Ref. TASK
53−83−01−400−801).

Subtask 28−24−25−941−003
C. Remove all the tools, equipment, and unwanted materials from the area.

Master
EFFECTIVITY: See Pageblock 28−24−25 page 601
28−24−25 Page 604
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

LEGEND.
1. Cap.
2. Bulkhead fitting.
3. Shutoff valve.
4. Hose clamp.
5. Drain line.
6. Fuel hose shroud.
7. Hose clamp.
8. Fuel hose.

7
6

3
5
8

4
2
1 ram2824256_001(1).dc, jp, 17/02/93

APU Fuel Feed Shutoff Valve − Inspection/Check

Figure 601

Master
EFFECTIVITY: See Pageblock 28−24−25 page 601
28−24−25 Page 605
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C ALL
PRESSURE REFUEL/DEFUEL SYSTEM − DESCRIPTION AND OPERATION

1. General
A. The pressure refuel/defuel system permits aircraft refueling from a single point on the
aircraft. It also controls the flow of fuel to the fuel tanks to make sure that they are not
overfilled. The pressure refuel/defuel system has the components that follow:
± One refuel/defuel single−point adapter
± One refuel/defuel check valve
**ON A/C 7008, 7011−7014, 7017−7018, 7020, 7022, 7026−7031, 7034−7035, 7037−7038, 7040,
7042−7051, 7053−7058, 7060, 7062, 7065−7067, 7069−7072, 7074, 7076−7085, 7087−7088,
7091−7092, 7095−7098, 7100−7102, 7105−7109, 7111−7112, 7115−7118, 7120, 7123−7124,
7126−7127, 7129, 7131−7133, 7137, 7139, 7141, 7143−7147, 7150−7151, 7153−7164, 7166,
7168−7175, 7177−7179, 7181−7188, 7191−7192, 7194−7199, 7201−7204, 7206−7219,
7221−7225, 7227−7246, 7249−7265, 7267−7281, 7284−7297, 7300−7328, 7330−7350,
7352−7364, 7366−7370, 7372, 7374−7377, 7379−7385, 7387−7390, 7392−7393, 7395−7402,
7404−7406, 7408−7412, 7414−7418, 7420−7430, 7432−7435, 7437−7438, 7440−7441,
7443−7448, 7450−7463, 7465−7477, 7479, 7481−7485, 7487−7493, 7495−7498, 7500−7566,
7568−7569, 7571−7572, 7574−7582, 7584−7604, 7606, 7608−7616, 7618, 7620−7624,
7626−7628, 7631−7737, 7739−7845, 7847−7861, 7863, 7865−7900, 7903−7909, 7911−7972,
7974−7989, 8000−8045, 8047−8059, 8061−8064
± One refuel/defuel control panel
**ON A/C 7003−7007, 7009−7010, 7015−7016, 7019, 7021, 7023−7025, 7032−7033, 7036, 7039,
7041, 7052, 7059, 7061, 7063−7064, 7073, 7075, 7086, 7089−7090, 7093−7094, 7099,
7103−7104, 7110, 7113−7114, 7119, 7121−7122, 7125, 7128, 7130, 7134−7136, 7138, 7140,
7142, 7148−7149, 7152, 7165, 7167, 7176, 7180, 7189−7190, 7193, 7200, 7205, 7220, 7226,
7247−7248, 7266, 7282−7283, 7298−7299, 7329, 7351, 7365, 7371, 7373, 7378, 7386, 7391,
7394, 7403, 7407, 7413, 7419, 7431, 7436, 7439, 7442, 7449, 7464, 7478, 7480, 7486, 7494,
7499, 7567, 7570, 7573, 7583, 7605, 7607, 7617, 7619, 7625, 7629−7630, 7738, 7846, 7862,
7864, 7901−7902, 7910, 7973, 7990, 8046, 8060, 8066−8068
± Two refuel/defuel control panels
**ON A/C ALL
± Three refuel/defuel shutoff valves
± Three restrictors
± Three high−level sensors.

Master
EFFECTIVITY: See Pageblock 28−25−00 page 1
28−25−00 Page 1
Dec 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
2. Component Details
A. Refuel/Defuel Single−Point Adapter
**ON A/C 7008, 7011−7014, 7017−7018, 7020, 7022, 7026−7031, 7034−7035, 7037−7038, 7040,
7042−7051, 7053−7058, 7060, 7062, 7065−7067, 7069−7072, 7074, 7076−7085, 7087−7088,
7091−7092, 7095−7098, 7100−7102, 7105−7109, 7111−7112, 7115−7118, 7120, 7123−7124,
7126−7127, 7129, 7131−7133, 7137, 7139, 7141, 7143−7147, 7150−7151, 7153−7164, 7166,
7168−7175, 7177−7179, 7181−7188, 7191−7192, 7194−7199, 7201−7204, 7206−7219,
7221−7225, 7227−7246, 7249−7265, 7267−7281, 7284−7297, 7300−7328, 7330−7350,
7352−7364, 7366−7370, 7372, 7374−7377, 7379−7385, 7387−7390, 7392−7393, 7395−7402,
7404−7406, 7408−7412, 7414−7418, 7420−7430, 7432−7435, 7437−7438, 7440−7441,
7443−7448, 7450−7463, 7465−7477, 7479, 7481−7485, 7487−7493, 7495−7498, 7500−7566,
7568−7569, 7571−7572, 7574−7582, 7584−7604, 7606, 7608−7616, 7618, 7620−7624,
7626−7628, 7631−7737, 7739−7845, 7847−7861, 7863, 7865−7900, 7903−7909, 7911−7972,
7974−7989, 8000−8045, 8047−8059, 8061−8064

Refer to Figure 1.
**ON A/C 7003−7007, 7009−7010, 7015−7016, 7019, 7021, 7023−7025, 7032−7033, 7036, 7039,
7041, 7052, 7059, 7061, 7063−7064, 7073, 7075, 7086, 7089−7090, 7093−7094, 7099,
7103−7104, 7110, 7113−7114, 7119, 7121−7122, 7125, 7128, 7130, 7134−7136, 7138, 7140,
7142, 7148−7149, 7152, 7165, 7167, 7176, 7180, 7189−7190, 7193, 7200, 7205, 7220, 7226,
7247−7248, 7266, 7282−7283, 7298−7299, 7329, 7351, 7365, 7371, 7373, 7378, 7386, 7391,
7394, 7403, 7407, 7413, 7419, 7431, 7436, 7439, 7442, 7449, 7464, 7478, 7480, 7486, 7494,
7499, 7567, 7570, 7573, 7583, 7605, 7607, 7617, 7619, 7625, 7629−7630, 7738, 7846, 7862,
7864, 7901−7902, 7910, 7973, 7990, 8046, 8060, 8066−8068
Refer to Figure 2.
**ON A/C ALL
(1) The refuel/defuel single−point adapter is a manually−operated poppet valve. The
refuel/defuel single−point adapter lets the operator connect the refueling nozzle to
the aircraft to refuel. The adapter is installed behind the fairing between the
fuselage and the right wing. It is connected to the refuel/defuel check valve.
(2) The refuel/defuel single−point adapter has a cap, a poppet, a plunger, a spring, and
a valve body. The cap keeps unwanted material out of the adapter. When the
operator removes the cap and puts the refueling nozzle into the adapter, the
refueling nozzle pushes the poppet which opens the passage in the valve body.
The poppet also pushes the plunger through the adapter, and pushes on the refuel
poppet in the refuel/defuel check valve.
(3) When the refueling nozzle is removed, the spring pushes the poppet and the
plunger back into position and closes the adapter.
B. Refuel/Defuel Check Valve
(1) The refuel/defuel check valve is a manually−operated, dual−poppet valve. The
refuel/defuel check valve controls the flow of fuel through the single−point adapter.
This check valve is installed in the forward bulkhead of the center wing box,
connected between the single−point adapter and the refuel/defuel manifold.
(2) The refuel/defuel check valve has a refuel poppet, a defuel poppet, two springs,
and a valve body. When the refueling nozzle is put into the single−point adapter,
the plunger in the adapter pushes the refuel poppet. This opens a passage in the
valve body and lets fuel flow through the check valve and into the refuel/defuel

Master
EFFECTIVITY: See Pageblock 28−25−00 page 1
28−25−00 Page 2
Dec 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
manifold.
(3) During defueling, the refueling nozzle opens the refuel poppet and supplies suction
to the defuel poppet. When the pressure in the check valve is 1 pound per square
inch (7 kPa) less than the pressure in the refuel/defuel manifold, the defuel poppet
opens. Suction then causes fuel to flow from the refuel/defuel manifold, through the
check valve, and into the refueling nozzle.
(4) When defueling pressure stops, the spring on the defuel poppet pushes the poppet
back in position. When the refueling nozzle is removed, the spring on the refuel
poppet pushes the refuel poppet back in position and closes the valve.
C. Refuel/Defuel Control Panel
**ON A/C 7008, 7011−7014, 7017−7018, 7020, 7022, 7026−7031, 7034−7035, 7037−7038, 7040,
7042−7051, 7053−7058, 7060, 7062, 7065−7067, 7069−7072, 7074, 7076−7085, 7087−7088,
7091−7092, 7095−7098, 7100−7102, 7105−7109, 7111−7112, 7115−7118, 7120, 7123−7124,
7126−7127, 7129, 7131−7133, 7137, 7139, 7141, 7143−7147, 7150−7151, 7153−7164, 7166,
7168−7175, 7177−7179, 7181−7188, 7191−7192, 7194−7199, 7201−7204, 7206−7219,
7221−7225, 7227−7246, 7249−7265, 7267−7281, 7284−7297, 7300−7328, 7330−7350,
7352−7364, 7366−7370, 7372, 7374−7377, 7379−7385, 7387−7390, 7392−7393, 7395−7402,
7404−7406, 7408−7412, 7414−7418, 7420−7430, 7432−7435, 7437−7438, 7440−7441,
7443−7448, 7450−7463, 7465−7477, 7479, 7481−7485, 7487−7493, 7495−7498, 7500−7566,
7568−7569, 7571−7572, 7574−7582, 7584−7604, 7606, 7608−7616, 7618, 7620−7624,
7626−7628, 7631−7737, 7739−7845, 7847−7861, 7863, 7865−7900, 7903−7909, 7911−7972,
7974−7989, 8000−8045, 8047−8059, 8061−8064
(1) The refuel/defuel control panel is an electronic panel that is used to control all of the
refueling and defueling operations, to display fuel quantity and to do tests of the fuel
system. The refuel/defuel control panel is installed in the right side of the fuselage,
forward of the right wing.
(2) The refuel/defuel control panel has the controls and indicators that follow:
± One POWER switch and ON indicator light
± One LAMP TEST pushbutton
± One mode selector switch
± One FAULT ANNUNC. indicator
± One BITE INITIA. pushbutton
± One preselect−fuel quantity display
± One INC./DEC. selector switch
± One refuel start switch
± Three fuel−tank quantity displays
± Three refuel shutoff−valve switches
± Three valve CL (closed) and three valve OP (open) indicators
± Three H. LEVEL DETECTOR indicators.

Master
EFFECTIVITY: See Pageblock 28−25−00 page 1
28−25−00 Page 3
Dec 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C 7003−7007, 7009−7010, 7015−7016, 7019, 7021, 7023−7025, 7032−7033, 7036, 7039,
7041, 7052, 7059, 7061, 7063−7064, 7073, 7075, 7086, 7089−7090, 7093−7094, 7099,
7103−7104, 7110, 7113−7114, 7119, 7121−7122, 7125, 7128, 7130, 7134−7136, 7138, 7140,
7142, 7148−7149, 7152, 7165, 7167, 7176, 7180, 7189−7190, 7193, 7200, 7205, 7220, 7226,
7247−7248, 7266, 7282−7283, 7298−7299, 7329, 7351, 7365, 7371, 7373, 7378, 7386, 7391,
7394, 7403, 7407, 7413, 7419, 7431, 7436, 7439, 7442, 7449, 7464, 7478, 7480, 7486, 7494,
7499, 7567, 7570, 7573, 7583, 7605, 7607, 7617, 7619, 7625, 7629−7630, 7738, 7846, 7862,
7864, 7901−7902, 7910, 7973, 7990, 8046, 8060, 8066−8068
(3) The refuel/defuel control panels are electronic panels that are used to control all of
the refueling and defueling operations, display fuel quantity and to do tests of the
fuel system. One refuel/defuel control panel is installed in the right side of the
fuselage, forward of the right wing. The other refuel/defuel control panel is installed
in the flight compartment, behind the copilot seat.
(4) The refuel/defuel control panel has the controls and indicators that follow:
± One POWER switch and ON indicator light
± One LAMP TEST pushbutton
± One mode selector switch
± One FAULT ANNUNC. indicator
± One BITE INITIA. pushbutton
± One preselect−fuel quantity display
± One INC./DEC. selector switch
± One refuel start switch
± Three fuel−tank quantity displays
± Three refuel shutoff−valve switches
± Three valve CL (closed) and three valve OP (open) indicators
± Three H. LEVEL DETECTOR indicators.
**ON A/C ALL
(5) The POWER switch is a covered, two−position, toggle switch that controls the
supply of 28−volt−dc power to the control panel. When the switch is in the up
position, the ON indicator comes on.
(6) The mode selector switch is a five−position rotary switch that controls the function
of the pressure refuel/defuel system. In the OFF position, the control panel is
inactive. In the TEST position, the control panel starts a test of the pressure
refuel/defuel system and its related components. In the FUEL AUTO position, the
control panel controls automatic refueling from preselected fuel levels entered by
the operator. In the FUEL MANUAL position, the operator controls the refuel
operation with the refuel/defuel shutoff−valve switches. In the DEFUEL position, the
operator controls defueling.
(7) The FAULT ANNUNC. indicator comes on when there is a fault found in the fuel
system.
(8) The BITE INITIA. is a momentary−contact pushbutton. It is used to control the
display of fault codes. When the FAULT ANNUNC. indicator comes on, the operator
pushes the BITE INITIA. pushbutton. This causes the fuel−tank quantity displays to
show fault codes that agree with the failed components. When the operator holds
the pushbutton down, the displays will show other applicable fault codes.

Master
EFFECTIVITY: See Pageblock 28−25−00 page 1
28−25−00 Page 4
Dec 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
(9) The preselect−fuel quantity display is an eight−segment, five−digit,
light−emitting−diode (LED) numeric display. It shows the preselect fuel quantity that
is set by the operator for automatic refuel operation.
(10) The INC./DEC. selector switch is a three−position, momentary−contact, center−off
toggle switch. When the operator pushes the selector switch up to the INC. position,
the fuel quantity shown on the preselect−fuel quantity display increases. When the
operator pushes the selector switch down to the DEC. position, the fuel quantity
shown on the preselect−fuel quantity display decreases.
(11) The refuel start switch is a two−position toggle switch that controls the refuel
operation during an automatic pressure refueling. When the switch is in the ON
position, the refuel/defuel shutoff valves open and the automatic refuel operation
starts.
(12) The fuel−tank quantity displays are eight−segment, four−digit, LED numeric
displays. Each display shows the current fuel quantity of the related fuel tank. If a
failure occurs, the displays can also show a fault code of the failure.
(13) The refuel/defuel shutoff−valve switches are two−position toggle switches that
control the position of the related refuel/defuel shutoff valve. These switches are
used to control the manual refuel or defuel operation.
(14) The valve CL and OP indicators come on to show the current position of the related
refuel/defuel shutoff valve. The CL indicator comes on when the valve is closed.
The OP indicator comes on when the valve is open.
(15) The H. LEVEL DETECTOR indicators come on when the high−level sensors are
submerged in fuel. The indicators that come on show which fuel tanks are full.
(16) The LAMP TEST pushbutton is a momentary−contact pushbutton. When it is
pressed, it supplies test current to all of the indicators and displays. The test current
causes all of the indicators to come on and causes all of the digits in the displays to
come on.
D. Refuel Shutoff Valve
Refer to Figure 3.
(1) The refuel/defuel shutoff valves are electrically−controlled piston−type valves that
control the flow of fuel from the refuel/defuel manifold to the applicable fuel tank.
They are installed in the center wing box, connected to the ends of the refuel/defuel
manifold.
(2) Each refuel/defuel shutoff valve has a control solenoid, a valve−position switch, an
actuator arm, a piston, a spring, and a valve body. When an open−valve signal is
supplied to the control solenoid, the control solenoid moves the actuator arm. The
actuator arm then pushes the piston and opens a passage in the valve body. This
causes the contacts on the valve−position switch to change and to supply a
valve−open signal.
(3) When the open valve signal stops, the control solenoid goes off, and the spring
pushes the piston back into position and closes the valve. This also causes the
contacts on the valve−position switch to change and to supply a valve−closed
signal.

Master
EFFECTIVITY: See Pageblock 28−25−00 page 1
28−25−00 Page 5
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
E. Restrictor
(1) The restrictors are metal washers that control the rate of fuel flow into the fuel
tanks. They are installed in the center wing box. The restrictors for each fuel tank
are installed on the input port of the related refuel/defuel shutoff valve.
F. High−Level Sensor
(1) The high−level sensors are thermistors which prevent an overfill condition in the
fuel tanks. There is one sensor installed in each fuel tank, close to the upper wing
skin.
(2) Each high−level sensor has a thermistor network and an electrical connector. An ac
signal is supplied to the high−level sensor through the electrical connector. When
the high−level sensor is submerged in fuel, the impedance of the thermistor network
changes, which changes the characteristics of the return signal.
3. Operation
Refer to Figure 4 and Figure 5.
A. The pressure refuel/defuel system controls the pressure refuel and defuel operations of
the aircraft. The pressure refuel/defuel system controls the functions that follow:
± Refuel/defuel system test
± Automatic pressure−refuel operation
± Manual pressure−refuel operation
± Suction defueling.
B. The refuel/defuel system operational−test starts when with fuel pressure supplied to the
refuel/defuel adapter, the operator energizes the refuel/defuel control panel and sets the
mode selector switch to TEST for 3 seconds. The control panel sends a signal to the fuel
system computer (FSC) to start the test. The FSC then sends a signal to the
refuel/defuel shutoff valves to open the shutoff valves. The FSC also sends a test signal
to the high−level sensors that causes the return signal of a full fuel tank from the
high−level sensors. When the FSC receives the correct return signal from the high−level
sensors, the FSC sends another signal to the refuel shutoff valves to close the shutoff
valves.
C. The automatic pressure−refuel operation is performed when the operator connects the
refueling nozzle to the refuel/defuel single−point adapter and supplies fuel pressure. The
fuel flows through the refuel/defuel single−point adapter and the refuel/defuel check
valve to the refuel/defuel manifold. The operator then sets the mode selector switch on
the refuel/defuel control panel to the FUEL AUTO position. The desired fuel quantity is
also set at the refuel/defuel control panel. The operator then puts the refuel start switch
to the ON position. This opens the refuel/defuel shutoff valves and fuel flows into the fuel
tanks.
D. When the total fuel quantity in the fuel tanks is close to the preselect quantity set at the
control panel, the FSC closes the refuel/defuel shutoff valves for 2 or 3 seconds, then
reopens the refuel/defuel shutoff valves for the top−up phase. This brings the actual fuel
quantity closer to the preselected quantity. The FSC also sends a signal to the control
panel which makes the CL indicators come on and the OP indicators go off.
E. If one of the high−level sensors is submerged in fuel during the automatic
pressure−refuel operation, it sends a signal to the FSC. The FSC then closes the
applicable refuel shutoff valve. This prevents an overfill condition in the fuel tank. The
computer also sends a signal to the control panel which makes the applicable CL and H.

Master
EFFECTIVITY: See Pageblock 28−25−00 page 1
28−25−00 Page 6
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
LEVEL DETECTOR indicators go on, and the applicable OP indicator go off.
F. The manual pressure−refuel operation starts when the operator connects the refueling
nozzle to the refuel/defuel single−point adapter and supplies fuel pressure. The fuel
flows through the refuel/defuel single−point adapter and the refuel/defuel check valve to
the refuel/defuel manifold.
G. The operator then sets the mode selector switch on the refuel/defuel control panel to the
FUEL MANUAL position. The operator also puts the applicable refuel/defuel
shutoff−valve switches to the ON position. With the signal received from the
corresponding refuel/defuel shutoff valve, the FSC then sends a signal which opens the
refuel/defuel shutoff valve. When the refuel/defuel shutoff valve opens, fuel flows into the
related fuel tank. The computer then sends a signal to the control panel to make the
applicable CL indicator go off and the applicable OP indicator come on.
H. As fuel flows into the fuel tanks, the fuel−tank quantity displays show the amount of fuel
in each fuel tank. When the fuel tank has the correct fuel level, the operator puts the
refuel/defuel shutoff−valve switches to the OFF position. A signal is received by the FSC
to send the CL signal which closes the refuel/defuel shutoff valve and stops the flow of
fuel into the fuel tank. The computer then sends a signal to the control panel to make the
applicable OP indicator go off and the applicable CL indicator come on.
I. If one of the high−level sensors is submerged in fuel during the manual pressure−refuel
operation, it sends a signal to the FSC. The FSC then closes the applicable refuel/defuel
shutoff valve. This prevents an overfill condition in the fuel tank. The computer also
sends a signal to the control panel which makes the applicable CL and H. LEVEL
DETECTOR indicators come on, and the applicable OP indicator go off.
J. The operator sets the mode selector switch on the refuel/defuel control panel to the
DEFUEL position. Suction defueling is performed when the operator connects the
refueling nozzle to the refuel/defuel single−point adapter and supplies suction.
K. The operator puts the applicable refuel/defuel shutoff−valve switches to the ON position.
This sends a signal to the FSC which opens the applicable refuel/defuel shutoff valves.
With the signal received from the refuel/defuel shutoff valve , the FSC sends a signal to
the control panel to make the applicable CL indicator go off and the applicable OP
indicator come on. When the refuel/defuel shutoff valves open, fuel flows from the
related fuel tank, through the refuel/defuel shutoff valve, and through the refuel/defuel
manifold. From there, it flows through the refuel/defuel check valve, into the refuel/defuel
single−point adapter, and into the refueling nozzle.
L. As the fuel tanks are defueled, the fuel−tank quantity displays show the amount of fuel in
each fuel tank. When the fuel level in the fuel tank is correct, the operator puts the
refuel/defuel shutoff−valve switches to the OFF position. This sends a signal to the FSC
which closes the refuel/defuel shutoff valve and stops the flow of fuel into the fuel tank.
With the signal received from the refuel/defuel shutoff valve, the FSC sends a signal to
the control panel to make the applicable OP indicator go off and the applicable CL
indicator come on.
M. The high−level sensors are not used during suction defueling.
4. Component Location Index
Refer to Figure 6.

Master
EFFECTIVITY: See Pageblock 28−25−00 page 1
28−25−00 Page 7
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

**ON A/C 7008, 7011−7014, 7017−7018, 7022, 7026−7031, 7034−7035, 7037−7038, 7040,
7042−7044, 7046, 7048, 7050, 7055−7056, 7062, 7066−7067, 7069−7070, 7072, 7076−7077,
7079−7080, 7085, 7088, 7091−7092, 7100−7102, 7105−7106, 7108−7109, 7111, 7115−7117,
7123, 7127, 7129, 7131−7133, 7137, 7139, 7141, 7143, 7145−7147, 7150−7151, 7154,
7156−7159, 7162−7163, 7168−7169, 7171−7175, 7178−7179, 7181, 7185−7188, 7191−7192,
7194−7196, 7199, 7202−7204, 7206−7219, 7221−7222, 7224−7225, 7227−7233, 7235−7236,
7238−7246, 7249−7265, 7267−7271, 7273−7281, 7284−7294 Pre SB601R−24−090
COMPONENT NAME QTY ACCESS/ZONE REFERENCE
Adapter, refuel/defuel single−point 1 192BR, 192BB 28−25−01
Check valve, refuel/defuel 1 610BB, 192BR, 192BB 28−25−04
Circuit breakers:
FUEL DEFL, B14 1 CB−5/311 −
EMRG REFL, B15 1 CB−5/311 −
Control panel, refuel/defuel 1 162AB 28−25−16
Restrictor 3 510BB, 610BB, 610AB 28−25−07
Sensor, high−level 3 510BB, 550FB, 650FB 28−25−13
Valve, refuel/defuel shutoff, center 1 610AB 28−25−07
tank
Valve, refuel/defuel shutoff, left main 1 510BB, 540AB 28−25−07
tank
Valve, refuel/defuel shutoff, right main 1 610BB, 640AB 28−25−07
tank

**ON A/C 7020, 7045, 7047, 7049, 7051, 7053−7054, 7057−7058, 7060, 7065, 7071, 7074, 7078,
7081−7084, 7087, 7095−7098, 7107, 7112, 7118, 7120, 7124, 7126, 7144, 7153, 7155,
7160−7161, 7164, 7166, 7170, 7177, 7182−7184, 7197−7198, 7201, 7223, 7234, 7237, 7272,
7295−7297, 7300−7328, 7330−7350, 7352−7364, 7366−7370, 7372, 7374−7377, 7379−7385,
7387−7390, 7392−7393, 7395−7402, 7404−7406, 7408−7412, 7414−7418, 7420−7430,
7432−7435, 7437−7438, 7440−7441, 7443−7448, 7450−7463, 7465−7477, 7479, 7481−7485,
7487−7493, 7495−7498, 7500−7566, 7568−7569, 7571−7572, 7574−7582, 7584−7604, 7606,
7608−7616, 7618, 7620−7624, 7626−7628, 7631−7737, 7739−7845, 7847−7861, 7863,
7865−7900, 7903−7909, 7911−7972, 7974−7989, 8000−8045, 8047−8059, 8061−8064 and ON
A/C 7008, 7011−7014, 7017−7018, 7022, 7026−7031, 7034−7035, 7037−7038, 7040, 7042−7044,
7046, 7048, 7050, 7055−7056, 7062, 7066−7067, 7069−7070, 7072, 7076−7077, 7079−7080,
7085, 7088, 7091−7092, 7100−7102, 7105−7106, 7108−7109, 7111, 7115−7117, 7123, 7127,
7129, 7131−7133, 7137, 7139, 7141, 7143, 7145−7147, 7150−7151, 7154, 7156−7159,
7162−7163, 7168−7169, 7171−7175, 7178−7179, 7181, 7185−7188, 7191−7192, 7194−7196,
7199, 7202−7204, 7206−7219, 7221−7222, 7224−7225, 7227−7233, 7235−7236, 7238−7246,
7249−7265, 7267−7271, 7273−7281, 7284−7294 Post SB601R−24−090
COMPONENT NAME QTY ACCESS/ZONE REFERENCE
Adapter, refuel/defuel single−point 1 192BR, 192BB 28−25−01
Check valve, refuel/defuel 1 610BB, 192BR, 192BB 28−25−04
Circuit breakers:
FUEL DEFL, B6 1 CB−5/311 −
EMRG REFL, B7 1 CB−5/311 −

Master
EFFECTIVITY: See Pageblock 28−25−00 page 1
28−25−00 Page 8
Dec 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL

COMPONENT NAME QTY ACCESS/ZONE REFERENCE

Control panel, refuel/defuel 1 162AB 28−25−16
Restrictor 3 510BB, 610BB, 610AB 28−25−07
Sensor, high−level 3 510BB, 550FB, 650FB 28−25−13
Valve, refuel/defuel shutoff, center 1 610AB 28−25−07
tank
Valve, refuel/defuel shutoff, left main 1 510BB, 540AB 28−25−07
tank
Valve, refuel/defuel shutoff, right main 1 610BB, 640AB 28−25−07
tank

**ON A/C 7004−7007, 7009−7010, 7015−7016, 7019, 7021, 7023−7025, 7032−7033, 7036, 7039,
7041, 7052, 7059, 7061, 7063−7064, 7073, 7075, 7086, 7089−7090, 7093−7094, 7099,
7103−7104, 7110, 7113−7114, 7119, 7121−7122, 7125, 7128, 7130, 7134−7136, 7138, 7140,
7142, 7148−7149, 7152, 7165, 7167, 7176, 7180, 7189−7190, 7193, 7200, 7205, 7220, 7226,
7247−7248, 7266, 7282−7283 Pre SB601R−24−090
COMPONENT NAME QTY ACCESS/ZONE REFERENCE
Adapter, refuel/defuel single−point 1 192BR, 192BB 28−25−01
Check valve, refuel/defuel 1 610BB, 192BR, 192BB 28−25−04
Circuit breakers:
FUEL DEFL, B14 1 CB−5/311 −
EMRG REFL, B15 1 CB−5/311 −
Control panel, refuel/defuel 2 162AB, 222 28−25−16
Restrictor 3 510BB, 610BB, 610AB 28−25−07
Sensor, high−level 3 510BB, 550FB, 650FB 28−25−13
Valve, refuel/defuel shutoff, center 1 610AB 28−25−07
tank
Valve, refuel/defuel shutoff, left main 1 510BB, 540AB 28−25−07
tank
Valve, refuel/defuel shutoff, right main 1 610BB, 640AB 28−25−07
tank

**ON A/C 7003, 7298−7299, 7329, 7351, 7365, 7371, 7373, 7378, 7386, 7391, 7394, 7403, 7407,
7413, 7419, 7431, 7436, 7439, 7442, 7449, 7464, 7478, 7480, 7486, 7494, 7499, 7567, 7570,
7573, 7583, 7605, 7607, 7617, 7619, 7625, 7629−7630, 7738, 7846, 7862, 7864, 7901−7902,
7910, 7973, 7990, 8046, 8060, 8066−8068 and ON A/C 7004−7007, 7009−7010, 7015−7016,
7019, 7021, 7023−7025, 7032−7033, 7036, 7039, 7041, 7052, 7059, 7061, 7063−7064, 7073,
7075, 7086, 7089−7090, 7093−7094, 7099, 7103−7104, 7110, 7113−7114, 7119, 7121−7122,
7125, 7128, 7130, 7134−7136, 7138, 7140, 7142, 7148−7149, 7152, 7165, 7167, 7176, 7180,
7189−7190, 7193, 7200, 7205, 7220, 7226, 7247−7248, 7266, 7282−7283 Post SB601R−24−090
COMPONENT NAME QTY ACCESS/ZONE REFERENCE
Adapter, refuel/defuel single−point 1 192BR, 192BB 28−25−01
Check valve, refuel/defuel 1 610BB, 192BR, 192BB 28−25−04
Circuit breakers:

Master
EFFECTIVITY: See Pageblock 28−25−00 page 1
28−25−00 Page 9
Dec 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL

COMPONENT NAME QTY ACCESS/ZONE REFERENCE

FUEL DEFL, B6 1 CB−5/311 −
EMRG REFL, B7 1 CB−5/311 −
Control panel, refuel/defuel 2 162AB, 222 28−25−16
Restrictor 3 510BB, 610BB, 610AB 28−25−07
Sensor, high−level 3 510BB, 550FB, 650FB 28−25−13
Valve, refuel/defuel shutoff, center 1 610AB 28−25−07
tank
Valve, refuel/defuel shutoff, left main 1 510BB, 540AB 28−25−07
tank
Valve, refuel/defuel shutoff, right main 1 610BB, 640AB 28−25−07
tank

Master
EFFECTIVITY: See Pageblock 28−25−00 page 1
28−25−00 Page 10
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

C B
A

LAMP
CL OP SOV CL OP SOV CL OP
ON ON DEFUEL TEST

TEST

OFF OFF FUEL OFF

ON MANUAL
H.LEVEL DETECTOR FUEL AUTO
RIGHT LEFT

POWER
PRES. TOTAL QTY
INC. ON
FUEL QTY
FAULT BITE
ANNUNC. INITIA. DEC. OFF

A REFUEL/DEFUEL CONTROL PANEL

ram2825000_004(1).dg, jc, 27/10/99

B REFUEL/DEFUEL
C REFUEL/DEFUEL CHECK VALVE
SINGLE−POINT ADAPTER

Pressure Refuel/Defuel System Refueling − Component Location/Recognition

Figure 1

Master
EFFECTIVITY: See Pageblock 28−25−00 page 1
28−25−00 Page 11
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

LAMP
CL OP SOV CL OP SOV CL OP
ON ON DEFUEL TEST

TEST

OFF OFF FUEL OFF

ON MANUAL
H.LEVEL DETECTOR FUEL AUTO
RIGHT LEFT

POWER
PRES. TOTAL QTY
INC. ON
FUEL QTY
FAULT BITE
ANNUNC. INITIA. DEC. OFF

A REFUEL/DEFUEL CONTROL PANEL

B REFUEL/DEFUEL
SINGLE−POINT ADAPTER
ram2825000_006.dc, dc/kms, 31/08/95

C REFUEL/DEFUEL CHECK VALVE

Pressure Refuel/Defuel System Refueling − Component Location/Recognition

Figure 2

Master
EFFECTIVITY: See Pageblock 28−25−00 page 1
28−25−00 Page 12
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

B
A
B
A
A

RESTRICTOR

A REFUEL
SHUTOFF VALVE

ram2825000_005(1).dc, jp, 31/08/95

B HIGH−LEVEL SENSOR

Pressure Refuel/Defuel System − Component Location/Recognition

Figure 3

Master
EFFECTIVITY: See Pageblock 28−25−00 page 1
28−25−00 Page 13
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

REFUEL RESTRICTOR
SHUTOFF VALVE REFUEL/DEFUEL
REFUEL/DEFUEL CHECK VALVE
SINGLE−POINT
ADAPTER
RESTRICTOR

REFUEL
SHUTOFF VALVE
HIGH−LEVEL REFUEL
SENSOR SHUTOFF VALVE

PRESSURE RELIEF
HIGH−LEVEL (PIN HOLE) IN
SENSOR RH MAIN

HIGH−LEVEL
SENSOR

ram2825000_001(1).dg, ks/kms, 31/08/95

Pressure Refuel/Defuel System − Schematic

Figure 4

Master
EFFECTIVITY: See Pageblock 28−25−00 page 1
28−25−00 Page 14
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

TRANSFER
SYSTEM
(28−13−00)

APU FUEL
REFUEL/

TEST SIGNALS
FEED
DEFUEL
FUEL SYSTEM
CONTROL
TANK (28−24−00)
QTY’S PANEL

FUEL QTY

COMMAND

STATUS
GAUGING
SYSTEM
(28−41−00)

FUEL SYSTEM COMPUTER

RESPONSE

RESPONSE

RESPONSE
COMMAND

COMMAND

COMMAND
EXCITER

EXCITER
EXCITER
STATUS

STATUS

STATUS

HI− HI− HI−

REFUEL LEVEL REFUEL LEVEL REFUEL LEVEL
SOV SENSOR SOV SENSOR SOV SENSOR

ram2825000_002(1).dg, ks/gd, 11/03/93

Pressure Refuel/Defuel System − Electrical Schematic

Figure 5

Master
EFFECTIVITY: See Pageblock 28−25−00 page 1
28−25−00 Page 15
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

192 192 162AB

BB BR
610AB

510BB

610BB 540AB

640AB

550FB
650FB

NOTE
500 series panels are on the left side.
600 series panels are on the right side.
ram2825000_003(2).dg, ks/rm, 29/07/97

Pressure Refuel/Defuel System − Component Access

Figure 6

Master
EFFECTIVITY: See Pageblock 28−25−00 page 1
28−25−00 Page 16
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C ALL
PRESSURE REFUEL/DEFUEL SYSTEM − ADJUSTMENT/TEST

1. General
A. The maintenance procedure that follows is for the operational test of the pressure
refuel/defuel system. The test is done at the refuel/defuel control panel.
NOTE: It is necessary to apply fuel pressure to the pressure refuel/defuel system to do
this test.

TASK 28−25−00−710−801
Operational Test of the Refuel/Defuel System

1.
Subtask 28−25−00−946−006
A. Reference Information
REFERENCE DESIGNATION
TASK 10−11−00−869−801 Grounding of the Aircraft
TASK 12−00−07−861−801 Connect External AC Power
TASK 12−00−07−861−802 Remove External AC Power
TASK 12−11−28−910−801 Safety Precautions
FIM 28−40−00 Fault isolation manual, indicating system

2. Job Set−Up
**ON A/C 7004−7019, 7021−7044, 7046, 7048, 7050, 7052, 7055−7056, 7059, 7061−7064,
7066−7067, 7069−7070, 7072−7073, 7075−7077, 7079−7080, 7085−7086, 7088−7094,
7099−7106, 7108−7111, 7113−7117, 7119, 7121−7123, 7125, 7127−7143, 7145−7152, 7154,
7156−7159, 7162−7163, 7165, 7167−7169, 7171−7176, 7178−7181, 7185−7196, 7199−7200,
7202−7222, 7224−7233, 7235−7236, 7238−7271, 7273−7294 Pre SB601R−24−090

Subtask 28−25−00−865−001
A. Make sure that the circuit breakers that follow are closed:
CB PANEL CB NO. NAME ZONE
CBP−1 M12 FUEL SYST CONT 221
CBP−4 B10 FUEL SYST CONT 222
CBP−5 B14 FUEL DEFL 311
CBP−5 B15 EMRG REFL 311

Master
EFFECTIVITY: See Pageblock 28−25−00 page 501
28−25−00 Page 501
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C 7003, 7020, 7045, 7047, 7049, 7051, 7053−7054, 7057−7058, 7060, 7065, 7071, 7074,
7078, 7081−7084, 7087, 7095−7098, 7107, 7112, 7118, 7120, 7124, 7126, 7144, 7153, 7155,
7160−7161, 7164, 7166, 7170, 7177, 7182−7184, 7197−7198, 7201, 7223, 7234, 7237, 7272,
7295−7990, 8000−8064, 8066−8068 and ON A/C 7004−7019, 7021−7044, 7046, 7048, 7050,
7052, 7055−7056, 7059, 7061−7064, 7066−7067, 7069−7070, 7072−7073, 7075−7077,
7079−7080, 7085−7086, 7088−7094, 7099−7106, 7108−7111, 7113−7117, 7119, 7121−7123,
7125, 7127−7143, 7145−7152, 7154, 7156−7159, 7162−7163, 7165, 7167−7169, 7171−7176,
7178−7181, 7185−7196, 7199−7200, 7202−7222, 7224−7233, 7235−7236, 7238−7271,
7273−7294 Post SB601R−24−090

Subtask 28−25−00−865−002
B. Make sure that the circuit breakers that follow are closed:
CB PANEL CB NO. NAME ZONE
CBP−1 M12 FUEL SYST CONT 221
CBP−4 B10 FUEL SYST CONT 222
CBP−5 B6 FUEL DEFL 311
CBP−5 B7 EMRG REFL 311

**ON A/C ALL

Subtask 28−25−00−010−001
C. Open the access door that follows:
ACCESS DESCRIPTION
192BR Pressure−refuel adapter door
D. Open the access panel that follows:
ACCESS DESCRIPTION
162AB Refuel/defuel control panel

Subtask 28−25−00−861−001
E. Connect the external AC power (Ref. TASK 12−00−07−861−801).
NOTE: The external ground power may be used, but the aircraft battery power is
recommended.

Master
EFFECTIVITY: See Pageblock 28−25−00 page 501
28−25−00 Page 502
Dec 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
3. Procedure
**ON A/C 7008, 7011−7014, 7017−7018, 7020, 7022, 7026−7031, 7034−7035, 7037−7038, 7040,
7042−7051, 7053−7058, 7060, 7062, 7065−7067, 7069−7072, 7074, 7076−7085, 7087−7088,
7091−7092, 7095−7098, 7100−7102, 7105−7109, 7111−7112, 7115−7118, 7120, 7123−7124,
7126−7127, 7129, 7131−7132, 7137, 7139, 7141, 7143−7147, 7150−7151, 7153−7164, 7166,
7168−7175, 7177−7179, 7181−7188, 7191−7192, 7194−7199, 7201−7204, 7206−7219,
7221−7225, 7227−7246, 7249−7265, 7267−7281, 7284−7297, 7300−7328, 7330−7350,
7352−7364, 7366−7370, 7372, 7374−7377, 7379−7385, 7387−7390, 7392−7393, 7395−7402,
7404−7406, 7408−7412, 7414−7418, 7420−7430, 7432−7435, 7437−7438, 7440−7441,
7443−7448, 7450−7463, 7465−7477, 7479, 7481−7485, 7487−7493, 7495−7498, 7500−7566,
7568−7569, 7571−7572, 7574−7582, 7584−7604, 7606, 7608−7616, 7618, 7620−7624,
7626−7628, 7631−7737, 7739−7845, 7847−7861, 7863, 7865−7900, 7903−7909, 7911−7972,
7974−7989, 8000−8045, 8047−8059, 8061−8064 and ON A/C 7226 Pre SB601R−28−034

Subtask 28−25−00−710−001
Refer to Figure 501.
CAUTION: STOP THE REFUEL OPERATION IMMEDIATELY IF THE TEST CONDITIONS
THAT FOLLOW DO NOT OCCUR. IF YOU DO NOT DO THIS, YOU CAN CAUSE
DAMAGE TO THE EQUIPMENT.
A. The procedure below describes the operational test of the pressure refuel/defuel system
and of the refuel/defuel control panel.
B. Do the operational test of the pressure refuel/defuel system and of the refuel/defuel
control panel as follows:
WARNING: MAKE SURE THAT THE FUEL TENDER, THE AIRCRAFT, AND THE
FUEL NOZZLE ARE GROUNDED BEFORE YOU REFUEL/DEFUEL
THE AIRCRAFT. A STATIC ELECTRIC SPARK DURING THE
REFUELING/DEFUELING CAN CAUSE AN EXPLOSION OR FIRE.
(1) Make sure that the aircraft is grounded (Ref. TASK 10−11−00−869−801).
(2) Make sure that the fuel nozzle and the fuel tender are grounded.
(3) Remove the cap from the refuel/defuel single−point adapter (1) and connect the fuel
nozzle from the fuel tender.
NOTE: Make sure that the fuel pressure on the fuel tender is set to 50 ± 5 psi
(345 ± 34 kPa) maximum.
(4) Make sure that the three ON−OFF refuel−shutoff−valve (SOV) toggle switches (2)
are set to OFF.
(5) Make sure that the ON−OFF refuel start switch (3) is set to OFF.
(6) Obey all the refuel/defuel safety precautions (Ref. TASK 12−11−28−910−801).
(7) Lift the guard off the POWER toggle switch (4).
(8) Set the POWER toggle switch (4) to on. Make sure that the POWER ON indicator
light (5) comes on.
NOTE: Make sure that the FAULT ANNUNC. indicator light (6) is not on. If it is
on, refer to the Fault Isolation Manual (Ref. FIM 28−40−00). When the AC
power is selected ON the AUTO XFLOW INHIBIT white status message
will be shown on the EICAS statutory page.

Master
EFFECTIVITY: See Pageblock 28−25−00 page 501
28−25−00 Page 503
Dec 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
(9) Push and hold the LAMP−TEST pushbutton (7) and make sure that all the lights on
the refuel/defuel control panel come on.
(10) Release the LAMP−TEST pushbutton (7) and make sure that the POWER ON
indicator light (5) stays on and that all the other lights on the refuel/defuel control
panel go off.
(11) Push and release the BITE INITIA. pushbutton (8).
(12) Make sure that the RIGHT, CTR and LEFT fuel−tank quantity displays (9) show
888.
(13) Make sure that the PRES. TOTAL QTY preselected−fuel quantity display (10)
shows 888.
(14) Start the fuel tender and open the manual shutoff valve on the fuel nozzle to apply
pressure to the fuel system.
(15) Set the mode selector switch (11) to TEST.
(16) Make sure that the three shutoff−valve (SOV) indicator−lights CL (12) are off.
(17) Make sure that the three shutoff−valve (SOV) indicator−lights OP (13) come on for
approximately 5 to 20 seconds in sequence.
(18) Make sure that the related three H.LEVEL DETECTOR indicator lights (14) also
come on and then go off in sequence.
(19) Make sure that the three SOV indicator−lights OP (13) go off and that the three
SOV indicator−lights CL (12) come on.
(20) Make sure that the FAULT ANNUNC. indicator light (6) has not come on. If it has
come on, do as follows:
(a) Push and hold the BITE INITIA. pushbutton (8) for a minimum of 30 seconds.
(b) Look at the quantity displays (9) and (10) for the codes.
(c) Write these codes and refer to the Fault Isolation Manual (Ref. FIM
28−40−00).
(d) Release the BITE INITIA. pushbutton (8).
(21) Set the mode selector switch (11) to OFF.
(22) Set the POWER toggle switch (4) to OFF and lower the guard.
NOTE: If the POWER toggle switch is left to ON an AUTO XFLOW INHIBIT
status message will be displayed on EICAS.
(23) Make sure that the POWER ON indicator light (5) goes off.

Master
EFFECTIVITY: See Pageblock 28−25−00 page 501
28−25−00 Page 504
Dec 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C 7003−7007, 7009−7010, 7015−7016, 7019, 7021, 7023−7025, 7032−7033, 7036, 7039,
7041, 7052, 7059, 7061, 7063−7064, 7073, 7075, 7086, 7089−7090, 7093−7094, 7099,
7103−7104, 7110, 7113−7114, 7119, 7121−7122, 7125, 7128, 7130, 7133−7136, 7138, 7140,
7142, 7148−7149, 7152, 7165, 7167, 7176, 7180, 7189−7190, 7193, 7200, 7205, 7220,
7247−7248, 7266, 7282−7283, 7298−7299, 7329, 7351, 7365, 7371, 7373, 7378, 7386, 7391,
7394, 7403, 7407, 7413, 7419, 7431, 7436, 7439, 7442, 7449, 7464, 7478, 7480, 7486, 7494,
7499, 7567, 7570, 7573, 7583, 7605, 7607, 7617, 7619, 7625, 7629−7630, 7738, 7846, 7862,
7864, 7901−7902, 7910, 7973, 7990, 8046, 8060, 8066−8068 and ON A/C 7226 Post
SB601R−28−034

Subtask 28−25−00−710−002
Refer to Figure 501.
CAUTION: STOP THE REFUEL OPERATION IMMEDIATELY IF THE TEST CONDITIONS
THAT FOLLOW DO NOT OCCUR. IF YOU DO NOT DO THIS, YOU CAN CAUSE
DAMAGE TO THE EQUIPMENT.
C. The procedure below describes the operational test of the pressure refuel/defuel system
and both refuel/defuel control panels. Do the tests of the cockpit and the right
wing/fuselage refuel/defuel control panels independently.
D. Do the operational test of the pressure refuel/defuel system and of the refuel/defuel
control panels as follows:
WARNING: MAKE SURE THAT THE FUEL TENDER, THE AIRCRAFT, AND THE
FUEL NOZZLE ARE GROUNDED BEFORE YOU REFUEL/DEFUEL
THE AIRCRAFT. A STATIC ELECTRIC SPARK DURING THE
REFUELING/DEFUELING CAN CAUSE AN EXPLOSION OR FIRE.
(1) Make sure that the aircraft is grounded (Ref. TASK 10−11−00−869−801).
(2) Make sure that the fuel nozzle and the fuel tender are grounded.
(3) Remove the cap from the refuel/defuel single−point adapter (1) and connect the fuel
nozzle from the fuel tender.
NOTE: Make sure that the fuel pressure on the fuel tender is set to 50 ± 5 psi
(345 ± 34 kPa) maximum.
(4) Make sure that the three ON−OFF refuel−shutoff−valve (SOV) toggle switches (2)
are set to OFF.
(5) Make sure that the ON−OFF refuel start switch (3) is set to OFF.
(6) Obey all the refuel/defuel safety precautions (Ref. TASK 12−11−28−910−801).
(7) Lift the guard off the POWER toggle switch (4).
(8) Set the POWER toggle switch (4) to on. Make sure that the POWER ON indicator
light (5) comes on.
NOTE: Make sure that the FAULT ANNUNC. indicator light (6) is not on. If it is
on, refer to the Fault Isolation Manual (Ref. FIM 28−40−00).
(9) Push and hold the LAMP−TEST pushbutton (7) and make sure that all the lights on
the refuel/defuel control panel come on.
(10) Release the LAMP−TEST pushbutton (7) and make sure that the POWER ON
indicator light (5) stays on and that all the other lights on the refuel/defuel control
panel go off.

Master
EFFECTIVITY: See Pageblock 28−25−00 page 501
28−25−00 Page 505
Dec 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
(11) Push and release the BITE INITIA. pushbutton (8).
(12) Make sure that the RIGHT, CTR and LEFT fuel−tank quantity displays (9) show
888.
(13) Make sure that the PRES. TOTAL QTY preselected−fuel quantity display (10)
shows 888.
(14) Start the fuel tender and open the manual shutoff valve on the fuel nozzle to apply
pressure to the fuel system.
(15) Set the mode selector switch (11) to TEST.
(16) Make sure that the three shutoff−valve (SOV) indicator−lights CL (12) are off.
(17) Make sure that the three shutoff−valve (SOV) indicator−lights OP (13) come on for
approximately 5 to 20 seconds in sequence.
(18) Make sure that the related three H.LEVEL DETECTOR indicator lights (14) also
come on and then go off in sequence.
(19) Make sure that the three SOV indicator−lights OP (13) go off and that the three
SOV indicator−lights CL (12) come on.
(20) Make sure that the FAULT ANNUNC. indicator light (6) has not come on. If it has
come on, do as follows:
(a) Push and hold the BITE INITIA. pushbutton (8) for a minimum of 30 seconds.
(b) Look at the quantity displays (9) and (10) for the codes.
(c) Write these codes and refer to the Fault Isolation Manual (Ref. FIM
28−40−00).
(d) Release the BITE INITIA. pushbutton (8).
(21) Set the mode selector switch (11) to OFF.
(22) Set the POWER toggle switch (4) to off and lower the guard.
NOTE: If the POWER toggle switch is left to ON an AUTO XFLOW INHIBIT
status message will be displayed on EICAS.
(23) Make sure that the POWER ON indicator light (5) goes off.
**ON A/C ALL

4. Close Out
Subtask 28−25−00−861−002
A. Remove the external AC power, if used (Ref. TASK 12−00−07−861−802).

Subtask 28−25−00−410−001
B. Close the access door that follows:
ACCESS DESCRIPTION
192BR Pressure−refueling adapter door
C. Close the access panel that follows:

Master
EFFECTIVITY: See Pageblock 28−25−00 page 501
28−25−00 Page 506
Dec 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL

ACCESS DESCRIPTION
162AB Fuel/defuel control panel

Subtask 28−25−00−840−003
Refer to Figure 502.
D. Remove the grounding wire as follows:
(1) If the grounding wire has an alligator clamp, remove the clamp from the grounding
lug (1) on the right side wall of the nose landing gear (NLG) compartment.
(2) If the grounding wire has an alligator stud, remove the stud from the nearest
grounding stud receptacle (2) on the wing leading edge.

Subtask 28−25−00−840−004
E. Disconnect the fuel nozzle and install the cap to the single−point adapter (1).
F. Disconnect the fuel nozzle and tender ground.

Master
EFFECTIVITY: See Pageblock 28−25−00 page 501
28−25−00 Page 507
Dec 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL

LEGEND
1. Refuel/defuel single−
point adapter.
2. Refuel SOV toggle−switch.
3. Refuel start switch.
4. Toggle switch.
5. Indicator light.
6. Indicator light.
7. Pushbutton. 1
8. Pushbutton. A
9. Fuel−tank quantity display.
B
10. Preselected−fuel quantity display.
11. Mode selector switch.
12. SOV indicator light.
13. SOV indicator light.
14. Indicator light.

PRESSURE−REFUEL
A
ADAPTER DOOR

2 12 13 12 2 13 12 13 2 11

7
LAMP
CL OP SOV CL OP SOV CL OP
ON ON DEFUEL TEST
5
TEST

OFF OFF FUEL OFF

ON MANUAL
H.LEVEL DETECTOR FUEL AUTO
14 RIGHT CTR LEFT

POWER
PRES. TOTAL QTY
INC. ON
FUEL QTY
FAULT BITE
4 ANNUNC. INITIA. DEC. OFF
ram2825005_001.dg, jp/rm, 04/03/97

9 6 14 9 14 8 9 3 10

B REFUEL/DEFUEL CONTROL PANEL

Pressure Refuel/Defuel System − Adjustment/Test

Figure 501

Master
EFFECTIVITY: See Pageblock 28−25−00 page 501
28−25−00 Page 508
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

LEGEND.
1. Grounding lug.
2. Ground stud receptacle.

B B

FW
D

ram1011002_004(1).dg, ab/gg, 02/11/00

B
A

Grounding of the Aircraft − Maintenance Practices

Figure 502

Master
EFFECTIVITY: See Pageblock 28−25−00 page 501
28−25−00 Page 509
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C ALL
ADAPTER, REFUELING − REMOVAL/INSTALLATION

1. General
A. The maintenance procedures that follow are for the removal and installation of the
refueling adapter. There is one refueling adapter in the fuel system. It is installed in the
right leading edge, at the junction between the wing and the fuselage. The refueling
adapter is connected to the refuel/defuel check valve.
B. Because a small amount of fuel can flow from the right hand tank pressure relief line to
the refuel/defuel manifold, defueling of the right hand main tank should be carried out
before removing or installing the refuelling adapter.

TASK 28−25−01−000−801
Removal of the Refueling Adapter

1. Job Set−Up Information

Subtask 28−25−01−943−001
A. Tools and Equipment
REFERENCE DESIGNATION
None specified Container, fuel

Subtask 28−25−01−946−001
B. Reference Information
REFERENCE DESIGNATION
TASK 20−30−00−910−802 Wiggins Couplings − Maintenance Practices
TASK 28−00−00−910−801 Fuel Safety Precautions
TASK 53−82−01−000−802 Removal of the Right Forward Wing−to− Fuselage
Fairing

2. Job Set−Up
Subtask 28−25−01−910−001
WARNING: OBEY ALL THE FUEL SAFETY PRECAUTIONS WHEN YOU DO WORK ON THE
FUEL SYSTEM AND/OR A FUEL SYSTEM COMPONENT. IF YOU DO NOT DO
THIS, YOU CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO
EQUIPMENT.
A. Obey all the fuel safety precautions (Ref. TASK 28−00−00−910−801).

Master
EFFECTIVITY: See Pageblock 28−25−01 page 401
28−25−01 Page 401
Sep 10/2004
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C 7004−7019, 7021−7044, 7046, 7048, 7050, 7052, 7055−7056, 7059, 7061−7064,
7066−7067, 7069−7070, 7072−7073, 7075−7077, 7079−7080, 7085−7086, 7088−7094,
7099−7106, 7108−7111, 7113−7117, 7119, 7121−7123, 7125, 7127−7143, 7145−7152, 7154,
7156−7159, 7162−7163, 7165, 7167−7169, 7171−7176, 7178−7181, 7185−7196, 7199−7200,
7202−7222, 7224−7233, 7235−7236, 7238−7271, 7273−7294 Pre SB601R−24−090

Subtask 28−25−01−865−001
B. Open, safety, and tag the circuit breakers that follow:
CB PANEL CB NO. NAME ZONE
CBP−1 M12 FUEL SYST CONT 221
CBP−4 B10 FUEL SYST CONT 222
CB−5 B14 FUEL DEFL 311
CB−5 B15 EMRG REFL 311

**ON A/C 7003, 7020, 7045, 7047, 7049, 7051, 7053−7054, 7057−7058, 7060, 7065, 7071, 7074,
7078, 7081−7084, 7087, 7095−7098, 7107, 7112, 7118, 7120, 7124, 7126, 7144, 7153, 7155,
7160−7161, 7164, 7166, 7170, 7177, 7182−7184, 7197−7198, 7201, 7223, 7234, 7237, 7272,
7295−7990, 8000−8064, 8066−8068 and ON A/C 7004−7019, 7021−7044, 7046, 7048, 7050,
7052, 7055−7056, 7059, 7061−7064, 7066−7067, 7069−7070, 7072−7073, 7075−7077,
7079−7080, 7085−7086, 7088−7094, 7099−7106, 7108−7111, 7113−7117, 7119, 7121−7123,
7125, 7127−7143, 7145−7152, 7154, 7156−7159, 7162−7163, 7165, 7167−7169, 7171−7176,
7178−7181, 7185−7196, 7199−7200, 7202−7222, 7224−7233, 7235−7236, 7238−7271,
7273−7294 Post SB601R−24−090

Subtask 28−25−01−865−003
C. Open, safety, and tag the circuit breakers that follow:
CB PANEL CB NO. NAME ZONE
CBP−1 M12 FUEL SYST CONT 221
CBP−4 B10 FUEL SYST CONT 222
CB−5 B6 FUEL DEFL 311
CB−5 B7 EMRG REFL 311

**ON A/C ALL

Subtask 28−25−01−010−001
D. Open the access door that follows:
ACCESS DESIGNATION
192BR Pressure fueling door
E. Remove the access panel that follows (Ref. TASK 53−82−01−000−802):

Master
EFFECTIVITY: See Pageblock 28−25−01 page 401
28−25−01 Page 402
Dec 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL

ACCESS DESIGNATION
192BB Right forward wing−to−fuselage fairing

Subtask 28−25−01−490−001
F. Put a fuel container below the refueling adapter.

3. Procedure
Subtask 28−25−01−020−001
Refer to Figure 401.
A. Remove the refueling adapter as follows:
(1) Remove the bolts (5), the washers (6), the retaining ring (7), and the gasket (8)
from the refueling adapter (9).
(2) Loosen the clamp (1) and move the shroud (2) to disconnect the coupling (3).
(3) Disconnect the coupling (3) and remove the retainer (4) (Ref. TASK
20−30−00−910−802).
(4) Remove the refueling adapter (9).
(5) Remove the preformed packings (10) from the refueling adapter (9) and the tube
assembly. Discard the preformed packings.
(6) Remove the split ring (11) and the coupling (3) from the refueling adapter (9).

Master
EFFECTIVITY: See Pageblock 28−25−01 page 401
28−25−01 Page 403
Sep 10/2004
 C
AIRCRAFT MAINTENANCE MANUAL

2
TUBE
ASSEMBLY 10
(REF) 4
10
11 9
3
8
7
LEGEND.
1. Clamp
2. Shroud
3. Coupling
4. Retainer
5. Bolt
6. Washer
7. Retaining ring
8. Gasket
ram2825014_001.dc, CR, rf, 5/11/91

9. Refeuling adapter
10. Preformed packing
11. Split ring

6
5

Refueling Adapter − Removal/Installation

Figure 401

Master
EFFECTIVITY: See Pageblock 28−25−01 page 401
28−25−01 Page 404
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
TASK 28−25−01−400−801
Installation of the Refueling Adapter

1. Job Set−Up Information

Subtask 28−25−01−945−001
A. Parts
REF NAME OF PART QTY IPC SEQUENCE NO.
10 Preformed packing 2 IPC 28−25−00−1A−035

Subtask 28−25−01−946−002
B. Reference Information
REFERENCE DESIGNATION
TASK 20−30−00−910−802 Wiggins Couplings − Maintenance Practices
TASK 53−82−01−400−802 Installation of the Right Forward Wing−to−
Fuselage Fairing
TASK 28−25−00−710−801 Operational Test of the Pressure Refuel/Defuel
System

2. Procedure
Subtask 28−25−01−869−001
A. Make sure that the aircraft is in the same configuration as in the removal task.

Subtask 28−25−01−420−001
Refer to Figure 401.
B. Install the refueling adapter as follows:
NOTE: For Wiggins coupling installation procedures, refer to Wiggins Couplings −
Maintenance Practices (Ref. TASK 20−30−00−910−802).
(1) Install the coupling (3) and the split ring (11) on the refueling adapter (9).
(2) Lubricate and install the preformed packings (10) on the refueling adapter (9) and
the tube assembly.
(3) Install the refueling adapter (9).
(4) Connect the shroud (2) to the coupling (3) and tighten the clamp (1).
(5) Install the gasket (8), the retaining ring (7), the washers (6), and the bolts (5) on the
refueling adapter (9). Make sure that the notch on the retaining ring is installed
adjacent to the chain on the adapter assembly.
(6) Install the retainer (4) and connect the coupling (3).

Master
EFFECTIVITY: See Pageblock 28−25−01 page 401
28−25−01 Page 405
Sep 10/2004
 C
AIRCRAFT MAINTENANCE MANUAL
3. Close Out
Subtask 28−25−01−410−001
A. Install the access panel that follows (Ref. TASK 53−82−01−400−802):
ACCESS DESIGNATION
152AR Right forward wing−to−fuselage fairing

**ON A/C 7004−7019, 7021−7044, 7046, 7048, 7050, 7052, 7055−7056, 7059, 7061−7064,
7066−7067, 7069−7070, 7072−7073, 7075−7077, 7079−7080, 7085−7086, 7088−7094,
7099−7106, 7108−7111, 7113−7117, 7119, 7121−7123, 7125, 7127−7143, 7145−7152, 7154,
7156−7159, 7162−7163, 7165, 7167−7169, 7171−7176, 7178−7181, 7185−7196, 7199−7200,
7202−7222, 7224−7233, 7235−7236, 7238−7271, 7273−7294 Pre SB601R−24−090

Subtask 28−25−01−865−002
B. Remove the tags and close the circuit breakers that follow:
CB PANEL CB NO. NAME ZONE
CBP−1 M12 FUEL SYST CONT 221
CBP−4 B10 FUEL SYST CONT 222
CB−5 B14 FUEL DEFL 311
CB−5 B15 EMRG REFL 311

**ON A/C 7003, 7020, 7045, 7047, 7049, 7051, 7053−7054, 7057−7058, 7060, 7065, 7071, 7074,
7078, 7081−7084, 7087, 7095−7098, 7107, 7112, 7118, 7120, 7124, 7126, 7144, 7153, 7155,
7160−7161, 7164, 7166, 7170, 7177, 7182−7184, 7197−7198, 7201, 7223, 7234, 7237, 7272,
7295−7990, 8000−8064, 8066−8068 and ON A/C 7004−7019, 7021−7044, 7046, 7048, 7050,
7052, 7055−7056, 7059, 7061−7064, 7066−7067, 7069−7070, 7072−7073, 7075−7077,
7079−7080, 7085−7086, 7088−7094, 7099−7106, 7108−7111, 7113−7117, 7119, 7121−7123,
7125, 7127−7143, 7145−7152, 7154, 7156−7159, 7162−7163, 7165, 7167−7169, 7171−7176,
7178−7181, 7185−7196, 7199−7200, 7202−7222, 7224−7233, 7235−7236, 7238−7271,
7273−7294 Post SB601R−24−090

Subtask 28−25−01−865−004
C. Remove the tags and close the circuit breakers that follow:
CB PANEL CB NO. NAME ZONE
CBP−1 M12 FUEL SYST CONT 221
CBP−4 B10 FUEL SYST CONT 222
CB−5 B6 FUEL DEFL 311
CB−5 B7 EMRG REFL 311

Master
EFFECTIVITY: See Pageblock 28−25−01 page 401
28−25−01 Page 406
Dec 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C ALL

Subtask 28−25−01−710−001
D. Do an operational test of the refueling adapter (Ref. TASK 28−25−00−710−801).

Subtask 28−25−01−941−001
E. Close the access door that follows:
ACCESS DESIGNATION
192BR Pressure fueling door
F. Remove all tools, equipment, and unwanted materials from the area.

Master
EFFECTIVITY: See Pageblock 28−25−01 page 401
28−25−01 Page 407
Sep 10/2004
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C ALL
CHECK VALVE, REFUEL/DEFUEL − REMOVAL/INSTALLATION

1. General
A. The maintenance procedures that follow are for the removal and installation of the
refuel/defuel check valve (written as the "check valve" in this procedure). There is one
check valve in the fuel system. It is attached to the right forward bulkhead of the center
tank. It is connected to the refuel/defuel adapter.
B. It is necessary to defuel, drain, and remove the fuel fumes from the right hand tank and
the center tank to remove or install the check valve.

TASK 28−25−04−000−801
Removal of the Refuel/Defuel Check Valve

1. Job Set−Up Information

Subtask 28−25−04−943−001
A. Tools and Equipment
REFERENCE DESIGNATION
None specified Container, 5−U.S. gallon (20 L)

Subtask 28−25−04−946−001
B. Reference Information
REFERENCE DESIGNATION
TASK 12−11−28−650−804 Suction Defueling
TASK 20−30−00−910−802 Wiggins Couplings − Maintenance Practices
TASK 28−00−00−910−801 Fuel Safety Precautions
TASK 28−11−00−840−801 Prepare Fuel Tank for Access
TASK 28−11−00−840−802 Removal of Fuel Fumes
TASK 28−11−01−000−802 Removal of the Graphite Access Panel
TASK 53−82−01−000−802 Removal of the Right Forward Wing−to− Fuselage
Fairing

Master
EFFECTIVITY: See Pageblock 28−25−04 page 401
28−25−04 Page 401
Sep 10/2004
 C
AIRCRAFT MAINTENANCE MANUAL
2. Job Set−Up
Subtask 28−25−04−910−001
WARNING: OBEY ALL THE FUEL SAFETY PRECAUTIONS WHEN YOU DO WORK ON THE
FUEL SYSTEM AND/OR A FUEL SYSTEM COMPONENT. IF YOU DO NOT DO
THIS, YOU CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO
EQUIPMENT.
A. Obey all the fuel safety precautions (Ref. TASK 28−00−00−910−801).

Subtask 28−25−04−650−001
B. Defuel the center tank (Ref. TASK 12−11−28−650−804).

Subtask 28−25−04−010−001
C. Remove the access panel that follows (Ref. TASK 28−11−01−000−802):
ACCESS DESIGNATION
610AB Fuel tank access panel
D. Remove the access panel that follows (Ref. TASK 53−82−01−000−802):
ACCESS DESIGNATION
192BB Right forward wing−to−fuselage fairing
E. Open the refuel access door 192BR.

Subtask 28−25−04−840−001
F. Prepare the center tank for access (Ref. TASK 28−11−00−840−801).
G. Remove the fuel fumes from the center tank (Ref. TASK 28−11−00−840−802).

Subtask 28−25−04−680−001
H. Put a fuel container below the check valve.
I. Remove the fuel cap from the refueling adapter.
J. Use a blunt object to open the poppet assembly. Drain the fuel out of the check valve.

3. Procedure
Subtask 28−25−04−020−001
Refer to Figure 401.
A. Remove the shutoff valve as follows:
NOTE: For Wiggins coupling removal procedures, refer to Wiggins Couplings −
Maintenance Practices (Ref. TASK 20−30−00−910−802).
(1) Disconnect the coupling (1).
(2) Remove the retainer (2) and the preformed packings (3). Discard the preformed
packings.

Master
EFFECTIVITY: See Pageblock 28−25−04 page 401
28−25−04 Page 402
Sep 10/2004
 C
AIRCRAFT MAINTENANCE MANUAL
(3) Put a protective plug in the refuel manifold.
(4) Loosen the clamp (4) and move the shroud (5) to remove the bolts (6).
CAUTION: HOLD THE CHECK VALVE WHILE THE BOLTS ARE REMOVED. IF
THE CHECK VALVE FALLS, IT WILL CAUSE DAMAGE TO THE
ADJACENT STRUCTURE.
(5) Remove the bolts (6) and the washers (7).
(6) Remove the valve (8) and the preformed packings (9) and (10). Discard the
preformed packings.
(7) Remove the drain line (15), fitting (13), and the preformed packing (14). Discard the
preformed packing.
(8) Remove the split ring (11) and the coupling nut (12) from the valve (8).

Master
EFFECTIVITY: See Pageblock 28−25−04 page 401
28−25−04 Page 403
Sep 10/2004
 C
AIRCRAFT MAINTENANCE MANUAL

REFUEL
MANIFOLD
(REF)
1

3
2
3
11
12

6
8

14
13 4

14
5
15
10
9
LEGEND
1. Coupling. FLANGE
2. Retainer. (REF)
3. Preformed packing.
4. Clamp.
5. Shroud.
6. Bolt.
7. Washer.
ram2825044_001(2).dc, kms, 31/08/95

8. Check valve.
9. Preformed packing.
10. Preformed packing.
11. Split ring.
12. Coupling nut.
13. Fitting.
14. Preformed packing.
15. Drain line.

Refuel/Defuel Check Valve − Removal/Installation

Figure 401

Master
EFFECTIVITY: See Pageblock 28−25−04 page 401
28−25−04 Page 404
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
TASK 28−25−04−400−801
Installation of the Refuel/Defuel Check Valve

1. Job Set−Up Information

Subtask 28−25−04−945−001
A. Parts
REF NAME OF PART QTY IPC SEQUENCE NO.
3 Preformed packing 2 IPC 28−25−00−1A−035
9 Preformed packing 1 IPC 28−25−00−1A−100
10 Preformed packing 1 IPC 28−25−00−1A−110
14 Preformed packing 2 IPC 28−25−00−1A−050

Subtask 28−25−04−946−002
B. Reference Information
REFERENCE DESIGNATION
TASK 12−11−28−650−801 Automatic Pressure Refueling
TASK 12−11−28−650−804 Suction Defueling
TASK 12−11−28−650−803 Gravity Refueling
TASK 20−30−00−910−802 Wiggins Couplings − Maintenance Practices
TASK 28−11−01−400−802 Installation of the Graphite Access Panel
TASK 53−82−01−400−802 Installation of the Right Forward Wing−to−
Fuselage Fairing

2. Procedure
Subtask 28−25−04−869−001
A. Make sure that the aircraft is in the same configuration as in the removal task.

Subtask 28−25−04−420−001
Refer to Figure 401.
B. Install the check valve as follows:
NOTE: For Wiggins coupling installation procedures, refer to Wiggins Couplings −
Maintenance Practices (Ref. TASK 20−30−00−910−802).
(1) Install the coupling nut (12) and the split ring (11) on the valve (8).
(2) Lubricate and install the preformed packings (9) and (10) on the valve (8).
(3) Install the valve (8), the washers (7), and the bolts (6).
(4) Remove the protective plug from the refuel manifold.
(5) Lubricate and install the preformed packings (3) and the retainer (2).
(6) Connect the coupling (1).
(7) Lubricate and install the preformed packing (14) on the fitting (13). Install the fitting
(13) and the drain line (15) on the check valve (8).

Master
EFFECTIVITY: See Pageblock 28−25−04 page 401
28−25−04 Page 405
Sep 10/2004
 C
AIRCRAFT MAINTENANCE MANUAL
(8) Connect the shroud (5) to the flange and tighten the clamp (4).

3. Close Out
Subtask 28−25−04−410−001
A. Install the access panel that follows (Ref. TASK 28−11−01−400−802):
ACCESS DESIGNATION
610AB Fuel tank access panel

Subtask 28−25−04−210−001
B. Refuel the aircraft (Ref. TASK 12−11−28−650−801).
C. Examine the area around the refuel/defuel adapter for leaks.

Subtask 28−25−04−650−002
D. Defuel the aircraft (Ref. TASK 12−11−28−650−804).
E. Examine the area around the refuel/defuel adapter for leaks.

Subtask 28−25−04−650−003
F. Refuel the aircraft (Ref. TASK 12−11−28−650−803).

Subtask 28−25−04−410−002
G. Install the access panel that follows (Ref. TASK 53−82−01−400−802):
ACCESS DESIGNATION
192BB Right forward wing−to−fuselage fairing
H. Install the fuel cap on the refueling adapter.
I. Close the refuel access door 192BR.

Subtask 28−25−04−941−002
J. Remove all the tools, equipment, and unwanted materials from the area.

Master
EFFECTIVITY: See Pageblock 28−25−04 page 401
28−25−04 Page 406
Sep 10/2004
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C ALL
VALVE, REFUEL SHUTOFF − REMOVAL/INSTALLATION

1. General
A. The maintenance procedures that follow are for the removal and installation of the refuel
shutoff valve. There are three refuel shutoff valves in the fuel system. They are in the
center tank, connected to the refuel/defuel manifolds of the related fuel tank.
B. It is necessary to defuel, drain, and remove the fuel fumes from the center tank to
remove or install the refuel shutoff valves. Defuel, drain, and remove the fuel fumes from
the related main tank to remove or install the refuel shutoff valves of the main tanks.

TASK 28−25−07−000−801
Removal of the Refuel Shutoff Valve

1. Job Set−Up Information

Subtask 28−25−07−946−001
A. Reference Information
REFERENCE DESIGNATION
TASK 12−11−28−650−804 Suction Defueling
TASK 20−30−00−910−802 Wiggins Couplings − Maintenance Practices
TASK 28−00−00−910−801 Fuel Safety Precautions
TASK 28−11−00−840−801 Prepare Fuel Tank for Access
TASK 28−11−00−840−802 Removal of Fuel Fumes
TASK 28−11−01−000−802 Removal of the Graphite Access Panel
TASK 53−83−01−000−801 Removal of the MLG Wheel Bin
WM 20−12−00 Wiring − Installation
WM 20−17−10 Wiring Manual

2. Job Set−Up
Subtask 28−25−07−910−001
WARNING: OBEY ALL THE FUEL SAFETY PRECAUTIONS WHEN YOU DO WORK ON THE
FUEL SYSTEM AND/OR A FUEL SYSTEM COMPONENT. IF YOU DO NOT DO
THIS, YOU CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO
EQUIPMENT.
A. Obey all the fuel safety precautions (Ref. TASK 28−00−00−910−801).

Subtask 28−25−07−650−001
B. Defuel the center tank and the related main tank (Ref. TASK 12−11−28−650−804).

Master
EFFECTIVITY: See Pageblock 28−25−07 page 401
28−25−07 Page 401
Aug 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
Subtask 28−25−07−010−001
C. Remove the applicable access panels that follow (Ref. TASK 28−11−01−000−802):
ACCESS DESIGNATION ITEM
610AB Fuel tank access panel Center tank refuel shutoff valve
510BB Fuel tank access panel Left main tank refuel shutoff valve
540BB Fuel tank access panel Left main tank refuel shutoff valve
610BB Fuel tank access panel Right main tank refuel shutoff valve
640BB Fuel tank access panel Right main tank refuel shutoff valve
D. For the refuel shutoff valve of the center tank, remove the wheel bin from the right
landing gear well (Ref. TASK 53−83−01−000−801).
E. For the refuel shutoff valve of the left main tank, do the steps that follow:
(1) Remove the left wheel bin (163AZ) from the main wheel well (Ref. TASK
53−83−01−000−801).
(2) Prepare the left main tank for access (Ref. TASK 28−11−00−840−801).
(3) Remove the fuel fumes from the left main tank (Ref. TASK 28−11−00−840−802).
F. For the refuel shutoff valve of the right main tank, do the steps that follow:
(1) Remove the right wheel bin (164AZ) from the main wheel well (Ref. TASK
53−83−01−000−801).
(2) Prepare the right main tank for access (Ref. TASK 28−11−00−840−801).
(3) Remove the fuel fumes from the right main tank (Ref. TASK 28−11−00−840−802).

Subtask 28−25−07−840−001
G. Prepare the center tank for access (Ref. TASK 28−11−00−840−801).
H. Remove the fuel fumes from the center tank (Ref. TASK 28−11−00−840−802).

**ON A/C 7004−7019, 7021−7044, 7046, 7048, 7050, 7052, 7055−7056, 7059, 7061−7064,
7066−7067, 7069−7070, 7072−7073, 7075−7077, 7079−7080, 7085−7086, 7088−7094,
7099−7106, 7108−7111, 7113−7117, 7119, 7121−7123, 7125, 7127−7143, 7145−7152, 7154,
7156−7159, 7162−7163, 7165, 7167−7169, 7171−7176, 7178−7181, 7185−7196, 7199−7200,
7202−7222, 7224−7233, 7235−7236, 7238−7271, 7273−7294 Pre SB601R−24−090

Subtask 28−25−07−865−003
I. Open, safety, and tag the circuit breakers that follow:
CB PANEL CB NO. NAME ZONE
CBP−1 M12 FUEL SYST CONT 221
CBP−4 B10 FUEL SYST CONT 222
CBP−5 B14 FUEL/DEFL 311
CBP−5 B15 EMRG REFL 311

Master
EFFECTIVITY: See Pageblock 28−25−07 page 401
28−25−07 Page 402
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C 7003, 7020, 7045, 7047, 7049, 7051, 7053−7054, 7057−7058, 7060, 7065, 7071, 7074,
7078, 7081−7084, 7087, 7095−7098, 7107, 7112, 7118, 7120, 7124, 7126, 7144, 7153, 7155,
7160−7161, 7164, 7166, 7170, 7177, 7182−7184, 7197−7198, 7201, 7223, 7234, 7237, 7272,
7295−7990, 8000−8064, 8066−8068 and ON A/C 7004−7019, 7021−7044, 7046, 7048, 7050,
7052, 7055−7056, 7059, 7061−7064, 7066−7067, 7069−7070, 7072−7073, 7075−7077,
7079−7080, 7085−7086, 7088−7094, 7099−7106, 7108−7111, 7113−7117, 7119, 7121−7123,
7125, 7127−7143, 7145−7152, 7154, 7156−7159, 7162−7163, 7165, 7167−7169, 7171−7176,
7178−7181, 7185−7196, 7199−7200, 7202−7222, 7224−7233, 7235−7236, 7238−7271,
7273−7294 Post SB601R−24−090

Subtask 28−25−07−865−001
J. Open, safety, and tag the circuit breakers that follow:
CB PANEL CB NO. NAME ZONE
CBP−1 M12 FUEL SYST CONT 221
CBP−4 B10 FUEL SYST CONT 222
CBP−5 B6 FUEL DEFL 311
CBP−5 B7 EMRG REFL 311

**ON A/C ALL

3. Procedure
NOTE: For Wiggins coupling removal procedures, refer to Wiggins Couplings − Maintenance
Practices(Ref. TASK 20−30−00−910−802).
Subtask 28−25−07−030−001
A. Disconnect the electrical connections (Ref. WM 20−17−10).
B. Remove the wires from the electrical conduit as follows:
(1) If applied, remove the sealant from the nut (1) and the fitting (2).
(2) Disconnect the electrical conduit (3) from the refuel shutoff valve (4).
(3) Remove the wires from the electrical conduit (Ref. WM 20−12−00).

**ON A/C 7989−7990, 8000−8034 and ON A/C 7003−7031, 7033−7067, 7069−7132, 7134−7190,
7192−7204, 7206−7271, 7273−7293, 7295−7507, 7509−7689, 7691−7743, 7745−7765,
7767−7777, 7779−7780, 7782−7787, 7789−7939 Pre SB601R−28−053

Subtask 28−25−07−020−001
Refer to Figure 401.
C. Remove the refuel shutoff valve (4) as follows:
(1) Disconnect the coupling (5).
(2) Remove the retainer (6), the restrictor (14), and the preformed packings (7).
Discard the preformed packings (7).
(3) Put a protective plug in the refuel/defuel manifold.
(4) Remove the sealing compound from the bolts (8) and the contour of the mating
surface of the refuel shutoff valve (4).

Master
EFFECTIVITY: See Pageblock 28−25−07 page 401
28−25−07 Page 403
Dec 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
(5) Remove the bolts (8), the washers (9), and the refuel shutoff valve (4).
(6) Remove and discard the seal (10).
(7) For the refuel shutoff valve in the center tank, remove and discard the packing (11)
from the outlet manifold.
(8) Remove the split ring (12) and the coupling nut (13) from the refuel shutoff valve
(4).

**ON A/C 7032, 7133, 7191, 7205, 7272, 7294, 7508, 7690, 7744, 7766, 7778, 7781, 7788,
7940−7988, 8035−8064, 8066−8068 and ON A/C 7003−7031, 7033−7067, 7069−7132,
7134−7190, 7192−7204, 7206−7271, 7273−7293, 7295−7507, 7509−7689, 7691−7743,
7745−7765, 7767−7777, 7779−7780, 7782−7787, 7789−7939 Post SB601R−28−053

Subtask 28−25−07−020−002
Refer to Figure 402.
D. Remove the refuel shutoff valve as follows:
(1) Disconnect the coupling (5).
(2) Remove the retainer (6) and the preformed packings (7). Discard the preformed
packings (7).
(3) Put a protective plug in the refuel/defuel manifold.
(4) Remove the sealing compound from the bolts (8) and the contour of the mating
surface of the refuel shutoff valve (4).
(5) Remove the bolts (8), the washers (9), and the refuel shutoff valve (4).
(6) Remove and discard the seal (10).
(7) For the refuel shutoff valve in the center tank, remove and discard the packing (11)
from the outlet manifold.
(8) Remove the split ring (12) and the coupling nut (13) from the refuel shutoff valve
(4).

Master
EFFECTIVITY: See Pageblock 28−25−07 page 401
28−25−07 Page 404
Dec 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL

8
9

RBL45.00
11 A

LBL45.00
10

4
2
3
1

13

12
7

14
A
7

LEGEND
1. Nut. 8. Bolt.
ram2825074_001.dg, ds/yf, 12/05/05

2. Fitting. 9. Washer. 5
3. Electrical conduit. 10. Seal.
4. Refuel shutoff valve. 11. Preformed packing.
5. Coupling. 12. Split ring.
6. Retainer. 13. Coupling nut.
7. Preformed packing. 14. Restrictor.

Refuel Shutoff Valve − Removal/Installation

Figure 401

Master
EFFECTIVITY: See Pageblock 28−25−07 page 401
28−25−07 Page 405
Aug 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL

8
9

RBL45.00
11 A

LBL45.00
10

4
2
3
1

13

12
7

7
A

LEGEND 5
1. Nut. 8. Bolt.
ram2825074_002.dg, ds/yf, 11/05/05

2. Fitting. 9. Washer.
3. Electrical conduit. 10. Seal. OUTLET TUBE
4. Refuel shutoff valve. 11. Preformed packing. (REF)
5. Coupling. 12. Split ring.
6. Retainer. 13. Coupling nut.
7. Preformed packing.

Refuel Shutoff Valve − Removal/Installation

Figure 402

Master
EFFECTIVITY: See Pageblock 28−25−07 page 401
28−25−07 Page 406
Aug 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C ALL
TASK 28−25−07−400−801
Installation of the Refuel Shutoff Valve

1. Job Set−Up Information

Subtask 28−25−07−943−001
A. Tools and Equipment
REFERENCE DESIGNATION
87INTL or equivalant Digital Low Resistance Ohmmeter (DLRO)

Subtask 28−25−07−944−002
B. Consumable Materials
REFERENCE DESIGNATION
06−002 Petrolatum
09−013 Sealing compound

**ON A/C 7989−7990, 8000−8034 and ON A/C 7003−7031, 7033−7067, 7069−7132, 7134−7190,
7192−7204, 7206−7271, 7273−7293, 7295−7507, 7509−7689, 7691−7743, 7745−7765,
7767−7777, 7779−7780, 7782−7787, 7789−7939 Pre SB601R−28−053

Subtask 28−25−07−945−002
C. Parts
REF NAME OF PART QTY IPC SEQUENCE NO.
7 Preformed packing 2 IPC 28−25−00−1A−240
8 Bolt 4 IPC 28−25−00−1A−200
9 Washer 4 IPC 28−25−00−1A−205
10 Gasket 1 IPC 28−25−00−1A−210
11 Preformed packing 1 IPC 28−25−00−1A−325
14 Restrictor 1 IPC 28−25−00−1A−215

**ON A/C 7032, 7133, 7191, 7205, 7272, 7294, 7508, 7690, 7744, 7766, 7778, 7781, 7788,
7940−7988, 8035−8064, 8066−8068 and ON A/C 7003−7031, 7033−7067, 7069−7132,
7134−7190, 7192−7204, 7206−7271, 7273−7293, 7295−7507, 7509−7689, 7691−7743,
7745−7765, 7767−7777, 7779−7780, 7782−7787, 7789−7939 Post SB601R−28−053

Subtask 28−25−07−945−001
D. Parts
REF NAME OF PART QTY IPC SEQUENCE NO.
7 Preformed packing 2 IPC 28−25−00−1A−240
8 Bolt 4 IPC 28−25−00−1A−200
9 Washer 4 IPC 28−25−00−1A−205

Master
EFFECTIVITY: See Pageblock 28−25−07 page 401
28−25−07 Page 407
Dec 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL

REF NAME OF PART QTY IPC SEQUENCE NO.

10 Gasket 1 IPC 28−25−00−1A−210
11 Preformed packing 1 IPC 28−25−00−1A−325

**ON A/C ALL

Subtask 28−25−07−946−002
E. Reference Information
REFERENCE DESIGNATION
TASK 20−30−00−910−802 Wiggins Couplings − Maintenance Practices
TASK 28−11−01−400−802 Installation of the Graphite Access Panel
TASK 51−23−00−390−808 Application of Sealant with a Brush
TASK 51−23−00−390−815 Curing of Sealant
TASK 53−83−01−400−801 Installation of the MLG Wheel Bin
WM 20−12−00 Wiring − Installation
WM 20−17−10 Wiring Manual

2. Procedure
Subtask 28−25−07−869−001
NOTE: For Wiggins coupling installation procedures, refer to Wiggins Couplings − Maintenance
Practices(Ref. TASK 20−30−00−910−802).
A. Make sure that the aircraft is in the same configuration as in the removal task.

**ON A/C 7989−7990, 8000−8034 and ON A/C 7003−7031, 7033−7067, 7069−7132, 7134−7190,
7192−7204, 7206−7271, 7273−7293, 7295−7507, 7509−7689, 7691−7743, 7745−7765,
7767−7777, 7779−7780, 7782−7787, 7789−7939 Pre SB601R−28−053

Subtask 28−25−07−420−001
Refer to Figure 401.
B. Install the refuel shutoff valve as follows:
(1) Install the coupling nut (13) and the split ring (12) on the refuel shutoff valve (4).
(2) For the refuel shutoff valve in the center tank, lubricate and install the preformed
packing (11) on the outlet tube.
(3) For the refuel shutoff valves for the left or right main tanks, apply a brush coating of
sealing compound to the threads of the bolts (8).
(4) For the refuel shutoff valves for the left or right main tanks, apply sealant around the
base of the shutoff valve (4) and the seal (10).
(5) Hold the seal (10) in position and install the refuel shutoff valve (4), the washers (9),
and the bolts (8).
(6) Remove the protective plug from the refuel/defuel manifold.

Master
EFFECTIVITY: See Pageblock 28−25−07 page 401
28−25−07 Page 408
Dec 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
(7) Lubricate and install the preformed packings (7), the restrictor (14), and the retainer
(6).
(8) Connect the coupling (5).
(9) Let the sealant cure (Ref.TASK 51−23−00−390−815).

**ON A/C 7032, 7133, 7191, 7205, 7272, 7294, 7508, 7690, 7744, 7766, 7778, 7781, 7788,
7940−7988, 8035−8064, 8066−8068 and ON A/C 7003−7031, 7033−7067, 7069−7132,
7134−7190, 7192−7204, 7206−7271, 7273−7293, 7295−7507, 7509−7689, 7691−7743,
7745−7765, 7767−7777, 7779−7780, 7782−7787, 7789−7939 Post SB601R−28−053

Subtask 28−25−07−420−002
Refer to Figure 402.
C. Install the refuel shutoff valve as follows:
(1) Install the coupling nut (13) and the split ring (12) on the refuel shutoff valve (4).
(2) For the refuel shutoff valve in the center tank, lubricate and install the preformed
packing (11) on the outlet tube.
(3) For the refuel shutoff valves for the left or right main tanks, apply a brush coating of
sealing compound to the threads of the bolts (8).
(4) For the refuel shutoff valves for the left or right main tanks, apply sealant around the
base of the shutoff valve (4) and the seal (10).
(5) Hold the seal (10) in position and install the refuel shutoff valve (4) with the washers
(9), and the bolts (8).
(6) With a brush, apply sealant to the head of the bolts (8) (Ref. TASK
51−23−00−390−808).
(7) Remove the protective plug from the refuel/defuel manifold.
(8) Lubricate and install the preformed packings (7) and the retainer (6).
(9) Connect the coupling (5) to the shutoff valve (4).
(10) Let the sealant cure (Ref.TASK 51−23−00−390−815).

**ON A/C ALL

Subtask 28−25−07−430−002
D. Install the wires in the electrical conduit as follows:
(1) Install the wires in the electrical conduit (Ref. WM 20−12−00).
(2) Connect the nut (1) to the fitting (2).
(3) With a brush, apply sealant 09−013 on the nut (1) and the fitting (2).
(4) Make sure that you completely cover the gasket of the the fitting (2) with sealant.
(5) Let the sealant cure (Ref. TASK 51−23−00−390−815).
E. Connect the electrical connections (Ref. WM 20−17−10).

Master
EFFECTIVITY: See Pageblock 28−25−07 page 401
28−25−07 Page 409
Dec 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
Subtask 28−25−07−760−001
F. With a Digital Low Resistance Ohm meter (DLRO) or equivalent, do a check of the
resistance between the tube connector (15) and the aircraft structure. The measured
resistance must be 10 ohms or less.

Subtask 28−25−07−790−001
G. Refuel the applicable tank and check for leaks at the conduit output.

3. Close Out
**ON A/C 7004−7019, 7021−7044, 7046, 7048, 7050, 7052, 7055−7056, 7059, 7061−7064,
7066−7067, 7069−7070, 7072−7073, 7075−7077, 7079−7080, 7085−7086, 7088−7094,
7099−7106, 7108−7111, 7113−7117, 7119, 7121−7123, 7125, 7127−7143, 7145−7152, 7154,
7156−7159, 7162−7163, 7165, 7167−7169, 7171−7176, 7178−7181, 7185−7196, 7199−7200,
7202−7222, 7224−7233, 7235−7236, 7238−7271, 7273−7294 Pre SB601R−24−090

Subtask 28−25−07−865−004
A. Remove the tags and close the circuit breakers that follow:
CB PANEL CB NO. NAME ZONE
CBP−1 M12 FUEL SYST CONT 221
CBP−4 B10 FUEL SYST CONT 222
CBP−5 B14 FUEL/DEFL 311
CBP−5 B15 EMRG REFL 311

**ON A/C 7003, 7020, 7045, 7047, 7049, 7051, 7053−7054, 7057−7058, 7060, 7065, 7071, 7074,
7078, 7081−7084, 7087, 7095−7098, 7107, 7112, 7118, 7120, 7124, 7126, 7144, 7153, 7155,
7160−7161, 7164, 7166, 7170, 7177, 7182−7184, 7197−7198, 7201, 7223, 7234, 7237, 7272,
7295−7990, 8000−8064, 8066−8068 and ON A/C 7004−7019, 7021−7044, 7046, 7048, 7050,
7052, 7055−7056, 7059, 7061−7064, 7066−7067, 7069−7070, 7072−7073, 7075−7077,
7079−7080, 7085−7086, 7088−7094, 7099−7106, 7108−7111, 7113−7117, 7119, 7121−7123,
7125, 7127−7143, 7145−7152, 7154, 7156−7159, 7162−7163, 7165, 7167−7169, 7171−7176,
7178−7181, 7185−7196, 7199−7200, 7202−7222, 7224−7233, 7235−7236, 7238−7271,
7273−7294 Post SB601R−24−090

Subtask 28−25−07−865−002
B. Remove the tags and close the circuit breakers that follow:
CB PANEL CB NO. NAME ZONE
CBP−1 M12 FUEL SYST CONT 221
CBP−4 B10 FUEL SYST CONT 222
CBP−5 B6 FUEL DEFL 311
CBP−5 B7 EMRG REFL 311

Master
EFFECTIVITY: See Pageblock 28−25−07 page 401
28−25−07 Page 410
Dec 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C ALL

Subtask 28−25−07−410−001
C. Install the applicable access panels that follow (Ref. TASK 28−11−01−400−802):
ACCESS DESIGNATION ITEM
610AB Fuel tank access panel Center tank refuel shutoff valve
510BB Fuel tank access panel Left main tank refuel shutoff valve
540BB Fuel tank access panel Left main tank refuel shutoff valve
610BB Fuel tank access panel Right main tank refuel shutoff valve
640BB Fuel tank access panel Right main tank refuel shutoff valve
D. Install the applicable wheel bin in the landing gear well (Ref. TASK 53−83−01−400−801).

Master
EFFECTIVITY: See Pageblock 28−25−07 page 401
28−25−07 Page 411
Aug 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C ALL
SENSOR, HIGH−LEVEL − REMOVAL/INSTALLATION

1. General
A. The maintenance procedures that follow are for the removal and installation of the
high−level sensor. There are three high−level sensors in the fuel system. They are found
in the outboard sections of each main tank and the forward center section of the center
tank.
B. It is necessary to defuel, drain, and remove the fuel fumes from the applicable fuel tank
to remove or install the high−level sensor.

TASK 28−25−13−000−801
Removal of the High−Level Sensor

1. Job Set−Up Information

Subtask 28−25−13−946−001
A. Reference Information
REFERENCE DESIGNATION
TASK 12−11−28−650−804 Suction Defueling
TASK 28−00−00−910−801 Fuel Safety Precautions
TASK 28−11−00−840−801 Prepare Fuel Tank for Access
TASK 28−11−00−840−802 Removal of Fuel Fumes
TASK 28−11−01−000−801 Removal of the Honeycomb Access Panel
TASK 28−11−01−000−802 Removal of the Graphite Access Panel

2. Job Set−Up
Subtask 28−25−13−910−001
WARNING: OBEY ALL THE FUEL SAFETY PRECAUTIONS WHEN YOU DO WORK ON THE
FUEL SYSTEM AND/OR A FUEL SYSTEM COMPONENT. IF YOU DO NOT DO
THIS, YOU CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO
EQUIPMENT.
A. Obey all the fuel safety precautions (Ref. TASK 28−00−00−910−801).

Subtask 28−25−13−650−001
B. Defuel the applicable fuel tank (Ref. TASK 12−11−28−650−804).

Master
EFFECTIVITY: See Pageblock 28−25−13 page 401
28−25−13 Page 401
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C 7004−7019, 7021−7044, 7046, 7048, 7050, 7052, 7055−7056, 7059, 7061−7064,
7066−7067, 7069−7070, 7072−7073, 7075−7077, 7079−7080, 7085−7086, 7088−7094,
7099−7106, 7108−7111, 7113−7117, 7119, 7121−7123, 7125, 7127−7143, 7145−7152, 7154,
7156−7159, 7162−7163, 7165, 7167−7169, 7171−7176, 7178−7181, 7185−7196, 7199−7200,
7202−7222, 7224−7233, 7235−7236, 7238−7271, 7273−7294 Pre SB601R−24−090

Subtask 28−25−13−865−003
C. Open, safety, and tag the circuit breakers that follow:
CB PANEL CB NO. NAME ZONE
CBP−1 M12 FUEL SYST CONT 221
CBP−4 B10 FUEL SYST CONT 222
CBP−5 B14 FUEL/DEFL 311
CBP−5 B15 EMRG REFL 311

**ON A/C 7003, 7020, 7045, 7047, 7049, 7051, 7053−7054, 7057−7058, 7060, 7065, 7071, 7074,
7078, 7081−7084, 7087, 7095−7098, 7107, 7112, 7118, 7120, 7124, 7126, 7144, 7153, 7155,
7160−7161, 7164, 7166, 7170, 7177, 7182−7184, 7197−7198, 7201, 7223, 7234, 7237, 7272,
7295−7990, 8000−8064, 8066−8068 and ON A/C 7004−7019, 7021−7044, 7046, 7048, 7050,
7052, 7055−7056, 7059, 7061−7064, 7066−7067, 7069−7070, 7072−7073, 7075−7077,
7079−7080, 7085−7086, 7088−7094, 7099−7106, 7108−7111, 7113−7117, 7119, 7121−7123,
7125, 7127−7143, 7145−7152, 7154, 7156−7159, 7162−7163, 7165, 7167−7169, 7171−7176,
7178−7181, 7185−7196, 7199−7200, 7202−7222, 7224−7233, 7235−7236, 7238−7271,
7273−7294 Post SB601R−24−090

Subtask 28−25−13−865−001
D. Open, safety, and tag the circuit breakers that follow:
CB PANEL CB NO. NAME ZONE
CBP−1 M12 FUEL SYST CONT 221
CBP−4 B10 FUEL SYST CONT 222
CBP−5 B6 FUEL DEFL 311
CBP−5 B7 EMRG REFL 311

**ON A/C ALL

Subtask 28−25−13−010−001
E. For the high−level sensors in the main tanks, remove the applicable access panel that
follows (Ref. TASK 28−11−01−000−802):
ACCESS DESIGNATION
550FB Fuel tank access panel
650FB Fuel tank access panel
F. For the high−level sensor in the center tank, remove the access panel that follows (Ref.
TASK 28−11−01−000−801):

Master
EFFECTIVITY: See Pageblock 28−25−13 page 401
28−25−13 Page 402
Dec 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL

ACCESS DESIGNATION
510BB Fuel tank access panel

Subtask 28−25−13−840−001
G. Prepare the applicable fuel tank for access (Ref. TASK 28−11−00−840−801).
H. Remove the fuel fumes from the applicable fuel tank (Ref. TASK 28−11−00−840−802).

3. Procedure
Subtask 28−25−13−020−001
Refer to Figure 401.
A. Remove the high−level sensor as follows:
(1) Remove the sealant from the screws (3) and (4) and remove the screws, and the
washers (5), and the high−level sensor (2). Discard the screws and the washers.
NOTE: The screw on the upper mounting (3) of the high−level sensor has a
larger diameter than the screw on the lower mounting (4). Examine the
screws to help in the installation.
(2) Disconnect the electrical connector (1) from the high−level sensor (2). Put a
protective cap on the electrical connector.

Master
EFFECTIVITY: See Pageblock 28−25−13 page 401
28−25−13 Page 403
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

LEGEND
1. Electrical connector.
2. High−level sensor.
3. Screw.
4. Screw.
5. Washer.
6. Washer.

1
ram2825134_001(2).dg, jp/kms, 31/08/95

TYPICAL

High−Level Sensor − Removal/Installation

Figure 401

Master
EFFECTIVITY: See Pageblock 28−25−13 page 401
28−25−13 Page 404
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
TASK 28−25−13−400−801
Installation of the High−Level Sensor

1. Job Set−Up Information

Subtask 28−25−13−944−001
A. Consumable Materials
REFERENCE DESIGNATION
09−013 Sealing compound

Subtask 28−25−13−945−001
B. Parts
REF NAME OF PART QTY IPC SEQUENCE NO.
3 Screw 1 IPC 28−41−00−1A−085
4 Screw 1 IPC 28−41−00−1A−080
5 Washer 1 IPC 28−41−00−1A−090
6 Washer 1 IPC 28−41−00−1A−095

Subtask 28−25−13−946−002
C. Reference Information
REFERENCE DESIGNATION
TASK 51−80−00−100−802 Preparation for Electrical Bonding
TASK 28−11−01−400−801 Installation of the Honeycomb Access Panel
TASK 28−11−01−400−802 Installation of the Graphite Access Panel
TASK 28−11−00−790−802 Leak Rate Check of the Fuel Tank
TASK 28−25−00−710−801 Operational Test of the Refuel/Defuel System

2. Procedure
Subtask 28−25−13−869−001
A. Make sure that the aircraft is in the same configuration as in the removal task.

Subtask 28−25−13−420−001
Refer to Figure 401.
B. Install the high−level sensor as follows:
(1) Prepare the high level sensor for electrical bonding (Ref. TASK
51−80−00−100−802).
(2) Remove the protective cap from the electrical connector (1). Connect the electrical
connector to the high−level sensor (2).
(3) Install the high−level sensor (2), the washers (5), and the screws (3) and (4). Make

Master
EFFECTIVITY: See Pageblock 28−25−13 page 401
28−25−13 Page 405
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
sure that the electrical connector on the high−level sensor points down.
NOTE: The screw on the upper mounting (3) has a larger diameter than the
screw on the lower mounting (4).
(4) Coat the screws (3) and (4) with sealant.

3. Close Out
**ON A/C 7004−7019, 7021−7044, 7046, 7048, 7050, 7052, 7055−7056, 7059, 7061−7064,
7066−7067, 7069−7070, 7072−7073, 7075−7077, 7079−7080, 7085−7086, 7088−7094,
7099−7106, 7108−7111, 7113−7117, 7119, 7121−7123, 7125, 7127−7143, 7145−7152, 7154,
7156−7159, 7162−7163, 7165, 7167−7169, 7171−7176, 7178−7181, 7185−7196, 7199−7200,
7202−7222, 7224−7233, 7235−7236, 7238−7271, 7273−7294 Pre SB601R−24−090

Subtask 28−25−13−865−004
A. Remove the tags and close the circuit breakers that follow:
CB PANEL CB NO. NAME ZONE
CBP−1 M12 FUEL SYST CONT 221
CBP−4 B10 FUEL SYST CONT 222
CBP−5 B14 FUEL/DEFL 311
CBP−5 B15 EMRG REFL 311

**ON A/C 7003, 7020, 7045, 7047, 7049, 7051, 7053−7054, 7057−7058, 7060, 7065, 7071, 7074,
7078, 7081−7084, 7087, 7095−7098, 7107, 7112, 7118, 7120, 7124, 7126, 7144, 7153, 7155,
7160−7161, 7164, 7166, 7170, 7177, 7182−7184, 7197−7198, 7201, 7223, 7234, 7237, 7272,
7295−7990, 8000−8064, 8066−8068 and ON A/C 7004−7019, 7021−7044, 7046, 7048, 7050,
7052, 7055−7056, 7059, 7061−7064, 7066−7067, 7069−7070, 7072−7073, 7075−7077,
7079−7080, 7085−7086, 7088−7094, 7099−7106, 7108−7111, 7113−7117, 7119, 7121−7123,
7125, 7127−7143, 7145−7152, 7154, 7156−7159, 7162−7163, 7165, 7167−7169, 7171−7176,
7178−7181, 7185−7196, 7199−7200, 7202−7222, 7224−7233, 7235−7236, 7238−7271,
7273−7294 Post SB601R−24−090

Subtask 28−25−13−865−002
B. Remove the tags and close the circuit breakers that follow:
CB PANEL CB NO. NAME ZONE
CBP−1 M12 FUEL SYST CONT 221
CBP−4 B10 FUEL SYST CONT 222
CBP−5 B6 FUEL DEFL 311
CBP−5 B7 EMRG REFL 311

Master
EFFECTIVITY: See Pageblock 28−25−13 page 401
28−25−13 Page 406
Dec 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C ALL

Subtask 28−25−13−410−001
C. For the high−level sensors in the main tanks, install the applicable access panel that
follows (Ref. TASK 28−11−01−400−802):
ACCESS DESIGNATION
550FB Fuel tank access panel
650FB Fuel tank access panel
D. For the high−level sensor in the center tank, install the access panel that follows (Ref.
TASK 28−11−01−400−801):
ACCESS DESIGNATION
510BB Fuel tank access panel

Subtask 28−25−13−790−001
E. Do a leak rate check of the fuel tank access panel removed for the job (Ref. TASK
28−11−00−790−802).

Subtask 28−25−13−710−001
F. Do an operational test of the refuel/defuel system (Ref. TASK 28−25−00−710−801).

Master
EFFECTIVITY: See Pageblock 28−25−13 page 401
28−25−13 Page 407
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C ALL
PANEL, REFUEL/DEFUEL CONTROL − REMOVAL/INSTALLATION

1. General
A. The maintenance procedures that follow are for the removal and installation of the
refuel/defuel control panel.

TASK 28−25−16−000−801
Removal of the Fuselage−Refuel/Defuel Control Panel

1. Job Set−Up
**ON A/C 7004−7019, 7021−7044, 7046, 7048, 7050, 7052, 7055−7056, 7059, 7061−7064,
7066−7067, 7069−7070, 7072−7073, 7075−7077, 7079−7080, 7085−7086, 7088−7094,
7099−7106, 7108−7111, 7113−7117, 7119, 7121−7123, 7125, 7127−7143, 7145−7152, 7154,
7156−7159, 7162−7163, 7165, 7167−7169, 7171−7176, 7178−7181, 7185−7196, 7199−7200,
7202−7222, 7224−7233, 7235−7236, 7238−7271, 7273−7294 Pre SB601R−24−090

Subtask 28−25−16−865−001
A. Open, safety, and tag the circuit breakers that follow:
CB PANEL CB NO. NAME ZONE
CBP−1 M12 FUEL SYST CONT 221
CBP−4 B10 FUEL SYST CONT 222
CBP−5 B14 FUEL DEFL 311
CBP−5 B15 EMRG REFL 311

**ON A/C 7003, 7020, 7045, 7047, 7049, 7051, 7053−7054, 7057−7058, 7060, 7065, 7071, 7074,
7078, 7081−7084, 7087, 7095−7098, 7107, 7112, 7118, 7120, 7124, 7126, 7144, 7153, 7155,
7160−7161, 7164, 7166, 7170, 7177, 7182−7184, 7197−7198, 7201, 7223, 7234, 7237, 7272,
7295−7990, 8000−8064, 8066−8068 and ON A/C 7004−7019, 7021−7044, 7046, 7048, 7050,
7052, 7055−7056, 7059, 7061−7064, 7066−7067, 7069−7070, 7072−7073, 7075−7077,
7079−7080, 7085−7086, 7088−7094, 7099−7106, 7108−7111, 7113−7117, 7119, 7121−7123,
7125, 7127−7143, 7145−7152, 7154, 7156−7159, 7162−7163, 7165, 7167−7169, 7171−7176,
7178−7181, 7185−7196, 7199−7200, 7202−7222, 7224−7233, 7235−7236, 7238−7271,
7273−7294 Post SB601R−24−090

Subtask 28−25−16−865−005
B. Open, safety, and tag the circuit breakers that follow:
CB PANEL CB NO. NAME ZONE
CBP−1 M12 FUEL SYST CONT 221
CBP−4 B10 FUEL SYST CONT 222
CBP−5 B6 FUEL DEFL 311
CBP−5 B7 EMRG REFL 311

Master
EFFECTIVITY: See Pageblock 28−25−16 page 401
28−25−16 Page 401
Dec 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C ALL

Subtask 28−25−16−010−001
C. Open the access door that follows:
ACCESS DESIGNATION
162AB Refuel/defuel−control−panel access door

2. Procedure
Subtask 28−25−16−020−001
Refer to Figure 401.
A. Remove the fuselage−refuel/defuel control panel as follows:
NOTE: This refuel/defuel control panel is installed in the right fuselage, forward of the
wing root.
(1) Remove the screws (1) from the front of the refuel/defuel control panel (2).
(2) Pull the refuel/defuel control panel (2) out to get access to the electrical
connector (3).
(3) Disconnect the electrical connector (3) from the refuel/defuel control panel (2). Put
a protective cap on the electrical connector.
(4) Remove the refuel/defuel control panel (2).

Master
EFFECTIVITY: See Pageblock 28−25−16 page 401
28−25−16 Page 402
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

LEGEND
1. Screw.
2. Control panel.
3. Electrical connector.

1
2

3
ram2825164_001(1).dc, kms, 31/08/95

Refuel/Defuel Control Panel − Removal/Installation

Figure 401

Master
EFFECTIVITY: See Pageblock 28−25−16 page 401
28−25−16 Page 403
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
TASK 28−25−16−400−801
Installation of the Fuselage−Refuel/Defuel Control Panel

1. Job Set−Up Information

Subtask 28−25−16−946−001
A. Reference Information
REFERENCE DESIGNATION
TASK 28−25−00−710−801 Operational Test of the Refuel/Defuel System

2. Procedure
Subtask 28−25−16−869−001
A. Make sure the aircraft is in the same configuration as in the removal task.

Subtask 28−25−16−420−001
Refer to Figure 401.
B. Install the refuel/defuel control panel as follows:
(1) Remove the protective cap from the electrical connector (3). Connect the electrical
connector to the refuel/defuel control panel (2).
(2) Install the refuel/defuel control panel (2).
(3) Install the screws (1) in the front of the refuel/defuel control panel (2).

3. Close Out
**ON A/C 7004−7019, 7021−7044, 7046, 7048, 7050, 7052, 7055−7056, 7059, 7061−7064,
7066−7067, 7069−7070, 7072−7073, 7075−7077, 7079−7080, 7085−7086, 7088−7094,
7099−7106, 7108−7111, 7113−7117, 7119, 7121−7123, 7125, 7127−7143, 7145−7152, 7154,
7156−7159, 7162−7163, 7165, 7167−7169, 7171−7176, 7178−7181, 7185−7196, 7199−7200,
7202−7222, 7224−7233, 7235−7236, 7238−7271, 7273−7294 Pre SB601R−24−090

Subtask 28−25−16−865−002
A. Remove the tags and close the circuit breakers that follow:
CB PANEL CB NO. NAME ZONE
CBP−1 M12 FUEL SYST CONT 221
CBP−4 B10 FUEL SYST CONT 222
CBP−5 B14 FUEL DEFL 311
CBP−5 B15 EMRG REFL 311

Master
EFFECTIVITY: See Pageblock 28−25−16 page 401
28−25−16 Page 404
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C 7003, 7020, 7045, 7047, 7049, 7051, 7053−7054, 7057−7058, 7060, 7065, 7071, 7074,
7078, 7081−7084, 7087, 7095−7098, 7107, 7112, 7118, 7120, 7124, 7126, 7144, 7153, 7155,
7160−7161, 7164, 7166, 7170, 7177, 7182−7184, 7197−7198, 7201, 7223, 7234, 7237, 7272,
7295−7990, 8000−8064, 8066−8068 and ON A/C 7004−7019, 7021−7044, 7046, 7048, 7050,
7052, 7055−7056, 7059, 7061−7064, 7066−7067, 7069−7070, 7072−7073, 7075−7077,
7079−7080, 7085−7086, 7088−7094, 7099−7106, 7108−7111, 7113−7117, 7119, 7121−7123,
7125, 7127−7143, 7145−7152, 7154, 7156−7159, 7162−7163, 7165, 7167−7169, 7171−7176,
7178−7181, 7185−7196, 7199−7200, 7202−7222, 7224−7233, 7235−7236, 7238−7271,
7273−7294 Post SB601R−24−090

Subtask 28−25−16−865−006
B. Remove the tags and close the circuit breakers that follow:
CB PANEL CB NO. NAME ZONE
CBP−1 M12 FUEL SYST CONT 221
CBP−4 B10 FUEL SYST CONT 222
CBP−5 B6 FUEL DEFL 311
CBP−5 B7 EMRG REFL 311

**ON A/C ALL

Subtask 28−25−16−710−001
C. Do a test of the refuel/defuel control panel (Ref. TASK 28−25−00−710−801).

Subtask 28−25−16−410−001
D. Close the access door that follows:
ACCESS DESIGNATION
162AB Refuel/defuel access door

Master
EFFECTIVITY: See Pageblock 28−25−16 page 401
28−25−16 Page 405
Dec 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C 7003−7007, 7009−7010, 7015−7016, 7019, 7021, 7023−7025, 7032−7033, 7036, 7039,
7041, 7052, 7059, 7061, 7063−7064, 7073, 7075, 7086, 7089−7090, 7093−7094, 7099,
7103−7104, 7110, 7113−7114, 7119, 7121−7122, 7125, 7128, 7130, 7134−7136, 7138, 7140,
7142, 7148−7149, 7152, 7165, 7167, 7176, 7180, 7189−7190, 7193, 7200, 7205, 7220, 7226,
7247−7248, 7266, 7282−7283, 7298−7299, 7329, 7351, 7365, 7371, 7373, 7378, 7386, 7391,
7394, 7403, 7407, 7413, 7419, 7431, 7436, 7439, 7442, 7449, 7464, 7478, 7480, 7486, 7494,
7499, 7567, 7570, 7573, 7583, 7605, 7607, 7617, 7619, 7625, 7629−7630, 7738, 7846, 7862,
7864, 7901−7902, 7910, 7973, 7990, 8046, 8060, 8066−8068
TASK 28−25−16−000−802
Removal of the Flight−Compartment−Refuel/Defuel Control Panel

1. Job Set−Up
**ON A/C 7004−7007, 7009−7010, 7015−7016, 7019, 7021, 7023−7025, 7032−7033, 7036, 7039,
7041, 7052, 7059, 7061, 7063−7064, 7073, 7075, 7086, 7089−7090, 7093−7094, 7099,
7103−7104, 7110, 7113−7114, 7119, 7121−7122, 7125, 7128, 7130, 7134−7136, 7138, 7140,
7142, 7148−7149, 7152, 7165, 7167, 7176, 7180, 7189−7190, 7193, 7200, 7205, 7220, 7226,
7247−7248, 7266, 7282−7283 Pre SB601R−24−090

Subtask 28−25−16−865−003
A. Open, safety, and tag the circuit breakers that follow:
CB PANEL CB NO. NAME ZONE
CBP−1 M12 FUEL SYST CONT 221
CBP−4 B10 FUEL SYST CONT 222
CBP−5 B14 FUEL DEFL 311
CBP−5 B15 EMRG REFL 311

**ON A/C 7003, 7298−7299, 7329, 7351, 7365, 7371, 7373, 7378, 7386, 7391, 7394, 7403, 7407,
7413, 7419, 7431, 7436, 7439, 7442, 7449, 7464, 7478, 7480, 7486, 7494, 7499, 7567, 7570,
7573, 7583, 7605, 7607, 7617, 7619, 7625, 7629−7630, 7738, 7846, 7862, 7864, 7901−7902,
7910, 7973, 7990, 8046, 8060, 8066−8068 and ON A/C 7004−7007, 7009−7010, 7015−7016,
7019, 7021, 7023−7025, 7032−7033, 7036, 7039, 7041, 7052, 7059, 7061, 7063−7064, 7073,
7075, 7086, 7089−7090, 7093−7094, 7099, 7103−7104, 7110, 7113−7114, 7119, 7121−7122,
7125, 7128, 7130, 7134−7136, 7138, 7140, 7142, 7148−7149, 7152, 7165, 7167, 7176, 7180,
7189−7190, 7193, 7200, 7205, 7220, 7226, 7247−7248, 7266, 7282−7283 Post SB601R−24−090

Subtask 28−25−16−865−007
B. Open, safety, and tag the circuit breakers that follow:
CB PANEL CB NO. NAME ZONE
CBP−1 M12 FUEL SYST CONT 221
CBP−4 B10 FUEL SYST CONT 222
CBP−5 B6 FUEL DEFL 311
CBP−5 B7 EMRG REFL 311

Master
EFFECTIVITY: See Pageblock 28−25−16 page 401
28−25−16 Page 406
Dec 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C 7003−7007, 7009−7010, 7015−7016, 7019, 7021, 7023−7025, 7032−7033, 7036, 7039,
7041, 7052, 7059, 7061, 7063−7064, 7073, 7075, 7086, 7089−7090, 7093−7094, 7099,
7103−7104, 7110, 7113−7114, 7119, 7121−7122, 7125, 7128, 7130, 7134−7136, 7138, 7140,
7142, 7148−7149, 7152, 7165, 7167, 7176, 7180, 7189−7190, 7193, 7200, 7205, 7220, 7226,
7247−7248, 7266, 7282−7283, 7298−7299, 7329, 7351, 7365, 7371, 7373, 7378, 7386, 7391,
7394, 7403, 7407, 7413, 7419, 7431, 7436, 7439, 7442, 7449, 7464, 7478, 7480, 7486, 7494,
7499, 7567, 7570, 7573, 7583, 7605, 7607, 7617, 7619, 7625, 7629−7630, 7738, 7846, 7862,
7864, 7901−7902, 7910, 7973, 7990, 8046, 8060, 8066−8068

2. Procedure
Subtask 28−25−16−020−002
Refer to Figure 402.
A. Remove the refuel/defuel control panel in the flight compartment as follows:
NOTE: This refuel/defuel control panel is installed on the aft wall, behind the copilot’s
seat.
(1) Remove the screws (1) and the washers (2) from the mounting plate (3).
(2) Carefully pull out the mounting plate (3) to get access to the electrical connector (4).
CAUTION: DO NOT LET THE ELECTRICAL HARNESS FALL BEHIND THE
CIRCUIT BREAKER PANEL. THIS CAN CAUSE AN ELECTRICAL
SHORT CIRCUIT AND DAMAGE EQUIPMENT.
(3) Disconnect the electrical connector (4) from the refuel/defuel control panel (5).
(4) Put a protective cap on the electrical connector (4).
(5) Put the electrical harness in a plastic bag and close the bag with a tie wrap.
(6) Attach the plastic bag to the mounting bracket with a tie wrap.
NOTE: This will prevent the electrical harness from falling behind the co−pilot’s
circuit breaker panel.
(7) Remove the refuel/defuel control panel (5).
(8) Remove the locknuts (6), the washers (7), the screws (8), and the mounting plate
(3) from the refuel/defuel control panel (5). Discard the locknuts.

Master
EFFECTIVITY: See Pageblock 28−25−16 page 401
28−25−16 Page 407
Dec 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL

LEGEND.
1. Screw.
2. Washer.
3. Mounting plate.
4. Electrical connector.
5. Refuel/defuel control
panel.
6. Locknut.
7. Washer.
8. Screw.

5 6
7

ram2825164_002.dc, JR/jp, 15/12/91

2
8 1

Flight Compartment Refuel/Defuel Control Panel − Removal/Installation

Figure 402

Master
EFFECTIVITY: See Pageblock 28−25−16 page 401
28−25−16 Page 408
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
TASK 28−25−16−400−802
Installation of the Flight−Compartment−Refuel/Defuel Control Panel

1. Job Set−Up Information

Subtask 28−25−16−945−003
A. Parts
REF NAME OF PART QTY IPC SEQUENCE NO.
6 Locknut 4 IPC 28−25−16−2C−035

Subtask 28−25−16−946−002
B. Reference Information
REFERENCE DESIGNATION
TASK 28−25−00−710−801 Operational Test of the Refuel/Defuel System

2. Procedure
Subtask 28−25−16−420−013
Refer to Figure 402.
A. Install the refuel/defuel control panel as follows:
(1) Install the mounting plate (3), the screws (8), the washers (7), and the locknuts (6)
on the refuel/defuel control panel (5).
(2) Remove the tie wrap, the plastic bag, and the protective cap from the electrical
connector (4).
(3) Connect the electrical connector (4) to the refuel/defuel control panel (5).
(4) Hold the mounting plate (3) in position and install the washers (2) and the
screws (1).

3. Close Out
**ON A/C 7004−7007, 7009−7010, 7015−7016, 7019, 7021, 7023−7025, 7032−7033, 7036, 7039,
7041, 7052, 7059, 7061, 7063−7064, 7073, 7075, 7086, 7089−7090, 7093−7094, 7099,
7103−7104, 7110, 7113−7114, 7119, 7121−7122, 7125, 7128, 7130, 7134−7136, 7138, 7140,
7142, 7148−7149, 7152, 7165, 7167, 7176, 7180, 7189−7190, 7193, 7200, 7205, 7220, 7226,
7247−7248, 7266, 7282−7283 Pre SB601R−24−090

Subtask 28−25−16−865−004
A. Remove the tags and close the circuit breakers that follow:
CB PANEL CB NO. NAME ZONE
CBP−1 M12 FUEL SYST CONT 221
CBP−4 B10 FUEL SYST CONT 222
CBP−5 B14 FUEL DEFL 311

Master
EFFECTIVITY: See Pageblock 28−25−16 page 401
28−25−16 Page 409
Sep 10/2004
 C
AIRCRAFT MAINTENANCE MANUAL

CB PANEL CB NO. NAME ZONE

CBP−5 B15 EMRG REFL 311

**ON A/C 7003, 7298−7299, 7329, 7351, 7365, 7371, 7373, 7378, 7386, 7391, 7394, 7403, 7407,
7413, 7419, 7431, 7436, 7439, 7442, 7449, 7464, 7478, 7480, 7486, 7494, 7499, 7567, 7570,
7573, 7583, 7605, 7607, 7617, 7619, 7625, 7629−7630, 7738, 7846, 7862, 7864, 7901−7902,
7910, 7973, 7990, 8046, 8060, 8066−8068 and ON A/C 7004−7007, 7009−7010, 7015−7016,
7019, 7021, 7023−7025, 7032−7033, 7036, 7039, 7041, 7052, 7059, 7061, 7063−7064, 7073,
7075, 7086, 7089−7090, 7093−7094, 7099, 7103−7104, 7110, 7113−7114, 7119, 7121−7122,
7125, 7128, 7130, 7134−7136, 7138, 7140, 7142, 7148−7149, 7152, 7165, 7167, 7176, 7180,
7189−7190, 7193, 7200, 7205, 7220, 7226, 7247−7248, 7266, 7282−7283 Post SB601R−24−090

Subtask 28−25−16−865−008
B. Remove the tags and close the circuit breakers that follow:
CB PANEL CB NO. NAME ZONE
CBP−1 M12 FUEL SYST CONT 221
CBP−4 B10 FUEL SYST CONT 222
CBP−5 B6 FUEL DEFL 311
CBP−5 B7 EMRG REFL 311

**ON A/C 7003−7007, 7009−7010, 7015−7016, 7019, 7021, 7023−7025, 7032−7033, 7036, 7039,
7041, 7052, 7059, 7061, 7063−7064, 7073, 7075, 7086, 7089−7090, 7093−7094, 7099,
7103−7104, 7110, 7113−7114, 7119, 7121−7122, 7125, 7128, 7130, 7134−7136, 7138, 7140,
7142, 7148−7149, 7152, 7165, 7167, 7176, 7180, 7189−7190, 7193, 7200, 7205, 7220, 7226,
7247−7248, 7266, 7282−7283, 7298−7299, 7329, 7351, 7365, 7371, 7373, 7378, 7386, 7391,
7394, 7403, 7407, 7413, 7419, 7431, 7436, 7439, 7442, 7449, 7464, 7478, 7480, 7486, 7494,
7499, 7567, 7570, 7573, 7583, 7605, 7607, 7617, 7619, 7625, 7629−7630, 7738, 7846, 7862,
7864, 7901−7902, 7910, 7973, 7990, 8046, 8060, 8066−8068

Subtask 28−25−16−710−002
C. Do a test of the refuel/defuel control panel (Ref. TASK 28−25−00−710−801).

Master
EFFECTIVITY: See Pageblock 28−25−16 page 401
28−25−16 Page 410
Dec 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C ALL
PANEL, FUEL CONTROL − REMOVAL/INSTALLATION

1. General
A. The maintenance procedures that follow are for the removal and installation of the
FUEL−control panel in the overhead panel of the flight compartment. The panel is
removed and installed in this procedure, as follows:

TASK 28−31−01−000−801
Removal of the FUEL Control Panel

1. Job Set−Up Information

Subtask 28−31−01−946−001
A. Reference Information
REFERENCE DESIGNATION
TASK 24−00−00−910−801 Electrical/Electronic Safety Precautions

2. Job Set−Up
Subtask 28−31−01−910−001
A. Obey all of the electrical and electronic safety precautions (Ref. TASK
24−00−00−910−801.

Subtask 28−31−01−865−002
B. Open, safety, and tag the circuit breakers that follow:
CB PANEL CB NO. NAME ZONE
CBP−1 H5 EICAS LDU L 221
CBP−1 M6 L FUEL PUMP 221
CBP−1 M7 L FUEL PUMP CONT 221
CBP−1 M8 XFLOW SOV 221
CBP−1 M12 FUEL SYST CONT 221
CBP−1 N9 XFER LEFT FUEL SOV 221
CBP−1 N10 XFER/APU FUEL PUMP 221
CBP−1 N11 XFER/APU CONT 221
CBP−2 G10 R FUEL PUMP 222
CBP−2 G11 R FUEL PUMP CONT 222
CBP−2 P9 XFER RIGHT FUEL SOV 222
CBP−2 Q8 EICAS CONT PNL 222
CBP−2 Q9 EICAS LDU R 222
CBP−4 B9 FUEL GRAV XFLOW 222
CBP−4 B10 FUEL SYST CONT 222

Master
EFFECTIVITY: See Pageblock 28−31−01 page 401
28−31−01 Page 401
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
3. Procedure
Subtask 28−31−01−020−001
Refer to Figure 401.
A. Remove the FUEL−control panel as follows:
(1) Release the four captive fasteners (1).
(2) Carefully pull the FUEL−control panel (2) out of the overhead console and hold.
(3) Push and turn counter clockwise the two bayonet−type connectors (3) to electrically
disconnect the FUEL−control panel (2) from the overhead console.
(4) Put the FUEL−control panel (2) on a clean, dry, flat surface.
(5) Put protective covers on each of the FUEL−control−panel, connectors (4).
(6) Put protective covers on each of the overhead−console, connectors (3).

Master
EFFECTIVITY: See Pageblock 28−31−01 page 401
28−31−01 Page 402
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

OVERHEAD
CONSOLE (REF)
LEGEND
1. Captive fastner.
2. FUEL control panel.
3. Female connector.
4. Male connector.
3

LB
O
PU OST 4
MP
F ON GR
U INO XFAVIT
P LO Y
E W
FA
L IL RB
L OP O
PU OST
EN MP
ON 3
AU XFL ON
FA TO O
IL OV W INO
ER P
RID
E
MA
N
R
ram2831014_001.dg, jp, 09/03/99

ON
FA
IL

FUEL Control Panel − Removal/Installation

Figure 401

Master
EFFECTIVITY: See Pageblock 28−31−01 page 401
28−31−01 Page 403
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
TASK 28−31−01−400−801
Installation of the FUEL Control Panel

1. Job Set−Up Information

Subtask 28−31−01−946−002
A. Reference Information
REFERENCE DESIGNATION
TASK 24−00−00−910−801 Electrical/Electronic Safety Precautions
TASK 31−52−00−710−801 Operational Test of the Warning Lights System
TASK 28−00−00−710−801 Operational Test of the Fuel System

2. Job Set−Up
Subtask 28−31−01−910−002
A. Obey all of the electrical and electronic safety precautions (Ref. TASK
24−00−00−910−801).

Subtask 28−31−01−869−001
B. Make sure that the aircraft is in the same configuration as in the removal task.

3. Procedure
Subtask 28−31−01−420−001
A. Install the FUEL−control panel as follows:
Refer to Figure 401.
(1) Remove the protective covers from each of the overhead−console, connectors (3).
(2) Remove the protective covers from each of the FUEL−control panel, connectors (4).
(3) Lift the FUEL control panel (2) to the overhead console and hold.
(4) Align, push in and turn clockwise the two bayonet−type connectors (3) to electrically
connect the FUEL control panel (2) to the overhead console.
(5) Carefully install the FUEL−control panel (2) into the overhead console.
(6) Push and turn the four captive fasteners (1) to lock the FUEL−control panel in the
overhead console.

4. Close Out
Subtask 28−31−01−865−001
A. Remove the tags and close the circuit breakers that follow:

Master
EFFECTIVITY: See Pageblock 28−31−01 page 401
28−31−01 Page 404
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

CB PANEL CB NO. NAME ZONE

CBP−1 H5 EICAS LDU L 221
CBP−1 M6 L FUEL PUMP 221
CBP−1 M7 L FUEL PUMP CONT 221
CBP−1 M8 XFLOW SOV 221
CBP−1 M12 FUEL SYST CONT 221
CBP−1 N9 XFER LEFT FUEL SOV 221
CBP−1 N10 XFER/APU FUEL PUMP 221
CBP−1 N11 XFER/APU CONT 221
CBP−2 G10 R FUEL PUMP 222
CBP−2 G11 R FUEL PUMP CONT 222
CBP−2 P9 XFER RIGHT FUEL SOV 222
CBP−2 Q8 EICAS CONT PNL 222
CBP−2 Q9 EICAS LDU R 222
CBP−4 B9 FUEL GRAV XFLOW 222
CBP−4 B10 FUEL SYST CONT 222

Subtask 28−31−01−710−001
B. Do an operational test of the warning lights system (Ref. TASK 31−52−00−710−801).

Subtask 28−31−01−710−002
C. Do an operational test of the fuel system (Ref. TASK 28−00−00−710−801).

Subtask 28−31−01−941−001
D. Remove all tools, equipment, and unwanted materials from the work area.

Master
EFFECTIVITY: See Pageblock 28−31−01 page 401
28−31−01 Page 405
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C ALL
FUEL INDICATING SYSTEM − DESCRIPTION AND OPERATION

1. General
A. The indicating system monitors the fuel quantity, temperature and pressure in the fuel
system. The indicating system includes the systems that follow:
± Fuel−quantity gauging system (28−41−00)
± Fuel warning system (28−42−00).
2. Description
A. Fuel−Quantity Gauging System
(1) The fuel−quantity gauging system monitors the fuel quantity in the fuel tanks. The
fuel system computer (FSC) calculates the amount of fuel in the aircraft from the
signals from the fuel−quantity transmitter probes and the compensators. As an
alternate fuel quantity measurement, this system also includes magnetic fuel−level
indicators that measure the fuel quantity while the aircraft is on the ground.
B. Fuel Warning System
(1) The fuel warning system monitors the fuel pressure and temperature in the fuel
system. The fuel warning system includes pressure switches and temperature
sensors that supply status signals to the data concentration units (DCU’s) and the
FSC.
3. Operation
Refer to Figure 1.
A. Fuel−Quantity Gauging System
(1) The fuel−quantity transmitter probes and the compensators are variable capacitors
that change capacitance in relation to the amount of fuel that is inside. The sum of
all of the transmitter probes and compensators are used by the FSC to calculate the
fuel quantity for each fuel tank. This information is provided to the engine indication
and crew alerting system (EICAS) display and to the refuel/defuel control panel.
(2) Fuel quantity data is used by the FSC to control and monitor refuel/defuel
operations (28−25−00), and to control and monitor fuel transfer and power
crossflow (28−13−00).
B. Fuel Warning System
(1) Failures of the fuel system due to a loss of fuel pressure or low fuel temperature
(<−40 degrees C) are displayed on the EICAS. To monitor fuel pressure, the fuel
warning system uses pressure switches at the fuel manifolds and lines that follow:
± Left and right engine feed manifolds (main ejector pressure) (28−21−00)
± Left and right motive flow lines for the aft scavenge−ejector pumps (28−22−00)
± Left and right standby fuel−feed manifolds (booster pumps) (28−23−00)
± APU feed manifold (28−24−00).
(2) If there is a loss of fuel pressure at any of the pressure switches, the applicable
pressure switch sends a signal to the EICAS to show a caution message to the
flight crew.

Master
EFFECTIVITY: See Pageblock 28−40−00 page 1
28−40−00 Page 1
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
(3) The fuel temperature sensor (28−42−00) monitors the fuel temperature. When the
fuel temperature drops below −40 degrees C, a BULK FUEL TEMP caution
message is generated by the EICAS.

Master
EFFECTIVITY: See Pageblock 28−40−00 page 1
28−40−00 Page 2
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

LEFT MAIN FUEL

TANK
TEMPERATURE TRANSFER
SENSOR FUEL SYSTEM
(28−42−00) QTY. PROBES (28−13−00)
AND
COMPENSATORS
(28−41−00)
LEFT AND RIGHT
ENGINE
FUEL FEED
SYSTEM REFUEL/
(28−21−00) DEFUEL
(MAIN EJECTOR) SYSTEM
FUEL
(28−25−00)
QUANTITY
GAUGING
LEFT AND RIGHT (28−41−00)
MOTIVE
FLOW
SYSTEM
EICAS
(28−22−00)
DISPLAY
(SCAV. EJECTOR) FUEL
WARNING
(28−42−00)
LEFT AND RIGHT
STANDBY
FUEL FEED
SYSTEM
(28−23−00)
(BOOST PUMP)

APU FUEL
FEED
SYSTEM
(28−24−00)
ram2840000_001(2).dg, kms/pw, 10/04/01
(BOOST PUMP)

Indicating System − Block Diagram

Figure 1

Master
EFFECTIVITY: See Pageblock 28−40−00 page 1
28−40−00 Page 3
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C ALL
FUEL QUANTITY GAUGING SYSTEM − DESCRIPTION AND OPERATION

1. General
A. The fuel−quantity gauging system measures the amount of fuel in each fuel tank. This
information is used to control the fuel transfer and refuel and defuel systems and also
provides the aircrew with fuel quantity indication on the EICAS. The fuel−quantity
gauging system includes the components that follow:
± Fifteen fuel−quantity transmitter probes
± One fuel system computer (FSC)
± Five fuel magnetic level−indicators
± Two compensators
± Two aircraft attitude indicators.
The refuel/defuel panel (28−25−00) is also used in the fuel−quantity gauging system.
2. Component Details
A. Fuel−Quantity Transmitter Probe

Refer to Figure 1.
(1) The fuel−quantity transmitter probes are fiberglass−and−epoxy, capacitance−type
probes. These probes measure the fuel level in the related section of the fuel tank.
There are six probes in each main tank and three probes in the center tank.
(2) Each fuel−quantity transmitter probe has a fiberglass and epoxy body, a filter
circuit, and a terminal block. An AC signal (EXCT and RTN) is supplied to the probe
through the terminal block, and to the filter circuit. When the probe is in the fuel, the
capacitance of the probe is proportional to the level of the fuel. The signal (SIG) is
changed by the capacitance of the probe. When the fuel level changes, the
capacitance of the probe changes, which changes the signal (SIG). For every
change in the fuel level there is a proportional change in the probe capacitance and
the signal (SIG) from the probe.
B. Compensator
(1) The compensators are fiberglass−and−epoxy, capacitance−type probes. These
probes measure the fuel density in the main tanks. There is one probe in each main
tank near the inboard bulkhead.
(2) The compensators are identical to the fuel−quantity transmitter probes, but are
installed in each main tank near the bottom and parallel to the fuel tank floor.
Because the compensators are usually fully covered with fuel, their compensation
signal (COMP SIG) only changes when the density of the fuel changes due to the
temperature.
C. Fuel Magnetic Level−Indicator
(1) The fuel magnetic level−indicators are magnetically−controlled, manually−operated
measurement sticks. They are used to measure the fuel level in the fuel tanks when
the aircraft is on the ground if there is a failure in the fuel−quantity gauging system.
There are two level−indicators in each main tank and one level−indicator in the
center tank.

Master
EFFECTIVITY: See Pageblock 28−41−00 page 1
28−41−00 Page 1
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
(2) Each fuel magnetic level−indicator has a stick housing, a graduated magnetic
measurement−stick, and a magnetic float. As the fuel level in the fuel tanks
changes, the magnetic float moves up and down on the stick housing as it floats in
the fuel. When the operator releases the measurement stick from the housing, the
magnet on the stick comes near the magnet on the float. When the two magnets
are near each other, the measurement stick is held in place by the magnetic field.
The operator then examines the exposed marks on the measurement stick to
measure the fuel level.
D. Fuel System Computer
Refer to Figure 2.
(1) The fuel system computer is a dual−powered, two−channel computer. It is used to
automatically control the fuel system operations that follow:
± Automatic refueling of the aircraft (28−25−00)
± Fuel quantity measurement
± Power fuel crossflow between the main tanks (28−13−00)
± Fuel transfer from the center tank to the main tanks (28−13−00)
± Continuous built−in−test of the fuel system.
The fuel system computer is on the right side of the main avionics compartment, on
the top shelf.
(2) The fuel system computer has two microprocessor channels, two power supply
modules, and is housed in a 1/4 ATR type unit. The microprocessor channels
operate independently and are used as a backup in case one channel has a failure.
The microprocessor channels receive discrete signals from the fuel system and
aircraft attitude information. The microprocessor channels calculate the fuel level in
each tank and monitor the status of the pumps and valves of the fuel system. The
microprocessor channels supply signals to the power supply modules to change the
status of the pumps and valves when necessary.
(3) The power supply modules supply power to the microprocessor channels and
excitation signals (EXCT and RTN) to the fuel probes, the compensators, and the
high−level sensors. The power supply modules also supply driver signals to control
the valves and pumps of the fuel system. The power supply modules operate
independently and are used as a backup if one module has a failure.
E. Aircraft Attitude Indicator
(1) The aircraft attitude indicators are used to measure aircraft attitude while the aircraft
is on the ground. The attitude indicators are used with the fuel magnetic
level−indicators when the fuel levels are measured manually. The attitude indicators
are installed on the flight compartment right FWD bulkhead behind the copilot.
3. Operation
Refer to Figure 3.
A. The fuel system computer supplies a continuous excitation signal (EXCT and RTN) to
the fuel−quantity transmitter probes, the compensators, and the high−level sensors
(28−25−00). This signal goes to the filter circuit of the fuel probes and compensators.
The probes, compensators and the high−level sensors then change the signal (SIG) in
relation to the amount of fuel that covers each fuel probe or compensator. The fuel
system computer changes the probe analog signal to a digital signal and uses the
compensator signal to calculate the fuel density. The fuel density data is then used as a

Master
EFFECTIVITY: See Pageblock 28−41−00 page 1
28−41−00 Page 2
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
constant with the data from the fuel probes to calculate the fuel quantity in each fuel
tank. Total fuel quantity and fuel−used data are also calculated by the fuel system
computer.
B. Fuel quantity information is supplied to the refuel/defuel control panel and to the flight
compartment on the engine indication and crew alerting system (EICAS) display. The
fuel system computer also uses this data to calculate fuel balance. If there is a fuel
imbalance of more than 200 pounds (90 kg), the fuel system computer will operate the
transfer system (28−13−00) to move fuel from one main tank to the other.
C. Fuel quantity information is also used to control fuel transfer from the center tank to the
main tanks. If the fuel level in either of the main tanks is less than 93 percent full, the fuel
system computer will operate the fuel transfer system. The fuel transfer system then
moves fuel from the center tank to the applicable main tank. Fuel transfer will continue
until the main tank is 97 percent full.
D. During automatic refuel operations, the fuel system computer uses fuel quantity
information to control the pressure refuel/defuel system (28−25−00). Fuel quantity
information from the fuel system computer is supplied to the refuel/defuel control panel
for all pressure refuel/defuel operations.
E. If there is a failure of the fuel−quantity gauging system, the fuel level can be measured
when the aircraft is on the ground. The operator uses the fuel magnetic level−indicators
to measure the level of the fuel in each fuel tank. The operator then examines the aircraft
attitude indicators to measure the aircraft attitude. With this data, the operator examines
a reference table found in the aircraft flight manual (AFM) to calculate the fuel level in
each tank.
4. Component Location Index
Refer to Figure 4.
COMPONENT NAME QTY ACCESS/ZONE REFERENCE
Circuit breakers:
FUEL SYST CONT, M12 1 CBP−1/221 −
FUEL SYST CONT, B10 1 CBP−4/222 −
Compensator 2 540AB, 640AB 28−41−19
Computer, fuel system 1 811 28−41−16
Indicator, attitude (pitch) 1 222 28−41−25
Indicator, attitude (roll) 1 221 28−41−23
Indicator, fuel magnetic level 5 510AB, 540AB, 550BB, 28−41−10
640AB, 650BB
Probe, fuel quantity transmitter:
Left main tank 6 540AB, 540BB, 540EB, 28−41−04
550BB, 550DB, 550HB
Right main tank 6 640AB, 640BB, 640EB, 28−41−04
650BB, 650DB, 650HB
Center tank 3 510AB, 510BB, 610BB 28−41−04

Master
EFFECTIVITY: See Pageblock 28−41−00 page 1
28−41−00 Page 3
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

LEGEND 7 8 CL A
1. Main tank no.6. 6
2. Main tank no.5. 5
3. Main tank no.4. 4
4. Main tank no.3.
5. Main tank no.2. 3
6. Main tank no.1. 2
7. Center tank no.2.
1
8. Center tank no.1.
9. Center tank no.3. A
9

B CL

B B

GAUGING COMPONENT CODES

Fuel Quantity Transmitter B
Probe and Compensator
Fuel Magnetic Level Indicator

ram2841000_001.dg, ks/rm, 06/10/00

A
FUEL QUANTITY TRANSMITTER B
PROBE AND COMPENSATOR FUEL MAGNETIC LEVEL INDICATOR

Fuel Quantity Gauging System − Component Location/Recognition

Figure 1

Master
EFFECTIVITY: See Pageblock 28−41−00 page 1
28−41−00 Page 4
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

ram2841000_002.dc, KS, 04/07/91

A FUEL SYSTEM COMPUTER

Fuel System Computer − Component Location/Recognition

Figure 2

Master
EFFECTIVITY: See Pageblock 28−41−00 page 1
28−41−00 Page 5
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

COMPENSATOR

CENTER TANK FUEL QUANTITY

LEFT TRANSMITTER
RIGHT PROBES
MAIN
MAIN
TANK TANK

EICAS DISPLAY

TOTAL FUEL FUEL FUEL USED

KG OR LBS KG OR LBS
1060 KG

P P

KG OR LBS KG OR LBS

35 C 36 C

APU
LO PRESS LO PRESS
FUEL CH 1/2 FAIL

FUEL SYSTEM
COMPUTER
FUEL
DENSITY

FUEL FUEL
QUANTITY QTY
LAMP

LB CL OP SOV
ON
CL OP SOV
ON
CL OP
DEFUEL TEST

FUEL OR TEST

ON
OFF OFF FUEL
MANUAL
OFF

TRANSFER KG RIGHT
H.LEVEL DETECTOR
LEFT
FUEL AUTO

(28−13−00) POWER
PRES. TOTAL QTY
INC. ON
FUEL QTY
ram2841000_003(2).dg, ks/kms, 7/07/95

FAULT BITE
ANNUNC. KG OR LBS INITIA. DEC. OFF

REFUEL/DEFUEL
PRESSURE CONTROL PANEL
REFUEL/
DEFUEL
(28−25−00)

Fuel Quantity Gauging System − Schematic

Figure 3

Master
EFFECTIVITY: See Pageblock 28−41−00 page 1
28−41−00 Page 6
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

811

510AB 540BB
640BB
640AB
640CB

550DB
650DB

550HB
650HB

610AB 510BB 540AB 540CB

540EB
550BB 640EB
650BB

NOTE
500 series panels are on the left side.
600 series panels are on the right side.
ram2841000_004(2).dg, gg, 10/07/95

Fuel Quantity Gauging System − Component Access

Figure 4

Master
EFFECTIVITY: See Pageblock 28−41−00 page 1
28−41−00 Page 7
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C ALL
PROBE, FUEL QUANTITY TRANSMITTER − REMOVAL/INSTALLATION

1. General
A. The maintenance procedures that follow are for the removal and installation of the fuel
quantity transmitter probe (written as the "fuel probe" in this procedure). There are 15
fuel probes in the fuel system. There are six fuel probes in each main tank and three fuel
probes in the center tank.
B. It is necessary to defuel, drain, and remove the fuel fumes from the applicable fuel tank
to remove or install the fuel probes.

TASK 28−41−04−000−801
Removal of the Fuel Quantity Transmitter Probe

1. Job Set−Up Information

Subtask 28−41−04−946−001
A. Reference Information
REFERENCE DESIGNATION
TASK 12−11−28−650−804 Suction Defueling
TASK 28−00−00−910−801 Fuel Safety Precautions
TASK 28−11−00−840−801 Prepare Fuel Tank for Access
TASK 28−11−00−840−802 Removal of Fuel Fumes
TASK 28−11−01−000−801 Removal of the Honeycomb Access Panel
TASK 28−11−01−000−802 Removal of the Graphite Access Panel

2. Job Set−Up
Subtask 28−41−04−910−001
WARNING: OBEY ALL THE FUEL SAFETY PRECAUTIONS WHEN YOU DO WORK ON THE
FUEL SYSTEM AND/OR A FUEL SYSTEM COMPONENT. IF YOU DO NOT DO
THIS, YOU CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO
EQUIPMENT.
A. Obey all the fuel safety precautions (Ref. TASK 28−00−00−910−801).

Subtask 28−41−04−650−001
B. Defuel the applicable fuel tank (Ref. TASK 12−11−28−650−804).

Subtask 28−41−04−010−001
C. Remove the applicable access panels that follow (Ref. TASK 28−11−01−000−802):

Master
EFFECTIVITY: See Pageblock 28−41−04 page 401
28−41−04 Page 401
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

ACCESS DESIGNATION ITEM

510BB Fuel tank access panel Center fuel probe at LBL25.0
610BB Fuel tank access panel Center fuel probe at RBL43.0
540AB Fuel tank access panel Aft left fuel probe at WS47.0
540EB Fuel tank access panel Left fuel probe at WS125.0
550BB Fuel tank access panel Left fuel probe at WS196.0
550DB Fuel tank access panel Left fuel probe at WS239.0
640AB Fuel tank access panel Aft right fuel probe at WS47.0
640EB Fuel tank access panel Right fuel probe at WS125.0
650BB Fuel tank access panel Right fuel probe at WS196.0
650DB Fuel tank access panel Right fuel probe at WS239.0
D. Remove the applicable access panels that follow (Ref. TASK 28−11−01−000−801):
ACCESS DESIGNATION ITEM
510AB Fuel tank access panel Center fuel probe at LBL3.0
540BB Fuel tank access panel Forward left fuel probe at WS47.0
550HB Fuel tank access panel Left fuel probe at WS295.0
640BB Fuel tank access panel Forward right fuel probe at WS47.0
650HB Fuel tank access panel Right fuel probe at WS295.0

Subtask 28−41−04−840−001
E. Prepare the applicable fuel tank for access (Ref. TASK 28−11−00−840−801).
F. Remove the fuel fumes from the applicable fuel tank (Ref. TASK 28−11−00−840−802).

**ON A/C 7004−7019, 7021−7044, 7046, 7048, 7050, 7052, 7055−7056, 7059, 7061−7064,
7066−7067, 7069−7070, 7072−7073, 7075−7077, 7079−7080, 7085−7086, 7088−7094,
7099−7106, 7108−7111, 7113−7117, 7119, 7121−7123, 7125, 7127−7143, 7145−7152, 7154,
7156−7159, 7162−7163, 7165, 7167−7169, 7171−7176, 7178−7181, 7185−7196, 7199−7200,
7202−7222, 7224−7233, 7235−7236, 7238−7271, 7273−7294 Pre SB601R−24−090

Subtask 28−41−04−865−004
G. Open, safety and tag the circuit breakers that follow:
CB PANEL CB NO. NAME ZONE
CBP−1 M12 FUEL SYST CONT 221
CBP−4 B10 FUEL SYST CONT 222
CBP−5 B14 FUEL DEFL 311
CBP−5 B15 EMRG REFL 311

Master
EFFECTIVITY: See Pageblock 28−41−04 page 401
28−41−04 Page 402
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C 7003, 7020, 7045, 7047, 7049, 7051, 7053−7054, 7057−7058, 7060, 7065, 7071, 7074,
7078, 7081−7084, 7087, 7095−7098, 7107, 7112, 7118, 7120, 7124, 7126, 7144, 7153, 7155,
7160−7161, 7164, 7166, 7170, 7177, 7182−7184, 7197−7198, 7201, 7223, 7234, 7237, 7272,
7295−7990, 8000−8064, 8066−8068 and ON A/C 7004−7019, 7021−7044, 7046, 7048, 7050,
7052, 7055−7056, 7059, 7061−7064, 7066−7067, 7069−7070, 7072−7073, 7075−7077,
7079−7080, 7085−7086, 7088−7094, 7099−7106, 7108−7111, 7113−7117, 7119, 7121−7123,
7125, 7127−7143, 7145−7152, 7154, 7156−7159, 7162−7163, 7165, 7167−7169, 7171−7176,
7178−7181, 7185−7196, 7199−7200, 7202−7222, 7224−7233, 7235−7236, 7238−7271,
7273−7294 Post SB601R−24−090

Subtask 28−41−04−865−001
H. Open, safety and tag the circuit breakers that follow:
CB PANEL CB NO. NAME ZONE
CBP−1 M12 FUEL SYST CONT 221
CBP−4 B10 FUEL SYST CONT 222
CBP−5 B6 FUEL DEFL 311
CBP−5 B7 EMRG REFL 311

**ON A/C ALL

3. Procedure
Subtask 28−41−04−020−001
Refer to Figure 401.
A. Remove the fuel probe as follows:
NOTE: Before removing fuel probe, measure height for reinstallation.
(1) Remove the ty−wraps holding the wires (1) to the fuel probe (2).
(2) Disconnect the wires (1) from the fuel probe (2).
(3) Remove the screws (3), the clamps (4), and the fuel probe (2).
(4) Remove the tube guide (5) from the fuel probe (2).

Master
EFFECTIVITY: See Pageblock 28−41−04 page 401
28−41−04 Page 403
Dec 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL

NOTE:
Right side is shown.
Left side is opposite.

4
5
3

LEGEND.
1. Wire.
2. Fuel probe. 4
3. Screw.
4. Clamp.
5. Tube guide.

2
4
1
3

4
ram2841044_001(1).dc, jp, 16/02/93

TYPICAL

Fuel Quantity Transmitter Probe − Removal/Installation

Figure 401

Master
EFFECTIVITY: See Pageblock 28−41−04 page 401
28−41−04 Page 404
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
TASK 28−41−04−400−801
Installation of the Fuel Quantity Transmitter Probe

1. Job Set−Up Information

Subtask 28−41−04−945−001
A. Parts
REF NAME OF PART QTY IPC SEQUENCE NO.
3 Screw 4 IPC 28−41−00−1A−060
4 Clamp 2 IPC 28−41−00−1A−055
5 Tube guide 1 IPC 28−41−00−1A−070

Subtask 28−41−04−946−002
B. Reference Information
REFERENCE DESIGNATION
TASK 28−11−01−400−801 Installation of the Honeycomb Access Panel
TASK 28−11−01−400−802 Installation of the Graphite Access Panel
TASK 28−25−00−710−801 Operational Test of the Refuel/Defuel System
WM20−17−10 Wiring Manual

2. Procedure
Subtask 28−41−04−869−001
A. Make sure that the aircraft is in the same configuration as in the removal task.

Subtask 28−41−04−420−001
Refer to Figure 401.
B. Install the fuel probe as follows:
(1) Install the tube guide (5) on the rubber grommet on the fuel probe (2).
(2) Install the fuel probe (2), the clamps (4), and the screws (3).
(3) Connect the wires (1) to the fuel probe (2) (Ref. WM20−17−10).
(4) Secure the wires (1) over the fuel probe (2) using ty−wraps.

Master
EFFECTIVITY: See Pageblock 28−41−04 page 401
28−41−04 Page 405
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
3. Close Out
**ON A/C 7004−7019, 7021−7044, 7046, 7048, 7050, 7052, 7055−7056, 7059, 7061−7064,
7066−7067, 7069−7070, 7072−7073, 7075−7077, 7079−7080, 7085−7086, 7088−7094,
7099−7106, 7108−7111, 7113−7117, 7119, 7121−7123, 7125, 7127−7143, 7145−7152, 7154,
7156−7159, 7162−7163, 7165, 7167−7169, 7171−7176, 7178−7181, 7185−7196, 7199−7200,
7202−7222, 7224−7233, 7235−7236, 7238−7271, 7273−7294 Pre SB601R−24−090

Subtask 28−41−04−865−003
A. Remove the tags and close the circuit breakers that follow:
CB PANEL CB NO. NAME ZONE
CBP−1 M12 FUEL SYST CONT 221
CBP−4 B10 FUEL SYST CONT 222
CBP−5 B14 FUEL/DEFL 311
CBP−5 B15 EMRG REFL 311

**ON A/C 7003, 7020, 7045, 7047, 7049, 7051, 7053−7054, 7057−7058, 7060, 7065, 7071, 7074,
7078, 7081−7084, 7087, 7095−7098, 7107, 7112, 7118, 7120, 7124, 7126, 7144, 7153, 7155,
7160−7161, 7164, 7166, 7170, 7177, 7182−7184, 7197−7198, 7201, 7223, 7234, 7237, 7272,
7295−7990, 8000−8064, 8066−8068 and ON A/C 7004−7019, 7021−7044, 7046, 7048, 7050,
7052, 7055−7056, 7059, 7061−7064, 7066−7067, 7069−7070, 7072−7073, 7075−7077,
7079−7080, 7085−7086, 7088−7094, 7099−7106, 7108−7111, 7113−7117, 7119, 7121−7123,
7125, 7127−7143, 7145−7152, 7154, 7156−7159, 7162−7163, 7165, 7167−7169, 7171−7176,
7178−7181, 7185−7196, 7199−7200, 7202−7222, 7224−7233, 7235−7236, 7238−7271,
7273−7294 Post SB601R−24−090

Subtask 28−41−04−865−002
B. Remove the tags and close the circuit breakers that follow:
CB PANEL CB NO. NAME ZONE
CBP−1 M12 FUEL SYST CONT 221
CBP−4 B10 FUEL SYST CONT 222
CBP−5 B6 FUEL DEFL 311
CBP−5 B7 EMRG REFL 311

**ON A/C ALL

Subtask 28−41−04−410−001
C. Install the applicable access panels that follow (Ref. TASK 28−11−01−400−802):
ACCESS DESIGNATION ITEM
510BB Fuel tank access panel Center fuel probe at LBL25.0
610BB Fuel tank access panel Center fuel probe at RBL43.0
540AB Fuel tank access panel Aft left fuel probe at WS47.0
540EB Fuel tank access panel Left fuel probe at WS125.0

Master
EFFECTIVITY: See Pageblock 28−41−04 page 401
28−41−04 Page 406
Dec 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL

ACCESS DESIGNATION ITEM

550BB Fuel tank access panel Left fuel probe at WS196.0
550DB Fuel tank access panel Left fuel probe at WS239.0
640AB Fuel tank access panel Aft right fuel probe at WS47.0
640EB Fuel tank access panel Right fuel probe at WS125.0
650BB Fuel tank access panel Right fuel probe at WS196.0
650DB Fuel tank access panel Right fuel probe at WS239.0
D. Install the applicable access panels that follow (Ref. TASK 28−11−01−400−801):
ACCESS DESIGNATION ITEM
510AB Fuel tank access panel Center fuel probe at LBL3.0
540BB Fuel tank access panel Forward left fuel probe at WS47.0
550HB Fuel tank access panel Left fuel probe at WS295.0
640BB Fuel tank access panel Forward right fuel probe at WS47.0
650HB Fuel tank access panel Right fuel probe at WS295.0

Subtask 28−41−04−710−001
E. Do an operational test of the fuel probe (Ref. TASK 28−25−00−710−801).

Master
EFFECTIVITY: See Pageblock 28−41−04 page 401
28−41−04 Page 407
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C ALL
PROBES, FUEL QUANTITY TRANSMITTERS − ADJUSTMENT/TEST

TASK 28−41−04−720−801
Functional Test of the Fuel Quantity Transmitter Probes
1. General
A. The maintenance procedure that follows is for the functional test of the fuel quantity
transmitter probes. The test is done to verify the capacitance of each fuel quantity probe.
B. It is necessary to defuel and drain the fuel from the fuel tanks to do this test.

2. Job Set−Up Information

Subtask 28−41−04−943−001
A. Tools and Equipment
REFERENCE DESIGNATION
GSB2030001 or equivalent ARINC 429 databus analyzer
G601R340002−1 or equivalent Cable kit − ARINC 429

Subtask 28−41−04−946−003
B. Reference Information
REFERENCE DESIGNATION
TASK 10−11−00−869−801 Grounding of the Aircraft
TASK 12−00−07−861−801 Connect External AC Power
TASK 12−00−07−861−802 Remove External AC Power
TASK 12−11−28−910−801 Safety Precautions
TASK 12−11−28−650−804 Suction Defueling
TASK 28−00−00−910−801 Fuel Safety Precautions

Subtask 28−41−04−910−002
C. Obey all the fuel safety precautions (Ref. TASK 28−00−00−910−801).

3. Job Set−Up
Subtask 28−41−04−650−002
WARNING: OBEY ALL THE FUEL SAFETY PRECAUTIONS WHEN YOU DO WORK ON THE
FUEL SYSTEM AND/OR A FUEL SYSTEM COMPONENT. IF YOU DO NOT DO
THIS, YOU CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO
EQUIPMENT.
A. Suction defuel the aircraft (Ref. TASK 12−11−28−650−804).

Master
EFFECTIVITY: See Pageblock 28−41−04 page 501
28−41−04 Page 501
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
Subtask 28−41−04−865−005
B. Make sure that the circuit breakers that follow are closed:
CB PANEL CB NO. NAME ZONE
CBP−1 M12 FUEL SYST CONT 221
CBP−4 B10 FUEL SYST CONT 222

Subtask 28−41−04−010−002
C. Open the access door that follows:
ACCESS DESCRIPTION
811 Main Avionics Compartment

Subtask 28−41−04−480−001
D. On JB8 in the main avionics bay, remove the dust cap from connector J224.
E. Connect the databus reader to J224 as follows:
(1) Channel 1 ARINC output J224 (98) High, J224 (99) Low.
(2) Channel 2 ARINC output J224 (96) High, J224 (97) Low.
F. Connect the external AC power to the aircraft (Ref. TASK 12−00−07−861−801).
G. Set the databus reader options in the RECEIVER SETUP screen as follows:
NOTE: Follow these setup instructions for the Datatrac 400 ARINC 429 Databus
Analyzer. Refer to the operation manual for your specific databus reader for
detailed operating instructions for receiver setup.
RECEIVER SETUP
Control Setting Control Setting
Power ON Equip ID 000
Function RCV Format BCD
Channel 1 ON Max Digital (1,3,7,9) 7
ON/OFF ON Number of Digit (0−6) 5
Bus speed 12.5 KHZ (low) Number of Discrete 0
Data Format EDIT (USER) Range 1234.56
H. On the databus reader, push ENTER.
I. Set the databus reader options in the USER DEFINED DATA FORMAT SETUP screen
as follows:
(1) In the RECEIVER SETUP screen, scroll to the Data Format option, push ENTER.
(2) Select EDIT in the DATA FORMAT SELECTION screen, push ENTER.

Master
EFFECTIVITY: See Pageblock 28−41−04 page 501
28−41−04 Page 502
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
4. Procedure
Subtask 28−41−04−720−001
A. Do the test of the left tank fuel quantity transmitter probes as follows:
(1) In the USER DEFINED DATA FORMAT screen, in sequence, enter the options as
follows:
USER DEFINED DATA FORMAT
Control Setting Control Setting
Format Number 00 Number of Digit (0−6) 5
Equipment ID 000 Number of Discrete 0
Label 300 Range 1234.56
Format BDC Units USR
Max Digital (1,3,7,9) 7
(2) On the databus reader press ENTER.
(3) On the databus reader, make sure the label 257 is received as follows:
PROBE # EXPECTED VALUE ACTUAL CODED VALUE
1 37.00 − 39.30 04WX.Y0
2 27.00 − 29.50 08WX.Y0
3 42.40 − 44.60 0CWX.Y0
4 21.50 − 23.00 10WX.Y0
5 27.00 − 28.10 14WX.Y0
6 16.00 − 17.40 18WX.Y0
COMP. 56.80 − 59.00 1CWX.Y0

NOTE: WX.Y0 is the decoded capacitance value. Example: Probe #1 = 0458.90.

The decoded capacitance value is 58.90 pF.
B. Do the test of the right tank fuel quantity transmitter probes as follows:
(1) In the USER DEFINED DATA FORMAT screen, in sequence, enter the options as
follows:
USER DEFINED DATA FORMAT
Control Setting Control Setting
Format Number 02 Number of Digit (0−6) 5
Equipment ID 000 Number of Discrete 0
Label 302 Range 1234.56
Format BDC Units USR
Max Digital (1,3,7,9) 7
(2) On the databus reader press ENTER.
(3) On the databus reader, make sure the label 261 is received as follows:

Master
EFFECTIVITY: See Pageblock 28−41−04 page 501
28−41−04 Page 503
Mar 15/2005
 C
AIRCRAFT MAINTENANCE MANUAL

PROBE # EXPECTED VALUE ACTUAL CODED VALUE

1 37.00 − 39.30 04WX.Y0
2 27.00 − 29.50 08WX.Y0
3 42.40 − 44.60 0CWX.Y0
4 21.50 − 23.00 10WX.Y0
5 27.00 − 28.10 14WX.Y0
6 16.00 − 17.40 18WX.Y0
COMP. 56.80 − 59.00 1CWX.Y0

NOTE: WX.Y0 is the decoded capacitance value. Example: Probe #1 = 0458.90.

The decoded capacitance value is 58.90 pF.
C. Do the test of the center tank fuel quantity transmitter probes as follows:
(1) In the USER DEFINED DATA FORMAT screen, in sequence, enter the options as
follows:
USER DEFINED DATA FORMAT
Control Setting Control Setting
Format Number 01 Number of Digit (0−6) 5
Equipment ID 000 Number of Discrete 0
Label 301 Range 1234.56
Format BDC Units USR
Max Digital (1,3,7,9) 7
(2) On the databus reader press ENTER.
(3) On the databus reader, make sure the label 260 is received as follows:
PROBE # EXPECTED VALUE ACTUAL CODED VALUE
1 52.50 − 54.30 04WX.Y0
2 67.00 − 68.60 08WX.Y0
3 30.00 − 32.00 0CWX.Y0

NOTE: WX.Y0 is the decoded capacitance value. Example: Probe #1 = 0458.90.

The decoded capacitance value is 58.90 pF.

5. Close Out
Subtask 28−41−04−861−002
A. Remove external AC power from the aircraft (Ref. TASK 12−00−07−861−802).

Subtask 28−41−04−080−002
B. Disconnect Datatrac from J224.
C. Install the dust cap on the junction box.

Master
EFFECTIVITY: See Pageblock 28−41−04 page 501
28−41−04 Page 504
Mar 15/2005
 C
AIRCRAFT MAINTENANCE MANUAL
Subtask 28−41−04−941−001
D. Remove all tools, equipment and unwanted materials from the work area.

Subtask 28−41−04−410−002
E. Close the access door that follows:
ACCESS DESCRIPTION
811 Main Avionics Compartment

Master
EFFECTIVITY: See Pageblock 28−41−04 page 501
28−41−04 Page 505
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C ALL
INDICATOR, FUEL MAGNETIC LEVEL − REMOVAL/INSTALLATION

1. General
A. The maintenance procedures that follow are for the removal and installation of the fuel
magnetic level indicator (MLI). There are five MLI’s in the fuel system. There are two in
each main tank and one in the center tank.
B. It is necessary to defuel, drain, and remove the fuel fumes from the applicable fuel tank
to remove the MLI.

TASK 28−41−10−400−804
Removal of the Fuel Magnetic Level Indicator

1. Job Set−Up Information

Subtask 28−41−10−943−005
A. Tools and Equipment
REFERENCE DESIGNATION
None specified Scraper, nonmetallic

Subtask 28−41−10−946−004
B. Reference Information
REFERENCE DESIGNATION
TASK 12−11−28−650−804 Suction Defueling
TASK 28−00−00−910−801 Fuel Safety Precautions
TASK 28−11−00−840−801 Prepare Fuel Tank for Access
TASK 28−11−00−840−802 Removal of Fuel Fumes
TASK 28−11−01−000−801 Removal of the Honeycomb Access Panel
TASK 28−11−01−000−802 Removal of the Graphite Access Panel

2. Job Set−Up
Subtask 28−41−10−910−001
WARNING: OBEY ALL THE FUEL SAFETY PRECAUTIONS WHEN YOU DO WORK ON THE
FUEL SYSTEM AND/OR A FUEL SYSTEM COMPONENT. IF YOU DO NOT DO
THIS, YOU CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO
EQUIPMENT.
A. Obey all the fuel safety precautions (Ref. TASK 28−00−00−910−801).

Master
EFFECTIVITY: See Pageblock 28−41−10 page 401
28−41−10 Page 401
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
Subtask 28−41−10−650−002
CAUTION: WHEN DEFUELING THE AIRCRAFT, DO NOT CREATE A FUEL IMBALANCE OF
MORE THAN 2500 POUNDS (1134 KG). DAMAGE TO THE AIRCRAFT AND
EQUIPMENT CAN OCCUR.
B. Defuel the applicable fuel tank (Ref. TASK 12−11−28−650−804).
NOTE: It is not necessary to defuel the main tanks if the MLI in the centre tank has to
be removed.

Subtask 28−41−10−010−003
C. Remove the applicable access panels that follow (Ref. TASK 28−11−01−000−801):
ACCESS DESIGNATION ITEM
540BB Fuel tank access panel Left main tank inboard MLI
640BB Fuel tank access panel Right main tank inboard MLI
D. Remove the applicable access panels that follow (Ref. TASK 28−11−01−000−802):
ACCESS DESIGNATION ITEM
550BB Fuel tank access panel Left main tank outboard MLI
650BB Fuel tank access panel Right main tank outboard MLI
610AB Fuel tank access panel Center tank MLI

Subtask 28−41−10−840−002
E. Prepare the applicable fuel tank for access (Ref. TASK 28−11−00−840−801).
F. Remove the fuel fumes from the applicable fuel tank (Ref. TASK 28−11−00−840−802).

3. Procedure
Subtask 28−41−10−020−003
Refer to Figure 401.
A. Remove the MLI as follows:
(1) Use a nonmetallic scraper to remove the sealant around the bottom of the MLI
housing (1).
(2) Bend the tab on the lockwasher (5) away from the jamnut (2).
(3) Loosen the jamnut (2).
(4) Lower the MLI (1) and remove the cap (3) and the float (4).
(5) Remove the jamnut (2), the lockwasher (5), the spacer (6), and the MLI (1). Discard
the lockwasher.
(6) Remove and discard the preformed packing (7).
(7) Install the spacer (6), the lockwasher (5), the jamnut (2), the float (4), and the
cap (3) on the MLI (1).

Master
EFFECTIVITY: See Pageblock 28−41−10 page 401
28−41−10 Page 402
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

SUPPORT
BRACKET
(REF) 3

P
TO

LEGEND.
4 1. Fuel stick housing.
2. Jamnut.
3. Cap.
4. Float.
5. Lockwasher.
6. Spacer.
7. Preformed packing.
2

LOWER WING
SKIN (REF)
6 ram2841104_002.dg, ks, 20/08/92

7
1
TYPICAL

Fuel Magnetic Level Indicator − Removal/Installation

Figure 401

Master
EFFECTIVITY: See Pageblock 28−41−10 page 401
28−41−10 Page 403
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
TASK 28−41−10−400−805
Installation of the Fuel Magnetic Level Indicator

1. Job Set−Up Information

Subtask 28−41−10−944−002
A. Consumable Materials
REFERENCE DESIGNATION
06−002 Lubricant, petrolatum
09−013 Sealing compound

Subtask 28−41−10−945−002
B. Parts
REF NAME OF PART QTY IPC SEQUENCE NO.
7 Preformed packing 1 IPC 28−42−10−1A−020

Subtask 28−41−10−946−005
C. Reference Information
REFERENCE DESIGNATION
TASK 12−11−28−650−801 Automatic Pressure Refueling
TASK 28−11−01−400−801 Installation of the Honeycomb Access Panel
TASK 28−11−01−400−802 Installation of the Graphite Access Panel
TASK 51−80−00−100−802 Surface Preparation for Electrical Bonding

2. Procedure
Subtask 28−41−10−869−003
A. Make sure that the aircraft is in the same configuration as in the removal task.

Subtask 28−41−10−420−003
Refer to Figure 401.
B. Install the MLI as follows:
(1) Remove the cap (3), the float (4), the jamnut (2), the lockwasher (5), and the spacer
(6) from the MLI (1).
(2) Prepare the mating surfaces of the lower wing skin and the MLI (1) for electrical
bonding (Ref. TASK 51−80−00−100−802).
(3) Install the preformed packing (7) on the MLI (1).
(4) Put the MLI (1) through the hole in the lower wing skin.
(5) Slide the spacer (6), the lockwasher (5), and the jamnut (2) on the MLI. Do not
tighten the jamnut at this time.

Master
EFFECTIVITY: See Pageblock 28−41−10 page 401
28−41−10 Page 404
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
(6) Install the float (4) and the cap (3). Make sure that the TOP placard is on the top of
the float.
(7) Put the cap (3) into the support bracket. Tighten the jamnut (2).
(8) Move the float (4) up and down with your hand. Make sure that the float operates
smoothly along the full length of the MLI (1).
(9) Bend the tab on the lockwasher (5).
(10) Apply a brush coating of sealing compound on the lockwasher (5), the jamnut (2),
the spacer (6), and the lower wing skin.

Subtask 28−41−10−941−002
C. Remove all the tools, equipment, and unwanted materials from the area.

3. Close Out
Subtask 28−41−10−410−003
A. Install the applicable access panels that follow (Ref. TASK 28−11−01−400−801):
ACCESS DESIGNATION ITEM
540BB Fuel tank access panel Left main tank inboard MLI
640BB Fuel tank access panel Right main tank inboard MLI
B. Install the applicable access panels that follow (Ref. TASK 28−11−01−400−802):
ACCESS DESIGNATION ITEM
610AB Fuel tank access panel Center tank MLI
550BB Fuel tank access panel Left main tank outboard MLI
650BB Fuel tank access panel Right main tank outboard MLI

Subtask 28−41−10−210−002
C. Refuel the applicable fuel tank (Ref. TASK 12−11−28−650−801).
D. Examine the area around the MLI for leaks.

Master
EFFECTIVITY: See Pageblock 28−41−10 page 401
28−41−10 Page 405
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C ALL
COMPUTER, FUEL SYSTEM − REMOVAL/INSTALLATION

1. General
A. The maintenance procedures that follow are for the removal and installation of the fuel
system computer. There is one fuel system computer in the fuel system. It is on the right
side of the main avionics compartment, on the top shelf.

TASK 28−41−16−000−801
Removal of the Fuel System Computer

1. Job Set−Up Information

Subtask 28−41−16−946−001
A. Reference Information
REFERENCE DESIGNATION
TASK 24−00−00−910−801 Electrical/Electronic Safety Precautions

2. Job Set−Up
Subtask 28−41−16−010−001
A. Open the access door that follows:
ACCESS DESIGNATION
311BB Circuit breaker access door
811 Main avionics compartment door

**ON A/C 7004−7019, 7021−7044, 7046, 7048, 7050, 7052, 7055−7056, 7059, 7061−7064,
7066−7067, 7069−7070, 7072−7073, 7075−7077, 7079−7080, 7085−7086, 7088−7094,
7099−7106, 7108−7111, 7113−7117, 7119, 7121−7123, 7125, 7127−7143, 7145−7152, 7154,
7156−7159, 7162−7163, 7165, 7167−7169, 7171−7176, 7178−7181, 7185−7196, 7199−7200,
7202−7222, 7224−7233, 7235−7236, 7238−7271, 7273−7294 Pre SB601R−24−090

Subtask 28−41−16−865−001
B. Open, safety, and tag the circuit breakers that follow:
CB PANEL CB NO. NAME ZONE
CBP−1 M12 FUEL SYS CONT 221
CBP−4 B10 FUEL SYS CONT 222
CBP−5 B14 FUEL DEFL 311
CBP−5 B15 EMRG REFL 311

Master
EFFECTIVITY: See Pageblock 28−41−16 page 401
28−41−16 Page 401
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C 7003, 7020, 7045, 7047, 7049, 7051, 7053−7054, 7057−7058, 7060, 7065, 7071, 7074,
7078, 7081−7084, 7087, 7095−7098, 7107, 7112, 7118, 7120, 7124, 7126, 7144, 7153, 7155,
7160−7161, 7164, 7166, 7170, 7177, 7182−7184, 7197−7198, 7201, 7223, 7234, 7237, 7272,
7295−7990, 8000−8064, 8066−8068 and ON A/C 7004−7019, 7021−7044, 7046, 7048, 7050,
7052, 7055−7056, 7059, 7061−7064, 7066−7067, 7069−7070, 7072−7073, 7075−7077,
7079−7080, 7085−7086, 7088−7094, 7099−7106, 7108−7111, 7113−7117, 7119, 7121−7123,
7125, 7127−7143, 7145−7152, 7154, 7156−7159, 7162−7163, 7165, 7167−7169, 7171−7176,
7178−7181, 7185−7196, 7199−7200, 7202−7222, 7224−7233, 7235−7236, 7238−7271,
7273−7294 Post SB601R−24−090

Subtask 28−41−16−865−003
C. Open, safety, and tag the circuit breakers that follow:
CB PANEL CB NO. NAME ZONE
CBP−1 M12 FUEL SYS CONT 221
CBP−4 B10 FUEL SYS CONT 222
CBP−5 B6 FUEL DEFL 311
CBP−5 B7 EMRG REFL 311

**ON A/C ALL

Subtask 28−41−16−910−001
D. Obey all of the electrical/electronic safety precautions (Ref. TASK 24−00−00−910−801).

3. Procedure
Subtask 28−41−16−020−001
Refer to Figure 401.
A. Remove the fuel system computer as follows:
(1) Release the captive front clamp (1) that holds the fuel system computer (2) to the
mounting tray (3).
(2) Carefully pull the fuel system computer (2) out of the mounting tray (3). Do not lift it
until the connector is clear of the receptacle. Remove the fuel system computer.
(3) Install protective caps on the electrical connectors.

Master
EFFECTIVITY: See Pageblock 28−41−16 page 401
28−41−16 Page 402
Dec 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL

LEGEND.
1. Captive front clamp.
2. Fuel system computer.
3. Mounting tray.

1
ram2841164_001(1).dc, cr/pb, 09/03/93

Fuel System Computer − Removal/Installation

Figure 401

Master
EFFECTIVITY: See Pageblock 28−41−16 page 401
28−41−16 Page 403
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
TASK 28−41−16−400−801
Installation of the Fuel System Computer

1. Job Set−Up Information

Subtask 28−41−16−946−002
A. Reference Information
REFERENCE DESIGNATION
TASK 28−41−16−740−801 Fuel Computer Bite Check

2. Procedure
Subtask 28−41−16−420−001
Refer to Figure 401.
A. Install the fuel system computer as follows:
(1) Remove the protective caps from the electrical connectors.
(2) Put the fuel system computer (2) on the mounting tray (3). Carefully push it into the
mounting tray to engage the electrical connector.
(3) Set the captive front clamp (1) on the front of the mounting tray (3) to engage the
computer mounting−tray projection. Tighten the clamp.

3. Close Out
**ON A/C 7004−7019, 7021−7044, 7046, 7048, 7050, 7052, 7055−7056, 7059, 7061−7064,
7066−7067, 7069−7070, 7072−7073, 7075−7077, 7079−7080, 7085−7086, 7088−7094,
7099−7106, 7108−7111, 7113−7117, 7119, 7121−7123, 7125, 7127−7143, 7145−7152, 7154,
7156−7159, 7162−7163, 7165, 7167−7169, 7171−7176, 7178−7181, 7185−7196, 7199−7200,
7202−7222, 7224−7233, 7235−7236, 7238−7271, 7273−7294 Pre SB601R−24−090

Subtask 28−41−16−865−002
A. Remove the tags and close the circuit breakers that follow:
CB PANEL CB NO. NAME ZONE
CBP−1 M12 FUEL SYS CONT 221
CBP−4 B10 FUEL SYS CONT 222
CBP−5 B14 FUEL DEFL 311
CBP−5 B15 EMRG REFL 311

Master
EFFECTIVITY: See Pageblock 28−41−16 page 401
28−41−16 Page 404
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C 7003, 7020, 7045, 7047, 7049, 7051, 7053−7054, 7057−7058, 7060, 7065, 7071, 7074,
7078, 7081−7084, 7087, 7095−7098, 7107, 7112, 7118, 7120, 7124, 7126, 7144, 7153, 7155,
7160−7161, 7164, 7166, 7170, 7177, 7182−7184, 7197−7198, 7201, 7223, 7234, 7237, 7272,
7295−7990, 8000−8064, 8066−8068 and ON A/C 7004−7019, 7021−7044, 7046, 7048, 7050,
7052, 7055−7056, 7059, 7061−7064, 7066−7067, 7069−7070, 7072−7073, 7075−7077,
7079−7080, 7085−7086, 7088−7094, 7099−7106, 7108−7111, 7113−7117, 7119, 7121−7123,
7125, 7127−7143, 7145−7152, 7154, 7156−7159, 7162−7163, 7165, 7167−7169, 7171−7176,
7178−7181, 7185−7196, 7199−7200, 7202−7222, 7224−7233, 7235−7236, 7238−7271,
7273−7294 Post SB601R−24−090

Subtask 28−41−16−865−004
B. Remove the tags and close the circuit breakers that follow:
CB PANEL CB NO. NAME ZONE
CBP−1 M12 FUEL SYS CONT 221
CBP−4 B10 FUEL SYS CONT 222
CBP−5 B6 FUEL DEFL 311
CBP−5 B7 EMRG REFL 311

**ON A/C ALL

Subtask 28−41−16−710−001
C. Do the fuel computer bite check (Ref. TASK 28−41−16−740−801).

Subtask 28−41−16−410−001
D. Close the access door that follows:
ACCESS DESIGNATION
811 Main avionics compartment door
311BB Circuit breaker access door

Master
EFFECTIVITY: See Pageblock 28−41−16 page 401
28−41−16 Page 405
Dec 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C ALL
COMPUTER, FUEL SYSTEM − ADJUSTMENT/TEST

1. General
A. The maintenance procedure that follows is for the bite check of the fuel computer. Do
this test after the fuel computer is replaced.

TASK 28−41−16−740−801
Fuel Computer Bite Check

1. Job Set−Up Information

Subtask 28−41−16−946−003
A. Reference Information
REFERENCE DESIGNATION
TASK 12−00−07−861−801 Connect External AC Power
TASK 12−00−07−861−802 Remove External AC Power
TASK 24−00−00−910−801 Electrical/Electronic Safety Precautions

2. Job Set−up
Subtask 28−41−16−861−002
A. Obey all the electrical/electronic safety precautions (Ref. TASK 24−00−00−910−801).
B. Connect the external AC power (Ref. TASK 12−00−07−861−801).

Subtask 28−41−16−865−005
C. Make sure that the circuit breakers that follow are closed:
CB PANEL CB NO. NAME ZONE
CBP−1 H3 EICAS PRIM DISPL 221
CBP−1 H4 EICAS SEC DISPL 221
CBP−1 H5 EICAS LDU L 221
CBP−1 H6 EICAS BRT/DIM PWR SUPPL 1 221
CBP−1 H7 EICAS BRT/DIM PWR SUPPL 2 221
CBP−1 H8 EICAS BRT/DIM PWR SUPPL 3 221
CBP−1 M12 FUEL SYS CONT 221
CBP−2 C12 INTEG LTS C/PLT PNLS 222
CBP−2 K2 MFD 2 222
CBP−2 K3 EFIS CONT PNL 2 222
CBP−2 Q2 EICAS DCU 1 CH A 222
CBP−2 Q3 EICAS DCU 1 CH B 222
CBP−2 Q4 EICAS DCU 2 CH A 222
CBP−2 Q5 EICAS DCU 2 CH B 222

Master
EFFECTIVITY: See Pageblock 28−41−16 page 501
28−41−16 Page 501
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

CB PANEL CB NO. NAME ZONE

CBP−2 Q6 EICAS PRIM DISPL 222
CBP−2 Q7 EICAS SEC DISPL 222
CBP−2 Q8 EICAS CONT PNL 222
CBP−2 Q9 EICAS LDU R 222
CBP−2 Q10 EICAS BRT/DIM PWR SUPPL 1 222
CBP−2 Q11 EICAS BRT/DIM PWR SUPPL 2 222
CBP−2 Q12 EICAS BRT/DIM PWR SUPPL 3 222
CBP−3 B12 INTEG LTS PLT PNLS 221
CBP−4 B10 FUEL SYS CONT 222
CBP−4 C3 EFIS CRT DIMMING 222
CBP−4 C9 EFIS CONT PNL 1 222
CBP−4 C10 EICAS DCU 1 CH A 222
CBP−4 C11 EICAS DCU 1 CH B 222
CBP−4 D11 MFD 1 222
CBP−5 A6 DCU 2/3 311
CBP−5 B14 FUEL DEFL 311
CBP−5 B15 EMERG REFL 311

Subtask 28−41−16−010−002
D. Open the access door that follows:
ACCESS DESIGNATION
162AB Refuel/defuel control−panel access door

Subtask 28−41−16−861−004
E. Lift the guard and set the refuel/defuel control panel switch to ON.

3. Procedure
Subtask 28−41−16−740−001
A. Do the bite check of the fuel computer as follows:
(1) Push and hold the BITE INITIA. button on the refuel/defuel control panel and make
sure of the indications that follow:
(a) The LEFT FUEL QTY digits show 8888
(b) The CENTER FUEL QTY digits show 8888
(c) The RIGHT FUEL QTY digits show 8888
(d) The PRES TOTAL QTY digits show 88888
(2) Release the BITE INITIA. button.

Master
EFFECTIVITY: See Pageblock 28−41−16 page 501
28−41−16 Page 502
Sep 10/2004
 C
AIRCRAFT MAINTENANCE MANUAL
(3) If all the FUEL QTY digits are 88888 do the steps that follow:
NOTE: If any other code is displayed, go to step (6) of this procedure and find the
cause of the malfunction.
(a) Press the FUEL push−button on the engine indication and crew alerting
(EICAS) control panel.
(b) Make sure that the FUEL synoptic page is shown on the EICAS display ED 2.
(c) Make sure that the fuel messages on the FUEL synoptic page are shown as
follows:
DISPLAY MESSAGE
TOTAL FUEL Green
Fuel quantity left wing and right wing Green
Fuel quantity center tank Green
(if installed) (White if the tank is empty)
FUEL USED White
Fuel feel temperature Green
LH Engine fuel feed LO PRESS Amber
RH Engine fuel feed LO PRESS Amber
Fuel AUTO XFLOW INHIB White
NOTE: 1. The TOTAL FUEL quantity color changes according to the fuel computer
low level fuel label 276 bit 23 status.
2. The fuel quantity left wing and right wing color changes according to the
fuel computer labels 276 and 277 bit status.
3. The fuel quantity center tank color changes according to the fuel computer
label 276 bit 27 status.
4. The fuel feed temperature color changes to amber if the temperature is
less than 5 °C.
(4) Monitor the EICAS FUEL synoptic page as follows:
(a) Make sure that the fuel system components outlines that follow are shown in
white.
± Gravity XFLOW SOV
± XFLOW SOVs
± XFER SOVs
± APU Fuel SOV
± Engine Fuel SOVs
± Engine
± APU
(b) Make sure that the fuel system components outlines that follow are shown in
blue.
± Left tank fuel
± Right tank fuel
± Center tank fuel

Master
EFFECTIVITY: See Pageblock 28−41−16 page 501
28−41−16 Page 503
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
(5) If all the FUEL QTY digits are 88888 and the EICAS FUEL synoptic page displays
the correct indication, go to the Close Out.
(6) If the FUEL QTY digits show any other number, do the steps that follow:
(a) Set the maintenance (MAINT) switch to the MFD 1 or MFD 2 position. The
MAINT switch is installed on the lower panel of CBP−1.
(b) Make sure that the MAINTENANCE MENU page is shown on the MFD, with
the cursor at LRU STATUS.
(c) Use the BRG button to move the cursor to the LRU DIAGNOSITCS line.
(d) Press the RDR button on the display control panel.
(e) Make sure that the LRU DIAGNOSTIC DATA page shows on the MFD.
(f) Use the BRG button to scroll through the pages until the FQGC LRU is
displayed.
(g) Make sure that the bit sequence that follows is shown:
1 0000 0000 0000 0000 0000 0000
(h) Check the displayed bits against the tables that follow.
NOTE: Read the bits from right to left.
Fuel quantity gauge control (FQGC) diagnostic data word, octal address 276
BIT VALUE BIT NUMBER DESCRIPTION
1 9 *SDI code
2 10 *SDI code
4 11 APU pump on
8 12 APU pump failure

1 13 Left power transfer shut off valve (SOV) shut

2 14 Left power transfer SOV failure
4 15 Right power transfer SOV shut
8 16 Right power transfer SOV failure

1 17 Left cross−flow SOV shut

2 18 Left cross−flow SOV failure
4 19 Right cross−flow SOV shut
8 20 Right cross−flow SOV failure

1 21 Fuel unbalance >800 pounds

2 22 Spare
4 23 Low level fuel (Total = 900 pounds or < 900 pounds)
8 24 Computer channel 1 failure

1 25 Computer channel 2 failure

2 26 Fuel balance prevented
4 27 Center tank fitted

Master
EFFECTIVITY: See Pageblock 28−41−16 page 501
28−41−16 Page 504
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

Fuel quantity gauge control (FQGC) diagnostic data word, octal address 276
BIT VALUE BIT NUMBER DESCRIPTION
8 28 Units of measure (0 = pounds, 1 = kilograms)

1 29 Spare
2 30 * SSM code
4 31 * SSM code
8 32 Parity (odd)

*SDI Code: Bit 10 Bit 9 LRU Number **SSM Code: Bit 31 Bit 30 LRU Status
0 0 Not used 0 0 Normal
0 1 Channel 1 0 1 No data
1 0 Channel 2 1 0 Functional test
1 1 Not used 1 1 Failure

FQGC diagnostic data word, octal address 277

BIT VALUE BIT NUMBER DESCRIPTION
1 9 *SDI code
2 10 *SDI code
4 11 Tank mismatch (2/3)
8 12 Fuel units mismatch (kilograms/pounds)

1 13 Low fuel in the left wing

2 14 Low fuel in the right wing
4 15 Autofuel crossflow on
8 16 Autofuel crossflow override on (manual)

1 17 Spare
2 18 Spare
4 19 Spare
8 20 Left crossflow on

1 21 Right crossflow on
2 22 Left crossflow failure
4 23 Right crossflow failure
8 24 Spare

1 25 Spare
2 26 Spare
4 27 Spare
8 28 Spare

Master
EFFECTIVITY: See Pageblock 28−41−16 page 501
28−41−16 Page 505
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

FQGC diagnostic data word, octal address 277

BIT VALUE BIT NUMBER DESCRIPTION

1 29 Spare
2 30 * SSM code
4 31 * SSM code
8 32 Parity (odd)

*SDI Code: Bit 10 Bit 9 LRU Number **SSM Code: Bit 31 Bit 30 LRU Status
0 0 Not used 0 0 Normal
0 1 Channel 1 0 1 No data
1 0 Channel 2 1 0 Functional test
1 1 Not used 1 1 Failure

4. Close−Out
Subtask 28−41−16−860−002
A. If the maintenance (MAINT) switch was set to ON, set the maintenance (MAINT) switch
to the OFF position. The MAINT switch is installed on the lower panel of CBP−1.

Subtask 28−41−16−861−005
B. Set the refuel/defuel control panel switch to OFF and close the guard.

Subtask 28−41−16−410−002
C. Close the access door that follows:
ACCESS DESIGNATION
162AB Refuel/defuel control−panel access door

Subtask 28−41−16−861−001
D. Remove the external AC power (Ref. TASK 12−00−07−861−802).

Subtask 28−41−16−941−001
E. Remove all tools, equipment, and unwanted materials from the work area.

Master
EFFECTIVITY: See Pageblock 28−41−16 page 501
28−41−16 Page 506
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C 7288, 7368, 7528, 7801 Post SB601R−28−043
FILTER, ELECTRONIC − REMOVAL/INSTALLATION

1. General
A. The maintenance procedures that follow are for the removal and installation of the fuel
system electronic filter. There is one fuel system electronic filter in the fuel system. It is
on the right side of the main avionics compartment, on the top shelf.

TASK 28−41−17−000−801
Removal of the Fuel System Electronic Filter

1. Job Set−Up Information

Subtask 28−41−17−946−001
A. Reference Information
REFERENCE DESIGNATION
TASK 24−00−00−910−801 Electrical/Electronic Safety Precautions

2. Job Set−Up
Subtask 28−41−17−010−001
A. Open the access door that follows:
ACCESS DESIGNATION
311BB Circuit breaker access door
811 Main avionics compartment door

**ON A/C 7288 (Pre SB601R−24−090 and Post SB601R−28−043)

Subtask 28−41−17−865−001
B. Open, safety, and tag the circuit breakers that follow:
CB PANEL CB NO. NAME ZONE
CBP−1 M12 FUEL SYS CONT 221
CBP−4 B10 FUEL SYS CONT 222
CBP−5 B14 FUEL DEFL 311
CBP−5 B15 EMRG REFL 311

Master
EFFECTIVITY: See Pageblock 28−41−17 page 401
28−41−17 Page 401
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C 7288 (Post SB601R−24−090 and Post SB601R−28−043) and ON A/C 7368, 7528, 7801
Post SB601R−28−043

Subtask 28−41−17−865−002
C. Open, safety, and tag the circuit breakers that follow:
CB PANEL CB NO. NAME ZONE
CBP−1 M12 FUEL SYS CONT 221
CBP−4 B10 FUEL SYS CONT 222
CBP−5 B6 FUEL DEFL 311
CBP−5 B7 EMRG REFL 311

**ON A/C 7288, 7368, 7528, 7801 Post SB601R−28−043

Subtask 28−41−17−910−001
D. Obey all of the electrical/electronic safety precautions (Ref. TASK 24−00−00−910−801).

3. Procedure
Subtask 28−41−17−020−001
Refer to Figure 401
A. Remove the fuel system electronic filter as follows:
(1) Disconnect the electrical connectors (1) from the electronic filter.
(2) Install protective caps on the electrical connectors.
(3) Remove the nuts (3) and the washers (4) and (7) from the bonding straps (2).
(4) Remove the bonding straps (2).
(5) Remove the screws (5) and the washers (6) from the electronic filter.
(6) Remove the electronic filter.
(7) Install protective caps on the electrical connectors.

Master
EFFECTIVITY: See Pageblock 28−41−17 page 401
28−41−17 Page 402
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

5 LEGEND
6 1. Electrical connector.
2. Bonding strap.
ram2841174_001, ds, 14/08/03

2 3. Nut.
7 4. Washer.
4 5. Screw.
3 A
6. Washer.
7. Washer.

Electronic Filter − Removal / Installation

Figure 401

Master
EFFECTIVITY: See Pageblock 28−41−17 page 401
28−41−17 Page 403
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
TASK 28−41−17−400−801
Installation of the Fuel System Electronic Filter

1. Job Set−Up Information

Subtask 28−41−17−945−001
A. Parts
REF NAME OF PART QTY IPC SEQUENCE NO.
2 Bonding Strap 2 28−41−00−1A−205
3 Nut 2 28−41−00−1A−210
4 Washer 2 28−41−00−1A−215
5 Screw 4 28−41−00−1A−195
6 Washer 4 28−41−00−1A−200
7 Washer 2 28−41−00−1A−220

Subtask 28−41−17−869−001
B. Make sure that the aircraft is in the same configuration as the removal task.

Subtask 28−41−17−946−002
C. Reference Information
REFERENCE DESIGNATION
TASK 28−41−16−740−801 Fuel Computer Bite Check

2. Procedure
Refer to Figure 401
Subtask 28−41−17−420−001
A. Install the fuel system electronic filter as follows:
(1) Remove the protective caps from the electrical connectors.
(2) Install the electronic filter with the screws (5) and washers (6).
(3) Install the bonding straps (2) with the nuts (3) and the washers (4) and (7).
(4) Connect the electrical connectors (1).

3. Close Out
**ON A/C 7288 (Pre SB601R−24−090 and Post SB601R−28−043)

Subtask 28−41−17−865−003
A. Remove the tags and close the circuit breakers that follow:

Master
EFFECTIVITY: See Pageblock 28−41−17 page 401
28−41−17 Page 404
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

CB PANEL CB NO. NAME ZONE

CBP−1 M12 FUEL SYS CONT 221
CBP−4 B10 FUEL SYS CONT 222
CBP−5 B14 FUEL DEFL 311
CBP−5 B15 EMRG REFL 311

**ON A/C 7288 (Post SB601R−24−090 and Post SB601R−28−043) and ON A/C 7368, 7528, 7801
Post SB601R−28−043

Subtask 28−41−17−865−004
B. Remove the tags and close the circuit breakers that follow:
CB PANEL CB NO. NAME ZONE
CBP−1 M12 FUEL SYS CONT 221
CBP−4 B10 FUEL SYS CONT 222
CBP−5 B6 FUEL DEFL 311
CBP−5 B7 EMRG REFL 311

**ON A/C 7288, 7368, 7528, 7801 Post SB601R−28−043

Subtask 28−41−17−710−001
C. Do the fuel computer bite check (Ref. TASK 28−41−16−740−801).

Subtask 28−41−17−410−001
D. Close the access door that follows:
ACCESS DESIGNATION
811 Main avionics compartment door
311BB Circuit breaker access door

Master
EFFECTIVITY: See Pageblock 28−41−17 page 401
28−41−17 Page 405
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C ALL
COMPENSATOR − REMOVAL/INSTALLATION

1. General
A. The maintenance procedures that follow are for the removal and installation of the
compensator. There are two compensators in the fuel system. They are found in the
inboard sections of the main tanks.
B. It is necessary to defuel, drain, and remove the fuel fumes from the applicable main tank
to remove or install the compensator.

TASK 28−41−19−000−801
Removal of the Compensator

1. Job Set−Up Information

Subtask 28−41−19−946−001
A. Reference Information
REFERENCE DESIGNATION
TASK 12−11−28−650−804 Suction Defueling
TASK 28−00−00−910−801 Fuel Safety Precautions
TASK 28−11−00−840−801 Prepare Fuel Tank for Access
TASK 28−11−00−840−802 Removal of Fuel Fumes
TASK 28−11−01−000−801 Removal of the Honeycomb Access Panel

2. Job Set−Up
Subtask 28−41−19−910−001
WARNING: OBEY ALL THE FUEL SAFETY PRECAUTIONS WHEN YOU DO WORK ON THE
FUEL SYSTEM AND/OR A FUEL SYSTEM COMPONENT. IF YOU DO NOT DO
THIS, YOU CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO
EQUIPMENT.
A. Obey all the fuel safety precautions (Ref. TASK 28−00−00−910−801).

Subtask 28−41−19−650−001
B. Defuel the applicable main tank (Ref. TASK 12−11−28−650−804).

Subtask 28−41−19−010−001
C. Remove the applicable access panels that follow (Ref. TASK 28−11−01−000−801):
ACCESS DESIGNATION
540BB Fuel tank access panel
640BB Fuel tank access panel

Master
EFFECTIVITY: See Pageblock 28−41−19 page 401
28−41−19 Page 401
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
Subtask 28−41−19−840−001
D. Prepare the applicable main tank for access (Ref. TASK 28−11−00−840−801).
E. Remove the fuel fumes from the applicable main tank (Ref. TASK 28−11−00−840−802).

**ON A/C 7004−7019, 7021−7044, 7046, 7048, 7050, 7052, 7055−7056, 7059, 7061−7064,
7066−7067, 7069−7070, 7072−7073, 7075−7077, 7079−7080, 7085−7086, 7088−7094,
7099−7106, 7108−7111, 7113−7117, 7119, 7121−7123, 7125, 7127−7143, 7145−7152, 7154,
7156−7159, 7162−7163, 7165, 7167−7169, 7171−7176, 7178−7181, 7185−7196, 7199−7200,
7202−7222, 7224−7233, 7235−7236, 7238−7271, 7273−7294 Pre SB601R−24−090

Subtask 28−41−19−865−003
F. Open, safety and tag the circuit breakers that follow:
CB PANEL CB NO. NAME ZONE
CBP−1 M12 FUEL SYST CONT 221
CBP−4 B10 FUEL SYST CONT 222
CBP−5 B14 FUEL DEFL 311
CBP−5 B15 EMRG REFL 311

**ON A/C 7003, 7020, 7045, 7047, 7049, 7051, 7053−7054, 7057−7058, 7060, 7065, 7071, 7074,
7078, 7081−7084, 7087, 7095−7098, 7107, 7112, 7118, 7120, 7124, 7126, 7144, 7153, 7155,
7160−7161, 7164, 7166, 7170, 7177, 7182−7184, 7197−7198, 7201, 7223, 7234, 7237, 7272,
7295−7990, 8000−8064, 8066−8068 and ON A/C 7004−7019, 7021−7044, 7046, 7048, 7050,
7052, 7055−7056, 7059, 7061−7064, 7066−7067, 7069−7070, 7072−7073, 7075−7077,
7079−7080, 7085−7086, 7088−7094, 7099−7106, 7108−7111, 7113−7117, 7119, 7121−7123,
7125, 7127−7143, 7145−7152, 7154, 7156−7159, 7162−7163, 7165, 7167−7169, 7171−7176,
7178−7181, 7185−7196, 7199−7200, 7202−7222, 7224−7233, 7235−7236, 7238−7271,
7273−7294 Post SB601R−24−090

Subtask 28−41−19−865−001
G. Open, safety and tag the circuit breakers that follow:
CB PANEL CB NO. NAME ZONE
CBP−1 M12 FUEL SYST CONT 221
CBP−4 B10 FUEL SYST CONT 222
CBP−5 B6 FUEL DEFL 311
CBP−5 B7 EMRG REFL 311

**ON A/C ALL

3. Procedure
Subtask 28−41−19−020−001
Refer to Figure 401.

Master
EFFECTIVITY: See Pageblock 28−41−19 page 401
28−41−19 Page 402
Dec 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
A. Remove the compensator as follows:
(1) Cut and discard the ty−wraps.
(2) Disconnect the wires (1) from the compensator (2).
(3) Remove the screws (3), the clamps (4), and the compensator (2).
(4) Remove the tube guide (5) from the compensator (2).

Master
EFFECTIVITY: See Pageblock 28−41−19 page 401
28−41−19 Page 403
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

LEGEND.
1. Wire.
2. Compensater.
3. Screw.
4. Bracket.
5. Tube guide.

5
4

4 4

3
2

3
ram2841194_001(1).dc, ks, 11/03/93

Compensator − Removal/Installation
Figure 401

Master
EFFECTIVITY: See Pageblock 28−41−19 page 401
28−41−19 Page 404
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
TASK 28−41−19−400−801
Installation of the Compensator

1. Job Set−Up Information

Subtask 28−41−19−946−002
A. Reference Information
REFERENCE DESIGNATION
TASK 28−11−01−400−801 Installation of the Honeycomb Access Panel
TASK 28−25−00−710−801 Operational Test of the Refuel/Defuel System
WM20−17−10 Wiring Manual

2. Procedure
Subtask 28−41−19−869−001
A. Make sure that the aircraft is in the same configuration as in the removal task.

Subtask 28−41−19−420−001
Refer to Figure 401.
B. Install the compensator as follows:
(1) Install the tube guide (5) on the compensator (2).
(2) Install the compensator (2), the brackets (4), and the screws (3).
(3) Connect the wires (1) to the compensator (2) (Ref. WM20−17−10).
(4) Secure the wires (1) to the compensator (2) using three ty−wraps.

3. Close Out
**ON A/C 7004−7019, 7021−7044, 7046, 7048, 7050, 7052, 7055−7056, 7059, 7061−7064,
7066−7067, 7069−7070, 7072−7073, 7075−7077, 7079−7080, 7085−7086, 7088−7094,
7099−7106, 7108−7111, 7113−7117, 7119, 7121−7123, 7125, 7127−7143, 7145−7152, 7154,
7156−7159, 7162−7163, 7165, 7167−7169, 7171−7176, 7178−7181, 7185−7196, 7199−7200,
7202−7222, 7224−7233, 7235−7236, 7238−7271, 7273−7294 Pre SB601R−24−090

Subtask 28−41−19−865−004
A. Remove the tags and close the circuit breakers that follow:
CB PANEL CB NO. NAME ZONE
CBP−1 M12 FUEL SYST CONT 221
CBP−4 B10 FUEL SYST CONT 222
CBP−5 B14 FUEL DEFL 311
CBP−5 B15 EMRG REFL 311

Master
EFFECTIVITY: See Pageblock 28−41−19 page 401
28−41−19 Page 405
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C 7003, 7020, 7045, 7047, 7049, 7051, 7053−7054, 7057−7058, 7060, 7065, 7071, 7074,
7078, 7081−7084, 7087, 7095−7098, 7107, 7112, 7118, 7120, 7124, 7126, 7144, 7153, 7155,
7160−7161, 7164, 7166, 7170, 7177, 7182−7184, 7197−7198, 7201, 7223, 7234, 7237, 7272,
7295−7990, 8000−8064, 8066−8068 and ON A/C 7004−7019, 7021−7044, 7046, 7048, 7050,
7052, 7055−7056, 7059, 7061−7064, 7066−7067, 7069−7070, 7072−7073, 7075−7077,
7079−7080, 7085−7086, 7088−7094, 7099−7106, 7108−7111, 7113−7117, 7119, 7121−7123,
7125, 7127−7143, 7145−7152, 7154, 7156−7159, 7162−7163, 7165, 7167−7169, 7171−7176,
7178−7181, 7185−7196, 7199−7200, 7202−7222, 7224−7233, 7235−7236, 7238−7271,
7273−7294 Post SB601R−24−090

Subtask 28−41−19−865−002
B. Remove the tags and close the circuit breakers that follow:
CB PANEL CB NO. NAME ZONE
CBP−1 M12 FUEL SYST CONT 221
CBP−4 B10 FUEL SYST CONT 222
CBP−5 B6 FUEL DEFL 311
CBP−5 B7 EMRG REFL 311

**ON A/C ALL

Subtask 28−41−19−410−001
C. Install the applicable access panels that follow (Ref. TASK 28−11−01−400−801):
ACCESS DESIGNATION
540BB Fuel tank access panel
640BB Fuel tank access panel

Subtask 28−41−19−710−001
D. Do an operational test of the compensator (Ref. TASK 28−25−00−710−801).

Master
EFFECTIVITY: See Pageblock 28−41−19 page 401
28−41−19 Page 406
Dec 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C ALL
ATTITUDE INDICATORS − REMOVAL/INSTALLATION

1. General
A. The maintenance procedures that follow are for the removal and installation of the
aircraft attitude indicators. There are two indicators that show aircraft orientation,
measured in degrees, one for roll and one for pitch. These are used together with the
fuel magnetic level indicators to manually find the aircraft‘s fuel quantity. The attitude
indicators are installed on the flight compartment, right forward bulkhead, behind the
copilots seat.

TASK 28−41−23−000−801
Removal of the Attitude Indicators

1. Procedure
**ON A/C 7003−7067, 7069−7082

Subtask 28−41−23−020−001
Refer to Figure 401.
A. Remove the ROLL attitude Indicator as follows:
(1) Remove the two screws (1) from the front of the ROLL attitude Indicator (2) and put
in a safe location.
(2) Pull the ROLL attitude indicator (2) away from its installed recess.
(3) Remove the ROLL attitude (2) indicator from the aircraft.

**ON A/C 7083−7990, 8000−8064, 8066−8068

Subtask 28−41−23−020−002
Refer to Figure 402.
B. Remove the ROLL attitude Indicator as follows:
(1) Remove the two screws (1), together with plastic washers (2) from the front of the
ROLL attitude Indicator (3) and put in a safe location.
(2) Pull the ROLL attitude indicator (3) away from its recess.
(3) Remove the ROLL attitude indicator (3) from the aircraft.

**ON A/C 7003−7067, 7069−7082

Subtask 28−41−23−020−003
Refer to Figure 401.
C. Remove the PITCH attitude Indicator as follows:
(1) Remove the two screws (3) from the front of the PITCH attitude Indicator (4) and
put in a safe location.
(2) Pull the PITCH attitude indicator (4) away from its recess.

Master
EFFECTIVITY: See Pageblock 28−41−23 page 401
28−41−23 Page 401
Dec 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
(3) Remove the PITCH attitude indicator (4) from the aircraft.

**ON A/C 7083−7990, 8000−8064, 8066−8068

Subtask 28−41−23−020−004
Refer to Figure 402.
D. Remove the PITCH attitude Indicator as follows:
(1) Remove the two screws (4), together with plastic washers (5) from the front of the
PITCH attitude indicator (6) and put in a safe location.
(2) Pull the PITCH attitude indicator (6) away from its recess.
(3) Remove the PITCH attitude indicator (6) from the aircraft.

Master
EFFECTIVITY: See Pageblock 28−41−23 page 401
28−41−23 Page 402
Dec 10/2005
 AIRCRAFT MAINTENANCE MANUAL
C
LEGEND
1. Screw.
2. ROLL indicator.
3. Screw.
4. PITCH indicator.

RIG
WI HT
N
UG
A P2
B
1
O

C
D
F 1
E
RO
O

G
H
J
K
LL
L
M
N
GR P
OU Q
2
ND R
FU ATT S 2 L
EL ITU
T WIEFT
O

ML DE
I S IN U N
YS DIC
TE A V UPG
M TO
R W

CH 2 1
PIT
ram2841234_001.dg, jp, 05/02/99

4 3
6 5
7
8
109 R
11 DIC
ATO
E IN EM
UD ST
TIT SY
AT MLI
ND EL
OU FU
GR

Attitude Indicators − Removal/Installation

Figure 401

Master
EFFECTIVITY: See Pageblock 28−41−23 page 401
28−41−23 Page 403
Apr 20/2004
 AIRCRAFT MAINTENANCE MANUAL
C
LEGEND
1. Screw.
2. Captive washer.
3. ROLL indicator.
4. Screw.
5. Captive washer.
6. PITCH indicator.

1 RIG
WI HT
N
UG
2 A P2
B
O

C
D
F 1
E
RO
O

G
H
J
K
LL
L
M
N
GR P
OU Q
3
ND R
FU ATT S 2 L
EL ITU
T WIEFT
O

ML DE
I S IN U N
YS DIC
TE A V UPG
M TO
R W

1
2

CH 2 1
PIT 4
ram2841234_002.dg, jp, 05/02/99

4 3
6 5

09
8
7
5
111 ATO
R
DIC
E IN EM
UD ST
TIT SY
AT MLI
ND EL
OU FU
GR

4
5

Attitude Indicators − Removal/Installation

Figure 402

Master
EFFECTIVITY: See Pageblock 28−41−23 page 401
28−41−23 Page 404
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C ALL
TASK 28−41−23−400−801
Installation of the Attitude Indicators

1. Job Set−Up Information

Subtask 28−41−23−946−001
A. Reference Information
REFERENCE DESIGNATION
SRM 51−22−41 Structural Repair Manual − General Non−Structural
Bonding of Different Materials for Operational
Temperatures of −55°C (−67°F) to 71°C (160°F)
TASK 08−20−00−589−801 Levelling of the Aircraft
TASK 20−21−00−910−801 Torquing − Maintenance Practices

2. Job Set−Up
Subtask 28−41−23−869−001
A. Make sure that the aircraft is in the same configuration as in the removal task.

Subtask 28−41−23−589−001
B. Level the aircraft (Ref. TASK 08−20−00−589−801).

3. Procedure
**ON A/C 7003−7067, 7069−7082

Subtask 28−41−23−420−001
Refer to Figure 401.
A. Install the ROLL attitude indicator as follows:
(1) Apply bonding cement to the recess (Ref. SRM 51−22−41).
(2) Put ROLL attitude indicator (2) in its recess.
(3) Install the two screws (1) and tighten by hand only.
(4) Adjust the position of the ROLL attitude indicator (2) until the bubble shows 0° (zero
degrees).
(5) Torque the two screws (1) (Ref. TASK 20−21−00−910−801).

**ON A/C 7083−7990, 8000−8064, 8066−8068

Subtask 28−41−23−420−002
Refer to Figure 402.

Master
EFFECTIVITY: See Pageblock 28−41−23 page 401
28−41−23 Page 405
Dec 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
B. Install the ROLL attitude indicator as follows:
(1) Apply bonding cement to the recess (Ref. SRM 51−22−41).
(2) Put ROLL attitude indicator (3) in its recess.
(3) Install the two screws (1), together with plastic washers (2) and tighten by hand
only.
(4) Adjust the position of the ROLL attitude indicator (3) until the bubble shows 0° (zero
degrees).
(5) Turn the two plastic washers (2) until you have a clear view of the text and the sight
glass.
(6) Torque the two screws (1) (Ref. TASK 20−21−00−910−801).

**ON A/C 7003−7067, 7069−7082

Subtask 28−41−23−420−003
Refer to Figure 401.
C. Install the PITCH attitude indicator as follows:
(1) Apply bonding cement to the recess (Ref. SRM 51−22−41).
(2) Put PITCH attitude indicator (4) in its recess.
(3) Install the two screws (3) and tighten by hand only.
(4) Adjust the position of the PITCH attitude indicator (4) until the bubble shows 0°
(zero degrees).
(5) Torque the two screws (3) (Ref. TASK 20−21−00−910−801).

**ON A/C 7083−7990, 8000−8064, 8066−8068

Subtask 28−41−23−420−004
Refer to Figure 402.
D. Install the PITCH attitude indicator as follows:
(1) Apply bonding cement to the recess (Ref. SRM 51−22−41).
(2) Put PITCH attitude indicator (6) in its recess.
(3) Install the two screws (4), together with plastic washers (5) and tighten by hand
only.
(4) Adjust the position of the PITCH attitude indicator (6) until the bubble shows 0°
(zero degrees).
(5) Turn the top plastic washer (5) until you can clearly see the text.
(6) Torque the two screws (4) (Ref. TASK 20−21−00−910−801).
**ON A/C ALL

Master
EFFECTIVITY: See Pageblock 28−41−23 page 401
28−41−23 Page 406
Dec 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
4. Close Out
Subtask 28−41−23−941−001
A. Remove all tools, equipment and unwanted materials from the work area.

Master
EFFECTIVITY: See Pageblock 28−41−23 page 401
28−41−23 Page 407
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C ALL
FUEL WARNING SYSTEM − DESCRIPTION AND OPERATION

1. General
A. The fuel warning system measures the amount of fuel pressure and the fuel temperature
in the fuel system. This information is used to monitor the operation of the fuel system
and is displayed on the EICAS. The fuel warning system includes the components that
follow:
± Two boost−pump pressure switches
± Two engine−fuel−feed pressure switches (main ejector pressure)
± Two boost−pump control relays
± Two scavenge−ejector differential−pressure switches
± One auxiliary power unit (APU)−fuel−pump pressure switch
± One fuel temperature sensor.
2. Component Details
A. Boost−Pump Pressure Switch
Refer to Figure 1.
(1) The boost−pump pressure switches are double−pole, double−throw,
pressure−actuated switches. These pressure switches measure the fuel pressure in
the standby fuel−feed manifold. They are installed in the main wheel well on the
rear bulkhead of the center wing box.
(2) Each boost−pump pressure switch has an electrical connector, and a pressure
actuated switch. When the pressure in the standby fuel−feed manifold is 10.0 psi
(69.0 kPa), one set of switch contacts close to supply a ground signal to the data
concentrator unit (DCU).
(3) When the pressure in the standby fuel−feed manifold is less than 8.0 (+1.0) psi
(55.2 kPa), the switch contacts move back to the relaxed position. The switch then
supplies another ground signal to the DCU through another set of contacts.
B. Engine−Fuel−Feed Pressure Switch
(1) The engine−fuel−feed pressure switches are double−pole, double−throw,
pressure−actuated switches. These pressure switches measure the fuel (L & R
main ejector) pressure in the engine fuel−feed manifold. They are installed in the
main wheel well on the rear bulkhead of the center wing box. These pressure
switches are the same as the boost−pump pressure switches.
(2) Each engine−fuel−feed pressure switch has an electrical connector, and pressure
actuated switches. When the pressure in the engine fuel−feed manifold (L or R
main ejector) is more than 10 psi (69 kPa), one of the normally closed contacts
open. This removes the ground from the boost pump relay coils. The other set of
normally closed contacts open, removing the ground from the DCU, which cancels
the EICAS L (R) MAIN EJECTOR caution message.
(3) When the pressure in the engine−fuel−feed manifold is less than 8.0 (+1.0) psi
(55.2 kPa), one set of open contacts return to the normally closed position
supplying a ground return for the boost pump relay coils. The other set of open
contacts return to the normally closed position supplying a ground for the DCU
which generates the EICAS L (R) MAIN EJECTOR caution message.

Master
EFFECTIVITY: See Pageblock 28−42−00 page 1
28−42−00 Page 1
Mar 15/2005
 C
AIRCRAFT MAINTENANCE MANUAL
C. Scavenge−Ejector Differential−Pressure Switch
(1) The scavenge−ejector differential−pressure switches are single−pole, single−throw,
pressure−actuated switches. These switches measure the fuel pressure difference
in the venturi of the motive flow system (28−22−00). They are installed on the
inboard bulkhead of each main tank.
(2) Each scavenge−ejector differential−pressure switch has a differential pressure (∆ p)
actuated switch, a HIGH−pressure port and a LOW−pressure port. When the
pressure at the HIGH−pressure port is 3.3 psi (22.8 kPa) more than the pressure in
the LOW−pressure port, the switch opens. When the switch opens, it disconnects a
ground signal from the DCU which cancels the L (R) SCAV EJECTOR, EICAS
message.
(3) When the pressure difference at the pressure ports decreases to less than 2.1 to
(+1.4) psi (15.5 kPa), the switch contacts return to the closed position which
provides the ground signal to the DCU which generates the EICAS L (R) SCAV
EJECTOR message.
D. APU−Fuel−Pump Pressure Switch
(1) The APU−fuel−pump pressure switch is a double−pole, double−throw,
pressure−actuated switch. This switch measures the APU fuel pump discharge
pressure. It is installed in the right main wheel well on the APU fuel−pump cartridge
(28−24−00).
(2) The APU−fuel pump pressure switch has an electrical connector and a pressure
actuated switch. When the discharge pressure from the APU fuel pump is 12.0 psi
(82.8 kPa), the switch closes. The switch then supplies a ground signal to the fuel
system computer.
(3) When the pressure in the APU fuel pump is less than 7.5 (+1.0) psi (51.8 kPa), the
switch opens. When the switch opens, the switch removes the ground signal from
the fuel system computer.
E. Fuel Temperature Sensor
(1) The fuel temperature sensor has a thyrister sensing element. As the temperature of
the fuel changes, the resistance of the thyrister changes. The fuel temperature
sensor is mounted in the left main fuel tank.
3. Operation
Refer to Figure 2.
A. During normal operation, the engine fuel−feed system (28−21−00) supplies fuel pressure
to the engine feed manifold. The fuel pressure is monitored by the engine−fuel−feed
pressure switch. When there is engine fuel feed pressure, the pressure switch removes
the ground return from the boost−pump control relay coil and removes the MAIN
EJECTOR LOW PRESSURE ground from the DCU. When the boost pump switch/light is
off and there is no pressure in the standby fuel−feed manifold, as sensed by the boost
pump pressure switch, a FUEL PUMP INOPERATIVE signal is supplied to the DCU.
B. If the engine fuel−feed system has a failure, the engine−fuel−feed pressure switch
provides a ground return to the boost−pump control relay. The boost−pump control relay
then energizes and supplies 28 vac to the electric boost pump. The boost−pump control
relay also supplies a MAIN EJECTOR LOW PRESSURE ground to the DCU which
causes the L (R) MAIN EJECTOR warning to be shown on the engine indication and

Master
EFFECTIVITY: See Pageblock 28−42−00 page 1
28−42−00 Page 2
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
crew alerting system (EICAS) display.
NOTE: The L or R boost pump must be selected ON for the boost pump relay to
energize.
C. When the electric boost pump operates, it supplies fuel pressure to the standby
fuel−feed manifold. This fuel pressure is monitored by the boost−pump pressure switch.
When there is pressure at the pressure switch, the pressure switch removes the BOOST
PUMP INOPERATIVE ground from the DCU, and supplies the BOOST PUMP
OPERATIVE ground.
D. If there is pressure at the engine−fuel−feed pressure switch again, the pressure switch
removes the ground return from the boost−pump control relay. The electric boost pump
then turns off.
E. When the motive flow system (28−22−00) operates, it supplies pressure to the venturi
which has high and low pressure lines that connect it to the scavenge−ejector
differential−pressure switch. When there is a >3.3 ∆ p at the pressure switch, the
pressure switch removes the SCAVENGE EJECTOR LOW PRESSURE ground from the
DCU. If the motive flow system has a failure, the differential pressure switch provides the
SCAVENGE EJECTOR LOW PRESSURE ground to the DCU. The DCU causes the L
(R) SCAV EJECTOR warning to be shown on the EICAS display.
F. When the APU fuel−feed system (28−24−00) operates, it supplies pressure to the
APU−fuel−pump pressure switch. When there is pressure at the pressure switch, the
pressure switch supplies a XFLOW/APU PUMP PRESS ground to the fuel system
computer. If the APU fuel pump is off or the APU fuel−feed system has a failure, the
APU−fuel−pump pressure switch removes the XFLOW/APU PUMP PRESS from the fuel
system computer.
G. Fuel temperature is monitored by a temperature sensor found in the left main fuel tank.
When the fuel temperature reaches −40 degrees Celcius, the resistance of the fuel
temperature thyrister−type sensor generates the BULK FUEL TEMP caution message
on the EICAS.
4. Component Location Index
Refer to Figure 3.
COMPONENT NAME QTY ACCESS/ZONE REFERENCE
Pressure switch, boost pump 2 163AZ, 164AZ 28−42−01
Pressure switch, engine fuel feed 2 163AZ, 164AZ 28−42−04
Pressure switch, scavenge ejector 2 540AB, 640AB 28−42−07
differential
Pressure switch, APU fuel pump 1 164AZ 28−42−10
Sensor, fuel temperature 1 540BB, 28−42−15

Master
EFFECTIVITY: See Pageblock 28−42−00 page 1
28−42−00 Page 3
Mar 15/2005
 C
AIRCRAFT MAINTENANCE MANUAL

D
A
A

B D
D
FW
C
B
D
FW

S
LO ES
PR

SS
HI PRE

ENGINE−FUEL−FEED PRESSURE SWITCH SCAVENGE EJECTOR

A B
AND BOOST−PUMP−PRESSURE SWITCH DIFFERENTIAL−PRESSURE−SWITCH

ram2842000_001(3).dc, kms/pm, 25/03/98

NOTE
A right−side fuel
temperature sensor
may be installed.

APU−FUEL−PUMP FUEL TEMPERATURE

C D
PRESSURE SWITCH SENSOR

Fuel Warning System − Component Location/Recognition

Figure 1

Master
EFFECTIVITY: See Pageblock 28−42−00 page 1
28−42−00 Page 4
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

APU FUEL
FSC
PUMP
PRESSURE
SWITCH APU/ TOTAL FUEL FUEL FUEL USED

XFER
12100 LBS 3900 LBS
2340 LBS

PUMP
P = > 12 PSI P AUTO
BAL

PRESS INHIB

SCAVENGE EJECTOR
DIFFERENTIAL P P

PRESSURE SWITCH 4870 LBS 4890 LBS

P = 3.3 PSI DCU

35 C 36 C

FROM APU
SCAV
APU

FUEL PUMP
LO PRESS LO PRESS
FUEL CH 1/2 FAIL

EJECT
(28−24−00) EICAS SYNOPTIC
LOW
FROM MOTIVE FLOW PRESS DISPLAY
FUEL (28−22−00) BULK
TEMPERATURE FUEL
SENSOR BOOST PUMP TEMP
o
PRESSURE < − 40 C
T SWITCH 93.0 93.0 MLG BAY OVHT
DISPLAY COOL

FUEL
REV REV END
90.0
N1
750 750

P = > 10 PSI PUMP ITT

OP 95.0 95.0

C−ALT RATE P
N2
3100 100 7.7
3500 FF (PPH) 3500
GEAR
115 OIL TEMP 115

FUEL
DN DN DN
82 OIL PRESS 82 FLAPS 15

FUEL QTY (LBS)

PUMP 4870 2340 4890

TOTAL FUEL 12100

INOP
FROM STANDBY FUEL MAIN
FEED (28−23−00) EJECT EICAS PRIMARY
ENGINE LOW DISPLAY
FUEL FEED PRESS
PRESSURE
POWER
SWITCH
ELECTRIC
BOOST
BOOST PUMP P = > 10 PSI +28 VDC PUMP
SWITCH/LIGHT BUS 2 (28−23−01)
(28−23−00) BOOST PUMP
CONTROL
ram2842000_002(2).dg, pm/jc, 16/11/00
RELAY

+28 FROM ENGINE FUEL

VDC FEED (28−21−00) NOTE
BUS 2 Right fuel warning
system shown.
ON R BOOST Left is similar.
INOP PUMP

Fuel Warning System − Schematic

Figure 2

Master
EFFECTIVITY: See Pageblock 28−42−00 page 1
28−42−00 Page 5
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

640BB 540BB
640AB 540AB

164AZ

163AZ

D
FW
ram2842000_003(3).dg, kms/pm, 26/03/98

NOTE
500 series panels are on the left side.
600 series panels are on the right side.

Fuel Warning System − Component Access

Figure 3

Master
EFFECTIVITY: See Pageblock 28−42−00 page 1
28−42−00 Page 6
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C ALL
PRESSURE SWITCH, BOOST PUMP − REMOVAL/INSTALLATION

1. General
A. The maintenance procedures that follow are for the removal and installation of the boost
pump pressure switch (written as the "pressure switch" in this procedure). There are two
pressure switches (left pump and right pump) in the fuel system. They are found on the
rear bulkhead of the center wing box.
B. It is not necessary to defuel the fuel tanks to remove or install the pressure switch.

TASK 28−42−01−000−801
Removal of the Boost Pump Pressure Switch

1. Job Set−Up Information

Subtask 28−42−01−943−001
A. Tools and Equipment
REFERENCE DESIGNATION
None specified Container, fuel

Subtask 28−42−01−946−001
B. Reference Information
REFERENCE DESIGNATION
TASK 28−00−00−910−801 Fuel Safety Precautions
TASK 53−83−01−000−801 Removal of the MLG Wheel Bin

2. Job Set−Up
Subtask 28−42−01−910−001
WARNING: OBEY ALL THE FUEL SAFETY PRECAUTIONS WHEN YOU DO WORK ON THE
FUEL SYSTEM AND/OR A FUEL SYSTEM COMPONENT. IF YOU DO NOT DO
THIS, YOU CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO
EQUIPMENT.
A. Obey all the fuel safety precautions (Ref. TASK 28−00−00−910−801).

Subtask 28−42−01−941−001
WARNING: DO NOT OPERATE THE ENGINES OR THE ELECTRIC BOOST PUMPS WHILE
THE PRESSURE SWITCH IS REMOVED. PRESSURIZED FUEL WILL FLOW
OUT OF THE BULKHEAD FITTING AND CAN CAUSE A FIRE.
B. Put safety tags in the flight compartment on the controls and indicators that follow:
± ENG L START switch/light on the engine control panel
± ENG R START switch/light on the engine control panel
± L BOOST PUMP switch/light on the FUEL control panel

Master
EFFECTIVITY: See Pageblock 28−42−01 page 401
28−42−01 Page 401
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
± R BOOST PUMP switch/light on the FUEL control panel.

Subtask 28−42−01−865−001
C. Open, safety, and tag the circuit breakers that follow:
CB PANEL CB NO. NAME ZONE
CBP−1 M6 L FUEL PUMP 221
CBP−1 M7 L FUEL PUMP CONT 221
CBP−1 M12 FUEL SYST CONT 221
CBP−2 G10 R FUEL PUMP 222
CBP−2 G11 R FUEL PUMP CONT 222
CBP−4 B10 FUEL SYST CONT 222

Subtask 28−42−01−010−001
D. For the left pressure switch, remove the left wheel bin (163AZ) from the main wheel well
(Ref. TASK 53−83−01−000−801).
E. For the right pressure switch, remove the right wheel bin (164AZ) from the main wheel
well (Ref. TASK 53−83−01−000−801).
F. Put the fuel container below the applicable pressure switch.

3. Procedure
Subtask 28−42−01−020−001
Refer to Figure 401.
A. Remove the pressure switch as follows:
(1) Disconnect the electrical connector (1) from the pressure switch (2). Put a
protective cap on the electrical connector.
(2) Remove the lockwire from the pressure switch (2) and install a cap in the bulkhead
fitting.
(3) Remove the pressure switch (2).
(4) Remove and discard the preformed packing (3).

Master
EFFECTIVITY: See Pageblock 28−42−01 page 401
28−42−01 Page 402
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

NOTE:
Left side is shown.
Right side is opposite.

S3QA
(REF)

LEGEND
1. Electrical connector.
J1QD
Left − P11QA
(REF)
Right − P12QA
2. Pressure Switch.
Left − S1QA
Right − S2QA
S1QA 3. Preformed packing.
(REF)

BULKHEAD
FITTING
(REF)
3
ram2842014_001(1).dc, gg/kms, 6/07/95

2
D
FW

Boost Pump Pressure Switch − Removal/Installation

Figure 401

Master
EFFECTIVITY: See Pageblock 28−42−01 page 401
28−42−01 Page 403
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
TASK 28−42−01−400−801
Installation of the Boost Pump Pressure Switch

1. Job Set−Up Information

Subtask 28−42−01−944−001
A. Consumable Materials
REFERENCE DESIGNATION
05−005 Lockwire

Subtask 28−42−01−945−001
B. Parts
REF NAME OF PART QTY IPC SEQUENCE NO.
3 Preformed packing 1 IPC 28−23−00−1A−135

Subtask 28−42−01−946−002
C. Reference Information
REFERENCE DESIGNATION
TASK 28−23−01−710−801 Operational Test of the Electric Boost Pump
TASK 53−83−01−400−801 Installation of the MLG Wheel Bin

2. Procedure
Subtask 28−42−01−869−001
A. Make sure that the aircraft is in the same configuration as in the removal task.

Subtask 28−42−01−420−001
B. Install the pressure switch as follows:
(1) Remove the cap from the bulkhead fitting.
(2) Install the preformed packing (3) and the pressure switch (2) on the bulkhead fitting.
(3) Safety the pressure switch (2) with lockwire.
(4) Remove the protective cap from the electrical connector (1). Connect the electrical
connector.

3. Close Out
Subtask 28−42−01−865−002
A. Remove the tags and close the circuit breakers that follow:

Master
EFFECTIVITY: See Pageblock 28−42−01 page 401
28−42−01 Page 404
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

CB PANEL CB NO. NAME ZONE

CBP−1 M6 L FUEL PUMP 221
CBP−1 M7 L FUEL PUMP CONT 221
CBP−1 M12 FUEL SYST CONT 221
CBP−2 G10 R FUEL PUMP 222
CBP−2 G11 R FUEL PUMP CONT 222
CBP−4 B10 FUEL SYST CONT 222

Subtask 28−42−01−941−002
B. Remove the safety tags that are installed in the flight compartment on the controls and
indicators that follow:
± ENG L START switch/light on the engine control panel
± ENG R START switch/light on the engine control panel
± L BOOST PUMP switch/light on the FUEL control panel
± R BOOST PUMP switch/light on the FUEL control panel.

Subtask 28−42−01−710−001
C. Do an operational test of the pressure switch (Ref. TASK 28−23−01−710−801).

Subtask 28−42−01−210−001
D. Examine the area around the pressure switch for fuel leaks.

Subtask 28−42−01−410−001
E. For the left pressure switch, install the left wheel bin (163AZ) in the main landing gear
(Ref. TASK 53−83−01−400−801).
F. For the right pressure switch, install the right wheel bin (164AZ) in the main landing gear
(Ref. TASK 53−83−01−400−801).

Subtask 28−42−01−941−003
G. Remove all the tools, equipment, and unwanted materials from the area.

Master
EFFECTIVITY: See Pageblock 28−42−01 page 401
28−42−01 Page 405
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C ALL
PRESSURE SWITCH, ENGINE FUEL FEED − REMOVAL/INSTALLATION

1. General
A. The maintenance procedures that follow are for the removal and installation of the
primary ejector pressure switch (written as the "pressure switch" in this procedure).
There are two pressure switches in the fuel system. They are found on the rear bulkhead
of the center wing box.
B. It is not necessary to defuel the fuel tanks to remove or install the pressure switch.

TASK 28−42−04−000−801
Removal of the Engine Fuel Feed Pressure Switch

1. Job Set−Up Information

Subtask 28−42−04−943−001
A. Tools and Equipment
REFERENCE DESIGNATION
None specified Container, fuel
TBD Safety tag, DANGER − DO NOT OPERATE

Subtask 28−42−04−946−001
B. Reference Information
REFERENCE DESIGNATION
TASK 28−00−00−910−801 Fuel Safety Precautions
TASK 53−83−01−000−801 Removal of the MLG Wheel Bin

2. Job Set−Up
Subtask 28−42−04−910−001
WARNING: OBEY ALL THE FUEL SAFETY PRECAUTIONS WHEN YOU DO WORK ON THE
FUEL SYSTEM AND/OR A FUEL SYSTEM COMPONENT. IF YOU DO NOT DO
THIS, YOU CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO
EQUIPMENT.
A. Obey all the fuel safety precautions (Ref. TASK 28−00−00−910−801).

Master
EFFECTIVITY: See Pageblock 28−42−04 page 401
28−42−04 Page 401
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
Subtask 28−42−04−941−001
WARNING: DO NOT OPERATE THE ENGINES OR THE ELECTRIC BOOST PUMPS WHILE
THE PRESSURE SWITCH IS REMOVED. PRESSURIZED FUEL WILL FLOW
OUT OF THE BULKHEAD FITTING AND CAN CAUSE A FIRE.
B. Put safety tags in the flight compartment on the controls and indicators that follow:
± ENG L START switch/light on the engine control panel
± ENG R START switch/light on the engine control panel
± L BOOST PUMP switch/light on the FUEL control panel
± R BOOST PUMP switch/light on the FUEL control panel.

Subtask 28−42−04−865−001
C. Open, safety, and tag the circuit breakers that follow:
CB PANEL CB NO. NAME ZONE
CBP−1 M6 L FUEL PUMP 221
CBP−1 M7 L FUEL PUMP CONT 221
CBP−1 M12 FUEL SYST CONT 221
CBP−2 G10 R FUEL PUMP 222
CBP−2 G11 R FUEL PUMP CONT 222
CBP−4 B10 FUEL SYST CONT 222

Subtask 28−42−04−010−001
D. For the left pressure switch, remove the left wheel bin (163AZ) from the main wheel well
(Ref. TASK 53−83−01−000−801).
E. For the right pressure switch, remove the right wheel bin (164AZ) from the main wheel
well (Ref. TASK 53−83−01−000−801).
F. Put the fuel container below the applicable pressure switch.

3. Procedure
Subtask 28−42−04−020−001
Refer to Figure 401.
A. Remove the pressure switch as follows:
(1) Disconnect the electrical connector (1) from the pressure switch (2). Put a
protective cap on the electrical connector.
(2) Remove and discard the lockwire from the pressure switch (2).
(3) Remove the pressure switch (2) and install the cap in the bulkhead fitting.
(4) Remove and discard the preformed packing (3) from the bulkhead fitting.

Master
EFFECTIVITY: See Pageblock 28−42−04 page 401
28−42−04 Page 402
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

NOTE:
Left side is shown.
Right side is opposite.

BULKHEAD 1
FITTING
(REF)

LEGEND
ram2842044_001(1), gg/kms, 6/07/95

1. Electrical connector.
D Left − P13QA
FW Right − P14QA
2. Pressure Switch.
Left − S3QA
Right − S4QA
3. Preformed packing.

Engine Fuel Feed Pressure Switch − Removal/Installation

Figure 401

Master
EFFECTIVITY: See Pageblock 28−42−04 page 401
28−42−04 Page 403
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
TASK 28−42−04−400−801
Installation of the Engine Fuel Feed Pressure Switch

1. Job Set−Up Information

Subtask 28−42−04−944−001
A. Consumable Materials
REFERENCE DESIGNATION
05−005 Lockwire

Subtask 28−42−04−945−001
B. Parts
REF NAME OF PART QTY IPC SEQUENCE NO.
3 Preformed packing 1 IPC 28−21−00−1A−080

Subtask 28−42−04−946−002
C. Reference Information
REFERENCE DESIGNATION
TASK 28−23−01−710−801 Operational Test of the Electric Boost Pump
TASK 53−83−01−400−801 Installation of the MLG Wheel Bin

2. Procedure
Subtask 28−42−04−869−001
A. Make sure that the aircraft is in the same configuration as in the removal task.

Subtask 28−42−04−420−001
B. Install the pressure switch as follows:
(1) Remove the cap from the bulkhead fitting.
(2) Install the preformed packing (3) and the pressure switch (2) on the bulkhead fitting.
(3) Safety the pressure switch (2) with lockwire.
(4) Remove the protective cap from the electrical connector (1). Connect the electrical
connector.

3. Close Out
Subtask 28−42−04−865−002
A. Remove the tags and close the circuit breakers that follow:

Master
EFFECTIVITY: See Pageblock 28−42−04 page 401
28−42−04 Page 404
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

CB PANEL CB NO. NAME ZONE

CBP−1 M6 L FUEL PUMP 221
CBP−1 M7 L FUEL PUMP CONT 221
CBP−1 M12 FUEL SYST CONT 221
CBP−2 G10 R FUEL PUMP 222
CBP−2 G11 R FUEL PUMP CONT 222
CBP−4 B10 FUEL SYST CONT 222

Subtask 28−42−04−941−002
B. Remove the safety tags that are installed in the flight compartment on the controls and
indicators that follow:
± ENG L START switch/light on the engine control panel
± ENG R START switch/light on the engine control panel
± L BOOST PUMP switch/light on the FUEL control panel
± R BOOST PUMP switch/light on the FUEL control panel.

Subtask 28−42−04−710−001
C. Do an operational test of the pressure switch (Ref. TASK 28−23−01−710−801).

Subtask 28−42−04−210−001
D. Examine the area around the pressure switch for fuel leaks.

Subtask 28−42−04−410−001
E. For the left pressure switch, install the left wheel bin (163AZ) in the main landing gear
(Ref. TASK 53−83−01−400−801).
F. For the right pressure switch, install the right wheel bin (164AZ) in the main landing gear
(Ref. TASK 53−83−01−400−801).

Subtask 28−42−04−941−003
G. Remove all the tools, equipment, and unwanted materials from the area.

Master
EFFECTIVITY: See Pageblock 28−42−04 page 401
28−42−04 Page 405
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C ALL
PRESSURE SWITCH, SCAVENGE EJECTOR DIFFERENTIAL − REMOVAL/INSTALLATION

1. General
A. The maintenance procedures that follow are for the removal and installation of the
scavenge ejector differential pressure switch (written as the "pressure switch" in this
procedure). There are two pressure switches (left and right) in the fuel system. They are
connected to the motive flow lines of the aft scavenge ejector pump and are located on
the rear spar of the wing inside the wet section on the main fuel tanks, adjacent to the rib
at BL45.00.
B. It is necessary to defuel, drain, and remove the fuel fumes from the applicable main tank
to remove or install the pressure switch.

TASK 28−42−07−000−801
Removal of the Scavenge Ejector Differential Pressure Switch

1. Job Set−Up Information

Subtask 28−42−07−946−001
A. Reference Information
REFERENCE DESIGNATION
TASK 12−11−28−650−804 Suction Defueling
TASK 24−00−00−861−802 Remove Electrical Power to the Aircraft
TASK 28−00−00−910−801 Fuel Safety Precautions
TASK 28−11−00−840−801 Prepare Fuel Tank for Access
TASK 28−11−00−840−802 Removal of Fuel Fumes
TASK 28−11−01−000−802 Removal of the Graphite Access Panel
WM20−12−00 Wiring − Installation
WM20−17−10 Wiring Manual
WM28−20−00 Wiring Manual

2. Job Set−Up
Subtask 28−42−07−910−001
WARNING: OBEY ALL THE FUEL SAFETY PRECAUTIONS WHEN YOU DO WORK ON THE
FUEL SYSTEM AND/OR A FUEL SYSTEM COMPONENT. IF YOU DO NOT DO
THIS, YOU CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO
EQUIPMENT.
A. Obey all the fuel safety precautions (Ref. TASK 28−00−00−910−801).
B. Remove all of the electrical power from the aircraft (Ref. TASK 24−00−00−861−802).

Master
EFFECTIVITY: See Pageblock 28−42−07 page 401
28−42−07 Page 401
Dec 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
Subtask 28−42−07−650−001
C. Defuel the applicable main tank (Ref. TASK 12−11−28−650−804).

Subtask 28−42−07−010−001
D. Remove the applicable access panels that follow (Ref. TASK 28−11−01−000−802):
ACCESS DESCRIPTION
540AB Fuel tank access panel
640AB Fuel tank access panel

Subtask 28−42−07−840−001
E. Prepare the applicable main tank for access (Ref. TASK 28−11−00−840−801).
F. Remove the fuel fumes from the applicable main tank (Ref. TASK 28−11−00−840−802).

3. Procedure
Subtask 28−42−07−030−001
Refer to Figure 401.
A. Disconnect the electrical connections (Ref. WM20−17−10).
B. Remove the red and white wires from the electrical conduit as follows:
NOTE: To remove the left pressure switch S5QA, disconnect the red and white fly
leads at P5QA pins u and v. For the right pressure switch S6QA, disconnect
the red and white fly leads at P8QA pins u and v.
(1) Disconnect the electrical conduit (1) from the pressure switch (2).
(2) Remove the wires from the electrical conduit (Ref. WM20−12−00).

Subtask 28−42−07−020−001
C. Remove the pressure switch as follows:
(1) Disconnect the low and high pressure lines (3) from the elbow fittings (5).
(2) Remove the screws (7), the washers (8), and the pressure switch (2) from the
mounting bracket.
(3) Loosen the jam nuts (4). Remove the elbow fittings (5) from the pressure switch (2).
(4) Remove and discard the preformed packings (6) from the pressure switch (2).

Master
EFFECTIVITY: See Pageblock 28−42−07 page 401
28−42−07 Page 402
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

NOTE
Left side is shown.
Right side is opposite.

5
A

3
4

LOW PRESS

MOUNTING
BRACKET 2
(REF)

8
7

4
LEGEND
1. Electrical conduit.
ram2842074_001.dg, kms/rm, 06/10/00

2. Pressure switch. HI PRESS

3. Pressure line.
4. Jamnut.
5
5. Elbow fitting.
6. Preformed packing.
7. Screw.
8. Washer. 3

Scavenge Ejector Differential Pressure Switch − Removal/Installation

Figure 401

Master
EFFECTIVITY: See Pageblock 28−42−07 page 401
28−42−07 Page 403
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
TASK 28−42−07−400−801
Installation of the Scavenge Ejector Differential Pressure Switch

1. Job Set−Up Information

Subtask 28−42−07−945−001
A. Parts
REF NAME OF PART QTY IPC SEQUENCE NO.
4 Jam nut 2 IPC 28−22−00−1A−150
5 Elbow fitting 2 IPC 28−22−00−1A−145
6 Preformed packing 2 IPC 28−22−00−1A−155
7 Screw 2 IPC 28−22−00−1A−165
8 Washer 2 IPC 28−22−00−1A−170

Subtask 28−42−07−946−002
B. Reference Information
REFERENCE DESIGNATION
TASK 12−00−07−861−801 Connect External Electrical Power
TASK 28−11−01−400−802 Installation of the Graphite Access Panel
TASK 28−13−22−710−801 Operational Test of the Aft Scavenge Ejector
Pump
WM20−12−00 Wiring − Installation
WM20−17−10 Wiring Manual
WM28−20−00 Wiring Manual

2. Procedure
Subtask 28−42−07−420−001
Refer to Figure 401.
A. Install the pressure switch as follows:
(1) Install the preformed packings (6) and the elbow fittings (5). Tighten the jam
nuts (4).
(2) Install the pressure switch (2), the washers (8), and the screws (7) on the mounting
bracket. Make sure that the LOW side of the pressure switch (2) is pointing up.
(3) Connect the low and high pressure lines (3) to the elbow fittings (5).
(4) Make sure the pressure lines (3) are tightened.

Subtask 28−42−07−430−001
B. Install the wires in the electrical conduit as follows:
(1) Install the wires in the electrical conduit (Ref. WM20−12−00).
(2) Connect the electrical conduit (1) to the pressure switch (2).

Master
EFFECTIVITY: See Pageblock 28−42−07 page 401
28−42−07 Page 404
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
(3) Make sure the electrical conduit fitting is tightened.
NOTE: To install the left pressure switch S5QA, connect the red and white fly
leads at P5QA Pins u and v.
C. Connect the electrical connections (Ref. WM20−17−10 and WM28−20−00).

3. Close Out
Subtask 28−42−07−941−001
A. Remove all tools, equipment, and unwanted materials from the work area.

Subtask 28−42−07−410−001
B. Install the applicable access panel that follows (Ref. TASK 28−11−01−400−802):
ACCESS DESCRIPTION
540AB Fuel tank access panel
640AB Fuel tank access panel

Subtask 28−42−07−790−001
C. Examine the area on the rear bulkhead of the center wing (left or right) where the
electrical conduit for the pressure switch is located. Make sure there are no fuel leaks.

Subtask 28−42−07−861−001
D. Connect the external AC power to the aircraft (Ref. TASK 12−00−07−861−801).

Subtask 28−42−07−710−001
E. Do an operational test of the pressure switch (Ref. TASK 28−13−22−710−801).

Master
EFFECTIVITY: See Pageblock 28−42−07 page 401
28−42−07 Page 405
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C ALL
PRESSURE SWITCH, AUXILIARY POWER UNIT (APU) FUEL PUMP −
REMOVAL/INSTALLATION

1. General
A. The maintenance procedures that follow are for the removal and installation of the
auxiliary power unit (APU) fuel pump pressure switch (written as the "pressure switch" in
this procedure). There is one pressure switch in the fuel system. It is found on the aft
bulkhead of the center wing box right hand side, connected to the APU fuel pump.
B. It is not necessary to defuel the fuel tanks to remove or install the pressure switch.

TASK 28−42−10−000−801
Removal of the APU Fuel Pump Pressure Switch

1. Job Set−Up Information

Subtask 28−42−10−943−001
A. Tools and Equipment
REFERENCE DESIGNATION
None specified Container, fuel

Subtask 28−42−10−946−001
B. Reference Information
REFERENCE DESIGNATION
TASK 28−00−00−910−801 Fuel Safety Precautions
TASK 53−83−01−000−801 Removal of the MLG Wheel Bin

2. Job Set−Up
Subtask 28−42−10−910−001
WARNING: OBEY ALL THE FUEL SAFETY PRECAUTIONS WHEN YOU DO WORK ON THE
FUEL SYSTEM AND/OR A FUEL SYSTEM COMPONENT. IF YOU DO NOT DO
THIS, YOU CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO
EQUIPMENT.
A. Obey all the fuel safety precautions (Ref. TASK 28−00−00−910−801).

Master
EFFECTIVITY: See Pageblock 28−42−10 page 401
28−42−10 Page 401
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
Subtask 28−42−10−865−004
WARNING: DO NOT OPERATE THE XFER/APU FUEL PUMP WHILE THE PRESSURE
SWITCH IS REMOVED. PRESSURIZED FUEL WILL FLOW OUT OF THE
ADAPTER AND CAN CAUSE A FIRE.
B. Put safety tags in the flight compartment on the controls and indicators that follow:
± PWR FUEL switchlight on the APU control panel
± START/STOP switchlight on the APU control panel.

**ON A/C 7004−7019, 7021−7044, 7046, 7048, 7050, 7052, 7055−7056, 7059, 7061−7064,
7066−7067, 7069−7070, 7072−7073, 7075−7077, 7079−7080, 7085−7086, 7088−7094,
7099−7106, 7108−7111, 7113−7117, 7119, 7121−7123, 7125, 7127−7143, 7145−7152, 7154,
7156−7159, 7162−7163, 7165, 7167−7169, 7171−7176, 7178−7181, 7185−7196, 7199−7200,
7202−7222, 7224−7233, 7235−7236, 7238−7271, 7273−7294 Pre SB601R−24−090

Subtask 28−42−10−865−001
C. Open, safety, and tag the circuit breakers that follow:
CB PANEL CB NO. NAME ZONE
CBP−1 M12 FUEL SYST CONT 221
CBP−1 N10 XFER/APU FUEL PUMP 221
CBP−1 N11 XFER/APU CONT 221
CBP−1 N12 XFER/APU APU ECU 221
CBP−4 B10 FUEL SYST CONT 222
CBP−5 B14 FUEL/DEFUEL 311

**ON A/C 7003, 7020, 7045, 7047, 7049, 7051, 7053−7054, 7057−7058, 7060, 7065, 7071, 7074,
7078, 7081−7084, 7087, 7095−7098, 7107, 7112, 7118, 7120, 7124, 7126, 7144, 7153, 7155,
7160−7161, 7164, 7166, 7170, 7177, 7182−7184, 7197−7198, 7201, 7223, 7234, 7237, 7272,
7295−7990, 8000−8064, 8066−8068 and ON A/C 7004−7019, 7021−7044, 7046, 7048, 7050,
7052, 7055−7056, 7059, 7061−7064, 7066−7067, 7069−7070, 7072−7073, 7075−7077,
7079−7080, 7085−7086, 7088−7094, 7099−7106, 7108−7111, 7113−7117, 7119, 7121−7123,
7125, 7127−7143, 7145−7152, 7154, 7156−7159, 7162−7163, 7165, 7167−7169, 7171−7176,
7178−7181, 7185−7196, 7199−7200, 7202−7222, 7224−7233, 7235−7236, 7238−7271,
7273−7294 Post SB601R−24−090

Subtask 28−42−10−865−005
D. Open, safety, and tag the circuit breakers that follow:
CB PANEL CB NO. NAME ZONE
CBP−1 M12 FUEL SYST CONT 221
CBP−1 N10 XFER/APU FUEL PUMP 221
CBP−1 N11 XFER/APU CONT 221
CBP−1 N12 XFER/APU APU ECU 221
CBP−4 B10 FUEL SYST CONT 222
CBP−5 B6 FUEL/DEFUEL 311

Master
EFFECTIVITY: See Pageblock 28−42−10 page 401
28−42−10 Page 402
Dec 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C ALL

Subtask 28−42−10−010−001
E. Remove the right wheel bin (164AZ) from the main wheel well (Ref. TASK
53−83−01−000−801).
F. Put the fuel container below the pressure switch.

3. Procedure
Subtask 28−42−10−020−001
Refer to Figure 401.
WARNING: DO NOT OPERATE THE AUTO FUEL PUMP WHILE THE PRESSURE SWITCH
IS REMOVED. PRESSURIZED FUEL WILL FLOW OUT OF THE ADAPTER
FITTING AND CAN CAUSE A FIRE.
A. Remove the pressure switch as follows:
(1) Disconnect the electrical connector (1) from the pressure switch (2). Put a
protective cap on the electrical connector.
(2) Remove the lockwire, the pressure switch (2), and the preformed packing (3) from
the adapter fitting (4). Discard the lockwire and the preformed packing.
(3) Put a protective plug in the adapter fitting (4).

Master
EFFECTIVITY: See Pageblock 28−42−10 page 401
28−42−10 Page 403
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

LEGEND
1. Electrical connector. (P9QB)
2. Pressure switch. (S1QB)
3. Preformed packing.
4. Adapter fitting.

FUEL TANK
BULKHEAD
(REF)

APU FUEL
PUMP (REF)
(MPE1QB)
S1QB 4
(REF) 3
ram2842104_001(3).dg, kms/rm, 29/07/98

P9QB D
2 FW
(REF)

1
A

APU Fuel Pump Pressure Switch − Removal/Installation

Figure 401

Master
EFFECTIVITY: See Pageblock 28−42−10 page 401
28−42−10 Page 404
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
TASK 28−42−10−400−801
Installation of the APU Fuel Pump Pressure Switch

1. Job Set−Up Information

Subtask 28−42−10−944−001
A. Consumable Materials
REFERENCE DESIGNATION
05−004 Lockwire

Subtask 28−42−10−945−001
B. Parts
REF NAME OF PART QTY IPC SEQUENCE NO.
3 Preformed packing 1 IPC 28−24−00−03−055

Subtask 28−42−10−946−002
C. Reference Information
REFERENCE DESIGNATION
TASK 28−24−01−710−801 Operational Test of the APU Fuel Pump
TASK 53−83−01−400−801 Installation of the MLG Wheel Bin

2. Procedure
Subtask 28−42−10−420−001
A. Install the pressure switch as follows:
(1) Remove the protective plug from the adapter fitting (4).
(2) Install the preformed packing (3) and the pressure switch (2) on the adapter fitting
(4). Safety the pressure switch with lockwire.
(3) Remove the protective cap from the electrical connector (1). Connect the electrical
connector to the pressure switch (2).

Master
EFFECTIVITY: See Pageblock 28−42−10 page 401
28−42−10 Page 405
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
3. Close Out
**ON A/C 7004−7019, 7021−7044, 7046, 7048, 7050, 7052, 7055−7056, 7059, 7061−7064,
7066−7067, 7069−7070, 7072−7073, 7075−7077, 7079−7080, 7085−7086, 7088−7094,
7099−7106, 7108−7111, 7113−7117, 7119, 7121−7123, 7125, 7127−7143, 7145−7152, 7154,
7156−7159, 7162−7163, 7165, 7167−7169, 7171−7176, 7178−7181, 7185−7196, 7199−7200,
7202−7222, 7224−7233, 7235−7236, 7238−7271, 7273−7294 Pre SB601R−24−090

Subtask 28−42−10−865−002
A. Remove the tags and close the circuit breakers that follow:
CB PANEL CB NO. NAME ZONE
CBP−1 M12 FUEL SYST CONT 221
CBP−1 N10 XFER/APU FUEL PUMP 221
CBP−1 N11 XFER/APU CONT 221
CBP−1 N12 XFER/APU APU ECU 221
CBP−4 B10 FUEL SYST CONT 222
CBP−5 B14 FUEL/DEFUEL 311

**ON A/C 7003, 7020, 7045, 7047, 7049, 7051, 7053−7054, 7057−7058, 7060, 7065, 7071, 7074,
7078, 7081−7084, 7087, 7095−7098, 7107, 7112, 7118, 7120, 7124, 7126, 7144, 7153, 7155,
7160−7161, 7164, 7166, 7170, 7177, 7182−7184, 7197−7198, 7201, 7223, 7234, 7237, 7272,
7295−7990, 8000−8064, 8066−8068 and ON A/C 7004−7019, 7021−7044, 7046, 7048, 7050,
7052, 7055−7056, 7059, 7061−7064, 7066−7067, 7069−7070, 7072−7073, 7075−7077,
7079−7080, 7085−7086, 7088−7094, 7099−7106, 7108−7111, 7113−7117, 7119, 7121−7123,
7125, 7127−7143, 7145−7152, 7154, 7156−7159, 7162−7163, 7165, 7167−7169, 7171−7176,
7178−7181, 7185−7196, 7199−7200, 7202−7222, 7224−7233, 7235−7236, 7238−7271,
7273−7294 Post SB601R−24−090

Subtask 28−42−10−865−006
B. Remove the tags and close the circuit breakers that follow:
CB PANEL CB NO. NAME ZONE
CBP−1 M12 FUEL SYST CONT 221
CBP−1 N10 XFER/APU FUEL PUMP 221
CBP−1 N11 XFER/APU CONT 221
CBP−1 N12 XFER/APU APU ECU 221
CBP−4 B10 FUEL SYST CONT 222
CBP−5 B6 FUEL/DEFUEL 311

**ON A/C ALL

Subtask 28−42−10−865−003
C. Remove the safety tags that are installed in the flight compartment on the controls and
indicators that follow:
± PWR FUEL switch light on the APU control panel

Master
EFFECTIVITY: See Pageblock 28−42−10 page 401
28−42−10 Page 406
Dec 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
± START/STOP switch light on the APU control panel.

Subtask 28−42−10−710−001
D. Do an operational test of the pressure switch (Ref. TASK 28−24−01−710−801).

Subtask 28−42−10−790−001
E. Examine the area around the pressure switch for fuel leaks.

Subtask 28−42−10−941−001
F. Remove all the tools, equipment, and unwanted materials from the area.

Subtask 28−42−10−410−001
G. Install the right wheel bin (164AZ) in the main landing gear (Ref. TASK
53−83−01−400−801).

Master
EFFECTIVITY: See Pageblock 28−42−10 page 401
28−42−10 Page 407
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C ALL
SENSOR, FUEL TEMPERATURE − REMOVAL/INSTALLATION

1. General
A. The maintenance procedure that follows is for the removal and installation of the fuel
temperature sensor (written as the "sensor"). The sensor is installed in the left−main fuel
tank near the wing root at STA. W61.00L.
B. It is necessary to defuel, drain, and remove the fuel fumes from the left fuel tank to
remove and install the sensor.

TASK 28−42−15−000−801
Removal of the Fuel Temperature Sensor

1. Job Set−Up Information

Subtask 28−42−15−946−001
A. Reference Information
REFERENCE DESIGNATION
TASK 12−11−28−650−804 Suction Defueling
TASK 28−00−00−910−801 Fuel Safety Precautions
TASK 28−11−00−840−801 Prepare Fuel Tank for Access
TASK 28−11−00−840−802 Removal of Fuel Fumes
TASK 28−11−01−000−802 Removal of the Aluminum Access Panel
TASK 53−83−01−000−801 Removal of the MLG Wheel Bin

2. Job Set−Up
Subtask 28−42−15−910−001
WARNING: OBEY ALL THE FUEL SAFETY PRECAUTIONS WHEN YOU DO WORK ON THE
FUEL SYSTEM AND/OR A FUEL SYSTEM COMPONENT. IF YOU DO NOT DO
THIS, YOU CAN CAUSE INJURIES TO PERSONS AND/OR DAMAGE TO
EQUIPMENT.
A. Obey all the fuel safety precautions (Ref. TASK 28−00−00−910−801).

Subtask 28−42−15−650−001
B. Defuel the applicable fuel tank (Ref. TASK 12−11−28−650−804).

Subtask 28−42−15−010−001
C. Remove the fuel−tank access panel 540AB (Ref. TASK 28−11−01−000−802).

Master
EFFECTIVITY: See Pageblock 28−42−15 page 401
28−42−15 Page 401
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
Subtask 28−42−15−840−001
D. Prepare the tank for access (Ref. TASK 28−11−00−840−801).
E. Remove the fuel fumes from the tank (Ref. TASK 28−11−00−840−802).

Subtask 28−42−15−010−002
F. Remove the left MLG wheel bin (163AZ) (Ref. TASK 53−83−01−000−801).

3. Procedure
Subtask 28−42−15−020−001
Refer to Figure 401.
A. Remove the sensor as follows:
(1) Loosen the backshell coupler and disconnect the electrical connector (1) from the
bulkhead connector (2).
(2) Put a protective cap on the electrical connector (1) and the bulkhead connector (2).
(3) Remove the screws (3), with the washers (4) to disconnect the sensor (5) from the
mounting bracket on the wing rib.
(4) Remove the thumbscrews (6) and open the hinged clamps (7).
(5) Remove the conduit line (8) from the clamps (7).
**ON A/C 7185−7990, 8000−8064, 8066−8068
(6) Remove and discard the lockwire from the jam nut (9).
**ON A/C ALL
(7) Remove the jam nut (9) and the washer (10) from the bulkhead connector (2) and
remove the connector from the aft wall of the fuel tank.
(8) Remove and discard the preformed packing (11) from the bulkhead connector (2).
(9) Remove the line (8), with the bulkhead connector (2) and the sensor (5) from the
fuel tank.

Master
EFFECTIVITY: See Pageblock 28−42−15 page 401
28−42−15 Page 402
Dec 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL

C
D

LEGEND
INB D
D FW
1. Electrical connector. C
2. Bulkhead connector.
3. Screw.
4. Washer.
5. Fuel temperature
AFT BULKHEAD
sensor. A (REF)
6. Thumb screw. B
7. Hinged clamp.
8. Conduit line.
9. Jamnut.
10. Washer. BACKSHELL
11. Preformed packing. COUPLER 2
(REF)

INB 11
D D
FW 1
10
9

4
6
ram2842154_001(4).dg, rm/pm, 22/04/98

C 5
TYPICAL D

Fuel Temperature Sensor − Removal/Installation

Figure 401

Master
EFFECTIVITY: See Pageblock 28−42−15 page 401
28−42−15 Page 403
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
TASK 28−42−15−400−801
Installation of the Fuel Temperature Sensor

1. Job Set−Up Information

Subtask 28−42−15−944−004
A. Consumable Materials
REFERENCE DESIGNATION
05−004 Lockwire

Subtask 28−42−15−945−001
B. Parts
REF NAME OF PART QTY IPC SEQUENCE NO.
3 Screw 2 IPC 28−42−15−01−010
4 Washer 2 IPC 28−42−15−01−015
6 Thumbscrew 4 IPC 28−42−15−01−025
7 Hinged clamp 4 IPC 28−42−15−01−020
9 Jam nut 1 IPC 28−42−15−01−035
10 Washer 1 IPC 28−42−15−01−040
11 Preformed packing 1 IPC 28−42−15−01−045

Subtask 28−42−15−946−002
C. Reference Information
REFERENCE DESIGNATION
TASK 12−11−28−650−801 Automatic Pressure Refueling
TASK 28−11−01−400−802 Installation of the Aluminum Access Panel
TASK 28−42−15−TBD Operational Test of the Fuel Temperature Sensor
TASK 53−83−01−400−801 Installation of the MLG Wheel Bin

2. Procedure
Subtask 28−42−15−869−001
A. Make sure that the aircraft is in the same configuration as in the removal task.

Subtask 28−42−15−420−001
Refer to Figure 401.
B. Install the sensor as follows:
(1) Install the preformed packing (11) on the bulkhead connector (2).
(2) Move the sensor assembly into position in the tank and put the connector (2)
through the mounting hole in the aft bulkhead.

Master
EFFECTIVITY: See Pageblock 28−42−15 page 401
28−42−15 Page 404
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
(3) Install the jam nut (9) with the washer (10). Make sure that the keyway on the
bulkhead connector is at the top when the jam nut is fully tightened.
NOTE: when connected, the backshell coupler must point inboard at the three
o’clock position. This is to prevent fouling between the backshell coupler
and a MLG hydraulic tube assembly.
**ON A/C 7185−7990, 8000−8064, 8066−8068
(4) Safety the jam nut (9) with lockwire.
**ON A/C ALL
(5) Attach the sensor (5) to the mounting bracket on the wing rib with the washers (4)
and the screws (3).
(6) Install the conduit line (8) in the hinged clamps (7). Close the hinged clamps (7) and
lock them with the thumbscrews (6).

3. Close Out
Subtask 28−42−15−790−001
A. Refuel the applicable fuel tank (Ref. TASK 12−11−28−650−801).
B. Examine the newly installed temperature sensor installation for fuel leaks at the
bulkhead connector.

Subtask 28−42−15−710−001
C. Do an operational test of the fuel temperature sensor (Ref. TASK 28−42−15−TBD).

Subtask 28−42−15−410−001
D. Install the fuel−tank access panel 540AB (Ref. TASK 28−11−01−000−802).
E. Install the left MLG wheel bin (Ref. TASK 53−83−01−400−801).

Subtask 28−42−15−941−001
F. Remove all tools, equipment, and unwanted materials from the work area.

Master
EFFECTIVITY: See Pageblock 28−42−15 page 401
28−42−15 Page 405
Dec 10/2005
 C
AIRCRAFT MAINTENANCE MANUAL
**ON A/C ALL
SENSOR, FUEL TEMPERATURE − ADJUSTMENT/TEST

1. General
A. The maintenance procedures that follow shall be used to test the fuel temperature
sensor. Procedure one is to be followed when the aircraft has no fuel in the left main
tank. Procedure two is to be followed when the aircraft has fuel in the left main tank.

TASK 28−42−15−720−801
Functional Test of the Fuel Temperature Sensor

1. Job Set−Up Information

Subtask 28−42−15−943−001
A. Tools and Equipment
REFERENCE DESIGNATION
None specified Calibrated Thermometer

Subtask 28−42−15−720−001
B. Reference Information
REFERENCE DESIGNATION
TASK 12−00−07−861−801 Connect External AC Power
TASK 12−00−07−861−802 Remove External AC Power
TASK 12−11−28−650−805 Gravity Defueling

2. Job Set−Up
Subtask 28−42−15−865−001
A. Open, safety and tag the circuit breakers that follow:
CB PANEL CB NO. NAME ZONE
CBP−2 K6 EICAS DCU 3 CH A (Spare with only two DCUs) 222
CPP−2 K7 EICAS DCU 3 CH B (Spare with only two DCUs) 222
CPP−2 Q2 EICAS DCU 1 CH A 222
CPP−2 Q3 EICAS DCU 1 CH B 222
CPP−2 Q4 EICAS DCU 2 CH A 222
CPP−2 Q5 EICAS DCU 2 CH B 222

Subtask 28−42−15−861−001
B. Connect the external AC power to the aircraft (Ref. TASK 12−00−07−861−801).
C. Select MFD2 with the MAINT switch on CBP−1.

Master
EFFECTIVITY: See Pageblock 28−42−15 page 501
28−42−15 Page 501
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL
D. Make sure that the MDC menu is shown on the EFIS multi−function display. No fault
messages should be shown.
E. Push the FUEL push−button on the engine indication and crew alerting system (EICAS)
control panel to get the FUEL synoptic display.

3. Procedure One
Subtask 28−42−15−720−002
A. Do a test of the fuel temperature sensor as follows:
(1) Remove the tag and close the circuit breakers that follow:
CB PANEL CB NO. NAME ZONE
CPP−2 Q2 EICAS DCU 1 CH A 222
CPP−2 Q3 EICAS DCU 1 CH B 222
(2) Compare the bulk fuel temperature displayed on the FUEL page with the indication
on a calibrated thermometer. The displayed temperature should be ambient ±9°F
(±5°C).
(3) Open, safety and tag the circuit breakers that follow:
CB PANEL CB NO. NAME ZONE
CPP−2 Q2 EICAS DCU 1 CH A 222
CPP−2 Q3 EICAS DCU 1 CH B 222
(4) Remove the tag and close the circuit breakers that follow:
CB PANEL CB NO. NAME ZONE
CPP−2 Q4 EICAS DCU 2 CH A 222
CPP−2 Q5 EICAS DCU 2 CH B 222
(5) Compare the bulk fuel temperature displayed on the FUEL page with the indication
on a calibrated thermometer. The displayed temperature should be ambient ±9°F
(±5°C).
(6) Open, safety and tag the circuit breakers that follow:
CB PANEL CB NO. NAME ZONE
CPP−2 Q4 EICAS DCU 2 CH A 222
CPP−2 Q5 EICAS DCU 2 CH B 222

**ON A/C 7003−7007, 7009−7010, 7015−7016, 7019, 7021, 7023−7025, 7028−7030, 7034, 7039,
7041, 7045, 7047, 7049, 7051, 7054−7056, 7058, 7060, 7064−7067, 7071, 7073−7074, 7078,
7082−7083, 7086−7087, 7089−7090, 7093, 7095−7098, 7101−7102, 7104, 7107, 7112−7115,
7118−7122, 7124, 7128, 7130, 7135−7136, 7140, 7152, 7165, 7176, 7198, 7200−7201, 7206,
7209, 7220, 7224, 7227, 7266, 7282, 7298
(7) Remove the tag and close the circuit breakers that follow:

Master
EFFECTIVITY: See Pageblock 28−42−15 page 501
28−42−15 Page 502
Dec 15/2004
 C
AIRCRAFT MAINTENANCE MANUAL

CB PANEL CB NO. NAME ZONE

CPP−2 K6 EICAS DCU 3 CH A 222
CPP−2 K7 EICAS DCU 3 CH B 222
(8) Compare the bulk fuel temperature displayed on the FUEL page with the indication
on a calibrated thermometer. The displayed temperature should be ambient ±9°F
(±5°C).
(9) Open, safety and tag the circuit breakers that follow:
CB PANEL CB NO. NAME ZONE
CPP−2 K6 EICAS DCU 3 CH A 222
CPP−2 K7 EICAS DCU 3 CH B 222

4. Procedure Two
**ON A/C ALL

Subtask 28−42−15−720−003
A. Do a test of the fuel temperature sensor as follows:
(1) Get a sample of fuel from the left main tank (Ref. TASK 12−11−28−650−805).
(2) Find the temperature of the fuel sample with a calibrated thermometer.
(3) Remove the tag and close the circuit breakers that follow:
CB PANEL CB NO. NAME ZONE
CPP−2 Q2 EICAS DCU 1 CH A 222
CPP−2 Q3 EICAS DCU 1 CH B 222
(4) Compare the bulk fuel temperature displayed on the FUEL page with the indication
on a calibrated thermometer. The displayed temperature should be the fuel sample
temperature ±9°F (±5°C).
(5) Open, safety and tag the circuit breakers that follow:
CB PANEL CB NO. NAME ZONE
CPP−2 Q2 EICAS DCU 1 CH A 222
CPP−2 Q3 EICAS DCU 1 CH B 222
(6) Remove the tag and close the circuit breakers that follow:
CB PANEL CB NO. NAME ZONE
CPP−2 Q4 EICAS DCU 2 CH A 222
CPP−2 Q5 EICAS DCU 12 CH B 222
(7) Compare the bulk fuel temperature displayed on the FUEL page with the indication
on a calibrated thermometer. The displayed temperature should be the fuel sample
temperature ±9°F (±5°C).
(8) Open, safety and tag the circuit breakers that follow:

Master
EFFECTIVITY: See Pageblock 28−42−15 page 501
28−42−15 Page 503
Apr 20/2004
 C
AIRCRAFT MAINTENANCE MANUAL

CB PANEL CB NO. NAME ZONE

CPP−2 Q4 EICAS DCU 2 CH A 222
CPP−2 Q5 EICAS DCU 2 CH B 222

**ON A/C 7003−7007, 7009−7010, 7015−7016, 7019, 7021, 7023−7025, 7028−7030, 7034, 7039,
7041, 7045, 7047, 7049, 7051, 7054−7056, 7058, 7060, 7064−7067, 7071, 7073−7074, 7078,
7082−7083, 7086−7087, 7089−7090, 7093, 7095−7098, 7101−7102, 7104, 7107, 7112−7115,
7118−7122, 7124, 7128, 7130, 7135−7136, 7140, 7152, 7165, 7176, 7198, 7200−7201, 7206,
7209, 7220, 7224, 7227, 7266, 7282, 7298
(9) Remove the tag and close the circuit breakers that follow:
CB PANEL CB NO. NAME ZONE
CPP−2 K6 EICAS DCU 3 CH A 222
CPP−2 K7 EICAS DCU 3 CH B 222
(10) Compare the bulk fuel temperature displayed on the FUEL page with the indication
given by the calibrated thermometer. The displayed temperature should be the fuel
sample temperature ±9°F (±5°C).

5. Close Out
**ON A/C ALL

Subtask 28−42−15−865−002
A. Remove the tags and close the circuit breakers that follow:
CB PANEL CB NO. NAME ZONE
CPP−2 Q2 EICAS DCU 1 CH A 222
CPP−2 Q3 EICAS DCU 1 CH B 222
CPP−2 Q4 EICAS DCU 2 CH A 222
CPP−2 Q5 EICAS DCU 2 CH B 222

Subtask 28−42−15−861−002
B. Select OFF with the MAINT switch on CBP−1.
C. Remove the external AC power from the aircraft (Ref. TASK 12−00−07−861−802).

Subtask 28−42−15−941−002
D. Remove all the tools, equipment and unwanted materials from the work area.

Master
EFFECTIVITY: See Pageblock 28−42−15 page 501
28−42−15 Page 504
Dec 15/2004