PUBLISHED BY BOEING CO MMERCIAL AIRPLAN ES GROUP, SEATTLE, WASHINGTON, USA

• A DIVISION OF THE BOEING COMPANY • 

# DECLARATION STATEMENT

To: All holders of this Boeing Document

This document has EAR data with Export Control Classification Numbers (ECCN) of: 9E991

Export of this technology is controlled under the United States Export Administration Regulations (EAR) (15 CFR 730-774). An export license may be required before it is used for development, production or use by foreign persons from specific countries. The controller of this data has the individual re sponsibility to abide by all export laws.

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This document includes proprietary information owned by The Boeing Company and/or one or more third parties. Treatment of the document and the information it contains is governed by contract with Boeing. For more information, contact The Boeing Company, P.O. Box 3707, Seattle, Washington 98124.

Boeing, the Boeing signature, the Boeing symbol, 707, 717, 727, 737, 747, 757, 767, 777, 787, Dreamliner, BBJ, DC-8, DC-9, DC-10, KC-10, KDC-10, MD-10, MD-11, MD-80, MD-88, MD-90, P-8A, Poseidon and the Boeing livery are all trademarks owned by The Boeing Company; and no trademark license is granted in connection with this document unless provided in writing by Boeing.Report Number: MDC-92K9145

TWINJET SPECIAL COMPLIANCE ITEMS REPORT

Revision date: 2/05/2013 Revision letter: M

Issue date: 10/3111994 Contract number:

Prepared by:

# ~A'----'~'-"''ll"'-""c:___.!I-'-----L**~~-"'-- -----------**  M.A.COX,sat'et/ frl ;tleering Modification Services, Long Beach Division

P.V. Fiocca, Chi esign Engineer Signing for DC-9/MD-80/MD-90 Design Office, Long Beach Division

Approved by:

# --'------'--**fZ** 

# ___ _ T .J. Croslin, Chief Project Engineer All Long Beach Models, Long Beach Division

This report is FAA approved and specifies Special Compliance Items (SCls) as required by Part 25.1529 of the Federal Aviation Regulations, and SFAR 88 Airworthiness Limitation Instructions (ALis) & Critical Design Configuration Control Limitations (CDCCLs) required by Parts 25.981, 25.1529 and 26.33 of the Federal Aviation Regulations, unless an alternative program has been approved by FAA Engineering of the Los Angeles Aircraft Certification Office (LA-ACO). This revision of the SCI report was approved by the Manager, Los Angeles Certification Office, Transport Airplane Directorate, on 

# du.oe /<{
1 :l.OL3

. Changes to this report must be approved by the LA-ACO.

This document has EAR data with Export Control Classification Numbers (ECCN) of: 9E991

Export of this technology is controlled under the United States Export Administration Regulations (EAR) (15 CFR 730-774). An export license
may be required before it is used for development, production or use by foreign persons from specific countries. The controller of this data has the individual responsibility to abide by all export laws.

BOEING PROPRIETARY, CONFIDENTIAL, AND/OR TRADE SECRET Copyright © 2013 The Boeing Company Unpublished Work- All Rights Reserved

Boeing claims copyright in each page of this document only to the extent that the page contains copyrightable subject matter

. Boeing also claims copyright in this document as a compilation and/or collective work.

This document includes proprietary information owned by The Boeing Company and/or one or more third parties. Treatment of the document and the information it contains is governed by contract with Boeing

. For more information, contact The Boeing Company, P.O. Box 3707, Seattle, Washington 98124.

Boeing, the Boeing signature, the Boeing symbol, 707, 717, 727, 737, 747, 757, 767, 777, 787, BBJ, DC-8. DC-9, DC-10, MD-10, MD-11, MD-80, MD-88, MD-90, and the red-white-and-blue Boeing livery are all trademarks owned by The Boeing Company; and no trademark license is granted in connection with this document unless provided in writing by Boeing.U.S. Deportmen t of Tr o nsportQtion Federa l A vi ati o n Adm i n istr ation

june 14

, 2013



### I n Reply ) Refer To: 1 40L-l3-138

The Boeing Company ATTN.: 

### Mr

. Robert A. Beaudreau. Senior**Manager .** **Airworthines~** 1 85 5' Lakewood Boule v ard Long Bea ch. CA 90846

- 000 1 Transport Airplan e Dirc etura t c Lo · Angele s Air c raft Certi fi ca t ion Office .3%0 Pummow1L H oul.:1

. trJ Lai..I!I\IIOU

. t"»lithmia 90-12-113-



### RECEIVED



## JUN 2 0 2 0 1 3

CERTIFICATI ON & 

### AIRWORTHINESS

Reference: B oe ing l ette r C P- L4L-13-00294 dated June 10

, 20 1 3

Dear Mr

. B ea udre a u

Subject : D C- 9 / MD-80 / MD-9

. 0 / 7 17 Serie s -Spec ial Compliance [tern Report Re v i s i o n 

### M a nd R eq u est for G l oba l Alternative Met h o d o f Compliance 

### AMOC

The Federal Av i ation Administration (FAA) ha s recei ve d your reference letter dated Jun e 10 .2013

, with revised FAA Fo rm s 8100-9 reque sting approval of T wi nj e t Special Co mplian ce Item Report. MDC-92K9l45, Re v i s ion M and approve the Appendices B. C

a nd 0 oflbe re yjsed report as an AMOC to AD 200 8-11 -15

, par agrap h s (g) and ( h )

, as requested in Boeing letter C P-L4L-l3-00128 dat e d April22, 2013

.

The FAA h as co mple ted review of your AMOC request and approves the Twinjet Special Compliance Ttem Report.**MOC-92K9145~** R evision 

### M Appendices B. 

### C and 

### 0 a s

an AMOC t o 

### AD 20 08-11

- 15. paragraph s (g) and ( h ).

In accordance 

### wi rh FAA Order 811 0.103A

. da ted September 28. 201 0. t h e 'following conditions ap pl y:

l. A11 pr ovis ion s of A 0 2008- L 1-1 5 that are not s p eci fi ca ll y referenced above remain 

### full) a ppli cable and m ust be complied 

### wi th acc o rdingly

.

..., This a ppr ova l i s applicable o nly ro Boein g DC- 9/ t\ID-80 / MD-90 1 717 Se rl e

. model airplane s.

3. Thi s app r ova l is transferabl e"\\ ith airplane{s) t o ot her operators.

4

. B efo r e using thi s AMOC, noti1}: yo ur appropriate principal ins pector. o r l acking a princ i pal inspector. Lh e manager of the l ocal 

### flight sta.nda rd s di':itrict

o ffi ce / certiticate holding district oll i ce.

hut m.\,,•.n ,, , ' I f • I "I rli

### Should ) o u ha\ e 

### any questions. please contac t this office or 

### Aviation**Safet~ Engin~er**  

### Serj I Jarutunian at 

### telephone number 

### 562 -6 27-5254. fax 

### 562

- 627

- 52 1 0. or electronjc mail
at**~en** 

### lLmLtuman a !aa.!:W\

Sincere))'

,

# /!:**~~** 

# )i._c(

Ke vin 

### Hull Manager. 

### L os Angeles Aircraft Certification Office



### cc: J ohn Fox. 

### LGB-AEG. Brent Bandl ey 

### ANM-IOOL-COS PMMDC

- 92K9145 Re vision E

REVlSED 'UVISION LETTER

## ~----**-- ------** **---- --~llim** **~E=X~O ~F~P~A~G~E~C~** **H~A ~N~G~E~S------~--** **-- --** **~----~** PAGES AFFECTED REMARKS

New

A

B



## c

D

E REVISED ADDEO DELETED

1 -3

1.4 Title Page

Title Page I- 4

1

- 5,18

Titl e Page

Title Pa ge

Dl All Initi al release.

4

5

3

6

- 1 5

App. B & 

## c Add item #2

.

Add item # 3. Removed revision record.

Added 717 appucabi l ity. Added/re-numbered It ems #3, # 4, # 5.

C larified intent of SCI's versus CMR's.

Moved items 1

- 5 to appe ndix A. Separated item # I into SC!s 27

- 1 thru 27- 4; renumbered item #2 into SCI 35-1; renumbered item #3 into SCI 35-2; renumbered item #4 into SCT 35-3; renumbered item # 5 into SC124-l.

Revi se d title and added r e vision record.

Revi sed title page signatures as a result of SF AR88 activities. Added revision letter
to each page in report.

Added CDCCL's and ALl's in Appendices B and C, respective l y, as a result ofSFAR88 activity.

R

evised page number and applicability in Appendix D to include ALl's as well as SC I 's. Revised word in g o n short

- term extensions in Appendix D.

Due to content and timing issues regarding FAA approval of revision E and F of this report, tbe content of these two revisions have been swapped; previou s revision F is now revision E, and previous revision E wi ll in the future be revision F.

Both previous revisions have been rescinded by Boeing.

BOEING PROPRI E TARY IN FO RM A TIO N Copy right ©

- The Boeing Co mpan y- U npubli s hed Work APPROVED BY BY

M. 3 /1 8 / 1994 McKelvey

D. Olsen I 0 /3 1 / 1 994

D. Olsen 9 /26 / 1995

G. Nixon 6 / 1 /2 00 I

J. Bouey 11 /5/2 004

M. 12/15 / 2005 McKelvey**~** 

# \-vll':i/o·J"

Page iI

RE VISION LETTER

f INDEX OF PAGE CHANGES PAGES AFFECTE D REMARKS R EV I SED ADDED D ELE T E D

82

8 22,824

822-823

823

824

827

833

C6-C7 II

C8- C9 AJO Added addhional l ndex of Change Pages,

to accommodate changed information for revision f.

Deleted SCI 27-4 for the 717 horizonta l stab ili ze r primary trim relay, as the SCI

was incorrectly generated for a failure mode which was designed out for the 717.

Revised C DCCL implementation intent from an Ope r ator's maint e nance program to their control documents. This ensures that an Operator's Engineering department has visibility of control limita ti on information.

Lear-Romec PIN RRI 2559A was d e l eted,

as it is a fuel pump s ub-a ssem bly

, rather than the end item PIN RR 12551 A.

Added Nash fuel pump volute PIN's previously and inadvertently omitted.

Revi se d Argo

- Tech fue l pump CMM revision level; this lat est r ev ision in cludes speci tic SF AR88 warnings.

Revised Lear-Romec fuel pump CMM revision level to r eflect the current

re l eased version.

Revised DC

- 9 Indicator CMM revision level; this latest revision includes specific SF AR88 warnings.

Revised CDCCL 28-7 to provide an acceptable, al t ernate means of ensuring the fue l ptunp connector is p r oper l y torqued.

Revised ALl 20-2 to delete the MD-90 model, which uses a different wiring design.

Added ALI 20-3 for the MD-90 configur ation, reflecting a different wiring design than in ALI 20-2.

BO EING Pll OP RI ETARY INFORMATION Co p yrig ht ©

- The B oe ing Company- Unpublished Work MDC-92K9145 Revision f

REV IS ED 

### BY

M. McKelvey APPROVED 

### BY

8 / 9 / 2006

Page ii

### REVISION LETTER

G MDC-92K9145 Revision G

INDEX OF PAGE CHANGES 

### PAGES AFFECTED REVISED ADDED DELETED

A2

A4-A9

Bl9

B22-B24, B33

B27 iii 

### REMARKS REVISED
BY

Added additional Index of Change Pages, M.
to accommodate changed information for McKelvey revision F.

SCI reference to short-term extensions

was appendix B ; it should have been appendix D.

Revised SCis 27-1, 27-2 and 27-3 to change "remove and replace " with "remove, then replace with OEM overhauled or new", thus eliminating the potential for refurbishment per CMM. Added alternate PIN of same relay. Replaced incorrect AMM references with
correct AMM references; moved inspection interval rationale to SCI interval question 8 in SCI 27-3.

Revi sed CDCCL 20-11 to change the word " ri ght" to "either", as some twinjets have an auxiliary hydraulic pump in the l eft wheelwell.

Revised CDCCL 28-2 for Argo-Tech fuel
pump CMM 28-20-6 to r evision 6 and added new pump assembly P IN 398000-2
to both CDCCLs 28-2 and 28-7, reflecting a SF AR88 design change (lead wire shield) and reliability enhancement (gold plated connector pins).

Revised Goodrich I Simmonds I Liquidomter fuel quantity master indicator CMMs 28-40-14 and 28-41-41 to revision 4

, as it was inadver-tently not revised in the previous revision to this SCI; revision 4 includes specific SF AR88 warnings. 

### APPROVED
BY

6/7 / 2007

### ~~**---- ----~------~--** **----L-------~------------------------~---- --~----** **--~**

BOEING PROPRfET AR Y INFORMATION Copyrigh t ©- The Boeing Co mpan y- Unpublished Work Page iiiMDC-92K9145 Revision L

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page iv 

### INDEX OF PAGE CHANGES
PAGES AFFECTED REVISION

LETTER REVISE D ADDED DELETED REMARKS REVISED BY APPROVED BY

H

I

J vi-vii

A12

A14

A14-A15

B2

B22-B34

B30

vi-viii iv

A13

B21

v Added additional Index of Page Changes, to accommodate changed information for revision H.

Revised Table of Contents to add CDCCL 20-13 and increment page numbers for following CDCCLs.

Revised SCI 35-2 to remove incorrect AMM 35-20-00 reference and insert correct AMM task references. Revised interval from 12 years to 15 years.

Revised SCI 35-3 to remove incorrect AMM 35-10-00 reference and insert correct AMM task references; also changed the words “generator canisters” in paragraph 5 to “oxygen cylinder”.

All pages have been incremented to accommodate inclusion of revised SCI 35-2.

Revised second to last paragraph to clarify CDCCL configuration control information to applicable Operator’s Maintenance documentation.

Added CDCCL 20-13 for float and pressure switch circuit fuse sleeves, part of BDCO Project LB07-0018.

All pages have been incremented to accommodate inclusion of new CDCCL 20-13.

Revised CMM Revision Levels for CMM 28-40-34 from Rev 5 to Rev 7 and 28-40- 58 Rev 12 to Rev 15.

Revision I is not used

Added additional Index of Page Changes, to accommodate changed information for revision H.

Revised pages to accommodate new Index of Page Changes Page and updated page numbers to accommodate new page. M. Cox

M.Cox 1/18/2008

M. McKelveyREVISION LETTER

J

K INDEX OF PAGE CHANGES
PAGES AFFECTED REMARKS REVISED ADDED DELETED

vi, Al4

Al5

B21 B22

B22-B35

B25

B29

B31

B33

v ix

ix

B4

BlO

B13 Added CFR 26.33 Statement

Revised SCI 35-3 inspection interval from 3 years to 5 years to match DOT standards.

Revised SCI 24-1 to include alternate method of determining life

Added the fuse to CDCCL 20-13 and 717 applicability

Incremented pages to accommodate new page

CDCCL 28-2 revised CMM Revision Levels for CMM 28-20-1 from Rev 5 to Rev 6, CMM 28-20-2 Rev 2 to Rev 3 and CMM 28-20-03 Rev 5 to Rev 6.

CDCCL 28-4 revised CMM Revision Levels for CMM 28-40-14 from Rev 4 to Rev 5.

CDCCL 28-5 revised CMM Revision Levels for CMM 28-40-53 from Rev 8 to Rev 10

.

CDCCL 28-6 revised CMM Revision Levels for CMM 28-40-93 from Rev 2 to Rev 4 and 28-40-99 Rev IR to Rev 2

Revised IOPC added new IOPC, incremented pages table of contents

Revised table of contents to add new CDCCL and new ALis

CDCCL 20-1 was revised the limitations section to replace with same gauge.

CDCCL 20-5 limitations was revised to allow use of the SWPM

CDCCL 20-8 characteristics and limitations section re-written to further clarify the design intent and to allow additional documents that are allowed in the limitation

BOEING PROPRIETARY INFORMATION Copyright©- The Boeing Company- Unpublished Work MDC-92K9145 Revision J

REVISED BY APPROVED BY

J. Van Dalen

I 'I...--. 

# ' {C.

H. Don I t 1 A' I

A. Macias



### J..tt,, 

## 2/Z/10

M. McKelvey

# A~**'~**

9 "l;tJ/Jo

T. Harris 

## -{3&)

B. Nozari

## !lt~r

PagevREVISION LETTER

K

L

M INDEX OF PAGE CHANGES
PAGES AFFECTED REMARKS REVISED ADDED DELETED

B17-B19

B21-B22

B31

B33

ix

vi-ix

B31

B 33

C4-C5 B36

, C10-Cll

C1 2 -C15

X

A16-A19 CDCCL 20

- 10 and CDCCL 20-11 limitations was revised to allow more documents that can maintain the limitation

CDCCL 20-13, added applicability
statement.

CDCCL 28-5 Revised CMM Rev level from 15 to 16 for CMM 28-40-58

CDCCL 28-6 Revised CMM Rev level from 2 to 3 for CMM 28-40-99

Added Ground Fault Indicator CDCCL 28-8 and Associated ALI test 28-1

ALI 28-2 was added to check uncommanded running circuit.

Revised Table of Contents to remove CDCCL 28-8

, ALI 28-1 and ALI 28-2

B36

, C10- Removed Ground Fault Indicator CDCCL C 11 28-8 and Associated ALI test 28-1

,

C12-C15 Removed ALI 28-2 to check uncommanded running circuit.

Revised IOPC

, added new sheet. Causing the table of contents to move a page

. Revised table of contents to add SCI 34- 1, C DCCL 2 8-8

, ALI 2 8- 1 2 8- 2, and revise the name o f ALI 20-1

Added SC I 3 4- 1 F unctional Te st o f the C apta in and First O ffice r s Alt ime t er

Revised CDCCL 2 8 -5 to reflect CMM 28-40-53 revised to Rl2 from RIO.

Revised CDCCL 28-5 to reflect CMM 28-40-93 revised to R5 from R4

Revised ALI 20-1 re-titled and revised to include all circuit protection devices for**fue~** pumps and aux hydraulic pumps from just circuit breakers.

BOEING PROPRIETARY INFORMATION Copyright ©- The Boeing Company- Unpublished Work MDC-92K9145 Revision M 

### I

REVISED BY

M.Cox APPROVED BY

See Previous Page

Page viMDC-92K9145 Revision M

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page vii 

### INDEX OF PAGE CHANGES
REVISION

LETTER PAGES AFFECTED REMARKS REVISED BY APPROVED BY REVISE D ADDED DELETED

M B36, C10-C12

C13-C15 Added Ground Fault Indicator CDCCL 28-8 and Associated ALI test 28-1

ALI 28-2 was added to check uncommanded running circuit.MDC-92K9145 Revision M

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page viii 

### TWINJET SPECIAL COMPLIANCE ITEMS REPORT

TABLE OF CONTENTS

PAGE No. TITLE INTERVAL SUMMARY At intervals, prior to, but not to exceed:

1 Discussion

A1 Appendix A - SCIs

A4 27-1 DC-9 Replace Primary Longitudinal 8,000 flt hrs Up/Down Contactors

A6 27-2 MD-80 Replace Primary Longitudinal 16,000 flt hrs Up/Down Contactors

A8 27-3 MD-90 Replace Primary Longitudinal 16,000 flt hrs Up/Down Contactors

A10 Blank Page

A11 35-1 MD-80/MD-90 Replace Scott Aviation 12 years Passenger Chemical Oxygen Generators

A12 35-2 717 Replace Drager Passenger 15 years Chemical Oxygen Generators

A14 35-3 717 Replace Flight Deck Composite 5 years (inspect/retest) Oxygen Cylinder 15 years (replacement)

A15 24-1 DC-9/MD-80 Replace Emergency 3 years Power Switch

A16 34-1 Functional Test of the Captains and 48 months First Officer’s Altimeter MMDC-92K9145 Revision M

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page ix 

### TWINJET SPECIAL COMPLIANCE ITEMS REPORT

TABLE OF CONTENTS

PAGE No. TITLE _______________________

B1 Appendix B - CDCCLs

B4 20-1 Twinjet Repair Wire Gauges

B5 20-2 Twinjet FQIS Wire Isolation

B6 20-3 Twinjet In-Tank Wire Splices

B8 20-4 Twinjet Repair Wire Types

B10 20-5 Twinjet Wire Installations

B11 20-6 Twinjet Prohibition of Power Feeder Splices in Areas Above Fuel Tanks

B12 20-7 717 Float Switch Conduit Sleeves

B13 20-8 Twinjet Fuel Tank Access Door Bonding

B15 20-9 717/MD-80/MD-90 Wing R oot Area Lightning Protection

B17 20-10 Twinjet Fuel Tank Structural Design

B19 20-11 DC-9 Auxiliary Hydraulic Pump Conduit

B20 20-12 Twinjet Wiring Near Fuel Tanks and Fuel Pipes

B21 20-13 DC-9/MD-80/MD-90/717 Float and Pressure Switch Circuit Fuse Sleeves

B23 28-1 Twinjet Prohibit Safety Wire, Lockwire, Safety Cable or Cotter Pins Inside Fuel Tanks

B24 28-2 Twinjet Fuel Pump (Boost or Transfer) and Housing Assemblies

B27 28-3 Twinjet Fuel Pump Electrical Connector Wire/Conduit AssemblyMDC-92K9145 Revision M

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page x 

### TWINJET SPECIAL COMPLIANCE ITEMS REPORT

TABLE OF CONTENTS

PAGE No. TITLE _______________________

Appendix B – CDCCLs (cont’d)

B29 28-4 DC-9 Fuel Quantity Master Indicators

B31 28-5 MD-80/MD-90 Fuel Quantity Standard Electronic Module

B33 28-6 MD-80/MD-90/717 Fuel Quantity Standard Electronic Module

B35 28-7 Twinjet Fuel Pump Connector

B36 28-8 Twinjet Ground Fault Interrupter

PAGE No. TITLE INTERVAL SUMMARY At intervals, prior to, but not to exceed: C1 Appendix C - ALIs

C4 20-1 Twinjet Fuel Pump and Auxiliary On condition Hydraulic Pump Circuit Protection Devices Reset

C6 20-2 MD-80 Auxiliary Hydraulic 5,000 flt hrs (effective Pump Power Feeder Wiring 8/2/2006)

C8 20-3 MD-90 Auxiliary Hydraulic Pump 5,000 flt hrs (effective Power Feeder Wiring 8/2/2006)

C10 28-1 Twinjet Ground Fault Interrupter Test 4,000 flt hrs

C13 28-2 Twinjet Auxiliary and Center Wing Tank 4,000 flt hrs Fuel Pump Low Pressure Indication Sys Test

D1 Appendix D - Short Term Extensions M M

MMDC-92K9145 Revision J

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page 1 

### DISCUSSION

Certain systems in the twinjet fleet (see below) have been analyzed and found to require fixedinterval checks or limitations, as follows:

 Special Compliance Items (SCIs) - see Appendix A for their description and a listing of SCI’s

 Critical Design Configuration Control Limitations (CDCCLs) - see Appendix B for their description and a listing of CDCCL’s resulting from SFAR88 activities

 Airworthiness Limitation Instructions (ALIs) - see Appendix C for their description and a listing of ALIs resulting from SFAR88 activities

This Special Compliance Items (SCI) Report is the Type Certificate Data Sheet (TCDS) referenced report, which contains and documents SCIs, CDCCLs and ALIs.

14 CFR Part 26.33 Airworthiness Limitations

Applicable airplanes have been analyzed a nd found to meet the flammability requirements without any limitations.

DC-9 Series

DC-9-11 DC-9-12 DC-9-13 DC-9-14 DC-9-15 DC-9-15F DC-9-21 DC-9-31 DC-9-32 DC-9-32 (VC-9C) DC-9-32F DC-9-32F (C-9A, C-9B) DC-9-33F DC-9-34 DC-9-34F DC-9-41
DC-9-51
MD-80 Series

DC-9-81 DC-9-82 DC-9-83 DC-9-87 MD-88
MD-90 Series

MD-90-30
717 Series

717-200 JMDC-92K9145 Revision D

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page A1 

### Appendix A

Special Compliance Items (SCIs)MDC-92K9145 Revision G

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page A2 

### TWINJET SPECIAL COMPLIANCE ITEM REPORT

Special Compliance Items (SCIs) are a means of notifying the FAA, operators, and others of critical design items that cannot be changed w ithout violating the design intent, potentially making the airplane unsafe. For example, the SC I might require a repetitive check of pitot probe drains; similarly, the SCI might require a re move and replace task for emergency power switches.

Certification Maintenance Requirements (CMR’s) are used to limit the latency (exposure time) for certain safety-significant failures which directly impact Top Event numerical probabilities found in fault tree analysis; these can be found in MDC-J1271.

The terms of the applicable twinjet Type Certif icate are only valid when the SCIs are performed within the time intervals specified. SCIs are equivalent to one-star CMR’s, per Advisory Circular (AC) 25-19: the tasks and intervals specified are mandatory and cannot be changed, escalated, or deleted without the approval of FAA Engineering within the Aircraft Certification Office having cognizance over the type design.

Temporary deviations from the SCI intervals are permitted within the limitations of Appendix D.

While each SCI is included in this report, it is required that each SCI also be included in an appropriate document where it will be visible to airline personnel; therefore each SCI must be included in each Operator's Maintenance Program.

The SCIs herein are in addition to the mainte nance requirements established by the Maintenance Review Board activity and documented in the Main tenance Review Board Report. Inclusion of SCIs herein is only intended to limit the extension of task intervals for those portions of twinjet systems identified.MDC-92K9145 Revision D

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page A3 

### Each SCI specified herein includes the name of the system in which the SCI is needed, and the following information:

1. What twinjet model does this SCI apply to?

2. What part or LRU is being checked?

3. What failure mode is being looked for?

4. How is it found?

5. What tasks are to be performed?

6. Is test equipment needed?

7. What is the pass-fail criteria?

8. What is the SCI interval?

Each Pass-Fail criteria entry identifies each SCI task as an Inspection or Check, using the MRB definitions.

Please report any negative inspection results to your local Boeing Field Service Representative. If the Boeing Field Service Representative is not available, you may send the report to:

The Boeing Company 3855 Lakewood Blvd. Long Beach, CA, USA 90846

Attn: Manager - Avionics & Electrical Systems (Dept. L33) Service Engineering Technical Services & Modifications Mail Code: D800-0035MDC-92K9145 Revision G

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page A4 

### SCI 27-1 - DC-9 Replace Primary Longitudinal Up/Down Contactors

1. What twinjet model does this SCI apply to?

DC-9 Series

2. What part or LRU is being checked?

Primary longitudinal up/down contactors are being replaced or overhauled by OEM, not checked nor refurbished using CMM. The part is Leach P/N 5D0355-1 or 9207-10296.

3. What failure mode is being looked for?

The contactors are being replaced prior to their anticipated wear-out.

4. How is it found?

Remove the primary longitudinal up/down contactors per 5. below, then replace with OEM overhauled or new.

5. What tasks are to be performed?

Remove the primary longitudinal up/down c ontactors per Airplane Maintenance Manual (AMM) section 27-40-4 Page 401, and then replace with OEM overhauled or new.

Note: Airworthiness Directive (AD) 91- 21-07, titled "Inspection/Replacement of the Primary Longitudinal Trim Relays (Up and Down) Leach" mandates removal and replacement of these relays (Leach P/N 5D0355-1 or 9207-10296). The following references have been used to formulate the recalculation of this removal and replacement period: 1. DAC AVI "DC-9/MD-80 Existing Airw orthiness Directives Applicable to the MD-90", revision A, dated 11/17/92

2. DAC AVI C1-ECR-JMS-071 "MD-80 Comparison to DC-9 Flight Hours and Application to the Trim Relay Hard Time", dated 12/21/90

3. DAC AVI C1-ECR-JMS-023-Rev. A "R eliability Analysis of Trim Relay Hard-time", dated 12/19/90

6. Is test equipment needed?

None.MDC-92K9145 Revision G

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### SCI 27-1 - DC-9 Replace Primary Longitudinal Up/Down Contactors (cont’d )

7. What is pass/fail criteria?

There is no pass/fail criteria. This SCI consists of “remove and replace with OEM overhauled or new” tasks.

8. What is the SCI interval?

Remove and replace with OEM overhauled or new at intervals prior to, but not to exceed, 8,000 flight hours.MDC-92K9145 Revision G

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### SCI 27-2 - MD-80 Replace Primary Longitudinal Up/Down Contactors

1. What twinjet model does this SCI apply to?

MD-80 Series

2. What part or LRU is being checked?

Primary longitudinal up/down contactors are being replaced or overhauled by OEM, not checked nor refurbished using CMM. The part is Leach P/N 5D0355-1 or 9207-10296.

3. What failure mode is being looked for?

The contactors are being replaced prior to their anticipated wear-out.

4. How is it found?

Remove the primary longitudinal up/down contactors per 5. below, then replace with OEM overhauled or new.

5. What tasks are to be performed?

Remove the primary longitudinal up/down c ontactors per Airplane Maintenance Manual (AMM) section 27-40-04 Page 403, and then replace with OEM overhauled or new

Note: Airworthiness Directive (AD) 91- 21-07, titled "Inspection/Replacement of the Primary Longitudinal Trim Relays (Up and Down) Leach" mandates removal and replacement of these relays (Leach P/N 5D0355-1 or 9207-10296). The following references have been used to formulate the recalculation of this removal and replacement period: 1. DAC AVI "DC-9/MD-80 Existing Airw orthiness Directives Applicable to the MD-90", revision A, dated 11/17/92

2. DAC AVI C1-ECR-JMS-071 "MD-80 Comparison to DC-9 Flight Hours and Application to the Trim Relay Hard Time", dated 12/21/90

3. DAC AVI C1-ECR-JMS-023-Rev. A "R eliability Analysis of Trim Relay Hard-time", dated 12/19/90

6. Is test equipment needed?

None.MDC-92K9145 Revision G

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### SCI 27-2 - MD-80 Replace Primary Longitudinal Up/Down Contactors (cont’d )

7. What is pass/fail criteria?

There is no pass/fail criteria. This SCI consists of “remove and replace with OEM overhauled or new” tasks.

8. What is the SCI interval?

Remove and replace with OEM overhauled or new at intervals prior to, but not to exceed, 16,000 flight hours.MDC-92K9145 Revision G

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### SCI 27-3 - MD-90 Replace Primary Longitudinal Up/Down Contactors

1. What twinjet model does this SCI apply to?

MD-90 Series

2. What part or LRU is being checked?

Primary longitudinal up/down contactors are being replaced or overhauled by OEM, not checked nor refurbished using CMM. The part is Leach P/N 5D0355-1 or 9207-10296.

3. What failure mode is being looked for?

The contactors are being replaced prior to their anticipated wear-out.

4. How is it found?

Remove the primary longitudinal up/down contactors per 5. below, then replace with OEM overhauled or new.

5. What tasks are to be performed?

Remove the primary longitudinal up/down c ontactors per Airplane Maintenance Manual (AMM) section 27-41-03 Page 401, and then replace with OEM overhauled or new.

6. Is test equipment needed?

None.

7. What is pass/fail criteria?

There is no pass/fail criteria. This SCI consists of “remove and replace with OEM overhauled or new” tasks.MDC-92K9145 Revision G

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### SCI 27-3 - MD-90 Replace Primary Longitudinal Up/Down Contactors (cont’d )

8. What is the SCI interval?

Remove and replace with OEM overhauled or new at intervals prior to, but not to exceed, 16,000 flight hours.

Note: For the MD-90 series airplanes, these same relays are used in the same manner and environment as used for the DC-9 and MD-80 series airplanes; the only variable of concern when recalculating the removal and replacement time is average flight time, since the time in the cruise flight phase is the only variable that significantly changes. Service expe rience has shown that the MD-80 series airplanes average flight time is  1.45 hours; the average flight time for the MD90 series airplanes is estimated to be  1.50 hours. Therefore, expected usage of the relay has slightly increased, by 1.50/1.45, or  1.03. Since the slight increase in exposure tim e for relay failure occurs during the cruise phase of flight, where primary trim is used less, relay usage for the MD-90 series airplanes will not significantly change from the MD-80 series airplanes; the associated removal and replacement interv al will also not significantly change from the MD-80 series airplanes to the MD-90 series airplanes.MDC-92K9145 Revision F

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### BLANK PAGEMDC-92K9145 Revision D

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### SCI 35-1 – MD-80/MD-90 Replace Scott Aviation Passenger Chemical Oxygen Generators

1. What twinjet model does this SCI apply to?

MD-80 Series MD-90 Series

2. What part or LRU is being checked?

Passenger chemical oxygen generators are being replaced, not checked. The part is Scott Aviation P/N 801386-( ).

3. What failure mode is being looked for?

The oxygen generators are being replaced prior to their anticipated life-limit.

4. How is it found?

Remove and replace the passenger chemical oxygen generators per 5. below.

5. What tasks are to be performed?

Remove and replace the passenger chemical oxygen generators per Airplane Maintenance Manual (AMM) 35-20-00.

Note: The performance of the passenger chemical oxygen generator, originally installed in the MD-80, was evaluated over a period of 12 years to a Douglas supervised test program. The generato rs continued to perform to the test criteria during the entire time.

6. Is test equipment needed?

None.

7. What is pass/fail criteria?

There is no pass/fail criteria. This SCI consists of remove and replace tasks.

8. What is the SCI interval?

Remove and replace at intervals prior to, but not to exceed, 12 years.MDC-92K9145 Revision H

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### SCI 35-2 – 717 Replace Drager Passenger Chemical Oxygen Generators

1. What twinjet model does this SCI apply to?

717 Series

2. What part or LRU is being checked?

Passenger chemical oxygen generators are be ing replaced, not checked. The parts are Drager Aerospace P/N’s E74020-00, E74030-00 and E74040-01.

3. What failure mode is being looked for?

The oxygen generators are being replaced prior to their anticipated life-limit.

4. How is it found?

Remove and replace the passenger chemical oxygen generators per 5. below.

5. What tasks are to be performed?

Remove the passenger chemical oxygen ge nerators per the following Airplane Maintenance Manual (AMM) Tasks:

 Task 35-21-01-000-801 (Passenger Service Units)

 Task 35-21-01-000-802 (Forward Flight Attendant)

 Task 35-21-01-000-803 (Lavatory)

 Task 35-21-01-000-804 (Aft Flight Attendant)

Install replacement passenger chemical oxygen generators per the following AMM Tasks:

 Task 35-21-01-400-801 (Passenger Service Units)

 Task 35-21-01-400-802 (Forward Flight Attendant)

 Task 35-21-01-400-803 (Lavatory)

 Task 35-21-01-400-804 (Aft Flight Attendant)

Note: The Drager oxygen generators ha ve successfully passed the oxygen flow performance test after being subject ed, during the qualification test, to equivalent aircraft vibration level (reference Drager Aerospace report FPSUGEN-SDRL-05.08). The Drager passenge r chemical oxygen generators have established a maximum life of 15 years. H

H

HMDC-92K9145 Revision H

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### SCI 35-2 – 717 Replace Drager Passenger Chemical Oxygen Generators (cont’d)

6. Is test equipment needed?

None.

7. What is pass/fail criteria?

There is no pass/fail criteria. This SCI consists of remove and replace tasks.

8. What is the SCI interval?

Remove and replace at intervals prior to, but not to exceed, 15 years. HMDC-92K9145 Revision J

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### SCI 35-3 – 717 Replace Flight Deck Composite Oxygen Cylinder

1. What twinjet model does this SCI apply to?

717 Series

2. What part or LRU is being checked?

Flight deck composite oxygen cylinder

3. What failure mode is being looked for?

Composite oxygen cylinder integrity and capacity

4. How is it found?

Re-inspect and retest the composite oxygen cylinder per 5. below.

5. What tasks are to be performed?

Re-inspect and hydrostatically retest the composite oxygen cylinder every 5 years in accordance with 49 CFR-173.34(E) as prescribed for DOT 3HT cylinders.

Remove the oxygen cylinder per Airplane Maintenance Manual (AMM) Task 35-11-01- 000-802. Install replacement oxygen cylinder per AMM Task 35-11-01-400-802.

Note: The B/E Aerospace composite oxyge n cylinder is approved for use per specification DOT-E8162-1850. The maximum life of the composite oxygen cylinder is 15 years.

6. Is test equipment needed?

Hydrostatic test equipment, per 49 CFR-173.34(E) as prescribed for DOT 3HT cylinders.

7. What is pass/fail criteria?

Successful re-inspection and retest of the cylinder, up to its maximum life of 15 years.

8. What is the SCI interval?

Inspect and retest at intervals prior to, but not to exceed, 5 years.

Remove and replace at intervals prior to, but not to exceed, 15 years. J

JMDC-92K9145 Revision J

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### SCI 24-1 – DC-9/MD-80 Replace Emergency Power Switch

1. What twinjet model does this SCI apply to?

DC-9 Series MD-80 Series

2. What part or LRU is being checked?

Emergency power switch, P/N 103-2200

3. What failure mode is being looked for?

Replacement of the emergency power switch prior to its anticipated wear-out.

4. How is it found?

Remove and replace the emergency power switch per 5. below.

5. What tasks are to be performed?

Remove and replace the emergency power switch per Airplane Maintenance Manual (AMM) 24-23-02

6. Is test equipment needed?

None.

7. What is pass/fail criteria?

There is no pass/fail criteria. This SCI consists of remove and replace tasks.

8. What is the SCI interval?

Remove and replace at intervals prior to, but not to exceed, 3 years or 10,000 off-to-onto-off cycles.

Cycles are determined by the following procedure (AD AMOC): 1. Determine average flight cycles per day for the airframe 2. Determine switch cycles per day 3. Determine Airline Factor (AF) by dividing flights per day by switch cycles per day 4. Multiply Airline Factor (AF) by 10,000 to determine flight cycles between switch replacements. J

J JMDC-92K9145 Revision M

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### SCI 34-1 – FUNCTIONAL TEST OF THE CAPTAIN AND FIRST OFFICER’S ALTIMETER

1. What model does this SCI apply to? MD-80 series, MD-90 series, 717 series that are approved for flying in Reduced Vertical Separation Minimum (RVSM) airspace.

2. What part or LRU is being checked? MD-80, MD-90: Air Data Computer 717: Air Data Module

3. What failure mode is being looked for? The failure mode tested is transducer degradation of the air data system, which can cause erroneous altitude indication.

4. How is it found? Perform inspection per 5 below.

5. What tasks are to be performed? FUNCTIONAL TEST OF THE CAPTAI N’S AND FIRST OFFICER’S ALTIMETER 1. Job Set-up:

a. Open the circuit breakers referenced in the following AMM procedures: i. MD-90: LEAK TEST OF THE PITOT/STATIC SYSTEM (3,000 FEET) TASK 34-11-00-790-805 and install safety tags. ii. 717: LEAK TEST OF A PITOT SYSTEM TASK 34-11-00-790-808. iii. MD-80: Task Adjustment/Test Pitot Static System, 34-11-00 (Page Block 200). b. Apply aircraft electrical power: i. MD-90: APPLY EXTERNAL POWER, TASK 24-40-00-861-801. ii. 717: APPLY EXTERNAL POWER, TASK 24-40-00-861-801. iii. MD-80: EXTERNAL POWER – DESCRIPTION AND OPERATION 24-40- 00 (P/B 001).

c. Connect the test equipment as follows: i. 717 ONLY: 1. On the ICE PROTECTION panel, make sure that the AIR DATA HEAT switch light is off. 2. Put a DO NOT OPERATE tag, STD-858 on the AIR DATA HEAT switch light. 3. Ensure that Captain’s and First Officer’s PFD are on. 4. Ensure that the Captain’s and First Officer’s CADC switch light is off. ii. MD-80 and MD-90 ONLY: On the overhead panel, place the CADC switch to NORM. On the captain’s and first officer’s gusset panels, place the STATIC AIR switches to NORM. iii. On the ATC control panel, put the mode select knob to the STBY position. MMDC-92K9145 Revision M

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### SCI 34-1 – FUNCTIONAL TEST OF THE CAPTAIN AND FIRST OFFICER’S ALTIMETER (cont’d)

WARNING : USE ONLY RED POLYESTER TAPE TO SEAL STATIC PORTS. IF THE HOLES BECOME CLOGGED WITH TAPE RESIDUE, INCORRECT AIRSPEED-SENSING AND ALTITUDE-SENSING SIGNALS CAN OCCUR. THIS CAN CAUSE DANGEROUS FLIGHT CONDITIONS. iv. Seal the captain’s and first officer’s pitot tube drain holes with red polyester tape or other suitable device.

v. Connect the air data tester to the captain’s and first officer’s pitot tube. vi. Connect the air data tester to the captain’s and first officer’s static ports using suitable adapter. vii. Seal the opposite side static ports using red polyester tape or other suitable device. d. Set the Captain’s and First Officer’s BARO set to 29.92 in/Hg (1013.21 mBar).

WARNING : MAKE SURE ALL PERSONS AND EQUIPMENT ARE CLEAR OF THE AREAS AROUND THE CONTROL SURFACES. THE TEST CAN CAUSE THE AIRCRAFT CONTROL SURFACES TO MOVE. SUDDEN MOVEMENT OF THE CONTROL SURFACES CAN CAUSE INJURY TO PERSONS AND DAMAGE TO EQUIPMENT.

CAUTION : MAKE SURE THE AIR DATA TESTER OPERATES CORRECTLY. IF IT DOES NOT OPERATE CORRECTLY, IT CAN CAUSE DAMAGE TO THE INSTRUMENTATION SENSOR DEVICES.

CAUTION : WHEN YOU CHANGE ALTITUDE, DO NOT LET THE RATE OF CHANGE BE MORE THAN 6,000 FEET PER MINUTE. WHEN YOU CHANGE AIRSPEED, DO NOT LET THE RATE OF CHANGE BE MORE THAN 100 KNOTS PER MINUTE. DO NOT SUDDENLY RELEASE PRESSURE TO THE ATMOSPHERE FROM THE PITOT/STATIC LINES WHILE THE AIR DATA TESTER IS CONNECTED. DO NOT LET THE STATIC PRESSURE BE MORE THAN THE PITOT PRESSURE. THIS WILL HELP PREVENT DAMAGE TO THE EQUIPMENT.

2. Do the functional test of the Captain’s and First Officer’s Altimeter as follows:

a. On the air data tester, adjust the altitude to 41,000 feet (12,497 m). b. On the air data tester, adjust the airspeed to 105 knots.

c. On the captain’s instrument panel: i. Captain’s altitude requirements, the altitude shown on the captain’s altimeter must be 41,000 feet (12,497 meters) ± 75 feet (23 meters). MMDC-92K9145 Revision M

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### SCI 34-1 – FUNCTIONAL TEST OF THE CAPTAIN AND FIRST OFFICER’S ALTIMETER (cont’d) ii. Captain’s airspeed requirements, the airspeed shown on the captain’s airspeed indication must be 105 knots ± 4 knots. d. On the first officer’s instrument panel: i. First Officer’s altitude requirements, the altitude shown on the First Officer’s altimeter must be 41,000 feet (12,497 meters) ± 75 feet (23 meters). ii. First Officer’s airspeed requirements, the airspeed shown on the First Officer’s airspeed indication must be 105 knots ± 4 knots.

e. On the air data tester, slowly return the pitot and static pressure to the atmospheric pressure. 3. Job Close-up:

a. Remove the test equipment as follows: i. Disconnect the air data tester from the captain’s pitot tube and captain’s static port. ii. Remove tape from the captain’s pitot tube drain holes and static port. b. Remove all the tools and equipment from the work area. Make sure the area is clean.

c. Remove the safety tags and close these circuit breakers opened in Job Set-up. d. Remove external power from the aircraft. i. MD-90: REMOVE EXTERNAL POWER, TASK 24-40-00-862-801. ii. 717: REMOVE EXTERNAL POWER, TASK 24-40-00-862-801. iii. MD-80: EXTERNAL POWER – DESCRIPTION AND OPERATION 24-40- 00 (P/B 001).

6. Is test equipment needed?

 Tester, Air Data: must have a maximum altitude tolerance of +/-15ft (5 m) at 41,000ft (12,497 m).

 Adapter, Static Port

 Adapter, Pitot Head

 Tape - Polyester, Red, Silicone Adhesive: Specification DPM 850-24 or equivalent.

7. What is pass/fail criteria?

 Pass:

o Captain’s altitude requirements, the altitude shown on the captain’s altimeter must be 41,000 feet (12,497 meters) ± 75 feet (23 meters) at 41,000 feet (12,497 meters).

o Captain’s airspeed requirements, the airspeed shown on the captain’s airspeed indication must be 105 knots ± 4 knots at 105 knots.

o First Officer’s altitude requirements, the altitude shown on the First Officer’s altimeter must be 41,000 feet (12,497 meters) ± 75 feet (23 meters) at 41,000 feet (12,497 meters).

o First Officer’s airspeed requirements, the airspeed shown on the First Officer’s airspeed indication must be 105 knots ± 4 knots at 105 knots. MMDC-92K9145 Revision M

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### SCI 34-1 – FUNCTIONAL TEST OF THE CAPTAIN AND FIRST OFFICER’S ALTIMETER (cont’d)

 Fail:

o If any of the altitude and airspeed requirements are outside the tolerances listed in the pass criteria.

8. What is SCI interval? Intervals not to exceed 48 months. MMDC-92K9145 Revision E

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### Appendix B

Critical Design Configuration Control Limitations (CDCCLs)MDC-92K9145 Revision H

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### TWINJET CRITICAL DESIGN CONFI GURATION CONTROL LIMITATIONS

For some twinjet system functions, for complia nce with SFAR 88 and Advisory Circular (AC) 25.981-1B, limitations for certain SFAR88 design c onfigurations are required using AC 25-19 “Certification Maintenance Requirements (CMRs)” methodology as a guide.

Critical Design Configuration Control Limitations (CDCCLs) are a means of notifying the FAA, operators, and maintenance facilities of certain design configuration aspects that cannot be changed without violating the design intent, pot entially making the airplane non-compliant with FAR 25.981(b). Therefore, these configuration aspect s must be controlled such that they remain in the configuration as specified in each CDCCL.

The following CDCCLs are features that Boeing ha s identified as not obvious or intuitive that a change could impact safety. This list is not incl usive of every potential change or feature that is possible. For example, changing a circuit breaker to a higher current rating is not covered here because such a change obviously needs to be eval uated for impact to the circuit it protects. Changing a wire to a smaller gauge would have to be evaluated to determine if it could carry the required currents. However, a change to a larg er wire gauge has in the past been allowed without specific assessment, but this could in crease the chance of a tank wall burn through so it is identified as a CDCCL. Any ch ange or repair to any part of the aircraft not performed in accordance with OEM published data must be assessed by the modifier for safety and certification impact per the FARs; any changes or repairs performed in accordance with OEM published date prior to the CDCCL compliance tim e do not require reassessment. This list is only an aid to the operator and to the FAA in ev aluating future fuel system related repairs and changes for potential tank ignition risk.

The terms of the appropriate twinjet Type Certificate are only valid when the design configuration aspects specified by th ese CDCCLs are maintained as stated

. The configuration control limitations are mandatory and cannot be ch anged or deleted without the approval of FAA Engineering of the Los Angeles Airc raft Certification Office (LA-ACO).

SFAR88 established requirements for CDCCLs; it includes an implementation schedule for changes to the operator’s control documents to manage compliance with these limitations.

While each CDCCL is included in this report, it is required that each CDCCL also be included in an appropriate document where it will be visible to airline personnel; therefore each CDCCL configuration control information must be included in each Operator's appropriate maintenance documentation.

All maintenance and repair instructions provi ded by Boeing have been updated where required to ensure compatibility with these design limitations. HMDC-92K9145 Revision K

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### Each CDCCL specified herein includes the name of the system in which the CDCCL is needed, and the following information:

1. What model twinjet does this CDCCL apply to?

2. What part, LRU or system is the CDCCL levied against?

3. What characteristic of the design configuration for this item must be retained under control of this Limitation, and why?

4. What is the specific Limitation?

5. Were all applicable aircraft in compliance w ith this CDCCL at delivery from the Original Equipment Manufacturer (OEM)? If not, is there an applicable Service Bulletin or Service Rework package required for some aircraft?

6. When does this CDCCL become effective?MDC-92K9145 Revision K

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### CDCCL 20-1 - Twinjet Repair Wire Gauges

1. What twinjet model does this CDCCL apply to?

DC-9 Series MD-80 Series MD-90 Series 717 Series

2. What part, LRU or system is the CDCCL levied against?

Any repair wiring used inside or within 6” of the fuel tanks and fuel pipes.

3. What characteristic of the design configuration for this item must be retained under control of this Limitation, and why?

Adverse excessive temperatures that c ould result from wire arcing events are characterized for a limited, known set of OEM-approved wire gauges.

4. What is the specific Limitation?

Any repair wiring inside or with in 6” of the fuel tanks and fuel pipes must use the same wire gauge as the wire being replaced.

5. Were all applicable aircraft in complian ce with this CDCCL at delivery from the OEM? If not, is there an applicable S ervice Bulletin or Service Rework package required for some aircraft?

DC-9 Series All airplane type designs comply. MD-80 Series All airplane type designs comply. MD-90 Series All airplane type designs comply. 717 Series All airplane type designs comply.

6. When does this CDCCL become effective?

This CDCCL becomes effective for all repairs performed after August 1, 2006.MDC-92K9145 Revision E

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### CDCCL 20-2 - Twinjet FQIS Wire Isolation

1. What twinjet model does this CDCCL apply to?

DC-9 Series MD-80 Series MD-90 Series 717 Series

2. What part, LRU or system is the CDCCL levied against?

Fuel Quantity Indication System (FQIS) wiring.

3. What characteristic of the design configuration for this item must be retained under control of this Limitation, and why?

FQIS wires must be isolated or separated fr om other aircraft wiring, to prevent chafing that can lead to shorting to an incompatible power source.

4. What is the specific Limitation?

FQIS wires (as defined below) must maintain isolation from other aircraft wiring or have an integral physical barrier (as part of the approved FQIS wire construction).

FQIS Wire Bundle Definition

DC-9 - Master Indicator to Tank entry points MD-80/MD-90/717 – Standard Electronic Module (SEM) to Tank entry points

5. Were all applicable aircraft in complian ce with this CDCCL at delivery from the OEM? If not, is there an applicable S ervice Bulletin or Service Rework package required for some aircraft?

DC-9 Series All airplane type designs comply. MD-80 Series All airplane type designs comply. MD-90 Series All airplane type designs comply. 717 Series All airplane type designs comply (for Fuselages 5100 thru 5127, a portion of the wiring at the front of the SEM is not separated; it is found to be safe with no rework required).

6. When does this CDCCL become effective?

This CDCCL becomes effective for all repairs performed after August 1, 2006.MDC-92K9145 Revision E

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### CDCCL 20-3 - Twinjet In-Tank Wire Splices

1. What twinjet model does this CDCCL apply to?

DC-9 Series MD-80 Series MD-90 Series 717 Series

2. What part, LRU or system is the CDCCL levied against?

Any wiring inside the fuel tanks, including those routed in conduit located inside the fuel tank.

 Wiring going to AC and DC fuel pumps.

 Wiring belonging to the fuel quantity gauging system (FQGS).

 Wiring going to fuel high-level and low-level float switches (as applicable).

 Wiring going to wing upper skin ice detectors (as applicable).

This does not include wiring inside a LRU.

3. What characteristic of the design configuration for this item must be retained under control of this Limitation, and why?

Wiring inside fuel tanks shall not contai n splices, including wiring within in-tank conduits. Splices may allow fuel penetration to the conductors of the spliced wires. A deteriorated wire splice could result in a high resistance electrical path, higher than allowable wire temperatures, arcing and/or breach of the conduit assembly. Improper shielding/insulation at the splice could result in arcing to the conduit and breach of the conduit assembly.

4. What is the specific Limitation?

Splices of any type, including crimp or solder type, shall not be allowed on wires in the fuel tank or on wires inside conduits that are in the fuel tank.MDC-92K9145 Revision E

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### CDCCL 20-3 - Twinjet In-Tank Wire Splices (cont’d)

5. Were all applicable aircraft in complian ce with this CDCCL at delivery from the OEM? If not, is there an applicable S ervice Bulletin or Service Rework package required for some aircraft?

DC-9 Series All airplane type designs comply. MD-80 Series All airplane type designs comply. MD-90 Series All airplane type designs comply. 717 Series All airplane type designs comply.

6. When does this CDCCL become effective?

This CDCCL becomes effective for all repairs performed after August 1, 2006.MDC-92K9145 Revision E

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### CDCCL 20-4 - Twinjet Repair Wire Types

1. What twinjet model does this CDCCL apply to?

DC-9 Series MD-80 Series MD-90 Series 717 Series

2. What part, LRU or system is the CDCCL levied against?

Any repair wiring used inside or within 6” of the fuel tanks and fuel pipes.

3. What characteristic of the design configuration for this item must be retained under control of this Limitation, and why?

Adverse excessive temperatures that c ould result from wire arcing events are characterized for a limited, known set of OEM-approved wire gauges.

4. What is the specific Limitation?

Any repair wiring used inside or within 6” of the fuel tanks and fuel pipes cannot use any of the following wire types:

1. DES-SM2006 (PVC/Nylon  ) 2. 7484444 (“Quad 4”, PVC/Fiberglass/Nylon  ) 3. 7616964 (PVC/Nylon & PVC/Fiberglass/Nylon  ) 4. 7706560 (MIL-W-81044/9, XL-Polyolefin/XL-Kynar  ) 5. 7891145 (was Poly-X  , then later was Stilan  ) 6. BXS7007 (Aromatic Polyimide)MDC-92K9145 Revision E

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### CDCCL 20-4 - Twinjet Repair Wire Types (cont’d)

5. Were all applicable aircraft in complian ce with this CDCCL at delivery from the OEM? If not, is there an applicable S ervice Bulletin or Service Rework package required for some aircraft?

DC-9 Series Aircraft as originally built with previously approved wire types are acceptable. New repairs should onl y be made with OEM approved wire types. MD-80 Series Aircraft as originally built with previously approved wire types are acceptable. New repairs should onl y be made with OEM approved wire types. MD-90 Series Aircraft as originally built with previously approved wire types are acceptable. New repairs should onl y be made with OEM approved wire types. 717 Series Aircraft as originally built w ith previously approved wire types are acceptable. New repairs should onl y be made with OEM approved wire types.

6. When does this CDCCL become effective?

This CDCCL becomes effective for all repairs performed after August 1, 2006.MDC-92K9145 Revision K

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page B10 

### CDCCL 20-5 - Twinjet Wire Installations

1. What twinjet model does this CDCCL apply to?

DC-9 Series MD-80 Series MD-90 Series 717 Series

2. What part, LRU or system is the CDCCL levied against?

Any wiring used within 6” of fuel tanks and fuel pipes.

3. What characteristic of the design configuration for this item must be retained under control of this Limitation, and why?

Adverse excessive temperatures that c ould result from wire arcing events are characterized for a limited, known set of OEM- approved wire distance to the fuel tank walls or pipes.

4. What is the specific Limitation?

Repair of wiring within 6” of fuel tanks and fuel pipes must use existing wire routing and clipping established per OEM-approved wire inst allation or maintain wire clearances as prescribed in the applicable sections of SWPM 20-00-06 and/or SWPM 20-10-01.

5. Were all applicable aircraft in complian ce with this CDCCL at delivery from the OEM? If not, is there an applicable S ervice Bulletin or Service Rework package required for some aircraft?

DC-9 Series All airplane type designs comply. MD-80 Series All airplane type designs comply. MD-90 Series All airplane type designs comply. 717 Series All airplane type designs comply.

6. When does this CDCCL become effective?

This CDCCL becomes effective for all repairs performed after August 1, 2006.MDC-92K9145 Revision E

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### CDCCL 20-6 - Twinjet Prohibition of Power Feeder Splices in Areas Above Fuel Tanks

1. What twinjet model does this CDCCL apply to?

DC-9 Series MD-80 Series MD-90 Series 717 Series

2. What part, LRU or system is the CDCCL levied against?

Power feeders above any fuel tank.

Power feeders are defined as any wire 10 gauge and larger (10, 8, 6, 4, 2, 0, 00, 000, and 0000 wire gauges).

3. What characteristic of the design configuration for this item must be retained under control of this Limitation, and why?

Maintain wire continuity over fuel tanks without breaks. This will prevent adverse temperature effects on the fuel tank due to a potential splice failure.

4. What is the specific Limitation?

Power Feeders above any fuel tank shall be maintained without splices. Any needed repair splice needs to be implemented at a location at least 3 feet or 2 wire supports (whichever is further) from the fuel tank boundaries.

5. Were all applicable aircraft in complian ce with this CDCCL at delivery from the OEM? If not, is there an applicable S ervice Bulletin or Service Rework package required for some aircraft?

DC-9 Series All airplane type designs comply. MD-80 Series All airplane type designs comply. MD-90 Series All airplane type designs comply. 717 Series All airplane type designs comply.

6. When does this CDCCL become effective?

This CDCCL becomes effective for all repairs performed after August 1, 2006.MDC-92K9145 Revision E

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### CDCCL 20-7 – 717 Float Switch Conduit Sleeves

1. What twinjet model does this CDCCL apply to?

717 Series

2. What part, LRU or system is the CDCCL levied against?

High Level Float Switch Conduit. Low Level Float Switch Conduit.

3. What characteristic of the design configuration for this item must be retained under control of this Limitation, and why?

Teflon® hoses are to be installed inside the float switch conduits to provide wire protection from chafing and shorting to the conduit wall.

4. What is the specific Limitation?

Any replacement work must have Teflon® hose installed as built by the OEM.

5. Were all applicable aircraft in complian ce with this CDCCL at delivery from the OEM? If not, is there an applicable S ervice Bulletin or Service Rework package required for some aircraft?

717 Series All airplane type designs comply.

6. When does this CDCCL become effective?

This CDCCL becomes effective for all repairs performed after August 1, 2006.MDC-92K9145 Revision K

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### CDCCL 20-8 - Twinjet Fuel Tank Access Door Bonding

1. What twinjet model does this CDCCL apply to?

DC-9 Series MD-80 Series MD-90 Series 717 Series

2. What part, LRU or system is the CDCCL levied against?

All fuel tank access doors

3. What characteristic of the design configuration for this item must be retained under control of this limitation, and why?

Electrical current paths are defined by the installation and bonding processes in the relevant OEM fuel tank access door and access door installation design drawings. The paths are intended to conduct lightning current flowing along the skin, across the doors, or to disperse lightning current from an att achment point on an attach bolt, or a door, to the skin without arcing/sparking. The effectiveness of the conductive paths depends on specific surface treatments, sealants, sealing pr ocedures, seals, o-rings, fastener types, materials, conductive rubstrips, interference fit fasteners, and coatings.

The non-conductive features of the door installation shall also be maintained as they help to direct current flow to the conductive path. This includes anodizing, priming and sealing, as well as the seals (a type of rubber O-ring) on the door and the dome nuts.

Departing from the OEM designed electrical current path across different interfaces could create hazardous ignition sources inside the tank.

4. What is the specific limitation?

The conductive and non conductive path design which includes specific surface treatments, sealants, sealing procedures, seals, o-rings, fastener types, materials, conductive rubstrips, interference fit fasteners, and coatings must be maintained per OEM design data which includes Boeing design drawings or the Boeing SRM or the Boeing AMM or Boeing approved repairs or any combination of those.MDC-92K9145 Revision K

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### CDCCL 20-8 - Twinjet Fuel Tank Access Door Bonding (cont’d)

5. Were all applicable aircraft in complian ce with this CDCCL at delivery from the OEM? If not, is there an applicable S ervice Bulletin or Service Rework package required for some aircraft?

DC-9 Series All airplane type designs comply. MD-80 Series All airplane type designs comply. MD-90 Series All airplane type designs comply. 717 Series All airplane type designs comply.

6. When does this CDCCL become effective?

This CDCCL becomes effective for all repairs performed after August 1, 2006.MDC-92K9145 Revision E

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### CDCCL 20-9 – 717/MD-80/MD-90 Wing Root Area Lightning Protection

1. What twinjet model does this CDCCL apply to?

MD-80 Series MD-90 Series 717 Series

2. What part, LRU or system is the CDCCL levied against?

Sheet metal aluminum straps in the wing leadi ng edge area of the wing fillet connecting the ribs together and connecting the ribs to the fu selage. Also the overbraid shielding and or wire shield, depending on the model, and their grounding at both ends.

3. What characteristic of the design configur ation for this item must be retained under control of this limitation, and why?

The intense electromagnetic field created by lightning current in the wing root area is attenuated by a number of metal straps between the wing forward section (leading edge) at the most inboard rib and the fuselage. Depending on the model, the wire harnesses in the wing root area could be further protected w ith metal overbraid shields, grounded at both ends. In some models the wire shields, gr ounded at both ends, could be additional or only protection provided for some of the wiring. Th ese straps and shields, as defined in the relevant OEM drawings provide lightning protection to the aircraft equipment interfaced with the wires spanning across the wing root area.

The straps, as defined in the applicable OEM drawings, must be continuous and unbroken, the low-resistance electrical bonds at the two ends must be maintained. The overbraid must be continuous and undamaged by cuts, frayi ng, corrosion or other defects. The lowresistance bonds or grounds must be maintained at both ends of the overbraid/wire shield for it to be effective.

All replacement wires in the wing-root area re quire lightning protection to prevent induced transients from contaminating and threatening other aircraft systems in common wire harness inside the aircraft and wing.

The lightning protection in the wing root ar ea for different models are as follows:

- MD-80/-90: Aluminum straps, and wire shie lds (grounded at both ends) for some of the

wiring.

- 717: Aluminum straps and metal overbraid shielding (grounded at both ends) for all

wiring.MDC-92K9145 Revision E

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page B16 

### CDCCL 20-9 – 717/MD-80/MD-90 Wing Root Area Lightning Protection (cont’d)

4. What is the specific limitation?

Do not alter or remove the wing-root area li ghtning protection straps, wire overbraids and shields. Any replacement wires in this area must also be shielded/overbraided in the same manner, with the overbraids grounded at both ends.

5. Were all applicable aircraft in complian ce with this CDCCL at delivery from the OEM? If not, is there an applicable S ervice Bulletin or Service Rework package required for some aircraft?

MD-80 Series All airplane type designs comply. MD-90 Series All airplane type designs comply. 717 Series All airplane type designs comply.

6. When does this CDCCL become effective?

This CDCCL becomes effective for all repairs performed after August 1, 2006.MDC-92K9145 Revision K

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page B17 

### CDCCL 20-10 - Twinjet Fuel Tank Structural Design

1. What twinjet model does this CDCCL apply to?

DC-9 Series MD-80 Series MD-90 Series 717 Series

2. What part, LRU or system is the CDCCL levied against?

Fuel tank structure.

3. What characteristic of the design configur ation for this item must be retained under control of this Limitation, and why?

The electrical bonding path must be maintained at all tank penetrations and applicable equipment mounting brackets internal and extern al to the tank. Specifically the types of surface preparation prior to assembly and type s of fasteners used must assure that all mechanical joints and penetrations can handle the lightning currents at the respective locations. The non-conductive features (anodizing, priming, painting and sealing) also must be preserved, since they could be part of the design to direct current to the conductive parts, prevent arcing at specific locations or contain minor arcing.

4. What is the specific Limitation?

The conductive and non conductive path design wh ich includes specific surface treatments, sealants, sealing procedures, fastener types, and coatings must be maintained per OEM design data which includes Boeing design draw ings or the Boeing SRM or the Boeing AMM or Boeing approved repairs or any combination of those.

5. Were all applicable aircraft in complian ce with this CDCCL at delivery from the OEM? If not, is there an applicable S ervice Bulletin or Service Rework package required for some aircraft?

DC-9 Series All airplane type designs comply. MD-80 Series All airplane type designs comply. MD-90 Series All airplane type designs comply. 717 Series All airplane type designs comply.MDC-92K9145 Revision K

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page B18 

### CDCCL 20-10 - Twinjet Fuel Tank Structural Design (cont’d)

6. When does this CDCCL become effective?

This CDCCL becomes effective for all repairs performed after August 1, 2006.MDC-92K9145 Revision K

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page B19 

### CDCCL 20-11 – DC-9 Auxiliary Hydraulic Pump Conduit

1. What twinjet model does this CDCCL apply to?

DC-9 Series

2. What part, LRU or system is the CDCCL levied against?

Auxiliary Hydraulic Pump conduit.

3. What characteristic of the design configuration for this item must be retained under control of this Limitation, and why?

Auxiliary Hydraulic Pump wiring installed in metallic conduit in the either main wheelwell provides wire protection from chafing and potential shorts.

4. What is the specific Limitation?

Auxiliary Hydraulic Pump wiring must be inst alled in metallic conduit and maintained per SWPM 20-10-14 5. Were all applicable aircraft in complian ce with this CDCCL at delivery from the OEM? If not, is there an applicable S ervice Bulletin or Service Rework package required for some aircraft?

DC-9 Series All airplane type designs comply.

6. When does this CDCCL become effective?

This CDCCL becomes effective for all repairs performed after August 1, 2006.MDC-92K9145 Revision E

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page B20 

### CDCCL 20-12 - Twinjet Wiring Near Fuel Tanks and Fuel Pipes

1. What twinjet model does this CDCCL apply to?

DC-9 Series MD-80 Series MD-90 Series 717 Series

2. What part, LRU or system is the CDCCL levied against?

All wiring used near the fuel tanks and fuel pipes.

3. What characteristic of the design configuration for this item must be retained under control of this Limitation, and why?

Proper wire assembly and wire installati on techniques, wire bundle cleanliness, and adherence to the following requirements will minimize the likelihood that severe overheat or burn-through events will occur near fuel tanks and certain fuel pipes.

4. What is the specific Limitation?

Wires/wire assemblies, when installed within 6 inches of any fuel tank or fuel pipe, shall conform to Standard Wiring Practice Ma nual (Boeing Document Number D6-82481), Section 20-00-06.

5. Were all applicable aircraft in complian ce with this CDCCL at delivery from the OEM? If not, is there an applicable S ervice Bulletin or Service Rework package required for some aircraft?

DC-9 Series All airplane type designs comply. MD-80 Series All airplane type designs comply. MD-90 Series All airplane type designs comply. 717 Series All airplane type designs comply.

6. When does this CDCCL become effective?

This CDCCL becomes effective for all repairs performed after August 1, 2006.MDC-92K9145 Revision K

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page B21 

### CDCCL 20-13 – DC-9/MD-80/MD-90/717 Float and Pressure Switch Circuit

1. What model Twinjet does this CDCCL apply to?

DC-9 Series MD-80 Series MD-90 Series 717 Series

2. What part, LRU or system is the CDCCL levied against?

The fuse and DMS 2109 or DMS 2379 Type 4 sleeving material installed over the powered wire leads from the fuse to tank pe netration point on float and pressure switch circuits.

3. What characteristic of the design configur ation for this item must be retained under control of this Limitation, and why?

The fuse must be installed to protect the circuit.

DMS 2109 or DMS 2379 Type 4 sleeving material must be installed between the fuse and the tank penetration point, to isolate th e power lead from ot her wiring and provide additional wire protection from chafing and shorting.

For fuse installations that incorporate a dr ip loop near the fuse, sleeving will only extend from tank penetration point to bottom of the drip loop.

4. What is the specific Limitation?

Any replacement fuse must be the same type and rating as defined in the applicable service bulletin or per SWPM 20-20-02

Any replacement or repair of wiring or sleevi ng from the fuse to tank penetration point must have DMS 2109 or DMS 2379 Type 4 sleev ing installed per SWPM 20-10-01 or in accordance with the applicable service bulletin.

5. Were all applicable aircraft in complian ce with this CDCCL at delivery from the Original Equipment Manufacturer (OEM)? If no t, is there an applic able Service Bulletin or Service Rework package required for some aircraft?

DC-9 Series Service Bulletin DC9-28-217 revision New or later Service Bulletin DC9-28-217 revisi on 1 or later for the fuselage numbers listed below. KMDC-92K9145 Revision K

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page B22 

### CDCCL 20-13 – DC-9/MD-80/MD-90/717 Float and Pressure Switch Circuit (cont’d) Fuselage Number 281 304 340 377 399 421 438 458 530 539 548 552 647 650 653 656 659 662 665 668 670 686 692 696 698
700 702 704 707 765 769 774 784 786 795 801 809 811 843 934 954 982 1081 1084



### MD-80 Series Service Bulletin MD80-28-226 revision New or later MD-90 Series Service Bulletin MD90-28-012 revision New or later 717 Series Ships 5151 and subs were delivered within compliance Service Bulletin 717-28-014 revision New or later for all others.

6. When does this CDCCL become effective?

This CDCCL becomes effective after incorporation of Service Bulletin DC9-28-217, MD80-28-226, MD90-28-012, or 717-28-014 as applicable. KMDC-92K9145 Revision J

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### CDCCL 28-1 – Twinjet Prohibit Safety Wire, Lockwire, Safety Cable or Cotter Pins Inside Fuel Tanks

1. What twinjet model does this CDCCL apply to?

DC-9 Series MD-80 Series MD-90 Series 717 Series

2. What part, LRU or system is the CDCCL levied against?

Inside airplane fuel tanks.

3. What characteristic of the design configuration for this item must be retained under control of this Limitation, and why?

The use of safety wire, lockwire, safety cable or cotter pins within fuel tanks are not permitted.

Safety wire, lockwire, safety cable or co tter pins could become loose and have the potential to become FOD (foreign object debris) and cause filament heating, or arcing.

4. What is the specific Limitation?

Safety wire, lockwire, safety cable or cotter pi ns are not to be installed inside the fuel tanks. Components or equipment installed inside fuel tanks shall not use safety wire or cotter pins for hardware retention. Safety wire, lockwire, safety cable and cotter pins may be used if they are contained within the housing of an explosion proof, tank mounted LRU, and must be installed per applicab le Original Equipment Manufacture (OEM) design/repair/ maintenance documentation. In-shop LRU repairs must adhere to OEM Component Maintenance Manual (CMM) documen ted procedures and sole use of parts specified in the OEM’s CMM.

5. Were all applicable aircraft in complian ce with this CDCCL at delivery from the OEM? If not, is there an applicable S ervice Bulletin or Service Rework package required for some aircraft?

DC-9 Series All airplane type designs comply. MD-80 Series All airplane type designs comply. MD-90 Series All airplane type designs comply. 717 Series All airplane type designs comply.

6. When does this CDCCL become effective?

This CDCCL becomes effective for all repairs performed after August 1, 2006. JMDC-92K9145 Revision J

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page B24 

### CDCCL 28-2 - Twinjet Fuel Pump (Boost or Transfer) and Housing Assemblies

1. What twinjet model does this CDCCL apply to?

DC-9 Series MD-80 Series MD-90 Series 717 Series

2. What part, LRU or system is the CDCCL levied against?

Tank mounted electrically operated fuel pumps. Affected parts are:

 Nash Fuel Pump part number 65-5093-4 a nd associated volute part numbers 65- 5094-1, 65-5094-3, 65-5094-2, 65-5095-1, 65-5095-3

 Nash Fuel Pump Volute part numbers 65-5107-1, 65-5107-2.

 Nash Fuel Pump Volute part numbers 65-5095-2, 65-5095-4

 TRW / Argo-Tech Fuel Pump part numbers 398000-1, 398000-and associated volute part numbers 399300-2, 399500-1, 702200-1, 702300-1.

 Lear-Romec Fuel Pump part number RR12551A and associated volute part number RR12552A.

3. What characteristic of the design configuration for this item must be retained under control of this Limitation, and why?

Fuel pumps must be maintained to protect:

 original Explosion-proof features,

 electrical circuit integrity,

 impeller and housing material,

 protection from FOD ingestion,

 bonding paths,

 prevent exposure to mercury, and

 lead wire position retention.

The pump stators must specifically be wound w ith the same gauge wire and install the same thermal fuses in an identical manner as the OEM in order to protect the pumps dry running and overheat performance as demonstrated in qualification tests.

The pumps must retain all features desi gned by the OEM to provide explosion proof properties. These include but are not lim ited to: Bearing materials and clearances, Housing materials and thickness, size of vent and cooling holes and installation of flamearresting plates, and metal-to-metal faying surfaces. JMDC-92K9145 Revision J

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page B25 

### CDCCL 28-2 - Twinjet Fuel Pump (Boost or Transfer) and Housing Assemblies (cont’d)

The pump must retain all OEM features of the inlet housing shape and clearances and materials as well as the materials of the impellers (including the reprime impellers when installed). Non-sparking materials must be used where pump inlet surfaces might rub to prevent inlet ignition events.

Pump volute design and inlet screens must be maintained as designed by Boeing and/or OEM. This is to prevent FOD ingestion.

Connector detail design must continue to ma tch connector explosion proof test results. The pump connector wire lead routing inside the pump housing must be installed so that it cannot contact the rotor and charge the rotor wh ich could lead to an electrical arc between the inlet impeller and the housing.

The electrical bonding paths from the motor hous ing to the inlet housing to the volute and to ground must be maintained. Changes to material coatings at motor housing joints, motor-to-volute interface, and volute-to-struc ture interface could defeat fault current bonding paths.

Exposure of pump and volute’s aluminum com ponents to mercury may result in material embrittlement, which could compromise critical design features of the pump or volute.

All OEM design features, CMM instructions, or combinations of the two as applicable to a given pump model must be retained to prev ent contact between the stator lead wire(s) and rotor assembly, which could result in an energized rotor condition.

4. What is the specific Limitation?

Any repair to the fuel pumps must be ma de in accordance with the OEM’s Component Maintenance Manuals (CMMs) listed below or an FAA approved service bulletin.

Part Number(s) CMM CMM Revision (DC-9, MD-80, MD-90)

65-5093-4 65-5094-1 65-5094-2 65-5094-3 65-5095-1 65-5095-3 28-20-1 6

(DC-9, MD-80, MD-90)

65-5107-1 65-5107-2 28-20-2 3 J

J

JMDC-92K9145 Revision J

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page B26 

### Part Number(s) CMM CMM Revision (DC-9, MD-80, MD-90)

65-5095-2 65-5095-4 28-20-3 2

(DC-9, MD-80, MD-90)

398000-1 398000-2 399300-2 399500-1 702200-1 702300-1 28-20-6 6

(717)

398000-1 398000-2 399300-2 399500-1 28-20-6 6

(DC-9, MD-80, MD-90, 717)

RR12551A RR12552A 28-20-03 6

Any deviation from the OEM’s CMM must be justified by the modifier and approved by the FAA LA-ACO.

Exposure of any pump or volute assembly or their subcomponents to mercury is prohibited.

5. Were all applicable aircraft in complian ce with this CDCCL at delivery from the OEM? If not, is there an applicable S ervice Bulletin or Service Rework package required for some aircraft?

DC-9 Series All airplane type designs comply. MD-80 Series All airplane type designs comply. MD-90 Series All airplane type designs comply. 717 Series All airplane type designs comply.

6. When does this CDCCL become effective?

This CDCCL becomes effective for all repairs performed after August 1, 2006. J

JMDC-92K9145 Revision J

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### CDCCL 28-3 – Twinjet Fuel Pump Electrical Connector Wire/Conduit Assembly

1. What twinjet model does this CDCCL apply to?

DC-9 Series MD-80 Series MD-90 Series 717 Series

2. What part, LRU or system is the CDCCL levied against?

The aircraft installed fuel pump electrical connector/wiring/conduit assembly located inside the fuel tanks, passing through the fuel tank bulkhead, terminating at an electrical terminal strip or connector which connects the fuel pump to the aircraft power system.

This does not include wiring inside the fuel pump.

3. What characteristic of the design configuration for this item must be retained under control of this Limitation, and why?

1. Connector, Only P/N’s 14158-1 or 14158-2 can be used when rebuilding or repairing a pump conduit assembly for a DC-9. Only P/N 14158-2 can be used in MD-80s, MD-90s and 717s (used to maintain the explosion proof qualities when connected to the fuel pump connector).

2. Assembly procedures for the wire harne ss/conduit assembly are to be used to maintain the design intent to prevent c onnector, wiring and conduit damage and/or failure inside the tank.

4. What is the specific Limitation?

Only connector P/N’s 14158-1 or 14158-2 can be used when rebuilding or repairing a pump conduit assembly for a DC-9. Only connector P/N 14158-2 can be used wh en rebuilding or repairing a pump conduit assembly for a MD-80, MD-90 or 717. Repairs to the fuel pump conduit/wire assembly must be done with the assembly removed from the aircraft and in accordance with DC-9, MD-80, MD-90, 717 Overhaul Manual chapter 28-20-7, Revision 6 or later dated May 15, 1999. JMDC-92K9145 Revision J

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page B28 

### CDCCL 28-3 – Twinjet Fuel Pump Electrical Connector Wire/Conduit Assembly (cont’d)

5. Were all applicable aircraft in complian ce with this CDCCL at delivery from the OEM? If not, is there an applicable S ervice Bulletin or Service Rework package required for some aircraft?

DC-9 Series Not all DC-9 aircraft we re in compliance with this CDCCL at delivery. Boeing Service Bulle tin DC9-28-26, Revision 1 dated 4/21/1976 or later is effective for DC-9 Fuselage Number 1 through Fuselage Number 764. MD-80 Series All airplane type designs comply. MD-90 Series All airplane type designs comply. 717 Series All airplane type designs comply.

6. When does this CDCCL become effective?

This CDCCL becomes effective for all repairs performed after August 1, 2006. JMDC-92K9145 Revision J

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page B29 

### CDCCL 28-4 – DC-9 Fuel Quantity Master Indicators

1. What twinjet model does this CDCCL apply to?

DC-9 Series

2. What part, LRU or system is the CDCCL levied against?

All DC-9 airplanes which utilize the following fuel quantity gauging system (FQGS) components:

 Master indicator P/N’s B118-244 and B118-264 for Goodrich/Simmonds/Liquidometer FQGS installations

 Master indicator P/N’s 200-002-001 a nd 200-002-002 for Parker/Gull FQGS installations

3. What characteristic of the design configuration for this item must be retained under control of this Limitation, and why?

FQGS master indicator maintenance procedures must be controlled to protect its internal electrical circuit integrity, limiting operational and failure conditions to a known set of results.

4. What is the specific Limitation?

Any repair to a FQGS master indicator mu st be made in accordance with the OEM’s Component Maintenance Manuals (CMMs) lis ted below or an FAA approved service bulletin.

Part Number(s) CMM CMM Revision

200-002-001 and 200-002-002 28-40-14 5

B118-244 28-41-41 4 B118-264 28-41-11 B

Any deviation from the OEM’s CMM must be justified by the modifier and approved by the FAA LA-ACO. J

JMDC-92K9145 Revision J

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page B30 

### CDCCL 28-4 – DC-9 Fuel Quantity Master Indicators (cont’d)

5. Were all applicable aircraft in complian ce with this CDCCL at delivery from the OEM? If not, is there an applicable S ervice Bulletin or Service Rework package required for some aircraft?

DC-9 Series All airplane type designs comply.

6. When does this CDCCL become effective?

This CDCCL becomes effective for all repairs performed after August 1, 2006. JMDC-92K9145 Revision M

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page B31 

### CDCCL 28-5 – MD-80/MD-90 Fuel Quantity Standard Electronic Module

1. What twinjet model does this CDCCL apply to?

MD-80 Series MD-90 Series

2. What part, LRU or system is the CDCCL levied against?

Fuel quantity gauging system (FQGS) Standard Electronic Module (SEM).

 SEM P/N’s 367-010-001, 367-010-002, 367-010-005, 367-010-006, 367-010-011 and 367-010-012 for Parker/Gull FQGS installations

3. What characteristic of the design configuration for this item must be retained under control of this Limitation, and why?

FQGS SEM maintenance procedures must be c ontrolled to protect its internal electrical circuit integrity, limiting operational and failure conditions to a known set of results.

4. What is the specific Limitation?

Any repair to a FQGS SEM must be made in accordance with the OEM’s Component Maintenance Manuals (CMMs) listed below or an FAA approved service bulletin.

Part Number(s) CMM CMM Revision (MD-80)

367-010-001 and 367-010-002 28-40-34 7

(MD-80)

367-010-005 and 367-010-006 28-40-58 16

(MD-80 and MD-90)

367-010-011 and 367-010-012 28-40-53 12

MMDC-92K9145 Revision J

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page B32 

### CDCCL 28-5 – MD-80/MD-90 Fuel Quantity Standard Electronic Module (cont’d)



### Any deviation from the OEM’s CMM must be justified by the modifier and approved by the FAA LA-ACO.

5. Were all applicable aircraft in complian ce with this CDCCL at delivery from the OEM? If not, is there an applicable S ervice Bulletin or Service Rework package required for some aircraft?

MD-80 Series All airplane type designs comply. MD-90 Series All airplane type designs comply.

6. When does this CDCCL become effective?

This CDCCL becomes effective for all repairs performed after August 1, 2006. JMDC-92K9145 Revision M

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### CDCCL 28-6 – MD-80/MD-90/717 Fuel Quantity Standard Electronic Module

1. What twinjet model does this CDCCL apply to?

MD-80 Series MD-90 Series 717 Series

2. What part, LRU or system is the CDCCL levied against?

Fuel quantity gauging system (FQGS) Standard Electronic Module (SEM).

 MD-80/MD-90 SEM P/N 367-100-001 and 367- 100-002 for Parker FQGS installations

 717 SEM P/N 367-200-101 for Parker FQGS installations

3. What characteristic of the design configuration for this item must be retained under control of this Limitation, and why?

FQGS SEM maintenance procedures must be c ontrolled to protect its internal electrical circuit integrity, limiting operational and failure conditions to a known set of results.

4. What is the specific Limitation?

Any repair to a FQGS SEM must be made in accordance with the OEM’s Component Maintenance Manuals (CMMs) listed below or an FAA approved service bulletin.

Part Number(s) CMM CMM Revision (MD-80 and MD-90)

367-100-001 and 367-100-002 28-40-93 5

(717)

367-200-101 28-40-99 3

Any deviation from the OEM’s CMM must be justified by the modifier and approved by the FAA LA-ACO. M

MMDC-92K9145 Revision J

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### CDCCL 28-6 – MD-80/MD-90/717 Fuel Quantity Standard Electronic Module (cont’d)



### 5. Were all applicable aircraft in complian ce with this CDCCL at delivery from the OEM? If not, is there an applicable S ervice Bulletin or Service Rework package required for some aircraft?

MD-80 Series All airplane type designs comply. MD-90 Series All airplane type designs comply. 717 Series All airplane type designs comply.

6. When does this CDCCL become effective?

This CDCCL becomes effective for all repairs performed after August 1, 2006. JMDC-92K9145 Revision J

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### CDCCL 28-7 – Twinjet Fuel Pump Connector

1. What twinjet model does this CDCCL apply to?

DC-9 Series MD-80 Series MD-90 Series 717 Series

2. What part, LRU or system is the CDCCL levied against?

Tank mounted electrically operated fuel pumps. Affected parts are:

 Nash Fuel Pump part number 65-5093-4.

 TRW / Argo-Tech Fuel Pump part number 398000-1 and 398000-2.

 Lear-Romec Fuel Pump part numbers RR12551A and RR12559A.

3. What characteristic of the design configuration for this item must be retained under control of this Limitation, and why?

Proper torque of electrical connector to pump. An under torqued connector may leak fuel into the connector, or may back off and open the connector, leading to short circuits of the pump power wires and potentially an ignition source within the fuel tank.

4. What is the specific Limitation?

Inspection of the pump connector/torquing is to be witnessed by second individual every time the pump connector is installed.

or if a second individual is not available: An individual mechanic must double check the torque and confirm by applying a torque stripe to the connector every time a pump connector is installed.

5. Were all applicable aircraft in complian ce with this CDCCL at delivery from the OEM? If not, is there an applicable S ervice Bulletin or Service Rework package required for some aircraft?

DC-9 Series All airplane type designs comply. MD-80 Series All airplane type designs comply. MD-90 Series All airplane type designs comply. 717 Series All airplane type designs comply.

6. When does this CDCCL become effective?

This CDCCL becomes effective for all repairs performed after August 1, 2006. JMDC-92K9145 Revision M

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### CDCCL 28-8 – Twinjet Ground Fault Interrupter

1. What twinjet model does this CDCCL apply to?

DC-9 Series MD-80 Series MD-90 Series

2. What part, LRU or system is the CDCCL levied against?

Ground Fault Interrupter (GFI) installed on Auxiliary Fuel Tanks and MD-80/MD-90 center fuel tanks pumps.

3. What characteristic of the design configuration for this item must be retained under control of this Limitation, and why?

The ground fault detection and interruption feature protects against electrical arc burnthrough fuel tank ignition source threats that may result from certain electrical failure modes of the fuel pump motor assembly and fuel pump housing electrical connector.

4. What is the specific Limitation?

Any replacement boost and transfer fuel pump ground fault interrupter must be a Boeing approved part for installation on the applicable model.

5. Were all applicable aircraft in complian ce with this CDCCL at delivery from the OEM? If not, is there an applicable S ervice Bulletin or Service Rework package required for some aircraft?

DC-9 Series Service Bulletin DC9-28-218 Rev New or Later MD-80 Series Service Bulletin MD80-28-228 Rev New or Later MD-90 Series Service Bulletin MD90-28-013 Rev New or Later

6. When does this CDCCL become effective?

This CDCCL becomes effective after inco rporation of Service Bulletins DC9-28-218, MD80-28-228, or MD90-28-013 MMDC-92K9145 Revision E

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### Appendix C

Airworthiness Limitation Instruction (ALIs)MDC-92K9145 Revision E

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### TWINJET AIRWORTHINESS LIMITATION INSTRUCTIONS (ALI’s)

For some twinjet system functions, complian ce with SFAR 88 and Advisory Circular (AC) 25.981-1C require inspections 

### for certain design configurations, using AC 25-19 “Certification Maintenance Requirements (CMRs)” methodology as a guide.

Similarly, Airworthiness Limitation Instructi on (ALIs) are a means of detecting safety significant conditions, potentially making the ai rplane non-compliant with SFAR 88 and FAR 25.981(b). When an ALI detects such a condition, maintenance action to correct it is required.

The terms of the twinjet Type Certificate are only valid when associated checks specified by these ALIs are performed within the time interval s specified. ALIs are equivalent to one-star CMRs (per AC 25-19): The configuration contro l checks and intervals specified are mandatory and cannot be changed, escalated, or deleted w ithout the approval of FAA Engineering of the Los Angeles Aircraft Certification Office (LA-ACO).

Temporary deviations from the ALI intervals are permitted within the limitations of Appendix D.

While each ALI is included in this report, it is required that each ALI also be included in an appropriate document where it will be visible to airline personnel; therefore each ALI must be included in each Operator's Maintenance Program . SFAR88 established requirements for ALIs; it includes an implementation schedule of change s to the operator’s maintenance program to manage compliance with these limitations and implementation of these checks.

All maintenance and repair instructions provi ded by Boeing have been updated where required to ensure compatibility with these inspections.MDC-92K9145 Revision E

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### Each ALI specified herein includes the name of the system in which the ALI is needed, and the following information:

1. What model twinjet does this ALI apply to?

2. What part, LRU or system is the ALI levied against?

3. What part, LRU or system characteristic is being looked for?

4. How is it found?

5. What checks are to be performed?

6. Is test equipment needed?

7. What is the pass-fail criteria?

8. What is the ALI accomplishment interval?

9. When does this ALI become effective?

Please report any negative inspection results to your local Boeing Field Service Representative. If the Boeing Field Service Representative is not available, you may send the report to:

The Boeing Company 3855 Lakewood Blvd. Long Beach, CA, USA 90846

Attn: Manager - Avionics & Electrical Systems (Dept. L33) Service Engineering Technical Services & Modifications Mail Code: D800-0035MDC-92K9145 Revision M

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### ALI 20-1 - Twinjet Fuel Pump and Auxiliary Hydraulic Pump Circuit Protection Devices Reset

1. What twinjet model does this ALI apply to?

DC-9 Series MD-80 Series MD-90 Series 717 Series

2. What part, LRU or system is the ALI levied against?

All fuel pump and auxiliary hydraulic pump circuit protection devices, i.e. circuit breakers, ground fault interrupter, fault current detector, and fuse.

3. What part, LRU or system characteristic is being looked for?

This limitation prohibits the resetting of a ny tripped fuel pump and auxiliary hydraulic pump circuit protection devices until it has been determined it is safe to do so.

4. How is it found?

Tripped fuel pump and auxiliary hydraulic pump circuit protection devices will be reported by flight crew and will generate maintenance action.

5. What checks are to be performed?

Verify it is safe to reset the circuit prot ection device(s) by following the applicable OEM troubleshooting procedures. Fault(s) that resulted in circuit protection device trip must be isolated and corrected prior to reset if the fault(s) occurred inside the fuel tank or adjacent to any fuel tank wall.

6. Is test equipment needed?

Yes, standard electrical tools.

7. What is the pass-fail criteria?

Pass - It is safe to reset the circuit protec tion device(s) if the troubleshooting procedures are successfully completed, and problem has been corrected.

Fail - It is not safe to reset the circuit protec tion device(s) if the troubleshooting procedures are not successfully completed. M M

M

M

M

MMDC-92K9145 Revision M

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### ALI 20-1 - Twinjet Fuel Pump and Auxiliary Hydraulic Pump Circuit Protection Devices Reset (cont’d)

8. What is the ALI accomplishment interval?

There is no fixed inspection interval. Th is ALI applies only when the open circuit protection device condition occurs in service.

9. When does this ALI become effective?

August 2, 2006 M MMDC-92K9145 Revision F

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### ALI 20-2 – MD-80 Auxiliary Hydraulic Pump Power Feeder Wiring

1. What twinjet model does this ALI apply to?

 

### MD-80 Series

2. What part, LRU or system is the ALI levied against?

Auxiliary hydraulic pump power feeder wiring near the fuel tank.

3. What part, LRU or system characteristic is being looked for?

Physical separation of power feeder wiring from fuel tank walls.

4. How is it found?

Visual inspection.

5. What checks are to be performed?

(a) Verify that auxiliary hydraulic pump power feeders do not contact the fuel tank. (b) Verify that auxiliary hydraulic pump power feeders are properly installed in DMS 2109 sleeving, per Standard Wiring Practices Manual (Boeing document number D6-82481), section 20-10-01, in the paragraph titled “Protec tion of Installed Wire Bundles”, over the entire harness length that is adjacent to th e fuel tank. Additionally verify that the sleeving does not show signs of rubbing against fuel tank wall structure.

6. Is test equipment needed?

No.MDC-92K9145 Revision F

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### ALI 20-2 – MD-80 Auxiliary Hydraulic Pump Power Feeder Wiring (cont’d)

7. What is the pass-fail criteria?

Pass - The auxiliary hydraulic pump power feeder harness does not contact or show signs of rubbing against the fuel tank wall, and DMS 2109 sleeving is properly installed per paragraph 5.

Fail - The applicable length of auxiliary hydraulic pump power feeder harness shows signs of contact or rubbing against the fu el tank wall, or the DMS 2109 sleeving is not properly installed.

8. What is the ALI accomplishment interval?

At intervals prior to, but not to exceed, 5,000 flight hours.

9. When does this ALI become effective?

August 2, 2006MDC-92K9145 Revision F

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### ALI 20-3 – MD-90 Auxiliary Hydraulic Pump Power Feeder Wiring

1. What twinjet model does this ALI apply to?

 

### MD-90 Series

2. What part, LRU or system is the ALI levied against?

Auxiliary hydraulic pump power feeder wiring near the fuel tank.

3. What part, LRU or system characteristic is being looked for?

Physical separation of power feeder wiring from fuel tank walls.

4. How is it found?

Visual inspection.

5. What checks are to be performed?

(a) Verify that auxiliary hydraulic pump power feeders do not contact the fuel tank. (b) Verify that auxiliary hydraulic pump power f eeders are properly covered with a textile overbraid (outer layer) over the entire length that is adjacent to the fuel tank. Additionally, verify that the textile overbraid (outer layer) does not show signs of rubbing against fuel tank wall structure. NOTE: These power feeders are covered with a metallic inner layer and a textile overbraid outer layer.MDC-92K9145 Revision F

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### ALI 20-3 – MD--90 Auxiliary Hydraulic Pump Power Feeder Wiring (cont’d)

6. Is test equipment needed?

No.

7. What is the pass-fail criteria?

Pass - The auxiliary hydraulic pump power feeder harness does not contact or show signs of rubbing against the fuel tank wall, and the textile overbraid (outer layer) is properly installed per paragraph 5.

Fail - The applicable length of auxiliary hydraulic pump power feeder harness shows signs of contact or rubbing against the fuel tank wall, or the textile overbraid (outer layer) is not properly installed.

8. What is the ALI accomplishment interval?

At intervals prior to, but not to exceed, 5,000 flight hours.

9. When does this ALI become effective?

August 2, 2006MDC-92K9145 Revision M

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### ALI 28-1 - Twinjet Ground Fault Interrupter (GFI) Test

1. What twinjet model does this ALI apply to?

DC-9 Series MD-80 Series MD-90 Series

2. What part, LRU or system is the ALI levied against?

All Ground Fault Interrupters installed on MD -80/MD-90 center wing fuel tank and DC9/MD-80/MD-90 auxiliary fuel tank (if installed) fuel pump circuits

3. What part, LRU or system characteristic is being looked for?

The functionality of the ground fault interruption and indication features.

4. How is it found?

Functional Check of the GFI

5. What checks are to be performed? 1. Put the aircraft into the fuel pump operational/functional test condition per the AMM (Ref.DC-9 AMM 28-20-18, MD- 80 AMM 28-20-07, MD-80 AMM 28-20- 18, or MD-90 AMM 28-20-00 ). 2. Access applicable GFI to be tested. 3. Turn on applicable fuel pump to be tested (Ref. DC-9 AMM 28-20-18, MD-80 AMM 28-20-07, MD-80 AMM 28-20-18, or MD-90 AMM 28-20-00). 4. Verify fuel pump being tested is functional (Ref. DC-9 AMM 28-20-18, MD-80 AMM 28-20-07, MD-80 AMM 28-20-18, or MD-90 AMM 28-20-00). 5. Press the TEST Pushbutton, located at the top of the GFI being tested and release and verify the RESET Indicator has popped up and the white band on the Indicator is visible. 6. Verify fuel pump being tested is no longer functional, low fuel pressure indication should show for the applicable pump 7. Turn off the fuel pump being tested 8. To functionally reset the applicable fuel pump control GFI, press the RESET Indicator on the top of the GFI. 9. Press the RESET Indicator. Verify the RE SET Indicator remains depressed and the white band on the Indicator is no longer visible 10. Turn on applicable fuel pump to be tested (Ref. DC-9 AMM 28-20-18, MD-80 AMM 28-20-07, MD-80 AMM 28-20-18, or MD-90 AMM 28-20-00). MMDC-92K9145 Revision M

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### ALI 28-1 - Twinjet Ground Fault Interrupter Test (Contd)

11. Verify fuel pump being tested is functional (Ref. DC-9 AMM 28-20-18, MD-80 AMM 28-20-07, MD-80 AMM 28-20-18, or MD-90 AMM 28-20-00).

12. Repeat test on remaining GFIs.

6. Is test equipment needed?

No.

7. What is the pass-fail criteria?

Pass - The GFI de-energizes the pump and the RESET indicator pops up showing the white band.

Fail - The GFI does not de-energize the pump or the RESET indicator does not pop up. 8. What is the ALI accomplishment interval?

At intervals prior to, but not to exceed, 4,000 flight hours.

9. When does this ALI become effective?

This ALI becomes effective after incor poration of Service Bulletins DC9-28-218, MD80- 28-228, or MD90-28-013 MMDC-92K9145 Revision M

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### ALI 28-2 - Twinjet Auxiliary and Center Wing Tank Fuel Pump Low Pressure Indication System Test

1. What twinjet model does this ALI apply to?

DC-9 Series MD-90 Series

2. What part, LRU or system is the ALI levied against?

All fuel pump pressure indication systems installed for MD-90 Enhanced Flight Deck Configuration center wing fuel tanks and for DC-9 auxiliary fuel tanks (if installed).

3. What part, LRU or system characteristic is being looked for?

Wire and relay contact continuity check of the fuel pump low pressure indication system.

4. How is it found?

Electrical continuity checks of wiring and relay contacts.

5. What checks are to be performed?

General Set-Up and Access 1. Put the aircraft into the fuel pump operational/functional test condition per the AMM (Ref.DC-9 AMM 28-20-7, or MD-90 AMM 28-44-00). 2. Access applicable areas requiring temporary disconnection of wires 3. For DC-9/C-9 checks, verify airplane Ground Control system is configured to show an airplane “on-ground” status.

DC-9/C-9 – Forward and Aft Auxiliary Fuel Tanks with Direct Engine Feed Boost Pumps

WARNING: Power to the relay is needed for the test. Pulling associated breaker to remove and reattach the wire may be necessary.

4. Disconnect wire Q468F20 from the A1 terminal of Relay R2-1511

CAUTION: The relay A1 terminal will be powered with 28VDC while the fuel pump is commanded ON. MMDC-92K9145 Revision M

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### ALI 28-2 - Twinjet Auxiliary and Center Wing Tank Fuel Pump Low Pressure Indication System Test (Cont’d)

5. On the flight deck overhead panel, switch forward auxiliary fuel tank boost pump A to ON 6. Verify the applicable auxiliary fuel tank pump low pressure light on the OAP illuminates momentarily 7. On the flight deck overhead panel, switch forward auxiliary fuel tank boost pump A to OFF 8. Reconnect wire Q468F20 to the A1 terminal of Relay R2-1511 9. Repeat steps 4 thru 8 substituting the wires, relay and switch found in the table below
Wire Relay Switch Q468G20 R2-1512 FWD AUX BOOST PUMP B Q472F20 R2-1513 AFT AUX BOOST PUMP A Q472G20 R2-1514 AFT AUX BOOST PUMP B



### DC-9/C-9 – Forward Auxiliary Fuel Tank with Single Transfer Fuel Pump

Do steps 4 thru 8 of the DC-9/C-9 – Forward and Aft Auxiliary Fuel Tanks with Direct Engine Feed Boost Pumps substituting the wires, relay and switch found in the table below.
Wire Relay Switch Q478A20 R2-1511 FWD AUX BOOST PUMP



### DC-9/C-9 – Forward Auxiliary Fuel Tank with Single Transfer Fuel Pump and Aft Auxiliary Fuel Tank with Two Transfer Pumps

Do steps 4 thru 8 of the DC-9/C-9 – Forward and Aft Auxiliary Fuel Tanks with Direct Engine Feed Boost Pumps substituting the wires, relay and switch found in the table below.
Wire Relay Switch Q482E20 R2-1511 FWD AUX BOOST PUMP Q486B20 R2-1512 AFT AUX fuel NORM Tank Boost Pump* Q486C20 R2-1513 AFT AUX ALT Boost Pump



### DC-9/C-9 – Forward Auxiliary Fuel Tank with Two Transfer Pumps

Do steps 4 thru 8 of the DC-9/C-9 – Forward and Aft Auxiliary Fuel Tanks with Direct Engine Feed Boost Pumps substituting the wires, relay and switch found in the table below.
Wire Relay Switch Q482E20 R2-1511 FWD AUX fuel NORM Tank Boost Pump Q482D20 R2-1512 FWD AUX ALT Boost Pump MMDC-92K9145 Revision M

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### ALI 28-2 - Twinjet Auxiliary and Center Wing Tank Fuel Pump Low Pressure Indication System Test (Cont’d)

MD-90 Enhanced Flight Deck Configur ation Center Wing Tank Fuel Pumps

Verify open circuit exists for the circuit running through contacts 12/13 in relay R2- 1494 and contacts D2/D3 in relay R2-583 for center tank forward pump and contacts 12/13 in relay R2-1495 and contacts D2/D3 in relay R2-582 for center tank aft pump with applicable fuel pump commanded ON:

To evaluate the Center FWD Boost Pump, access VIA R-T-S Discrete Status Screens, Insert A, and do the following:

1) Put the Center FWD Boost Pump to ON and look at the state of Pin G8. (a) Verify O is shown for VIA-1. (b) Verify O is shown for VIA-2. (c) Put the Center FWD Boost Pump to OFF.

To evaluate the Center AFT Boost Pump, access VIA R-T-S Discrete Status Screens, Insert D, and do the following:

1) Put the Center AFT Boost Pump to ON and look at the state of Pin G8. (a) Verify O is shown for VIA-1 (b) Verify O is shown for VIA-2 (c) Put the Center AFT Boost Pump to OFF.

6. Is test equipment needed?

Electrical continuity test equipment

7. What is the pass-fail criteria?

C-9/DC-9 Auxiliary Fuel Tank Fuel Pumps Pass - auxiliary fuel tank pump low pressure light on the OAP illuminates momentarily

Fail - auxiliary fuel tank pump low pressure light on the OAP does not illuminate momentarily

MD-90 Enhanced Flight Deck Confi guration Center Wing Tank Fuel Pumps

Pass - Open circuit exists for pin A-G8, CTR FWD FUEL PMP RELAY in VIA-1 and VIA-2 R-T-S Discrete Status Screens, Insert A with the center tank forward pump commanded ON; MMDC-92K9145 Revision M

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### ALI 28-2 - Twinjet Auxiliary and Center Wing Tank Fuel Pump Low Pressure Indication System Test (Cont’d)

AND open circuit exists for pin D-G8, CTR AFT FUEL PMP RELAY in VIA-1 and VIA-2 R-T-S Discrete Status Screens, Insert D with the center tank aft pump commanded ON

Fail - Ground circuit exists for A-G8, CTR FWD FUEL PMP RELAY in VIA-1 or VIA2 R-T-S Discrete Status Screens, Insert A with the center tank forward pump commanded ON; OR ground circuit exists for pin D-G8, CTR AFT FUEL PMP RELAY in VIA-1 or VIA-2 R-T-S Discrete Status Screens, Insert D with the center tank aft pump commanded ON

8. What is the ALI accomplishment interval?

At intervals prior to, but not to exceed, 4,000 flight hours.

9. When does this ALI become effective?

This ALI becomes effective after incorporation of Service Bulletins DC9-28-218 or MD90-28-013 as applicable MMDC-92K9145 Revision E

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### APPENDIX D - SHORT-TERM EXTENSIONS

Since SCIs and ALIs are based on analysis using AC 25-19 methodology, temporary deviation from the SCI/ALI intervals in this document are permitted in accordance with the limitations within this Appendix. Such an extension shoul d be handled similar to the operator's Approved Short-term Escalation Procedures. Each time an operator uses such a temporary SCI/ALI interval extension, the operator must notify th eir local regulatory authority (e.g. Principle Maintenance Inspector) as soon as practicable that a short-term extension has been utilized.

Any deviation beyond the limitations within this Appendix requires approval of the responsible Los Angeles Aircraft Certification Office (LA- ACO), prior to its use. Extensions within the limitations of this Appendix have LA-ACO approval.

o Deviations are permitted only for an ex ceptional, short-term extension of an individual SCI/ALI for a specific airplane.

o Repeated use of extensions, either on the same airplane or on similar airplanes in the operator's fleet, must not be used as a substitute for good management practices.

o Repeated extensions for the same SCI/ALI are not allowed.

o Extensions may not be used for fleet SCI/ALI escalation or extension.

o Short-term is defined as 10% of the SCI/ALI interval, up to a maximum of 30 days; this is applicable to each SCI/ALI in this report unless specifically defined in the applicable SCI/ALI.

o The purpose of this Appendix is to allo w very short-term "get home" capability in those exceptional cases where uncontrollable or une xpected events ground an airplane with insufficient time remaining on a SCI/ALI. It is intended that use of such short-term exceptional extensions be rare . If they are desired more ofte n at an airline, it is evidence of trouble in maintenance planning. It is not allowed to repetitively use the authority of this Appendix for relief for such a situation.