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.

Effective 12/31/2009 references to MDC, DAC, MCDONNELL DOUGLAS or the DOUGLAS AIRCRAFT COMPANY contained in the content, header or footer refer to The Boeing Company.

BOEING PROPRIETARY, CONFIDENTIAL, AND/OR TRADE SECRET Copyright © 2013 The Boeing Company Unpublished Work - All Rights Reserved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, 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-02K1 003

TRIJET SPECIAL COMPLIANCE ITEM REPORT

Revision date: 02/0112013 Revision letter: K

Issue date: 5/17/2002 Contract number:

Prepared by:

## ~ 

# A (!

«

## --~ M:A:COX, Safety Engineering

Commercial Aviation Services, Long Beach Division

Approved by:

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_

·

_

·

# -~**~_ -.J** **r- ~**  ___ ....

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___ _ S.J. Jinadasa, DC-10/MD-11 Chief Design Engineer
OOP Design Office, Long Beach Division

This report is FAA approved and specifies Special Compliance Items (SC!s) as required by Part 25.1529 of the Federal Aviation Regulations, and
SFAR 88 Airworthiness Limitation Instructions (AL!s) & Critical Design Configuration Control Limitations (CDCCLs) required by Parts 25.981,
25.!529 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 5 ·Ol- 13

. 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 infonnation, contact The Boeing Compmty, 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, MD80, 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 v.Titing by Boeing.U.S. Department
of Transportation

Federal Aviation Administration

May I, 2013

In reply refer to: 120L-13-171

The Boeing Company
ATTN.: Mr. Robert Beaudreau,
Senior Manager, Certification & Airworthiness
2401 E. Wardlow Rd., M/C DS00-0018 Long Beach, CA 90807-5309

# R~c~'"~o**\'\fl.~** (\ 

## 3 '1.\)\3

## j\\R\\IOR'ffi~'i>S

## ct.RTI.HCi\.1\0~ &

Reference: Boeing letter CP-L4L-13-00052, dated March 6, 2013 with FAA Forms
8100-9 and Boeing Report MDC-02KI003, Revision K, dated February I,
2013 (Enclosure B)

Dear Mr. Beaudreau:

Subject: Boeing Request for Approval of Revision K to Boeing Report No. MDC-02KI003, 'Trijet Special Compliance Item Report"

The Federal Aviation Administration (FAA) has received the referenced letter requesting approval of Revision K to Boeing Report No. MDC-02KI003, 'Trijet Special Compliance

Item Report." This request is applicable to McDonnell Douglas Models MD-II series, MDI 0 series and DC-I 0 series airplanes.

The report contains additional maintenance requirements for design critical items identified

as special compliance items (SCis ), and serves as a notification to operators and authorities
of these SCis. The SCis are equivalent to one-star CMRs. The tasks and intervals defined
in the SCis are mandatory and carmot be changed without approval from the cognizant FAA
office.

Revision K to this report added SCI 34-4, functional test of the captain and first officer's altimeter, and revised the airplane maintenance manual reference for the MD-II landing

gears.

We have reviewed the document and approve Revision K to Boeing Report MDC-02KI003.Should you have any questions regarding this approval, please contact this office or Ms. Nenita Odesa at telephone number (562) 627-5234, FAX (562) 627-5210, or electronic
mail at nenita.odesa@faa.gov.

Sincerely,

# ~11-**J'~.r** Kevin Hull Manager, Los Angeles Aircraft Certification Office

cc: LGB-AEG (Buffington)
ANM-IOOL (Bandley) 2INDEX OF PAGE CHANGES MDC-02KI003

Revision B

REVISION PAGES AFFECTED REMARKS REVISED APPROVED

LETTER REVISED ADDED DELETED BY BY

New

A Title page

01

B

IV-VI

A4-A9

B2

B21 All

Appendix

B&C

iii Initial release. M. McKelvey

Revised title page signatures as a result of M.

SF AR88 activities. McKelvey

AIO Added CDCCL's and ALI's m Appendices B and C, respectively

, as a result of SF AR88 activity.

Revised page number and applicability in Appendix D to include ALI ' s as well as SCI ' s.

Added additional Index of Change Pages,

to accommodate changed information for

revision B

.

Revised Table of Contents to delete SCI
number

, title and interval summary for

page A I 0; otherwise

, the other pages incremented their page numbers due to

new Index of Changed Pages sheet.

Revised inspection interval and procedure

of SCI's 34-1 thru 34-3 to be consistent

with AD 2006-02-11.

Deleted SCI 33-1

, as issuance of service

bulletin MD 11-33-075 constitutes tenninating action to AD 2000-26-15 (this AD required inspection and repair as documented m SCI 33-1 and service

bulletin MD II-33A069)

.

Revised CDCCL implementation intent

from an Operator ' s maintenance program

to their control documents

. This ensures that an Operator's Engineering department has visibility of control limitation

information

.

Revised Limitation of C DCCL to include configuration information for DPS red

wrap tape

.

BOEING PROPRI E TARY I N FORMATION
C op y right ©

- The Boein g C ompan y- U npublish e d Work M

. McKelvey 12115 / 2005

8 / 9 / 2006

Page iiREVISION
LETTER

B



### c

D INDEX OF PAGE CHANGES

PAGES AFFECTED REMARKS
REVISED ADDED DELETED
B25-B26

B33

B39

B40

C6-C7

V- Vl

B24

B25

- B42

B38

B40 lV

A4-A10 Added a new, improved "-4" Hydro-Aire
fuel pump to the CDCCL; this additionally caused a CMM revision

.

Revised fuel pump CMM (PIN 568-1- 27202-002) to include SF AR88 specific warning on Cover Page only and improved assembly quality checks

.

Revised Densitometer CMM to include
SF AR88 specific warnings.

Revised MJP CMM to include:

• Six new, enhanced MJP PIN's (003-
008-208 thru -213) per Service

Letter MD-11-SL-28-107-A, dated
2/10 / 2006

• Change the CMM revision level;
this latest revision includes specific
SF AR88 warnings

.

Added new ALI to inspect MD-11 Tail
Tank FQGS wiring (both the metallic
overbraid and the DMS 2186 red wrap tape).

Deleted SCis 34-1 thru 34-3 and added
CDCCL 20-15 to Table of Contents

.

Deleted SCis 34-1 thru 34-3 since AD
2006-02-11 contains all necessary information.

Added CDCCL 20-15 for float and

pressure switch circuit fuse sleeves, part ofBDCO Project LB06-0039.

All pages have been incremented to accommodate inclusion of new CDCCL
20-15

.

Added 217-003-132 and 217-003-132M

to CMM 28-41-25 at Rev 1. These part numbers were inadvertently left off in Supplier CMM data lists, and was added
when the CMM itself was reviewed.

Revised CMM 28-40-88 (part of CDCCL 28-8) to include newly approved SEM
part number and to roll the CMM revision
level.

BOEING PROPRIETARY INFORMATION Copyright©- The Boeing Company- Unpublished Work REVISED

BY

M

. McKelvey

M. McKelvey

M.Cox 11'/11-' 

### 6/fl"'" MDC-02K1003
Revision D

APPROVED

BY

8/9 / 2006

### ~**~** 

### (II '').11b(,..

S. Jinadasa 

## 7f JJt { oJ

M

. McKelvey

Page iiiINDEX OF PAGE CHANGES MDC-02K1003
Revision E

REVISION 1----.::..P.:..:A:...:::G;.::E:..=S....::.A.=F:...::F:...::E:...:C:..;:T:...::E:.=D:.....___---l

LETTER REVISED ADDED DELETED REMARKS REVISED
BY APPROVED
BY

E iv -v

vi- viii

Vl

A4-A12

Al3-A22

A23-A32

A33-A42

A43-A52

A53-A62

A63-A72

A73-A93

A94-A95

A96-A97

B2

B27 Added new Index of Change pages for
revision E. M Cox M

. McKelvey

# ~ Incremented Table of Contents pages to accommodate new Index of Change Page

.

Added SCis 27-1 thru 27-8, 32-1 and 32-
2 to Table of Contents.

Added SCI 27-1 for DC-10 horizontal 

# ptt1.fZ ")_

stabilizer lubrication procedure. ' 

### 0;

Added SCI 27-2 for MD-10 horizontal
stabilizer lubrication procedure.

Added SCI 27-3 for MD-11 horizontal
stabilizer lubrication procedure.

Added SCI 27-4 for DC-10 two chain
horizontal stabilizer wear check.

Added SCI 27-5 for DC-10 four chain
horizontal stabilizer wear check.

Added SCI 27-6 for MD-10 two chain
horizontal stabilizer wear check.

Added SCI 27-7 for MD-10 four chain
horizontal stabilizer wear check.

Added SCI 27-8 for MD-11 horizontal
stabilizer wear check.

Added SCI 32-1 for Trijet landing gear truck beam pivot bolt lubrication

Added SCI 32-2 for Trijet landing gear truck beam pivot bolt inspection

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

In CDCCL 28-2, CMM 28-22-03 changed to revision 8, to support Service
Bulletin DC10-28A254R1 and MD11-
28Al34R1 release. Changed CMM 28-
22-01 revision level to support Service
Bulletin DC10-28A259 and MD11-
28Al38

.

BOEING PROPRIETARY INFORMATION Copyright©- The Boeing Company- Unpublished Work M. Lasley

J. Reynolds

A. Macias

Page ivREVISION

LETTER

E

F

G INDEX OF PAGE CHANGES

PAGES AFFECTED REMARKS REVISED

REVISED ADDED DELETED BY

B31-B32 CDCCL 28-4 moved to Report MDC09Kl000.

B36

B37

B38

B40-B41

B21

, C6,C7

Bl6-Bl7

B24

B 27

A 4

, All, Al3, A21,
A23-A26

Bl7 CDCCL 28-6 Changed CMM 28-20-02
revision level ; latest approved CMM

.

CDCCL 28-7 Changed CMM 28-41-01 to
CMM 28-41-20; latest approved CMM

. PIN contained in CMM 28-41-01 were moved to CMM 28-41-20.

CDCCL 28-7 Changes CMMs revision
levels of 28-41-20, 28-41-17, 28-41-24

, and 28-41-25 ; latest approved CMMs.

Revised CDCCL 28-8 to include latest
revision levels to CMMs 28-40-87

, 28-
40-88 28-40-86 and 28-41-63

. Added
PIN 367-040-073 to CMM 28-40-88

, it is
controlled by the CMM and inadvertently
left off.

Revised CDCCL 20-12 and ALI 20-2. Replaced "red-wrap" tape with DMS
2186 self adhering tape

Added CFR 26

. 33 Statement

Re v i s ed CDCCL 20-9 to include a new SIB for wire protections

Added fu s e as part of CDCCL 2 0-15

Re v i s ed C MM re v is i on le v el in C D CCL
28-2 See
Previous

Page

M

. Cox



# . ,

SCI 27-1, 27-2, 27-3 we r e upd ated to M. Cox
incl ud e the use of B MS 3-33 grease 

### ,4/,f-e--

Revised SIB DCl0-28-262 to reflect
revision 1 or later.

BOEING PROPRIETARY INFORMATION Copyright©- The Boeing Company- Unpublished Work MD C- 02K1003
Revision G

APPROVED
BY

See Previous Page

M. McKelvey

A. Macia s

M. McKelvey**~**

M. Lasley 

## JA1R.J-.

PagevREVISION
LETTER

H

I

J

K INDEX OF PAGE CHANGES

PAGES AFFECTED REMARKS
REVISED ADDED

vi-viii ix

B4, B12, B14, B18, B19, B21,

C7

viii

A98

B6-B7

B 23

B 2 9-B 3 0

B 40

viii-ix

A94-A95

A98-
A102 DELETED

Added new Index of page changes, table
of contents are on new page numbers

. Added new CDCCL and ALI to table of

contents

Revised CDCCL information referring to OEM data to further defme OEM data

sources.

ALI 20-2 Fail criteria was revised to add "Repair per SWPM 20-10-01 "

Revision Level Not Used

Revised name of CDCCL 20-14 to reflect
alternate parts, now includes all Trijets

, and SCI 33-1

SCI 33-1 re-instated to reference AML
MD-10-AML-33-101. The AML
contains instructions for repetitive inspection and terminating action to inspection

.

CDCCL 20-3 updated to include alternate part drawing

.

CDCCL 20-14 name changed from
MD11/MD-10 to Trijet, updated CDCCL

to include drawing reference for alternate
parts

. Clarification was added fo r MD- 1 1
conduits without sleeving

.

C MM 2 8- 2 3-0 2 was re v ised to r evision
1 0

.

CMM 2 8 -40- 8 7 was revised to revision 5.

Added SCI 34-4

Revised MD-11 AMM reference from
12-21-01 to 12-21

Added SCI 34-4 Functional Test of the Captain and First Officer's Altimeter

BOEING PROPRIETARY INFORMATION Copyright©· The Boeing Company- Unpublished Work REVISED BY

M.Cox

## ~ A**Ali.~.-** 

# <eli

M.Cox



### )_ 

# I

,... 

# '

# JV~

M.Cox**~~~-** MDC-02K1003
Revision K

APPROVED BY

M. McKelvey

B

. Nozari

T. Harris

A. Macias

M.McKelvey

K. Balbas

T

. Harris

A

. Macias

## ~ r--.

## J~

Page viMDC-02K1003
Revision E

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page vii TRIJET SPECIAL COMPLIANCE ITEM 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-10 Horizontal Stabilizer Actuator 1,800 flt hrs (effective
Lubrication 10/1/2009)

A13 27-2 MD-10 Horizontal Stabilizer Actuator 1,800 flt hrs (effective
Lubrication 10/1/2009)

A23 27-3 MD-11 Horizontal Stabilizer Actuator 1,800 flt hrs (effective
Lubrication 10/1/2009)

A33 27-4 DC-10 Horizontal Stabilizer Actuator 15,000 flt hrs (effective Wear Check (Aircraft wi th Two Drive 10/1/2009) Chains)

A43 27-5 DC-10 Horizontal Stabilizer Actuator 15,000 flt hrs (effective Wear Check (Aircraft wi th Four Drive 10/1/2009) Chains)

A52 27-6 MD-10 Horizontal Stabilizer Actuator 15,000 flt hrs (effective Wear Check (Aircraft wi th Two Drive 10/1/2009) Chains)

A62 27-7 MD-10 Horizontal Stabilizer Actuator 15,000 flt hrs (effective Wear Check (Aircraft wi th Four Drive 10/1/2009) Chains)

A72 27-8 MD-11 Horizontal Stabilizer Actuator 15,000 flt hrs (effective
Wear Check 10/1/2009)

A94 32-1 Trijet Main La nding Gear Truck Beam
Pivot Bolt Lubrication EMDC-02K1003
Revision K

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page viii TRIJET SPECIAL COMPLIANCE ITEM REPORT

TABLE OF CONTENTS

PAGE No. TITLE __________________________

A96 32-2 Trijet Main Landing Gear Truck Beam Pivot Bolt Inspection

A98 33-1 MD-10 Map Light Inspection and Terminating Action

A99 34-4 Functional Test of the Capt ain and First Offi cer’s Altimeter

B1 Appendix B - CDCCLs

B4 20-1 Trijet Repair Wire Gauges

B5 20-2 Trijet FQIS Wire Isolation

B6 20-3 Trijet Fuel Pump Conduit Sleeves

B8 20-4 Trijet In-T ank Wire Splices

B10 20-5 Trijet Repair Wire Types

B12 20-6 Trijet Wire Installations

B13 20-7 Trijet Prohibition of Power Feeder Splices in Areas Above Fuel Tanks

B14 20-8 Trijet Fuel Tank Access Door Bonding

B16 20-9 Trijet Wing Root Area Lightning Protection

B18 20-10 Trijet Fuel Tank Structural Design

B19 20-11 MD-11 Maintenance of Winglet Bonds

B21 20-12 MD-11 Maintenance of Tail Tank FQIS Wiring Overbraid

B22 20-13 Trijet Wiring Near Fu el Tanks and Fuel Pipes

B23 20-14 Trijet Float Switch Conduit Sleeves

B24 20-15 Trijet Float and Pressure Switch Circuit Fuse Sleeves

B25 28-1 Trijet Prohibit Safety Wire, Lockwire, Safety Cable or Cotter Pins Inside Fuel
Tanks KMDC-02K1003
Revision K

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page ix TRIJET SPECIAL COMPLIANCE ITEM REPORT

TABLE OF CONTENTS

PAGE No. TITLE __________________________

Appendix B – CDCCLs (cont’d)

B26 28-2 Trijet Fuel Pump (Boost or Transfer) and Housing Assemblies

B29 28-3 DC-10/MD-10 Fuel Pump (APU Start) and Housing Assemblies

B31 28-4 KC-10, KDC-10 Fuel Pump Assembly

B33 28-5 MD-11 Fuel Pump and Canister Assemblies

B35 28-6 Trijet Fuel Pump (APU Start) Assembly

B37 28-7 DC-10 Fuel Quantity Master Indicators

B40 28-8 MD-11 Fuel Quantity Standard Electronic Module, Densitometer, Multi-Junction Probe, and Ultrasonic Processor Drive Unit

B42 28-9 MD-10 Fuel Quantity Processor Unit

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

C1 Appendix C - ALIs

C4 20-1 Trijet Fuel Pump and Auxiliary On condition Hydraulic Pump Circuit Breaker
Reset

C6 20-2 MD-11 Inspection of Tail Tank 5 years (effective FQGS Wiring Overbraid 8/2/2006)

D1 Appendix D – Short-Term Extensions KMDC-02K1003
Revision F

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

Certain systems in the trijet 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 de scription 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 an d 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-10 Series

DC-10-10

DC-10-40

DC-10-30

DC-10-30F
DC-10-30F (KC-10A, KDC-10)

DC-10-10F

DC-10-40F

DC-10-15

MD-10 Series

MD-10-10F

MD-10-30F

MD-11 Series

MD-11

MD-11F FMDC-02K1003
Revision New

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

Special Compliance Items (SCIs)MDC-02K1003
Revision New

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

The terms of the applicable trijet Type Certif icate are only valid when the SCIs are performed within the time intervals specified. SCIs ar e 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 maintena nce 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 trijet systems identified.MDC-02K1003
Revision New

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 trijet 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 inspec tion results to your local Boeing Field Service Representative. If the Boeing Field Service Representative is not available, you ma y send the report to:

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

Attn: Manager - Avionics & Electri cal Systems (Dept. L33) Service Engineering
Technical Services & Modifications
Mail Code: D800-0035MDC-02K1003
Revision G

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page A4 SCI 27-1 - DC-10 HORIZONTAL STABILIZER ACTUATOR LUBRICATION

1. What model does this SCI apply to?

DC-10 series aircraft

2. What part or LRU is being checked?

Horizontal stabilizer actuator

3. What failure mode is being looked for?

A check for a failure mode does not apply. Th is SCI provides a lubrication procedure for
the horizontal stabilizer actuator.

4. How is it found?

Not applicable

5. What tasks are to be performed?

Perform the following horizontal stabilizer actuator lubrication procedure:

1. General

A. The grease removal and lubrication procedur es must be done together and in the sequence listed.

B. The use of clean, dry rags instead of solven t to remove the grease from the acme screws and acme nuts is recommended to prevent solvent contamination in the acme nuts.

C. When lubricating vented joints (grease can fr eely and visibly flow out), apply grease to the fittings until only new grease shows from the joints.

D. Do not intermix different grease specifications or different gr ease brands within the same specification.

E. When changing from one grease specificati on or brand to another, do the procedure “Change the Approved Grease Specification or Brand” in DC-10 AMM Chapter 12-00- 00, paragraph entitled “General Lubr ication - Maintenance Practice.”

F. Refer to DC-10 MM 12-21-00 for gene ral lubrication instructions. GMDC-02K1003
Revision E

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page A5 SCI 27-1 - DC-10 HORIZONTAL STABILIZER ACTUATOR LUBRICATION (cont’d)

G. The left and right horizontal stabilizer actuators are located forward of the horizontal
stabilizer constant section.

H. Access to the horizontal stab ilizer actuators is through access door 311AB, zone 311, in the lower aft fuselage compartment.

2. Remove the used grease from the horizontal stabilizer actuators.

A. Move the horizontal stabilizer to th e full aircraft nose down (AND) position.

WARNING : BEFORE PRESSURIZING HYDRAULIC SYSTEMS, MAKE
CERTAIN THAT LANDING GEAR GROUND LOCKPINS ARE
INSTALLED AND THAT APPLICABLE CONTROLS ARE IN
CORRECT POSITION TO PREVEN T INADVERTENT OPERATION
OF LANDING GEAR AND FLIG HT CONTROL SYSTEMS.

(1) Pressurize hydraulic systems 1 and 3 (Ref. DC-10 MM 29-00-00, Page 201).

WARNING : BEFORE MOVING HORIZONTAL STABILIZER TRIM CONTROLS,
MAKE CERTAIN THAT AREAS AROUND HORIZONTAL
STABILIZER AND ELEVATORS ARE CLEAR OF PERSONNEL AND EQUIPMENT AND THAT UPPER TAIL CONE DOORS ARE
CLOSED.

(2) Using the horizontal stabilizer trim sw itches on either control wheel, move the stabilizer to the full AND position.

(3) Shut off the hydraulic pressure source.

(4) Make sure that all thr ee hydraulic systems are depr essurized (Ref. DC-10 MM 29- 00-00, Page 201).

(5) Open and tag the following circuit breakers:

WARNING : TAG AND SAFETY CIRCUIT BREAKERS.

Circuit Breaker Panel Location Panel Area

AUTO PITCH TRIM A Avionics DC BUS 1

AUTO PITCH TRIM B Avionics DC BUS 3

HOR STAB ALTN TRIM CONT Avionics DC BUS 3 EMDC-02K1003
Revision E

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page A6 PRIMARY HORIZ STAB TRIM Upper Main DC BUS 2

SCI 27-1 - DC-10 HORIZONTAL STABILIZER ACTUATOR LUBRICATION (cont’d)

(6) Put a “DO NOT OPERATE” tag on the horiz ontal stabilizer trim handles on the control pedestal.

B. Apply grease to the left and right acme nut grease fittings (Ref. Figure 1).

C. Clean the exposed threads on the left and righ t acme screws above the acme nuts and the tops of the acme nuts with clean, dry rags to remove as much grease as possible.

D. Move the horizontal stabilizer to th e full aircraft nose up (ANU) position.

(1) Remove the safety tag and close the following circuit breaker:

Circuit Breaker Panel Location Panel Area

PRIMARY HORIZ STAB TRIM Upper Main DC BUS 2

WARNING : BEFORE PRESSURIZING HYDRAULIC SYSTEMS, MAKE
CERTAIN THAT LANDING GEAR GROUND LOCKPINS ARE
INSTALLED AND THAT APPLICABLE CONTROLS ARE IN
CORRECT POSITION TO PREVEN T INADVERTENT OPERATION
OF LANDING GEAR AND FLIG HT CONTROL SYSTEMS.

(2) Pressurize hydraulic systems 1 and 3 (Ref. DC-10 MM 29-00-00, Page 201).

WARNING : BEFORE MOVING HORIZONTAL STABILIZER TRIM CONTROLS,
MAKE CERTAIN THAT AREAS AROUND HORIZONTAL
STABILIZER AND ELEVATORS ARE CLEAR OF PERSONNEL AND EQUIPMENT AND THAT UPPER TAIL CONE DOORS ARE
CLOSED.

(3) Using the horizontal stabilizer trim sw itches on either control wheel, move the stabilizer to the full ANU position.

(4) Shut off the hydraulic pressure source.

(5) Make sure that all thr ee hydraulic systems are depr essurized (Ref. DC-10 MM 29- 00-00, Page 201). EMDC-02K1003
Revision E

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page A7 SCI 27-1 - DC-10 HORIZONTAL STABILIZER ACTUATOR LUBRICATION (cont’d)

(6) Open and tag the following circuit breaker:

WARNING : TAG AND SAFETY CIRCUIT BREAKER.

Circuit Breaker Panel Location Panel Area

PRIMARY HORIZ STAB TRIM Upper Main DC BUS 2

E. Clean the exposed threads on the left and righ t acme screws below the acme nuts and the bottoms of the acme nuts with clean, dry rags to remove as much grease as possible.

3. Lubricate the horizontal stabiliz er actuators (Ref. Figure 1).

A. Put a layer of grease around the complete ci rcumference of the e xposed threads on the left and right acme screws. Make sure that th e grease is liberally a pplied to the threads, including the flanks and botto m of each thread valley.

B. Move the horizontal stabili zer to the full AND position.

(1) Remove the safety tag and close the following circuit breaker:

Circuit Breaker Panel Location Panel Area

PRIMARY HORIZ STAB TRIM Upper Main DC BUS 2

WARNING : BEFORE PRESSURIZING HYDRAULIC SYSTEMS, MAKE
CERTAIN THAT LANDING GEAR GROUND LOCKPINS ARE
INSTALLED AND THAT APPLICABLE CONTROLS ARE IN
CORRECT POSITION TO PREVEN T INADVERTENT OPERATION
OF LANDING GEAR AND FLIG HT CONTROL SYSTEMS.

(2) Pressurize hydraulic systems 1 and 3 (Ref. DC-10 MM 29-00-00, Page 201).

WARNING : BEFORE MOVING HORIZONTAL STABILIZER TRIM CONTROLS,
MAKE CERTAIN THAT AREAS AROUND HORIZONTAL
STABILIZER AND ELEVATORS ARE CLEAR OF PERSONNEL AND EQUIPMENT AND THAT UPPER TAIL CONE DOORS ARE
CLOSED.

(3) Using the horizontal stabilizer trim sw itches on either control wheel, move the stabilizer to the full AND position.

(4) Shut off the hydraulic pressure source.

SCI 27-1 - DC-10 HORIZONTAL STABILIZER ACTUATOR LUBRICATION EMDC-02K1003
Revision E

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page A8 (cont’d)

(5) Make sure that all thr ee hydraulic systems are depr essurized (Ref. DC-10 MM 29- 00-00, Page 201).

(6) Open and tag the following circuit breaker:

WARNING : TAG AND SAFETY CIRCUIT BREAKER.

Circuit Breaker Panel Location Panel Area

PRIMARY HORIZ STAB TRIM Upper Main DC BUS 2

C. Put a layer of grease around the complete ci rcumference of the e xposed threads on the left and right acme screws. Make sure grease is liberally applied to the threads, including the flanks and bottom of each thread valley.

D. Apply grease to the left and right acme nut grease fittings.

E. Apply grease to the left a nd right sprocket bearings.

F. Move the horizontal stabilizer to distri bute the grease equally in the actuator.

(1) Remove the safety tag and close the following circuit breaker:

Circuit Breaker Panel Location Panel Area

PRIMARY HORIZ STAB TRIM Upper Main DC BUS 2

WARNING : BEFORE PRESSURIZING HYDRAULIC SYSTEMS, MAKE
CERTAIN THAT LANDING GEAR GROUND LOCKPINS ARE
INSTALLED AND THAT APPLICABLE CONTROLS ARE IN
CORRECT POSITION TO PREVEN T INADVERTENT OPERATION
OF LANDING GEAR AND FLIG HT CONTROL SYSTEMS.

(2) Pressurize hydraulic systems 1 and 3 (Ref. DC-10 MM 29-00-00, Page 201).

WARNING : BEFORE MOVING HORIZONTAL STABILIZER TRIM CONTROLS,
MAKE CERTAIN THAT AREAS AROUND HORIZONTAL
STABILIZER AND ELEVATORS ARE CLEAR OF PERSONNEL AND EQUIPMENT AND THAT UPPER TAIL CONE DOORS ARE
CLOSED.

(3) Using the horizontal stabilizer trim sw itches on either control wheel, move the
horizontal stabilizer to the full ANU and then the full AND positions.

SCI 27-1 - DC-10 HORIZONTAL STABILIZER ACTUATOR LUBRICATION (cont’d) EMDC-02K1003
Revision E

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page A9 (4) Move the horizontal stabilizer to the zero (neu tral) position.

(5) Shut off the hydraulic pressure source.

(6) Make sure that all thr ee hydraulic systems are depr essurized (Ref. DC-10 MM 29- 00-00, Page 201).

(7) Open and tag the following circuit breaker:

WARNING : TAG AND SAFETY CIRCUIT BREAKER.

Circuit Breaker Panel Location Panel Area

PRIMARY HORIZ STAB TRIM Upper Main DC BUS 2

G. Remove the grease that is not necessary from the left and right actuators. Do not remove grease from the working surfaces.

H. Clean the structural areas around the actuators. Remove any grease that is not necessary and any loose materials (sand, dirt, drill sh avings, etc.) that could contaminate the

actuators.

I. Remove the safety tags and clos e the following circuit breakers:

Circuit Breaker Panel Location Panel Area

AUTO PITCH TRIM A Avionics DC BUS 1

AUTO PITCH TRIM B Avionics DC BUS 3

HOR STAB ALTN TRIM CONT Avionics DC BUS 3

PRIMARY HORIZ STAB TRIM Upper Main DC BUS 2

J. Remove the “DO NOT OPERATE” tag from the horizontal stab ilizer trim handles on the control pedestal. EMDC-02K1003
Revision E

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page A10 SCI 27-1 - DC-10 HORIZONTAL STABILIZER ACTUATOR LUBRICATION (cont’d)

Figure 1 (Sheet 1) EMDC-02K1003
Revision G

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page A11 SCI 27-1 - DC-10 HORIZONTAL STABILIZER ACTUATOR LUBRICATION (cont’d)

ITEM

NO. ITEM DESCRIPTION LUBE
TYPE APPLICATION NUMBER
OF
FITTINGS
OR AREAS

1 Acme screw ++ Brush 1

2 Acme nut ++ Gun 1 3 Sprocket bearing WTR Gun 2

++ Grease - Special Purpose (Aeroshell 14)

WTR Grease - Wide Temperature Range - MIL-PRF-81322

NOTE : WTR or BMS 3-33 grease may be used as an alternative to Special Purpose (++) grease for items 1 and 2. BMS 3-33 grease may be us ed as an alternative to WTR grease for item 3. Obey the grease intermix and cha nging precautions in Paragraph 1, General.

Figure 1 (Sheet 2) GMDC-02K1003
Revision E

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page A12 SCI 27-1 - DC-10 HORIZONTAL STABILIZER ACTUATOR LUBRICATION (cont’d)

6. Is test equipment needed?

No test equipment is required.

7. What is pass/fail criteria?

This SCI provides a lubrication servicing pr ocedure; pass/fail cr iteria do not apply.

8. What is SCI interval?

The horizontal stabilizer actuator lubrication procedure shall be pe rformed at intervals not to exceed 1,800 flight hours. EMDC-02K1003
Revision G

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page A13 SCI 27-2 - MD-10 HORIZONTAL STABILIZER ACTUATOR LUBRICATION

1. What model does this SCI apply to?

MD-10 series aircraft

2. What part or LRU is being checked?

Horizontal stabilizer actuator

3. What failure mode is being looked for?

A check for a failure mode does not apply. Th is SCI provides a lubrication procedure for
the horizontal stabilizer actuator.

4. How is it found?

Not applicable

5. What tasks are to be performed?

Perform the following horizontal stabilizer actuator lubrication procedure:

1. General

A. The grease removal and lubrication procedur es must be done together and in the sequence listed.

B. The use of clean, dry rags instead of solvent to remove grease from the acme screws and nuts is recommended to prevent solven t contamination in the acme nuts.

C. When lubricating vented joints (grease can fr eely and visibly flow out), apply grease to the fittings until only new grease shows from the joints.

D. Do not intermix different grease specifications or different gr ease brands within the same specification.

E. When changing from one grease specificati on or brand to another, do the procedure “Change the Approved Grease Specification or Brand” in MD-10 AMM Chapter 12-00- 00, paragraph entitled “General Lubric ation – Maintenance Practices.”

F. Refer to MD-10 AMM 12-21-00 for ge neral lubricati on instructions. GMDC-02K1003
Revision E

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page A14 SCI 27-2 - MD-10 HORIZONTAL STABILIZER ACTUATOR LUBRICATION (cont’d)

G. The left and right horizontal stabilizer actuators are located forward of the horizontal
stabilizer constant section.

H. Access to the horizontal stab ilizer actuators is through access door 311AB, zone 311, in the lower aft fuselage compartment.

2. Remove Used Grease from Ho rizontal Stabilizer Actuators

A. Move the horizontal stabilizer to th e full aircraft nose down (AND) position.

WARNING : BEFORE PRESSURIZING HYDRAULIC SYSTEMS, MAKE
CERTAIN THAT LANDING GEAR GROUND LOCKPINS ARE
INSTALLED AND THAT APPLICABLE CONTROLS ARE IN
CORRECT POSITION TO PREVEN T INADVERTENT OPERATION
OF LANDING GEAR AND FLIG HT CONTROL SYSTEMS.

(1) Pressurize hydraulic systems 1 and 3 (MD-10 AMM, PAGE BLOCK 29-00-00/201).

WARNING : BEFORE MOVING HORIZONTAL STABILIZER TRIM CONTROLS,
MAKE CERTAIN THAT AREAS AROUND HORIZONTAL
STABILIZER AND ELEVATORS ARE CLEAR OF PERSONNEL AND EQUIPMENT AND THAT UPPER TAIL CONE DOORS ARE
CLOSED.

(2) Using the horizontal stabilizer trim sw itches on either control wheel, move the stabilizer to the full AND position.

(3) Shut off the hydraulic pressure source.

(4) Make sure that all three hydraulic sy stems are depressurized (MD-10 AMM, PAGEBLOCK 29-00-00/201). EMDC-02K1003
Revision E

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page A15 SCI 27-2 - MD-10 HORIZONTAL STABILIZER ACTUATOR LUBRICATION (cont’d)

WARNING : TAG AND USE SAFETY CLI PS TO SAFETY THE CIRCUIT
BREAKERS. IF THE CIRCUIT BREAKERS ARE NOT OPENED, TAGGED, AND SAFETIED, INJURY TO PERSONS AND DAMAGE TO EQUIPMENT CAN OCCUR.

(5) Open these circuit breakers and install safety tags:

AVIONICS, FLIGHT CONTROL DC BUS 1

Row Col Number Name

C 8 B1-693 AUTO PITCH TRIM 1

AVIONICS, MISC DC BUS 2

Row Col Number Name

F 3 B1-507 PRIMARY HORIZ STAB TRIM

OVERHEAD, RIGHT EMER DC BUS

Row Col Number Name

E 26 B1-694 AUTO PITCH TRIM 2

(6) Put a “DO NOT OPERATE” tag on the horiz ontal stabilizer trim handles on the control pedestal.

B. Apply grease to the left and right acme nut grease fittings (Figure 1).

C. Clean the exposed threads on the left and righ t acme screws above the acme nuts and the tops of the two acme nuts with clean, dry ra gs to remove as much grease as possible.

D. Move the horizontal stabilizer to th e full aircraft nose up (ANU) position.

(1) Remove the safety tag and close this circuit breaker:

AVIONICS, MISC DC BUS 2

Row Col Number Name

F 3 B1-507 PRIMARY HORIZ STAB TRIM EMDC-02K1003
Revision E

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page A16 SCI 27-2 - MD-10 HORIZONTAL STABILIZER ACTUATOR LUBRICATION (cont’d)

WARNING : BEFORE PRESSURIZING HYDRAULIC SYSTEMS, MAKE
CERTAIN THAT LANDING GEAR GROUND LOCKPINS ARE
INSTALLED AND THAT APPLICABLE CONTROLS ARE IN
CORRECT POSITION TO PREVEN T INADVERTENT OPERATION
OF LANDING GEAR AND FLIG HT CONTROL SYSTEMS.

(2) Pressurize hydraulic systems 1 and 3 (MD-10 AMM, PAGE BLOCK 29-00-00/201).

WARNING : BEFORE MOVING HORIZONTAL STABILIZER TRIM CONTROLS,
MAKE CERTAIN THAT AREAS AROUND HORIZONTAL
STABILIZER AND ELEVATORS ARE CLEAR OF PERSONNEL AND EQUIPMENT AND THAT UPPER TAIL CONE DOORS ARE
CLOSED.

(3) Using the horizontal stabilizer trim switches on either control wheel, move the stabilizer to the full ANU position.

(4) Shut off the hydraulic pressure source.

(5) Make sure that all three hydraulic sy stems are depressurized (MD-10 AMM, PAGEBLOCK 29-00-00/201).

WARNING : TAG AND USE A SAFETY CLIP TO SAFETY THE CIRCUIT BREAKER. IF THE CIRCUIT BREAKER IS NOT OPENED, TAGGED, AND SAFETIED, INJURY TO PERSONS AND DAMAGE TO EQUIPMENT CAN OCCUR.

(6) Open this circuit breaker and install a safety tag:

AVIONICS, MISC DC BUS 2

Row Col Number Name

F 3 B1-507 PRIMARY HORIZ STAB TRIM

E. Clean the exposed threads on the left and righ t acme screws below the acme nuts and the bottoms of the acme nuts with clean, dry rags to remove as much grease as possible.

3. Lubricate Horizontal Stabilizer Actuators (Figure 1)

A. Put a layer of grease around the complete ci rcumference of the e xposed threads on the left and right acme screws. Make sure that th e grease is liberally a pplied to the threads, including the flanks and botto m of each thread valley. EMDC-02K1003
Revision E

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page A17 SCI 27-2 - MD-10 HORIZONTAL STABILIZER ACTUATOR LUBRICATION (cont’d)

B. Move the horizontal stabili zer to the full AND position.

(1) Remove the safety tag and close this circuit breaker:

AVIONICS, MISC DC BUS 2

Row Col Number Name

F 3 B1-507 PRIMARY HORIZ STAB TRIM

WARNING : BEFORE PRESSURIZING HYDRAULIC SYSTEMS, MAKE
CERTAIN THAT LANDING GEAR GROUND LOCKPINS ARE
INSTALLED AND THAT APPLICABLE CONTROLS ARE IN
CORRECT POSITION TO PREVEN T INADVERTENT OPERATION
OF LANDING GEAR AND FLIG HT CONTROL SYSTEMS.

(2) Pressurize hydraulic systems 1 and 3 (MD-10 AMM, PAGE BLOCK 29-00-00/201).

WARNING : BEFORE MOVING HORIZONTAL STABILIZER TRIM CONTROLS,
MAKE CERTAIN THAT AREAS AROUND HORIZONTAL
STABILIZER AND ELEVATORS ARE CLEAR OF PERSONNEL AND EQUIPMENT AND THAT UPPER TAIL CONE DOORS ARE
CLOSED.

(3) Using the horizontal stabilizer trim sw itches on either control wheel, move the stabilizer to the full AND position.

(4) Shut off the hydraulic pressure source.

(5) Make sure that all three hydraulic sy stems are depressurized (MD-10 AMM, PAGEBLOCK 29-00-00/201).

WARNING : TAG AND USE A SAFETY CLIP TO SAFETY THE CIRCUIT BREAKER. IF THE CIRCUIT BREAKER IS NOT OPENED, TAGGED, AND SAFETIED, INJURY TO PERSONS AND DAMAGE TO EQUIPMENT CAN OCCUR.

(6) Open this circuit breaker and install a safety tag:

AVIONICS, MISC DC BUS 2

Row Col Number Name

F 3 B1-507 PRIMARY HORIZ STAB TRIM EMDC-02K1003
Revision E

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page A18 SCI 27-2 - MD-10 HORIZONTAL STABILIZER ACTUATOR LUBRICATION (cont’d)

C. Put a layer of grease around the complete ci rcumference of the e xposed threads on the left and right acme screws. Make sure that th e grease is liberally a pplied to the threads, including the flanks and botto m of each thread valley.

D. Apply grease to the left and right acme nut grease fittings.

E. Apply grease to the left a nd right sprocket bearings.

F. Move the horizontal stabilizer to distri bute the grease equally in the actuator.

(1) Remove the safety tag and close this circuit breaker:

AVIONICS, MISC DC BUS 2

Row Col Number Name

F 3 B1-507 PRIMARY HORIZ STAB TRIM

WARNING : BEFORE PRESSURIZING HYDRAULIC SYSTEMS, MAKE
CERTAIN THAT LANDING GEAR GROUND LOCKPINS ARE
INSTALLED AND THAT APPLICABLE CONTROLS ARE IN
CORRECT POSITION TO PREVEN T INADVERTENT OPERATION
OF LANDING GEAR AND FLIG HT CONTROL SYSTEMS.

(2) Pressurize hydraulic systems 1 and 3 (MD-10 AMM, PAGE BLOCK 29-00-00/201).

WARNING : BEFORE MOVING HORIZONTAL STABILIZER TRIM CONTROLS,
MAKE CERTAIN THAT AREAS AROUND HORIZONTAL
STABILIZER AND ELEVATORS ARE CLEAR OF PERSONNEL AND EQUIPMENT AND THAT UPPER TAIL CONE DOORS ARE
CLOSED.

(3) Using the horizontal stabilizer trim sw itches on either control wheel, move the
horizontal stabilizer to the full ANU and then the full AND positions.

(4) Move the horizontal stabilizer to the zero (neu tral) position.

(5) Shut off the hydraulic pressure source.

(6) Make sure that all three hydraulic sy stems are depressurized (MD-10 AMM, PAGEBLOCK 29-00-00/201). EMDC-02K1003
Revision E

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page A19 SCI 27-2 - MD-10 HORIZONTAL STABILIZER ACTUATOR LUBRICATION (cont’d)

WARNING : TAG AND USE A SAFETY CLIP TO SAFETY THE CIRCUIT BREAKER. IF THE CIRCUIT BREAKER IS NOT OPENED, TAGGED, AND SAFETIED, INJURY TO PERSONS AND DAMAGE TO EQUIPMENT CAN OCCUR.

(7) Open this circuit breaker and install a safety tag:

AVIONICS, MISC DC BUS 2

Row Col Number Name

F 3 B1-507 PRIMARY HORIZ STAB TRIM

G. Remove the grease that is not necessary from the left and right actuators. Do not remove grease from the working surfaces.

H. Clean the structural areas around the actuators. Remove any grease that is not necessary and any loose material (sand, dirt, drill sh avings, etc.) that co uld contaminate the

actuators.

I. Remove the safety tags and close these circuit breakers:

AVIONICS, FLIGHT CONTROL DC BUS 1

Row Col Number Name

C 8 B1-693 AUTO PITCH TRIM 1

AVIONICS, MISC DC BUS 2

Row Col Number Name

F 3 B1-507 PRIMARY HORIZ STAB TRIM

OVERHEAD, RIGHT EMER DC BUS

Row Col Number Name

E 26 B1-694 AUTO PITCH TRIM 2

J. Remove the “DO NOT OPERATE” tag from the horizontal stab ilizer trim handles on the control pedestal. EMDC-02K1003
Revision E

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page A20 SCI 27-2 - MD-10 HORIZONTAL STABILIZER ACTUATOR LUBRICATION (cont’d)

Figure 1 (Sheet 1) E

CAG(IGDS) LUBRICATION PLACARD /

NOTE:

LEFT SID RIGHT**SI~~~~~ONSITE.** ACCESS DOOR

DC-10 LUB F1MDC-02K1003
Revision G

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page A21 SCI 27-2 - MD-10 HORIZONTAL STABILIZER ACTUATOR LUBRICATION (cont’d)

ITEM

NO. ITEM DESCRIPTION LUBE TYPE APPLICATION NUMBER OF
FITTINGS
OR AREAS

1 Acme screw ++ Brush 1

2 Acme nut ++ Gun 1 3 Sprocket bearing WTR Gun 2 ++ Grease - Special Purpose (Aeroshell 14)

WTR Grease - Wide Temperature Range - MIL-PRF-81322

NOTE : WTR or BMS 3-33 grease may be used as an alternative to Special Purpose (++) grease for items 1 and 2. BMS 3-33 grease may be
used as an alternative to WTR grease for item 3. Obey the grease intermix and changing precautions in Paragraph 1, General.

Figure 1 (Sheet 2) GMDC-02K1003
Revision E

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page A22 SCI 27-2 - MD-10 HORIZONTAL STABILIZER ACTUATOR LUBRICATION (cont’d)

6. Is test equipment needed?

No test equipment is required.

7. What is pass/fail criteria?

This SCI provides a lubrication servicing pr ocedure; pass/fail cr iteria do not apply.

8. What is SCI interval?

The horizontal stabilizer actuator lubrication procedure shall be pe rformed at intervals not to exceed 1,800 flight hours. EMDC-02K1003
Revision G

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page A23 SCI 27-3 - MD-11 HORIZONTAL STABILIZER ACTUATOR LUBRICATION

1. What model does this SCI apply to?

MD-11 series aircraft

2. What part or LRU is being checked?

Horizontal stabilizer actuator

3. What failure mode is being looked for?

A check for a failure mode does not apply. Th is SCI provides a lubrication procedure for
the horizontal stabilizer actuator.

4. How is it found?

Not applicable

5. What tasks are to be performed?

Perform the following horizontal stabilizer actuator lubrication procedure:

1. General

A. This procedure has the instructions for lubricating the horizontal stabilizer actuator.

B. The grease removal and lubrication procedur es must be done together and in the sequence listed.

C. The use of clean, dry rags instead of solvent to remove grease from the acme screws and nuts is recommended to prevent solven t contamination in the acme nuts.

D. When lubricating vented joints (grease can fr eely and visibly flow out), apply grease to the fittings until only new grease shows from the joints.

E. Do not intermix different grease specifications or different grease brands in the same specification.

F. When changing from one grease specification or brand to another, do the procedure in MD-11 AMM Chapter 12-00-00 (C HANGE THE APPROVED GREASE SPECIFICATION OR BRAND, TASK 12-00-00-617-801). GMDC-02K1003
Revision G

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page A24 SCI 27-3 - MD-11 HORIZONTAL STABILIZER ACTUATOR LUBRICATION (cont’d)

G. The referenced TASK numbers apply to the MD-11 AMM.

2. LUBRICATION OF THE HORIZONTAL STABILIZER ACTUATOR

A. Fixtures, Tools, Test and Support Equipment

(1) Fixtures, Tools, Test and Support Equipment

NOTE : Equivalent replacements are permitted for the items that follow.

Table 1

REFERENCE DESIGNATION Not specified Grease gun Not specified Brush Not specified Maintenance platform, 10-15 ft (3-5 m) high

B. Consumable Materials

(1) Consumable Materials

NOTE : Equivalent replacements are permitted for the items that follow.

NOTE : It is possible that some materials in the Consumable Materials chart
cannot be used for some or all of th eir necessary applications. Before you use the materials, make sure the types, quantities, and applications of the materials necessary are legally perm itted in your location. All persons must obey all applicable federal, st ate, local, and provincial laws and regulations when it is necessary to work with these materials.

Table 2

REFERENCE DESIGNATION

MIL-PRF-81322 (DPM 5348) Grease, wide temperature range (WTR)

DPM 5850 Grease, special purpose, Aeroshell 14 (**)

BMS 3-33 Grease, general purpose (GPG) GMDC-02K1003
Revision G

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page A25 SCI 27-3 - MD-11 HORIZONTAL STABILIZER ACTUATOR LUBRICATION (cont’d)

C. References

Reference Title

12-00-00-617-801

27-40-00-860-801 CHANGE THE APPROVED GREASE
SPECIFICATION OR BRAND (MD-11 AMM, P/B 201)

OPERATION OF THE HORIZONTAL STABILIZER (MD-11 AMM, P/B 201)

D. Access Panel

Number Name/Location
311AB AFT FUSELAGE

E. Job Set-up - Horizontal Stabi lizer Actuator Lubrication

(1) Open this access panel:

Number Name/Location

311AB AFT FUSELAGE

F. Procedure - Horizontal Stabi lizer Actuator Lubrication

WARNING : USE THE HAZARDOUS MATERIA L WARNINGS GIVEN BELOW
FOR THE STEPS THAT FOLLOW.

THE HAZARDOUS MATERIAL WARN INGS ARE LISTED AFTER
THE INTRODUCTION SECTION IN THE FRONT OF THE MD-11
AMM. Hazardous Material Warnings

HAZMAT 1013, LUBRICANT/GRE ASE (DPM 5348/317/326) HAZMAT 1000, REFER TO MSDS HAZMAT 1741, BMS 3-33 G

GMDC-02K1003
Revision G

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page A26 SCI 27-3 - MD-11 HORIZONTAL STABILIZER ACTUATOR LUBRICATION (cont’d)

NOTE : A number identifies the lubrication points . A lubrication symbol and a two or three letter key at each point shows the lubricant and equipment used.

Table 3

ITEM NO. ITEM DESCRIPTIO N LUBE TYPE APPLICATION NO. OF
FITTINGS
OR AREAS

1 Acme screw ** (DPM 5850) Brush 1

2 Acme nut ** (DPM 5850) Grease gun 1

3 Sprocket bearing WTR(MIL-PRF81322) Grease gun 2

NOTE : The number of fittings or areas is for one side only. The opposite side is the

same.

NOTE : WTR or BMS 3-33 grease may be used as an alternative to DPM 5850 (**) grease for items 1 and 2. BMS 3-33 grease may be used as an alternative to WTR grease for item 3. Obey the grease intermix and changing precautions in Paragraph 1, General.

(1) Remove the used grease from the horizontal stabilizer actuators. (Figure 1)

(a) Move the horizontal stabilizer to th e full aircraft nose down (AND) position. (OPERATION OF THE HORIZONTAL STABILIZER, TASK 27-40-00-860- 801)

WARNING : TAG AND USE SAFETY CLI PS TO SAFETY THE CIRCUIT
BREAKERS. IF THE CIRCU IT BREAKERS ARE NOT OPENED, TAGGED, AND SAFETIED, INJURY TO PERSONS AND DAMAGE TO EQUIPMENT CAN OCCUR.

(b) Open these circuit breakers and install safety tags:

AVIONICS, FLIGHT CONTROL DC BUS 1

Row Col Number Name

C 8 B1-693 AUTO PITCH TRIM 1 GMDC-02K1003
Revision E

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page A27 SCI 27-3 - MD-11 HORIZONTAL STABILIZER ACTUATOR LUBRICATION (cont’d)

AVIONICS, MISC DC BUS 2

Row Col Number Name

F 3 B1-507 PRIMARY HORIZ STAB TRIM

OVERHEAD, RIGHT EMER DC BUS

Row Col Number Name

E 26 B1-694 AUTO PITCH TRIM 2

(c) Put a “DO NOT OPERATE” tag on the hor izontal stabilizer suitcase handles on the control pedestal.

(d) Apply grease to the grease fittings on the left and right acme nuts.

(e) Clean the exposed threads on the left a nd right acme screws above the acme nuts and the tops of the two acme nuts w ith clean, dry rags to remove as much grease as possible.

(f) Remove the safety tag and close this circuit breaker:

AVIONICS, MISC DC BUS 2

Row Col Number Name

F 3 B1-507 PRIMARY HORIZ STAB TRIM

(g) Move the horizontal stabilizer to th e full aircraft nos e up (ANU) position. (OPERATION OF THE HORIZONTAL STABILIZER, TASK 27-40-00-860- 801)

WARNING : TAG AND USE A SAFETY CLIP TO SAFETY THE CIRCUIT BREAKER. IF THE CIRCUIT BREAKER IS NOT OPENED, TAGGED, AND SAFETIED, INJURY TO PERSONS AND DAMAGE TO EQUIPM ENT CAN OCCUR.

(h) Open this circuit breaker and install a safety tag:

AVIONICS, MISC DC BUS 2

Row Col Number Name

F 3 B1-507 PRIMARY HORIZ STAB TRIM
SCI 27-3 - MD-11 HORIZONTAL STABILIZER ACTUATOR LUBRICATION EMDC-02K1003
Revision E

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page A28 (cont’d)

(i) Clean the exposed threads on the left and right acme screws below the acme
nuts and the bottoms of the two acme nuts with clean, dry rags to remove as much grease as possible.

(2) Lubricate the horizontal stabiliz er actuators. (Figure 1)

(a) Put a layer of grease around the complete circumference of the exposed threads on the left and right acme screws. Make sure that the grease is liberally applied to the threads, including the fl anks and bottom of each thread valley.

(b) Remove the safety tag and close this circuit breaker:

AVIONICS, MISC DC BUS 2

Row Col Number Name

F 3 B1-507 PRIMARY HORIZ STAB TRIM

(c) Move the horizontal stabilizer to the full AND position. (OPERATION OF
THE HORIZONTAL STABILIZER , TASK 27-40-00-860-801)

WARNING : TAG AND USE A SAFETY CLIP TO SAFETY THE CIRCUIT BREAKER. IF THE CIRCUIT BREAKER IS NOT OPENED, TAGGED, AND SAFETIED, INJURY TO PERSONS AND DAMAGE TO EQUIPM ENT CAN OCCUR.

(d) Open this circuit breaker and install a safety tag:

AVIONICS, MISC DC BUS 2

Row Col Number Name

F 3 B1-507 PRIMARY HORIZ STAB TRIM

(e) Put a layer of grease around the complete circumference of the exposed threads
on the two acme screws. Make sure that the grease is liberally applied to the threads, including the flanks and bottom of each thread valley.

(f) Apply grease to the left and right acme nuts.

(g) Apply grease to the left a nd right sprocket bearings. EMDC-02K1003
Revision E

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page A29 SCI 27-3 - MD-11 HORIZONTAL STABILIZER ACTUATOR LUBRICATION (cont’d)

(h) Remove the safety tag and close this circuit breaker:

AVIONICS, MISC DC BUS 2

Row Col Number Name

F 3 B1-507 PRIMARY HORIZ STAB TRIM

(i) Move the horizontal stabilizer to distribute the grease equally in the actuator. (OPERATION OF THE HORIZONTAL STABILIZER, TASK 27-40-00-860- 801)

1) Move the horizontal stabilizer to the full ANU and then the full AND positions.

2) Move the horizontal stabilizer to the zero (neu tral) position.

WARNING : TAG AND USE A SAFETY CLIP TO SAFETY THE CIRCUIT BREAKER. IF THE CIRCUIT BREAKER IS NOT OPENED, TAGGED, AND SAFETIED, INJURY TO PERSONS AND DAMAGE TO EQUIPM ENT CAN OCCUR.

(j) Open this circuit breaker and install a safety tag:

AVIONICS, MISC DC BUS 2

Row Col Number Name

F 3 B1-507 PRIMARY HORIZ STAB TRIM

(k) Remove the grease that is not necessary from the left and right actuators. Do not remove grease from the working surfaces.

(l) Clean the structural areas around the actua tors. Remove any grease that is not necessary and any loose mate rial (sand, dirt, drill shavings, etc.) that could
contaminate the actuators.

G. Job Close-up - Horizontal St abilizer Actuator Lubrication

(1) Remove all the tools and equipment from th e work area. Make sure the area is
clean. EMDC-02K1003
Revision E

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page A30 SCI 27-3 - MD-11 HORIZONTAL STABILIZER ACTUATOR LUBRICATION (cont’d)

(2) Close this access panel:

Number Name/Location

311AB AFT FUSELAGE

(3) Remove the safety tags and close these circuit breakers:

AVIONICS, FLIGHT CONTROL DC BUS 1

Row Col Number Name

C 8 B1-693 AUTO PITCH TRIM 1

AVIONICS, MISC DC BUS 2

Row Col Number Name

F 3 B1-507 PRIMARY HORIZ STAB TRIM

OVERHEAD, RIGHT EMER DC BUS

Row Col Number Name

E 26 B1-694 AUTO PITCH TRIM 2

(4) Remove the “DO NOT OPERATE” tag from the horizontal stabilizer suitcase handles on the control pedestal. EMDC-02K1003
Revision E

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page A31 SCI 27-3 - MD-11 HORIZONTAL STABILIZER ACTUATOR LUBRICATION (cont’d)

Figure 1 EMDC-02K1003
Revision E

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page A32 SCI 27-3 - MD-11 HORIZONTAL STABILIZER ACTUATOR LUBRICATION (cont’d)

6. Is test equipment needed?

No test equipment is required.

7. What is pass/fail criteria?

This SCI provides a lubrication servicing pr ocedure; pass/fail cr iteria do not apply.

8. What is SCI interval?

The horizontal stabilizer actuator lubrication procedure shall be pe rformed at intervals not to exceed 1,800 flight hours. EMDC-02K1003
Revision E

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page A33 SCI 27-4 - DC-10 HORIZONTAL STABILIZER ACTUATOR WEAR CHECK (AIRCRAFT WITH TWO DRIVE CHAINS)

1. What model does this SCI apply to?

DC-10 series aircraft with two horizontal stab ilizer actuator drive ch ains (service bulletin DC10-27-162 incorporated)

2. What part or LRU is being checked?

Horizontal stabilizer actuator

3. What failure mode is being looked for?

This SCI checks for wear rather than a failure mode. A wear check is being performed to
make certain that actuator and actuator-to-hor izontal stabilizer attach point wear has not
exceeded the service limits.

4. How is it found?

Check the actuator and acme screw attach point for wear as de tailed in number 5 below.

5. What tasks are to be performed?

Perform the following horizontal stabilizer actuator wear check procedure:

1. General

A. The left and right horizontal stabilizer actuators are located forward of the horizontal
stabilizer constant section.

B. Access to horizontal stabilizer actuators is through access door 311AB, zone 311, in the lower aft fuselage compartment.

2. Equipment and Materials

NOTE : Equivalent substitutes may be used instead of the following listed items:

Name and Number

Gage set (DZZ7121-501) EMDC-02K1003
Revision E

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page A34 SCI 27-4 - DC-10 HORIZONTAL STABILIZER ACTUATOR WEAR CHECK (AIRCRAFT WITH TWO DRIVE CHAINS) (cont’d)

Torque Wrench (200 foot-pounds capacity)

Torque Wrench(30 to 60 inchpounds range)

Force indicator (20 to 25 pounds range)

Quill Shaft
Installation tool (DZZ7291-1)

Tester, drive
chain tension (DZZ7293-1)

3. Check Horizontal Stabilizer Actuator Wear Tolerances

WARNING : BEFORE PRESSURIZING HYDRAULIC SYSTEMS, MAKE CERTAIN
THAT LANDING GEAR GROUND LOCKPINS ARE INSTALLED AND
THAT APPLICABLE CONTROLS ARE IN CORRECT POSITION TO
PREVENT INADVERTENT OPERAT ION OF LANDING GEAR AND
FLIGHT CONTROL SYSTEMS.

A. Pressurize hydraulic systems 1 and 3 (Ref. DC-10 MM 29-00-00, Page 201).

WARNING : BEFORE MOVING HORIZONTAL STABILIZER TRIM CONTROLS,
MAKE CERTAIN THAT AREAS AROUND HORIZONTAL
STABILIZER AND ELEVATORS ARE CLEAR OF PERSONNEL AND EQUIPMENT AND THAT UPPER TAIL CONE DOORS ARE CLOSED.

B. Using the horizontal stabilizer trim handles on the control pede stal, move the stabilizer to the zero (neutral) position. EMDC-02K1003
Revision E

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page A35 SCI 27-4 - DC-10 HORIZONTAL STABILIZER ACTUATOR WEAR CHECK (AIRCRAFT WITH TWO DRIVE CHAINS) (cont’d)

C. Manually actuate the primary trim control valv es located on the aft pressure bulkhead to align both actuators as show n in Figure 1, Views A and B.

NOTE : This procedure indexes the horizontal stab ilizer actuators correctly to ensure the proper re-installation of the drive chains.

D. Shut off the hydraulic pressure source.

E. Make sure that all three hydraulic systems are depressu rized (Ref. DC-10 MM 29-00-00, Page 201).

F. Open and tag the following circuit breakers:

WARNING : TAG AND SAFETY CIRCUIT BREAKERS.

Circuit Breaker Panel Location Panel Area

AUTO PITCH TRIM A Avionics DC BUS 1

AUTO PITCH TRIM B Avionics DC BUS 3

HOR STAB ALTN TRIM CONT Avionics DC BUS 3

PRIMARY HORIZ STAB TRIM Upper Main DC BUS 2

G. Put a “DO NOT OPERATE” tag on the horizontal stabilizer trim handles on the control pedestal.

CAUTION : QUILL SHAFT WILL DROP IF IT IS NOT SUPPORTED WHEN CROSS
BOLT IS REMOVED.

H. Remove the cross bolt at the bottom of quill sh aft and carefully remove the quill shaft.

I. Check the first actuator; either the left or ri ght actuator may be checked first (Ref. Figure 2).

(1) Loosen the drive chain on the actuator not being checked.

NOTE : This procedure should provide enough slack in the drive chain to remove the chain from the actuator sprock et without disconnecting the chain
master link. EMDC-02K1003
Revision E

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page A36 SCI 27-4 - DC-10 HORIZONTAL STABILIZER ACTUATOR WEAR CHECK (AIRCRAFT WITH TWO DRIVE CHAINS) (cont’d)

(a) Loosen and disconnect the turnbuckle at the drive chain id ler sprocket to relieve the tension on the drive chain, and rotate the idler sprocket clear of the
chain.

(b) Remove the drive chain from the acme nut sprocket.

(2) Install the gauge set torque adapter on the actuator not being checked.

(3) Clean any grease or loose material from th e surfaces of the horizontal stabilizer fitting and the acme nut hub where the indi cator probes will touch on the actuator being checked.

(4) Install the gauge set indicators and re straint on the actuato r being checked.

(a) Position the probe from indicator (A) against the surface of the acme nut hub. Move the indicator toward the hub until the probe is compressed approximately one half travel and th e indicator needle is pointed up.

(b) Position the probe from indicator (B ) against the uppe r surface of the horizontal stabilizer fitting (acme scre w attach point). Move the indicator toward the fitting until the probe is co mpressed approximately one half travel and the indicator needle is pointed up.

(c) Install the actuator restraint on the acm e nut hub lugs and clamp the end of the restraint to the adjacent structural beam.

(5) Using the torque adapter, rotate the acme nut hub back and forth to relieve the tension on the actuator, and then rotate the acme nut hub in a clockwise direction until the torque wrench indicates 200 ft-lbs.

NOTE : The torque shall be 200 ft-lbs, as appl ied to the actuator screw. With the torque adapter installed, the torque wrench reading shall be 200 ft-lbs when the wrench handle is parallel to the acme nut hub lugs. The torque wrench reading shall be 155 ft-lbs when the wrench handle is perpendicular to the nut hub lugs.

(6) Set both indicator dials to the zero position.

(7) Rotate the acme nut hub in a countercloc kwise direction until the torque wrench
indicates 200 ft-lbs. EMDC-02K1003
Revision E

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page A37 SCI 27-4 - DC-10 HORIZONTAL STABILIZER ACTUATOR WEAR CHECK (AIRCRAFT WITH TWO DRIVE CHAINS) (cont’d)

(8) Record the amount of indicator needle movement on each indicator.

NOTE : The two indicator needles will move in opposite directions during the
check. The amount of movement for th e needle that moves in the positive direction can be read directly from the indicator scale. The amount of
movement for the needle that moves in the negative direction must be
calculated.

(9) Rotate the acme nut hub in a clockwise di rection until the torque wrench indicates 200 ft-lbs, and check that both indicators have returned to the zero reading.

(10) Reset the indicators to read zero, if necessary.

(11) Repeat steps (7) through (10) until three consecutive readings are obtained on each indicator that are no more than 0.003 inch ap art, with a return to the zero reading
each time.

(12) Using the highest of the three readings obt ained from each indicator in step (11), do any of the following work items that apply.

(a) If the nut-to-screw reading (indicator A) is more than 0.068 inch, replace the

actuator.

(b) If the screw-to-stabilizer-connection read ing (indicator B) is more than 0.023 inch, repair the connection as necessary.

(c) If the combination of readings (indic ators A and B) is more than 0.080 inch, replace the actuator and/or repa ir the connection as necessary.

J. Perform steps I.(1) through I.(12) on the second actuator being checked.

K. Remove the gauge set indicators, restrain t, and torque adaptor from actuators.

L. Make certain that both actuators are ali gned and positioned as shown in Figure 1, Views
A and B

M. Place the drive chains on the acme nut sprockets.

(1) Position the master links at Po ints B as shown in Figure 1. EMDC-02K1003
Revision E

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page A38 SCI 27-4 - DC-10 HORIZONTAL STABILIZER ACTUATOR WEAR CHECK (AIRCRAFT WITH TWO DRIVE CHAINS) (cont’d)

(2) Make certain that the slack is removed fr om the sections of the chains located on the forward side of the acme nut sprockets.

CAUTION : DO NOT EXCEED 60 INCH-POUNDS OF TORQUE ON IDLER
SPROCKET TURNBUCKLES.

(3) Connect the turnbuckles at the idler spro ckets, and tighten each turnbuckle to a torque of 30 to 60 inch-pounds. While tight ening the turnbuckles, check to see that the acme nut sprockets are free to rotate so that the chain tensions can equalize.

(4) Safety the idler sprocket turnbuckles with clips.

N. Check the tension of each dr ive chain (Ref. DC-10 MM 27-44 -01, paragraph 3.B., Install Acme Screw Actuator).

O. Check the dimensions of each actuator (Ref. DC-10 MM 27-44-01, paragraph 3.B., Install Acme Screw Actuator).

P. Install the quill shaft (Ref . DC-10 MM 27-44-01, paragraph 3.B., Install Acme Screw Actuator).

Q. Lubricate the drive chains (R ef. DC-10 MM 12-21-03, figure 305).

R. Remove the safety tags and clos e the following circuit breakers:

Circuit Breaker Panel Location Panel Area

AUTO PITCH TRIM A Avionics DC BUS 1

AUTO PITCH TRIM B Avionics DC BUS 3

HOR STAB ALTN TRIM CONT Avionics DC BUS 3

PRIMARY HORIZ STAB TRIM Upper Main DC BUS 2

S. Remove the “DO NOT OPERATE” tag from the horizontal stab ilizer trim handles on the control pedestal. EMDC-02K1003
Revision E

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page A39 SCI 27-4 - DC-10 HORIZONTAL STABILIZER ACTUATOR WEAR CHECK (AIRCRAFT WITH TWO DRIVE CHAINS) (cont’d)

WARNING : BEFORE PRESSURIZING HYDRAULIC SYSTEMS, MAKE CERTAIN
THAT LANDING GEAR GROUND LOCKPINS ARE INSTALLED AND
THAT APPLICABLE CONTROLS ARE IN CORRECT POSITION TO
PREVENT INADVERTENT OPERAT ION OF LANDING GEAR AND
FLIGHT CONTROL SYSTEMS.

T. Pressurize hydraulic systems 1 and 3 (Ref. DC-10 MM 29-00-00, Page 201).

WARNING : BEFORE MOVING TRIM CONTROLS, MAKE CERTAIN THAT AREAS
AROUND HORIZONTAL STABILI ZER AND ELEVATORS ARE CLEAR OF PERSONNEL AND EQUIPMENT AND THAT UPPER TAIL CONE
DOORS ARE CLOSED.

U. Using the horizontal stabilizer trim handles on the control pedestal , move the horizontal stabilizer to the full aircraft nose up and full aircraft nose down positions, and check the actuators for smooth operation without binding.

V. Move the horizontal stabilizer to the zero (neu tral) position.

W. Shut off the hydraulic pressure source.

X. Lubricate the horizontal stabilizer actu ators (Ref. SCI 27-1 - DC-10 HORIZONTAL STABILIZER ACTUATOR LUBRICATION). EMDC-02K1003
Revision E

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page A40 SCI 27-4 - DC-10 HORIZONTAL STABILIZER ACTUATOR WEAR CHECK (AIRCRAFT WITH TWO DRIVE CHAINS) (cont’d)

Figure 1 E DIMENSIONS C & D EQUAL WITHIN 0.15 INCH

GREASE FITTING 

# I

ON TOP OF NUT (TYPICAL) •

HOISTING LUG CIRCULAR !DENTATION INDEX MARKS (BOTH ACTUATOR) 

# 0

FWD 1

# ~ LOCATE MASTER LINK POINT IN THIS AREA B

VIEW A LOOKING DOWN

r,..... --'1, I

# ()~OCRONST\ 

# 0

A A

# of~

30.49 ± 0.20 INCHES

VIEW B

# ~~t

I I -----.1

LH ACTUATOR SECTION A·A

VIEW LOOKING DOWN 30.49 ± 0.20 INCHES

RH ACTUATOR D

INDEXED TOOTH (BOTH ACTUATORS)

CA2·27-558DMDC-02K1003
Revision E

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page A41 SCI 27-4 - DC-10 HORIZONTAL STABILIZER ACTUATOR WEAR CHECK (AIRCRAFT WITH TWO DRIVE CHAINS) (cont’d)

Figure 2 E

RIGHT AC**ACTUATO~E** SCREW

NOTE:

SHOWN WITH TO CHECK**LEGlf~cSTET** INSTALLED UATOR

CA2-27-560MDC-02K1003
Revision E

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page A42 SCI 27-4 - DC-10 HORIZONTAL STABILIZER ACTUATOR WEAR CHECK (AIRCRAFT WITH TWO DRIVE CHAINS) (cont’d)

6. Is test equipment needed?

A list of the required equipment and materi als can be found in paragraph 2. of the actuator wear check procedure in number 5 above.

7. What is pass/fail criteria?

The pass/fail criteria can be found in paragr aph 3.I.(12) of the actuator wear check procedure in number 5 above.

8. What is SCI interval?

The actuator wear check shall be performed at intervals not to exceed 15,000 flight hours. EMDC-02K1003
Revision E

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page A43 SCI 27-5 - DC-10 HORIZONTAL STABILIZER ACTUATOR WEAR CHECK (AIRCRAFT WITH FOUR DRIVE CHAINS)

1. What model does this SCI apply to?

DC-10 series aircraft with four horizontal stabilizer actuator drive chains (service bulletin DC10-27-162 not incorporated)

2. What part or LRU is being checked?

Horizontal stabilizer actuator

3. What failure mode is being looked for?

This SCI checks for wear rather than a failure mode. A wear check is being performed to
make certain that actuator and actuator-to-hor izontal stabilizer attach point wear has not
exceeded the service limits.

4. How is it found?

Check the actuator and acme screw attach point for wear as de tailed in number 5 below.

5. What tasks are to be performed?

Perform the following horizontal stabilizer actuator wear check procedure:

1. General

A. The left and right horizontal stabilizer actuators are located forward of the horizontal
stabilizer constant section.

B. Access to the horizontal stab ilizer actuators is through access door 311AB, zone 311, in the lower aft fuselage compartment.

2. Equipment and Materials

NOTE : Equivalent substitutes may be used instead of the following listed items:

Name and Number

Gage set (DZZ7121-501) EMDC-02K1003
Revision E

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page A44 SCI 27-5 - DC-10 HORIZONTAL STABILIZER ACTUATOR WEAR CHECK (AIRCRAFT WITH FOUR DRIVE CHAINS) (cont’d)

Torque Wrench (200 foot-pounds capacity)

Torque Wrench(30 to 60 inchpounds range)

Force indicator (20 to 25 pounds range)

Tester, drive
chain tension (DZZ7293-1)

3. Check Horizontal Stabilizer Actuator Wear Tolerances

WARNING : BEFORE PRESSURIZING HYDRAULIC SYSTEMS, MAKE CERTAIN
THAT LANDING GEAR GROUND LOCKPINS ARE INSTALLED AND
THAT APPLICABLE CONTROLS ARE IN CORRECT POSITION TO
PREVENT INADVERTENT OPERAT ION OF LANDING GEAR AND
FLIGHT CONTROL SYSTEMS.

A. Pressurize hydraulic systems 1 and 3 (Ref. DC-10 MM 29-00-00, Page 201).

WARNING : BEFORE MOVING HORIZONTAL STABILIZER TRIM CONTROLS,
MAKE CERTAIN THAT AREAS AROUND HORIZONTAL STABILIZER
AND ELEVATORS ARE CLEAR OF PERSONNEL AND EQUIPMENT
AND THAT UPPER TAIL CONE DOORS ARE CLOSED.

B. Using the horizontal stabilizer trim handles on the control pede stal, move the stabilizer to the zero (neutral) position.

C. Manually actuate the primary trim control valv es located on the aft pressure bulkhead to align both actuators as show n in Figure 1, Views A and B.

NOTE : This procedure indexes the horizontal stab ilizer actuators correctly to ensure the proper re-installation of the drive chains. EMDC-02K1003
Revision E

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page A45 SCI 27-5 - DC-10 HORIZONTAL STABILIZER ACTUATOR WEAR CHECK (AIRCRAFT WITH FOUR DRIVE CHAINS) (cont’d)

D. Shut off the hydraulic pressure source.

E. Make sure that all three hydraulic systems are depressu rized (Ref. DC-10 MM 29-00-00, Page 201).

F. Open and tag the following circuit breakers:

WARNING : TAG AND SAFETY CIRCUIT BREAKERS.

Circuit Breaker Panel Location Panel Area

AUTO PITCH TRIM A Avionics DC BUS 1

AUTO PITCH TRIM B Avionics DC BUS 3

HOR STAB ALTN TRIM CONT Avionics DC BUS 3

PRIMARY HORIZ STAB TRIM Upper Main DC BUS 2

G. Put a “DO NOT OPERATE” tag on the horizontal stabilizer trim handles on the control pedestal.

H. Check the first actuator; either the left or ri ght actuator may be checked first (Ref. Figure 2).

(1) Loosen the drive chains on th e actuator not being checked.

NOTE : This procedure should provide enough sl ack in the drive chains to remove
the chains from the actuator acme nut sprockets without disconnecting the
chain master links.

(a) Loosen and disconnect the turnbuckles at the drive chain idler sprockets to relieve the tension on the drive chains, a nd rotate the idler sprockets clear of
the chains.

(b) Remove the drive chains from the acme nut sprockets.

(2) Install the gauge set torque adapter on the actuator not being checked.

(3) Clean any grease or loose material from th e surfaces of the horizontal stabilizer fitting and the acme nut hub where the indi cator probes will touch on the actuator being checked. EMDC-02K1003
Revision E

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page A46 SCI 27-5 - DC-10 HORIZONTAL STABILIZER ACTUATOR WEAR CHECK (AIRCRAFT WITH FOUR DRIVE CHAINS) (cont’d)

(4) Install the gauge set indicators and re straint on the actua tor being checked.

(a) Position the probe from indicator (A) against the surface of the acme nut hub. Move the indicator toward the hub until the probe is compressed approximately one half travel and th e indicator needle is pointed up.

(b) Position the probe from indicator (B ) against the uppe r surface of the horizontal stabilizer fitting (acme scre w attach point). Move the indicator toward the fitting until the probe is co mpressed approximately one half travel and the indicator needle is pointed up.

(c) Install the actuator restraint on the acm e nut hub lugs and clamp the end of the restraint to the adjacent structural beam.

(5) Using the torque adapter, rotate the acme nut hub back and forth to relieve the tension on the actuator, and then rotate the acme nut hub in a clockwise direction until the torque wrench indicates 200 ft-lbs.

NOTE : The torque shall be 200 ft-lbs, as appl ied to the actuator screw. With the torque adapter installed, the torque wrench reading shall be 200 ft-lbs when the wrench handle is parallel to the acme nut hub lugs. The torque wrench reading shall be 155 ft-lbs when the wrench handle is perpendicular to the nut hub lugs.

(6) Set both indicator dials to the zero position.

(7) Rotate the acme nut hub in a countercloc kwise direction until the torque wrench
indicates 200 ft-lbs.

(8) Record the amount of indicator needle movement on each indicator.

NOTE : The two indicator needles will move in opposite directions during the
check. The amount of movement for th e needle that moves in the positive direction can be read directly from the indicator scale. The amount of
movement for the needle that moves in the negative direction must be
calculated.

(9) Rotate the acme nut hub in a clockwise di rection until the torque wrench indicates 200 ft-lbs, and check that both indicators have returned to the zero reading.

(10) Reset the indicators to read zero, if necessary. EMDC-02K1003
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BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page A47 SCI 27-5 - DC-10 HORIZONTAL STABILIZER ACTUATOR WEAR CHECK (AIRCRAFT WITH FOUR DRIVE CHAINS) (cont’d)

(11) Repeat steps (7) through (10) until three consecutive readings are obtained on each indicator that are no more than 0.003 inch ap art, with a return to the zero reading
each time.

(12) Using the highest of the three readings obt ained from each indicator in step (11), do any of the following work items that apply.

(a) If the nut-to-screw reading (indicator A) is more than 0.068 inch, replace the

actuator.

(b) If the screw-to-stabilizer-connection read ing (indicator B) is more than 0.023 inch, repair the connection as necessary.

(c) If the combination of readings (indic ators A and B) is more than 0.080 inch, replace the actuator and/or repa ir the connection as necessary.

I. Perform steps H.(1) through H.(12) on the second actuator being checked.

J. Remove the gauge set indicators, restrain t, and torque adaptor from actuators.

K. Make certain that both actuators are ali gned and positioned as shown in Figure 1, Views
A and B

L. Place the drive chains on the acme nut sprockets.

(1) Position the master links at Po ints B as shown in Figure 1.

(2) Make certain that the slack is removed fr om the sections of the chains located on the forward side of the acme nut sprockets.

CAUTION : DO NOT EXCEED 60 INCH-POUNDS OF TORQUE ON IDLER
SPROCKET TURNBUCKLES.

(3) Connect the turnbuckles at the idler spro ckets, and tighten each turnbuckle to a torque of 30 to 60 inch-pounds. While tight ening the turnbuckles, check to see that the acme nut sprockets are free to rotate so that the chain tensions can equalize.

(4) Safety the idler sprocket turnbuckles with clips. EMDC-02K1003
Revision E

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page A48 SCI 27-5 - DC-10 HORIZONTAL STABILIZER ACTUATOR WEAR CHECK (AIRCRAFT WITH FOUR DRIVE CHAINS) (cont’d)

M. Check the tension of each dr ive chain (Ref. DC-10 MM 27-44 -01, paragraph 3.B., Install Acme Screw Actuator).

N. Check the dimensions of each actuator (Ref. DC-10 MM 27-44-01, paragraph Install Acme Screw Actuator).

O. Lubricate the drive chains (R ef. DC-10 MM 12-21-03, figure 305).

P. Remove the safety tags and clos e the following circuit breakers:

Circuit Breaker Panel Location Panel Area

AUTO PITCH TRIM A Avionics DC BUS 1

AUTO PITCH TRIM B Avionics DC BUS 3

HOR STAB ALTN TRIM CONT Avionics DC BUS 3

PRIMARY HORIZ STAB TRIM Upper Main DC BUS 2

Q. Remove the “DO NOT OPERATE” tag from the horizontal stab ilizer trim handles on the control pedestal.

WARNING : BEFORE PRESSURIZING HYDRAULIC SYSTEMS, MAKE CERTAIN
THAT LANDING GEAR GROUND LOCKPINS ARE INSTALLED AND
THAT APPLICABLE CONTROLS ARE IN CORRECT POSITION TO
PREVENT INADVERTENT OPERAT ION OF LANDING GEAR AND
FLIGHT CONTROL SYSTEMS.

R. Pressurize hydraulic systems 1 and 3 (Ref. DC-10 MM 29-00-00, Page 201).

WARNING : BEFORE MOVING TRIM CONTROLS, MAKE CERTAIN THAT AREAS
AROUND HORIZONTAL STABILI ZER AND ELEVATORS ARE CLEAR OF PERSONNEL AND EQUIPMENT AND THAT UPPER TAIL CONE
DOORS ARE CLOSED.

S. Using the horizontal stabilizer trim handles on the control pedest al, move horizontal stabilizer to the full aircraft nose up and full aircraft nose down positions, and check the actuators for smooth operation without binding.

T. Move the horizontal stabilizer to the zero (neu tral) position.

U. Shut off the hydraulic pressure source. EMDC-02K1003
Revision E

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page A49 SCI 27-5 - DC-10 HORIZONTAL STABILIZER ACTUATOR WEAR CHECK (AIRCRAFT WITH FOUR DRIVE CHAINS) (cont’d)

V. Lubricate the horizontal stabilizer actu ators (Ref. SCI 27-1 - DC-10 HORIZONTAL STABILIZER ACTUATOR LUBRICATION). EMDC-02K1003
Revision E

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page A50 SCI 27-5 - DC-10 HORIZONTAL STABILIZER ACTUATOR WEAR CHECK (AIRCRAFT WITH FOUR DRIVE CHAINS) (cont’d)

Figure 1 E DIMENSIONS A & B EQUAL WITHIN 0.15 INCH

A

NUT STOP

HOISTING LUG

NOTE:
WHEN MAKING AN INDEX CHECK, ASSUMING THE LEFT HAND ACTUATOR NUT LUGS ARE EQUAL, THERE CAN BE NO PRACTICAL IMPROVEMENT MADE IN INDEXING, UNLESS MISALIGNMENT OF RIGHT HAND ACTUATOR NUT LUGS ARE GREATER THAN 1/2 INCH.

30.49 +0.20 INCHES (2 PLACES)

VIEW B 

# I

B AFT PRESSURE BULKHEAD



### c DIMENSIONS C & D EQUIAL WITHIN 0.15 INCH

D

LOCATE MASTER UNK

# ~ IN THIS AREA B

VIEW A

VIEW LOOKING DOWN

NOTE: THIS PROVIDES GROSS ADJUSTMENT OF ACTUATORS. FOR FINE ADJUSTMENT SEE VIEW A 

### 0
FWD

SCREW**STOP~-** 

# oO

FWD INDEXED TOOTH (BOTH ACTUATORS)

SECTION B-B

VIEW LOOKING DOWN

DC-1 0 WEAR CHECK 4 CHAIN F1MDC-02K1003
Revision E

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page A51 SCI 27-5 - DC-10 HORIZONTAL STABILIZER ACTUATOR WEAR CHECK (AIRCRAFT WITH FOUR DRIVE CHAINS) (cont’d)

Figure 2 E

INDICATOR B (MEASURES TOLERANCE BETWEEN ACME SCREW**~~~B~~r~~~NTAL** POINT J ATTACH

INDICATOR A <MEASURES TOLERANCE BETWEEN ACME SCREW**~~g ~CME**  NUT RIGHT AC**ACTUATO_~E** SCREW

CHAIN DRIVE TURNBUCKLES

CA2-27-299AMDC-02K1003
Revision E

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page A52 SCI 27-5 - DC-10 HORIZONTAL STABILIZER ACTUATOR WEAR CHECK (AIRCRAFT WITH FOUR DRIVE CHAINS) (cont’d)

6. Is test equipment needed?

A list of the required equipment and materi als can be found in paragraph 2. of the actuator wear check procedure in number 5 above.

7. What is pass/fail criteria?

The pass/fail criteria can be found in paragr aph 3.H.(12) of the actuator wear check procedure in number 5 above.

8. What is SCI interval?

The actuator wear check shall be performed at intervals not to exceed 15,000 flight hours. EMDC-02K1003
Revision E

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page A53 SCI 27-6 - MD-10 HORIZONTAL STAB ILIZER ACTUATOR WEAR CHECK (AIRCRAFT WITH TWO DRIVE CHAINS)

1. What model does this SCI apply to?

MD-10 series aircraft with two horizontal stab ilizer actuator drive ch ains (service bulletin DC10-27-162 incorporated)

2. What part or LRU is being checked?

Horizontal stabilizer actuator

3. What failure mode is being looked for?

This SCI checks for wear rather than a failure mode. A wear check is being performed to
make certain that actuator and actuator-to-hor izontal stabilizer attach point wear has not
exceeded the service limits.

4. How is it found?

Check the actuator and acme screw attach point for wear as de tailed in number 5 below.

5. What tasks are to be performed?

Perform the following horizontal stabilizer actuator wear check procedure:

1. General

A. The left and right horizontal stabilizer actuators are located forward of the horizontal
stabilizer constant section.

B. Access to horizontal stabilizer actuators is through access door 311AB, zone 311, in the lower aft fuselage compartment.

2. Equipment and Materials

NOTE : Equivalent substitutes may be used instead of the following listed items:

Name and Number

Gage set (DZZ7121-501) EMDC-02K1003
Revision E

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page A54 SCI 27-6 - MD-10 HORIZONTAL STAB ILIZER ACTUATOR WEAR CHECK (AIRCRAFT WITH TWO DRIVE CHAINS) (cont’d)

Torque Wrenches (200 foot-pounds capacity) (30 to 60 inch-pounds range)

Force indicator (20 to 25 pounds range)

Quill Shaft Installation tool (DZZ7291-1)

Tester, drive chain tension (DZZ7293-1)

3. Check Horizontal Stabilizer Actuator Wear Tolerances

WARNING : BEFORE PRESSURIZING HYDRAULIC SYSTEMS, MAKE CERTAIN
THAT LANDING GEAR GROUND LOCKPINS ARE INSTALLED AND
THAT APPLICABLE CONTROLS ARE IN CORRECT POSITION TO
PREVENT INADVERTENT OPERAT ION OF LANDING GEAR AND
FLIGHT CONTROL SYSTEMS.

A. Pressurize hydraulic systems 1 and 3 (MD-10 AMM, PAGE BLOCK 29-00-00/201).

WARNING : BEFORE MOVING HORIZONTAL STABILIZER TRIM CONTROLS,
MAKE CERTAIN THAT AREAS AROUND HORIZONTAL
STABILIZER AND ELEVATORS ARE CLEAR OF PERSONNEL AND EQUIPMENT AND THAT UPPER TAIL CONE DOORS ARE CLOSED.

B. Using the horizontal stabilizer trim handles on the control pede stal, move the stabilizer to the zero (neutral) position.

C. Manually actuate the primary trim control valv es located on the aft pressure bulkhead to align both actuators as show n in Figure 1, Views A and B.

NOTE : This procedure indexes the horizonta l stabilizer actuators correctly to ensure the proper re-installa tion of the drive chains.

D. Shut off the hydraulic pressure source.

E. Make sure that all three hydraulic sy stems are depressurized (MD-10 AMM, PAGEBLOCK 29-00-00/201). EMDC-02K1003
Revision E

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page A55 SCI 27-6 - MD-10 HORIZONTAL STAB ILIZER ACTUATOR WEAR CHECK (AIRCRAFT WITH TWO DRIVE CHAINS) (cont’d)

WARNING : TAG AND USE SAFETY CLI PS TO SAFETY THE CIRCUIT
BREAKERS. IF THE CIRCUIT BREAKERS ARE NOT OPENED, TAGGED, AND SAFETIED, INJURY TO PERSONS AND DAMAGE TO EQUIPMENT CAN OCCUR.

F. Open these circuit breakers and install safety tags:

AVIONICS, FLIGHT CONTROL DC BUS 1

Row Col Number Name

C 8 B1-693 AUTO PITCH TRIM 1

AVIONICS, MISC DC BUS 2

Row Col Number Name

F 3 B1-507 PRIMARY HORIZ STAB TRIM

OVERHEAD, RIGHT EMER DC BUS

Row Col Number Name

E 26 B1-694 AUTO PITCH TRIM 2

G. Put a “DO NOT OPERATE” tag on the horizontal stabilizer trim handles on the control pedestal.

CAUTION : QUILL SHAFT WILL DROP IF IT IS NOT SUPPORTED WHEN CROSS
BOLT IS REMOVED.

H. Remove the cross bolt at the bottom of quill sh aft and carefully remove the quill shaft.

I. Check the first actuator; either the left or ri ght actuator may be checked first (Figure 2).

(1) Loosen the drive chain on the actuator not being checked.

NOTE : This procedure should provide enough slack in the drive chain to remove
the chain from the actuator acme nut sprocket without disconnecting the
chain master link. EMDC-02K1003
Revision E

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page A56 SCI 27-6 - MD-10 HORIZONTAL STAB ILIZER ACTUATOR WEAR CHECK (AIRCRAFT WITH TWO DRIVE CHAINS) (cont’d)

(a) Loosen and disconnect the turnbuckle at the drive chain id ler sprocket to relieve the tension on the drive chain, and rotate the idler sprocket clear of the
chain.

(b) Remove the drive chain from the acme nut sprocket.

(2) Install the gauge set torque adapter on the actuator not being checked.

(3) Clean any grease or loose material from th e surfaces of the horizontal stabilizer fitting and the acme nut hub where the indi cator probes will touch on the actuator being checked.

(4) Install the gauge set indicators and re straint on the actua tor being checked.

(a) Position the probe from indicator (A) against the surface of the acme nut hub. Move the indicator toward the hub until the probe is compressed approximately one half travel and th e indicator needle is pointed up.

(b) Position the probe from indicator (B ) against the uppe r surface of the horizontal stabilizer fitting (acme scre w attach point). Move the indicator toward the fitting until the probe is co mpressed approximately one half travel and the indicator needle is pointed up.

(c) Install the actuator restraint on the acm e nut hub lugs and clamp the end of the restraint to the adjacent structural beam.

(5) Using the torque adapter, rotate the acme nut hub back and forth to relieve the tension on the actuator, and then rotate the acme nut hub in a clockwise direction until the torque wrench indicates 200 ft-lbs.

NOTE : The torque shall be 200 ft-lbs, as appl ied to the actuator screw. With the torque adapter installed, the torque wrench reading shall be 200 ft-lbs when the wrench handle is parallel to the acme nut hub lugs. The torque wrench reading shall be 155 ft-lbs when the wrench handle is perpendicular to the nut hub lugs.

(6) Set both indicator dials to the zero position.

(7) Rotate the acme nut hub in a countercloc kwise direction until the torque wrench
indicates 200 ft-lbs. EMDC-02K1003
Revision E

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page A57 SCI 27-6 - MD-10 HORIZONTAL STAB ILIZER ACTUATOR WEAR CHECK (AIRCRAFT WITH TWO DRIVE CHAINS) (cont’d)

(8) Record the amount of indicator needle movement on each indicator.

NOTE : The two indicator needles will move in opposite directions during the
check. The amount of movement for th e needle that moves in the positive direction can be read directly from the indicator scale. The amount of
movement for the needle that moves in the negative direction must be
calculated.

(9) Rotate the acme nut hub in a clockwise di rection until the torque wrench indicates 200 ft-lbs, and check that both indicators have returned to the zero reading.

(10) Reset the indicators to read zero, if necessary.

(11) Repeat steps (7) through (10) until three consecutive readings are obtained on each indicator that are no more than 0.003 inch ap art, with a return to the zero reading
each time.

(12) Using the highest of the three readings obt ained from each indicator in step (11), do any of the following work items that apply.

(a) If the nut-to-screw reading (indicator A) is more than 0.068 inch, replace the

actuator.

(b) If the screw-to-stabilizer-connection read ing (indicator B) is more than 0.023 inch, repair the connection as necessary.

(c) If the combination of readings (indic ators A and B) is more than 0.080 inch, replace the actuator and/or repa ir the connection as necessary.

J. Perform steps I.(1) through I.(12) on the second actuator being checked.

K. Remove the gauge set indicators, restrain t, and torque adaptor from actuators.

L. Make certain that both actuators are ali gned and positioned as shown in Figure 1, Views
A and B.

M. Place the drive chains on the acme nut sprockets.

(1) Position the master links at Po ints B as shown in Figure 1. EMDC-02K1003
Revision E

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page A58 SCI 27-6 - MD-10 HORIZONTAL STAB ILIZER ACTUATOR WEAR CHECK (AIRCRAFT WITH TWO DRIVE CHAINS) (cont’d)

(2) Make certain that the slack is removed fr om the sections of the chains located on the forward side of the acme nut sprockets.

CAUTION : DO NOT EXCEED 60 INCH-POUNDS OF TORQUE ON IDLER
SPROCKET TURNBUCKLES.

(3) Connect the turnbuckles at the idler spro ckets, and tighten each turnbuckle to a torque of 30 to 60 inch-pounds. While tight ening the turnbuckles, check to see that the acme nut sprockets are free to rotate so that the chain tensions can equalize.

(4) Safety the idler sprocket turnbuckles with clips.

N. Check the tension of each drive ch ain (MD-10 AMM, PAGEBLOCK 27-44-01/201, INSTALL ACME SCREW ACTUATOR).

O. Check the dimensions of each actuat or (MD-10 AMM, PAGEBLOCK 27-44-01/201, INSTALL ACME SCREW ACTUATOR).

P. Install the quill shaft (MD-10 AMM, PAGEBLOCK 27-44-01/201, INSTALL ACME SCREW ACTUATOR).

Q. Lubricate the drive chains (MD-10 A MM, PAGEBLOCK 12-21-03/301, HORIZONTAL STABILIZER CONSTANT SECTION LUBRICATION).

R. Remove the safety tags and close these circuit breakers:

AVIONICS, FLIGHT CONTROL DC BUS 1

Row Col Number Name

C 8 B1-693 AUTO PITCH TRIM 1

AVIONICS, MISC DC BUS 2

Row Col Number Name

F 3 B1-507 PRIMARY HORIZ STAB TRIM EMDC-02K1003
Revision E

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page A59 SCI 27-6 - MD-10 HORIZONTAL STAB ILIZER ACTUATOR WEAR CHECK (AIRCRAFT WITH TWO DRIVE CHAINS) (cont’d)

OVERHEAD, RIGHT EMER DC BUS

Row Col Number Name

E 26 B1-694 AUTO PITCH TRIM 2

S. Remove the “DO NOT OPERATE” tag from the horizontal stab ilizer trim handles on the control pedestal.

WARNING : BEFORE PRESSURIZING HYDRAULIC SYSTEMS, MAKE CERTAIN
THAT LANDING GEAR GROUND LOCKPINS ARE INSTALLED AND
THAT APPLICABLE CONTROLS ARE IN CORRECT POSITION TO
PREVENT INADVERTENT OPERAT ION OF LANDING GEAR AND
FLIGHT CONTROL SYSTEMS.

T. Pressurize hydraulic systems 1 and 3 (MD-10 AMM, PAGE BLOCK 29-00-00/201).

WARNING : BEFORE MOVING TRIM CONTROLS, MAKE CERTAIN THAT AREAS
AROUND HORIZONTAL STABIL IZER AND ELEVATORS ARE CLEAR OF PERSONNEL AND EQUI PMENT AND THAT UPPER TAIL
CONE DOORS ARE CLOSED.

U. Using the horizontal stabilizer trim handles on the control pedest al, move horizontal stabilizer to the full aircraft nose up and full aircraft nose down positions, and check the actuators for smooth operation without binding.

V. Move the horizontal stabilizer to the zero (neu tral) position.

W. Shut off the hydraulic pressure source.

X. Lubricate the horizontal stabilizer ac tuators (SCI 27-2 - MD-10 HORIZONTAL STABILIZER ACTUATOR LUBRICATION). EMDC-02K1003
Revision E

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page A60 SCI 27-6 - MD-10 HORIZONTAL STAB ILIZER ACTUATOR WEAR CHECK (AIRCRAFT WITH TWO DRIVE CHAINS) (cont’d)

Figure 1 E DIMENSIONS C & D EQUAL WITHIN 0.15 INCH

GREASE FITTING 

# I

ON TOP OF NUT (TYPICAL) •

HOISTING LUG CIRCULAR !DENTATION INDEX MARKS (BOTH ACTUATOR) 

# 0

FWD 1

# ~ LOCATE MASTER LINK POINT IN THIS AREA B

VIEW A LOOKING DOWN

r,..... --'1, I

# ()~OCRONST\ 

# 0

A A

# of~

30.49 ± 0.20 INCHES

VIEW B

# ~~t

I I -----.1

LH ACTUATOR SECTION A·A

VIEW LOOKING DOWN 30.49 ± 0.20 INCHES

RH ACTUATOR D

INDEXED TOOTH (BOTH ACTUATORS)

CA2·27-558DMDC-02K1003
Revision E

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page A61 SCI 27-6 - MD-10 HORIZONTAL STAB ILIZER ACTUATOR WEAR CHECK (AIRCRAFT WITH TWO DRIVE CHAINS) (cont’d)

Figure 2 E

RIGHT AC**ACTUATO~E** SCREW

NOTE:

SHOWN WITH TO CHECK**LEGlf~cSTET** INSTALLED UATOR

CA2-27-560MDC-02K1003
Revision E

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page A62 SCI 27-6 - MD-10 HORIZONTAL STAB ILIZER ACTUATOR WEAR CHECK (AIRCRAFT WITH TWO DRIVE CHAINS) (cont’d)

6. Is test equipment needed?

A list of the required equipment and materi als can be found in paragraph 2. of the actuator wear check procedure in number 5 above.

7. What is pass/fail criteria?

The pass/fail criteria can be found in paragr aph 3.I.(12) of the actuator wear check procedure in number 5 above.

8. What is SCI interval?

The actuator wear check shall be performed at intervals not to exceed 15,000 flight hours. EMDC-02K1003
Revision E

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page A63 SCI 27-7 - MD-10 HORIZONTAL STAB ILIZER ACTUATOR WEAR CHECK (AIRCRAFT WITH FOUR DRIVE CHAINS)

1. What model does this SCI apply to?

MD-10 series aircraft with four horizontal stabilizer actuator drive chains (service bulletin DC10-27-162 not incorporated)

2. What part or LRU is being checked?

Horizontal stabilizer actuator

3. What failure mode is being looked for?

This SCI checks for wear rather than a failure mode. A wear check is being performed to
make certain that actuator and actuator-to-hor izontal stabilizer attach point wear has not
exceeded the service limits.

4. How is it found?

Check the actuator and acme screw attach point for wear as de tailed in number 5 below.

5. What tasks are to be performed?

Perform the following horizontal stabilizer actuator wear check procedure:

1. General

A. The left and right horizontal stabilizer actuators are located forward of the horizontal
stabilizer constant section.

B. Access to the horizontal stab ilizer actuators is through access door 311AB, zone 311, in the lower aft fuselage compartment.

2. Equipment and Materials

NOTE : Equivalent substitutes may be used instead of the following listed items:

Name and Number

Gage set (DZZ7121-501) EMDC-02K1003
Revision E

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page A64 SCI 27-7 - MD-10 HORIZONTAL STAB ILIZER ACTUATOR WEAR CHECK (AIRCRAFT WITH FOUR DRIVE CHAINS) (cont’d)

Torque Wrenches (200 foot-pounds capacity) (30 to 60 inch-pounds range)

Force indicator (20 to 25 pounds range)

Tester, drive chain tension (DZZ7293-1)

3. Check Horizontal Stabilizer Actuator Wear Tolerances

WARNING : BEFORE PRESSURIZING HYDRAULIC SYSTEMS, MAKE CERTAIN
THAT LANDING GEAR GROUND LOCKPINS ARE INSTALLED AND
THAT APPLICABLE CONTROLS ARE IN CORRECT POSITION TO
PREVENT INADVERTENT OPERAT ION OF LANDING GEAR AND
FLIGHT CONTROL SYSTEMS.

A. Pressurize hydraulic systems 1 and 3 (MD-10 AMM, PAGE BLOCK 29-00-00/201).

WARNING : BEFORE MOVING HORIZONTAL STABILIZER TRIM CONTROLS,
MAKE CERTAIN THAT AREAS AROUND HORIZONTAL
STABILIZER AND ELEVATORS ARE CLEAR OF PERSONNEL AND EQUIPMENT AND THAT UPPER TAIL CONE DOORS ARE CLOSED.

B. Using the horizontal stabilizer trim handles on the control pede stal, move the stabilizer to the zero (neutral) position.

C. Manually actuate the primary trim control valv es located on the aft pressure bulkhead to align both actuators as show n in Figure 1, Views A and B.

NOTE : This procedure indexes the horizontal stab ilizer actuators correctly to ensure the proper re-installation of the drive chains.

D. Shut off the hydraulic pressure source.

E. Make sure that all three hydraulic sy stems are depressurized (MD-10 AMM, PAGEBLOCK 29-00-00/201). EMDC-02K1003
Revision E

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page A65 SCI 27-7 - MD-10 HORIZONTAL STAB ILIZER ACTUATOR WEAR CHECK (AIRCRAFT WITH FOUR DRIVE CHAINS) (cont’d)

WARNING : TAG AND USE SAFETY CLI PS TO SAFETY THE CIRCUIT
BREAKERS. IF THE CIRCUIT BREAKERS ARE NOT OPENED, TAGGED, AND SAFETIED, INJURY TO PERSONS AND DAMAGE TO EQUIPMENT CAN OCCUR.

F. Open these circuit breakers and install safety tags:

AVIONICS, FLIGHT CONTROL DC BUS 1

Row Col Number Name

C 8 B1-693 AUTO PITCH TRIM 1

AVIONICS, MISC DC BUS 2

Row Col Number Name

F 3 B1-507 PRIMARY HORIZ STAB TRIM

OVERHEAD, RIGHT EMER DC BUS

Row Col Number Name

E 26 B1-694 AUTO PITCH TRIM 2

G. Put a “DO NOT OPERATE” tag on the horizontal stabilizer trim handles on the control pedestal.

H. Check the first actuator; either the left or ri ght actuator may be checked first (Figure 2).

(1) Loosen the drive chains on th e actuator not being checked.

NOTE : This procedure should provide enough sl ack in the drive chains to remove
the chains from the actuator acme nut sprockets without disconnecting the
chain master links.

(a) Loosen and disconnect the turnbuckles at the drive chain idler sprockets to relieve the tension on the drive chains, a nd rotate the idler sprockets clear of
the chains.

(b) Remove the drive chains from the acme nut sprockets.

(2) Install the gauge set torque adapter on the actuator not being checked.

SCI 27-7 - MD-10 HORIZONTAL STAB ILIZER ACTUATOR WEAR CHECK EMDC-02K1003
Revision E

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page A66 (AIRCRAFT WITH FOUR DRIVE CHAINS) (cont’d)

(3) Clean any grease or loose material from th e surfaces of the horizontal stabilizer fitting and the acme nut hub where the indi cator probes will touch on the actuator being checked.

(4) Install the gauge set indicators and re straint on the actua tor being checked.

(a) Position the probe from indicator (A) against the surface of the acme nut hub. Move the indicator toward the hub until the probe is compressed approximately one half travel and th e indicator needle is pointed up.

(b) Position the probe from indicator (B ) against the uppe r surface of the horizontal stabilizer fitting (acme scre w attach point). Move the indicator toward the fitting until the probe is co mpressed approximately one half travel and the indicator needle is pointed up.

(c) Install the actuator restraint on the acm e nut hub lugs and clamp the end of the restraint to the adjacent structural beam.

(5) Using the torque adapter, rotate the acme nut hub back and forth to relieve the tension on the actuator, and then rotate the acme nut hub in a clockwise direction until the torque wrench indicates 200 ft-lbs.

NOTE : The torque shall be 200 ft-lbs, as appl ied to the actuator screw. With the torque adapter installed, the torque wrench reading shall be 200 ft-lbs when the wrench handle is parallel to the acme nut hub lugs. The torque wrench reading shall be 155 ft-lbs when the wrench handle is perpendicular to the nut hub lugs.

(6) Set both indicator dials to the zero position.

(7) Rotate the acme nut hub in a countercloc kwise direction until the torque wrench
indicates 200 ft-lbs.

(8) Record the amount of indicator needle movement on each indicator.

NOTE : The two indicator needles will move in opposite directions during the
check. The amount of movement for th e needle that moves in the positive direction can be read directly from the indicator scale. The amount of
movement for the needle that moves in the negative direction must be
calculated. EMDC-02K1003
Revision E

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page A67 SCI 27-7 - MD-10 HORIZONTAL STAB ILIZER ACTUATOR WEAR CHECK (AIRCRAFT WITH FOUR DRIVE CHAINS) (cont’d)

(9) Rotate the acme nut hub in a clockwise di rection until the torque wrench indicates 200 ft-lbs, and check that both indicators have returned to the zero reading.

(10) Reset the indicators to read zero, if necessary.

(11) Repeat steps (7) through (10) until three consecutive readings are obtained on each indicator that are no more than 0.003 inch ap art, with a return to the zero reading
each time.

(12) Using the highest of the three readings obt ained from each indicator in step (11), do any of the following work items that apply.

(a) If the nut-to-screw reading (indicator A) is more than 0.068 inch, replace the

actuator.

(b) If the screw-to-stabilizer-connection read ing (indicator B) is more than 0.023 inch, repair the connection as necessary.

(c) If the combination of readings (indic ators A and B) is more than 0.080 inch, replace the actuator and/or repa ir the connection as necessary.

I. Perform steps H.(1) through H.(12) on the second actuator being checked.

J. Remove the gauge set indicators, restrain t, and torque adaptor from actuators.

K. Make certain that both actuators are ali gned and positioned as shown in Figure 1, Views
A and B

L. Place the drive chains on the acme nut sprockets.

(1) Position the master links at Po ints B as shown in Figure 1.

(2) Make certain that the slack is removed fr om the sections of the chains located on the forward side of the acme nut sprockets. EMDC-02K1003
Revision E

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page A68 SCI 27-7 - MD-10 HORIZONTAL STAB ILIZER ACTUATOR WEAR CHECK (AIRCRAFT WITH FOUR DRIVE CHAINS) (cont’d)

CAUTION : DO NOT EXCEED 60 INCH-POUNDS OF TORQUE ON IDLER
SPROCKET TURNBUCKLES.

(3) Connect the turnbuckles at the idler spro ckets, and tighten each turnbuckle to a torque of 30 to 60 inch-pounds. While tight ening the turnbuckles, check to see that the acme nut sprockets are free to rotate so that the chain tensions can equalize.

(4) Safety the idler sprocket turnbuckles with clips.

M. Check the tension of each drive ch ain (MD-10 AMM, PAGEBLOCK 27-44-01/201, INSTALL ACME SCREW ACTUATOR).

N. Check the dimensions of each actuat or (MD-10 AMM, PAGEBLOCK 27-44-01/201, INSTALL ACME SCREW ACTUATOR).

O. Lubricate the drive chains (MD-10 A MM, PAGEBLOCK 12-21-03/301, HORIZONTAL STABILIZER CONSTANT SECTION LUBRICATION).

P. Remove the safety tags and close these circuit breakers:

AVIONICS, FLIGHT CONTROL DC BUS 1

Row Col Number Name

C 8 B1-693 AUTO PITCH TRIM 1

AVIONICS, MISC DC BUS 2

Row Col Number Name

F 3 B1-507 PRIMARY HORIZ STAB TRIM

OVERHEAD, RIGHT EMER DC BUS

Row Col Number Name

E 26 B1-694 AUTO PITCH TRIM 2

Q. Remove the “DO NOT OPERATE” tag from the horizontal stab ilizer trim handles on the control pedestal. EMDC-02K1003
Revision E

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page A69 SCI 27-7 - MD-10 HORIZONTAL STAB ILIZER ACTUATOR WEAR CHECK (AIRCRAFT WITH FOUR DRIVE CHAINS) (cont’d)

WARNING : BEFORE PRESSURIZING HYDRAULIC SYSTEMS, MAKE CERTAIN
THAT LANDING GEAR GROUND LOCKPINS ARE INSTALLED AND
THAT APPLICABLE CONTROLS ARE IN CORRECT POSITION TO
PREVENT INADVERTENT OPERAT ION OF LANDING GEAR AND
FLIGHT CONTROL SYSTEMS.

R. Pressurize hydraulic systems 1 and 3 (MD-10 AMM, PAGE BLOCK 29-00-00/201).

WARNING : BEFORE MOVING TRIM CONTROLS, MAKE CERTAIN THAT AREAS
AROUND HORIZONTAL STABIL IZER AND ELEVATORS ARE CLEAR OF PERSONNEL AND EQUI PMENT AND THAT UPPER TAIL
CONE DOORS ARE CLOSED.

S. Using the horizontal stabilizer trim handles on the control pedest al, move horizontal stabilizer to the full aircraft nose up and full aircraft nose down positions, and check the actuators for smooth operation without binding.

T. Move the horizontal stabilizer to the zero (neu tral) position.

U. Shut off the hydraulic pressure source.

V. Lubricate the horizontal stabilizer ac tuators (SCI 27-2 - MD-10 HORIZONTAL STABILIZER ACTUATOR LUBRICATION). EMDC-02K1003
Revision E

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page A70 SCI 27-7 - MD-10 HORIZONTAL STAB ILIZER ACTUATOR WEAR CHECK (AIRCRAFT WITH FOUR DRIVE CHAINS) (cont’d)

Figure 1 E DIMENSIONS A & B EQUAL WITHIN 0.15 INCH

A

HOISTING LUG

NOTE:
WHEN MAKING AN INDEX CHECK, ASSUMING THE LEFT HAND ACTUATOR NUT LUGS ARE EQUAL, THERE CAN BE NO PRACTICAL IMPROVEMENT MADE IN INDEXING, UNLESS MISALIGNMENT OF RIGHT HAND ACTUATOR NUT LUGS ARE GREATER THAN 1/2 INCH.



# I

B



### ? 

# "

VIEW B AFT PRESSURE BULKHEAD

VIEW A

VIEW LOOKING DOWN

NOTE: THIS PROVIDES GROSS ADJUSTMENT OF ACTUATORS. FOR FINE ADJUSTMENT SEE VIEW A 

### c



### 0
FWD DIMENSIONS C & D EQUIAL WITHIN 0.15 INCH

D

INDEXED TOOTH (BOTH ACTUATORS)

SCREW**STOP~** 

# oO

FWD

SECTION B-B

VIEW LOOKING DOWN

DC-1 0 WEAR CHECK 4 CHAIN F1MDC-02K1003
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Figure 2 E

INDICATOR B (MEASURES TOLERANCE BETWEEN ACME SCREW**~~~B~~r~~~NTAL** POINT J ATTACH

INDICATOR A <MEASURES TOLERANCE BETWEEN ACME SCREW**~~g ~CME**  NUT RIGHT AC**ACTUATO_~E** SCREW

CHAIN DRIVE TURNBUCKLES

CA2-27-299AMDC-02K1003
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6. Is test equipment needed?

A list of the required equipment and materi als can be found in paragraph 2. of the actuator wear check procedure in number 5 above.

7. What is pass/fail criteria?

The pass/fail criteria can be found in paragr aph 3. H.(12) of the actuator wear check procedure in number 5 above.

8. What is SCI interval?

The actuator wear check shall be performed at intervals not to exceed 15,000 flight hours. EMDC-02K1003
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1. What model does this SCI apply to?

MD-11 series aircraft

2. What part or LRU is being checked?

Horizontal stabilizer actuator

3. What failure mode is being looked for?

This SCI checks for wear, rather than a failu re mode. A wear check is being performed
to make certain that the actuator wear and th e actuator-to-horizontal stabilizer attach lug
connection wear have not ex ceeded the service limits.

4. How is it found?

Check the actuator and the actuator-to-horizonta l stabilizer attach lug connection for wear
as detailed in number 5 below.

5. What tasks are to be performed?

Perform the following horizontal stabilizer actuator wear check procedure:

1. General

A. This procedure has the test inst ructions for the left and right horizontal stabilizer actuator wear tolerance (actuator wear check).

B. The horizontal stabilizer actuators are instal led at the aft pressure bulkhead, forward of
the horizontal stabilizer.

C. The referenced TASK numbers apply to the MD-11 AMM.

2. TEST OF THE HORIZONTAL STABILIZER ACTUATORS

A. Fixtures, Tools, Test and Support Equipment

(1) Fixtures, Tools, Test and Support Equipment

NOTE : Equivalent replacements are permitted for the items that follow. EMDC-02K1003
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Table 1

REFERENCE DESIGNATION Not specified Maintenance platform, 10-15 ft (3-5 m) high

DZZ7121-501 Gage set, horizontal stabilizer jack Not specified Torque wrench 200 ft-lb (271 N·m) capacity Not specified Torque wrench 30-60 in-lb (3.4-6.8 N·m) range Not specified Force indicator 20-25 lbs (9.1-11.3 kg) range

DZZ7291-1 Torque adapter, horizontal stabilizer spline

DZZ7293-1 Tension tester, horizontal stabilizer drive chain

B. Expendable Parts

(1) Expendable Parts

Table 2

REFERENCE/ITEM DESIGNATION IPC

7 Cotter Pin 27-44-20-001-610

11 Clip 27-44-20-001-220

C. References

Reference Title

12-24-09-600-801 LUBRICATION OF THE HORIZONTAL STABILIZER CONSTANT SECTION (MD-11 AMM, P/B 301)

27-40-00-710-802 FUNCTIONAL TEST OF THE HORIZONTAL STABILIZER RANGE OF MOVEMENT (MD-11 AMM, P/B 501)

29-00-00-860-802 APPLY HYDRAULIC PRESSURE, SYSTEM NO. 3 AUXILIARY PUMPS (MD-11 AMM, P/B 201)

29-00-00-860-805 REMOVE HYDRAULIC PRESSURE, SYSTEM NO. 3 AUXILIARY PUMPS (MD-11 AMM, P/B 201)

29-00-00-860-807 REMOVE HYDRAULIC PRESSURE, SYSTEM NO. 2 AUXILIARY PUMPS (MD-11 AMM, P/B 201)

29-00-00-860-808 REMOVE HYDRAULIC PRESSURE, SYSTEM NO. 1 AUXILIARY PUMPS (MD-11 AMM, P/B 201)

32-00-00-860-801 SAFETY THE LANDING GEAR FOR MAINTENANCE (MD-11 AMM, P/B 201)

27-44-20-001-220 Illustrated Parts Catalog
SCI 27-8 - MD-11 HORIZONTAL STAB ILIZER ACTUATOR WEAR CHECK EMDC-02K1003
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BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page A75 (cont’d)

Reference Title

27-44-20-001-610 Illustrated Parts Catalog

SCI 27-3 MD-11 HORIZONTAL STABILIZER ACTUATOR LUBRICATION (Report Nu mber MDC-02K1003)

D. Consumable Materials

NOTE : It is possible that some materials in the Consumable Materials chart cannot be used for some or all of the necessary applications. Before you use the materials, make sure the types, quantities, and app lications of the materials necessary are legally permitted in your location. All pe rsons must obey all applicable federal, state, local, and provincial laws and re gulations when it is necessary to work
with these materials.

Description Specification
Lockwire - .032 Steel Corrosion Resistant DPM 5865 (NASM20995C)

E. Access Panels

Number Name/Location
311AB AFT FUSELAGE

F. Job Set-up - Horizontal St abilizer Actuator Test

(1) Make sure the landing gear safety pi ns are installed. (SAFETY THE LANDING GEAR FOR MAINTENANCE, TASK 32-00-00-860-801)

(2) Make sure that this circuit breaker is closed:

AVIONICS, MISC DC BUS 2

Row Col Number Name

F 3 B1-507 PRIMARY HORIZ STAB TRIM

(3) Open this access panel:

Number Name/Location

311AB AFT FUSELAGE EMDC-02K1003
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G. Procedure - Horizontal St abilizer Actuator Test

(1) Pressurize the No. 1 and No. 3 hydrau lic systems. (APPLY HYDRAULIC PRESSURE, SYSTEM NO. 3 AUXILIAR Y PUMPS, TASK 29-00-00-860-802)

WARNING : MAKE SURE THE AREAS AROUND THE HORIZONTAL
STABILIZER AND ELEVATORS ARE CLEAR BEFORE THE
HORIZONTAL STABILIZER TRIM IS OPERATED. MAKE SURE
THE UPPER TAIL CONE DOOR S ARE CLOSED. IF THE
HORIZONTAL STABILIZER SYSTEM ACCIDENTALLY OPERATES, IT CAN CAUSE INJURY TO PERSONS AND DAMAGE TO EQUIPMENT.

(2) Align the horizontal stabilizer actuators as follows: (Figure 1) (F igure 2) (Figure 3) (Figure 4)

(a) Move the stabilizer to the zero (neutr al) position using the suitcase handles on the control pedestal or the control wheel switches.

(b) Manually operate the primary trim control valves (1) to align the left (2) and the right (3) horizontal stabilizer actuators.

1) Make sure the actuators (2) and (3) are at a height of 30.29-30.69 in. (769.4-779.5 mm) as shown in Figure 3.

NOTE : Measure from the bottom of the acme screw stop to the top of the acme nut on the left actuator, and from the bottom of the acme screw serrations to the top of the acme nut on the right actuator.

2) Align the index marks on the left (4) and the right (5) acme nut sprockets as shown in Figure 2. EMDC-02K1003
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WARNING : MAKE SURE YOU RELEASE THE PRESSURE FROM ALL
HYDRAULIC SYSTEMS AND THE SPECIFIED CIRCUIT
BREAKERS ARE OPEN. IF THE HORIZONTAL STABILIZER TRIM
SYSTEM ACCIDENTALLY OPERATES , IT CAN CAUSE INJURY TO PERSONS AND DAMAGE TO THE EQUIPMENT.

(3) Make sure that hydraulic pressure has been removed from all three hydraulic systems. (REMOVE HYDRAULIC PR ESSURE, SYSTEM NO. 3 AUXILIARY PUMPS, TASK 29-00-00-860-805) (R EMOVE HYDRAULIC PRESSURE, SYSTEM NO. 2 AUXILIARY PUMPS, TASK 29-00-00-860-807) (REMOVE HYDRAULIC PRESSURE, SYSTEM NO. 1 AUXILIARY PUMPS, TASK 29-00- 00-860-808)

WARNING : TAG AND USE SAFETY CLI PS TO SAFETY THE CIRCUIT
BREAKERS. IF THE CIRCUIT BREAKERS ARE NOT OPENED, TAGGED, AND SAFETIED, INJURY TO PERSONS AND DAMAGE TO EQUIPMENT CAN OCCUR.

(4) Open these circuit breakers and install safety tags:

AVIONICS, FLIGHT CONTROL DC BUS 1

Row Col Number Name

C 8 B1-693 AUTO PITCH TRIM 1

AVIONICS, MISC DC BUS 2

Row Col Number Name

F 3 B1-507 PRIMARY HORIZ STAB TRIM

OVERHEAD, RIGHT EMER DC BUS

Row Col Number Name

E 26 B1-694 AUTO PITCH TRIM 2

(5) Put a “DO NOT OPERATE” tag on the horizont al stabilizer suitcase handles on the control pedestal.

(6) Remove the quill shaft and the right dr ive chain as follows: (Figure 4)

(a) Remove and discard the lockwire from the head of the crossbolt (6). EMDC-02K1003
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(b) Remove and discard the cotter pin (7) from the nut (8).

CAUTION : HOLD THE QUILL SHAFT CORRECTLY WHEN YOU
REMOVE THE BOLT. IF NOT, THE QUILL SHAFT WILL
DROP.

(c) Remove the nut (8), the washer (9), a nd the crossbolt (6) at the bottom of the quill shaft (10).

(d) Remove the quill shaft (10).

(e) Remove and discard the two clips (1 1) from the right turnbuckle (12).

(f) Loosen the right turnbuckle ( 12) to release the tension.

(g) Remove and discard the cotter pin (7) from the nut (14) at the right turnbuckle (12).

(h) Remove the nut (14), the two washers ( 15), and the bolt (13) from the right turnbuckle (12).

(i) Move the right turnbuckle (12) aw ay from the idler sprocket (16).

(j) Move the right drive chain idler sprocket (16) away from the drive chain (17).

(k) Remove the drive chain (17) from the right acme nut sprocket (5).

(7) Install the horizontal stabilizer test gage set as follows: (Figure 5)

(a) Install the gage set torque adapter on the right acme nut sprocket (5).

(b) Clean any grease or loose material fro m the surfaces of the left horizontal stabilizer attach lug and the left acme nut sprocket (4) where the gage set indicator probes will touch.

(c) Install the two gage set indicators on the left actuator acme screw (2).

1) Set the probe of one indicator agains t the surface of the acme nut sprocket (4). Move the indicator toward the sprocket until the probe is compressed approximately one half travel and th e indicator needle is pointed up. EMDC-02K1003
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2) Set the probe of the other indicator ag ainst the top surface of the horizontal stabilizer attach lug. Move the indi cator toward the lug until the probe is compressed approximately one half tr avel and the indicator needle is pointed up.

(d) Install the actuator restraint on the left acme nut sprocket (4) lugs and attach the end of the restraint to the adj acent structural beam with a clamp.

(8) Do the tolerance test of the left horizontal stabilizer acme screw and nut as follows: (Figure 2) (Figure 5)

Table 3

STEP OPERATION VISUAL INSPECTION

1 Use the torque adapter to turn the right acme nut sprocket (5) clockwise and
counterclockwise. Remove the tension on the right actuator.

2 Turn the right acme nut sprocket (5) in a
clockwise direction unt il the torque wrench shows 200 ft-lb (271.2 N·m)

NOTE : The torque put to the actuator screw must be 200 ft-lb (271.2 N·m). The torque wrench must show 200 ft-lb (271.2 N·m) if the handle is installed parallel to the acme nut sprocket lugs. The torque wr ench must show 155 ft-lb (210.3 N·m) if the handle is installed at a right a ngle to the acme nut sprocket lugs.

3 Set the two gage set indi cator dials to the zero position.

4 Turn the right acme nut sprocket (5) in a
counterclockwise direct ion until the torque wrench shows 200 ft-lb (271.2 N·m).

5 Record the amount of indicator needle
movement on each indicator.

NOTE : The two indicator needles will move in opposite directions during the check.
The amount of movement for the needle that moves in the positive direction can be read directly from the indicator scale. The amount of movement for the needle that moves in the negativ e direction must be calculated.

6 Turn the right acme nut sprocket (5) in a
clockwise direction unt il the torque wrench shows 200 ft-lb (271.2 N·m). The two gage set indicators
should return to the zero position.

7 Reset the indicators to the zero position, if

necessary. EMDC-02K1003
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STEP OPERATION VISUAL INSPECTION

8 Repeat steps 4 through 7 until you get three dimensions, one after the other, on each
indicator that are no more than 0.003 inch (0.07 mm) apart, with a return to the zero reading each time. Record the applicable three
dimensions from each
indicator.

9 Use the highest dimension recorded in step 8
from each indicator to find out if the actuator wear is satisfactory. The highest indicator
dimension on the acme nut sprocket must not be more than 0.068 inch (1.72 mm). If it is, replace the actuator.

The highest indicator
dimension on the stabilizer attach lug must not be more than 0.023 inch (0.58 mm). If it is, repair the connection
between the actuator and the attach lug as necessary.

10 Add the two indicator dimensions from step 9 together. The sum of the two
indicator dimensions must
not be more than 0.080 inch (2.03 mm). If it is, replace the actuator and/or repair
the connection between the actuator and the attach lug

as necessary

(9) Remove the horizontal stabilizer test gage set as follows: (Figure 5)

(a) Remove the two gage set indicators fro m the left actuator acme screw (2).

(b) Remove the clamp from the actuator restraint and remove the restraint from the left acme nut sprocket (4).

(c) Remove the gage set torque adapter from the right acme nut sprocket (5).

(10) Remove the left drive chai n as follows: (Figure 4)

(a) Remove and discard the two clips (1 1) from the left turnbuckle (12).

SCI 27-8 - MD-11 HORIZONTAL STAB ILIZER ACTUATOR WEAR CHECK (cont’d) EMDC-02K1003
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BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page A81 (b) Loosen the left turnbuckle ( 12) to release the tension.

(c) Remove and discard the cotter pin (7) from the nut (14) at the left turnbuckle (12).

(d) Remove the nut (14), the two washers ( 15), and the bolt (13) from the left turnbuckle (12).

(e) Move the left turnbuckle (12) aw ay from the idler sprocket (16).

(f) Move the left drive chain idler sprocket (16) away from the drive chain (17).

(g) Remove the drive chain (17) from the left acme nut sprocket (4).

(11) Install the horizontal stabilizer test gage set as follows: (Figure 5)

(a) Install the gage set torque adapter on to the left acme nut sprocket (4).

(b) Clean any grease or loose material fro m the surfaces of the right horizontal stabilizer attach lug and the right acme nut sprocket (5) where the gage set indicator probes will touch.

(c) Install the two gage set indicators on the right actuator acme screw (3).

1) Set the probe of one indicator agains t the surface of the acme nut sprocket (5). Move the indicator toward the sprocket until the probe is compressed approximately one half travel and th e indicator needle is pointed up.

2) Set the probe of the other indicator ag ainst the top surfa ce of the horizontal stabilizer attach lug. Move the indi cator toward the lug until the probe is compressed approximately one half tr avel and the indicator needle is pointed up.

(d) Install the actuator restraint on the righ t acme nut sprocket (5) lugs and attach the end of the restraint to the adj acent structural beam with a clamp.

(12) Do the tolerance test of the right horiz ontal stabilizer acme screw and nut as follows: (Figure 2) (Figure 5) EMDC-02K1003
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Table 4

STEP OPERATION VISUAL INSPECTION

1 Use the torque adapter to turn the left acme nut sprocket (5) clockwise and
counterclockwise. Remove the tension on the
left actuator.

2 Turn the left acme nut sprocket (4) in a
clockwise direction unt il the torque wrench shows 200 ft-lb (271.2 N·m)

NOTE : The torque put to the actuator screw mu st be 200 ft-lb (271.2 N·m). The torque wrench must show 200 ft-lb (271.2 N·m) if the handle is installed parallel to the acme nut sprocket lugs. The torque wr ench must show 155 ft-lb (210.2 N·m) if the handle is installed at a right a ngle to the acme nut sprocket lugs.

3 Set the two gage set indi cator dials to the zero position.

4 Turn the left acme nut sprocket (5) in a
counterclockwise direct ion until the torque wrench shows 200 ft-lb (271.2 N·m).

5 Record the amount of indicator needle
movement on each indicator.

NOTE : The two indicator needles will move in opposite directions during the check.
The amount of movement for the needle that moves in the positive direction can be read directly from the indicator s cale. The amount of movement for the needle that moves in the negativ e direction must be calculated.

6 Turn the left acme nut sprocket (4) in a
clockwise direction unt il the torque wrench shows 200 ft-lb (271.2 N·m). The two gage set indicators
should return to the zero position.

7 Reset the indicators to the zero position, if

necessary.

8 Repeat steps 4 through 7 until you get three dimensions, one after the other, on each
indicator that are no more than 0.003 inch (0.07 mm) apart, with a return to the zero reading each time. Record the applicable three
dimensions from each
indicator. EMDC-02K1003
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STEP OPERATION VISUAL INSPECTION

9 Use the highest dimension recorded in step 8
from each indicator to find out if the actuator wear is satisfactory. The highest indicator
dimension on the acme nut sprocket must not be more than 0.068 inch (1.72 mm); if it is, replace the actuator.

The highest indicator
dimension on the stabilizer attach lug must not be more than 0.023 inch (0.58 mm); if it is, repair the connection
between the actuator and the attach lug as necessary.

10 Add the two indicator dimensions from step 9 together. The sum of the two
indicator dimensions must
not be more than 0.080 inch (2.03 mm); if it is, replace the actuator and/or repair
the connection between the actuator and the attach lug

as necessary

(13) Remove the horizontal stabilizer test gage set as follows: (Figure 5)

(a) Remove the two gage set indicators from the right actuator acme screw (3).

(b) Remove the clamp from the actuator restraint and remove the restraint from the right acme nut sprocket (5).

(c) Remove the gage set torque adapter fro m the left acme nut sprocket (4).

(14) Adjust the horizontal stabilizer actuators as follows: (Figure 2) (Figure 3) (Figure 4) (Figure 5)

(a) Make sure the drive chain idler sprockets (16) are free to move.

(b) Make sure that each of the actuators (2 ) and (3) is installed at a height of 30.29-30.69 in. (769.4-779.5 mm) as follows:

1) To check the left actuator height dimension, measure from the bottom of the acme screw stop to the top of the acme nut.

SCI 27-8 - MD-11 HORIZONTAL STAB ILIZER ACTUATOR WEAR CHECK EMDC-02K1003
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BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page A84 (cont’d)

2) To check the right actuator height di mension, measure from the bottom of the acme screw serrations to the top of the acme nut.

(c) For more precision, manually adjust th e actuators (2) and (3) as follows:

1) Make sure the difference between the two dimensions A and B is not more than 0.15 in. (3.8 mm).

2) Make sure the difference between the two dimensions C and D is not more than 0.15 in. (3.8 mm).

(d) Make sure the left and right acme nut gr ease fittings are each directly forward
of their related acme screws.

(e) Make sure the index marks on the acme nut sprockets (4) and (5) are each directly to the right of their related acme screws.

(15) Install the two drive chains (17) as follows: (Figure 2) (Figure 4)

(a) Make sure that the difference between the actuator height dimensions is no more than 0.40 inch (10.1 mm).

(b) Install the two drive chains (17), on the acme nut sprockets (4), and (5), and the drive chain idler sprockets (16).

(c) Make sure that any looseness in the ch ain is on the aft side of the acme nut sprockets (4) and (5).

(d) Make sure that each master link is betw een a drive chain idler sprocket (16) and an acme nut sprocket (4) or (5).

(e) Make sure that the right drive chain is installed in the two chain guards (18) and one chain guide (19).

(f) Install the two turnbuckles (12) as follows:

1) Move the drive chain idler sprockets (16) toward the drive chains (17)

2) Move the turnbuckles (12) towa rd the idler sprockets (16).

3) Install the two bolts (13), the four washers (15) and the two nuts (14). EMDC-02K1003
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4) Safety the nuts with two cotter pins (7).

5) Tighten the two turnbuckles (12) to a torque of 30-60 in-lb (3.4-6.7 N·m). While turning the turnbuckles, make sure that the acme nut sprockets (4) and (5) are free to turn so that th e drive chain tensi ons can equalize.

(16) Do a check of the horizontal stabilizer drive chain for the correct tension as follows: (Figure 2) (Figure 5)

(a) Install the force indicator on the drive chain tension tester and put the toggle pad against the support structure.

(b) With the pin against the left drive chai n (17), loosen the thumb screw at the bottom of the scale. Adjust the pointer to align with zero on the scale, and tighten the thumb screw.

(c) Put a forward load of 20 to 25 lb (9.1 to 11.3 Kg) on the drive chain between the acme nut sprocket (4) and the drive ch ain idler sprocket (16). If the chain moves more than 0.125 in. (3.17 mm), tight en the turnbuckle (12) to no more than 60 in-lb (6.7 N·m).

(d) With the pin against the right drive chai n (17), loosen the thumb screw at the bottom of the scale. Adjust the pointer to align with zero on the scale, and tighten the thumb screw.

(e) Put a forward load of 20 to 25 lb (9.1 to 11.3 Kg) on the drive chain between the acme nut sprocket (5) and the drive ch ain idler sprocket (16). If the chain moves more than 0.125 in. (3.17 mm), tight en the turnbuckle (12) to no more than 60 in-lb (6.7 N·m).

(17) Do a check of the horizontal stabilizer act uator dimensions as follows: (Figure 2)

(a) Make sure that dimensions A and C are each 12.37 to 13.13 inches (314.1 to 333.5 mm).

(b) Calculate the difference betw een dimensions A and C.

(c) If the difference is less than 0.40 inch (10.2 mm), go to step (18).

(d) If the difference is 0.40 inch (10.2 mm) or more, do the steps that follow: EMDC-02K1003
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1) Remove the drive chain (17) from the acme nut sprocket (4) or (5) that is farthest from the 12.75-inch (323.9-mm) dimension.

2) Turn the farthest acme nut sprocket one tooth toward the 12.75-inch (323.9-mm) dimension, and repeat steps (15) through (17).

(18) Install the four clips ( 11) in the two turnbuckl es (12). (Figure 4)

(19) Install the quill shaft (10) as follows: (Figure 4) (Figure 5)

CAUTION : DO NOT TURN AN ACME NUT SPROCKET (4) OR (5) TO HELP INSTALL THE QUILL SHAFT WITH THE DRIVE
CHAINS INSTALLED. TURN ING AN ACME NUT SPROCKET
WITH THE CHAINS INSTALLED CAN DAMAGE THE DRIVE
ASSEMBLY FUSE PIN.

(a) Install the spline torque adapter on the bottom of the drive assembly using the
crossbolt holes.

(b) Turn the spline torque adapter until the quill shaft (10) moves easily up into the gearbox.

(c) Hold the quill shaft (10) in position a nd remove the spline torque adapter.

(d) Install the crossbolt (6), the washer (9), and the nut (8).

(e) Safety the nut (8) with a new cotter pin (7).

(f) Safety the head of the crossbolt (6) with new 0.032-inch corrosion resistant
steel lockwire.

(20) Lubricate the drive chains. (L UBRICATION OF THE HORIZONTAL
STABILIZER CONSTANT SECTIO N, TASK 12-24-09-600-801)

(21) Remove the safety tags and close these circuit breakers:

AVIONICS, FLIGHT CONTROL DC BUS 1

Row Col Number Name

C 8 B1-693 AUTO PITCH TRIM 1 EMDC-02K1003
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AVIONICS, MISC DC BUS 2

Row Col Number Name

F 3 B1-507 PRIMARY HORIZ STAB TRIM

OVERHEAD, RIGHT EMER DC BUS

Row Col Number Name

E 26 B1-694 AUTO PITCH TRIM 2

(22) Remove the “DO NOT OPERATE” tag from the horizontal stabilizer suitcase handles on the control pedestal.

(23) Do a test of the horizontal stabilizer range of movement. (FUNCTIONAL TEST
OF THE HORIZONTAL STABILIZER RANGE OF MOVEMENT, TASK 27-40- 00-710-802)

H. Lubricate the horizontal stabilizer actu ators. (SCI 27-3 - MD-11 HORIZONTAL STABILIZER ACTUATOR LUBRICATION)

I. Job Close-up - Horizontal Stabilizer Actuator Test

(1) Remove all the tools and equipment from th e work area. Make sure the area is
clean.

(2) Close this access panel:

Number Name/Location

311AB AFT FUSELAGE EMDC-02K1003
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BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page A88 SCI 27-8 - MD-11 HORIZONTAL STAB ILIZER ACTUATOR WEAR CHECK (cont’d)

Figure 1

E

LEGEND:

1

. PA IMAft Y TA IM

CONTROL VALVE

CAG (IG OS)**082 27~89** **1**MDC-02K1003
Revision E

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page A89 SCI 27-8 - MD-11 HORIZONTAL STAB ILIZER ACTUATOR WEAR CHECK (cont’d)

Figure 2

E

A AND B DIMENSIONS MUST BE EQUAL OR LESS THAN 0.15 in. (3.8 mm) DIFFERENCE.

A

LEGEND:

2. LEFT ACTUATOR
4. LEFT ACME NUT SPROCKET
5. RIGHT ACME NUT SPROCKET 16. DRIVE CHAIN IDLER SPROCKET

CAGIIGDS) 8 AFT PRESSURE BULKHEAD

NOTE: MEASURE DIMENSIONS A, B, C AND D FROM THE AFT FACE OF LIFTING LUGS TO THE AFT PRESSURE BULKHEAD C AND D DIMENSIONS MUST BE EQUAL OR LESS THAN 0.15 in. (3.8 mm) DIFFERENCE.

5 

## t

A

MD-11 WEAR CHECK F2MDC-02K1003
Revision E

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page A90 SCI 27-8 - MD-11 HORIZONTAL STAB ILIZER ACTUATOR WEAR CHECK (cont’d)

Figure 3

E

30.19-30.69 l769.4-779.5mm) LEFT ACTUATOR

BOTTOM OF ACME SCREW STOP

LEFT ACME NUT SPROCKET

VIEW 

### A-A

VIEW LOOKING FORWARD

TO TOP OF NUT 30.29-30.69 !769.4-779.5m ml RIGHT ACTUATOR

BOTTOM OF ACME SCREW SERRATIONS 

# L RIGHTACME

### ~·:>.L_j'-":j' /NUT SPROCKET 

# r

MD-11 WEAR CHECK F3MDC-02K1003
Revision E

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page A91 SCI 27-8 - MD-11 HORIZONTAL STAB ILIZER ACTUATOR WEAR CHECK (cont’d)

Figure 4

E

LEGEND ·**·** LEFT ACTUt.TOR 

### 4:**~~~~~~~~WJ~R** S SPROCKET

.**~~QA~CmE** NUT

S. CROSS BOLT
7 · COTIER Pll4 8. NU T 9 · WASHER I O. QU I L L SHAFT

CAG(IGDS) II. CUP**: ~~~~** **UCKL E**  14

. NUT

1&. WAS HER

I S

.**~:~v~C~~~ IN**  ID L ER

17

. DRIVE CHA I N
18

. CHAIN GUARD 19

. CHAIN GUIDE VIEW C

NOTE:
R GHT S I DE I S LE FT S I DE I S TSHOWN HE SAME. V IE W A

DB 2

- 27-0 893BMDC-02K1003
Revision E

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page A92 SCI 27-8 - MD-11 HORIZONTAL STAB ILIZER ACTUATOR WEAR CHECK (cont’d)

Figure 5

E

RESTRAINT

LEGEND·

;· LEFT**~CTUATOR**
4**~~~~~~~~U~JOR** SPROCKET T

5. RIGHT ACME N
17. SPROCKET UT DRIVE CHAIN HORIZONTAL STABILIZER ATTACH LUG

THUMB SCREW

FORCE INDICATOR 5

DRIVE ASSEMBLY

082-27-08948 S000624463 1V2MDC-02K1003
Revision E

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page A93 SCI 27-8 - MD-11 HORIZONTAL STAB ILIZER ACTUATOR WEAR CHECK (cont’d)

6. Is test equipment needed?

A list of the required fixtures, tools, and test and support equipment can be found in paragraph 2.A. of the wear check procedure in number 5 above.

7. What is pass/fail criteria?

The pass/fail criteria can be found in paragra phs 2.G.(8) and 2.G.(12) of the actuator wear check procedure in number 5 above.

8. What is SCI interval?

The actuator wear check shall be performed at intervals not to exceed 15,000 flight hours. EMDC-02K1003
Revision K

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page A94 SCI 32-1 – TRIJET MAIN LANDING GEAR TRUCK BEAM PIVOT BOLT
LUBRICATION (Airplanes that visit Short Wavelength Roughness Level 2 Runways)

1. What model does this SCI apply to?

DC-10, MD-10, MD-11 series aircraft with visits to Short Wavelength Roughness (SWR) Level 2 Runways, as defined in the latest revisions of Service Letters DC-10-SL-32- 115, MD-10-SL-32-111 and MD-11-SL-32-120.

2. What part or LRU is being checked?

Left and Right Main Landing Gear Truck B eam Pivot Joint – Pivot Bolt and Pivot Bolt Bushings

3. What failure mode is being looked for?

A check for a failure mode does not apply. Th is SCI provides a lubrication procedure for the pivot bolt and pivot bolt bushings.

4. How is it found?

Not Applicable

5. What tasks are to be performed?

Lubricate the Truck Beam Pivot Bolt Attach Points on the Left and Right Main Landing Gear Strut and Main Landing G ear Truck per the AMM.

DC-10 AMM Reference 12-21-01 MD-10 AMM Reference 12-21-01

MD-11 AMM Reference 12-21

6. Is test equipment needed?

No test equipment is required.

7. What is pass/fail criteria?

This is a lubrication servicing proced ure; pass/fail crite ria do not apply.

8. What is SCI interval?

The pivot bolts on both main landing gear truc k beams are to be lubricated within 10 cycles before and within 10 cycles after each visit to a SWR Level 2 runway. After completion of the lubrication within 10 cycles before and after each SWR Level 2 visit,
return to MPD lubrication interval. KMDC-02K1003
Revision K

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page A95 SCI 32-1 – TRIJET MAIN LANDING GEAR TRUCK BEAM PIVOT BOLT
LUBRICATION (cont’d)

If the pivot bolts are not lubr icated within 10 cycles befo re a visit to a SWR Level 2 runway, then lubricate the pi vot bolts within 10 cycles af ter that SWR Level 2 runway visit. Repeat lubrication every 30 cycles thereafter until eith er the pivot bolt and bushings are inspected in accordance with SC I 32-2, or the pivot bolt and bushings are
overhauled. EMDC-02K1003
Revision J

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page A96 SCI 32-2 – TRIJET MAIN LANDING GEAR TRUCK BEAM PIVOT JOINT
INSPECTION (Airplanes with Short Wavelength Roughne ss Level 2 Runway Visits since last MLG Overhaul or Pivot Joint Inspection)

1. What model does this SCI apply to?

DC-10, MD-10, MD-11 series aircraft with visits to Short Wavelength Roughness (SWR) Level 2 Runways as defined in the latest revisions of Service Letters DC-10-SL-32-115,
MD-10-SL-32-111 and MD-11-SL-32-120.

2. What part or LRU is being checked?

Left and Right Main Landing Gear Truck B eam Pivot Joint – Pivot Bolt and Pivot Bolt Bushings

3. What failure mode is being looked for?

This SCI checks the pivot bolt and bushing for wear and heat damage. A check is being performed to make certain that the pivot bo lt and pivot bolt bushings have not exceeded
their service limits.

4. How is it found?

A detailed inspection of the pi vot bolt and pivot bolt bushing.

5. What tasks are to be performed?

Inspect the Pivot Bolt a nd Pivot Bolt Bushings

1. Remove the left or right main gear pivot bolt for inspection

a. Use AMM 32-12-01 “Removal/Installation Ma in Gear Truck Beam and Axle” for
the DC-10 and MD-10 fleet to remo ve the pivot bolt for inspection.

b. Use AMM 32-12-20 Task 32-12-20-000-801 “Rem oval of the Main Landing Gear Truck Assembly” for the MD-11 fleet to remove the pivot bolt for inspection.

2. Do a detailed inspection of the pivot bolt and bushings

a. Do a detailed inspection of the outer diam eter of the pivot bolt. If cracks are found in the pivot bolt, or if the pivo t bolt has bronze transfer, corrosion, or damage to the chrome plate, replace the pivot bolt with a new, overhauled, or serviceable pivot bolt before further flight. If bolt sh ank is less than 5.496" in diameter replace the pivot bolt with a new, overhauled, or serviceable pivot pin before further flight. EMDC-02K1003
Revision J

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page A97 SCI 32-2 – TRIJET MAIN LANDING GEAR TRUCK BEAM PIVOT JOINT
INSPECTION (cont’d)

b Do a detailed inspection of the pivot bolt bushings in the main landing gear truck beam assembly and the strut assembly including checking for bushing rotation or migration. Verify that the bushings longitudinal lubrication groove
is at the bottom of bore within +/- 5 degrees of vertical centerline at the bottom of bore. Verify all lubrication pa ssages are clear and have the ability to flow grease.
3. Return landing gear to serviceable condition

a. Use AMM 32-12-01 “Removal/Installation Main Gear Truck Beam and Axle”
for the DC-10 and MD-10 fleet

b. Use AMM 32-12-20 Task 32-12-20-400-801 “Installation of the Main Landing Gear Truck Assembly” for the MD-11 fleet

4. Repeat steps 1 through 3 for the opposite side main landing gear.

6. Is test equipment needed?

No test equipment is required.

7. What is pass/fail criteria?

Failure of the inspection is if cracks are found in the pivot bolt, or if the pivot bolt exhibits bronze transfer, corrosion, or damage to the chrome plate, bushings out of tolerance, else the inspection passes.

8. What is SCI interval?

Inspection of the pivot bolts is to be done on or before 500 SWR Level 2 Runway landings or 24 months of first SWR Level 2 ru nway landing, which ever comes first, after MLG overhaul or Main Landing Gear Truck Beam Pivot Joint Inspection (SCI 32-2). EMDC-02K1003
Revision J

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page A98 SCI 33-1 – MD-10 Map Light Assemblies

1. What model does this SCI apply to?

MD-10 Series with P/ N 2LA005916-XX installed

2. What part or LRU is being checked?

A functional/inspection check of the Map Light Assemblies

3. What failure mode is being looked for?

To detect broken light bulb housing and the resultant exposed power contactor.

4. How is it found?

Perform inspection and replacement per 5 below.

5. What tasks are to be performed?

Inspect per Aircraft Modifi cation Letter MD-10-AML-33-101.

6. Is test equipment needed?

No test equipment is required.

7. What is pass/fail criteria?

Pass: No cracks, damaged or broken component s (light bulb housing) or chafed/damaged map light assembly wires.

8. What is SCI interval?

All intervals prior to, but not to exceed, 700 flight hours until terminating action is accomplished per MD-10-AML-33-101 JMDC-02K1003
Revision K

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page A99 SCI 34-4 – FUNCTIONAL TEST OF THE CAPTAIN AND FIRST OFFICER’S
ALTIMETER

1. What model does this SCI apply to? DC-10 series, MD-10 series, MD-11 series that are approved for flying Reduced Vertical Separation Minimum (RVSM) airspace.

2. What part or LRU is being checked? DC-10 andMD-11: Air Data Computer
MD-10: Air Data Module

3. What failure mode is being looked for? The failure mode tested is transducer degrad ation 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 CAPTAIN’ S AND FIRST OFFI CER’S ALTIMETER
1. Job Set-up:

a. Open the circuit breakers referenc ed in the following AMM tasks:
i. DC-10: ADJUSTMENT/TEST PITOT STATIC SYSTEMS 34-11-00 (Page Block 200).
ii. MD-10: PITOT STATIC SYSTEM LEAK TEST 34-16-00 (P/B 500).
iii. MD-11: FUNCTIONAL CHECK OF TH E PITOT STATIC SYSTEM TASK
34-11-00-720-801.
b. Apply aircraft el ectrical power.
i. DC-10: EXTERNAL POWER – DES CRIPTION AND OPERATION 24-40- 00 (P/B 001).
ii. MD-10: EXTERNAL POWER – MAINTENANCE PRACTICES 24-40-00 (P/B 200).
iii. MD-11: ENERGIZE AIRCRAFT ELEC TRICAL POWER SYSTEM TASK
24-40-00-861-801.

c. Connect the test equipment as follows:
i. On the air data tester ATC control panel, place the ATC MODE SELECT switch in the STBY position.
ii. DC-10 ONLY:
1. Set the Captain’s and First officer’s static selector valve to NORM position.
2. On the Overhead Panel, se t the CADC switch to Norm.
iii. MD-10: On the Captain’s and First Of ficer’s Gusset Panels, set the CADC switch light off.
iv. MD-11:
1. Set the Captain’s and First officer’s static selector valve to NORM position.
2. On the Captain’s and First Officer’s Gusset Panels, set the CADC switch light off. KMDC-02K1003
Revision K

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page A100 SCI 34-4 – 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 BE COME CLOGGED WITH TAPE RESIDUE, INCORRECT AIRSPEED-SENSING
ANDALTITUDE-SENSING SIGNALS CAN OCCUR. THIS
CAN CAUSE DANGEROUS FL IGHT CONDITIONS.

v. Seal the captain’s and first officer’s p itot tube drain holes with red polyester tape or other suitable device.
vi. Connect the air data tester to the capta in’s and first officer’s pitot tube.
vii. Connect the air data tester to the captain ’s and first officer’s static ports using suitable adapter.
viii. Seal the opposite side static ports usi ng 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 CONT ROL SURFACES. THE TEST
CAN CAUSE THE AIRCRAFT CONT ROL 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 ALTITU DE, 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 TH E ATMOSPHERE FROM THE
PITOT/STATIC LINES WHILE THE AIR DATA TESTER IS
CONNECTED. DO NOT LET THE ST ATIC PRESSURE BE MORE
THAN THE PITOT PRESSURE. THIS WILL HELP PREVENT DAMAGE TO THE EQUIPMENT.

2. Do the functional test of the Captain’s a nd 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:
1. DC-10 and MD-10: The altitude shown on the captain’s altimeter must be 41,000 feet (12,497 meters) ± 75 feet (23 meters).
2. MD-11: The altitude shown on the captain’s altimeter must 40,955 feet (12,483 meters) ± 75 feet (23 meters). KMDC-02K1003
Revision K

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page A101 SCI 34-4 – FUNCTIONAL TEST OF THE CAPTAIN AND FIRST OFFICER’S ALTIMETER (cont’d)

ii. Captain’s airspeed requirements:
1. DC-10 and MD-10: The airspeed shown on the captain’s airspeed
indication must be 105 knots ± 4 knots.
2. MD-11: The airspeed shown on the capta in’s airspeed indication must be
104 knots ± 4 knots.
d. On the first officer’s instrument panel:
i. First Officer’s altitude requirements:
1. DC-10 and MD-10: The altitude show n on the First Officer’s altimeter must be 41,000 feet (12,497 meters ) ± 75 feet (23 meters).
2. MD-11: The altitude shown on the Fi rst Officer’s altimeter must be 40,955 feet (12,483 meters) ± 75 feet (23 meters).
ii. First Officer’s airspeed requirements:
1. DC-10 and MD-10: The airspeed show n on the First Officer’s airspeed
indication must be 105 knots ± 4 knots.
2. MD-11: The airspeed shown on the Fi rst Officer’s airspeed indication
must be 104 knots ± 4 knots.
3. Job Close-up:

a. Remove the test equipment as follows:
i. Disconnect the air data tester from the cap tain’s pitot tube and captain’s static port. ii. Remove tape from the captain’s pitot tube drain holes a nd 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 open ed in Job Set-up.
d. Remove external power from the aircraft.
i. DC-10: EXTERNAL POWER – DES CRIPTION AND OPERATION 24-40- 00 (P/B 001).
ii. MD-10: EXTERNAL POWER – MAINTENANCE PRACTICES 24-40-00 (P/B 200).
iii. MD-11: REMOVE ELECTRICAL POWER TASK 24-40-00-862-801.

6. Is test equipment needed?

 Tester, Air Data: must have a maximum altitu de 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 Criteria:

 Captain’s altitude requirements,

o DC-10 and MD-10: 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). KMDC-02K1003
Revision K

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page A102 SCI 34-4 – FUNCTIONAL TEST OF THE CAPTAIN AND FIRST OFFICER’S ALTIMETER (cont’d)

o MD-11: The altitude shown on the ca ptain’s altimeter must be 40,955 feet (12,483 meters) ± 75 feet (23 meters) at 41,000 feet (12,497 meters).

 Captain’s airspeed requirements,

o DC-10 and MD-10: The airspeed shown on the captain’s airspeed indication
must be 105 knots ± 4 knots at 105 knots.

o MD-11: The airspeed shown on the capta in’s airspeed indication must be 104
knots ± 4 knots at 105 knots.

 First Officer’s altitude requirements,

o DC-10 and MD-10: 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 MD-11: The altitude shown on the Fi rst Officer’s altimeter must be 40,955 feet (12,483 meters) ± 75 feet (23 mete rs) at 41,000 feet (12,497 meters).

 First Officer’s airspeed requirements,

o DC-10 and MD-10: The airspeed show n on the First Officer’s airspeed
indication must be 105 knots ± 4 knots at 105 knots.

o MD-11: The airspeed shown on the First Officer’s airspeed indication must be
104 knots ± 4 knots at 105 knots.

Fail: Is any of the altitude and airspeed requi rements are outside the tolerances listed in the pass criteria.

8. What is SCI interval?
MD-10/MD-11: Intervals not to exceed 48 months.
DC-10: Intervals not to exceed 24 months. KMDC-02K1003
Revision A

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page B1 Appendix B

Critical Design Configuration C ontrol Limitations (CDCCLs)MDC-02K1003
Revision E

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page B2 TRIJET CRITICAL DESIGN CONFIGURATION CONTROL LIMITATIONS

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

Critical Design Configuration Control Limitations (CDCCLs) are a means of notifying the FAA, operators, and maintenance facili ties of certain design configur ation aspects that cannot be changed without violating the design intent, potentially making the airplane non-compliant with FAR 25.981(b). Therefore, these co nfiguration aspects must be cont rolled such that they remain in the configuration as sp ecified in each CDCCL.

The following CDCCLs are features that Boeing has 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 rati ng 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 change or repair to any part of the ai rcraft 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 time 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 trijet Type Certif icate are only valid when the design configuration aspects specified by these CDCCLs are maintained as stated

. The configuration control limitations are mandatory and cannot be change d 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 cont rol 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 visibl e to airline personnel; therefore each CDCCL configuration control information must be in cluded in appropriate Operator's maintenance
documentation.

All maintenance and repair instructions provide d by Boeing have been up dated where required to ensure compatibility with these design limitations. EMDC-02K1003
Revision A

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page B3 Each CDCCL specified herein includes the name of the system in which the CDCCL is needed, and the following information:

1. What model trijet doe s this CDCCL apply to?

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

3. What characteristic of the desi gn configuration for this item mu st 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 ther e an applicable Service Bulletin or Service Rework package required for some aircraft?

6. When does this CDCCL become effective?MDC-02K1003
Revision H

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page B4 CDCCL 20-1 - Trijet Repair Wire Gauges

1. What trijet model does this CDCCL apply to?

DC-10 Series
MD-10 Series
MD-11 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 config uration for this item must be retained under control of this Limitation, and why?

Adverse excessive temperatures that coul d result from wire arcing events are characterized for a limited, known se t 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 compliance with this CDCCL at delivery from the OEM? If not, is there an applicable Service Bulletin or S ervice Rework package required for some aircraft?

DC-10 Series All airplane type designs comply. MD-10 Series All airpla ne type designs comply MD-11 Series All airpla ne type designs comply

6. When does this CDCCL become effective?

This CDCCL becomes effective for all repairs performed after August 1, 2006. HMDC-02K1003
Revision A

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page B5 CDCCL 20-2 - Trijet FQIS Wire Isolation

1. What trijet model does this CDCCL apply to?

DC-10 Series
MD-10 Series
MD-11 Series

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

Fuel Quantity Indication System (FQIS) wiring.

3. What characteristic of the design config uration 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 ai rcraft wiring or have an integral physical barrier (as part of the approved FQIS wire construction).

FQIS Wire Bundle Definition

DC-10/KC-10/KDC-10 - Master Indicator to Tank entry points
MD-10 – Fuel Quantity Processor Unit (FQPU) to Tank entry points

MD-11 – Standard Electronic Module (SEM) to Tank entry points

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

DC-10 Series All airplane type designs comply. MD-10 Series All airpla ne type designs comply. MD-11 Series All airpla ne type designs comply.

6. When does this CDCCL become effective?

This CDCCL becomes effective for all repairs performed after August 1, 2006.MDC-02K1003
Revision J

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page B6 CDCCL 20-3 – Trijet Fuel Pump Conduit Sleeves

1. What trijet model does this CDCCL apply to?

DC-10 Series
MD-10 Series
MD-11 Series

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

Fuel pump conduit.

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

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

4. What is the specific Limitation?

Teflon® hoses must be installed as a liner in metal fuel pump conduits per OEM drawings or AMM or SWPM or any combination of those.

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

DC-10 Series No, not all DC-10 type desi gns complied at time of delivery; see
below for Service Bulletin information:

Service Bulletin DC10-24-123 revi sion 2 Change Notice 1 dated
8/21/1984 or later DC-10 Series 10, 15, 30, 40 and KC-10A Service Rework Drawing WNP7003
Installs Teflon® liner around wire s in fuel boost pump conduits.

Service Bulletin DC10-24-128 re vision New dated 1/19/1984 or
later
DC-10 Series 30 Service Rework Drawing WGP7004
Installs Teflon® liner around wires in fuel boost pump conduits for Aft Supplemental Fuel Tank.

DC-10 Series 10, 15, 30, 40 and KC -10A may install alternate conduit tubing with Teflon® liners installed per Service Rework Drawing SR10280079 as an alternat e method of compliance to JMDC-02K1003
Revision J

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page B7 CDCCL 20-3 – Trijet Fuel Pump Conduit Sleeves (cont’d) DC-10-24-123 and DC10-24-128 service bulletins. MD-10 Series All airpla ne type designs comply. MD-11 Series All airpla ne type designs comply.

6. When does this CDCCL become effective?

This CDCCL becomes effective for all repairs performed after August 1, 2006. JMDC-02K1003
Revision A

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page B8 CDCCL 20-4 - Trijet In-Tank Wire Splices

1. What trijet model does this CDCCL apply to?

DC-10 Series
MD-10 Series
MD-11 Series

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

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

 Wiring going to AC and DC fuel pumps.

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

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

This does not include wiring inside a LRU.

3. What characteristic of the design config uration 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 a nd/or breach of the conduit assembly.

Improper shielding/insulation at the splice coul d 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 condui ts that are in the fuel tank.

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

DC-10 Series All airplane type designs comply. MD-10 Series All airpla ne type designs comply. MD-11 Series All airpla ne type designs comply.MDC-02K1003
Revision A

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page B9 CDCCL 20-4 - Trijet In-Tank Wire Splices (cont’d)

6. When does this CDCCL become effective?

This CDCCL becomes effective for all repairs performed after August 1, 2006.MDC-02K1003
Revision A

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page B10 CDCCL 20-5 – Trijet Repair Wire Types

1. What trijet model does this CDCCL apply to?

DC-10 Series
MD-10 Series
MD-11 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 config uration for this item must be retained under control of this Limitation, and why?

Adverse excessive temperatures that coul d result from wire arcing events are characterized for a limited, known set of OEM-previously approved wire types.

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)

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

DC-10 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-10 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-11 Series Aircraft as originally built with previously approved wire types are acceptable. New repairs should onl y be made with OEM approved wire types.MDC-02K1003
Revision A

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page B11 CDCCL 20-5 – Trijet Repair Wire Types (cont’d)

6. When does this CDCCL become effective?

This CDCCL becomes effective for all repairs performed after August 1, 2006.MDC-02K1003
Revision H

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page B12 CDCCL 20-6 - Trijet Wire Installations

1. What trijet model does this CDCCL apply to?

DC-10 Series
MD-10 Series
MD-11 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 config uration 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 compliance with this CDCCL at delivery from the OEM? If not, is there an applicable Service Bulletin or S ervice Rework package required for some aircraft?

DC-10 Series All aircraft type designs comply.
MD-10 Series All aircraft type designs comply.
MD-11 Series All aircraft type designs comply.

6. When does this CDCCL become effective?

This CDCCL becomes effective for all repairs performed after August 1, 2006. HMDC-02K1003
Revision A

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page B13 CDCCL 20-7 - Trijet Prohibition of Power Feed er Splices in Areas Above Fuel Tanks

1. What trijet model does this CDCCL apply to?

DC-10 Series
MD-10 Series
MD-11 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 config uration for this item must be retained under control of this Limitation, and why?

Maintain wire continuity over fuel tanks wi thout 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 maintain ed without splices. Any needed repair splice need 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 compliance with this CDCCL at delivery from the OEM? If not, is there an applicable Service Bulletin or S ervice Rework package required for some aircraft?

DC-10 Series All aircraft type designs comply.
MD-10 Series All aircraft type designs comply.
MD-11 Series All aircraft type designs comply.

6. When does this CDCCL become effective?

This CDCCL becomes effective for all repairs performed after August 1, 2006.MDC-02K1003
Revision H

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page B14 CDCCL 20-8 - Trijet Fuel Tank Access Door Bonding

1. What trijet model does this CDCCL apply to?

DC-10 Series
MD-10 Series
MD-11 Series

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

All fuel tank access doors.

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

Electrical current paths are defined by th e 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 curre nt 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 eff ectiveness of the conductive paths depends on specific surface treatments, sealants, sealing pr ocedures, seals, o-rings, fastener types, materials, conductive rubstrips, interfer ence fit fasteners, and coatings.

The non-conductive features of th e door installation sh all 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 acro ss different interfaces could create hazardous ignition sources inside the tank.

4. What is the specific Limitation?

The conductive and non conductive path de sign which includes specific surface treatments, sealants, sealing procedures, seals, o-rings, fastener types, materials, conductive rubstrips, inte rference fit fasteners, and coatin gs must be maintained per OEM design data which includes Boeing design dr awings or the Boeing SRM or the Boeing AMM or Boeing approved repairs or any combination of those. H

HMDC-02K1003
Revision H

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page B15 CDCCL 20-8 - Trijet Fuel Tank Access Door Bonding (cont’d)

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

DC-10 Series All aircraft type designs comply.
MD-10 Series All aircraft type designs comply. MD-11 Series All aircraft type designs comply. All aircraft upgraded to expand fuel tank capacity in accordan ce with Service Bulletin MD11-28-
018 revision 2 dated 3/26/ 1993 or later also comply.

6. When does this CDCCL become effective?

This CDCCL becomes effective for all repairs performed after August 1, 2006.MDC-02K1003
Revision G

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page B16 CDCCL 20-9 – Trijet Wing Root A rea Lightning Protection

1. What trijet model does this CDCCL apply to?

DC-10 Series
MD-10 Series
MD-11 Series

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

Sheet metal or braided electrica l bonding conductors or straps in the wing leading edge area of the wing fillet connecting the ribs together an d connecting the ribs to the fuselage. Also the metal overbraid shielding on the wire harn esses in the wing root area for the MD-10, MD-11, and early DC-10 FQGS.

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

a. The intense electromagnetic field created by lightning current in th e wing root area is attenuated by a number of metallic straps between the wing forward section (leading edge) at the most inboard rib and the fuselage . The wire harnesses in the wing root area are further protected with metal overbraid sh ields, grounded at both ends. These straps and shields provide lightning pr otection to the aircraft fuel system equipment interfaced with the wires spanning the wing root area.

b. The straps must be conti nuous and unbroken, the low-resist ance electrical bonds at the two ends must be maintained. The overbraid must be continuous and undamaged by cuts, fraying, corrosion or other defects. The low-resistan ce bonds or grounds must be
maintained at both ends of the ove rbraid for it to be effective.

c. All replacement wires in the wing-root ar ea require lightning pr otection to prevent induced voltages and currents from contaminat ion and threatening other aircraft systems
in common wire harnesses in side the aircraft and wing.

4. What is the specific Limitation?

Do not alter or remove the wing root lightni ng protection straps a nd wire overbraids and shields. Any replacement wires introduced in this area must also be sh ielded/overbraided in the same manner with the overbraids grounded at both ends.MDC-02K1003
Revision G

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page B17 CDCCL 20-9 – Trijet Wing Root Area Shielding (cont’d)

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

- Early DC-10s did not compl y. Bonding straps and FQGS overbraid were installed by

service bulletin:

 SB DC10-28-062 R1 dated 10/16/1981 or later (installs conduit on fuel probe wires in wing root)

 SB DC10-53-109 R4 dated 10/7/1992 or later (installs bonding straps for extended fillet)

 SB DC10-53-111 R3 dated 8/24/1992 or later (installs bonding straps for conventional fillet)

 SB DC10-28-262 Rev 1 or later (installs “Roundit 2000NX EMI” (DMS 2379, Type 5, Class 4) sleeving on fuel probe wi res in wing root, alternate to SB DC10-28-062 R1)

- Later trijets had the bonding stra ps, and/or overbraid installed at the factory as originally

delivered.

6. When does this CDCCL become effective?

This CDCCL becomes effective for all repairs performed after August 1, 2006. GMDC-02K1003
Revision H

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page B18 CDCCL 20-10 – Trijet Fuel Tank Structural Design

1. What trijet model does this CDCCL apply to?

DC-10 Series
MD-10 Series
MD-11 Series

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

Fuel tank structure.

3. What characteristic of the design config uration 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. Speci fically the types of surface preparation prior to assembly and type s of fasteners used must assure that all mechanical joints and penetrations can hand le the lightning currents at the respective locations. The non-conductive features (anodi zing, priming, painting and sealing) also must be preserved, since they co uld be part of the design to direct current to the conductive parts, prevent arcing at specific lo cations or contain minor arcing.

4. What is the specific Limitation?

The conductive and non conductive path design which includes specific surface treatments, sealants, sealing procedures, fastener types, and coatings must be maintained per OEM design data which includes Boeing de sign drawings or th e Boeing SRM or the Boeing AMM or Boeing approved repair s or any combination of those.

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

DC-10 Series All aircraft type designs comply.
MD-10 Series All aircra ft type designs comply.
MD-11 Series All aircra ft type designs comply.

6. When does this CDCCL become effective?

This CDCCL becomes effective for all repairs performed after August 1, 2006. HMDC-02K1003
Revision H

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page B19 CDCCL 20-11 – MD-11 Maintenan ce of Winglet Bonds

1. What trijet model does this CDCCL apply to?

MD-11 Series with the expanded wing fuel tank

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

The electrical bonding provision s at the interfaces, bolts, an d fasteners where the winglet structure is attached to the wing.

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

Maintenance of the original bonding desi gn, and maintenance of the sealing and encapsulation to prevent spark ge neration or release into the fuel tank in case of lightning strikes to the winglet.

4. What is the specific Limitation?

The 17 bolts, attaching the winglet , that enter the fuel vapor ar ea, shall be installed with the proper electrical bonding under the heads and nuts per the OEM design. The exposed fasteners shall be encapsulated with sealant after tighten ing per OEM design.

The electrical bonding in the countersinks fo r the fasteners on the strap attaching the winglet skin to the wing skin at the leading edge and trailing edge shall be maintained in the OEM configuration.

The conductive and non conductive path de sign which includes specific surface treatments, sealants, sealing procedures, seals, o-rings, fastener types, materials, conductive rubstrips, inte rference fit fasteners, and coatin gs must be maintained per OEM design data which includes Boeing design dr awings or the Boeing AMM or Boeing SRM Boeing approved repairs or any combination of those.

During and after assembly, the type-design s ealant applications sh all be observed. The fastener areas shall be encapsula ted with sealant where required.

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

MD-11 Series All aircraft comply as orig inally delivered. A ll aircraft upgraded to expand fuel tank capacity in accordance with Service Bulletin
MD11-28-018 revision 2 dated 3/26 /1993 or later also comply. HMDC-02K1003
Revision H

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page B20 CDCCL 20-11 – MD-11 Maintenan ce of Winglet Bonds (cont’d)

6. When does this CDCCL become effective?

This CDCCL becomes effective for all repairs performed after August 1, 2006.MDC-02K1003
Revision H

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page B21 CDCCL 20-12 – MD-11 Maintenance of Tail Tank FQIS Wiring Overbraid

1. What trijet model does this CDCCL apply to?

MD-11 Series

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

Overbraids installed on tail tank FQIS system wiring (FQIS wiring is located within wire assembly number AGS9124).

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

The metal overbraid and/or DMS 2186 self adhering tape should be undamaged and exhibit no visible signs of deterioration. Damage and/or deterioration may reduce the shielding effectiveness of metallic overbrai d. Undamaged DMS 2186 self adhering tape is an indicator that the underlying meta llic overbraid is intact and undamaged.

4. What is the specific Limitation?

The metallic overbraiding and DMS 2186 self adhering tape (as ap plicable) shall be maintained per the original OEM type desi gn or repair per SWPM 20-10-01 or AMM 20-
30-01.

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

MD-11 Series All aircraft comply as originally delivered.

6. When does this CDCCL become effective?

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

HMDC-02K1003
Revision A

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page B22 CDCCL 20-13 - Trijet Wiring Near Fu el Tanks and Fuel Pipes

1. What trijet model does this CDCCL apply to?

DC-10 Series
MD-10 Series
MD-11 Series

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

All wiring used near the fu el tanks and fuel pipes.

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

Proper wire assembly and wire installati on techniques, wire bundl e cleanliness, and adherence to the following requirements w ill minimize the likelihood that severe overheat or burn-through events will occur near fuel tank s 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 Manua l (Boeing Document Number D6-82481),
Section 20-00-06.

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

DC-10 Series All aircraft type designs comply.
MD-10 Series All aircra ft type designs comply.
MD-11 Series All aircra ft type designs comply.

6. When does this CDCCL become effective?

This CDCCL becomes effective for all repairs performed after August 1, 2006.MDC-02K1003
Revision J

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page B23 CDCCL 20-14 – Trijet Float Switch Conduit Sleeves

1. What trijet model does this CDCCL apply to?

DC-10 Series with alternat e conduit installed per SR10280079.
MD-10 Series
MD-11 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 config uration 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 shor ting to the conduit wall.

4. What is the specific Limitation?

Any replacement conduit must have Teflon® hoses installed as built by the OEM or OEM Drawings or AMM or SWPM or any combination of those.

Exception: MD-11 float switches installed in the Upper Auxiliary Tank are installed in bare metallic conduit (Conduit P/N AEP8600-505/-506/-513/-514).

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

DC-10 Series All aircraft type designs complied with intent when delivered with integral liner conduit. DC-10 Series 10, 15, 30, 40 and KC -10A may install alternate conduit tubing with Teflon® liners installed per Service Rework Drawing SR10280079.
MD-10 Series All aircraft type designs comply.
MD-11 Series All aircraft type designs comply.

6. When does this CDCCL become effective?

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

JMDC-02K1003
Revision F

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page B24 CDCCL 20-15 – Trijet Float and Pressure Sw itch Circuit Fuse Sleeves

1. What model Trijet does this CDCCL apply to?

DC-10 Series
MD-10 Series
MD-11 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 pene tration point on float and pressure switch
circuits.

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

The fuse must be installe d 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 the power lead from other wiring and provide additional wire protection from chafing and shorting.

For fuse installations that incorporate a drip loop near the fuse, sl eeving 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 as defined in the applicable service bulletin or Boeing approved part per SWPM 20-20-02. Any replacement or repair of wiring or sleev ing from the fuse to tank penetration point must have DMS 2109 or DMS 2379 Type 4 sleeving installed per SWPM 20-10-01.

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 applicable Service Bulletin or Service Rework package required for some aircraft?

DC-10 Series Service Bulletin DC 10-28-252 revision New or later
MD-10 Series Service Bulletin DC10-28-252 revision New or later
MD-11 Series Service Bulletin MD11-28-132 revision New or later

6. When does this CDCCL become effective?

This CDCCL becomes effective after incorp oration of Service Bulletin DC10-28-252 or MD11-28-132, as applicable. F F

FMDC-02K1003
Revision A

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page B25 CDCCL 28-1 – Trijet Prohibit Safety Wire, Lockwire, Safety Cable or Cotter Pins Inside
Fuel Tanks

1. What trijet model does this CDCCL apply to?

DC-10 Series
MD-10 Series
MD-11 Series

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

Inside airplane fuel tanks.

3. What characteristic of the design config uration 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 and co tter pins could become loose and have the potential to become FOD (for eign object debris) and cause fi lament heating, or arcing.

4. What is the specific Limitation?

Safety wire, lockwire, safety cable or cotter pins are not to be installed inside the fuel tanks. Components or equipment installed inside fuel tanks sh all not use safety wire or cotter pins for hardware retention. Safety wi re, lockwire, safety cable or 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 compliance with this CDCCL at delivery from the OEM? If not, is there an applicable Service Bulletin or S ervice Rework package required for some aircraft?

DC-10 Series All airplane type designs comply. MD-10 Series All airplane type designs comply. MD-11 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-02K1003
Revision B

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page B26 CDCCL 28-2 - Trijet Fuel Pump (Boost or Transfer) and Housing Assemblies

1. What model trijet does this CDCCL apply to?

DC-10 Series
MD-10 Series
MD-11 Series

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

A. Fuel Booster Pump, Pumping Unit, Part Numbers 60-847-1A, 60-847-2, 60-847-3 and
60-847-4.
B. Fuel Booster Pump Housing Assembly, Part Numbers 60-843, 60-843M, 60-843-1, 60- 843-1M, 60-843-2, 60-843-2M, 60-845, 60-84 5M, 60-845-1, 60-845-1M, 60-845-2, and
60-845-2M.
C. Pump Inlet System Components

3. What characteristic of the design config uration 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 FO D ingestion, and

 prevent exposure to mercury

Faulty pump stators must be replaced in strict accordance with OEM documentation to protect the pump’s dry running and overheat performance as de monstrated in qualification

tests.

The pump must retain all features desi gned by the OEM to provide explosion proof properties. These include but are not limite d 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.

The pump must retain all OEM features of the inlet housing shape, clearances, and
materials as well as the materials of a ll other rotating components and stationary interfacing surfaces (reprime impellers, liners, pl ates, bearings, bearing assemblies, shafts, etc.).MDC-02K1003
Revision F

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page B27 CDCCL 28-2 - Trijet Fuel Pump (Boost or Transfer) and Housing Assemblies (cont’d)

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

Electrical connectors must be repaired or replaced in strict accordance with OEM documentation to protect against electrical failures and maintain explosion proof
characteristics.

The pump stator lead wire routing inside the pump must be installed in strict accordance
with OEM documentation so that it cannot cont act the rotor and charge the rotor which
could lead to an electrical arc outside of the pump’s explos ion proof volume.

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

4. What is the specific Limitation?

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

Part Number(s) CMM CMM Revision

60-847-1A,

60-847-2,
60-847-3
60-847-4 28-22-03 8

60-843-1, 60-843-2, 60-843-2M,

60-843-3 60-845-1, 60-845-2,
60-845-2M

60-845-3 28-22-01 5

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 housing assembl y, or their subcomponents to mercury is prohibited. FMDC-02K1003
Revision A

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page B28 CDCCL 28-2 - Trijet Fuel Pump (Boost or Transfer) and Housing Assemblies (cont’d)

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

DC-10 Series All aircraft type designs comply.
MD-10 Series All aircraft type designs comply.
MD-11 Series All aircraft type designs comply.

6. When does this CDCCL become effective?

This CDCCL becomes effective for all repairs performed after August 1, 2006.MDC-02K1003
Revision J

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page B29 CDCCL 28-3 – DC-10/MD-10 Fuel Pump (APU Start) and Housing Assemblies

1. What model trijet does this CDCCL apply to?

DC-10 Series
MD-10 Series

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

A. Fuel Pump Assembly, Part Number 16710-1.
B. Fuel Pump Housing Assemb ly, Part Numbers 16720-1, 16720-2.
C. Pump Inlet System Components

3. What characteristic of the design config uration 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 FO D ingestion, and

 prevent exposure to mercury.

The pump 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.

Faulty pump stators must be replaced in strict accordance with OEM documentation to protect the pump’s dry running and overheat performance as de monstrated in qualification

tests.

Electrical connectors must be repaired or replaced in strict accordance with OEM documentation to protect against electrical failures and maintain explosion proof
characteristics.

The pump stator lead wire routing inside the pump must be installed in strict accordance
with OEM documentation so that it cannot cont act the rotor and charge the rotor which could lead to an electrical arc outside of the pump’s explosion proof volume.MDC-02K1003
Revision J

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page B30 CDCCL 28-3 – DC-10/MD-10 Fuel Pump (APU Start) and Housing Assemblies (cont’d)

The pump must retain all OEM features of the inlet housing shape, clearances, and
materials as well as the materials of a ll other rotating components and stationary interfacing surfaces (reprime impellers, liners, pl ates, bearings, bearing assemblies, shafts, etc.).

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

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

4. What is the specific Limitation?

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

Part Number(s) CMM CMM Revision
16710-1 28-23-01 1 16720-1,
16720-2 28-23-02 10

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 housing assembl y, or their subcomponents to mercury is prohibited.

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

DC-10 Series All aircraft type designs comply.
MD-10 Series All aircraft type designs comply.

6. When does this CDCCL become effective?

This CDCCL becomes effective for all repairs performed after August 1, 2006. JMDC-02K1003
Revision E

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page B31 CDCCL 28-4 – KC-10 and KDC-10 Fuel Pump Assembly

1. What model trijet does this CDCCL apply to?

All KC-10 and KDC-10 airplanes.

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

A. Fuel Pump Assembly, Part Number RR12690.

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

CDCCL has been moved to Report MD C-09K1000 “KC-10A AND KDC-10 SPECIAL
COMPLIANCE ITEM REPORT SUPPLEMENT”

If the CDCCL is applicable, contact Boei ng Export Control to obtain a copy of the supplemental report.MDC-02K1003
Revision E

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page B32 CDCCL 28-4 – KC-10 and KDC-10 Fuel Pump Assembly (cont’d)

CDCCL has been moved to Report MD C-09K1000 “KC-10A AND KDC-10 SPECIAL
COMPLIANCE ITEM REPORT SUPPLEMENT”MDC-02K1003
Revision A

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page B33 CDCCL 28-5 – MD-11 Fuel Pump and Canister Assemblies

1. What model trijet does this CDCCL apply to?

MD-11 Series airplane s with optional 2,000 gallon forwar d auxiliary tanks(s) installed.

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

A. Fuel Pump, Type 8410, Part Number 568-1-27202, Mark -002.
B. Fuel Pump Canister, Type 9114, Pa rt Number 568-1-29104, Mark –001.
C. Pump Inlet System Components

3. What characteristic of the design config uration 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 FO D ingestion, and

 prevent exposure to mercury.

Faulty pump stator assemblies must be replaced or repaired in strict accordance with OEM documentation to protect the pump’s dr y running and overhea t performance as demonstrated in qualification tests.

The pump must retain all features desi gned by the OEM to provide explosion proof properties. These include but are not limited to : Bearing materials and clearances, canister materials and thickness, size of vent and coo ling holes and installati on of flame-arresting plates, and metal-to-metal faying surfaces.

The pump must retain all OEM features of the inlet housing shape, clearances, and
materials as well as the materials of a ll other rotating components and stationary interfacing surfaces (reprime impellers, liners, pl ates, bearings, bearing assemblies, shafts, etc.).

Pump inlet screens must be maintained as de signed by Boeing and/or OEM. This is to prevent FOD ingestion.MDC-02K1003
Revision B

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page B34 CDCCL 28-5 – MD-11 Fuel Pump and Canister Assemblies (Cont’d)

Electrical connectors must be repaired or replaced in strict accordance with OEM documentation to protect against electrical failures and maintain explosion proof
characteristics.

The pump stator lead wire routing inside the pump must be installed in strict accordance
with OEM documentation so that it cannot cont act the rotor and charge the rotor which
could lead to an electrical arc outside of the pump’s explos ion proof volume.

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

4. What is the specific Limitation?

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

Part Number(s) CMM CMM Revision
568-1-27202-002 28-21-51 11
568-1-29104-001 28-21-52 8

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 housing assembl y, or their subcomponents to mercury is prohibited.

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

MD-11 Series All aircraft type designs comply.

6. When does this CDCCL become effective?

This CDCCL becomes effective for all repairs performed after August 1, 2006.MDC-02K1003
Revision A

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page B35 CDCCL 28-6 – Trijet Fuel Pump (APU Start) Assembly

1. What model trijet does this CDCCL apply to?

DC-10 Series - aircraft that have incorp orated McDonnell Douglas/Douglas Aircraft Company DC-10 Service Bulletin 28-187 revision 1 dated 5/7/1990 or later. MD-10 Series - aircraft that have incorp orated McDonnell Douglas/Douglas Aircraft Company DC-10 Service Bulletin 28-187 revision 1 dated 5/7/1990 or later.
MD-11 Series

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

Fuel Pump Assembly, Part Number 218387.

3. What characteristic of the design config uration 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 FO D ingestion, and

 prevent exposure to mercury.

The pump must retain all features desi gned by the OEM to provide explosion proof properties. These include but are not limited to: Bearing materials and clearances, pump housing materials and thickness, size of vent and cooling holes, and metal-to-metal faying
surfaces.

Faulty pump stators must be replaced in strict accordance with OEM documentation to protect the pump’s dry running and overheat performance as de monstrated in qualification tests. In addition, Thermal Fuses must be replaced in strict accordance with OEM documentation each time motor stator winding is removed for repair to ensure repeated reinstallation of the same thermal fuse does not compromise the pump’s overheat protection.

Electrical connectors must be repaired or replaced in strict accordance with OEM documentation to protect against electrical failures and maintain explosion proof
characteristics.

The pump stator lead wire routing inside the pump must be installed in strict accordance
with OEM documentation so that it cannot cont act the rotor and charge the rotor which
could lead to an electrical arc outside of the pump’s explos ion proof volume.MDC-02K1003
Revision E

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page B36 CDCCL 28-6 – Trijet Fuel Pump (APU Start) Assembly (cont’d)

The pump must retain all OEM features of the inlet housing shape, clearances, and
materials as well as the materials of a ll other rotating components and stationary interfacing surfaces (impellers, liners, plates, b earings, bearing assemblies, shafts, etc.).

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

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

4. What is the specific Limitation?

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

Part Number(s) CMM CMM Revision
218387 28-20-02 12

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 housing assembl y, or their subcomponents to mercury is prohibited.

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

DC-10 Series All aircraft comply with incorporation of McDonnell Douglas/ Douglas Aircraft Company Servi ce Bulletin DC10-28-187 revision 1
dated 5/7/1990 or later and a fuel pump assembly that meets the requirements of this CDCCL. MD-10 Series All aircraft comply with incorporation of McDonnell Douglas/ Douglas Aircraft Company Servi ce Bulletin DC10-28-187 revision 1
dated 5/7/1990 or later and a fuel pump assembly that meets the requirements of this CDCCL. MD-11 Series All aircraft comply as originally delivered.

6. When does this CDCCL become effective?

This CDCCL becomes effective for all repairs performed after August 1, 2006. EMDC-02K1003
Revision E

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page B37 CDCCL 28-7 – DC-10 Fuel Quantity Master Indicators

1. What trijet model does this CDCCL apply to?

DC-10 Series

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

All DC-10 airplanes which utilize the follo wing fuel quantity ga uging system (FQGS) components:

 Master indicator P/N’s 217-003-xxx (where xxx is 001 thru 003, 005 thru 007, 011, 012, 016, 103/M, 105/M thru 107/M, 109/M, 111/M, 112/M, 114/M, 116/M thru 118/M, 126/M, and 130/M) for Parker/Gull FQGS installations

3. What characteristic of the design config uration 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 operationa l 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) list ed below or an FAA approved service
bulletin.

Part Number(s) CMM CMM Revision

217-003-001,
217-003-002 28-41-20 8 EMDC-02K1003
Revision E

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page B38 CDCCL 28-7 – DC-10 Fuel Quantity Master Indicators (cont’d)

Part Number(s) CMM CMM Revision

217-003-003, 217-003-009, 217-003-103, 217-003-103M,

217-003-109, 217-003-109M,

217-003-011, 217-003-012, 217-003-016, 217-003-111, 217-003-111M,

217-003-112, 217-003-112M,

217-003-116,
217-003-116M 28-41-20 8

217-003-005, 217-003-006, 217-003-007, 217-003-105, 217-003-105M,

217-003-106, 217-003-106M,

217-003-107, 217-003-107M,

217-003-114, 217-003-114M,

217-003-118,
217-003-118M 28-41-17 6

217-003-117, 217-003-117M,

217-003-130,
217-003-130M 28-41-24 2

217-003-126,
217-003-126M 217-003-132,
217-003-132M 28-41-25 2

Any deviation from the OEM’s CMM must be justified by the modifier and approved by
the FAA LA-ACO. EMDC-02K1003
Revision A

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page B39 CDCCL 28-7 – DC-10 Fuel Quantity Master Indicators (cont’d)

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

DC-10 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-02K1003
Revision J

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page B40 CDCCL 28-8 – MD-11 Fuel Quantity Standard El ectronic Module, Densitometer, MultiJunction Probe, and Ultrasonic Processor Drive Unit

1. What trijet model does this CDCCL apply to?

MD-11 Series

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

Fuel quantity gauging system (FQGS) Standa rd Electronic Module (SEM), Densitometer, Multi-Junction Probe (MJP), and Ultr asonic Processor Drive Unit (PDU).

 SEM P/N’s 367-040-074, 367-040-080, 367-040-081, 367-040-084 and 367-040-085 for Parker/Gull FQGS installations

 Densitometer P/N’s 180-022-001 for Pa rker/Gull FQGS installations

 MJP P/N’s 003-008-001 thru 003-008-006 an d 003-008-008 for Parker/Gull FQGS
installations

 Ultrasonic PDU P/N 366-026-001 for Parker/Gull FQGS installations

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

FQGS SEM, densitometer, MJP, and ultrasoni c PDU maintenance pr ocedures 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 SEM, densitometer, MJP, and ultrasonic PDU must be made in accordance with the OEM’s Component Mainte nance Manuals (CMMs) listed below or an FAA approved service bulletin.

Part Number(s) CMM CMM Revision (SEM)
367-040-073
367-040-074
367-040-080
367-040-081
367-040-083
367-040-084
367-040-085
367-040-086 28-40-88 11

(Densitometer)

180-022-001 28-40-87 5 JMDC-02K1003
Revision J

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page B41 CDCCL 28-8 – MD-11 Fuel Quantity Standard El ectronic Module, Densitometer, MultiJunction Probe, and Ultrasonic Processor Drive Unit (cont’d)

Part Number(s) CMM CMM Revision (MJP)

003-008-001 thru 003-008- 006, 003-008-008,
003-008-208 thru 003-008-
213 28-40-86 6

(Ultrasonic PDU)

366-026-001 28-41-63 1

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 compliance with this CDCCL at delivery from the OEM? If not, is there an applicable Service Bulletin or S ervice Rework package required for some aircraft?

MD-11 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-02K1003
Revision A

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page B42 CDCCL 28-9 – MD-10 Fuel Quantity Processor Unit

1. What trijet model does this CDCCL apply to?

MD-10 Series

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

Fuel quantity gauging system (FQGS) Fuel Quantity Processor Unit.

 FQPU P/N 30163-01 for Goodr ich FQGS installations

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

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

4. What is the specific Limitation?

Any repair to a FQGS FQPU must be made in accordance with the OEM’s engineering drawings and tested per the OEM’s production ATP, or an FAA approved service bulletin.

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

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

MD-10 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-02K1003
Revision A

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page C1 Appendix C

Airworthiness Limitation Instruction (ALIs)MDC-02K1003
Revision A

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page C2 TRIJET AIRWORTHINESS LIMIATION INSTRUCTIONS

For some trijet system functions, compliance wi th 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 Instruction (ALI s) are a means of detecting safety significant conditions, potentially making the airplane non-compliant with SFAR 88 and FAR 25.981(b). When an ALI detects such a condition, mainte nance action to correct it is required.

The terms of the trijet Type Certificate are onl y valid when associated checks specified by these ALIs are performed within the time intervals specified. ALIs are equivalent to one-star CMRs (per AC 25-19): The configur ation control checks and intervals specified are mandatory and cannot be changed, escalated, or deleted without 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 provide d by Boeing have been up dated where required to ensure compatibility with these inspections.MDC-02K1003
Revision A

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page C3 Each ALI specified herein includes the name of the system in which the ALI is needed, and the following information:

1. What model trijet does this ALI apply to?

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

3. What part, LRU or system ch aracteristic 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 inspec tion results to your local Boeing Field Service Representative. If the Boeing Field Service Representative is not available, you ma y send the report to:

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

Attn: Manager - Avionics & Electri cal Systems (Dept. L33) Service Engineering
Technical Services & Modifications
Mail Code: D800-0035MDC-02K1003
Revision A

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page C4 ALI 20-1 - Trijet Fuel Pump and Auxiliary Hydraulic Pump Circuit Breaker Reset

1. What trijet model does this ALI apply to?

DC-10 Series
MD-10 Series
MD-11 Series

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

All fuel pump and auxiliary hydraulic pump circuit breakers

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

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

4. How is it found?

Tripped fuel pump and auxiliary hydraulic pump circuit breakers 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 breaker(s) by following the applicable OEM troubleshooting procedures. Fault(s) that resulted in circuit breaker tr ip must be isolated and corrected prior to reset if the fault(s) o ccurred 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 brea ker(s) if the troubles hooting procedures are successfully completed, and problem has been corrected.

Fail - It is not safe to reset the circ uit breaker(s) if the troubleshooting procedures are not successfully completed.

8. What is the ALI accomplishment interval?

There is no fixed inspection interval. This ALI applies only when the open circuit
breaker condition occurs in service.MDC-02K1003
Revision A

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page C5 ALI 20-1 - Trijet Fuel Pump and Auxiliary Hydraulic Pump Circuit Breaker Reset (cont’d)

9. When does this AL I become effective?

August 2, 2006MDC-02K1003
Revision H

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page C6 ALI 20-2 - MD-11 Inspection of Tail Tank FQGS Wiring Overbraid

1. What trijet model does this ALI apply to?

MD-11 Series

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

Metallic overbraiding installed on tail tank FQIS wiring (FQIS wiring is located within wire assembly number AGS9124).

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

The metal overbraid and/or DMS 2186 self adhering tape should be continuous (in wrapped area), undamaged, and exhi bit no signs of deterioration.

4. How is it found?

Detailed inspection.

5. What checks are to be performed?

(a) Verify that DMS 2186 self adhering ta pe is undamaged and does not exhibit deterioration. See Figure (a). (b) Verify that metallic overbraid (in areas not covered by DMS 2186 self adhering tape) is undamaged and does not exhibit de terioration. See Figure (b).

Figure (a) DMS
2186

Ta p e DMS
2186

Ta p eMDC-02K1003
Revision H

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page C7 ALI 20-2 - MD-11 Inspection of Tail Tank FQGS Wiring Overbraid (cont’d)

Figure (b)

6. Is test equipment needed?

No.

7. What is the pass-fail criteria?

Pass - DMS 2186 self adhering tape and metallic overbraid (in areas not covered by “red wrap” tape) do not exhibit damage or deterioration.

Fail - DMS 2186 self adhering tape and metallic overbraid (in areas not covered by “red wrap” tape) exhibits damage or de terioration. Repair per SWPM 20-10-01

8. What is the ALI accomplishment interval?

5 years

9. When does this AL I become effective?

August 2, 2006 Metallic
Overbraid

HMDC-02K1003
Revision A

BOEING PROPRIETARY INFORMATION Copyright © - The Boeing Company - Unpublished Work Page D1 APPENDIX D - SHORT-TERM EXTENSIONS

Since SCIs and ALIs are based on analysis using AC 25-19 methodol ogy, 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 au thority (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 exceptional, 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 fo r the same SCI/ALI are not allowed.

o Extensions may not be used fo r fleet SCI/ALI escala tion 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 defi ned 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.