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## REPORT NO. MDC-94K9000



# MD-90

AIRWORTHINESS LIMITATIONS INSTRUCTIONS (ALI)



# REVISION 6

September 2011

### Report No. MDC-94K9000

INITIAL RELEASE November 1994 REVISION 6 September 2011



# MD-90 AIRWORTHINESS LIMITATIONS INSTRUCTIONS (ALI)

Vinh Bui Principal Specialist Structural Mechanics Design and Technology J. Tom Principal Specialist Structural Mechanics Design and Technology

The Airworthiness Limitations Instructions (ALI) is Federal Aviation Authority (FAA) approved and specifies maint enance required und er Sections 43.16 and 91.403 of the Federal Aviation Regulations unless an alternative program has been FAA approved. The release of this ALI wa s approved by the Manager, Los Angeles Aircraft Certification Office, Transport Airplane Directorate, on June 8, 2012

.

MCDONNELL DOUGLAS CORPORATION PROPTIETARY RIGHTS ARE INCLUDED IN THE INFORMATION DISCLOSED HEREIN. RECIPENT BY ACCEPTING THIS DOCUMENT AGREES THAT NEITHER THIS DOCUMENT NOR THE INFORMATION DISCLOSED HEREIN NOR ANY PART THEREOF SHALL BE REPRODUCED OR TRANSFERRED TO OTHER DOCUMENTS OR USED OR DISCLOSED TO OTHERS FOR MANUFACTURING OR FOR ANY OTHER PURPOSE EXCEPT AS SPECIFICALLY AUTHOIRIZED IN WRITING BY MCDONNELL DOUGLAS CORPORATION. UNPUBLISHED – ALL RIGHTS RESERVED UNDER COPYRIGHT LAWS.

### MDC-94K9000 

### MD-90 AIRWORTHINESS LIMITATIONS INSTRUCTIONS (ALI) RECORD OF REVISION

REV. NO ISSUE DATE DATE INSERTED BY REV. NO ISSUE DATE DATE INSERTED BY



### ORIG NOV. 94 NOV. 94 DAC

1 JAN. 95 JAN. 95 DAC

2 JUL. 96 JUL. 96 DAC

3 NOV. 97 NOV. 97 BCAG

4 OCT. 01 OCT. 01 BCAG

5 SEPT 02 SEPT 02 BCAG

6 SEPT 11

RETAIN THIS RECORD IN THE FRONT OF THIS REPORT. UPON RECEIPT OF REVISIONS, INSERT REVISED PAGES IN THE DOCUMENT AND ENTER REVISION NUMBER, DATE INSERTED AND INITIAL.

McDonnell Douglas Corporation Proprietary Information. Use or disclosure of THESE DATA SUBJECT TO RESTRICTIVE LEGEND ON TITLE PAGE OR FIRST PAGE. September 2011

### MD-90 MDC-94K9000 AIRWORTHINESS LIMITATIONS INSTRUCTIONS (ALI) LIST OF EFFECTIVE PAGES

LIST OF EFFECTIVE PAGES PAGE I September 2011 SECTION PAGE ISSUE DATE

Title 6 SEPT 11

Record of Revisions 6 SEPT 11

List of Effective Pages I 6 SEPT 11 II 6 SEPT 11 III 6 SEPT 11

Revision Summary R-1 6 SEPT 11 R-2 6 SEPT 11

Preface P-1 4 OCT 01

SECTION 1

Table of Contents TC-1 3 NOV 97

Safe-Life Limits A1-1 3 NOV 97 A1-2 3 NOV 97 A1-3 3 NOV 97 A1-4 3 NOV 97 A1-5 3 NOV 97 A1-6 3 NOV 97 A1-7 3 NOV 97 A1-8 3 NOV 97 A1-9 3 NOV 97

List of PSE’s B1-1 4 OCT 01 B1-2 4 OCT 01 B1-3 6 SEPT 11

PSE Inspection Requirements B2-1 6 SEPT 11 B2-2 4 OCT 01 B2-3 0 NOV 94 B2-4 0 NOV 94 B2-5 0 NOV 94 B2-6 4 OCT 01 B2-7 0 NOV 94 B2-8 0 NOV 94 B2-9 0 NOV 94 B2-10 0 NOV 94 B2-11 0 NOV 94 B2-12 0 NOV 94 B2-13 0 NOV 94 B2-14 4 OCT 01 B2-15 0 NOV 94 SECTION PAGE ISSUE DATE

PSE Inspection B2-16 0 NOV 94 Requirements B2-17 0 NOV 94 B2-18 0 NOV 94 B2-19 0 NOV 94 B2-20 0 NOV 94 B2-21 0 NOV 94 B2-22 0 NOV 94 B2-23 0 NOV 94 B2-24 0 NOV 94 B2-25 0 NOV 94 B2-26 0 NOV 94 B2-27 0 NOV 94 B2-28 0 NOV 94 B2-29 0 NOV 94 B2-30 0 NOV 94 B2-31 0 NOV 94 B2-32 4 OCT 01 B2-33 4 OCT 01 B2-34 4 OCT 01 B2-35 1 JAN 95 B2-36 1 JAN 95 B2-37 1 JAN 95 B2-38 4 OCT 01 B2-39 1 JAN 95 B2-40 1 JAN 95 B2-41 1 JAN 95 B2-42 1 JAN 95 B2-43 1 JAN 95 B2-44 6 SEPT 11 B2-45 1 JAN 95 B2-46 1 JAN 95 B2-47 1 JAN 95 B2-48 4 OCT 01 B2-49 4 OCT 01 B2-50 6 SEPT 11 B2-51 6 SEPT 11 B2-52 6 SEPT 11 B2-53 6 SEPT 11 B2-54 6 SEPT 11 B2-55 6 SEPT 11 B2-56 6 SEPT 11 B2-57 6 SEPT 11 B2-58 6 SEPT 11 B2-59 6 SEPT 11 B2-60 6 SEPT 11 B2-61 6 SEPT 11

### MD-90 MDC-94K9000 AIRWORTHINESS LIMITATIONS INSTRUCTIONS (ALI) LIST OF EFFECTIVE PAGES

LIST OF EFFECTIVE PAGES PAGE II September 2011 SECTION PAGE ISSUE DATE

B2-62 6 SEPT 11 B2-63 6 SEPT 11 PSE Inspection Requirements (Continued) B2-64 6 SEPT 11 B2-65 6 SEPT 11 B2-66 6 SEPT 11 B2-67 6 SEPT 11 B2-68 6 SEPT 11 B2-69 6 SEPT 11 B2-70 6 SEPT 11 B2-71 6 SEPT 11 B2-72 6 SEPT 11 B2-73 6 SEPT 11 B2-74 6 SEPT 11 B2-75 6 SEPT 11 B2-76 6 SEPT 11 B2-77 6 SEPT 11 B2-78 6 SEPT 11 B2-79 6 SEPT 11 B2-80 6 SEPT 11 B2-81 6 SEPT 11 B2-82 6 SEPT 11 B2-83 6 SEPT 11 B2-84 6 SEPT 11 B2-85 6 SEPT 11 B2-86 6 SEPT 11 B2-87 6 SEPT 11

C1-1 4 OCT 01 Reporting of Inspection Results C1-2 0 NOV 94

SECTION 2

Introduction P2-1 0 NOV 94

Table of Contents TC-2 6 SEPT 11 TC-3 6 SEPT 11

References RF-1 4 OCT 01

20-00-00 1 4 OCT 01

NDI Techniques and Procedures

53.12.09.1 1 6 SEPT 11 2 6 SEPT 11 3 6 SEPT 11 SECTION PAGE ISSUE DATE

53.12.09.1 4 6 SEPT 11 (Continued) 

### 5 6 SEPT 11 6 6 SEPT 11 7 6 SEPT 11 8 6 SEPT 11 9 6 SEPT 11 10 6 SEPT 11 11 6 SEPT 11

54.10.04.1 1 4 OCT 01 2 6 SEPT 11 3 4 OCT 01 4 6 SEPT 11 5 4 OCT 01 6 4 OCT 01 7 4 OCT 01 8 4 OCT 01 9 4 OCT 01 10 4 OCT 01 11 4 OCT 01

54.40.01.2 1 4 OCT 01 2 4 OCT 01

54.40.03.1 1 6 SEPT 11 2 4 OCT 01

54.40.03.2 1 4 OCT 01 2 4 OCT 01

54.40.04.1 1 5 SEP 02 2 4 OCT 01

55.11.01.1 1 6 SEPT 11 2 6 SEPT 11 3 6 SEPT 11 4 6 SEPT 11 5 6 SEPT 11 6 6 SEPT 11 7 6 SEPT 11 8 6 SEPT 11

### MD-90 MDC-94K9000 AIRWORTHINESS LIMITATIONS INSTRUCTIONS (ALI) LIST OF EFFECTIVE PAGES

LIST OF EFFECTIVE PAGES PAGE III September 2011 SECTION PAGE ISSUE DATE

SECTION 2 SUPPLEMENT



### Table of Contents TC-4 6 SEPT 11



### Equipment Utilization 2-0 1 6 SEPT 11



### Reference Standards 2-1 1 2 3 6 6 6 SEPT SEPT SEPT 11 11 11



### High Frequency Eddy Current Probes 2-2 1 6 SEPT 11



### Low Frequency Eddy Current Probes 2-3 1 6 SEPT 11



### Inspection Fixtures 2-4 1 6 SEPT 11



### Ultrasonic Transducers 2-5 1 6 SEPT 11

### MDC-94K9000 MD-90 AIRWORTHINESS LIMITATIONS INSTRUCTIONS (ALI) REVISION NO. 6 SUMMARY

McDonnell Douglas Corporation Proprietary Information. Use of disclosure of R1 Revision Date: September 2011

THESE DATA SUBJECT TO RESTRICTIVE LEGEND ON TITLE PAGE OR FIRST PAGE 

### PAGE NO. CHANGE

Section 1 PSE Inspection Requirements

B1-3 New PSE title added

B2-1 Typographical correction

B2-44 Replaced “MTF” with “PTF”

B2-50-51 Added new PSE description and illustration

B2-59 Revised art

B2-52-87 Repaginate due to new PSE

Section 2 NDI Techniques and Procedures

Table of Contents TC-2 TC-3 Added PSE numbers and titles for the added procedures New table of contents for Section 2 Supplement

53.12.09.1 Pages 1-11 Added new procedure

54.10.04.1 Pages. 2, 4 Corrected Header information.

54.40.03.1 Page. 1 Number changes on Goodrich documents.

55.11.01.1 Pages. 1-8 Added new procedure.

### MDC-94K9000 MD-90 AIRWORTHINESS LIMITATIONS INSTRUCTIONS (ALI) REVISION NO. 6 SUMMARY

McDonnell Douglas Corporation Proprietary Information. Use of disclosure of R-2 Revision Date: September 2011

THESE DATA SUBJECT TO RESTRICTIVE LEGEND ON TITLE PAGE OR FIRST PAGE 

### PAGE NO. CHANGE

Section 2 Supplement Added

Page TC-4 Added equipment for new procedures

Section 2-0 Equipment Utilization

Page 1 Added for new procedures

Section 2-1 Reference Standards

Fig. 1.1 Pages. 1-3 Added reference standard

Section 2-2 High Frequency Eddy Current Probes

Page 1 Added for new procedures

Section 2-3 Low Frequency Eddy Current Probes

Fig. 3.1 Added probe Page. 1

Section 2-4 Inspection Fixtures

Page 1 Added for new procedures

Section 2-5 Ultrasonic Transducers

Page 1 Added for new procedures

### MD-90 MDC-94Kg000 AIRWORTHINESS LIMITATIONS INSTRUCTIONS (ALl) PREFACE

This ALl document contains information that defines mandatory replacement imes for SafeLife Structure, the inspection requirements for Principal Structural Elements (PSE) and also provides specific Non-Destructive Inspection (NDI) techniques and procedures for each PSE. NDI is a technology that is used to detect defects in materials utilizing techniques that do not damage or destroy the items being tested.

A Safe-Life Structure is defined as structure that has been shown to withstand repeated loads of variable magnitude expected during its service life without detectable cracks.

Principal Structural Elements (PSE’s) are those elements of structure which contribute significantly to carrying flight, ground, and pressurization loads, and whose failure could result in catastrophic failure of the airplane.

Continued Airworthiness requires the continued update of the inspection procedures as experience, data, and technology are increased. The ALl document is, therefore, prepared in an incremental fashion. The procedures must be sufficiently defined to provide instructions necessary to cover high time/cycle "fleet leader" aircraft, and are considered complete at the time of issue, and until subsequent additions are issued.

The content of the ALl document is divided into two Sections: Section 1 and Section 2, each with its own Table of Contents.

Section 1 Lists Safe-Life parts and mandatory replacement times as well as Principal Structural Element Inspection requirements. The Illustrations in this section are to be used for basic identification of the PSE only.

Section 2 - Provides tbe~etailed NDI techniques, tests, procedures and !nspection areas for each specific PSE inspection requirements.

NOTE: Detailed NDI instructions and procedures for the specific PSE’s are to be incorporated in this report and distributed to the operators a minimum ofone (1) year prior a PSE inspection coming due on the high time/cycle aircraft in the fleet.

The results of the analysis for Environmental Deterioration (ED) (i.e. corrosion) Accidental Damage (AD) required by type design (25.571 - Damage Tolerance and Fatigue Evaluation and 25.1529, Appendix H - Instructions for Continued Airworthiness) are located in the FAA Maintenance Review Board (MRB) Report, and identified as ED & AD tasks.

P-1

McDonnell Douglas Corporation Proprietary Information. Use or disclosure of THESE DATA SUBJECT TO RESTRICTIVE LEGEND ON TITLE PAGE OR FIRST PAGE. 

### Revision Date: OCT 2001

### MD-90 MDC-94K9000 AIRWORTHINESS LIMITATIONS INSTRUCTIONS (ALl)
SECTION 1
TABLE OF CONTENTS

SAFE-LIFE LIMITS ................................................................................................... A1-1

MD-90-30 (156,000 IbMTOGW) .......................................................................... A1-2

MD-90-30 EXR (168,000 Ib MTOGW), ER (166,000 Ib MTOGW

and HGW (160,000 IbMTOGW) ...................................................................... A1-6

INTRODUCTION TO PSE INSPECTION REQUIREMENTS ....................................... B1-1

PSE INSPECTION REQUIREMENTS ......................................................................... B2-1

REPORTING OF INSPECTION RESULTS ................................................................. C1-1

McDonnell Dou~ltlm Corporllttofl Proprietary Iflforn~ltion. Use or dilclolure or

THESE DATA SUBJECT TO RESTRICTIVE LEGEND ON TITLE PAGE OR FIRST PAGE. 

### TC-1 Revision Date: November 1997

# MD-90

SAFE-LIFE LIMITS

NOSE LANDING GEAR COMPONENTS

MAIN LANDING GEAR COMPONENTS

# MD-90

AIRWORTHINESS LIMITATIONS INSTRUCTIONS (ALl) MDC-94K9000
SAFE-LIFE LIMITS

This section contains the list of landing gear parts that have been categorized as safe-life. Parts which have limited life are shown with their respective life-limits specified in landings (cycles). Those parts which were considered safe-life, but have unlimited life are listed also. Unlimited life is equivalent to at least 300,000 landings (cycles), or 100 years of service.

NOTE

1. Parts which are used by the airlines only on the MD-90-30 airplane will have safe-life limits established for the MD-90 airplane.

. 

### A safe-life part which is being used interchangeably between two or more models of the DC-9, MD-80, MD-90 or MD-95 series has the lowest safe-life shown for any of the models on which it has been used, regardless of the time it has been used on each model.

. 

### Any part listed in this report that is reworked beyond component maintenancemanual limits or is modified due to discrepancies, must have its safe-life reestablished according to the loads and methods contained in report MDC-K5717 (MD-90-30 Landing Gear Safe-Life Limits).

It is the responsibility of the airlines to keep proper records to ensure compliance with the above.

McDonnell Dougl~l Corporation Proprietary Information. Use or dilclosure of

THESE DATA SUBJECT TO RESTRICTIVE LEGEND ON TITLE PAGE OR FIRST PAGE. 

### A 1-1 Revision Date: November 1997

# MD-90

AIRWORTHINESS LIMITATIONS INSTRUCTIONS (ALl) MDC-94K9000

SAFE-LIFE LIMITS MD-90-30 (156,000 Ib MTOGW)

Main Landing Gear parts which are considered safe-life and have limited life are listed below with the associated mandatory replacement times.

PART NO. ITEM

(A) 5935349-503 (B) 5937032-1 (C) 5935848-501 Link Assembly - Upper Lock Bracket Assembly - Bungee Fixed Side Link Assembly MANDATORY REPLACEMENT TIME
FAA

48,000 Ldgs. 48,000 Ldgs. 199,000 Ldgs.



## A 

# c \

\ B

McDonnell Douglas Corporation Proprietary Informalion. Use or disclosure of

THESE DATA SUBJECT TO RESTRICTIVE LEGEND ON TITLE PAGE OR FIRST PAGE. 

## A 1-2 Revision Date: November 199

# MD-90

AIRWORTHINESS LIMITATIONS INSTRUCTIONS (ALl) MDC-94K9000

SAFE-LIFE LIMITS MD-90-30 (156,000 Ib MTOGW)

Main Landing Gear parts which are considered
are listed below.

PART NO. ITEM

5935347-509,-511

5935348-503

3935358-1

5935352-1

3935368-501

5935374-1

5935353-1

5935351-501

5935346-503

5935350-501 .Piston

Cylinder

Restrictor

Restrictor Support Tube

Metering Pin Base

Upper Torque Arm

Lower Torque Arm

Lower Side Brace Link

Upper Side Brace Link

Lower Lock Link safe-life, but have unlimited life

MANDATORY REPLACEMENT TIME

FAA

Unlimited

Unlimited

Unlimited

Unlimited

Unlimited

Unlimited

Unlimited

Unlimited

Unlimited

Unlimited

McDonnell Douglm; Corporation Proprietary Information. Use or dilclosuro of

THESE DATA SUBJECT TO RESTRICTIVE LEGEND ON TIILE PAGE OR FIRST PAGE 

### A I-3 Revision Date: November 1997

# MD-90

AIRWORTHINESS LIMITATIONS INSTRUCTIONS (ALl) MDC-94K9000 SAFE-LIFE LIMITS MD-90-30 (156,000 Ib MTOGW)

Nose Landing Gear parts which are considered safe-life and have limited life are listed below with associated mandatory replacement times.

PART NO. ITEM MANDATORY REPLACEMENT TIME

FAA
(A) 3914464-503, -507 (B) 3913968-513 (C) 5927079-509,-511 Link Assembly - Upper Lock Link Assembly - Lower Lock Housing Assembly 46,500 Ldgs. 59,333 Ldgs. 76,000 Ldgs.



## A

B

/ 

## C

M DII0-AI.-2 CAG~IGDS)

McDonnell Douglas Corporetion Proprietary Informalion. Use or disclosure of
THESE OATA SUBJECT TO RESTRICTIVE LEGEND ON TITLE PAGE OR FIRST PAGE, A1-4 Revision Date: November 1997

# MD-90

AIRWORTHINESS LIMITATIONS INSTRUCTIONS (ALl) MDC-94Kg000
SAFE-LIFE LIMITS MD-90-30 (156,000 Ib MTOGW)

Nose Landing Gear parts which are considered safe-life but have unlimited life are
listed below.

PART NO.

5920603-511

5920602-511

5920210-503

5920209-503

5920209-504

2912726-1

5958412-511

5958412-513

3963295-1

3D0026-10

5920605-503

4958424-503

3928233-501

5963256-1 ITEM

Piston

Cylinder

Lower Drag Brace

Upper Drag Brace

Upper Drag Brace

Knee Hinge Nut

Torque Arm

Torque Arm

Torque Arm Apex Bolt

Torque Arm Apex Nut

Steering Lever

Nut Restrictor Support

Head Restrictor Support

Metering Pin Base MANDATORY REPLACEMENT TIME

FAA

Unlimited

~o 

### Unlimited

Unlimited

Unlimited

Unlimited

Unlimited

Unlimited

Unlimited

Unlimited

Unlimited

Unlimited

Unlimited

Unlimited

Unlimited

McDonnell Douglas Corporwtion Proprietary Information. Use or disclotlure of

THESE DATA SUBJECT TO RESTRICTIVE LEGEND ON TITLE PAGE OR FIRST PAGE. A 1-5 Revision Date: November 1997

# MD-90

AIRWORTHINESS LIMITATIONS INSTRUCTIONS (ALl) MDC-94K9000

SAFE-LIFE LIMITS MD-90-30 EXR (168,000 Ib MTOGW), ER (166,000 Ib MTOGW)

and HGW (160,000 Ib MTOGW)

Main Landing Gear parts which are considered safe-life and have limited life are listed below with the associated mandatory replacement times.

PART NO. ITEM MANDATORY REPLACEMENT TIME
FAA

(A) 5935349-503 (B) 5937032-1 (C) 5935848-501 (D) 5935348-503 Link Assembly - Upper Lock Bracket Assembly - Bungee Fixed Side Link Assembly Cylinder Assembly 48,000 Ldgs. 48,000 Ldgs. 194,000 Ldgs. 195,000 Ldgs.

\



### D 

## C A 

# \

\

MDg~AI-,1 CAEdIGOS)

McDonnell Ooughm Corporation Proprietary Information. Use or disclosure of

THESE DATA SUBJECT TO RESTRICTIVE LEGEND ON TITLE PAGE OR FIRST PAGE. 

### A1-6 

## B

Revision Date: November lgg7

# MD-90

AIRWORTHINESS LIMITATIONS INSTRUCTIONS (ALl) MDC-94K9000

SAFE-LIFE LIMITS MD-90-30 EXR (168,000 Ib MTOGW), ER (166,000 Ib MTOGW)

and HGW (160,000 Ib MTOGW)

Main Landing Gear parts which are listed below. are considered safe-life, but have unlimited life

PART NO. ITEM

Piston

Restrictor

Restrictor Support Tube

Metering Pin Base

Upper Torque Arm

Lower Torque Arm

Lower Side Brace Link

Upper Side Brace Link

Lower Lock Link 5935347-513

3935358-1

5935352-I

3935368-501

5935374-1

5935353-I

5935351-501

5935346-503

5935350-50i MANDATORY REPLACEMENT TIME
FAA

Unlimited

Unlimited

Unlimited

Unlimited

Unlimited

Unlimited

Unlimited

Unlimited

Unlimited

McDonnell Douglas Corporation Proprietary tnform~ion. Use or disclosure of

THESE DATA SUBJECT TO RESTRICTIVE LEGEND ON TITLE PAGE OR FIRST PAGE. 

### A 1-7 Revision Date: November 1997

# MD-90
AIRWORTHINESS LIMITATIONS INSTRUCTIONS (ALl) MDC-94K9000 SAFE-LIFE LIMITS MD-90-30 EXR (168,000 Ib MTOGW), ER (166,000 Ib MTOWG)

and HGW (160,000 Ib MTOGW)

Nose Landing Gear parts which are considered safe-life and have limited life are listed below with associated mandatory replacement times.

PART NO. ITEM

(A) 3914464-503, -507 (B) 3913968-513 (C) 5927079-511 Link Assembly - Upper Lock Link Assembly - Lower Lock Housing Assembly



## I MANDATORY REPLACEMENT TIME
FAA

46,500 Ldgs. 59,333 Ldgs. 46,000 Ldgs.



## A

B

/ 

## C

McDonnell Oougtas Corporation Proprietary Informalion, Use or disclosure or

THESE DATA SUBJECT TO RESTRICTIVE LEGEND ON TITLE PAGE OR FIRST PAGE. 

### A 1-8 Revision Date: November 1997

# MD-90

AIRWORTHINESS LIMITATIONS INSTRUCTIONS (ALl) MDC-94Kg000
SAFE-LIFE LIMITS MD-90-30 EXR (168,000 Ib MTOGW), ER (166,000 Ib MTOGW)

and HGW (160,000 Ib MTOGW)

Nose Landing Gear parts which are considered safe-life but have unlimited life are
listed below.

PART NO.

5920603-511

5920602-511

5920210-503

5920209-503

5920209-504

2912726-1

5958412-511

5958412-513

3963295-1

3D0026-10

5920605-503

4958424-503

3928233-501

5963256-1 ITEM

Piston

Cylinder

Lower Drag Brace

Upper Drag Brace

Upper Drag Brace

Knee Hinge Nut

Torque Arm

Torque Arm

Torque Anro. Apex,Bolt

Torque Arm Apex Nut

Steering Lever

Nut Restrictor Support

Head Restrictor Support

Metering Pin Base MANDATORY REPLACEMENT TIME

FAA

Unlimited

Unlimited

Unlimited

Unlimited

Unlimited

Unlimited

Unlimited

Unlimited

Unlimited

Unlimited

Unlimited

Unlimited

Unlimited

Unlimited

McDonnell Douglas Corporation Proprietary Information. Use or disclosure of

THESE DATA SUBJECT TO RESTRICTIVE LEGEND ON TITLE PAGE OR FIRST PAGE. A 1-9 Revision Date: November 1997

# MD-90 MDC-94K9000

AIRWORTHINESS LIMITATIONS INSTRUCTIONS (ALl) INTRODUCTION TO PSE INSPECTION REQUIREMENTS

This section contains the MD-90 Principal Structural Element (PSE) inspection requirements. Any deviations from these requirements (other than more frequent inspections than required), or any structural alterations/modifications to the PSE’s shall be coordinated with DAC and requires approval from the FAA Los Angeles Aircraft Certification Office.

The MD-90 PSE’s were selected based on the following critieria:

ANALYSIS & TEST

 ̄ operating stress level static/fatigue margins of safety

 ̄ severity of consequence of damage  ̄ operational experience of the DC-9/MD-80  ̄ DC-9/MD-80/MD-90 test data

OPERATIONAL SUSCEPTIBILITY TO  ̄ fatigue  ̄ corrosion  ̄ accidental damage  ̄ stress corrosion  ̄ manufacturing defects

assumed for damage tolerance assessment of the MD-90 Normal airplane operations are structure. Typical variations of flight range and gross weight were taken into account. The damage tolerance assessment were based on the principles of Linear Elastic Fracture Mechanics (LEFM). The resulting inspection requirements included in this document apply to all MD-90 airplane types.

Following is the list of MD-90 PSE’s:

1. 53.12.09.1

2. 53.12.09.2

3. 53.12.15.1

4. 53.12.15.2

53.12.15.3 CHAPTER 53

Fuselage Skin and Frames from Longeron 16 to Longeron 19, at all Frames in area above Wing and MLG

Fuselage Frame to Floor Beam Joints, at all frames above MLG Wheel Well

Bulkhead Skin & Stiffener at STA Z = 63.500, Left Side Only (Area of Firex Wye)

Bulkhead Skin & Stiffener at STA Z = 14.000, Between Finger Doublers & Blanket Attach Angles

Bulkhead Skin & Doublers at STA Z = -18.000

B1-1

McDonnell Douglas Corporation Proprietary Information. Use or disclosure of THESE DATA SUBJECT TO RESTRICTIVE LEGEND ON TITLE PAGE OR FIRST PAGE. 

### Revision Date: OCT 2001

# ~ 6. 53.12.15.4

7. 53.30.02.1

8. 53.30.02.2

9. 53.30.02.3

10. 53.30.02.4

11. 53.30.02.5

12. 53.30.02.6

13. 53.30.02.7

1. 54.10.01.1

2. 54.10.04.1

3. 54.10.08.1

4. 54.40.01.1

5. 54.40.01.2

6. 54.40.02.1

7. 54.40.03.1

8. 54.40.03.2

~9. 54.40.04.1 

# MD-90 MDC-94K9000

AIRWORTHINESS LMITATIONS INSTRUCTIONS (ALl) INTRODUCTION TO PSE INSPECTION REQUIREMENTS

Bulkhead - Fuselage Attachment Tee Radius between Longeron 6 & F.R.P.

Overwing Frame Splices above Wing & MLG Wheel Well, Longeron 8 to Longeron 12

Skin & Frame at STA 864.000 from Longeron 16 to Longeron 21

Fuselage Skin in Constant Section from Longeron 3 Left to Longeron 3 Right

Fuselage Hoop Skin Splice in Constant Section from Longeron 5 Left to Longeron 5 Right
Upper & Lower Window Belt Splices along entire length of Window Belt

Fuselage Skin around all Window Cutouts

Fuselage Skin Splice at Aft Pressure Bulkhead, Longeron 14 Left to Longeron 14 Right

CHAPTER 54

Pylon Front spar Upper Cap, from Fuselage Intersection to 10 inches Inboard of Fuselage

Rear Spar and Engine Thrust support fitting (Upper & Lower)

Shear Pin Plate, Shear Pin Holes (both Upper & Lower Holes)

Engine Yoke Flanges in vicinity of Support Fitting Attach Points

Pylon, Forward Upper & Lower Isolators and Cone Bolts

Yoke Support Frame Upper Lug

Pylon, Thrust Struts

Pylon, Thrust Isolator

Pylon, Aft Isolator & Cone Bolt

B1-2

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### Revision Date: OCT 2001

### MD-90 MDC-94K9000 AIRWORTHINESS LIMITATIONS INSTRUCTIONS (ALI)
INTRODUCTION TO PSE IN SPECTION REQUIREMENTS

B1-3

McDonnell Douglas Corporation Proprietary Information. Use or disclosure of Revision Date: September 2011
THESE DATA SUBJECT TO RESTRICTIVE LE GEND ON TITLE PAGE OR FIRST PAGE. 

### CHAPTER 55

1. 55.11.01.1 Rear Spar Upper Cap – between STA Xe = 5.000 and Xe = 14.000

2. 55.11.02.1 Rear Spar Upper Cap & Skin from STA Xh 7.234 to Xh 26.859

3. 55.11.03.1 Bushed Holes in Horizontal Stabilizer Jack Screw Attach Lug at STA Xh 6.625

4. 55.13.01.1 Upper Aft Skin Plank with Integral Stringers from STA Xh 7.234 to Xh 26.859

5. 55.53.01.1 Dorsal Fin Attach Angle & adjoining Fuselage Skin

CHAPTER 57

1. 57.11.01.1 Lower Front Spar Splice at STA Xcw 94.500, from STA Xcw 79.688 to Xcw 104.500

2. 57.11.01.2 Lower Front Spar Stringer Runout at STA Xcw 115.000, from STA Xcw 104.500 to Xcw 121.688

3. 57.11.01.3 Lower Front Spar Stringer Runout at STA Xrs 115.000, from STA Xrs 91.000 to Xrs 137.750

4. 57.11.01.4 Lower Front Spar Stringer Runout at STA Xrs 164.000, from STA Xrs 137.750 to Xrs 267.000

5. 57.11.02.1 Lower Rear Spar Splice at STA Xrs 111.500, from STA Xrs 85.000 to Xrs 130.000

6. 75.11.02.2 Lower Rear Spar Outboard from STA Xrs 130.000 to Xrs 180.000

7. 57.12.02.1 Lower Rear Spar Splice from STA Xcw 8.000 to Xcw 24.000

8. 57.12.02.2 Lower Rear Spar Inboard from STA Xcw 24.000 to Xcw 60.000

9. 57.12.03.1 Lower Rear Spar Splice from STA Xcw 60.000 to Xcw 100.000

10. 57.32.01.1 Center Wing Skin Splice at Stringer 17 from STA Xrs 121.688 to Xrs 214.000

11. 57.32.02.1 Lower Surface Access Door Cutouts STA Xrs 189.000 to Xrs 324.000

12. 57.34.01.1 Center Wing Skin Splice at Stringer 17 from STA Xcw 20.000 to Xcw 121.688

13. 57.34.01.2 Stringer 14, 15, 16 & Skin from STA Xcw 42.000 to Xcw 79.688

14. 57.34.01.3 Stringer 18, 19, 20 & Skin from STA Xcw 42.000 to Xcw 79.688

# PSE INSPECTION

REQUIREMENTSMD-90AIRWORTHINESS LIMITATIONS INSTRUCTIONS MDC-94K9000NOTE: ALL INTERVALS IN LANDINGS(CYCLES) UNLESS OTHERWISE NOTEDMcDonnell Douglas Corporation Proprietary Information. Use or disclosure ofTHESE DATA SUBJECT TO RESTRICTIVE LEGEND ON TITLE PAGE OR FIRST PAGE.B2-1INSPECTION INTERVALPSENumberDESCRIPTIONNDIPROCEDUREInitial RepeatZone(s)54.10.01.1Front Spar Pylon – STA 1364Pylon Front Spar, Upper Cap from Fuselage Intersection to 10 inchesInboard of FuselageDescription of PSE(NOTE: All PSE’s are symmetrical unless otherwise noted)SSI Title and Number for purpose ofcross reference to the MRB report.54.10.01.1Task NumberSequence Number NDI Procedure Number isATA Sub-Chapter identical to PSE Number.ATA ChapterAbbreviation forNDT Test(s) to be used at theapplicable inspection intervals.Refer to Section 2ETHFRefer to Section 2of this documentfor procedure.60,00010,900223Prepared by: DESIGN & TECHNOLOGYRevision Date: SEPT 2011DescriptionAbbreviationDiffracto-SightEddy Current High FrequencyEddy Current Low FrequencyPenetrant – Color ContrastPenetrant – FluorescentMagnetic Particle – Color ContrastMagnetic Particle – FluorescentMagneto Optic ImagingUltrasonic – “L” WaveUltrasonic – Shear WaveUltrasonic – Surface (90Rayleigh)X-ray RadiographyGamma-ray RadiographyVisual AidedTorque TestDSTETHFETLFPTPTFMTMTFMOIUTLUTSUTRRTRTGVTTTINITIAL – Task must beaccomplished by this time.REPEAT – Task must berepeated by this time.Repeat intervals start fromthe time operatoraccomplishes initialinspection.The NDI procedureselected, governs whenthe next inspection mustbe performed.Zone(s) in which task is applicable.Refer to Report No. ME-0001(Airplane Zoning)MD-90AIRWORTHINESS LIMITATIONS INSTRUCTIONS MDC-94K9000NOTE: ALL INTERVALS IN LANDINGS(CYCLES) UNLESS OTHERWISE NOTEDMcDonnell Douglas Corporation Proprietary Information. Use or disclosure ofTHESE DATA SUBJECT TO RESTRICTIVE LEGEND ON TITLE PAGE OR FIRST PAGE.B2-2INSPECTION INTERVALPSENumberDESCRIPTIONNDIPROCEDUREInitial RepeatZone(s)53.12.09.1.2Floor Beam to Frame Intersection, Overwing, STA’s 924 – 1041Fuselage Skin and Frames from Longeron 16 to Longeron 19, at allFrames in area above Wing and MLG Wheel WellFuselage Frame to Floor Beam Joints, at all Frames above MLG WheelWellRefer to Section 260,00060,00030,0009,800141, 151,161, 222144, 145222Prepared by: DESIGN & TECHNOLOGYRevision Date: OCT 2001

# M D-90 .,.wo,,..,..ss .,M,...,o.s ,.s..uc.,o.s MDC-94K9000

INSPECT FUSELAGE FRAME INNER FLANGE AND FRAME ATTACHMENTS COMMON TO FRAME AND SKIN BETWEEN LONGERON 16 AND 19 FROM STA 883.000 TO STA 1060.000 IN SHADED AREA, LEFT SIDE SHOWN (RIGHT SIDE OPPOSITE)

M D90-63-12-011-01 CAGpGDS) LONGERON 16

LONGERON 19 STA

883.000

I:! i:i

.., 

### !ip Ill !i!

FRAME ,~,,,,~



# I

SECTION A-A FUSELAGE SKIN STA 1060.000

F RAM En~,,,,,~r~ I



### A

II II I I
It II I I .l:::l I:l r:::l . LONGERON lS



### i’:::~ ~::

’1

- LONGERON 20

~ FUSELAGE

SKIN



## PSE 53.12._n9.t [ Fuselage SUn and Frames from Longeron 16 to Longeron 19, at all Frames In area above Wing and MLG Revision Date: Original

McOomwll Do~llm COrllOlltion Pml~leta~y l~on. ~ or d~ of THE ILLUSTRATION SHOWN ON THIS PAGE IS FOR GENERAL IDENTIFICATION ONLY,

THESE DATA SUBJECT TO RESTRICTIVE LEGEND ON TITLE PAGE OR FIRST PAGE. 

### B2-3 SEE SECTION I FOR THE DETAILED NDI PROCEDURE AND ILLUSTRATION(I).

### THIS PAGE INTENTIONALLY LEFT BLANK

McDonnoll DolNlll Corp~on Proprtltll~/In(orig. UI¢ m" dlsclmlufe Of 

### B2-4 Revision Date: ~  ̄  ̄ 8 THESE DATA SUBJECT O RESTRICTIVE LEGEND ON TITLE PAGE OR RRST PAGE, urlglnal

# M D-90 MDC-94K9000

FRP FRAME

SPLICE STA 1041.000 STA / STA 1022.000 ,,~



## I~OUTBD
~FWD INSPECT FUSELAGE FRAME, FLOORBEAM AND FASTENER HOLES IN SHADED AREA. RIGHT SIDE SHOWN (LEFT SIDE OPPOSITE)

FLOORBEAM

MDDO-.E3-124g-~2 CAG(IGOS) 

## VIEW A

LOOKING FORWARD STATION 1003.000 SIMILAR FOR STATION 1022.000

AND I041.000



### PSE 53.12.09.2 I Fuselage Frame to Floor Beam Joints, at all frames above MLG Wheel Well Revision Date: Original

McDonnell Dot,~Ms C, orporstt0n Prl)prletlry Info~on, Ulm or dhl¢loll,l~ of THE ILLUSTRATION SHOWN ON THIS PAGE IS FOR GENERAL IDENTIFICATION ONLY,

THESE DATA SUBJECT TO RESTRICTIVE LEGEND ON TITLE PAGE OR FIRST PAGE. 

### B2-5 SEE SECTION 2 FOR THE DETAILED NDI PROCEDURE AND ILLUSTRATfON(=).

# MD-90

AIRWORTHINESS LIMITATIONS INSTRUCTIONS MDC-94Kg000

PSE NDI INSPECTION INTERVAL Number DESCRIPTION PROCEDURE Zone(s) Initial Repeat

53.12.15 Pressure Bulkhead, Aft Fuselage, STA 1395 (Aft Face) Refer to Section 2

.1 Bulkhead Skin & Stiffener at STA Z = 63,500, Left Side Only (Area of 89,000 28,000 223 Firex Wye)

.2 Bulkhead Skin & Stiffener at STA Z = 14.000, Between Finger Doublers 89,000 15,500 223 & Blanket Attach Angles

.3 Bulkhead Skin & Stiffener at STA Z = -18.000 89,000 10,000 181

.4 Bulkhead - Fuselage Attachment Tee Radius Between Longeron 6 & 89,000 21,000 311 F.R.P.

Prepared by:. DESIGN & TECHNOLOGY Revision Date: OCT 2001

McDonnell Douglas Coq~ration Propdetanj Information. Use or disclosure of THESE DATA SUBJECT TO RESTRICTIVE LEGEND ON TITLE PAGE OR FIRST PAGE. 

### B2-6 NOTE: ALL INTERVALS IN LANDINGS (CYCLES) UNLESS OTHERWISE NOTED

# M D-90 MDC-94K9000

STA 1396.000

DOOR JAMB

STA Z =63.500

F.R.P. INSPECT BULKHEAD SKIN AND STIFFENER

IN SHADED AREA. LEFT SIDE ONLY

ATTACH TEE BULKHEAD STIFFENER /



# ~/~ ~i!!}!}!!!!:!!~!!!~!!!!i:!!~!!!!!i:!!!~:!i:!~:!!!~:!i:!!!i:!!}~:!~:!i:!i:!!!!~:ii:ii:!i:!!:~!!i:!!:~i-i !!’ ij--i i~’~~ z=S~’~oo

WYE SUPPORT



## VIEW A

MDgO--53-12-15-01 CAG(IGDS) I

AFT PRESSURE BULKHEAD LOOKING AFT

I 

### I Bulkhead Skin & Stiffener at STA Z = 63.500, Left Side Only (Area of Fimx Wye) I Revision Date: Original PSE53.12.15.1

B
McDonnell Doqllas Corpotle~ion Pmprl~ Informa~on. UN or dim of THE ILLUSTRATION SHOWN ON THIS PAGE IS FOR GENERAL IDENTIRCATION ONLY.

THESE DATA SUBJECT TO RESTRICTIVE LEGEND ON TITLE PAGE OR RRST PAGE. 

### 92-7 SEE SECTION 2 FOR THE DETAILED NDI PROCEDURE AND ILLUSTRATION(s).

### THIS PAGE INTENTIONALLY LEFT BLANK

Mr.JDon~ell Douglas Cocporwtion Pmpr~ In~,r’~r~Jon. Uie or disclosure of

THESE DATA SUBJECT TO RESTRICTIVE LJEGEHD ON TITLE PAGE OR FIRST PAGE. 

### B2-8 Revision Date: Original ~ m m m

# M D-90 .,.,...,o.s MDC-94K9000

STA 1395.000

INSPECT BULKHEAD SKIN AND STIFFENER IN SHADED AREA. LEFT SIDE SHOWN (RIGHT SIDE OPPOSITE) ATTACH TEE BULKHEAD ATTACH

/ SKIN ANGLE

DOOR JAMB ~,~

STA

STIFFENER STA Z=14.000 FINGER DOUBLERS 

## F.R.P. VIEW A

MDII0-63-12-16-1D2 CAG{mDS) I

AFT PRESSURE BULKHEAD LOOKING AFT



### PSE 53.12.15.2 L Bulkhead Sldn & Stiffener at STA Z = 14.000, Between Finger Doublers & Blanket Attach Angles " L Revision Date:Original

McDeemell Do~glm Corporodon Proprletlfy information. Ule or d~ of THE ILLUSTRATION SHOWN ON THIS PAGE IS FOR GENERAL IDENTIFICATION ONLY.

THESE DATA SUBJECT TO RESTRICTIVE LEGEND ON TITLE PAGE OR FIRST PAGE. 

### B2-9 SEE SECTION IE FOR THE DETAILED NOI PROCEDURE AND ILLUSTRATION(s).

### THIS PAGE INTENTIONALLY LEFT BLANK

McDcmnoi! DO4JgIN CorporaUon Pmprtatary Information. Use or disclosure of 

### THESE DATA SUSUEC~ TO RESTRIc’rr~ UEG~O O. ~rU~ P~E OR ~RST P~E. B2-10 Revision Date: Original

# M D-90 LIMITATIONS INSTRUCTIONS MDC-94K9000

STA 1395.000

INSPECT BULKHEAD SKIN AND DOUBLERS IN SHADED AREA. LEFT SIDE SHOWN (RIGHT SIDE OPPOSITE)

MOg0-S3-12-$1;-03 CAGIIGOS) F.R.P.

STA Z = -18.000

I

AFT PRESSURE BULKHEAD LOOKING AFT 

# - /,7 F RP

--.--. .... O

, 

## //V-l\\ ~ :---’,,’:: u ( ) o c~,’I/ II W 11 : :’~ ," ’ r~ ",.-../ r~ ~-J, // t ~ "./ II , , ’ , tJ t I s II

, o ,, , ,o ,.- v , 

# .: :. ........

..V/ -ST,

t J ) - = :~ -.:.+~....:....

- , -- ......... -. ~ ,.. ~. +. . "~ // Z =-18 oo0 -- ’ .’:": ~

:$i..~i i~ ~ ’~::’,~.i:~::" , "//

~.
. .:::;.:: ~.:.’:’::~: .~ ~ ~, :~.:~.:::  ̄ / .- ~- ::::::,¢::;;::

~.,.¢.~.::::~:~::: ~ ~..,.

..~.~.. (. / 

### ~,,~ ~::.~-~.’..:::.:’ ......:~ ......... ~::."~:: 0 ,-// 

##  ̄ <. ~::" ’, < ~!i~!i~:. .."/,7

-: :: "::i::W::~::;S: ,

\

~ "ATTACH TEE


# ,’"-.. .. . i} i: "BU~.EAD :° \’, ,.

, , ,,, .... .:.:.:.:

., , ......................................).~.............::~::$+..::::.:.’." ;J , ..::::~:~:~@i:i~i:~}~."4:~:.~:::~:~:..(~i:~:. ’ I .......~.~....,:..o,..’~.:~.:~’.’.:.:.:.:.~.:~.:.:

’ ," ".’,’.’~.’.’,’,’"" "" " .............. ,~" ~" "4~’" 

## d ~.,.~: .......~’\:::"~ .........~::~:~:!~ 4 ~!::" \ \ ’:iS~::¢:,~:::.

 ̄ .  ̄ ::~i~,ii~.;~,~:

 ̄ ::.~:~i :~i :..



# I

VIEW A

PSE 53.12.15.3 i

McDonnell Dougb-, Cor~n Propdmry Infomun~n. Utm or dlllclc~u~ Of

THESE DATA SUBJECT TO RESTRICTIVE LEGEND ON TITLE PAGE OR RRST PAGE. Bulkhead Skin & Doublers at STA Z = .18.000



### B2-11 

# I Revision Date: Original

THE ILLUSTRATION SHOWN ON THIS PAGE IS FOR GENERAL IDENTIFICATION ONLY.
SEE SECTION 2 FOR THE DETAILED NDI PROCEDURE AND ILLUSTt~.TION(s).

### THIS PAGE INTENTIONALLY LEFT BLANK

McDonnell Dougllm Corpomth)fl Proprilltlry Inf~mllUon. Uim or dllclolum of

THESE DATA SUBJECT TO RESTRICTIVE LEGEND ON TITLE PAGE OR FIRST PAGE. 

### B2-12 Revision Date: Original

# M D’g0.,RwoRT.,. ss .,.,T.T,o.s ,.STRUCT,O.S MDC-94K9000

STA 1395.000

INSPECT BULKHEAD.FUSELAGE ATTACHMENT TEE BETWEEN LONGERON 6 AND F.R.P. IN SHADED AREA. LEFT SIDE SHOWN (RIGHT SIDE OPPOSITE)

LONGERON 6



## A

F.R.P. BULKHEAD SKIN ATTACH TEE

MDIm-S3-12-15-04 CAGIIGDS) 

### I

AFT PRESSURE BULKHEAD LOOKING AFT 

## SECTION A-A

~SE 53.12.15.4 I Bulkhead - Fuselage Atlachment Tee Radius between Longeron 6 & F.R.P. Revision Date: Original

MoDerato41 I)~#lllll ~on Propdellary I~n. UIt ~" dkmlolmri of THE ILLUSTRATION SHOWN ON THIS PAGE IS FOR GENERAL IDENTIRCATION ONLY.

THESE DATA SUBJECT TO RESTR/CT/VE LEGEND ON TITLE PAGE OR FIRST PAGE. 

### B2-13 SEE SECTION 2 FOR THE DETAILED NDI PROCEDURE AND ILLUSTRATION(s).

# M D-90

AIRWORTHINESS LIMITATIONS INSTRUCTIONS MDC-94Kg000

PSE NDI INSPECTION INTERVAL Zone(s) Number DESCRIPTION PROCEDURE Initial Repeat

53.30.02 Skin Panels, STA 237 to 1395 Refer to Section 2

.1 Overwing Frame Splices above Wing & MLG Wheel Well, Longeron 8 to 60,000 30,000 220,222 Longeron 12

.2 Skin & Frame at STA 864.000 from Longeron 16 to Longeron 21 60,000 30,000 123,151, 152,220, 222

.3 Fuselage Skin in Constant Section from Longeron 3Left to Longeron 3 60,000 11,000 22O Right
.4 Fuselage Hoop Skin Splice in Constant Section from Longeron 5Left to 60,000 30,000 220 Longeron 5 Right

.5 Upper & Lower Window Belt Splices along entire length of Window Belt 60,000 30,000 220

.6 Fuselage Skin around all Window Cutouts 60,000 5,600 220

.7 Fuselage Skin Splice at Aft Pressure Bulkhead, Longeron 14 Left to 60,000 30,000 220,310 Longeron 14 Right

.8 Fuselage Skin & Frame at STA’s 1231.000, 1269.000, 1288.000, Longeron 60,000 30,000 220,223 16 to Longeron 18 (RH Side Only)

.9 Fuselage Skin & Frame at STA’s 1098.000 to 1155.000, Longeron 15 to 60,000 30,000 220,222 Longeron 18

Prepared by:. DESIGN & TECHNOLOGY Revision Date: OCT 2001

McDonnell Douglas Corporation Proprietary Information. Use or disclosure of THESE DATA SUBJECT TO RESTRICTIVE LEGEND ON TITLE PAGE OR FIRST PAGE. 

### B2-14 NOTE: ALL INTERVALS IN LANDINGS (CYCLES) UNLESS OTHERWISE NOTED

# M D-90 .,.,.A.,O.S ,.S..UC.,O.S MDC-94K9000

STA 883,000 STA

1041.000

UPPER FRAME

\\ \\ \\ \ \%

\\ \\ \\ LONGERON

FORMER

\ \ \ \ \\ \ \ \\

\\ \ \\ \

\\ FUSELAGE SKIN

INSPECT FUSELAGE SKIN, FRAMES SPLICES AND FORMERS AT ATTACHMENTS IN SHADED AREA. LEFT SIDE SHOWN (RIGHT SIDE OPPOSITE} LONGERON

TYPICAL FRAME SPLICE LOOKING FORWARD (SPLICE LOCATION VARIES BETWEEN LONGERON 8 AND 12) FORMER

MDg~S3-30.-O2.-Ol CAGOGDS) LOWER FRA~ LONGERON



### PSE 53,30.02.1 I Overwing Frame Splices above Wing & MLG Wheel Well, Longeron 8to Longeron 12 [ Revision Date: Original

McDonnell DOullllm Corporltion Proprietary Information. ~ or diKIosum of THE ILLUSTRATION SHOWN ON THIS PAGE IS FOR GENERAL IDENTIFICATION ONLY.

THESE DATA SUBJECT TO RE$TRICT/VE LEGEND ON TITLE PAGE OR FIRST PAGE. 

### B2-15 SEE SECTION 2 FOR THE DETAILED NDI PROCEDURE AND ILLUSTRATION(s).

### THIS PAGE INTENTIONALLY LEFT BLANK

McDonnell Doughm Cm’l~o. Pml~’h~w In/ormetkm. U~ or di~"l~ure of 

### B2-16 R evision Date:  ̄ ’%.’! I THESE OATA SUBJECT TO RESTRICTIVE LEGEND ON TITLE PAGE OR RRST PAGE. urlg real

# M D-90 MDC-94K9000

STA 864.000

INSPECT FRAME AND SKIN FROM LONGERON 16 TO 21 AND FRAME INNER FLANGE FROM I.ONGERON 18 TO 18 AT STA 864.000 IN SHADED AREA. LEFT SIDE SHOWN (RIGHT SIDE OPPOSITE)

,:,:,:.;,,:,:;:,:;:+,:;;,:;:,.,;,;,.



# I

SECTION A-A FUSELAGE SKIN

MD90-§3-30-O2--02 CAG|IGDS| 

## UP

~1 FWD

LONGERON 16

LONGERON

17

FUSELAGE,~ SKIN

LONGERON

18

LONGERON 19

LONGERON 20

LONGERON 21 STA 855.000 

# I STA

864.000 

# I ~RAME

-’1" I I I

I -T 

## ~ - _ _

L!:i:i:l



## ~!~

_ _ _ i!::i~)

~! ;~il

f.i!!:!:l



## ~::~ - _ _ ~i~ - - -

lii;:i:l 

### ~’:’::::i

I I



### i PSE 53.30.02.2 i Skin & Frame at STA 864.000 from Longeron 16 to Longeron 21 Revision Date: Original

McDofmell Doughm C~r~on Propel m Iffformlt~ Use or dllclwum of THE ILLUSTRATION SHOWN ON THIS PAGE IS FOR GENERAL IDENTIFICATION ONLY.

THESE DATA SUBJECT TO RESTRICTIVE LEGEND ON TITLE PAGE OR FIRST PAGE. 

### B2-17 SEE SECTION 2 FOR THE DETAILED ND1 PROCEDURE AND ILLUSTRATION(s).

### THIS PAGE INTENTIONALLY LEFT BLANK

McDom~,ll Do~im Corporation Pmprlma~, Informs~on. U~ or dlllchmtmb of
THESE DATA SUBJECT O RESTRICTIVE LEGEND ON TITLE PAGE OR FIRST PAGE. 

### B2-18 Revision Date: original ~ L ~ A

# M D-90 .,.,...,o.s MDC-94K9000

STA 1211.500

STA

STA 796.000

674~ STA 1288.000

INSPECT FUSELAGE SKIN IN CONSTANT SECTION FROM LONGERON 3 LEFT AND 3 RIGHT FROM STATIONS 674.000 TO 796.000 AND STATIONS 1211.500 TO 1288.000 IN SHADED AREA. LEFT SIDE SHOWN (RIGHT SIDE OPPOSITE) LONGERON 1

LONGERON 2L

LONGERON 3L

LONGERON

4L FUSELAGE SKIN 

# -....,

C STA STA STA STA STA

1211.500 1231.000 1250.000 1269.000 1288.000 

# [ I I I I

- -~w:%::;~i:~::~!:~::~w~:~:~x4::~a:~:~:~:~!~i~:~:~:~:~::~:!~:!:~:i~:~:~:~::~.W~-

- .’ "".: "":’ ’ "’:.~.’""..~:.’" ~::"" ":’ L: ’." "’::’.’ "".~.’""" ’" ’.’::" ’/:’.’ "::’/’" .~. ....... :": "’: ;" " .~." "~::.".:::. ":~’" l::. ti~ |



## ~_- ~.~.:,-:.:~.:.~:~:~ ....... ~:.~.:~i!w.:-:: ....... :,-~:...-....:.-:.:~...-.-x-.:.~::..-.:.:.:....--...:.~ - -~ _ ~::.~:::~.~.~::..~:~::~.~W.:::::~::~:~:~:~:.~::~.:::~::...-..::~:.~x~:....~:~:~.~:;~:~:~:c.‘:~:~

-

 ̄

. . ., .| :: ’::i :! "’!t ::



## _ _ ~.. .......... ~ ...............

~:~ .......-. ........~ ........-~ ~!~

- _ _ ::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::: _
I I I

I I

I I I I

I 

### _ _~1 ..... ~L .... JJ L~ _,L _



## -,~- _ n ;; .... -,~

STA STA STA STA STA STA
FUSELAGE 674.000 693°000 712.000 731.000 780.000 769.000

LONGERON 1 i

LONGERON 2L

LONGERON 3L~

LONGERON 4L~ C STA 796.000

STA 788.000 

# I

~’-~’~ .....................

. .......... . . ,..;,...-;,~-T~: .-..-....,.:.-...:.,.:.;.;.:.; ....... .- ....-..........v ..-.. -,... ̄|.~ .’.’,’.’.’.’.." - - ~.: .~.:~: :.~..:~: ..~..: V,:: :..~.: ~ :.~..: :~ :~: :~ :.~..: :~:~::~::~’:~’.’; "~:~’:’~:’~:~:’:~’:~:’:~:~:’:~: -.’..:::~:~i:~:i~!:~’:..-"~’:’....~.’:.. ..:::. .~-::~::- .~-’:-  ̄ ..,.. . ..~.,, .:. ,: :.. : .~...: , :,. ;, ...~,.......,;..:..,; ,..,..~.’...:. ~.:. ,:..... .~r. ;..:. :.. : .... .v ":’. ":v. ’;’.’. ),-’~."-’.’.’. ":’. ~:! I:.~ (:.. I t:. ~::. .t:.:

 ̄ -- ~’...~. -,.~:..’:~.,.~., .~.,.’~.-’..’~..’..’~.",,~’:"~.".-’~:.’~. ’..~:’:’ ."~’. ’.’~..’:.~..-,.---.....~,-..,.’C.,..--~.....’--.-..-.~’." ..~’.-:."~.".’~. ...... .’C....’~...-.’~..-.,~.::,,--.: .--’~..:. :~:~...’~..: ...... :...,.,"~..:..’~.,-:..~" "~ - ~ ~’.: :...,.. ............

.,.-..v,....-..,.....:...., :.~,;.:;,~:. ,~.:. ~,;::,’.’.’. :,’. ’.:-:;,~. :~;:.::~~ ..... w(.;(,.,,.. :,.~..:.g, ..~:. ,..~. ..,;,;..v...:,.~. ,;,;,t .L~.:.:~," ".~.; ’.:.’,’,v,’: ,:.v.’..~.w...,,.=..: ;Zv ~-. ~.,.., ~ ,. ~...,~ ....,=.....~, -. w..,." .~.-.’--

. _ ~:..:..:;~:~:~:~:.:.:.~:~x.~:.:.:~:~:.i~‘;:;~:~..~...~’~:

~ ~:’~:~:‘~:~;‘;~:":::~::~:#~;::~:~:~:::~:~:k:~:~::~:~::~:~.~:~;~’L~:~‘;-

I I I

I I

I I

I I

I I

I I

I

JJ ..... d .... J)- J J, bl 1,! ..... ].)_ _ 

## ~- -,," ,~ ;]

- -- ~I .~ - - -~ ,’; -,T

....

M DgO-53-30--OZ-03 CAGIIGDS)

I 

### I Fuselage Sldn In Constant Section from Longeron 3 Left to Longemn 3 Right I Revision Date: Original PSE 53.30.02.3
I
McOormell Dou0hm Corporl~on Proprletlry I~. U~ or dllclmmm of THE ILLUSTRATION SHOWN ON THIS PAGE IS FOR GENERAL IDENTIFICATION ONLY.

THESE DATA SUBJECT TO RESTRICTIVE LEGEND ON TITLE PAGE OR RRST PAGE. 

## B2-19 SEE SECTION 2 FOR THE DETAILED NDI PROCEDURE AND ILLUSTRATION(s).

### THIS PAGE INTENTIONALLY LEFT BLANK

McDm1~el! Douglm Corl~on Proprim Information. Use or dlw:losm of

THESE DATA SUBJECT TO RESTRICTIVE LEGEND ON TITLE PAGE OR FIRST PAGE. 

### B2-20 Revision Date: Original

# M D-90 A,.wo...,.ESS .,M,.A.,O.S ,.ST.UC.,O.S MDC-94K9000

STA STA 1145.600 

## STA 81eooo I /~ 

# L

~,,,~ [ "~y~ ~ ~ TOP CENTERLINE

ERON1



# I FwD

LONGERON 2L

INSPECT FUSELAGE SKIN, SPUCE STRAPS AND FINGER DOUBLERS FROM LONGERON BL TO LONGERON 5R AT STA 229.000, 588.000, 816o000, AND STA 1141.500 IN SHADED AREA LEFT SIDE SHOWN (RIGHT SIDE OPPOSITE)

LONGERON 6L

VIEW LOOKING DOWN AT UPPER SURFACE OF FUSELAGE t::i:::i:~:~. :::::::::::~

I I I !

I STA 229.000 

# tI

STA 588.000 816.000 ._ ~ii:!~i!ili!========================= li’~’:’!’i’i’!’~’i’li’i’i~i~i

__



# I

STA 1145.500

I 

### I Fuselage Hoop Skin Splice In Constant Section from Longeron 5 Left to Longeron 5 Right I Revision Date: Original PSE 

## 53.30.02.4

i
McOonmll Dou0hm Corpor~ion Prolprk~ Inllm’mstlan. ~ of dicl~mm of THE ILLUSTRATION SHOWN ON THIS PAGE IS FOR GENERAL IDENTIFICATION ONLY.

THESE DATA SUBJECT TO RESTRICTIVE LEGEND ON TITLE PAGE OR FIRST PAGE. 

## B2-21 SEE SECTION 2 FOR THE DETAILED NDI PROCEDURE AND ILLUSTRATION(s).

### THIS PAGE INTENTIONALLY LEFT BLANK

# M D-90 A,RWO.T.,..SS ",.,TA.,O.S ,.S..UCT,O.S MDC-94K9000

SKIN INNER FINGER DOUBLER
STA

218.000 STA

1328.000 INSPECT UPPER AND LOWER WINDOW BELT SPLICES ALONG ENTIRE LENGTH OF SPLICE AT FIRST TWO ATTACHMENT ROWS COMMON TO THE FUSELAGE SKIN AND INNER FINGER DOUBLERS, AND ALSO AT LAST ATTACHMENT ROW COMMON TO THE WINDOW BELT PANEL AND EXTERNAL DOUBLER IN SHADED AREA. LEFT SIDE SHOWN (RIGHT SIDE OPPOSITE)

INSPECT ALONG NOTED ROWS LONGERON 11

LONGERON 15 

## ..:.:: ~,!i:,:,!i! !!!!!!i!!!!!i!!!!!!!!!ij!!i!!!!!i!!!!!!!i!!!!!i!!!!!!!!!~ii~:

..... -.~ A ::::::::::::::::::::::::::::::::::::::::::::::::::::: ...........~!~i!~i:!~i~:~!~i~i~!~i~i~{.{i~i!~:.i~i:.~i~.~:.:.~.~i~i!~.!i~i!~



# J

WINDOW BELT PANEL

DOUBLER 

## OUTBD

VIEW A-A

MD90--53-3O-O2-O5 CAG(IGDS| LOOKING INBOARD UPPER AND LOWER WINDOW BELT SPLICE 

## UP

~1 FWD

I Upper & Lower Window Belt Splices along entire length of Window Belt I Revision Date: Original PSE 53,30,02,5 | McDonnell

Dowtls Cor~n Proprtetw~/I~n. Um or dleda~um of THE ILLUSTRATION SHOWN ON THIS PAGE IS FOR GENERAL IDENTIFICATION LY.

THESE DATA SUBJECT TO RESTRICTIVE LEGEND ON TITLE PAGE OR FIRST PAGE. B2-23 SEE SECTION :~ FOR THE DETAILED NDI PROCEDURE AND ILLUSTRATION(s).

### THIS PAGE INTENTIONALLY LEFT BLANK

McOonnsll Dougllm Corporation Propl, letm~ Informi~on. Use o¢ dillciosm~ of

THESE DATA SUBJECT TO RESTRICTIVE LEGEND ON TITLE PAGE OR FIRST PAGE. 

### B2-24 Revision Date: Original

# M D-90 .,,,wo,.-.,..ss LIMITATIONS INSTRUCTIONS MDC-94K9000

INSPECT FUSELAGE SKIN AROUND ALL CABIN WINDOWS IN SHADED AREA. LEFT SIDE SHOWN (RIGHT SIDE OPPOSITE)



## UP

CABIN WINDOW (TYPICAL) .08 INCH

1. k~-~ .70 INCH - OUTSIDE WINDOW

.1B INCH 

# L I_ 

# t

SECTION A-A

TYPICAL WINDOW CUTOUT SKIN SHOWN ONLY

M Dg0-.53-30-02-08 CAG(IGDS)



### PSE 53.30.02.6 i Fuselage Skin around all Window Cutouts Revision Date: Original

McOmm~l Drachm Corlmmtion Proprietary Ioft)fmatt~m. Ule or dim:toeum of THE ILLUSTRATION SHOWN ON THIS PAGE IS FOR GENERAL IDENTIFICATION LY,

THESE DATA SUBJECT TO RESTRICTIVE LEGEND ON TITLE PAGE OR FIRST PAGE. 

### B2-25 SEE SECTION 2 FOR THE DETAILED NDI PROCEDURE AND ILLUSTRATION(=).

### THIS PAGE INTENTIONALLY LEFT BLANK

McDonnell Douglse Col’~on Proprietary Information. Use or dlllckmum of

THESE DATA SUBJECT TO RESTRICTIVE LEGEND ON TITLE PAGE OR FIRST PAGE. 

### B2-26 Revision Date: Original

# M D-90 UMITATIONS INSTRUCTIONS MDC-94K9000

STA 1395.000 STA 1395.000

INSPECT FUSELAGE SKIN AND AFT PRESSURE BULKHEAD FRAME FROM LONGERON 14 LEFT TO 14 RIGHT IN SHADED AREA. LEFT SIDE SHOWN {RIGHT SIDE OPPOSITE) 

### I _ _ ~-~;il t~iii~
L ’, / ~ ~~-::il 

### |~-:~. 

### ..... ~~~.:;j i;~~ \

TOP CENTERLINE I=:=~ = = = = =1 ~Tr~:i" "’:-::::-::::~:: ::.::::::.-.-.-.::~ "-~ --- ~---J- :J :-1- 

### I I ~:i’.:::l ~~-~ ,
LONGERON 1F

FUSELAGE 

## I I ’ ~iil] ~~i i:::::::::::::::::::::::::::::::::::::::::::::

::::::::::::::::::::::::::::::::::::::: i ) ~^ ,~ / ~ ::]J::::::::::::::::::::;I I~::)::::::::::::::~.::::::::::: / 

### ~. ; ~.._._.__ ._,...~::::~:~::~:~ ~::;~::~:::~:~:: L _ _ _ --I ..... ~ ~ .,.-.~-~-. ,...~.’q~:,.’~..,:-?~: ..~-J I~. ;-~, ..:,."~, ..:~-:,.~...: "~.  ̄ __ ..... -1 

### ] ~.iiiiiiii;~ii~!i;~:~i;ililil [iil;i!i;ii~iii~i~ii~i;iiiii~i;iii~i~i / FUSELAGE | ::::::::::::::::::::::::::::;:::::::::::::::: :::::::::::::::::::::::::::::::::::::::" = 

### s KIN _ / ::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::: [i::i:: :::::::::::::::::::::::::::::

/ !i :: ii ::!. ::~ i!i!.ii ! :: ~::~ii ! : : !:::: :::::::::::::::::::::::::::::::::::::::::
/ ::::::::::::::::::::::::::::::::::::::::::::::: :::::::::::::::::::::::::::::::::::::::::::

LONGERON 14L :::::::::::::::::::::::::: i:i i:i:::~ .--~,.--’ ======================== 

### :::::::::::::::::::::::::::::::::::::::::::::::::::::::

i ~ i !;; il;::; i::;i!::;::;i;i!i~ii::;::~ii


## (ii!iii!i!i ~iiiiiii i iiiiiiii i!iiiii

I :::::::::::::::::::::::::::::: I ..... ========================================== ::iiii~i~ii~ i ~ i~iii~ \ = =-=: -_- ----~ Ji -~!:i~ii~iiiii ~!!~!i!i:..i E i: 

### /- - - - -r - ~ - ~i~ii::;i~:~::;i!i;i~i~i;~;~

!~i ::::::::::::::::::::::::::::::::::::::::::::

! !

~. ~._-._~ .... -I ~

I I ! I

LOOKING DOWN ~------~~ FUSELAGE UPPER SURFACE I
I I



# J

PSE 53.30.02,7 I Fuselage Skin Splice at Aft Pressure Bulkhead, Longeron 14Left to Longeron 14Right Revision Date: Original

I~l~n~ll Oeulll~ Corpemtion Pmprimry Infomtmton, UN ¢~ dimdum of THE ILLUSTRATION SHOWN ON THIS PAGE IS FOR GENERAL IDENTIRCATION ONLY,

THESE DATA SUBJECT TO RESTRICTIVE LEGEND ON TITLE PAGE OR RRST PAGE. 

### B2-27 SEE SECTION Z FOR THE DETAILED NDI PROCEDURE AND ILLUSTRATION(e).

### THIS PAGE INTENTIONALLY LEFT BLANK

McDonnell DoWIIm Corl~r~tion Pmpriewry Inform~bon. UIm or discl~u~re of 

### B2-28 Revision Date: f’~., "._z I
THESE DATA SUBJECT 1’O RESTRICTIVE LEGEND ON TITLE PAGE OR RRST PAGE. ~Jr,g,na,

# M D-90 A,.WO.T.,. ss.,.,.A.,O.S ,.S..UC.,O.S MDC-94K9000

STA p 1288.000

INSPECT FUSELAGE SKIN, FRAME INNER FLANGE AND SHEAR CLIPS BETWEEN LONGERON 16 AND 18 AT STATIONS 1231.000, 1269.000 AND 1288.000 IN SHADED AREA. RIGHT SIDE ONLY



## SECTION A-A

STA STA STA STA STA 1288.000 1276.000 1269.000 FUSELAGE 1250,000 1231,000

REF REF SHEAR I I I SKIN



# .

’ i -"~ii ~

..... ~ .... ~ I ~iiii!:i A f- iii~iiii:iii-~ A i:::!iiiiiiiiii

M D90-~3-30-02-08 ~ / CAGOOOS) LONGERON 16

LONGERON 17

LONGERON 18 "~ FUSELAGE SKIN



### PSE 53.30.02.8 ] Fuselage Sldn & Frame at STAs 1231.000, 1289.000, 1288.000, Longeron 16 to Longeron 18 (RH side only) J Revision Date: Original

McDonnell Dougllm Cm!~on Pro~ry Informm|oh. Use or dlactoslme or

THESE DATA SUBJECT TO RESTRICTIVE LEGEND ON TITLE PAGE OR FIRST PAGE. 

### B2-29 THE ILLUSTRATION SHOWN ON THIS PAGE IS FOR GENERAL IDENTIFICATION ONLY.
SEE SECTION 2 FOR THE DETAILED NOI PROCEDURE AND ILLUSTRATION(l).

### THIS PAGE INTENTIONALLY LEFT BLANK

McDonnell Douglm Co~n Pmpr~m Informat~o~ thin or disclosure of

THESE DATA SUBJECT TO RESTRiCTIVE LEGEND ON TITLE PAGE OR FIRST PAGE. 

### B2-30 Revision Date: Original

# M D-90 L,.,T.T,O.S MDC-94K9000

STA 1098.000 STA FUSELAGE

1155.000 SKIN

LONGERON 15 ~ C~

LONGERON 17 LONGERON 18 ~

1 LONGERON 17 ~ C~

LONGERON 18 ~ C STA STA STA STA 1098.000 1117.000 1136.000 1155.000

w

INSPECT FUSELAGE SKIN AND FRAMES BETWEEN LONGERON 15 AND 18 AT STATIONS I098.000, 1117.000, 1136.000 AND 1155.000 IN SHADED AREA. LEFT SIDE SHOWN (RIGHT SIDE OPPOSITE) 

### J

INSPECT FUSELAGE SKIN AND FRAME FITTING, FASTENERS AND FORMER BETWEEN AND INCLUDING STATIONS 1098.000 AND 1165.000 IN SHADED AREA. LEFT SIDE SHOWN IRIGHT SIDE OPPOSITE)

LONGERON 18 --

MDBO-S3-30-02-011 CAGgGDS| 

# ~ OUTBD

A

VIEW LOOKING FOPWARD (TYPICAL FRAHE) FUSELAGE SKIN ¢~j FRAME

FITTING



## SECTION A-A

PSE 53.30.02.9 I Fuselage Skin & Frame at STAs 1098.000 to 1155.000, Longeron 15 to Longeron 18 

# I Revision Date: Original

McD~II DoWIm Corporxtt~ Pmlerimmy Inf=rmatlon, UN ¢w dIMd~ of THE ILLUSTRATION SHOWN ON THIS PAGE IS FOR GENERAL IDENTIFICATION ONLY.

THESE DATA SUBJECT TO RESTRICTIVE LEGEND ON TITLE PAGE OR FIRST PAGE. 

### B2-31 SEE SECTION 2 FOR THE DETAILED NDI PROCEDURE AND ILLUSTRATION(=).

### PSE NDI INSPECTION INTERVAL Zone(s)

Number DESCRIPTION PROCEDURE Initial Repeat

54.10.01 Front Spar Pylon - STA 1364 Refer to Section 2

.1 Pylon Front Spar Upper Cap from Fuselage Intersection to 10 inches In- 60,000 10,200 223 board of Fuselage

Prepared by: DESIGN & TECHNOLOGY Revision Date: OCT 2001

NOTE: ALL INTERVALS IN LANDINGS (CYCLES) UNLESS OTHERWISE NOTED McDonnell Douglas Corporation Proprietary Information. Use or disclosure of THESE DATA SUBJECT TO RESTRICTIVE LEGEND ON TITLE PAGE OR FIRST PAGE. 

### 92-32

# MD-90 MDC-94K9000

FUSELAGE INTERSECTION

LONGERON

15 

# i

-- 10 INCHES

=i UPPER SPAR CAP



### 0

0

0

0 

## I o 

# Io

I o 0

0

0

0

0

0 INSPECT UPPER SPAR CAP AND FASTENERSIN SHADED AREA. LEFT SIDE SHOWN (RIGHT SIDE OPPOSITE) YOKE SUPPORT FITTING

FRONT SPAR

MD90-54-I0~01-01 CAGIIGDS) 

## ~ OUTBD

VIEW A-A

FRONT SPAR LOOKING FORWARD ANGLE 

## A

A

FORWARD ENGINE MOUNT YOKE 

# I PSE 54.10.01.1 I Pylon Front Spar Upper Cap, from Fuselage Intersection to 10 Inches Inboard of Fuselage I Revision Date: OCT 2001

McDonnell Douglas Corporation Proprietary Information. Use or disclosure of THE ILLUSTRATION SHOWN ON THIS PAGE IS FOR GENERAL IDENTIFICATION ONLY. THESE DATA SUBJECT TO RESTRICTIVE LEGEND ON TITLE PAGE OR FIRST PAGE. 

### B2-33 SEE SECTION 2 FOR DETAILED NDI PROCEDURE AND ILLUSTRATION(s).

# M D-90

AIRWORTHINESS LIMITATIONS iNSTRUCTiONS MDC-94K9000

PSE NDI INSPECTION INTERVAL Zone(s) Number DESCRIPTION PROCEDURE Initial Repeat

54.10.04 Thrust Bulkhead, Pylon - STA Yn 170.5 Referto Section 2

Only aircraft fuselage numbers 2094, 2095, 2096, 2097, 2098, 2099, 2100, 2115, 2117, 2120 2122 and 2123.

.1 Rear Spar and Engine Thrust support fitting (Upper & Lower) ETHF 15,000 4,500 431,441

Accomplishment of modification per Service Bulletin MD90-54-001 terminates ALl inspection requirements for PSE 54.10.04.1.

Prepared by:. DESIGN & TECHNOLOGY Revision Date: OCT 2001

NOTE: ALL INTERVALS IN LANDINGS (CYCLES) UNLESS OTHERWISE NOTED McDonnell Douglas Corporation Proprietary Information. Use or disclosure of THESE DATA SUBJECT TO RESTRICTIVE LEGEND ON TITLE PAGE OR RRST PAGE. 

### B2-34

# M D-90 .,.WO.TH,.ESS L,.,T.T,ONS ,NST.UCT, O.S MDC-94K9000

REAR SPAR INSPECT REAR SPAR AND ENGINE THRUST SUPPORT FITTING (UPPER AND LOWER CAPS) IN SHADED AREA. LEFT SIDE SHOWN (RIGHT SIDE OPPOSITE)

FUSELAGE AUXILIARY SPAR REAR SPAR

AFT ENGINE MOUNT SUPPORT PER CAP

LOWER CAP



## VIEW A

ENGINE THRUST SUPPORT FITTING

M DgO-S4-110-04-01 CAGilGDS) CLOSING RIB

PSE 54.10.04.1 

### I Rear Spar and Engine Thrust support fitting (Upper & Lower Ii Revision Date: JAN 1995

McDonnell Dougl-,s Corporation Proprietary Information. Use or disclosure of THE ILLUSTRATION SHOWN ON THIS PAGE IS FOR GENERAL IDENTIFICATION ONLY.

THESE DATA SUBJECT TO RESTRICTIVE LEGEND ON TITLE PAGE OR FIRST PAGE. 

### B2-35 SEE SECTION ;~ FOR THE DETAILED NDI PROCEDURE AND ILLUSTRATION(s). MIIOPSEBL

# M D-90 MDC-94Kg000

PSE NDI INSPECTION INTERVAL Zone(s) Number DESCRIPTION PROCEDURE Initial Repeat

54.10.08 Plate, Pylon Thrust Refer to Section 2

.1 Shear Pin Plate, Shear Pin Holes (both Upper & Lower Holes) 60,000 30,000 431,441

Prepared by: DESIGN & TECHNOLOGY Revision Date: JAN 1995

NOTE: ALL INTERVALS IN LANDINGS (CYCLES) UNLESS OTHERWISE NOTED McDonnell Douglas Corporation Proprietary Information. Use or disClosure of

THESE DATA SUBJECT TO RESTRICTIVE LEGEND ON TITLE PAGE OR FIRST PAGE. 

### B2-36 MgOPSO.V

# M D-90 A,.WOm,. ss ,.S .UCT, O.S MDC-94K9000

REAR SPAR FUSELAGE AUXILIARY SPAR 

# \ INSPECT SHEAR PIN HOLES

IN SHADED AREA. LEFT SIDE SHOWN (RIGHT SIDE OPPOSITE)

AFT ENGINE MOUNT SUPPORT UPPER AND LOWER SHEAR PIN HOLES



## UP

VIEW A

THRUST ISOLATOR PLATE LOOKING INBOARD

CLOSING RIB



### PSE 54.10.08.1 I Shear Pin Plate, Shear Pin Holes (both Upper & Lower Holes) 

# I Revision Date:JAN 1995

McDmmell DOUl;Im C~ Peopr~ In]brm~lMm. Umo ar dil~lom~e of

THESE DATA SUBJECT TO RESTRICTIVE LEGEND ON TITLE PAGE OR RRST PAGE. 

### B2-37 THE ILLUSTRATION E, HQNIN ON THIS PAGE I$ FOR GENERAL IDENTIFICATION ONLY

SEE SECTION ~ FOR THE DETAILED NOI PROCEDURE ANO ILLUSTRATION(t)

# M D-90

AIRWORTHINESS LIMITATIONS INSTRUCTIONS MDC-94Kg000

PSE NDI INSPECTION INTERVAL Zone(s) Number DESCRIPTION PROCEDURE Initial Repeat

54.40.01 Yoke - Forward Engine Mount, Pylon - STA 1364 Refer to Section 2

.1 Engine Yoke Flanges in vicinity of Support Fitting Attach Points 60,000 10,600 412, 422

.2 Pylon, Forward Upper & Lower Isolators and Cone Bolts (see note) MTF 15,000 15,000 412,422

NOTE: Accomplishment of the MD-90 ALl inspection procedure 54.40.01.2 at intervals specified in the document listed below for these components, is an acceptable means to satisfy the ALl requirements for PSE 54.40.01.2.

Maintenance Review Board Report McDonnell Douglas MD-90 Tasks (71-20-00/01 and 71-20-00/02)

Prepared by: DESIGN & TECHNOLOGY Revision Date: OCT 2001

NOTE: ALL INTERVALS IN LANDINGS (CYCLES) UNLESS OTHERWISE NOTED McDonnell Douglas Corporation Proprietary Information. Use or disclosure of THESE DATA SUBJECT TO RESTRICTIVE LEGEND ON TITLE PAGE OR FIRST PAGE. B2-38

# M D-90 UMFrATIONS INSTRUCTIONS MDC-94K9000

ORT FITTING

FRONT SPAR INSPECT INBOARD FLANGES BETWEEN ~ UPPER AND LOWER RIBS INSPECT AREA AROUND SUPPORT .,4 FITTING ATTACHMENT HOLES IN SHADED AREAS. ~ UPPERRIBS LEFT SIDE SHOWN (RIGHT SIDE OPPOSITE) /~: UPPER SUPPORT FITTING TO

"~.(::’.-c~E YOKE ATTACH POINT

LOWER RIBS 

## INBD

UPPER RIBS

INSPECT OUTBOARD FLANGES BETWEEN UPPER AND LOWER RIBS LOWER SUPPORT FITTING TO INSPECT AREA AROUND SUPPORT YOKE ATTACH POINT FITTING ATTACHMENT HOLES IN SHADED AREAS. LEFT SIDE SHOWN

~ :!i! LO WER (RIGHT SIDE OPPOSITE) i~. RIBS



## VIEW A

FORWARD ENGINE MOUNT LOOKING AFT FORWARD ENGINE MOUNT YOKE



### PSE 54.40.01.t I Engine Yoke Flanges In vicinity of Support Flffin9 Attach Points J Revision Date: JAN 1095

McOomtefl Omalllm Corl~ ~ h~ UIII or II1~ air THE ILLUSTRATION SHOWN ON THIS PAGE IS FOR GENERAL IDENTIFICATION ONLY

THESE DATA SUBJECT TO RESTRICTIVE LEGEND ON TITLE PAGE OR FIRST PAGE. 

## B2-39 SEE SECTION 1 FOR THE DETAILED NDI PROCEDURE AND ILLUSTRATION(sl

### THIS PAGE INTENTIONALLY LEFT BLANK



# I McOonnoll Douglm| Corporation Proprietary InFormation, Un or dl|closum of

THESE DATA SUBJECT TO RESTRICTIVE LEGEND ON TITLE PAGE OR FIRST PAGE. 

### B2-40 Revision Date: JAN 1995

# M D-90 .,..A.O.S ,NSTRUC ONS MDC-94K9000

YOKE CONE BOLT

UPPER COVER VIBRATION PLATE ISOLATOR



# % LOWER VIBRATION ISOLATOR

MDIO-E4-40-01-4)Z CA6(1OOS) INSPECT UPPER AND LOWER ISOLATORS AND CONE BOLTS IN SHADED AREAS. LEFT SIDE SHOWN {RIGHT SIDE OPPOSITE) COVER PLATE

CONE BOLT



# PSE S4.40.01.2 1 Pylon, Forward Upper & Lower Isolators and Cone Bolts 

# I Revision Date:JAN 1995

THE ILLUSTRATION SHOWN ON THIS PAGE ISFOR GENERAL IDENTIFICATION ONLY SEE SECTION = FOR THE OETAILEO NO, PROCEDURE AND ILLUSTRATIONIIJ. THESE DATA SUBJECT TO NESTRICTWE LEGEND ON TITLE PAGE OR FIRST PAGE. 

### B2-41

# M D-90 .,.wo.~.,.~ss .,.,~.~,o.~ ,.s~.oc~,o.s MDC-94K9000

PSE NDI INSPECTION INTERVAL Repeat Zone(s) Number DESCRIPTION PROCEDURE Initial

54.40.02 Fitting, Yoke Support Refer to Section 2
.1 Yoke Support Frame Upper Lug 60,000 30,000 412, 422

Prepared by: DESIGN & TECHNOLOGY Revision Date: JAN 1995

McDonnell Douglas Corporation Proprietary Information. Use or disclosure of THESE DATA SUBJECT TO RESTRICTIVE LEGEND ON TITLE PAGE OR FIRST PAGE, 

### B2-42 NOTE: ALL INTERVALS IN LANDINGS (CYCLES) UNLESS OTHERWISE NOTED

M00PSI~RVMD-90AIRWORTHINESS LIMITATIONS INSTRUCTIONS MDC-94K9000THE ILLUSTRATION SHOWN ON THIS PAGEIS FOR GENERAL IDENTIFICATION ONLY.SEE SECTION 2 FOR DETAILED NDI PROCEDURE AND ILLUSTRATION(s).B2-43McDonnell Douglas Corporation Proprietary Information. Use or disclosure ofTHESE DATA SUBJECT TO RESTRICTIVE LEGEND ON TITLE PAGE OR FIRST PAGE.YOKE SUPPORTFITTINGINBOARDFLANGELUG CONSTANTSECTIONFORWARD ENGINEMOUNT YOKEFRONT SPARYOKE SUPPORT FITTINGLOOKING AFTBBSECTION B-BVIEW A-AAAINSPECT UPPER CAPIN SHADED AREAS.LEFT SIDE SHOWN(RIGHT SIDE OPPOSITE)MD90-54-40-02-01CAG(IGDS)PSE 54.40.02.1Yoke Support Frame Upper LugRevision Date: JAN 1995MD-90AIRWORTHINESS LIMITATIONS INSTRUCTIONS MDC-94K9000NOTE: ALL INTERVALS IN LANDINGS(CYCLES) UNLESS OTHERWISE NOTEDMcDonnell Douglas Corporation Proprietary Information. Use or disclosure ofTHESE DATA SUBJECT TO RESTRICTIVE LEGEND ON TITLE PAGE OR FIRST PAGE.B2-44INSPECTION INTERVALPSENumberDESCRIPTIONNDIPROCEDUREInitial RepeatZone(s)54.40.03.1.2Links, Pylon ThrustPylon, Thrust StrutsPylon, Thrust IsolatorRefer to Section 2PTFMTF15,00015,00015,00015,000413, 423413, 423Prepared by: DESIGN & TECHNOLOGYRevision Date: SEPT 2011

# M D-90 UMITATIONS INSTRUCTIONS MDC-94K9000

,ENGINE

INSPECT UPPER AND LOWER THRUST STRUTS IN SHADED AREA. LEFT SIDE SHOWN IRIGHT SIDE OPPOSITE)

MDt0-S4-40-0$-01 CAGllGDS| THRUST STRUTS



## FWD THRUSTISOLATOR



# I PSE 54.40.03.1 [

McC.~-.-~:I Do~hm CmToretl~ Pr~rtotmy hdrm.mJeJ~, Ibm et dh~ltm~
THESE DATA SUBJECT TO RESTRICTIVE LEGEND ON TITLE PAGE OR RRflT PAGL 

### Pylon, Thrust Struts

B2-45 

# I Revision Date:JAN 1995

THE ILLUSTRATION SHOWN ON THIS PAGE IS FOR GENERAL IDENTIFICATION ONLY SEE SECTION | FOR THE DETAJLED NI PROCEDURE AND ILLUSTFU~,TION{s)

### THIS PAGE INTENTIONALLY LEFT BLANK



# i McDonnell DOuplN Corporation Proprietary Information. Ule or disclosure of

~
THESE DATA SUBJECT TO RESTRICTIVE LEGEND ON TITLE PAGE OR FIRST PAGE. B2-46 Revision Date: JAN 1995

# M D-90 .,.n’..,o.s ,.s..oc.,o.s MDC-94K9000



# % SUPPORT

/"/FITTING

INSPECT THRUST ISOLATOR IN SHADED AREA. LEFT SIDE SHOWN (RIGHT SIDE OPPOSITE) .,..~.......~THRUSTISOLATOR

M D90-~,-40--03-02 CAGIIGDS| 

# I PSE 54.40.03.2 I

,.,.,,,. McOommn OOBI)llm Coq~flltton Pml~ietmry toformtitk=n. Use or IP _ __tim Of
THESE DATA SUBJECT TO RESTRICTIVE LEGEND ON TITLE PAGE OR FIRST PAGE, 

### Pylon, Thrust Isolator

B2-47 

# I Revision Date:JAN tgg5

THE IllUSTRATION SHOWN ON THIS PAGE I,~ FOR GENERAL IDENTIFICATION ONLY
SEE SECTION 2 FOR THE DE’TAILED NDI PROCEDURE AND IllUSTRATION(s)

# M D-90

PSE NDI INSPECTION INTERVAL Zone(s) Number DESCRIPTION PROCEDURE Initial Repeat

54.40.04 Pylon, Aft Isolator Refer to Section 2

.I Pylon, Aft Isolator & Cone Bolt MTF 15,000 15,000 413, 423

NOTE: Accomplishment of the MD-90 ALl inspection procedure 54.40.04.1 at intervals specified in the document listed below for these components, i an acceptable means to satisfy the ALl requirements for PSE 54.40.04.1.

Maintenance Review Board Report McDonnell Douglas MD-90 Tasks (71-20-00/01 and 71-20-00/02)

| 

### Prepared by: DESIGN & TECHNOLOGY Revision Date: OCT 2001

McDonnell Douglas Corporation Proprietary InformaUon. Use or disclosure of THESE DATA SUBJECT TO RESTRICTIVE LEGEND ON TITLE PAGE OR FIRST PAGE 

### B2-48 NOTE: ALL INTERVALS IN LANDINGS (CYCLES) UNLESS OTHERWISE NOTED

# M D-90 .,.WORTH,. ss L,.,T.T,O.S,.ST. CT,O.S MDC-94K9000

AFT CONE BOLT

MD90-54-40-04-01 CAG(IGDS) 

### LM 442-S16 AFT CONE BOLT

AFT VIBRATION ISOLATOR



## INBD INSPECT AFT ISOLATOR AND AFT CONE BOLT IN SHADED AREA. LEFT SIDE SHOWN (RIGHT SIDE OPPOSITE)



### LM 442-SA6

PSE 54.40.04.1 I Pylon, Aft Isolator & Cone Bolt 

# I Revision Date: OCT 2001

THE 111USTRATION SHOY~ ON THIS PAGE IS FOR GENERAL IDENTIFICATION ONLY. McOonn~ Douglas Corpor~on Pmlxletl~ IrffOmllll~l. U~ or disclosure Of 

## B2-49 SEE SECTION 2 FOR THE DETAILED NDI PROCEDURE AND ILLUSTRATION(s). THESE DATA SUBJECT O RESTRICTIVE LEGEND ON Ti’II.IE PAGE OR RRST PAGEMD-90AIRWORTHINESS LIMITATIONS INSTRUCTIONS MDC-94K9000NOTE: ALL INTERVALS IN LANDINGS(CYCLES) UNLESS OTHERWISE NOTEDMcDonnell Douglas Corporation Proprietary Information. Use or disclosure ofTHESE DATA SUBJECT TO RESTRICTIVE LEGEND ON TITLE PAGE OR FIRST PAGE.B2-50INSPECTION INTERVALPSENumberDESCRIPTIONNDIPROCEDUREInitial RepeatZone(s)55.11.01.1Horizontal Stabilizer Rear Spar CapsRear Spar Upper Cap - between STA Xe = 5.000 and Xe = 14.000Refer to Section 251,0001,600330, 340Prepared by: DESIGN & TECHNOLOGYRevision Date: SEPT 2011MD-90AIRWORTHINESS LIMITATIONS INSTRUCTIONS MDC-94K9000THE ILLUSTRATION SHOWN ON THIS PAGEIS FOR GENERAL IDENTIFICATION ONLY.SEE SECTION 2 FOR DETAILED NDI PROCEDURE AND ILLUSTRATION(s).B2-51McDonnell Douglas Corporation Proprietary Information. Use or disclosure ofTHESE DATA SUBJECT TO RESTRICTIVE LEGEND ON TITLE PAGE OR FIRST PAGE.PSE 55.11.01.1Rear Spar Upper Cap - between STA Xe = 5.000 and Xe = 14.000Revision Date: SEPT 2011MD-90AIRWORTHINESS LIMITATIONS INSTRUCTIONS MDC-94K9000NOTE: ALL INTERVALS IN LANDINGS(CYCLES) UNLESS OTHERWISE NOTEDMcDonnell Douglas Corporation Proprietary Information. Use or disclosure ofTHESE DATA SUBJECT TO RESTRICTIVE LEGEND ON TITLE PAGE OR FIRST PAGE.B2-52INSPECTION INTERVALPSENumberDESCRIPTIONNDIPROCEDUREInitial RepeatZone(s)55.11.02.1Rear Spar – Center Box Caps, STA Xh 27 Left to Xh 27 RightRear Spar Upper Cap & Skin from STA Xh 7.234 to Xh 26.859Refer to Section 260,00028,200330, 340Prepared by: DESIGN & TECHNOLOGYRevision Date: SEPT 2011MD-90AIRWORTHINESS LIMITATIONS INSTRUCTIONS MDC-94K9000THE ILLUSTRATION SHOWN ON THIS PAGEIS FOR GENERAL IDENTIFICATION ONLY.SEE SECTION 2 FOR DETAILED NDI PROCEDURE AND ILLUSTRATION(s).B2-53McDonnell Douglas Corporation Proprietary Information. Use or disclosure ofTHESE DATA SUBJECT TO RESTRICTIVE LEGEND ON TITLE PAGE OR FIRST PAGE.MD90-55-11-02-01CAG(IGDS)INSPECT UPPER SPARCAP AND SKININ SHADED AREAS.LEFT SIDE SHOWN(RIGHT SIDE OPPOSITE)HORIZONTAL OUTER CONSTANT SECTIONUPPER REARSPAR CAPUPPER SKIN PLANKREAR SPAR PLANESTAXh=7.234STAXh=26.859PSE 55.11.02.1Rear Spar Upper Cap & Skin from STA Xh 7.234 to Xh 26.859Revision Date: SEPT 2011MD-90AIRWORTHINESS LIMITATIONS INSTRUCTIONS MDC-94K9000NOTE: ALL INTERVALS IN LANDINGS(CYCLES) UNLESS OTHERWISE NOTEDMcDonnell Douglas Corporation Proprietary Information. Use or disclosure ofTHESE DATA SUBJECT TO RESTRICTIVE LEGEND ON TITLE PAGE OR FIRST PAGE.B2-54INSPECTION INTERVALPSENumberDESCRIPTIONNDIPROCEDUREInitial RepeatZone(s)55.11.03.1Joints, Center Box, STA Xh 7.0 and Xh 26.0 (Left & Right Sides)Bushed Holes in Horizontal StabilizerJack Screw Attach Lug at STA Xh6.625Refer to Section 260,00030,000333, 343Prepared by: DESIGN & TECHNOLOGYRevision Date: SEPT 2011MD-90AIRWORTHINESS LIMITATIONS INSTRUCTIONS MDC-94K9000THE ILLUSTRATION SHOWN ON THIS PAGEIS FOR GENERAL IDENTIFICATION ONLY.SEE SECTION 2 FOR DETAILED NDI PROCEDURE AND ILLUSTRATION(s).B2-55McDonnell Douglas Corporation Proprietary Information. Use or disclosure ofTHESE DATA SUBJECT TO RESTRICTIVE LEGEND ON TITLE PAGE OR FIRST PAGE.MD90-55-11-03-01CAG(IGDS)INSPECT FOUR BUSHED HOLESIN SHADED AREAS.LEFT SIDE SHOWN(RIGHT SIDE OPPOSITE)AUPVIEW ALOOKING INBOARDFWDJACKSCREWATTACH LUGSTAXh=6.625PSE 55.11.03.1Bushed Holes in Horizontal Stabilizer Jack Screw Attach Lug at STA Xh 6.625Revision Date: SEPT 2011MD-90AIRWORTHINESS LIMITATIONS INSTRUCTIONS MDC-94K9000NOTE: ALL INTERVALS IN LANDINGS(CYCLES) UNLESS OTHERWISE NOTEDMcDonnell Douglas Corporation Proprietary Information. Use or disclosure ofTHESE DATA SUBJECT TO RESTRICTIVE LEGEND ON TITLE PAGE OR FIRST PAGE.B2-56INSPECTION INTERVALPSENumberDESCRIPTIONNDIPROCEDUREInitial RepeatZone(s)55.13.01.1Plates/Skin – Upper/Lower, STA Xh 27.2 Left to Xh 27.2 RightUpper Aft Skin Plank with Integral Stringers from Xh 7.234 to Xh 26.859Refer to Section 260,0008,100330, 340Prepared by: DESIGN & TECHNOLOGYRevision Date: SEPT 2011MD-90AIRWORTHINESS LIMITATIONS INSTRUCTIONS MDC-94K9000THE ILLUSTRATION SHOWN ON THIS PAGEIS FOR GENERAL IDENTIFICATION ONLY.SEE SECTION 2 FOR DETAILED NDI PROCEDURE AND ILLUSTRATION(s).B2-57McDonnell Douglas Corporation Proprietary Information. Use or disclosure ofTHESE DATA SUBJECT TO RESTRICTIVE LEGEND ON TITLE PAGE OR FIRST PAGE.MD90-55-13-01-01CAG(IGDS)HORIZONTAL OUTER CONSTANT SECTIONREAR SPAR PLANESTAXh=7.234INSPECT UPPER SKIN PLANKIN SHADED AREAS.LEFT SIDE SHOWN(RIGHT SIDE OPPOSITE)UPPER SKIN PLANKSTAXh=26.859PSE 55.13.01.1Upper Aft Skin Plank with Integral Stringers from STA Xh 7.234 to Xh 26.859Revision Date: SEPT 2011MD-90AIRWORTHINESS LIMITATIONS INSTRUCTIONS MDC-94K9000NOTE: ALL INTERVALS IN LANDINGS(CYCLES) UNLESS OTHERWISE NOTEDMcDonnell Douglas Corporation Proprietary Information. Use or disclosure ofTHESE DATA SUBJECT TO RESTRICTIVE LEGEND ON TITLE PAGE OR FIRST PAGE.B2-58INSPECTION INTERVALPSENumberDESCRIPTIONNDIPROCEDUREInitial RepeatZone(s)55.53.01.1Attach Angle, Top Fuselage to VerticalStabilizer Joint, STA 1458 to 1531Dorsal Fin Attach Angle & adjoining Fuselage SkinRefer to Section 260,00030,000310Prepared by: DESIGN & TECHNOLOGYRevision Date: SEPT 2011MD-90AIRWORTHINESS LIMITATIONS INSTRUCTIONS MDC-94K9000THE ILLUSTRATION SHOWN ON THIS PAGEIS FOR GENERAL IDENTIFICATION ONLY.SEE SECTION 2 FOR DETAILED NDI PROCEDURE AND ILLUSTRATION(s).B2-59McDonnell Douglas Corporation Proprietary Information. Use or disclosure ofTHESE DATA SUBJECT TO RESTRICTIVE LEGEND ON TITLE PAGE OR FIRST PAGE.PSE 55.53.01.1Dorsal Fin Attach Angle & adjoining Fuselage SkinRevision Date: SEPT 2011MD-90AIRWORTHINESS LIMITATIONS INSTRUCTIONS MDC-94K9000NOTE: ALL INTERVALS IN LANDINGS(CYCLES) UNLESS OTHERWISE NOTEDMcDonnell Douglas Corporation Proprietary Information. Use or disclosure ofTHESE DATA SUBJECT TO RESTRICTIVE LEGEND ON TITLE PAGE OR FIRST PAGE.B2-60INSPECTION INTERVALPSENumberDESCRIPTIONNDIPROCEDUREInitial RepeatZone(s)57.11.01.1.2.3.4Front Spar, STA Xcw 58.6 to Xw 560.8Lower Front Spar Splice at STA Xcw94.500, from STA Xcw 79.688 to Xcw104.500Lower Front Spar Stringer Runoutat STA Xcw 115.000, from STA Xcw104.500 to Xcw 121.688Lower Front Spar Stringer Runoutat STA Xrs 115.000, from STA Xrs91.000 to Xrs 137.750Lower Front Spar Stringer Runoutat STA Xrs 164.000, from STA Xrs137.750 to Xrs 267.000Refer to Section 260,00060,00060,00060,0001,2001,3006,3002,100142142520, 521,620, 621520, 521,620, 621Prepared by: DESIGN & TECHNOLOGYRevision Date: SEPT 2011MD-90AIRWORTHINESS LIMITATIONS INSTRUCTIONS MDC-94K9000THE ILLUSTRATION SHOWN ON THIS PAGEIS FOR GENERAL IDENTIFICATION ONLY.SEE SECTION 2 FOR DETAILED NDI PROCEDURE AND ILLUSTRATION(s).B2-61McDonnell Douglas Corporation Proprietary Information. Use or disclosure ofTHESE DATA SUBJECT TO RESTRICTIVE LEGEND ON TITLE PAGE OR FIRST PAGE.MD90-57-11-01-01CAG(IGDS)FWDOUTBDSTRINGER 27STAXcw=0.0STRINGER 26FRONTSPARREARSPARLEFT SIDE SHOWN(RIGHT SIDE OPPOSITE)IN SHADED AREASTAXcw=79.688STAXcw=79.688AFORWARDSKINSPLICEPLATESTRINGER 26INSPECT FRONT SPAR, SPLICE PLATE,SPLICE ANGLE, STRINGER 26AND LOWER FORWARD SKINSTAXcw=104.500STAXcw=94.500SPLICEANGLELOOKING UPLOWER FORWARD SKINVIEW AFRONTSPARPSE 57.11.01.1Lower Front Spar Splice at STA Xcw 94.500, from STA Xcw 79.688 to Xcw 104.500Revision Date: SEPT 2011Revision Date: SEPT 2011McDonnell Douglas Corporation Proprietary Information. Use or disclosure ofTHESE DATA SUBJECT TO RESTRICTIVE LEGEND ON TITLE PAGE OR FIRST PAGE.B2-62THIS PAGE INTENTIONALLY LEFT BLANKMD-90AIRWORTHINESS LIMITATIONS INSTRUCTIONS MDC-94K9000THE ILLUSTRATION SHOWN ON THIS PAGEIS FOR GENERAL IDENTIFICATION ONLY.SEE SECTION 2 FOR DETAILED NDI PROCEDURE AND ILLUSTRATION(s).B2-63McDonnell Douglas Corporation Proprietary Information. Use or disclosure ofTHESE DATA SUBJECT TO RESTRICTIVE LEGEND ON TITLE PAGE OR FIRST PAGE.MD90-57-11-01-02CAG(IGDS)FWDOUTBDVIEW ASTRINGER 25STAXcw=0.0STRINGER 25FRONTSPARREARSPARLEFT SIDE SHOWN(RIGHT SIDE OPPOSITE)ALOOKING UPLOWER FORWARD SKINFORWARDSKINFRONTSPARSPLICEPLATESPLICEPLATESTRINGER 24STRINGER 24STAXcw=104.500STAXcw=104.500STAXcw=121.688INSPECT FRONT SPAR, SPLICE PLATES,STRINGER 24, 25 AND LOWER FORWARD SKININ SHADED AREA.PSE 57.11.01.2Lower Front Spar Stringer Runout at STA Xcw 115.000, from STA Xcw 104.500 to Xcw 121.688Revision Date: SEPT 2011Revision Date: SEPT 2011McDonnell Douglas Corporation Proprietary Information. Use or disclosure ofTHESE DATA SUBJECT TO RESTRICTIVE LEGEND ON TITLE PAGE OR FIRST PAGE.B2-64THIS PAGE INTENTIONALLY LEFT BLANKMD-90AIRWORTHINESS LIMITATIONS INSTRUCTIONS MDC-94K9000THE ILLUSTRATION SHOWN ON THIS PAGEIS FOR GENERAL IDENTIFICATION ONLY.SEE SECTION 2 FOR DETAILED NDI PROCEDURE AND ILLUSTRATION(s).B2-65McDonnell Douglas Corporation Proprietary Information. Use or disclosure ofTHESE DATA SUBJECT TO RESTRICTIVE LEGEND ON TITLE PAGE OR FIRST PAGE.MD90-57-11-01-03CAG(IGDS)FWDOUTBDVIEW ASTAXcw=0.0FRONTSPARREARSPARLEFT SIDE SHOWN(RIGHT SIDE OPPOSITE)IN SHADED AREASTAXrs=91.000ALOOKING UPLOWER FORWARD SKINFORWARDSKINFRONTSPARSTRINGER 22FITTINGINSPECT FRONT SPAR, STRINGER 22,FITTING AND LOWER FORWARD SKINSTRINGER 22STAXrs=137.750STAXrs=115.000STAXrs=137.750MD90-57-11-01-03CAG(IGDS)FWDOUTBDVIEW ASTAXcw=0.0FRONTSPARREARSPARLEFT SIDE SHOWN(RIGHT SIDE OPPOSITE)IN SHADED AREASTAXrs=91.000ALOOKING UPLOWER FORWARD SKINFORWARDSKINFRONTSPARSTRINGER 22FITTINGINSPECT FRONT SPAR, STRINGER 22,FITTING AND LOWER FORWARD SKINSTRINGER 22STAXrs=137.750STAXrs=115.000STAXrs=137.750MD90-57-11-01-03CAG(IGDS)PSE 57.11.01.3Lower Front Spar Stringer Runout at STA Xrs 115.000, from STA Xrs 91.000 to Xrs 137.750Revision Date: SEPT 2011Revision Date: SEPT 2011McDonnell Douglas Corporation Proprietary Information. Use or disclosure ofTHESE DATA SUBJECT TO RESTRICTIVE LEGEND ON TITLE PAGE OR FIRST PAGE.B2-66THIS PAGE INTENTIONALLY LEFT BLANKMD-90AIRWORTHINESS LIMITATIONS INSTRUCTIONS MDC-94K9000THE ILLUSTRATION SHOWN ON THIS PAGEIS FOR GENERAL IDENTIFICATION ONLY.SEE SECTION 2 FOR DETAILED NDI PROCEDURE AND ILLUSTRATION(s).B2-67McDonnell Douglas Corporation Proprietary Information. Use or disclosure ofTHESE DATA SUBJECT TO RESTRICTIVE LEGEND ON TITLE PAGE OR FIRST PAGE.MD90-57-11-01-04CAG(IGDS)FWDOUTBDVIEW ASTAXcw=0.0FRONTSPARREARSPARLEFT SIDE SHOWN(RIGHT SIDE OPPOSITE)ALOOKING UPLOWER FORWARD SKINFORWARDSKINFRONTSPARSTRINGER 21STRINGER 20SPLICEFITTINGVOLTILONSTRINGER 20STRINGER 19STRINGER 21STAXrs=164.000STAXrs=267.000STAXrs=164.000STAXrs=137.750INSPECT FRONT SPAR, STRINGER 20, 21,SPLICE FITTING AND LOWER FORWARD SKININ SHADED AREA.MD90-57-11-01-04CAG(IGDS)FWDOUTBDVIEW ASTAXcw=0.0FRONTSPARREARSPARLEFT SIDE SHOWN(RIGHT SIDE OPPOSITE)ALOOKING UPLOWER FORWARD SKINFORWARDSKINFRONTSPARSTRINGER 21STRINGER 20SPLICEFITTINGVOLTILONSTRINGER 20STRINGER 19STRINGER 21STAXrs=164.000STAXrs=267.000STAXrs=164.000STAXrs=137.750INSPECT FRONT SPAR, STRINGER 20, 21,SPLICE FITTING AND LOWER FORWARD SKININ SHADED AREA.MD90-57-11-01-04CAG(IGDS)PSE 57.11.01.4Lower Front Spar Stringer Runout at STA Xrs 164.000, from STA Xrs 137.750 to Xrs 267.000Revision Date: SEPT 2011MD-90AIRWORTHINESS LIMITATIONS INSTRUCTIONS MDC-94K9000NOTE: ALL INTERVALS IN LANDINGS(CYCLES) UNLESS OTHERWISE NOTEDMcDonnell Douglas Corporation Proprietary Information. Use or disclosure ofTHESE DATA SUBJECT TO RESTRICTIVE LEGEND ON TITLE PAGE OR FIRST PAGE.B2-68INSPECTION INTERVALPSENumberDESCRIPTIONNDIPROCEDUREInitial RepeatZone(s)57.11.02.1.2Rear Spar, STA Xcw 121.6 to Xw 560.8Lower Rear Spar Splice at STA Xrs 111.500, from STA Xrs 85.000 to Xrs130.000Lower Rear Spar Outboard from STA Xrs 130.000 to Xrs 180.000Refer to Section 260,00060,0002,7004,400520, 521,620, 621520, 521,620, 621Prepared by: DESIGN & TECHNOLOGYRevision Date: SEPT 2011MD-90AIRWORTHINESS LIMITATIONS INSTRUCTIONS MDC-94K9000THE ILLUSTRATION SHOWN ON THIS PAGEIS FOR GENERAL IDENTIFICATION ONLY.SEE SECTION 2 FOR DETAILED NDI PROCEDURE AND ILLUSTRATION(s).B2-69McDonnell Douglas Corporation Proprietary Information. Use or disclosure ofTHESE DATA SUBJECT TO RESTRICTIVE LEGEND ON TITLE PAGE OR FIRST PAGE.MD90-57-11-02-01CAG(IGDS)FWDOUTBDVIEW AREARSPARSTRINGER 11STAXcw=0.0STRINGER 11AFTSKINFRONTSPARREARSPARALOOKING UPLOWER AFT SKINLEFT SIDE SHOWN(RIGHT SIDE OPPOSITE)IN SHADED AREASPLICEPLATESTAXrs=85.000STAXrs=111.500STAXrs=130.000STAXrs=111.500INSPECT REAR SPAR, SPLICEPLATE AND LOWER AFT SKINPSE 57.11.02.1Lower Rear Spar Splice at STA Xrs 111.500, from STA Xrs 85.000 to Xrs 130.000Revision Date: SEPT 2011Revision Date: SEPT 2011McDonnell Douglas Corporation Proprietary Information. Use or disclosure ofTHESE DATA SUBJECT TO RESTRICTIVE LEGEND ON TITLE PAGE OR FIRST PAGE.B2-70THIS PAGE INTENTIONALLY LEFT BLANKMD-90AIRWORTHINESS LIMITATIONS INSTRUCTIONS MDC-94K9000THE ILLUSTRATION SHOWN ON THIS PAGEIS FOR GENERAL IDENTIFICATION ONLY.SEE SECTION 2 FOR DETAILED NDI PROCEDURE AND ILLUSTRATION(s).B2-71McDonnell Douglas Corporation Proprietary Information. Use or disclosure ofTHESE DATA SUBJECT TO RESTRICTIVE LEGEND ON TITLE PAGE OR FIRST PAGE.MD90-57-11-02-02CAG(IGDS)FWDOUTBDVIEW AREARSPARSTRINGER 11STAXcw=0.0STRINGER 11AFTSKINFRONTSPARREARSPARLOOKING UPLOWER AFT SKINLEFT SIDE SHOWN(RIGHT SIDE OPPOSITE)IN SHADED AREAAVORTILONSTAXrs=164.000STAXrs=130.000STAXrs=164.000STAXrs=180.000INSPECT REAR SPARAND LOWER AFT SKINPSE 57.11.02.2Lower Rear Spar Outboardfrom STA Xrs 130.000 to Xrs 180.000Revision Date: SEPT 2011MD-90AIRWORTHINESS LIMITATIONS INSTRUCTIONS MDC-94K9000NOTE: ALL INTERVALS IN LANDINGS(CYCLES) UNLESS OTHERWISE NOTEDMcDonnell Douglas Corporation Proprietary Information. Use or disclosure ofTHESE DATA SUBJECT TO RESTRICTIVE LEGEND ON TITLE PAGE OR FIRST PAGE.B2-72INSPECTION INTERVALPSENumberDESCRIPTIONNDIPROCEDUREInitial RepeatZone(s)57.12.02.1.2Rear Spar, STA Xcw 58.6 Left to Xcw 58.6 RightLower Rear Spar Splice from STA Xcw 8.000 to Xcw 24.000Lower Rear Spar Inboard from STA Xcw 24.000 to Xcw 60.000Refer to Section 260,00060,0003,5004,200142142Prepared by: DESIGN & TECHNOLOGYRevision Date: SEPT 2011MD-90AIRWORTHINESS LIMITATIONS INSTRUCTIONS MDC-94K9000THE ILLUSTRATION SHOWN ON THIS PAGEIS FOR GENERAL IDENTIFICATION ONLY.SEE SECTION 2 FOR DETAILED NDI PROCEDURE AND ILLUSTRATION(s).B2-73McDonnell Douglas Corporation Proprietary Information. Use or disclosure ofTHESE DATA SUBJECT TO RESTRICTIVE LEGEND ON TITLE PAGE OR FIRST PAGE.MD90-57-12-02-01CAG(IGDS)FWDOUTBDVIEW AREARSPARSPLICEPLATESTRINGER 11STAXcw=0.0STRINGER 11AFTSKINFRONTSPARREARSPARASTAXcw=0.0LOOKING UPLOWER AFT SKINLEFT SIDE SHOWN(RIGHT SIDE OPPOSITE)IN SHADED AREASTAXcw=20.000STAXcw=8.000STAXcw=24.000INSPECT REAR SPAR, SPLICEPLATE AND LOWER AFT SKINPSE 57.12.02.1Lower Rear Spar Splice from STA Xcw 8.000 to Xcw 24.000Revision Date: SEPT 2011Revision Date: SEPT 2011McDonnell Douglas Corporation Proprietary Information. Use or disclosure ofTHESE DATA SUBJECT TO RESTRICTIVE LEGEND ON TITLE PAGE OR FIRST PAGE.B2-74THIS PAGE INTENTIONALLY LEFT BLANKMD-90AIRWORTHINESS LIMITATIONS INSTRUCTIONS MDC-94K9000THE ILLUSTRATION SHOWN ON THIS PAGEIS FOR GENERAL IDENTIFICATION ONLY.SEE SECTION 2 FOR DETAILED NDI PROCEDURE AND ILLUSTRATION(s).B2-75McDonnell Douglas Corporation Proprietary Information. Use or disclosure ofTHESE DATA SUBJECT TO RESTRICTIVE LEGEND ON TITLE PAGE OR FIRST PAGE.MD90-57-12-02-02CAG(IGDS)FWDOUTBDVIEW AREARSPARSTRINGER 11STAXcw=0.0STRINGER 11AFTSKINFRONTSPARREARSPARALOOKING UPLOWER AFT SKINLEFT SIDE SHOWN(RIGHT SIDE OPPOSITE)IN SHADED AREASTAXcw=42.000STAXcw=24.000STAXcw=42.000STAXcw=60.000INSPECT REAR SPARAND LOWER AFT SKINPSE 57.12.02.2Lower Rear Spar Inboard from STA Xcw 24.000 to Xcw 60.000Revision Date: SEPT 2011MD-90AIRWORTHINESS LIMITATIONS INSTRUCTIONS MDC-94K9000NOTE: ALL INTERVALS IN LANDINGS(CYCLES) UNLESS OTHERWISE NOTEDMcDonnell Douglas Corporation Proprietary Information. Use or disclosure ofTHESE DATA SUBJECT TO RESTRICTIVE LEGEND ON TITLE PAGE OR FIRST PAGE.B2-76INSPECTION INTERVALPSENumberDESCRIPTIONNDIPROCEDUREInitial RepeatZone(s)57.12.03.1Rear Spar, STA Xcw 58.6 to Xcw 121.6 (Left & Right Sides)Lower Rear Spar Splice from STA Xcw 60.000 to Xcw 100.000Refer to Section 260,0002,800142Prepared by: DESIGN & TECHNOLOGYRevision Date: SEPT 2011MD-90AIRWORTHINESS LIMITATIONS INSTRUCTIONS MDC-94K9000THE ILLUSTRATION SHOWN ON THIS PAGEIS FOR GENERAL IDENTIFICATION ONLY.SEE SECTION 2 FOR DETAILED NDI PROCEDURE AND ILLUSTRATION(s).B2-77McDonnell Douglas Corporation Proprietary Information. Use or disclosure ofTHESE DATA SUBJECT TO RESTRICTIVE LEGEND ON TITLE PAGE OR FIRST PAGE.MD90-57-12-03-01CAG(IGDS)FWDOUTBDVIEW AREARSPARSTRINGER 11STAXcw=0.0STRINGER 11AFTSKINFRONTSPARREARSPARALOOKING UPLOWER AFT SKINLEFT SIDE SHOWN(RIGHT SIDE OPPOSITE)IN SHADED AREASTAXcw=79.688STAXcw=79.688SPLICEPLATESTAXcw=100.000STAXcw=60.000INSPECT REAR SPAR, SPLICEPLATE AND LOWER AFT SKINPSE 57.12.03.1Lower Rear Spar Splice from STA Xcw 60.000 to Xcw 100.000Revision Date: SEPT 2011MD-90AIRWORTHINESS LIMITATIONS INSTRUCTIONS MDC-94K9000NOTE: ALL INTERVALS IN LANDINGS(CYCLES) UNLESS OTHERWISE NOTEDMcDonnell Douglas Corporation Proprietary Information. Use or disclosure ofTHESE DATA SUBJECT TO RESTRICTIVE LEGEND ON TITLE PAGE OR FIRST PAGE.B2-78INSPECTION INTERVALPSENumberDESCRIPTIONNDIPROCEDUREInitial RepeatZone(s)57.32.01.1Panels, Lower Wing, STA Xcw 58.6 to Xcw 560.8Center Wing Skin Splice at Stringer 17 from STA Xrs 121.688 to Xrs214.000Refer to Section 260,0009,400520, 521,620, 621Prepared by: DESIGN & TECHNOLOGYRevision Date: SEPT 2011MD-90AIRWORTHINESS LIMITATIONS INSTRUCTIONS MDC-94K9000THE ILLUSTRATION SHOWN ON THIS PAGEIS FOR GENERAL IDENTIFICATION ONLY.SEE SECTION 2 FOR DETAILED NDI PROCEDURE AND ILLUSTRATION(s).B2-79McDonnell Douglas Corporation Proprietary Information. Use or disclosure ofTHESE DATA SUBJECT TO RESTRICTIVE LEGEND ON TITLE PAGE OR FIRST PAGE.MD90-57-32-01-01CAG(IGDS)FWDOUTBDVIEW ASTRINGER 17STAXcw=0.0STRINGER 17FRONTSPARREARSPARALEFT SIDE SHOWN(RIGHT SIDE OPPOSITE)LOOKING UPCENTER WING SPLICEFORWARDSKINAFTSKINVORTILONSTRINGER 18STRINGER 16STAXrs=214.000STAXrs=111.500STAXrs=111.500STAXrs=121.688STAXrs=164.000STAXrs=214.000INSPECT STRINGER 17,FORWARD AND AFT SKININ SHADED AREA.PSE 57.32.01.1Center Wing Skin Splice at Stringer 17 from STA Xrs 121.688 to Xrs 214.000Revision Date: SEPT 2011MD-90AIRWORTHINESS LIMITATIONS INSTRUCTIONS MDC-94K9000NOTE: ALL INTERVALS IN LANDINGS(CYCLES) UNLESS OTHERWISE NOTEDMcDonnell Douglas Corporation Proprietary Information. Use or disclosure ofTHESE DATA SUBJECT TO RESTRICTIVE LEGEND ON TITLE PAGE OR FIRST PAGE.B2-80INSPECTION INTERVALPSENumberDESCRIPTIONNDIPROCEDUREInitial RepeatZone(s)57.32.02.1Cutouts, Lower Wing Door, STA Xcw 58.6 to Xcw 560.8Lower Surface Access Door Cutouts between STA Xrs 189.000 to Xrs 324.000Refer to Section 260,0008,000520, 521,620, 621Prepared by: DESIGN & TECHNOLOGYRevision Date: SEPT 2011MD-90AIRWORTHINESS LIMITATIONS INSTRUCTIONS MDC-94K9000THE ILLUSTRATION SHOWN ON THIS PAGEIS FOR GENERAL IDENTIFICATION ONLY.SEE SECTION 2 FOR DETAILED NDI PROCEDURE AND ILLUSTRATION(s).B2-81McDonnell Douglas Corporation Proprietary Information. Use or disclosure ofTHESE DATA SUBJECT TO RESTRICTIVE LEGEND ON TITLE PAGE OR FIRST PAGE.MD90-57-32-02-01CAG(IGDS)FWDOUTBDVIEW ASTAXcw=0.0FRONTSPARREARSPARLEFT SIDE SHOWN(RIGHT SIDE OPPOSITE)ASTRINGER 15STAXrs=189.00STRINGER 13STRINGER 12STRINGER 14AFTSKINSTAXrs=324.000STAXrs=189.000STAXrs=324.000IN SHADED AREA.ACCESS DOORCUTOUTINSPECT ACCESS DOOR CUTOUT,STRINGER 12, 15 AND LOWER AFT SKINLOOKING UPLOWER AFT SKINPSE 57.32.02.1Lower Surface Access Door Cutouts STA Xrs 189.000 to Xrs 324.000Revision Date: SEPT 2011MD-90AIRWORTHINESS LIMITATIONS INSTRUCTIONS MDC-94K9000NOTE: ALL INTERVALS IN LANDINGS(CYCLES) UNLESS OTHERWISE NOTEDMcDonnell Douglas Corporation Proprietary Information. Use or disclosure ofTHESE DATA SUBJECT TO RESTRICTIVE LEGEND ON TITLE PAGE OR FIRST PAGE.B2-82INSPECTION INTERVALPSENumberDESCRIPTIONNDIPROCEDUREInitial RepeatZone(s)57.34.01.1.2.3Panel, Lower Wing Skin, STA Xcw 58.6 Left to Xcw 58.6 RightCenter Wing Skin Splice at Stringer 17 from STA Xcw 20.000 to Xcw121.688Stringer 14, 15, 16 & Skin from STA Xcw 42.000 to Xcw 79.688Stringer 18, 19, 20 & Skin from STA Xcw 42.000 to Xcw 79.688Refer to Section 260,00060,00060,00010,50025,30025,300142142142Prepared by: DESIGN & TECHNOLOGYRevision Date: SEPT 2011MD-90AIRWORTHINESS LIMITATIONS INSTRUCTIONS MDC-94K9000THE ILLUSTRATION SHOWN ON THIS PAGEIS FOR GENERAL IDENTIFICATION ONLY.SEE SECTION 2 FOR DETAILED NDI PROCEDURE AND ILLUSTRATION(s).B2-83McDonnell Douglas Corporation Proprietary Information. Use or disclosure ofTHESE DATA SUBJECT TO RESTRICTIVE LEGEND ON TITLE PAGE OR FIRST PAGE.MD90-57-34-01-01CAG(IGDS)FWDOUTBDVIEW ASTAXcw=0.0FRONTSPARREARSPARLEFT SIDE SHOWN(RIGHT SIDE OPPOSITE)IN SHADED AREASTAXcw=20.000ASTRINGER 18STRINGER 16STRINGER 17STRINGER 17LOOKING UPCENTER WING SPLICEINSPECT STRINGER 17,LOWER FORWARD AND AFT SKINAFTSKINFORWARDSKINSTAXcw=20.000STAXcw=0.0STAXcw=121.688STAXcw=121.688PSE 57.34.01.1Center Wing Skin Splice at Stringer 17 from STA Xcw 20.000 to Xcw 121.688Revision Date: SEPT 2011Revision Date: SEPT 2011McDonnell Douglas Corporation Proprietary Information. Use or disclosure ofTHESE DATA SUBJECT TO RESTRICTIVE LEGEND ON TITLE PAGE OR FIRST PAGE.B2-84THIS PAGE INTENTIONALLY LEFT BLANKMD-90AIRWORTHINESS LIMITATIONS INSTRUCTIONS MDC-94K9000THE ILLUSTRATION SHOWN ON THIS PAGEIS FOR GENERAL IDENTIFICATION ONLY.SEE SECTION 2 FOR DETAILED NDI PROCEDURE AND ILLUSTRATION(s).B2-85McDonnell Douglas Corporation Proprietary Information. Use or disclosure ofTHESE DATA SUBJECT TO RESTRICTIVE LEGEND ON TITLE PAGE OR FIRST PAGE.MD90-57-34-01-02CAG(IGDS)FWDOUTBDVIEW ASTAXcw=0.0FRONTSPARREARSPARLEFT SIDE SHOWN(RIGHT SIDE OPPOSITE)STAXcw=58.688ASTRINGER 16STRINGER 14LOOKING UPLOWER AFT SKINAFTSKINSTAXcw=79.688STRINGER 15STAXcw=58.688STAXcw=42.000STRINGER 15INSPECT STRINGER 14, 15, 16AND LOWER AFT SKININ SHADED AREA.PSE 57.34.01.2Stringer 14, 15, 16 & Skin from STA Xcw 42.000 to Xcw 79.688Revision Date: SEPT 2011Revision Date: SEPT 2011McDonnell Douglas Corporation Proprietary Information. Use or disclosure ofTHESE DATA SUBJECT TO RESTRICTIVE LEGEND ON TITLE PAGE OR FIRST PAGE.B2-86THIS PAGE INTENTIONALLY LEFT BLANKMD-90AIRWORTHINESS LIMITATIONS INSTRUCTIONS MDC-94K9000THE ILLUSTRATION SHOWN ON THIS PAGEIS FOR GENERAL IDENTIFICATION ONLY.SEE SECTION 2 FOR DETAILED NDI PROCEDURE AND ILLUSTRATION(s).B2-87McDonnell Douglas Corporation Proprietary Information. Use or disclosure ofTHESE DATA SUBJECT TO RESTRICTIVE LEGEND ON TITLE PAGE OR FIRST PAGE.MD90-57-34-01-03CAG(IGDS)FWDOUTBDVIEW ASTAXcw=0.0FRONTSPARREARSPARLEFT SIDE SHOWN(RIGHT SIDE OPPOSITE)STAXcw=58.688ASTRINGER 20STRINGER 18STAXcw=79.688STRINGER 19STAXcw=58.688STAXcw=42.000STRINGER 19LOOKING UPLOWER FORWARD SKINFORWARDSKININSPECT STRINGER 18, 19, 20AND LOWER FORWARD SKININ SHADED AREA.PSE 57.34.01.3Stringer 18, 19, 20 & Skin from STA Xcw 42.000 to Xcw 79.688Revision Date: SEPT 2011

# REPORTING OF INSPECTION RESULTS

# MD-90 MDC-94Kg000
AIRWORTHINESS LIMITATIONS INSTRUCTIONS (ALl)

PSE REPORTING PROCEDURES

ReDortincj of Inspection Results

Whenever a PSE enters the inspection program phase, the form on page C1-2 shall be for providing further details when an inspection results in a crack finding.

Results of findings must be reported to Boeing Commercial Airplane Group at the following address;

Mail to: Senior Manager Stress and Aging Airplanes Technical and Fleet Support Service Engineering The Boeing Company Boeing Commercial Airplane Group Dept. L37 M/C D800-0037 P.O. Box 1771 Long Beach, California 90801-1771

McOonnell ~ Coqxxation Pro~rieta~ Information. Use of dsc~os~e of THESE DATA SUBJECT

TO RESTRICTIVE LEGEND ON TITLE PAGE OR FIRST PAGE C 

### 1-1 Revision Date: OCT 2001

# MD-90 PSE CRACK FINDINGS DETAIL FORM

Operator:. Reporting Date:

PSE SIDE SERIAL FUSELAGE DATE OF FLIGHT CYCLES/ TYPE OF NUMBER LH / RH NUMBER NUMBER INSPECTION HOURS LANDINGS INSPECTION

COMMENTS I ILLUSTRATIONS:

THIS PAGE MAY BE REPRODUCED 

### C1-2

### MD-90 AIRWORTHINESS LIMITATIONS INSTRUCTIONS (ALl)

NDI TECHNIQUES AND PROCEDURES MDC-94K9000

This section contains the MD-90 Principal Structural Element (PSE) Non-Destructive Inspection (NDI) techniques, tests and procedures.

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## P2-1 Revision Date: Original

### MD-90 MDC-94K9000 AIRWORTHINESS LIMITATIONS INSTRUCTIONS (ALI)

SECTION 2

TABLE OF CONTENTS

TC-2 Revision Date: September 2011 

### Title: Chapter Sub-Chapter Sequence No. Task No.:

Reference RF-1

CHAPTER 20 – STANDARD PRACTICES – AIRFRAME 20.00.00

CHAPTER 53 – FUSELAGE

Floor Beam to Frame Intersection, Overwing, STA’s 924 – 1041
Fuselage Skin and Frames from Longeron 16 to Longeron 19, at all Frames in area above Wing and MLG Wheel Well 53.12.09.1

CHAPTER 54 – NACELLES

Thrust Bulkhead, Pylon – STA Yn 170.5 Rear Spar and Engine Thrust Support Fitting (Upper & Lower) 54.10.04.1 Yoke – Forward Engine Mount, Pylon STA 1364 Pylon, Forward Upper & Lower Isolators and Cone Bolts 54.40.01.2
Links, Pylon Thrust Pylon, Thrust Struts 54.40.03.1
Pylon, thrust Isolator 54.40.03.2 Pylon, Aft Isolator Pylon, Aft Isolator & Cone Bolt 54.40.04.1

CHAPTER 55 – STABILIZERS

Horizontal Stabilizer Rear Spar Caps
Rear Spar Upper Cap - between STA Xe = 5.000 and Xe = 14.000 55.11.01.1

### MD-90 MDC-94K9000 AIRWORTHINESS LIMITATIONS INSTRUCTIONS (ALI)

SECTION 2

TABLE OF CONTENTS

TC-3 Revision Date: September 2011 

### Title: Chapter Sub-Chapter

SECTION 2 SUPPLEMENT

TABLE OF CONTENTS ................................................................................................ TC-4

EQUIPMENT UTILIZATION 2-0

REFERENCE STANDARDS 2-1

HIGH FREQUENCY EDDY CURRENT PROBES 2-2

LOW FREQUENCY EDDY CURRENT PROBES 2-3

INSPECTION FIXTURES 2-4

ULTRASONIC TRANSDUCERS 2-5

### MD-90 MDC-94K9000 AIRWORTHINESS LIMITATIONS INSTRUCTIONS (ALl)

SECTION 2

REFERENCES

=

. 

### Douglas Publication Entitled

"Nondestructive Testing Standard Practice Manual" (NDTSPM) Document No. MDC 93K0393

Douglas Publication Entitled

"MD-90 Aircraft Maintenance Manual" (AMM)

3, IAE/Goodrich Publication Entitled

" IAE Component Maintenance Manual" (CMM) for V2500/MD90 PYLON APRON ASSEMBLY

4. Lord Publication Entitled
"Component Maintenance Manual" (CMM)

RF-1 Revision Date: OCT 2001

### MD-90 MDC-94K9000 AIRWORTHINESS LIMITATIONS INSTRUCTIONS (ALl)
SECTION 2

STANDARD PRACTICES - AIRFRAME

° 

### General

A. 

### The Nondestructive Testing information previously documented in Chapter 20 has been updated and portions are now located in the Douglas Aircraft Company (DAC) Nondestructive Testing Standard Practice Manual (NDTSPM). Although the first release of the NDTSPM is in support of the Section 2 NDI Procedure requirements found within this document, the NDTSPM contains general NDT information and procedures applicable to all DAC aircraft.

B. Please refer to the NDTSPM as noted below for the following subjects:

Introduction

Part 01 General Information

Part 02 X-Ray

Part 03 Gamma-Ray

Part 04 Ultrasonic

Part 05 Sonic/Resonance

Part 06 Eddy Current

Part 07 Magnetic Particle

Part 08 Penetrant

Part 09 Visual/Optical

Part 10 Physical/Mechanical

Part 11 Chemical

Part 12 Leak Testing

Part 13 Thermal

Part 14 Laser or Light Energy (Proposed)

(Proposed)

(Proposed)

(Proposed)

(Proposed)



## Nondestructive Testing Methods - General
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## 20-00-00 Page 1 OCT 2001

# NDI TECHNIQUES

AND PROCEDURES

### MD-90 MDC-94K9000 AIRWORTHINESS LIMITATIONS INSTRUCTIONS (ALI)
SECTION 2
NDI PROCEDURES



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### September 2011 Title : Floor Beam to Frame Intersection, Overwing, STA’s 924 – 1041, Fuselage Skin and Frames from Longeron 16 to Longeron 19, at all Frames in area above Wing and MLG Wheel Well

Inspection Item : PSE 53.12.09.1

Model Affected : MD-90

Ships Affected : All

Service Bulletin : MD90-53A031

Drawing Reference : 9936483, 9936482, 9923410, 9923411, 9923412, 9923413, 9923414, 9936508, 9923435, 9919649

Requirement : TO COMPLETE THE REQUIREMENTS OF THIS PSE, THE PRIMARY

INSPECTION (01), OF EACH INSPECTION SEQUENCE, OR ITS

ALTERNATE SUBSTITUTE(S) MUST BE ACCOMPLISHED

. NOTES: (1) ALTERNATE INSPECTIONS WILL BE IDENTIFIED BY NUMERALS OTHER THAN 01.

(2) MULTIPLE ALTERNATE INSPECTIONS WHICH MUST BE PERFORMED TO ADEQUATELY REPLACE A PRIMARY INSPECTION WILL BE IDENTIFIED BY AN ALPHA CHARACTER FOLLOWING THE ALTERNATE DESIGNATOR, i.e., 02a and 02b, ETC.

Inspection Sequence 1 : (Outer Fuselage Skin)

01. Eddy Current, High Frequency

Inspection Sequence 2: (Inner Fuselage Skin)

01. Eddy Current, High Frequency

Inspection Sequence 3: (Frame Outer Flange)

01. Eddy Current, High Frequency

Inspection Sequence 4: (Frame Inner Flange)

01. Eddy Current, High Frequency

### MD-90 MDC-94K9000 AIRWORTHINESS LIMITATIONS INSTRUCTIONS (ALI)
SECTION 2
NDI PROCEDURES



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### Description :

Inspection Sequence 1 is a high frequency eddy current inspection of the fuselage skin at the fastener holes common to the frame. Inspect the skin from Longerons 16 to 19 at each of the ten frame locations where accessible. The purpose of these inspections is to detect fatigue cracks initiating at the fastener holes as shown on Figures 1, 2, and 3. The fatigue cracks will emanate in the forward and aft directions. Both sides of the fastener holes will be inspected.

Inspection Sequence 2 is a high frequency eddy current inspection of the fuselage skin from inside the cabin adjacent to the frames. Inspect the skin from Longerons 16 to 19 at each of the ten frame locations where accessible. The purpose of these inspections is to detect fatigue cracks initiating from beneath the frame and propagating beyond the frames. The fatigue cracks will emanate in the forward and aft directions. Both forward and aft sides of the frames will be inspected. See Figures 4 and 5.

Inspection Sequence 3 is a high frequency eddy current inspection of the frames at the outboard flange inboard face around the fasteners common with the fuselage skin. Inspect the frame from Longerons 16 to 19 at each of the ten frame locations where accessible. The purpose of these inspections is to detect fatigue cracks initiating at the fastener holes as shown on Figure 4 and 5. The fatigue cracks will emanate in the forward and aft directions.

Inspection Sequence 4 is a high frequency eddy current inspection of the frames at the inboard flange, inboard face at the leading and trailing edges of the “I beam” type configuration frames or the open side of the “C” channel type frames. Inspect the frame from Longerons 16 to 19 at each of the ten frame locations where accessible. The purpose of these inspections is to detect fatigue cracks initiating at the edge of the flange as shown on Figure 4 and 5. The fatigue cracks will emanate in the forward and aft directions.

### MD-90 MDC-94K9000 AIRWORTHINESS LIMITATIONS INSTRUCTIONS (ALI)
SECTION 2
NDI PROCEDURES



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### September 2011 Access:

FOLLOW APPLICABLE SAFETY INSTRUCTIONS AND PRECAUTIONS PER THE NONDESTRUCTIVE TESTING STANDARD PRACTICE MANUAL (NDTSPM) PART 01-00-01 AS WELL AS ALL LOCAL AND COMPANY REQUIREMENTS.

A. Major Zone 100, Submajor Zone 150, remove panels 150CL, 150FL, 150ML, and 150RL.

B. Major Zone 100, Submajor Zone 160, remove panels 160CR, 160FR, 160MR, and 160RR.

C. Remove seats, wall paneling, insulation, and floor panels per Chapter 25 of the MD-90 Maintenance Manual between fuselage stations Y=883.000 to Y=1060.000.

D. For access to aft side of Sta. 1060.000 frame below Longeron 18 on aft side, remove wall paneling, ceiling panels, and insulation per Chapter 25 of the MD-90 Maintenance Manual at fuselage station Y=1060.000 in the cargo bay area.

Preparation for Inspection :

A. Remove all dirt, grease, and loose paint from the inspection area.

B. Thoroughly clean the inspection area with an approved cleaning agent.

General Visual Inspection :

A. Perform a preliminary check of the general PSE area for cleanliness, presence of foreign objects, distortion, damage, cracks, corrosion, security of parts and evidence of loose attachments.

B. After completion of general area check, perform the specific PSE inspection(s) to complete the requirement.

NOTE : The presence of repairs and/or modifications in the inspection area may affect the inspectability of this PSE. Inspect non-discrepant areas of the PSE and report details of the discrepancy with inspection results to BCA-LBD.

C. If additional information regarding visual inspection is desired, See Part 09 of the NDTSPM.

### MD-90 MDC-94K9000 AIRWORTHINESS LIMITATIONS INSTRUCTIONS (ALI)
SECTION 2
NDI PROCEDURES



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### Inspection Procedure:

A. Inspection Sequence 1:

1. Inspection Method 01 (Eddy Current, High Frequency)

a. Utilizing the information supplied in Figures 1, 2, and 3, perform a surface eddy current inspection of the fuselage skin at the fastener holes common to the frame. Inspect the skin from Longerons 16 to 19 at each of the ten frame locations where accessible. The purpose of these inspections is to detect fatigue cracks initiating at the fastener holes and propagating in the forward and aft directions. Scan around the fasteners following the instructions found in the NDTSPM 06-10-01.001 (HFET - Procedure 1). Use Calibration Method “P” and Scan Method “47”.

B. Inspection Sequence 2:

1. Inspection Method 01 (Eddy Current, High Frequency)

a. Utilizing the information supplied in Figures 1, 4, and 5, perform a surface eddy current inspection of the fuselage skin from inside the cabin adjacent to the frames. Inspect the skin from Longerons 16 to 19 at each of the ten frame locations where accessible. The purpose of these inspections is to detect fatigue cracks initiating from beneath the frame and propagating in the forward and aft directions. Scan the forward and aft sides of the inner skin adjacent to the frame following the instructions found in the NDTSPM 06-10-01.001 (HFET - Procedure 1). Use Calibration Method “R” and Scan Method “63”.

C. Inspection Sequence 3:

1. Inspection Method 01 (Eddy Current, High Frequency)

a. Utilizing the information supplied in Figures 1, 4, and 5, perform a surface eddy current inspection of the frames at the outboard flange inboard face around the fasteners common with the fuselage skin. Inspect the frame from Longerons 16 to 19 at each of the ten frame locations where accessible. The purpose of these inspections is to detect fatigue cracks initiating at the fastener holes and propagating in the forward and aft directions Scan around the fasteners following the instructions found in the NDTSPM 06-10-01.001 (HFET - Procedure 1). Use Calibration Method “K” and Scan Method “44”.

### MD-90 MDC-94K9000 AIRWORTHINESS LIMITATIONS INSTRUCTIONS (ALI)
SECTION 2
NDI PROCEDURES



# 53.12.09.1

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### September 2011 D. Inspection Sequence 4:

1. Inspection Method 01 (Eddy Current, High Frequency)

a. Utilizing the information supplied in Figures 1, 4, and 5, perform a surface eddy current inspection of the frames at the inboard flange, inboard face at the leading and trailing edges of the “I beam” type configuration frames or the open side of the “C” channel type frames. Inspect the frame from Longerons 16 to 19 at each of the ten frame locations where accessible. The purpose of these inspections is to detect fatigue cracks initiating at the edge of the flange and propagating in the forward and aft directions. Perform a surface eddy current inspection of the frame following the instructions found in the NDTSPM 06-10- 01.001 (HFET - Procedure 1). Use Calibration Method “A” and Scan Method “79”.

Inspection Results:

A. Any indication is considered a crack which exhibits the same relative phase angle and an amplitude of 50 percent or greater than the indication obtained from the calibration notch in the reference standard.

B. Report all inspection results, Positive, Negative, or Discrepant.

1. Positive - Cracks found 2. Negative - Cracks not found 3. Discrepant - PSE inspection could not be completed or performed due to obstruction or other physical anomalies.

### MD-90 MDC-94K9000 AIRWORTHINESS LIMITATIONS INSTRUCTIONS (ALI)
SECTION 2
NDI PROCEDURES



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### Post Inspection Procedure:

A. Remove and secure all test equipment and materials from the area.

B. Install seats, wall paneling, insulation, and floor panels per Chapter 25 of the MD-90 Maintenance Manual between fuselage stations Y=883.000 to Y=1060.000.

C. Major Zone 100, Submajor Zone 150, install panels 150CL, 150FL, 150ML, and 150RL.

D. Major Zone 100, Submajor Zone 160, install panels 160CR, 160FR, 160MR, and 160RR.

E. Install wall paneling, ceiling panels, and insulation per Chapter 25 of the MD-90 Maintenance Manual at fuselage station Y=1060.000 in the cargo bay area.

### MD-90 MDC-94K9000 AIRWORTHINESS LIMITATIONS INSTRUCTIONS (ALI)
SECTION 2
NDI PROCEDURES



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NDI PROCEDURES



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SECTION 2
NDI PROCEDURES



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NDI PROCEDURES



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NDI PROCEDURES



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### MD-90 MDC-94K9000 AIRWORTHINESS LIMITATIONS INSTRUCTIONS (ALl)

SECTION 2
NDI PROCEDURES

Title: Rear Spar and Engine Thrust Support Fitting (Upper and Lower)

Inspection Item: PSE 54.10.04.1

Model Affected: MD-90

Ships Affected: 2094, 2095, 2096, 2097, 2098, 2099, 2100, 2115, 2117, 2120, 2122, 2123

Service Bulletin: MD-90-54-001

Drawing Reference: 5965128, 5965673

Requirement: TO COMPLETE THE REQUIREMENTS OF THIS PSE, THE PRIMARY

INSPECTION (01), OF EACH INSPECTION SEQUENCE, OR ITS

ALTERNATE SUBSTITUTE(S) MUST BE ACCOMPLISHED.

NOTES: (1) ALTERNATE INSPECTIONS WILL BE IDENTIFIED

NUMERALS OTHER THAN 01.

(2) MULTIPLE ALTERNATE INSPECTIONS WHICH MUST BE PERFORMED TO ADEQUATELY REPLACE A PRIMARY INSPECTION WILL BE IDENTIFIED BY AN ALPHA CHARACTER FOLLOWING THE ALTERNATE DESIGNATOR, i.e., 02a and 02b, ETC.

Inspection Sequence 1: (Upper and Lower Thrust Plates)

01. Eddy Current, High Frequency

Inspection Sequence 2: (Rear Spar and Thrust Support Fitting Caps)

01. Eddy Current, High Frequency

Inspection Sequence 3: (Radius of Thrust Plates)

01. Eddy Current, High Frequency

Inspection Sequence 4: (Rear Spar and Thrust Support Fitting Web)

01. Eddy Current, High Frequency

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SECTION 2
NDI PROCEDURES



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### Inspection Sequence 5: (Thrust Plates at Heat Shield Mount Plates)

01. Eddy Current, High Frequency

Description :

Inspection Sequence 1 is a high frequency eddy current inspection of the upper and lower thrust plates at the fastener holes common to the rear spar and thrust support fitting upper and lower caps. This sequence also inspects the thrust plates at fastener holes common to the –5 angle on the upper side and the –7 angle on the lower side. The purpose of these inspections is to detect fatigue cracks initiating at the fastener holes as shown on Figures 2, 3, and 4. The fatigue cracks will emanate in the forward and aft directions. Both sides of the fastener holes will be inspected. See Figures 2, 3, and 4.

Inspection Sequence 2 is a high frequency eddy current inspection of the rear spar and thrust support fitting upper and lower caps at the fastener holes common to the upper and lower thrust plates. The purpose of these inspections is to detect fatigue cracks initiating at the fastener holes as shown on Figures 2 and 3. The fatigue cracks will emanate in the forward and aft directions. Both sides of the fastener holes will be inspected. See Figures 2 and 3.

Inspection Sequence 3 is a high frequency eddy current inspection of the upper and lower thrust plates at the radius of the angle on the forward and aft sides (top side) of the upper plate and similarly for the bottom side of the lower plate. The purpose of these inspections is to detect fatigue cracks initiating at the forward and aft edges of the plates as shown on Figure 4 and 5. The fatigue cracks will emanate in the forward and aft directions. See Figures 4 and 5.

Inspection Sequence 4 is a high frequency eddy current inspection of the rear spar web and the thrust support fitting web adjacent to the upper and lower thrust plates at Zn=6.000 and Zn= -6.000. The purpose of these inspections is to detect fatigue cracks initiating at the top or bottom of the rear spar web and the thrust support fitting web adjacent to the thrust plates as shown on Figure 6. The fatigue cracks will emanate in the up or down direction. See Figure 6.

Inspection Sequence 5 is a high frequency eddy current inspection of the upper and lower thrust plates around and adjacent to the heat shield mount plates. The purpose of these inspections is to detect fatigue cracks initiating at the fastener holes in common with the thrust plates and the heat shield mount plates. The fatigue cracks will emanate in the forward and aft directions. See Figures 2 and 3.

### MD-90 MDC-94K9000 AIRWORTHINESS UMITATIONS INSTRUCTIONS (AU)
SECTION 2 NDI pROCEDURES

Access:

FOLLOW APPLICABLE SAFETY INSTRUCTIONS AND PRECAUTIONS PER THE NONDESTRUCTIVE TESTING STANDARD PRACTICE MANUAL (NDTSPM) PART 01-00-01 AS WELL AS ALL LOCAL AND COMPANY REQUIREMENTS.

A. Remove engine nacelles.

Preparation for Inspection:

A. Remove all dirt, grease, and loose paint from the inspection area.

B. Thoroughly clean the inspection area with an approved cleaning agent.

General Visual Inspection:

A. Perform a preliminary check of the general PSE area for cleanliness, presence of foreign objects, distortion, damage, cracks, corrosion, security of parts and evidence of loose attachments.

B. After completion of general area check, perform the specific PSE inspection(s) complete the requirement.

NOTE: The presence of repairs and/or modifications in the inspection area may affect the inspectability of this PSE. Inspect non-discrepant areas of the PSE and report details of the discrepancy with inspection results to BCA-LBD.

C. If additional information regarding visual inspection is desired, See Part 09 of the NDTSPM.

Inspection Procedure:

A. Inspection Sequence 1:

I. Inspection Method 01 (Eddy Current, High Frequency)

ao 

### Utilizing the information supplied in Figures 2, 3, and 4, perform a surface eddy current inspection of the upper and lower thrust plates from outside the torque box. Scan the forward and aft sides of the fasteners following the instructions found in the NDTSPM 06-10-01.001 (HFET - Procedure 1). Use Calibration Method =L ~ and Scan Method =42".

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### MD-90 MDC-94K9000 AIRWORTHINESS LIMITATIONS INSTRUCTIONS (ALI)
SECTION 2
NDI PROCEDURES



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### B. Inspection Sequence 2:

1. Inspection Method 01 (Eddy Current, High Frequency)

a. Utilizing the information supplied in Figures 2 and 3, perform a surface eddy current inspection of the rear spar cap and thrust support fitting from inside the torque box. Scan around the forward and aft sides of the fasteners. Scan the fastener hole areas following the instructions found in the NDTSPM 06-10- 01.001 (HFET - Procedure 1). Use Calibration Method “L” and Scan Method “41”.

C. Inspection Sequence 3:

1. Inspection Method 01 (Eddy Current, High Frequency)

a. Utilizing the information supplied in Figures 4 and 5, perform a surface eddy current inspection of the upper and lower thrust plates from outside the torque box. Scan the forward and aft sides of the thrust plates at the radii of the angle following the instructions found in the NDTSPM 06-10-01.001 (HFET - Procedure 1). Use Calibration Method “G” and Scan Method “69”.

D. Inspection Sequence 4:

1. Inspection Method 01 (Eddy Current, High Frequency)

a. Utilizing the information supplied in Figure 6, perform a surface eddy current inspection of the forward side of the rear spar adjacent to the upper thrust plate on the upper side and adjacent to the lower thrust plate on the lower side. Perform a surface eddy current inspection of the aft side of the thrust support fitting adjacent to the upper thrust plate on the upper side and adjacent to the lower thrust plate on the lower side. Scan following the instructions found in the NDTSPM 06-10-01.001 (HFET - Procedure 1). Use Calibration Method “R” and Scan Method “63”.

### MD-90 MDC-94K9000 AIRWORTHINESS LIMITATIONS INSTRUCTIONS (ALl)
SECTION 2
NDI PROCEDURES

E. Inspection Sequence 5:

1. Inspection Method 01 (Eddy Current, High Frequency)

ao 

### Utilizing the information supplied in Figures 2 and 3, perform a surface eddy current inspection of the upper and lower thrust plates adjacent to the upper and lower heat shield mount plates. Scan the thrust plates on the forward, aft, and inboard sides of the heat shield mount plates as shown. Scan following the instructions found in the NDTSPM 06-10-01.001 (HFET - Procedure 1). Use Calibration Method "R" and Scan Method =45".

Inspection Results:

Ao 

### Any indication is considered a crack which exhibits the same relative phase angle and an amplitude of 50 percent or greater than the indication obtained from the calibration notch in the reference standard.

B. Report all inspection results, Positive, Negative, or Discrepant.

1. Positive - Cracks found 2. Negative - Cracks not found 3. Discrepant - PSE inspection could not be completed or performed due to obstruction

or other physical anomalies.

Post Inspection Procedure:

A. Remove and secure all test equipment and materials from the area.

B. Install engine nacelles as required.

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## MD-90

AIRWORTHINESS LIMITATIONS INSTRUCTIONS (ALl) SECTION 2
NDI PROCEDURES MDC-94K9000

FUSELAGE AUXILIARY SPAR

PLATE

~/

~~/~-~ THRUST SUPPORT

:::::"’i...:~. ~ ’~::-<::~:"

REAR SPAR ~ ":" 0 ~ g)



# ~ ,~C (FIG 3)

INSPECT REAR SPAR AND ENGINE THRUST SUPPORT 

### VIEW A FITTING (UPPER AND LOWER CAPS) IN SHADED AREA. LEFT SIDE SHOWN (RIGHT SIDE OPPOSITE) ENGINE THRUST SUPPORT FITTING

MI~O-54.10.O4.1F1


# 54.10.04.1 Page 6 October 2001 INSPECTION AREA Figure 1

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### MD.90 AIRWORTHINESS LIMITATIONS INSTRUCTIONS (ALl)
SECTION 2
NDI PROCEDURES MDC-94K9000

CRACKS (T’YPICAL) -5 ANGLE

,| II 

### 0 O O 0 0,

,

EDDY CURRENT PROBE (TYPICAL)

SCAN DIRECTION (D ~\

. (TYPICAL) "" ........ 

### O REAR SPAR ’~’ O II UPPER CAP ~ I 

### © ©

IST SUPPORT FI’I-I’ING UPPER CAP

=../(~,~501) SCAN UPPER THRUST PLATE

ADJACENT TO HEAT SHIELD UPPER MOUNT PLATE 

# P °PPE" .osT o ’;3..-- o

.~TA

0 YN=170.500 HEAT SHIELD / UPPER MOUNT PLATE



### OANDID WEIGHT SAVINGS DESIGN (P/N 5965673)

PRE-WEIGHT SAVINGS DESIGN ........

(P/N 5965128)



### ~IFWD ~e’, ,, © O T~D ’ ,

’~qD ~’ ’~ ql) 

### VIEW B-B (FIG I) ’~ (D ’, ! (D VIEW LOOKING DOWN, LEFT SIDE, FRAME STATION YN=170.500 ~ (D i! (D t I 

# (RIGHT S,DE oPPosi~ ~,

o ’,,

. ...~-- 

# \,>’,

.......... --,,,: ~

I (101) SCAN UPPER THRUST PLATE ON FORWARI ~l ~.~-’"~"~.~" O

(~1~ AND AFT SLOES OF SHADED FASTENERS

(I ~01) SCAN FORWARD AND AFT SIDES OF SHADED FASTENERS

ON REAR SPAR UPPER CAP AND THRUST SUPPORT FITTING UPPER CAP FROM INSIDE AFT TORQUE BOX

MDg0-B4.10,04.1F2



### HIGH FREQUENCY EDDY CURRENT INSPECTION OF UPPER PLATE Figure 2

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## MD-90 MDC-94K9000

AIRWORTHINESS LIMITATIONS INSTRUCTIONS (ALl) SECTION 2 NDIPROCEDURES

HEAT SHIELD LOWER MOUNT ~._ ~



# o i ’O" REAR SPAR ~~~....._ / c~o,> scAR LDWER ~RUST.~

LOWER CAP ~_//"~"~"’’~t 4~_" ADJACENT TO HEAT SHIELD 

# ~,,c~.> "~.//. ~. ; - 7 " ’ ~ ~il

//(¢~.’ ,,’~ e_ll

//

~~ ’ I’~T~""~= TH RU ST SUPPORT

(TYPICAL) ~"..7~...~ PROBE(TYPICAL)

~ (D II



## I1_~.,"~’-"; I @ " 

# II ~),’:’:".Z~

 ̄  ̄  ̄  ̄  ̄ ’,: ~ //o

II " ,,’ ̄ W-’~
- - 1.1~.~ _ v r~ 

# +,,.o~ y2 ~.<,’__ ~ o :’,;;," I PRE-WEIGHT SAVINGS DESIGN i J _" ; - "" -- -’- L, - I

CP/N 5965128) 

## OTBD # e ,, I -_’~



# Is,’ !~ 

# 1’>,. :: iD, ,iD 

# v,Ew c-c <,,o,> !_’>,i i

VIEW LOOKING UP, LEFT SIDE, ~’ (D ; (D FRAME STATION YN=170.500 ~’Ar~ ,’ 

# ~.,G.’r SIDE OPPOS,m ~  ̄ t i ~. ,’0  ̄  ̄  ̄  ̄ -- _JL-" ---

WEIGHT SAVINGS DESIGN  ̄ AND (D (1101) SCAN LOWER THRUST PLATE ON FORWARD (P/N 5965673) 

# ~T~

AND AFT SIDES OF SHADED FASTENERS

lr 

### © | (201) SCAN FORWARD AND AFT SIDES OF SHADED FASTENERS ,41, ON REAR SPAR LOWER CAP AND THRUST SUPPORT 

## C|~ Fn’nNG ,OWER CAP FROM INSIDE AFTTORQUEBOX

MDgO-54.10.O4.1F3 

### HIGH FREQUENCY EDDY CURRENT INSPECTION OF LOWER PLATE Figure 3


# 54.10.04.1 Page 8 October 2001 McDonnell Douglas Corporation Proprietary Information. Use or disclosure of THESE SUBJECT TO RESTRICTIVE LEGEND ON TITLE PAGE OR FIRST PAGE.

## MD-90 AIRWORTHINESS LIMITATIONS INSTRUCTIONS (ALl) SECTION 2
NDI PROCEDURES MDC-94K9000

UPPER THRUST SCAN DIRECTION PLATE

J ! 

## ,O O

o ooo ooo E (FIG 6) t Ol, O  ̄  ̄  ̄  ̄  ̄ I STA
ZN=6.000

! I I

| F (FIG 6) CURRENT = , PROBE (TYPICAL) 

## I

II ~ I (301) SCAN RADIUS PLATEANGLEON

UPPER AND LOWER THRUST PLATE ON FORWARD AND AFT EDGEDS AS SHOWN IN SHADED AREA (4 PLACES)



## UP

~1 FWD

,.-THRUST SUPPORT
t FII-nNG | 

# o o o o o
STA J ,.x~,.~x\ WEIGHT SAVINGS DESIGN

I ZN=’6’000

~ . . . . . . ..  ̄

 ̄  ̄

 ̄ "  ̄ "~ [ (P/N5965673)



# ~[~
OlO 0 0 0 0 0 00uO 

## E’ .4~ o ’,

,, o o ~- iLol ,~

// , F .ooo oo.. 0, ,0 0 ’ ’

, , , ,, _ ,--JI , ,

. ’, , ! PRE-WEIGHT SAVINGS DESIGN

" ’ ! (P/N 5965128) STA

i ! YN=170.500 

## VIEW D-D (FIG 1)
VIEW LOOKING INBOARD, LEFT SIDE, FRAME STATION YN=170.500 (RIGHT SIDE OPPOSITE)

O I (101) SCAN UPPER AND LOWER THRUST PLATE ON FORWARD
(~T~ AND AFT SIDES OF SHADED FASTENERS



## HIGH FREQUENCY EDDY CURRENT INSPECTION OF UPPER AND LOWER PLATE

Figure 4

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# 54.10.04.1 Page 9 October 2001

### MD-90

AIRWORTHINESS LIMITATIONS INSTRUCTIONS (ALl)
SECTION 2
NDI PROCEDURES MDC-94K9000

LOWER INSPECTION AREA



### VIEW A (FIG 1) VIEW LOOKING INBOARD AND AFT, LEFT SIDE,

FRAME STATION YN=170.500 (RIGHT SIDE OPPOSITE) 

# ~h,~ 301) SCAN RADIUS OF PLATE ANGLE ON UPPER AND LOWER THRUST PLATES ON FORWARD AND AFT EDGES AS SHOWN IN SHADED AREA 

### UP

~FWD

MDgO-54.10.04.1F5



# 54.10.04.1 Page 10 October 2001 HIGH FREQUENCY EDDY CURRENT INSPECTION OF UPPER AND LOWER PLATE

Figure 5

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## MD-90 AIRWORTHINESS LIMITATIONS INSTRUCTIONS (ALl)
SECTION 2
NDI PROCEDURES MDC-94K9000

0

0

0

0

0

0

0 

# I° \

UP
OTBD PROBE (TYPICAL)

THRUST SUPPORT FITTING

/REAR SPAR ,e.-."

,.;>:..:.::;: ,,,,.~ STA

ZN=-6.000

LOWER THRUST PLATE UPPER THRUST PLATE 

# \

0

0

0

0

0

0

0

0

0

0



# /

LOWER THRUST PLATE 

# \

CRACK CrYPICAL)



## UP OTBD 

# H

VIEW E-E (FIG 4) 

### VIEW LOOKING AFT AT REAR SPAR, LEFT SIDE (RIGHT SIDE

OPPOSITE) 

## VIEW F-F (FIG 4) V1EW LOOKING FORWARD AT THRUST SUPPORT FII"rlNG, LEFT SIDE (RIGHT SIDE OPPOSITE)



# ~=~ 401) SCAN ALONG FORWARD SIDE OF REAR SPAR AND AFT SIDE OF THRUST SUPPORT FR-rlNG AT ZN-6.000 AND ZN=-6.000 IN SHADED AREAS



### HIGH FREQUENCY EDDY CURRENT INSPECTION OF REAR SPAR AND THRUST SUPPORT FITTING Figure 6

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# 54.10.04.1

Page 11 October 2001

### THIS PAGE INTENTIONALLY LEFT BLANK

### MD-90 MDC-94K9000 AIRWORTHINESS LIMITATIONS INSTRUCTIONS (ALl)
SECTION 2
NDI PROCEDURES

Title:

Inspection Item:

Model Affected:

Ships Affected:
Service Bulletin:

Drawing Reference:

Inspection Requirements: Pylon, Forward Upper and Lower Isolators and Cone Bolts

PSE 54.40.01.2

MD-90 All Series

All

None

5940573, LM-442-SA2, LM-442-SA20, LM-442-1

See Lord Component Maintenance Manual. Refer to Documents 71-20-27 and 71-20-24, pages 501 and subsequent pages and Figure 1 of this document for specific inspection requirements. For manual and updates contact

Lord Aerospace Products Lord Corporation 1635 West 12th Street Erie, PA 16514 Phone: (814) 456-8511

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# 54.40.01.2 Page 1 October 2001

## MD-90 AIRWORTHINESS LIMITATIONS INSTRUCTIONS (ALl)
SECTION 2 NDI PROCEDURES MDC-94K9000

 ̄ 0 0 qo"

~t~q~ 0 0

......~ ~ 

## °o ° "---
~ N~B

J \ UPPER COVER 

## t~ ~ ~B~ON PLATE
YOKE

~ ISOLATOR LM-442-SA2 OR LM-442.SA20

/

"~ LOWER

VIBRATION ISOLATOR LM-442-SA2 OR LM-442-SA20



# ~~ ~’"~’--.~ COVER PLATE

CONE BOLT

INSPECT- FORWARD UPPER AND LOWER ISOLATORS ~~/ 2-1"¢v~ /LM-44

AND CONE BOLTS PER LORD MAINTENANCE MANUAL

MD90-54.40,01.2F1 

# 54.40.01.2 Page 2 October 2001 INSPECTION ZONE Figure I

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### MD-90 MDC-94K9000 AIRWORTHINESS LIMITATIONS INSTRUCTIONS (ALI)
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NDI PROCEDURES



# 54.40.03.1

McDonnell Douglas Corporation Proprietary Information. Use or disclosure of 

### Page 1

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### September 2011 Title : Pylon, Thrust Struts

Inspection Item : PSE 54.40.03.1

Model Affected : MD-90 All Series

Ships Affected : All

Service Bulletin : None

Drawing Reference : ROHR 290-PL-2001

Inspection Requirements :

See International Aero Engines (IAE)/Goodrich Component

Maintenance Manual. Refer to Document 71-14-00, pages 501 and

subsequent pages, and Figure 1 of this document for specific inspection

requirements. For manual and updates, contact:

Goodrich Aerospace/Aerostructures Group

850 Lagoon DR.

Chula Vista, CA 91910

Telephone (619) 691-2719

techpubs@goodrich.com

### MD-90 AIRWORTHINESS LIMITATIONS INSTRUCTIONS (ALl)
SECTION 2
NDI PROCEDURES MDC-94K9000

THRUST ISOLATOR

THRUST STRUTS P/N 290-2001

INSPECT - UPPER AND LOWER THRUST STRUTS PER IAE MAINTENANCE MANUAL

MDgO-54.40.03.1F I


# 54.40.03.1 Page 2 October 2001 INSPECTION ZONE Figure 1

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### MD-90 MDC-94K9000 AIRWORTHINESS LIMITATIONS INSTRUCTIONS (ALl)
SECTION 2
NDI PROCEDURES

Title:

Inspection Item:

Model Affected:
Ships Affected:

Service Bulletin:

Drawing Reference:

Inspection Requirements: Pylon, Thrust Isolator

PSE 54.40.03.2

MD-90 All Series

All

None

5940573, LM-442-SA5, LM-442-SA15

See Lord Component Maintenance Manual. Refer to Document 71-20-25, pages 501 and subsequent pages and Figure 1 of this document for specific inspection requirements. For manual and updates contact

Lord Aerospace Products Lord Corporation 1635 West 12th Street Erie, PA 16514 Phone: (814) 456-8511

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# 54.40.03.2 Page 1 October 2001

### MD-90 AIRWORTHINESS LIMITATIONS INSTRUCTIONS (ALl)
SECTION 2
NDI PROCEDURES MDC-94K9000

SUPPORT

] w,.....-./ FFFTING

.d,./THRUST ISOLATOR REF LORD P/N LM-442-SA5 OR LM-442-SA15

INSPECT ° THRUST ISOLATOR PER LORD MAINTENANCE MANUAL

MDg0-~.40.03.2F 1


# 54.40.03.2 Page 2 October 2001 INSPECTION ZONE Figure I

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### MD-90 MDC-94K9000 AIRWORTHINESS LIMITATIONS INSTRUCTIONS (ALl)
SECTION 2
NDI PROCEDURES

Title:

Inspection Item:

Model Affected:
Ships Affected:
Service Bulletin:
Drawing Reference:
Inspection Requirements: Pylon, Aft Isolator and Cone Bolts

PSE 54.40.04.1

MD-90 All Series

All None
5940573, LM-442-SA6, LM-442-SA16, LM-442-13
See Lord Component Maintenance Manuals. Refer to Documents 71-20-26, 71-20-27 and 71-20-32 as applicable, pages 501 and subsequent pages and Figure 1 of this document for specific inspection requirements. For manual and updates contact:
Lord Aerospace Products Lord Corporation 1635 West 12th Street Ene, PA 16514 Phone: (814) 456-8511

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# 54.40.04.1 Page 1 September 2002

### MD~0 AIRWOTHINESSLIMITATIONSINSTRUCTIONS(ALI)

SECTION2
NDIPROCEDURES MDC-94K9000

AFT CONE BOLT LM J. ~.2-13

AFT VIBRATION

ISOLATOR LM-442-SA8 OR LM-442-SA-16 

### J~INBD

INSPECT - AFT ISOLATOR AND CONE BOLT PER LORD MAINTENANCE MANUAL

MDgO-84.40,04.1 F1 

### INSPECTION ZONE Figure I



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### MD-90 MDC-94K9000 AIRWORTHINESS LIMITATIONS INSTRUCTIONS (ALI)
SECTION 2
NDI PROCEDURES



# 55.11.01.1

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### September 2011 Title : Rear Spar Upper Cap - between STA Xe = 5.000 and Xe = 14.000

Inspection Item : PSE 55.11.01.1

Model Affected : MD-90

Ships Affected : All

Service Bulletin : MD-90 55A-012

Drawing Reference : 5964815, 5940483, 5918000

Requirement : TO COMPLETE THE REQUIREMENTS OF THIS PSE, THE PRIMARY

INSPECTION (01), OF EACH INSPECTION SEQUENCE, OR ITS

ALTERNATE SUBSTITUTE(S) MUST BE ACCOMPLISHED

. NOTES: (1) ALTERNATE INSPECTIONS WILL BE IDENTIFIED BY NUMERALS OTHER THAN 01.

(2) MULTIPLE ALTERNATE INSPECTIONS WHICH MUST BE PERFORMED TO ADEQUATELY REPLACE A PRIMARY INSPECTION WILL BE IDENTIFIED BY AN ALPHA CHARACTER FOLLOWING THE ALTERNATE DESIGNATOR, i.e., 02a and 02b, ETC.

Inspection Sequence 1 :

01. Eddy Current, Low Frequency

Description :

The inspection area consists of the horizontal stabilizer rear spar upper cap at the area between the aft two fastener rows common with the upper skin plank. The purpose of the inspection is to detect fatigue cracks in the horizontal flange of the upper cap between Stations Xe = 5.000 and Xe = 14.000. The fatigue cracks will emanate in the forward/aft direction in the inspection area. See Figures 1, 3, and 4.

### MD-90 MDC-94K9000 AIRWORTHINESS LIMITATIONS INSTRUCTIONS (ALI)
SECTION 2
NDI PROCEDURES



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### Access:

FOLLOW APPLICABLE SAFETY INSTRUCTIONS AND PRECAUTIONS PER THE NONDESTRUCTIVE TESTING STANDARD PRACTICE MANUAL (NDTSPM) PART 01-00-01 AS WELL AS ALL LOCAL AND COMPANY REQUIREMENTS.

A. Access to upper surface of horizontal stabilizer at the aft spar.

Preparation for Inspection :

A. Remove all dirt, grease, and loose paint from the inspection area.

B. Thoroughly clean the inspection area with an approved cleaning agent.

General Visual Inspection :

A. Perform a preliminary check of the general PSE area for cleanliness, presence of foreign objects, distortion, damage, cracks, corrosion, security of parts and evidence of loose attachments.

B. After completion of general area check, perform the specific PSE inspection(s) to complete the requirement.

NOTE : The presence of repairs and/or modifications in the inspection area may affect the inspectability of this PSE. Inspect non-discrepant areas of the PSE and report details of the discrepancy with inspection results to BCA-LBD.

C. If additional information regarding visual inspection is desired, See Part 09 of the NDTSPM.

### MD-90 MDC-94K9000 AIRWORTHINESS LIMITATIONS INSTRUCTIONS (ALI)
SECTION 2
NDI PROCEDURES



# 55.11.01.1

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### September 2011 Equipment/Materials



### DESCRIPTION METHOD APPLICABILITY

A. EDDY CURRENT 1. Flaw Detector (Impedance Plane Display). •NDT 24 Staveley Instruments Inc. 

### 101

2. Low Frequency Spot Probe operating at 1 KHz. See Figure 2 and Section 2-3, Figure 3.1 •SPO-5496 Staveley Technologies Inc. 

### 101

3. Low Frequency Reference Standard. See Figure 2 and Section 2- 1, Figure 1.1 •MD90-01 Source optional 

### 101

B. SURFACE PREPARATION 1. Cleaning Agent in conformance with environmental regulations and harmless to surfaces contacted.

• Source optional 

### ALL

NOTES : (1) The equipment/materials listed above were used to develop this procedure. See NDTSPM Part 06-00-04 for supplier/ vendor information. (2) Equipment/material substitutions producing results equivalent to those defined by this document may also be used. See NDTSPM Parts 01- and 06- 00-03 for equipment/material information.

### MD-90 MDC-94K9000 AIRWORTHINESS LIMITATIONS INSTRUCTIONS (ALI)
SECTION 2
NDI PROCEDURES



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### Inspection Procedure
A. Inspection Sequence 1:
1. Inspection Method 01 (Eddy Current, Low Frequency) a. Attach probe to eddy current instrument and set operating frequency to
1 KHz.

b. Place the eddy current probe on the reference standard as shown in Figure 2. Null/balance the instrument with the probe centered between fasteners to minimize fastener affect from forward fastener row.

c. Scan across the reference EDM notch area in the -5 detail and adjust the instrument display settings to obtain a display pattern similar to that shown in Figure 2.

d. Gain access to the inspection area at the horizontal stabilizer aft spar upper cap between Stations Xe = 5.000 and Xe = 14.000. Null/balance probe between fasteners at the inspection area in a manner similar to that which was done for the calibration process. Scan along inspection area in the shaded area as shown on Figure 3 and 4 looking for cracks in the upper spar cap (cracks in the forward and aft direction.)

Inspection Results:

A. Any indication is considered a crack which exhibits the same relative phase angle and an amplitude of 50 percent or greater than the indication obtained from the calibration notch in the reference standard.

B. Report all inspection results, Positive, Negative, or Discrepant.

1. Positive - Cracks found 2. Negative - Cracks not found 3. Discrepant - PSE inspection could not be completed or performed due to obstruction or other physical anomalies.

Post Inspection Procedure:

A. Remove and secure all test equipment and materials from the area.

### MD-90 MDC-94K9000 AIRWORTHINESS LIMITATIONS INSTRUCTIONS (ALI)
SECTION 2
NDI PROCEDURES



# 55.11.01.1

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### MD-90 MDC-94K9000 AIRWORTHINESS LIMITATIONS INSTRUCTIONS (ALI)
SECTION 2
NDI PROCEDURES



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### MD-90 MDC-94K9000 AIRWORTHINESS LIMITATIONS INSTRUCTIONS (ALI)
SECTION 2
NDI PROCEDURES



# 55.11.01.1

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### MD-90 MDC-94K9000 AIRWORTHINESS LIMITATIONS INSTRUCTIONS (ALI)
SECTION 2
NDI PROCEDURES



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### MD-90 MDC-94K9000 AIRWORTHINESS LIMITATIONS INSTRUCTIONS (ALI)
SECTION 2 SUPPLEMENT

TABLE OF CONTENTS

TC-4 Revision Date: September 2011 SECTION 2-0 EQUIPMENT UTILIZATION

TBD

SECTION 2-1 REFERENCE STANDARDS Figure 1.1 MD90-01 Horizontal St abilizer at Station Xe=7.0

SECTION 2-2 HIGH FREQUENCY EDDY CURRENY PROBES

TBD

SECTION 2-3 LOW FREQUENCY EDDY CURRENT PROBES Figure 3.1 SPO-5496 Probe

SECTION 2-4 INSPECTION FIXTURES

TBD

SECTION 2-5 ULTRASONIC TRANSDUCERS

TBD

# SECTION 2 SUPPLEMENT

EQUIPMENT UTILIZATION

### MD-90 MDC-94K9000 AIRWORTHINESS LIMITATIONS INSTRUCTIONS (ALI)
SECTION 2 SUPPLEMENT
EQUIPMENT UTILIZATION



# SECTION 2-0

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### September 2011 TBD

# SECTION 2 SUPPLEMENT

REFERENCE STANDARDS

### MD-90 MDC-94K9000 AIRWORTHINESS LIMITATIONS INSTRUCTIONS (ALI)
SECTION 2 SUPPLEMENT
REFERENCE STANDARDS



# SECTION 2-1

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### September 2011

### MD-90 MDC-94K9000 AIRWOTHINESS LIMITATIONS INSTRUCTIONS (ALI)
SECTION 2 SUPPLEMENT
REFERENCE STANDARDS



# SECTION 2-1
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### MD-90 MDC-94K9000 AIRWORTHINESS LIMITATIONS INSTRUCTIONS (ALI)
SECTION 2 SUPPLEMENT
REFERENCE STANDARDS



# SECTION 2-1

McDonnell Douglas Corporation Proprietary In formation. Use or disclosure of 

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### September 2011

# SECTION 2 SUPPLEMENT

HIGH FREQUENCY EDDY CURRENT PROBES

### MD-90 MDC-94K9000 AIRWORTHINESS LIMITATIONS INSTRUCTIONS (ALI)
SECTION 2 SUPPLEMENT
HIGH FREQUENCY EDDY CURRENT PROBES



# SECTION 2-2

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# SECTION 2 SUPPLEMENT

LOW FREQUENCY EDDY CURRENT PROBES

### MD-90 MDC-94K9000 AIRWORTHINESS LIMITATIONS INSTRUCTIONS (ALI)
SECTION 2 SUPPLEMENT
LOW FREQUENCY EDDY CURRENT PROBES



# SECTION 2-3

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### September 2011

# SECTION 2 SUPPLEMENT

INSPECTION FIXTURES

### MD-90 MDC-94K9000 AIRWORTHINESS LIMITATIONS INSTRUCTIONS (ALI)
SECTION 2 SUPPLEMENT
INSPECTION FIXTURES



# SECTION 2-4

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### September 2011 TBD

# SECTION 2 SUPPLEMENT

ULTRASONIC TRANSDUCERS

### MD-90 MDC-94K9000 AIRWORTHINESS LIMITATIONS INSTRUCTIONS (ALI)
SECTION 2 SUPPLEMENT
ULTRASONIC TRANSDUCERS



# SECTION 2-5

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### September 2011 TBD