HERCULES AIRFREIGHTER 

LOCKHEED MARTIN MODEL 

382, 382B, 382E, 382F AND 382G SERIES AIRCRAFT 

SERVICE MANUAL PUBLICATION (SMP) 

Supplemental Structural 

Inspection Document (SSID) 

SMP 515-C-SSID 

© 2007 Lockheed Martin Corporation 

Lockheed Martin Proprietary Information 

LOCKHEED MARTIN AERONAUTICS COMPANY

A Division of Lockheed Martin Corporation 

Marietta, Georgia 30063 

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Revisions Page

Date By 

Whom Description Page Revised 

Aug 07 - Change 0 - Original Issue. - 

Sep 07 S. F. 

Ramey 

Change 1 (Incorporates FAA Comments dated 7 

September 2007) - 

Added 382F applicability Title Page

Updated List of Acronyms vii through viii 

Deleted Section 6 - INDEX OF STRUCTURAL 

INSPECTION PROCEDURES 

Original 6-1 

through 6-8 

Renumbered Original Sections 7 through 9 to 

Revised Sections 6 through 8 6-1 through 8-18 

Revised all references to Original Sections 7 

through 9 in the text to reflect Revised Section 

Numbering 6 through 8 

1-1, 2-2, 5-6, 7-1 

Corrected misspelling and revised model 

numbers 

3-1 

Revised to include revision date in list of 

supplied data in Section 6.3 Table of PSE 

Inspection Requirements and Intervals 

6-1 

Moved explanation of when initial and recurring 

inspections are due from Section 6.2 to 6.3 and 

added further clarification 

6-2 and 6-3 

Added a sentence to explain the Section 6.3 PSE 

numbers ending in “XX” 6-3 

Deleted reference to Original Section 6 for 

applicable revision date of inspection procedure 6-3 

Clarified 10% maximum allowable extension 6-3 

Revised Section 6.3 to include: 

• Revision Date of Inspection Procedure in 

Table of PSE Inspection Requirements and 

Intervals 

• Total Flight Hours (TFH) for initial 

inspection intervals and Flight Hours (FH) 

for recurring intervals 

6-4 through 6-33 

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SMP 515-C-SSID 

Date By 

Whom Description Page Revised 

Deleted reference to Military Service Bulletins in 

SP- 38, 62, 74, 76, 88, 95, 107, 123, 124, 126, 

127, 135, 141, 195, 197, 219, 224, 265, 268, 271 

6-6, 6-7, 6-9, 6-10, 

6-13, 6-15, 6-16, 6-17, 

6-19, 6-20, 6-21, 6-25, 

6-28, 6-29, 6-30 

Updated TOC to reflect above changes, include 

sub-sections of Sections 6 through 8, and correct 

misspellings 

v 

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SMP 515-C-SSID 

Table of Contents

Section Item Page

 TITLE PAGE ------------------------------------------------------------------------------------ i 

 REVISIONS PAGE --------------------------------------------------------------------------- iii 

TABLE OF CONTENTS --------------------------------------------------------------------- v 

LIST OF ACRONYMS-----------------------------------------------------------------------vii 

 REFERENCES ---------------------------------------------------------------------------------ix 

1.0 PURPOSE ------------------------------------------------------------------------------------1-1 

2.0 INTRODUCTION ---------------------------------------------------------------------------2-1 

3.0 AFFECTED AIRCRAFT--------------------------------------------------------------------3-1 

4.0 PRINCIPLE STRUCTURAL ELEMENTS ----------------------------------------------4-1 

4.1 CHAPTER 53 – FUSELAGE ---------------------------------------------------------4-2 

4.2 CHAPTER 55 – EMPENNAGE ------------------------------------------------------4-4 

4.3 CHAPTER 57 – WINGS---------------------------------------------------------------4-5 

4.4 CHAPTER 71 – POWER PLANT----------------------------------------------------4-6 

5.0 DAMAGE TOLERANCE ANALYSIS METHODOLOGY ---------------------------5-1 

5.1 SAFETY LIMIT-------------------------------------------------------------------------5-1 

5.2 INITIAL FLAW CRITERIA ----------------------------------------------------------5-2 

5.3 INSPECTION CRITERIA -------------------------------------------------------------5-6 

6.0 STRUCTURAL INSPECTION REQUIREMENTS-------------------------------------6-1 

6.1 APPLICABILITY CODE--------------------------------------------------------------6-1 

6.2 INSPECTION INTERVALS AND OPERATIONAL USAGE SEVERITY ---6-2 

6.3 PSE INSPECTION REQUIREMENTS AND INTERVALS ---------------------6-3 

7.0 DISCREPANCY REPORTING ------------------------------------------------------------7-1 

7.1 FATIGUE AND CORROSION DAMAGE REPORTING------------------------7-1 

7.2 REPORTING OF SIGNIFICANT REPAIRS ---------------------------------------7-2 

8.0 INSPECTION ZONE DESCRIPTION----------------------------------------------------8-1 

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List of Acronyms

AASR Aging Aircraft Safety Rule 

AD Airworthiness Directive

a Crack Length 

ASIP Aircraft Structural Integrity Program 

ATA Air Transport Association 

BL Butt Line 

CAR Civil Airworthiness Regulations 

DAH Design Approval Holder 

DT Damage Tolerance 

DTA Damage Tolerance Assessment/Analysis 

Dwg Drawing 

FAA Federal Aviation Administration 

FEM Finite Element Model 

FH Flight Hours 

FS Fuselage Station 

HSS Horizontal Stabilizer Station 

in. inches 

LM Aero Lockheed Martin Aeronautics 

MED Multiple Element Damage 

MEP Manufacturing End Product 

MLG Main Landing Gear 

MSD Multiple Site Damage 

NDI Non-Destructive Inspection 

OUE Operational Usage Evaluation 

OWS Outer Wing Station 

P/N Part Number

POD Probability of Detection 

PSE Principle Structural Element 

QECU Quick Engine Change Unit 

SB, S/B Service Bulletin 

SEC Surface Eddy Current 

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vii
SMP 515-C-SSID 

List of Acronyms (Cont’d)

SCC Stress Corrosion Cracking 

SMP Service Manual Publication 

SSI Structurally Significant Item

SSID Supplemental Structural Inspection Document 

TFH Total Flight Hours 

USAF United States Air Force 

VSS Vertical Stabilizer Station 

WFD Widespread Fatigue Damage 

WL Water Line 

WS Wing Station 

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SMP 515-C-SSID 

References

1. SMP 515-C-MASTER, Hercules Airfreighter Inspection Program, Lockheed Martin Model 

282, 382B/C/D/E/F and G Series Aircraft, 1 December 2004 

2. LG82ER0147, “C-130 A/B/E/H Durability and Damage Tolerance Assessment (DADTA): 

General Methodology and Basic Data,” Lockheed-Georgia Company, September 1981. 

3. FAA Aging Airplane Safety, Final Rule, 14 CFRs Parts 119, 121, 129, 135 and 183, 

Federal Register Vol 70, No. 21, February 2 2005. 

4. SMP 583 Hercules Airfreighter Structural Repair Manual 

5. SMP 515-B Hercules Airfreighter Corrosion Prevention and Control Manual 

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SMP 515-C-SSID 

SECTION 1 

PURPOSE 

1.0 PURPOSE 

The purpose of this Service Manual Publication (SMP) is to provide commercial operators of the 

L-382 Series aircraft with a Supplemental Structural Inspection Document (SSID). The SSID 

defines the structural inspection requirements considered to be essential to maintain continuing

airworthiness in accordance with FAA requirements specified in 14 CFR Part 121.370a. In 

subsequent revisions to this SSID, additional supplemental inspection requirements may be 

identified for repairs and modifications that are contained in the Lockheed Martin 382 Series 

Aircraft Structural Repair Manual and previously issued Lockheed Martin 382 Series Aircraft 

Service Bulletins. 

It is anticipated that the FAA will issue an Airworthiness Directive (AD) in accordance with the 

inspection requirements identified in this SSID. 

This document identifies Principle Structural Elements (PSE) of the L-382 model aircraft that are 

susceptible to fatigue cracking, corrosion and/or stress corrosion cracking and if not detected and 

repaired in a timely manner could eventually lead to the catastrophic loss of the aircraft . 

The inspection procedures identified in this SSID are drawn from existing procedures developed 

by LM Aero for the SMP 515-C Hercules Airfreighter Inspection Program (Reference 1) and 

from Lockheed Martin 382 Series Aircraft Service Bulletins. L-382 operators who have had LM

Aero develop a customized SMP 515-C-X inspection program (“X” denotes the particular 

operators program number) currently have access to the inspection procedures identified in 

Section 6 of this SMP. These inspection procedures have been developed, in part, from Damage 

Tolerance requirements. Full scale fatigue test and service corrosion and cracking data has been 

used to determine the majority of the locations that require continuing inspections. 

Many of the Special Inspection (SP) intervals provided in this SMP were originally derived from

crack growth analysis of typical C-130E military transport usage in the late 1970’s consisting

primarily of training and logistics (cargo transport) operations. Recent analysis of usage data has

shown that typical commercial operations of the L-382 aircraft are at higher payloads than 

military operations with significantly less time in pilot training. Analysis and in service cracking 

data has also shown that the crack growth rate severity of typical commercial usage is very

similar to the baseline military usage, particularly in wing lower surface structure. 

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SECTION 2 

INTRODUCTION 

2.0 INTRODUCTION 

The FAA published the Aging Aircraft Safety Rule (AASR) in February 2005 which requires, in 

part, operators to have a maintenance program consisting of FAA approved damage tolerant

based structural inspection procedures. These inspections are required for the baseline structure

and also must consider the adverse affects of repairs, alterations and modifications. Although no 

specific requirement was identified for a Supplemental Structural Inspection Document to be

issued from the Design Approval Holder (DAH), the FAA is required to ensure that the AASR is 

successfully implemented by issuing an Airworthiness Directive (AD) against an FAA approved 

damage tolerant based inspection program. Lockheed Martin Aeronautics (LM Aero) has

prepared this SMP in order to provide a single document that specifies the critical structural

inspections required to ensure continued airworthiness. 

The primary means that LM Aero has provided L-382 operators with structural inspection 

requirements is through the SMP 515-C Hercules Airfreighter Inspection Program (Reference 1). 

This program contains scheduled inspection requirements for the complete aircraft, including the 

structure. SMP 515-C programs have been developed specific to the customer aircraft

configuration which includes modified structure by Service Bulletins. Customer particular 

programs are identified with a numeric character “X” (SMP 515-C-X). 

Where service cracking data has shown that there are additional areas that warrant inspection that 

are not addressed in the maintenance program, or where currently requirements do not

adequately address the fatigue cracking, LM Aero has issued Service Bulletins. When the L-382 

operator requests updates to their SMP 515-C-X inspection program, the inspection requirements 

contained in Service Bulletins issued since the last SMP 515-C-X update are incorporated into 

their maintenance plan. There are L-382 operators however, who have not had SMP 515-C 

updates in numerous years. There may also be some foreign commercially certified aircraft that 

do not have the SMP 515-C program. 

Structural inspection requirements to detect fatigue cracking provided in the SMP 515-C-X and 

in Service Bulletins are in part based on Damage Tolerance Assessments. Where the principal 

mechanism that propagates a crack has been identified as fatigue, crack growth analysis has been

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SMP 515-C-SSID 

SECTION 2 

INTRODUCTION 

performed to initially establish the inspection intervals. In some cases, these intervals have been

modified based on test and in service cracking data or by risk analysis methodologies. 

The key elements of the damage tolerance analysis are: 

• Generation of operational stress spectra for all significant load sources 

• Determination of fatigue crack geometric correction factors 

• Residual Strength Analysis of cracked structure to determine critical crack size 

• Establishing initial flaw sizes and continuing damage criteria 

• Fatigue crack growth analysis 

• Determination of detectable and non-detectable crack sizes 

• Establishing operational limits of time between scheduled inspection 

PSEs that are also susceptible to corrosion and/or Stress Corrosion Cracking (SCC) are 

addressed in this document by applicable inspection procedures. The L-382 structure contains 

numerous PSEs that are manufactured from 2XXX-T6 and 7XXX-T6 temper alloys that have a

known service history of corrosion and SCC. SMP 515-B (Reference 5) provides operators with 

detailed information for preventing and controlling corrosion. Inspection intervals for detecting

corrosion and SCC are based on service experience. 

This SSID also contains inspection requirements for structure that has been modified by LM 

Aero Service Bulletins. These modifications include fatigue preventative repairs and major 

component replacements. Where the Reference 4 structural repairs affect PSE inspections, these 

are also identified in Section 6. 

There are eight L-382 Airworthiness Directives which have been issued that affect the PSEs

identified in Section 4. These ADs relate to LM Aero previously issued Service Bulletins that 

contain inspections to primary structure. Where LM Aero has determined that recurring

inspection are required, these have been included in Section 6 along with the applicable

inspection procedure reference. The list of applicable ADs are contained in Table 2.1 below. 

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SECTION 2 

INTRODUCTION

Table 2.1 – L-382 ADs Affecting PSEs 

AD Number SB Number SB Title SP Number

96-12-20 A382-71-19 Power Plant – Inspection of Outboard Engine 

Truss Mount Tangs 

N/A 

94-26-15 382-57-74 Wing – Inspection of Kingpin Riser No. 18 on 

Outer Wing Lower Surface 

SP-265 

92-10-14 382-53-50 Fuselage – Repair/Reinforcement of 

Pressurized Fairing Support Structure 

SP-126 

SP-224 

88-10-06 382-57-70/

A82-608 

Wing – Modification and Inspection of Lower 

Surface Panel Riser Repairs 

SP-209 

88-10-05 A382-57-71

A82-612 

Wing – Inspection of Heat Shield and Aft 

Nacelle Fairing Nut Plate Holes 

SP-202 

75-19-02 82-371 Wing – Outer Wing Lower Forward and Rear 

Beam Caps/Skin Panels at Termination of 

Pylon Reinforcing Stiffener 

SP-76 

75-17-04 A82-374 Fuselage – Inspection of Main Frame at FS 

517 for Cracks and Installation of Prevent 

Repair 

N/A 

74-12-06 A82-346 Wing – Inspection of Outer Wing Front Beam 

Cap, Front Beam Web, and Lower Surface 

Forward Skin Panel at OWS 144 to 165 and 

OWS 195 to 214 for Fatigue Cracks 

SP-75 

SP-76 

It is important to recognize that the supplemental structural inspection program defined in this 

SMP does not take into account the affects of Widespread Fatigue Damage (WFD). Fatigue 

crack interaction effects due to Multiple Site Damage (MSD) and Multiple Element Damage 

(MED) are not modeled in the standard damage tolerance analysis procedure. LM Aero has 

completed a WFD assessment of the center wing lower surface structure using a probabilistic 

risk analysis methodology and has issued two Service Bulletins to address WFD: 

• 382-57-82 Rev 2 - Center Wing Upper and Lower Rainbow Fitting Inspection for 

Cracks and Replacement 

• 382-57-85 Rev 3 - Center Wing Lower Surface Generalized Cracking and 

Widespread Fatigue Damage Inspection Requirements 

It is anticipated that the FAA will issue separate ADs against the above two Service Bulletins.

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SECTION 2 

INTRODUCTION 

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SECTION 3 

AFFECTED AIRCRAFT 

3.0 AFFECTED AIRCRAFT 

The structural inspection requirements identified in this SMP are intended for all commercially 

certified 382, 382B/E/F and G series aircraft. Due to similarities in the military C-130 versions,

they can also be applied to military operated L-382 series aircraft. 

A current listing of commercial certified 382, 382B, 382E, 382F and 382G series aircraft is 

provided below. This listing was developed from Lockheed Martin Engineering Reports 

ER-7470M and ER-260M. Some of the aircraft listed below are currently being operated by 

foreign military organizations. 

Table 3.1 – Civil Certified 382, 382B/E/F and G Series Aircraft Manufactured by

Lockheed Martin Aeronautics Company 

3946 4248 4450 4691 4839 4956 

4101 4250 4472 4695 4850 4957 

4109 4299 4475 4698 4851 4960 

4129 4300 4477 4701 4853 4992 

4134 4301 4512 4706 4880 5000 

4137 4302 4558 4708 4883 5022 

4144 4303 4561 4710 4886 5024 

4145 4333 4562 4715 4889 5025 

4146 4350 4565 4763 4891 5027 

4147 4355 4582 4796 4893 5029 

4170 4358 4586 4798 4895 5032 

4176 4361 4590 4799 4917 5048 

4197 4362 4593 4800 4923 5055 

4208 4364 4600 4824 4949 5056 

4209 4383 4606 4826 4950 5225 

4221 4384 4610 4828 4951 5306 

4222 4385 4673 4830 4952 5307 

4225 4388 4676 4832 4953 5320 

4229 4391 4679 4833 4954

4234 4412 4684 4834 4955 

 Foreign Commercial (61 Aircraft) 

Domestic Commercial (14 Aircraft) 

 RED Attrited Commercial (43 Aircraft) 

 TOTAL 118 Commercial Aircraft 

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SECTION 3 

AFFECTED AIRCRAFT 

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SECTION 4 

PRINCIPLE STRUCTURAL ELEMENTS 

4.0 PRINCIPLE STRUCTURAL ELEMENTS 

This SMP identifies structural inspection requirements of Principle Structural Elements (PSEs) 

only. PSEs are defined as primary structural elements that contribute significantly to the 

carrying of flight, ground or pressurization loads and whose integrity is essential in maintaining 

the overall structural integrity of the aircraft. The term Structurally Significant Item (SSI) has 

also been used to identify critical primary structure. LM Aero has identified SSIs in Section V of 

SMP 515-C-MASTER (Reference 1) and also in customer specific SMP 515-C-X inspection 

programs, however, the PSEs identified in this document supersede the SSI definitions. 

The L-382 was originally civil certified under CAR 4b failsafe requirements in that design limit 

load can be sustained should any single PSE load path become severed. Engineering failsafe 

substantiation analysis reports were completed during the L-382 commercial certification 

program. During the early 1980’s, Damage Tolerance was introduced into the United States Air 

Force (USAF) Aircraft Structural Integrity Program (ASIP) and the principles of slow crack 

growth analysis was applied to the L-382 structure. Inspection intervals were derived in 

accordance with MIL-A-83444 requirements for establishing safe periods of operation between

scheduled inspections. The DADT Analysis was documented in numerous reports provided to 

the USAF. These inspection requirements and intervals for the PSEs were subsequently 

incorporated into the SMP 515-C-X Hercules Series Inspection Programs. 

Detection of a failed or partially failed PSE can be accomplished by numerous methods

including detection of fuel tank leakage and cabin pressurization leakage. These conditions are 

readily apparent to flight and ground crews as part of normal operations and maintenance. There 

are PSEs where routine visual inspection methods are inadequate to detect the damage and NonDestructive Inspection (NDI) procedures must be used. Even though the structure is failsafe for

a single PSE for a short period of time (typically at least for the remainder of the flight), a 

directed inspection is required to detect the damage and ensure that the Ultimate Strength

capability is restored in a timely manner. For this reason, all NDI requirements affecting PSEs

are identified in this SMP. 

Certain PSEs are failsafe by crack arrest features. An example is the upper and lower wing joint 

fittings. These are single piece parts which have multiple load path features such that cracking 

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SECTION 4 

PRINCIPLE STRUCTURAL ELEMENTS 

will arrest between individual load paths. These features provide opportunities to detect fatigue 

damage prior to a catastrophic multiple load path failure. 

The PSEs are listed in Table 1 below. Note that several individual parts may be identified as a

single PSE, for example, the BL 61 Longeron Splice Fittings. Similar structural parts are also 

identified as a single PSE, for example, there are three center wing lower surface panels. 

For identification and location of the PSEs provided in the following sections, refer to SMP 583 

Structural Repair Manual, Reference 4. 

4.1 CHAPTER 53 – FUSELAGE 

Chapter 53 lists the PSEs identified for the Forward Fuselage, Center Fuselage, Aft Fuselage, and 

Main Landing Gear Wheel Well Structure in Tables 4.1.1 through 4.1.3. 

Table 4.1.1 - Forward Fuselage Principle Structural Elements 

PSE Number Description 

53-30-01 Windshield Doublers, Posts, and Sills 

53-30-02 Forward Fuselage Upper BL 20 Longeron 

53-30-03 Forward Fuselage Upper BL 20 Longeron Splice Fittings 

53-30-04 Forward Fuselage Upper BL 61 Longeron 

53-30-05 Forward Fuselage Upper BL 61 Longeron Splice Fittings 

53-30-06 Forward Fuselage Lower BL 61 Longeron 

53-30-07 Forward Fuselage Lower BL 61 Longeron Splice Fittings 

53-30-08 Skins and Frames 

53-30-09 FS 165 Bulkhead Lower Cap and Diaphragm Attach Angle 

53-30-10 FS 180 Bulkhead 

53-30-11 FS 196 Bulkhead WL 145 Reinforcing Strap and Web

53-30-12 Crew Entry Door Skin, WL 195 Longeron, and FS 245 Longeron Fitting 

53-30-13 Underfloor Structure

53-30-14 Forward Fuselage Chine Caps and Plates 

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SECTION 4 

PRINCIPLE STRUCTURAL ELEMENTS

Table 4.1.2 - Center Fuselage Principle Structural Elements 

PSE Number Description 

53-40-01 Fuselage Production Joint Mounting Rings, FS 245 and 737 

53-40-02 Center Fuselage Upper BL 20 Longeron

53-40-03 Center Fuselage Upper BL 20 Longeron Splice Fittings 

53-40-04 Center Fuselage Upper BL 61 Longeron

53-40-05 Center Fuselage Upper BL 61 Longeron Splice Fittings 

53-40-06 Center Fuselage Lower BL 61 Longeron Splice Fittings 

53-40-07 Upper BL 61L to R Skins and Ring Segments 

53-40-08 BL 61 Upper to Lower Side Skins and Ring Segments 

53-40-09 BL 61L to R Lower (Belly) Skins 

53-40-10 Chine Caps and Angles, FS 245 to 737

53-40-11 Cargo Compartment and Ramp Underfloor Structure, FS 245 to 737 

53-40-12 Upper BL 61 Ring Splice Gusset Fittings, FS 245 to 737 

53-40-13 BL 61 Wing Attach Angle 

53-40-14 MLG Bow Beams and Fittings, FS 497, 537, and 557

53-40-15 MLG Track Support Beams and Main Frames, FS 517, 528, 577, 588, and 597 

53-40-16 WL 200 Shelf and Support Attachments, FS 477 to 597 

53-40-17 BL 61 Sidewall Panel at Access Openings, FS 477 to 617 

53-40-18 Floor Beam End Fittings and MLG Shelf Bracket Bolts, FS 517, 528, 577, 588, and 597 

53-40-19 FS 477, 497, and 617 Overhead Bulkheads 

53-40-20 BL 61 Pressurized Fairing Attachments, FS 477 to 517 and FS 597 to 617 

53-40-21 FS 477 and 617 Bulkhead Tension Tie Fittings 

53-40-22 FS 477 and 617 BL 61 External Ring Splice Fittings 

53-40-23 FS 477 and 617 Tie Down Fittings, Struts and Strut Support Fittings 

53-40-24 Paratroop Door Longeron, FS 697 to 737 

53-40-25 Paratroop Door Cutout Structure 

53-40-26 FS 245 and 737 Splice Fitting Bolts 

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SECTION 4 

PRINCIPLE STRUCTURAL ELEMENTS 

Table 4.1.3 - Aft Fuselage Principle Structural Elements 

PSE Number Description 

53-50-01 Aft Fuselage Upper BL 20 Longeron

53-50-02 Aft Fuselage Upper BL 20 FS 737 Longeron Splice Fittings 

53-50-03 Aft Fuselage Upper BL 61 Longeron

53-50-04 Aft Fuselage Upper BL 61 FS 737 Longeron Splice Fitting 

53-50-05 Upper BL 61L to R Skins and Ring Segments 

53-50-06 BL 61 Upper to Lower Side Skins and Ring Segments 

53-50-07 Aft Fuselage Side Bulkheads and Struts 

53-50-08 Aft Bulkhead and Strut Lower Attach Fittings 

53-50-09 Aft Fuselage Overhead Bulkheads and Fittings 

53-50-10 FS 737 Ring, Ring Segment and Floor Beam End Fitting 

53-50-11 FS 737 Bulkhead Struts and Attach Angles 

53-50-12 FS 737 and 1041 Sloping Longeron Splice Fittings 

53-50-13 BL 61 Aft Fuselage Sloping Longeron 

53-50-14 Aft Cargo Door Beams and Skin 

53-50-15 Ramp Side Beams 

53-50-16 Ramp Skin and Floor Beams 

53-50-17 

BL 61 Upper Longeron FS 1041 End Fitting and Horizontal Stabilizer Attachments 

Bolts

4.2 CHAPTER 55 - EMPENNAGE 

Table 4.2.1 lists the PSEs identified for the Vertical and Horizontal Stabilizers. 

Table 4.2.1 - Vertical and Horizontal Stabilizer Principle Structural Elements 

PSE Number Description 

55-10-01 FS 1041 Bulkhead 

55-10-02 Upper Surface Skin Panels 

55-10-03 Lower Surface Skin Panels 

55-10-04 Front and Rear Beam Caps and Webs

55-10-05 Typical Skin to Beam Cap Splice, HSS 69-180 

55-10-06 Vertical Stabilizer Attach Angle 

55-10-07 Vertical Stabilizer Lower Support Fittings 

55-10-08 Vertical Stabilizer Upper Support Fittings and Attach Bolts 

55-10-09 Rudder, Elevators, and Rudder and Elevator Hinges 

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PRINCIPLE STRUCTURAL ELEMENTS

4.3 CHAPTER 57 - WINGS 

Tables 4.3.1 and 4.3.2 provide the PSEs identified for the Center and Outer Wing, respectively. 

Table 4.3.1 - Center Wing Principle Structural Elements 

PSE Number Description 

57-30-01 Front Beam Lower Cap 

57-30-02 Rear Beam Lower Cap 

57-30-03 Front Beam Upper Cap 

57-30-04 Rear Beam Upper Cap 

57-30-05 Rear Beam Web

57-30-06 Front Beam Web

57-30-07 Lower Surface Skin Panels 

57-30-08 Upper Surface Skin Panels 

57-30-09 Lower Surface Skin Panel Stringers 

57-30-10 Upper Surface Skin Panel Stringers 

57-30-11 Diagonal Rib Upper and Lower Cap, WS 62 to WS 92

57-30-12 No. 2 and 3 Engine Nacelle Truss 

57-30-13 No. 2 and 3 Engine Nacelle Rib Cap and Attach Fittings 

57-30-14 Lower Front and Rear Beam Corner Fittings 

57-30-15 Upper Front and Rear Beam Corner Fittings 

57-30-16 Wing Joint Front and Rear Beam Vertical Attach Angles 

57-30-17 Upper Wing Joint Rainbow Fitting 

57-30-18 Lower Wing Joint Rainbow Fitting 

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SECTION 4 

PRINCIPLE STRUCTURAL ELEMENTS 

Table 4.3.2 - Outer Wing Principle Structural Elements 

PSE Number Description 

57-50-01 Upper Wing Joint Rainbow Fitting 

57-50-02 Lower Wing Joint Rainbow Fitting 

57-50-03 Wing Joint and Corner Fitting Attach Bolts 

57-50-04 Lower Front and Rear Beam Corner Fittings 

57-50-05 Upper Front and Rear Beam Corner Fittings 

57-50-06 Front Beam Lower Cap 

57-50-07 Rear Beam Lower Cap 

57-50-08 Front Beam Upper Cap 

57-50-09 Rear Beam Upper Cap 

57-50-10 Rear Beam Web

57-50-11 Front Beam Web

57-50-12 Lower Surface Skin Panels 

57-50-13 Upper Surface Skin Panels 

57-50-14 Rib Caps and Braces

57-50-15 King Pin Riser Fittings 

57-50-16 Flap Track Stiffeners and Braces, OWS 28, 100, 173, 241, and 303

57-50-17 Pylon Attach Fittings, OWS 72 and 92 

57-50-18 Web Splice Tees, OWS 158 and 201 

57-50-19 No. 1 and 4 Engine Nacelle Truss 

57-50-20 No. 1 and 4 Engine Nacelle Rib Cap and Attach Fittings 

57-50-21 Aileron and Aileron Hinges 

4.4 CHAPTER 71 – POWER PLANT

Chapter 71 lists the structural inspection requirements PSEs identified for the Engine Nacelle 

(Quick Engine Change Unit) in Table 4.4.1. 

Table 4.4.1 - Engine Nacelle Principle Structural Elements 

PSE Number Description 

71-10-01 QECU Lower Longerons

71-10-02 QECU Upper Longerons

71-10-03 Aft Engine Mount Beam and Support Fittings 

4-6 

Change 0 - 30 August 2007 Use and/or disclosure is governed by statement on the title page of this document. 
SMP 515-C-SSID 

SECTION 5 

DAMAGE TOLERANCE ANALYSIS METHODOLOGY 

5.0 DAMAGE TOLERANCE ANALYSIS METHODOLOGY 

This section defines the criteria and methodology used for crack growth analysis of the L-382 

primary airframe structure. The methodology was originally developed and documented in 

Reference 2 to meet the United States Air Force (USAF) DADTA standards and specifications 

defined in MIL-A-83444. Since these requirements were directed towards the design and testing 

of new aircraft, they were not necessarily applied “in total” to the L-382, which had many years 

of service and test experience. This service experience is recognized in establishing the criteria 

contained in the following subsections. 

The current FAA damage tolerance guidelines permit the use of either a fail safe or slow crack

growth approach to achieve the required damage tolerance. Although the L-382 primary 

structural airframe is inherently failsafe, major emphasis is on using the slow crack growth 

approach to evaluate the damage tolerance of the L-382 structure. 

The slow crack growth analytical approach provides for airframe safety through a combination 

of inspection frequencies, NDI techniques and crack growth characteristics conducted on single 

components or elements such as an individual beam cap or fitting. The safe extent of crack 

growth of a single element is maintained by requiring multiple inspections with a given NDI

technique such that the theoretical crack growth or final crack length between inspection periods 

never becomes larger than the stable crack length if limit tension stress were to be applied, with 

limit defined as the maximum design tension stress value for the structure. 

As necessary and appropriate, the inherent fail safety of the structure is recognized in the

establishment of recommended actions related to structural safety. 

5.1 Safety Limit 

In the DT Analysis, operational limits are determined which address the safety of the L-382 

structure. These limits are the safety limits, defined as the time (flight hours or pressurizations) 

beyond which it is recommended not to operate the aircraft without appropriate inspections, 

repairs or modifications. The safety limit is used as a basis for conducting inspections and 

establishing safe-use intervals of operation. 

5-1 

Change 0 - 30 August 2007 Use and/or disclosure is governed by statement on the title page of this document. 
SMP 515-C-SSID 

SECTION 5 

DAMAGE TOLERANCE ASSESSMENT METHODOLOGY 

For each critical area, the safety limit is the calculated flight hour interval (for a specific location 

within a PSE) for an assumed “worst” initial flaw size (ai) to grow to an unstable length (aCR) at 

limit load, when subjected to the analytical operational loads/environment spectra. 

This initial flaw is assumed to exist in the most unfavorable location and orientation with respect 

to the applied stresses and material properties. The assumed size is sufficiently large such that it 

is unlikely that a critical fastener hole location in a fleet of aircraft contains an initial flaw greater 

than ai. Figure 5.1.1 presents the safety limit with respect to the crack growth curve. 

Figure 5.1.1 Safety Limit Representation

5.2 Initial Flaw Criteria 

The initial flaw size and flaw shape assumptions as well as the structural flaw configuration used 

in the DTA crack growth analysis is based on those determined in Reference 2. The type of 

fastener (interference or non-interference), the fastener material and the method of hole

preparation (automated or semi-automated hole drilling versus hand-held drilling) are all features

that influence the selection of initial flaw sizes. 

The majority of the structural locations to be analyzed involve two structural elements joined by

a common fastener. The selected flaw model for this general structural configuration is 

illustrated in Figure 5.2.1. 

5-2 

Change 0 - 30 August 2007 Use and/or disclosure is governed by statement on the title page of this document. 
SMP 515-C-SSID 

SECTION 5 

DAMAGE TOLERANCE ASSESSMENT METHODOLOGY 

Figure 5.2.1. General Structural Configuration Initial Flaw Model

From Figure 5.2.1, note that in Part No. 1: 

• Flaws are located at the faying surface 

• The first flaw, (a)1, is oriented toward the ligament 

• The second flaw, (a)2, is located diametrically opposite to the first flaw 

The first flaw, (a)1, is termed the initial flaw, ai, and is located in the most adverse structural 

location within the model. The second flaw, (a)2, is located on the diametrically opposite side of 

the hole to permit continuing damage. Continuing damage allows crack growth to continue after 

the primary growth from the initial flaw has terminated due to structural discontinuities or

ligament failure. 

After locating the flaws in the model, the flaw sizes and flaw shapes have to be established. As

previously stated, the type of fastener and hole preparation must be identified in order to select the 

flaw sizes. A flaw size selection summary for safety limit calculations is provided in Figure 5.2.2. 

It is noted in Figure 5.2.2 that under the Continuing Damage column, the flaw size is quoted as

0.005” after ligament failure or 0.005” + ∆a from time zero. The term ∆a represents the length a

crack will propagate from the 0.005” flaw during the time the primary crack has grown from ai

through ligament failure. These two types of continuing damage assumptions and their effects on 

crack growth are illustrated in Figure 5.2.3. 

5-3 

Change 0 - 30 August 2007 Use and/or disclosure is governed by statement on the title page of this document. 
SMP 515-C-SSID 

SECTION 5 

DAMAGE TOLERANCE ASSESSMENT METHODOLOGY 

All crack growth calculations for the determination of the safety limits use crack growth rate data

consistent with an environment of 90% relative humidity. Hole Prep’n 

Type of 

Fastener or 

Structure 

Assumed 

Initial 

Flaw, ai

Flaw Shape Environment Continuing Damage

General 

Taperlok 0.03 in. 1⁄4 Circular 

Corner Flaw 

90% Relative

Humidity

0.005” Opposite Side of 

Fastener Hole After 

Ligament Failure 

General 

Hi-Loks, 

Hi-Tigues 

0.05 in. 1⁄4 Circular 

Corner Flaw 

90% Relative

Humidity

0.005” Opposite Side of 

Fastener Hole After 

Ligament Failure 

Joint Taperlok 0.05 in. 1⁄4 Circular 

Corner Flaw 

90% Relative

Humidity

0.005” + ∆a Opposite 

Side of Hole from Time 

Zero 

Hi-Loks, HiTigues, Bolts,

Rivets, and CutOuts 

0.05 in. 1⁄4 Circular 

Corner Flaw 

90% Relative

Humidity

0.005” + ∆a Opposite 

Side of Hole from Time 

Zero 

No Hole 0.125 in. 

Deep

Semi-Circular 

Surface Flaw 

90% Relative

Humidity N/A 

Automated or Semi-Automated Hole Drilling 

* 

Hand-Held Drilling 

 1 

 2 

 

2 

 1 

Figure 5.2.2: Initial Flaw Size Selection Summary 

5-4 

Change 0 - 30 August 2007 Use and/or disclosure is governed by statement on the title page of this document. 
SMP 515-C-SSID 

SECTION 5 

DAMAGE TOLERANCE ASSESSMENT METHODOLOGY 

Figure 5.2.3 Continuing Damage 

5-5 

Change 0 - 30 August 2007 Use and/or disclosure is governed by statement on the title page of this document. 
SMP 515-C-SSID 

SECTION 5 

DAMAGE TOLERANCE ASSESSMENT METHODOLOGY 

5.3 Inspection Criteria 

In order to develop safe-use intervals through a structural inspection plan, it is necessary to develop

inspection intervals based on operational flight hours. Inspection intervals are determined from the

Safety Limit. The assignment of Non-Destructive Inspection (NDI) procedures to PSEs are

provided in Section 6. 

5.3.1 Initial Inspection Interval 

The recommended initial inspection occurs at one-half the Safety Limit. Figure 5.3.1 illustrates the 

initial inspection time in relation to the Safety Limit on a standard crack growth curve. 

Figure 5.3.1 Initial Inspection Representation

5.3.2 Recurring Inspection Interval 

The recurring inspection occurs at one-half the time for a crack to grow from the maximum 

undetectable flaw size (aNDI) to an unstable length at design limit load (aCR), as described in Figure 

5.3.2. It should be noted that safe-use intervals of operation, equal to the recurring inspection

interval, can continue up to and beyond the calculated Safety Limit for a specific structural part,

provided that no cracking is detected by the specified Non-Destructive Inspection technique at the

time of recurring inspection. 

5-6 

Change 1 - 10 September 2007 Use and/or disclosure is governed by statement on the title page of this document. 
SMP 515-C-SSID 

SECTION 5 

DAMAGE TOLERANCE ASSESSMENT METHODOLOGY 

Figure 5.3.2 Recurring Inspection Intervals 

5.3.3 Non-Destructive Inspection Techniques 

In order to establish the recurring inspection interval for a given structural location, it is necessary to

establish a maximum undetectable flaw size (aNDI). This is the largest crack that can be missed by 

an inspector usually with a 90% reliability and 95% confidence. The value of aNDI is based on the

capabilities of the technique and the accessibility of the structure. In some cases, the geometry of

the structure will significantly hinder reliable detection and in these cases, the aNDI is sufficiently

large to account for cracks that will be hidden by other structure. 

Table 5.3.1 below identifies the basic capabilities of each of the common Non-Destructive 

Inspection methods. 

5-7 

Change 0 - 30 August 2007 Use and/or disclosure is governed by statement on the title page of this document. 
SMP 515-C-SSID 

SECTION 5 

DAMAGE TOLERANCE ASSESSMENT METHODOLOGY 

Table 5.3.1: Summary of NDI Techniques 

Non-Destructive Inspection Technique NDI 

Abbreviation 

Maximum 

Undetectable Flaw

Length aNDI

(inches) 

Automated Bolt Hole Eddy Current ABHEC 0.07 

Bolt Hole Eddy Current BHEC 0.15 

Surface Eddy Current SEC 0.20 

Low Frequency Eddy Current LFEC 0.50 

Ultrasonic Surface Scan US or USSS 0.20 

Radiography X-Ray 1.00

Liquid Fluorescent Penetrant LPI or LP 0.25 

Directed Visual V or Vis 1.00 

Magnetic Particle MPI or Mag 0.25 

Note: The aNDI values shown are the minimum and are increased as required to account for the 

structural accessibility and geometry. 

5-8 

Change 0 - 30 August 2007 Use and/or disclosure is governed by statement on the title page of this document. 
SMP 515-C-SSID 

SECTION 6 

STRUCTURAL INSPECTION REQUIREMENTS 

6.0 STRUCTURAL INSPECTION REQUIREMENTS 

The PSE structural inspection requirements are identified in this Section. For each ATA 

Chapter, the SMP 515-C inspection procedure card number, or Service Bulletin number is 

identified along with the inspection title, the aircraft model applicability code, the associated 

PSE number, the latest revision date and the initial inspection interval and recurring inspection

interval. 

Inspection intervals contained in this Section are derived from a combination of Damage 

Tolerance Analysis as defined in Section 5 and from full scale durability testing and service

cracking experience. Lockheed Martin maintains a crack history database of operator reported 

structural service cracks. 

Commercial operators who have an up to date SMP 515-C program and who also complete LM 

Aero Service Bulletins may currently be complying with the intent of this SSID. Inspection

intervals provided in this document should be compared to their current maintenance program 

and if necessary, adjusted to meet these minimum requirements. 

6.1 Applicability Code 

The applicability of the inspection procedures to L-382 Serial Numbers is identified by the 

following applicability codes (shown on the left column of the Section 6.3 Inspection 

Requirements): 

A - All Aircraft 

D - As Applicable 

G - LM 3501 – 4541 

P – Operational Usage Factor 

These codes were developed for the SMP 515-C Inspection Program and identify structural 

configuration differences between the various L-382 serial numbers. Structural redesigns and 

improvements to a PSE can either make a particular inspection procedure not applicable or

extend the required inspection interval. 

6-1 

Change 1 - 10 September 2007 Use and/or disclosure is governed by statement on the title page of this document. 
SMP 515-C-SSID 

SECTION 6 

STRUCTURAL INSPECTION REQUIREMENTS 

6.2 Inspection Intervals and Operational Usage Severity 

The initial and recurring inspection intervals provided in this section are based on typical 

military transport usage in the late 1970’s. This has been referred to as “Baseline Usage”, or

“Baseline Military Usage”. Crack growth analysis of operational usage that differs from the 

baseline can be expressed as a crack growth rate severity factor relative to the baseline. The term 

“Equivalent Baseline Hours” has been used to define an equivalent state of fatigue damage

between different operators with different operational usage severity factors. Recent analysis of

commercial operational usage indicates that the severity relative to the baseline usage is

approximately 1.0. Some customer specific SMP 515-C programs have included an adjustment 

of the baseline inspection intervals based on an Operational Usage Evaluation (OUE), or a 

Damage Tolerance Analysis program. Inspection procedures that are subject to operational 

usage severity are identified by the applicability code “P”. 

The inspection intervals provided in this Section should be taken as the minimum required 

intervals for a typical cargo transport operational usage with average payloads not exceeding

20,000 lbs. For routine carriage of cargo in excess of 30,000 lbs, the inspection intervals for 

wing lower surface PSEs should be reduced by a factor of 2. Extended operation at altitudes 

below 5,000 feet also significantly increases the crack growth rates on the wing lower surface 

PSEs which requires reduced inspection intervals. LM Aero has recommended in Service 

Bulletin 382-57-84 that all commercial operators have their usage assessed to establish the rates 

of fatigue crack growth such that appropriate intervals of inspection can be established. 

In no circumstances should the operator extend these inspection intervals without having 

completed an LM Aero Operational Usage Evaluation and obtaining FAA approval for an 

updated SMP 515-C inspection program. 

6-2 

Change 1 - 10 September 2007 Use and/or disclosure is governed by statement on the title page of this document. 
SMP 515-C-SSID 

SECTION 6 

STRUCTURAL INSPECTION REQUIREMENTS 

6-3 

Change 1 - 10 September 2007 

Use and/or disclosure is governed by statement on the title page of this document. 

6.3 PSE Inspection Requirements and Intervals 

The inspection procedures and intervals provided in this section are related to the PSEs identified 

in Section 4. In the majority of cases, there are numerous inspection procedures that relate to a 

single PSE. There are also cases where one inspection procedure is related to more than one 

PSE. Where an inspection applies to multiple PSEs within an ATA sub-chapter, the last two 

digits of the PSE number are shown as “XX”. It is important to understand that all inspections in 

this section are required to cover the PSEs unless otherwise stated as optional inspections. 

There are three sources of PSE inspection procedures identified in this Section: 

• Structural (ST) Inspection Cards 

• Special (SP) Inspection Cards 

• Service Bulletins (SB) 

Operators should contact Lockheed Martin Aeronautics Company if they do not currently have 

the latest version of these inspection procedures. 

Initial inspection intervals are based on the Total Flight Hours (TFH) and/or calendar time 

accumulated on the applicable major component/PSE since new. The recurring inspection 

intervals are based on the Flight Hours (FH) accumulated on the major component/PSE since the 

last inspection was due. 

The initial and recurring inspection intervals contained in this section shall be accomplished not 

later than +10% of the specified interval. Where intervals are given in both flight hours and 

calendar time, the inspection is due at whichever occurs first. 

Chapter 57 outer wing inspections requirements are identified by Outer Wing Serial Number, 

which may not necessarily be the same as the aircraft serial number (some operators will have 

moved outer wings from one aircraft serial number to another). Many L382 model aircraft 

manufactured prior to LM SN 4542 have had the outer wings replaced by LM Aero 

Manufacturing End Product (MEP) outer wings. 
SECTION 6 

STRUCTURAL INSPECTION REQUIREMENTS 

 INSPE

SB/CARD

NUMBER

REVISION

DATE

PSE

NUMBER TITLE INITIAL 

CHAPTER 52 - DOORS

A ST-20 1-Jan-93 53-50-16 Inspection Diagonal Truss Member, Cargo Ramp Bulkheads 6 Years A SP-112 1-Nov-86 53-50-14 Visual Inspection Aft Cargo Door Side Beams 25,200 

or 12 Ye

CHAPTER 53 - FUSELAGE

A SB A382-

53-51Rev 1 

6-Nov-90 53-30-10 Fuselage - Inspection of Forward Fuselage Cabin Underfloor 

Bulkhead Structure at FS180.5, WL170, Between BL18 to BL27, Left and Right Side for Cracks 

10,000 

D SB 382-

53-61Rev 4 

1-May-07 53-40-13 Fuselage – Inspection of Wing to Fuselage Attach Angle 

LM 4383 – LM 5252 and Aircraft Modified to Include Attach Angle Straps, P/N 3305081-1/-2, 3305082-1/-2, 3313369-1/-2, 3313369-3/-4, and 3313369-5/-6 

12 Year

A ST-1 1-Jul-99 53-30-XX

53-40-XX 53-50-XX 

Visual Inspection Exterior Fuselage Structure 6 Years 

A ST-4 1-Jul-99 53-40-26 Check Fuselage Longeron Splice Fitting Tension Bolts 12 YearA ST-14 1-Jan-93 53-40-14

through 53-40-18 

Visual Inspection of Main Landing Gear and Wheel Well 3 Years 

A ST-15 1-Jun-91 53-40-14

53-40-15 

Inspection Main Landing Gear Vertical Beam Bolts 3 Years 

A ST-16 1-Jan-93 53-40-15 Visual Inspection Main Landing Gear Vertical Beams 3 Years A ST-18 1-Jul-91 53-40-18 Check Main Landing Gear Shelf Bracket Bolt Torque 3 Years A ST-19 1-Jan-93 53-40-15 Inspection MLG Wheel Well FS 597 Beams 3 Years 

A ST-22 1-Jul-99 53-40-03

53-40-05 53-40-06 

Check Fuselage Splice Bolts for Specified Torque. 12,600 

or 12 Ye

6-4 Change 1 - 10 September 2007 

Use and/or disclosure is governed by statement on the title page of this document. 
SECTION 6 

STRUCTURAL INSPECTION REQUIREMENTS 

 INSPE

SB/CARD

NUMBER

REVISION

DATE

PSE

NUMBER TITLE INITIAL 

A ST-25 1-Jul-99 53-30-08

53-30-10 53-30-14 

Visual Inspection of Flight Deck and Under Deck Electronic Equipment Area

6 Years 

A SP-29 1-May-87 53-40-13 Visual Inspection of FS 477 to FS 617 Attach Angle 12,600 

or 12 Ye

A P 

SP-30 1-Mar-93 53-50-07

53-50-08 53-50-09 

Visual Inspection Fuselage Side Frame (Vertical Strut) Attach Fittings 16,000 

or 12 Ye

A SP-32 1-May-87 53-40-12 Visual Inspection Gusset Fittings BL 61 L/R FS 245 to 737 20,000 

or 12 Ye

A P 

SP-34 1-Mar-93 53-40-19

53-40-22 

Visual Inspection Bulkhead Outboard Cap Flanges and External Splice Fittings FS 477, FS 617, WL 258 to 220 

12,600 or 12 Ye

A SP-35 1-Jan-86 53-40-03 Visual Inspection Fuselage Splice Fittings 12,600 

or 12 Ye

A P 

SP-36 1-Jan-86 53-50-07 Visual Inspection FS 880 Cap and Web 12,600 

or 12 Ye

A P 

SP-37 1-Dec-85 53-30-01 Visual Inspection Window Areas and External Windshield Doublers 

LM 3501 - 4568 LM 4569 - LM 4760 LM 4761 and up 

12,600 or 6 Yea12,600 or 12 Ye30,000 or 18 Ye

Change 1 - 

Use and/or disclosure is governed by statement on the title page of this document. 
SECTION 6 

STRUCTURAL INSPECTION REQUIREMENTS 

 INSPE

SB/CARD

NUMBER

REVISION

DATE

PSE

NUMBER TITLE INITIAL 

A P 

SP-38 1-May-87 53-50-11 Visual Inspection Fuselage Bulkhead Struts 

LM 3946 - LM 4340 After S/B 382-044 and 382-070 Incorporation and onLM 4341 – LM 4966 LM 4967 and up 

3,400 Tor 3 Yea3,400 Tor 3 Yea12,000 or 9 Yea

A P 

SP-68 1-May-87 53-30-09 Visual/NDI Inspection FS 165 Structure – NDI As Required (LM 3501 

– LM 4760) (Visual Inspection only Aircraft with Steel Inner and Outer Attach Angles and LM 4761 and up) 

12,600 

A P 

SP-69 1-Jan-86 53-40-14 Visual Inspection FS 497, FS 537, and FS 557 Structure 9,450 T

or 9 Yea

A SP-70 1-Jan-86 53-40-16 Visual Inspection of MLG Wheel Well Structure, WL 200 FS 517 and 

FS 597 

20,000 or 12 Ye

A SP-71 1-Jan-86 53-40-16 Visual Inspection of MLG Wheel Well Structure, WL 200 FS 477 18,000 

or 12 Ye

A P 

SP-72 1-Jan-86 53-40-23 Visual Inspection FS 477 and FS 617 MLG Wheel Well Fittings 16,000 

or 12 Ye

D 

P 

SP-78 (See SP114) 

1-Jul-87 53-40-18 NDI Cargo Floor Bulkhead End (Aluminum Pork Chop) FS 597 

(LM 3501 - LM 4712) 

Inspection not applicable to LM 4713 and up or Aircraft with P/N 3313808 or 3314760 Steel Pork Chop Fittings

6,300 T

A SP-86 1-Nov-94 53-40-01 Visual Inspection Fuselage Mounting Rings FS 245 and FS 737 12,600 

or 12 Ye

6-6 Change 1 - 10 September 2007 

Use and/or disclosure is governed by statement on the title page of this document. 
SECTION 6 

STRUCTURAL INSPECTION REQUIREMENTS 

 INSPE

SB/CARD

NUMBER

REVISION

DATE

PSE

NUMBER TITLE INITIAL 

A SP-87 1-Nov-94 53-30-02

through 53-30-07 53-40-02 through 53-40-06 53-50-01 through 53-50-04 53-50-12 53-50-13 

Visual Inspection Fuselage Splice Attachment Fittings FS 245 and FS 737 

12,600 or 12 Ye

D SP-95 1-May-89 53-40-15 NDI Main Frame and Cap FS 517, WL 215 and BL 67 LM 3501 - LM

4751 

Inspection not applicable After Incorporation of S/B 382-53-19 (A382-189) and LM 4752 and up

10,000 

D 

P 

SP-96 1-Oct-98 53-30-12 NDI Area Above Crew Entry Door LM 3501 – LM 4871

Visual Inspection Only for Aircraft Modified per SMP 583 Figure 53-30-30 (See SP-274) 

6,300 T

A P 

SP-99 1-Jan-86 53-40-21 Visual Inspection of Upper Bulkhead Tension Tie Fittings FS 477 and 

617, BL 61 L/R 

12,600 or 12 Ye

D SP-107 1-Nov-95 53-40-24 Visual Inspection of Longeron Below Personnel Doors FS 697 

LM 3501 - LM 4568 

Inspection not applicable After S/B 382-53-21 Incorporation and LM4569 and up

20,000 or 12 Ye

D SP-108 1-Jan-86 53-40-17 Visual Inspection of MLG Access Panel Openings FS 522 and 583 

LM 3501 - LM 4673 

Inspection not applicable to Aircraft with Steel Doubler Installation and LM 4674 and up

16,000 or 12 Ye

Change 1 - 

Use and/or disclosure is governed by statement on the title page of this document. 
SECTION 6 

STRUCTURAL INSPECTION REQUIREMENTS 

 INSPE

SB/CARD

NUMBER

REVISION

DATE

PSE

NUMBER TITLE INITIAL 

D SP-109 1-Nov-92 53-50-12

53-50-13 

Visual and NDI longeron Fittings Lower BL 61 at FS 737 and 1041 LM 3501 - LM 4583 With P/N 356198-2L/2R or -3/-4 

Visual Only at FS 737 LM 3501 - LM 4583 With P/N 356198-5/-6 or Later Fittings and LM 4584 and up

At FS 1041 LM 3501 - LM 4586 With P/N 337426-L/-R 

Visual Only at FS 1041 LM 3501 - LM 4586 With P/N 337426-5/-6 or Later Fittings and LM 4587 and up

5 Years 5 Years 5 Years 5 Years 

A SP-110 1-Jul-99 53-50-09

55-10-06 

Visual Inspection of Aft Fuselage Top Bulkhead Frames 16,000 

or 12 Ye

A SP-113 1-Jul-87 53-50-13 NDI Longeron if Fitting at FS 1041 is Being Replaced FS 104

Replace

D SP-114

(See SP-78) 

1-Jun-94 53-40-18 NDI Cargo Floor Bulkhead End Fittings (P/N 371603 Aluminum Pork 

Chop) FS 597- After Repair Action LM 3501 - LM 4712 

Special Conditio

A SP-115 1-Jul-87 53-40-15 NDI FS 597 Main Frame 

Inspection not applicable to FS 597 Main Frames repaired per SMP 583, Figure 53-40-31

6,300 T

A SP-121 1-Jan-86 53-40-18 Visual Inspection of Cargo Floor Bulkhead End Fittings 25,200 

or 12 Ye

6-8 Change 1 - 10 September 2007 

Use and/or disclosure is governed by statement on the title page of this document. 
SECTION 6 

STRUCTURAL INSPECTION REQUIREMENTS 

 INSPE

SB/CARD

NUMBER

REVISION

DATE

PSE

NUMBER TITLE INITIAL 

A P 

SP-126 (See SP-224) 

1-Dec-95 53-40-19

53-40-20 

Visual Inspection of Area Between FS 477 and FS 517, BL 61 L/R, Above WL 256 and Fairing Attach Angles at FS 477 LM 3501 – LM 4932 LM 4933 - 5305 Incorporation of SB A382-53-49/382-53-50 Accomplishes the intent of the Initial Inspection. 

No inspection to Fairing Attach Angles P/N 340043-9L/9R is required after SB 382-53-27 incorporation and on LM 4761- LM 5305Inspection not applicable to LM 5306 and up

6,300 T6,300 T

A P 

SP-127 1-Dec-85 53-40-19

53-40-20 

Visual Inspection of Area Between FS 596 and FS 617, BL 61 L/R, Above WL 256 and Fairing Attach Angles at FS 617 

No inspection to Fairing Attach Angles P/N 343067-9 L/R after SB 382-53-27 and on LM 4968 and up 

12,600 

A SP-161 1-May-93 53-40-11

53-50-15 53-50-16 

Inspection of Cargo Compartment and Ramp Underfloor Areas LM3501 - LM 4991 LM 4992 and up 

3 Years 6 Years 

A SP-192 1-Dec-85 53-40-15 Visual Inspection Left and Right Fuselage BL 61 L/R Vertical Main

Frames, FS 517 and FS 597 at WL 256 

10,000 or 12 Ye

A P 

SP-200 1-Dec-86 53-40-15 NDI MLG Vertical Beam at FS 517, 528, 577, and 588

Inspection not applicable to Vertical Beams With Steel Doublers

12,600 

D SP-201 1-Apr-93 53-40-13 NDI Center Wing to Fuselage Drag Angle Inner Radius Between FS 

477 and 617 (Aircraft Without Strap Doublers on Horizontal and Vertical Legs of Drag Angle) LM 3501-4382 and Aircraft With Replacement MEP Wings without Strap Doublers Refer to SB 382-53-61 for inspection of attach angle with Strap Doublers

Inspection not applicable to 382G Series

16,000 or 12 Ye

Change 1 - 

Use and/or disclosure is governed by statement on the title page of this document. 
SECTION 6 

STRUCTURAL INSPECTION REQUIREMENTS 

 INSPE

SB/CARD

NUMBER

REVISION

DATE

PSE

NUMBER TITLE INITIAL 

A SP-224

(See SP126) 

1-Jan-93 53-40-19 NDI Fuselage Pressurized Fairing Support Structure, FS 477 to FS 

517, BL 61 L/R Above WL 256 Incorporation of SB A382-53-49 Accomplishes the Intent of the Initial Inspection. Incorporation of SB 382-53-50 Accomplishes the Intent of the Initial Inspection. 

Inspection not applicable to LM 5306 and up

6,300 T

A SP-262 1-Apr-93 53-40-23 NDI Lower Strut Attachment Fitting at FS 477 and FS 617 Frames 8,000 TA SP-271 1-Jul-99 53-50-10 NDI Inspection of FS 737, 777E or 817E Floor to Ring Bulkhead 

Fitting 

Fuselage Maximum Pressure Differential

HG PSIG

14.3 - 15.3 7.0 - 7.5 13.2 - 14.3 6.5 - 7.0 12.2 - 13.2 6.0 - 6.5 10.2 - 12.2 5.0 - 6.0 

 8.1 - 10.2 4.0 - 5.0 Less than 8.1 Less than 4.0

Inspection not applicable to Aircraft with Original or Replacement Fittings with Cold Worked Holes (SB 382-53-53)

8,000 T12,000 14,400 20,000 36,000 45,000 

A P 

SP-274 1-Jul-99 53-30-12 Visual Inspection Above Crew Entry Door (LM 4872 and up and 

Aircraft Modified per SMP 583, Figure 53-30-30) 

12,600 

A SP-297 1-Oct-01 53-30-08 NDI Fuselage Frames FS 132 L/R 24,000 A SP-298 1-Oct-01 53-30-08 NDI Fuselage Frames, FS 212 and 228L at WL 195 12 Year

6-10 Change 1 - 10 September 2007 

Use and/or disclosure is governed by statement on the title page of this document. 
SECTION 6 

STRUCTURAL INSPECTION REQUIREMENTS 

 INSPE

SB/CARD

NUMBER

REVISION

DATE

PSE

NUMBER TITLE INITIAL 

A SP-299 1-Oct-01 53-30-09

53-40-01 

NDI Diaphragm Attach Angle FS 165 BL 18L/R, Bulkhead Lower Cap FS 245 WL 126 - 146 BL 50 L/R and Bulkhead Lower Cap FS 165, WL 168 BL 18 – 27.5 

12 Year

A SP-300 1-Oct-01 53-30-11 NDI NLG Structure FS 196 L/R at WL 145 12 Year

A SP-303 1-Oct-01 53-40-10 NDI Center Fuselage Lower Chine Angles FS 517 – 597 L/R, Chine 

Caps FS 245 – 737 L/R and Cargo Ramp Outboard Floor Plates L/R 

12 Year

A SP-304 1-Oct-01 53-40-16 NDI Horizontal Beam Assembly and Fittings FS 517 – 597 L/R at WL 

200 

12 Year

A SP-305 1-Oct-01 53-50-12

53-50-13 

NDI Aft Fuselage Lower (Sloping) Longeron FS 737 (FS 817E on 382G) to FS 1041 L/R and Attach Fittings at FS 737 L/R (FS 817E L/R on 382G) 

12 Year

A SP-306 1-Oct-01 53-50-10 NDI Fuselage Ring and Ring Segment FS 737 L/R at WL 148 12 Year

A SP-308 1-Oct-01 53-40-25 NDI Paratroop Door Frame Structure 12 YearA SP-309 1-Oct-01 53-40-15 NDI MLG Beam FS 517 – 597 L/R, WL 140 – 168 12 Year

CHAPTER 54 - NACELLES

A SP-21 1-Jul-99 57-30-12

57-50-19 

Power Plant to Truss Mount Attachment Engine 

A SP-120 1-Nov-86 57-30-12

57-50-19 

NDI Engine Truss Mount Lugs at Diagonal Tube Attachment DuringInstallation of Press Fit Steel Bushing Repair 

See SP

CHAPTER 55 - STABILIZERS

A ST-5 1-May-93 55-10-02

through 55-10-04 

Visual Inspection of Vertical and Horizontal Stabilizer 6 Years 

A ST-6 1-Sep-91 53-50-12

53-50-17 55-10-08 

Visual Inspection Empennage Attachment Fittings 6 Years 

A ST-7 1-Apr-93 53-50-17

55-10-08 

Check Dorsal Fin, Vertical Stabilizer and Horizontal Attachment Bolts for Torque 

12,600 or 12 Ye

Change 1 - 

Use and/or disclosure is governed by statement on the title page of this document. 
SECTION 6 

STRUCTURAL INSPECTION REQUIREMENTS 

 INSPE

SB/CARD

NUMBER

REVISION

DATE

PSE

NUMBER TITLE INITIAL 

A ST-8 1-Jul-99 55-10-09 Inspection Elevators and Rudder 6 Years A ST-24 1-Jul-99 55-10-XX Visual Inspection of Vertical and Horizontal Stabilizer, Attach Fittings 

and Mating Surfaces

24 Year

A SP-39 1-Jan-90 55-10-07 Visual Inspection Vertical Stabilizer Fittings 9,450 T

or 9 Yea

CHAPTER 57 - WINGS

D SB 382-

57-78

14-May-03 57-30-01 Wings – Inspection of Center Wing Lower Forward Spar Cap at CWS 

168 to CWS 177 (LM 3501 – LM 5305) Internal SEC External SEC 

10,000 10,000 

D SB 382-

57-77

03-Oct-01 57-30-15 Wing – Inspection of Center Wing Upper Forward and Aft Corner

Fittings Manufactured From 7075-T6 Material 

12 Year

D SB 382-

71-23Rev 1 

28-Aug-06 57-30-12

57-50-19 

Power Plant – Inspection of Engine Truss Mount for Cracking of the Diagonal Brace Lugs with the Press Fit Steel Bushing Installed LM 4801 and up and Aircraft with Diagonal Lugs Modified by SB 382-71-13 and/or Repaired by SMP 583 to Install Press Fit Bushing or Replaced with Current Production Configuration Truss Mounts 

12,000 

A ST-9 1-Jul-99 57-30-12

57-50-19 

Inspection of Nacelle to Wing Truss Mounts

Aircraft with truss mount(s) P/N 360013-23, 360014-23, 360015-19, 360016-19, 360017-23, 360018-23 and subsequent, installed in any engine position do not require an inspection at the affected engineposition

3 Years 

A ST-10 1-May-93 57-30-XX

57-50-XX 

Visual Inspection of Wing Exterior Surfaces 6 Years 

A ST-11 1-May-93 57-50-XX Visual Inspection of Outer Wings Interior Structure 6 Years 

A ST-12 1-Jul-99 57-50-21 Inspection Ailerons and Aileron Control System 6 Years 

6-12 Change 1 - 10 September 2007 

Use and/or disclosure is governed by statement on the title page of this document. 
SECTION 6 

STRUCTURAL INSPECTION REQUIREMENTS 

 INSPE

SB/CARD

NUMBER

REVISION

DATE

PSE

NUMBER TITLE INITIAL 

A ST-13 1-Apr-93 57-50-03 Check WS 220 Wing Joint Bolts for Specified Torque 12,600 

or 12 Ye

A P 

SP-61 (See SP195/ SP199) 

1-Jun-94 57-50-12 NDI Outer Wing Lower Surface Kingpin Risers OWS 35 External 

Ultrasonic Inspection Procedure Note: Only one Inspection Workcard shall be used; however 

recurring interval is dependent on NDI technique selected 

LM 3501 - LM 4298 LM 4299 - LM 4541 LM 4542 up and Aircraft with MEP Type Replacement Outer Wings 

6,000 T7,800 T20,000 

D 

P 

SP-62 (See SP-196/ SP-197) 

1-Dec-86 57-50-06

57-50-12 

NDI Lower Forward Wing Panel Beam Cap OWS 54 and 108 LM 3609 - LM 4298 LM 3609 - LM 4298 After Dwg. 3304454 External Strap Installation(ECP 954) LM 4299 - LM 4541 LM 4299 - LM 4541 After Dwg 3304454 

Inspection not applicable to LM 3609 - 4541 After Incorporation ofDwg. 3312391 or Dwg. 3312416 of SB 382-187Inspection not Applicable to LM 4542 up and Aircraft with MEP Type Replacement Outer Wings

3,500 T3,500 T3,900 T3,900 T

G SP-64 1-Aug-84 57-50-20 Visual Inspection of Outer Wing Upper Rib Cap, OWS 162 and 197 

LM 3501 - LM 4298 After SB 382-051 Incorporation LM 4299 - LM 4541 

Inspection not applicable to LM 4542 up and Aircraft with MEP Type Replacement Outer Wings

3,400 T12,600 12,600 

Change 1 - 

Use and/or disclosure is governed by statement on the title page of this document. 
SECTION 6 

STRUCTURAL INSPECTION REQUIREMENTS 

 INSPE

SB/CARD

NUMBER

REVISION

DATE

PSE

NUMBER TITLE INITIAL 

A P 

SP-66 1-Aug-84 57-50-02 NDI Lower Outer Wing Attach Fitting (Rainbow) 

LM 3501 – LM 4333 LM 3501 - LM 4333 New Rainbow Fitting Installation (Dwg. 3302624)LM 4334 - LM 4454 LM 4334 - LM 4454 After SB 382-145 Incorporation LM 4455 - LM 4541 LM 4542 up and Aircraft with MEP Type Replacement Outer Wings 

6,300 T12,600 6,300 T12,600 12,600 30,000 

A SP-67 1-Aug-86 57-50-01 Visual Inspection of Upper Outer Wing Attach Fitting (Rainbow) 

LM 3501 - LM 4333 LM 4334 - LM 4541 and LM 3501 - LM 4333 With Dwg. 3302624 (New Rainbow Fitting)NOTE: Ultrasonic Inspection Required if Failsafe Straps are IncorporatedLM 4542 up and Aircraft with MEP Type Replacement Outer Wings 

6,300 T15,000 30,000 

A P 

SP-73 1-Jan-92 57-50-12 NDI Outer Wing Lower Surface Skin Panels OWS 18, 72, 90 and 231

LM 3501 - 4298 NOTE: Inspection not applicable at OWS 72 and 90 on LM 3501 - 

LM 3608 With Original Outer Wings Without Provisions for External Tanks 

After Dwg. 3304473 and 3304557 (Fastener Replacement) Incorporation LM 4299 - 4541 Aircraft with MEP Type Replacement Outer Wingsand LM 4542 up 

6,300 T12,600 18,900 47,200 

6-14 Change 1 - 10 September 2007 

Use and/or disclosure is governed by statement on the title page of this document. 
SECTION 6 

STRUCTURAL INSPECTION REQUIREMENTS 

 INSPE

SB/CARD

NUMBER

REVISION

DATE

PSE

NUMBER TITLE INITIAL 

A SP-74 1-Aug-84 57-50-01 NDI Outer Wing Upper Attach Fittings (Rainbow) 

LM 3501 - LM 4454 LM 3501 - LM 4333 After Incorporation of SB 382-145 and New Rainbow Fitting Installation (Dwg. 3302624) LM 4334 – LM 4454 After Incorporation of SB 382-145 LM 4455 - LM 4541 LM 4542 up and Aircraft with MEP Type Replacement Outer Wings 

6,300 T12,600 12,600 12,600 30,000 

G 

P 

SP-75 1-Dec-86 57-50-06

57-50-11 57-50-12 

NDI Outer Wing Forward Lower Surface Skin Panel, Beam Cap and Beam Web (Various OWS)OWS 144 to 165 and OWS 195 to 214 (X-Ray/Eddy Current) OWS 144 to 159 and OWS 200 to 214 (Visual Web only) After SB A382-169 Kit A Incorporation - (SP 207 also required) After SB A382-169 Kit B Incorporation OWS 144 to 159 and OWS 200 to 214 (Visual - Web only) - (SP 207 also required)After SB A382-169 Kit A and SB 382-152 Dwg. 3307167 Incorporation 

5,000 T5,400 T5,400 T5,400 T

OWS 153 to 159 and OWS 200 to 206 (X-Ray) Dwg. 144 to 159 and 

OWS 200 to 214 (Visual - Web) - (SP 207 also required) After SB A382-169 or Kit B and SB 382-152 Dwg. 3307167 Incorporation OWS 144 to 159 and OWS 200 to 214 (Visual - WebOnly) - (SP 207 also required) After SB A382-169, Kit A or B, and NWI Dwg. 3609103 Incorporation OWS 144 to 159 and OWS 200 to 214 (Visual - Web Only) (SP 207 also required) 

Inspection not applicable to LM 4542 up and Aircraft with MEP Type Replacement Outer Wings

5,400 T5,400 T5,400 T

Change 1 - 

Use and/or disclosure is governed by statement on the title page of this document. 
SECTION 6 

STRUCTURAL INSPECTION REQUIREMENTS 

 INSPE

SB/CARD

NUMBER

REVISION

DATE

PSE

NUMBER TITLE INITIAL 

A P 

SP-76 1-Jul-99 57-50-12 NDI Outer Wing Lower Surface Skin Panels OWS 162 and 197 

(Optional Inspection Techniques) Outer Wing Panel Number 1, 2, 3 and 4 LM 3501 to LM 4541  X-Ray  Ultrasonic After SB 382-152 Outer Wing Panel Number 3 and 4 Only LM 3501 to LM 4541 Dwg. 3307167 X-Ray  Ultrasonic 

Inspection not applicable After NWI Drawing. 3609103 or SB 382-57-73 Incorporation LM 3501 to LM 4541

Aircraft With MEP Type Replacement Outer Wings and LM 4542 up  X-Ray  Ultrasonic 

10,000 10,000 10,000 10,000 45,000 45,000 

A SP-82 1-Aug-84 57-50-13 NDI Outer Wing Upper Surface Panel Numbers 2 and 3 OWS 6 

LM 3501 - LM 4541 LM 4542 up and Aircraft with MEP Type Replacement Outer Wings 

30,000 60,000 

D 

P 

SP-83 1-Sep-89 57-50-13 NDI Outer Wing Upper Surface at Panel Attachment Holes 

LM 3609 - LM 4541 After Dwg. 3304473 (Fastener Replacement) Incorporation 

Inspection not applicable to LM 4542 up and Aircraft with MEP Type Replacement Outer Wings

6,300 T6,300 T

6-16 Change 1 - 10 September 2007 

Use and/or disclosure is governed by statement on the title page of this document. 
SECTION 6 

STRUCTURAL INSPECTION REQUIREMENTS 

 INSPE

SB/CARD

NUMBER

REVISION

DATE

PSE

NUMBER TITLE INITIAL 

A P 

SP-85 1-Mar-94 57-50-19 NDI Number 1 and Number 4 Engine Truss Mount Lugs 

LM 3501 - LM 4541 After Dwg. 3304390 Incorporation Aircraft with Replacement MEP Outer Wings and LM 4542 up 

6,300 T6,300 T23,000 

G 

P 

SP-88 1-Dec-86 57-50-07

57-50-10 57-50-12 

NDI Outer Wing Lower Surface Panel Number 4, Lower Aft Beam Cap and Beam Web OWS 54 and 108 LM 3501 - LM 4298 After Dwg 3304454 Incorporation External Strap Installation (ECP954) LM 4299 - LM 4541 After Dwg. 3304454 Incorporation External Strap Installation (ECP954) 

Inspection not applicable After Incorporation of Dwg. 3312419 or Dwg. 3312391 of SB 382-187Inspection not applicable to LM 4542 up and Aircraft with MEP Type Replacement Outer Wings

6,550 T6,550 T7,760 T7,760 T

A P 

SP-89 1-Jan-92 57-50-12 NDI Outer Wing Lower Surface Panels at OWS 6 

LM 3501 - LM 4298 LM 4299 - LM 4541 Aircraft With MEP Type Replacement Outer Wings and LM 4542 up 

6,300 T12,600 40,000 

A P 

SP-90 1-Jan-92 57-50-12 NDI Outer Wing Lower Surface Panel Splices

LM 3501 - LM 4298 LM 4299 - LM 4541 Aircraft With MEP Type Replacement Outer Wings and LM 4542 up 

6,300 T8,400 T40,000 

Change 1 - 

Use and/or disclosure is governed by statement on the title page of this document. 
SECTION 6 

STRUCTURAL INSPECTION REQUIREMENTS 

 INSPE

SB/CARD

NUMBER

REVISION

DATE

PSE

NUMBER TITLE INITIAL 

A SP-92 1-Aug-86 57-50-18 Visual Inspection Outer Wing Front Beam Splice Tee OWS 158 and 

OWS 201 

9,450 T

A P 

SP-103 1-Jul-99 57-50-04

57-50-06 57-50-11 57-50-12 

NDI Outer Wing Lower Forward Beam Cap, Web, Corner Fitting and Skin Panel Number 1, OWS 0 to 20, LM 3501 - LM 4541 Aircraft With MEP Type Replacement Outer Wings and LM 4542 up 

20,000 40,000 

D SP-104 1-Jul-99 57-50-12 NDI Outer Wing Lower Skin Panels at Forward and Aft Beam Caps 

OWS 0 to OWS 300 LM 3501 - LM 4347

Inspection not applicable After Incorporation of SB 382-57-44 or Dwg. 3306902-1/-2Inspection not applicable to LM 4542 up and Aircraft with MEP Type Replacement Outer Wings

15,000 

D SP-116 1-Aug-84 57-30-16 Visual Inspection Center Wing Vertical Attach Angles (CWS 220) 

LM 3501 - LM 4910 and Aircraft With Replacement MEP Center Wings 

Inspection not applicable to Center Wing Attach Angles Replaced or Repaired per SMP 583, Figure 57-30-23Inspection not applicable to LM 4911 and up

12 Mon

A P 

SP-118 1-Jul-99 57-30-12

57-50-19 

NDI Engine Truss Mount Lugs at Diagonal Tube Attachment LM 3501 – LM 4800 (non-bushed) Refer to SB 382-71-23 for inspection requirements of diagonal lugsmodified by SB 382-71-13 and/or repaired by installing a press fit bushing per SMP 583 and LM 4801 and up. 

4,000 T

A SP-119 1-Mar-93 57-30-XX Visual Inspection Center Wing Interior Structure 12 Year

6-18 Change 1 - 10 September 2007 

Use and/or disclosure is governed by statement on the title page of this document. 
SECTION 6 

STRUCTURAL INSPECTION REQUIREMENTS 

 INSPE

SB/CARD

NUMBER

REVISION

DATE

PSE

NUMBER TITLE INITIAL 

D 

P 

SP-123 1-Aug-86 57-50-06

57-50-11 

NDI Outer Wing Lower Forward Beam Cap OWS 72 and 90 LM 3609 - LM 4347 LM 4348 - LM 4541 LM 4542 up and Aircraft with MEP Type Replacement Outer Wings (Note: See SP-316) 

Inspection not applicable After Incorporation of SB 382-187 Dwg. 3312416 and Steel Web per Dwg. 3312417Inspection not applicable After Incorporation of NWI Dwg. 3609057 and Steel Web per Dwg. 3312417

8,500 T10,000 24,000 

G 

P 

SP-124 1-Aug-86 57-50-12 NDI Outer Wing Lower Surface Skin Panels Around Drain Holes 

OWS 170 LM 3501 - LM 4298 LM 3501 - LM 4298 After SB 382-152 (Dwg. 3307167) Only Inspect Panel Number 3 and 4 LM 4299 - LM 4541 (Refer to SP-202 in Event of Cracks) 

Inspection not applicable to LM 3501 - LM 4541 After Incorporation of NWI Dwg. 3609103 or SB 382-57-73Inspection not applicable to Aircraft with MEP Type Replacement Outer Wings and LM 4542 up

9,000 T12,000 13,400 

A P 

SP-128 1-Dec-85 57-50-04

57-50-07 57-50-10 57-50-12 

NDI Outer Wing Lower Rear Beam Cap, Web, Corner Fitting and Skin Panel Number 4, OWS 0 to 20 LM 3501 - LM 4541. LM 4542 up and Aircraft with MEP Type Replacement Outer Wings 

20,000 40,000 

Change 1 - 

Use and/or disclosure is governed by statement on the title page of this document. 
SECTION 6 

STRUCTURAL INSPECTION REQUIREMENTS 

 INSPE

SB/CARD

NUMBER

REVISION

DATE

PSE

NUMBER TITLE INITIAL 

A SP-129 1-Aug-84 57-50-13 Visual Inspection Outer Wing Upper Surface Panels 

LM 3501 - LM 4541. LM 4542 Up and MEP Type Replacement Outer Wings 

25,200 or 12 Ye30,000 or 12 Ye

A P 

SP-131 1-Mar-94 57-30-12 NDI Number 2 and Number 3 Engine Truss Mount Lugs 17,000 

G 

P 

SP-133 1-Aug-86 57-50-12 NDI Outer Wing Lower Surface Skin Panels in Areas of Riser Drain

Holes OWS 250, 253 and 256 LM 3501 - LM 4541. 

Inspection not applicable to LM 4542 up and Aircraft with MEP Type Replacement Outer Wings

20,000 

G 

P 

SP-134 1-Aug-86 57-50-12 NDI Outer Wing Lower Surface Skin Panels in Areas Where Brackets 

Attach to Risers, OWS 120 to 124 LM 3501 - LM 4541. 

Inspection not applicable to LM 4542 up and Aircraft with MEP Type Replacement Outer Wings

20,000 

G 

P 

SP-135 1-Nov-95 57-50-12 NDI Outer Wing Lower Surface Panel Risers at Rib Clip Attachments 

OWS 162 and 197 LM 3501 - LM 4298 - (After Incorporation of SB 382-152 No Further Inspection of Forward Clips Required)

Inspection not applicable After Incorporation of NWI Dwg. 3609103 or SB 382-57-73

LM 4299 - LM 4541 - (After Incorporation of SB 382-152 No Further Inspection of Forward Clips Required)

Inspection not applicable to LM 4542 up and Aircraft with MEP Type Replacement Outer Wings

9,000 T16,000 

6-20 Change 1 - 10 September 2007 

Use and/or disclosure is governed by statement on the title page of this document. 
SECTION 6 

STRUCTURAL INSPECTION REQUIREMENTS 

 INSPE

SB/CARD

NUMBER

REVISION

DATE

PSE

NUMBER TITLE INITIAL 

A P 

SP-136 1-Aug-86 57-50-12 NDI Outer Wing Lower Surface Skin Panels in Area Where Surge

Box Attaches to Panel Riser OWS 246 LM 3501 - LM 4541 LM 4542 up and Aircraft with MEP Type Replacement Outer Wings 

20,000 40,000 

G 

P 

SP-137 1-Aug-84 57-50-12 NDI Outer Wing Lower Surface Skin Panels 3 and 4 in Areas of Riser 

Drain Holes OWS 38, 41 and 44 LM 3501 - LM 4541

Inspection not applicable to LM 4542 up and Aircraft with MEP Type Replacement Outer Wings

14,000 

A P 

SP-138 1-Dec-86 57-30-07 NDI Center Wing Lower Surface Panels, BL 61, FS 517 to FS 597 20,000 

A P 

SP-139 1-Oct-96 57-50-15 NDI Outer Wing Lower Surface Kingpin Riser Stiffeners OWS 14 to

22 LM 3501 - LM 4541 LM 4542 up and Aircraft with MEP Type Replacement Outer Wings 

24,000 48,000 

A P 

SP-141 1-Aug-86 57-30-07 NDI Lower Surface Skin Panel At FS 597 From BL 58 to BL 61 

Incorporation of SB 382-57-50 Meets the Intent of the Initial Inspection After Incorporation of SMP 583 Figure 57-30-26, Perform Detailed Visual Inspection Around Periphery of Repair 

20,000 1,800 T

A SP-158 1-May-93 57-30-07

57-50-12 57-50-17 

Visual Inspection Under Engine Heat Shields - Wing Upper and Lower Trailing Edge Surface 

1 Year 

A SP-160 1-Dec-98 57-50-XX Visual Inspection Fuel Tanks 

LM 3501 - LM 4991 and Aircraft with Replacement MEP 12R/13/R Outer Wings LM 4992 and up and Aircraft with Replacement MEP 1T/2T, 9T/10T Outer Wings 

3 Years 6 Years 

Change 1 - 

Use and/or disclosure is governed by statement on the title page of this document. 
SECTION 6 

STRUCTURAL INSPECTION REQUIREMENTS 

 INSPE

SB/CARD

NUMBER

REVISION

DATE

PSE

NUMBER TITLE INITIAL 

A P 

SP-163 1-Jan-92 57-30-14 NDI Center Wing Forward Lower Corner Fittings 

LM 3501 - 4298, 4304 and up P/N 390619-1/-2, -5/-6 and -7/-8 (LongFittings) LM 4299 - 4303 P/N 388038-3/-4 (Short Fittings) LM 4299 - 4303 P/N 390619-1/-2, -5/-6 or -7/-8 (Replacement Long Fittings) 

15,000 10,000 15,000 

A SP-165 1-Jun-94 57-50-14 NDI Outer Wing Rib Caps and Braces

LM 3501 - 4991 and Aircraft With Replacement MEP 12R/13R Outer Wings Incorporation of SB 382-57-51 Meets the Intent of the Initial Inspection LM 4992 and up and Aircraft With Replacement MEP 1T/2T, 9T/10TOuter Wings 

12,000 30,000 

D 

P 

SP-168 1-Aug-84 57-30-07 NDI Center Wing Lower Surface Rectangular Fuel Tank Access 

Panel at CWS 120, Left and Right LM 4299 - 4313 After Incorporation of LM Repair Sketch SK 382-57-044, Perform Detailed Visual Inspection Around Periphery of Repair

15,000 1,800 T

A P 

SP-169 1-Dec-86 57-30-01

57-30-06 

NDI Center Wing Front Beam Web and Lower Cap Between CWS 77 and 81, Left and Right 

20,000 

A P 

SP-170 1-Jun-94 57-30-02

57-30-05 

NDI Center Wing Rear Beam Web and Lower Cap Between CWS 76 and 82, Left and Right 

20,000 

6-22 Change 1 - 10 September 2007 

Use and/or disclosure is governed by statement on the title page of this document. 
SECTION 6 

STRUCTURAL INSPECTION REQUIREMENTS 

 INSPE

SB/CARD

NUMBER

REVISION

DATE

PSE

NUMBER TITLE INITIAL 

A P 

SP-171 1-Dec-05 57-50-12 NDI Outer Wing Lower Surface Forward and Aft Panel to Beam Cap

Spanwise Splices OWS 7 to 300 Aircraft with SB 382-152 and 382-57-73 or NWI Dwg 3609103 Incorporated Do Not Require Inspection of the Panels Between OWS 144 and 214 LM 3501 - LM 4298 LM 4299 - LM 4541 LM 4542 and up and Aircraft With MEP Type Replacement Outer Wings 

5,500 T8,000 T35,000 

A P 

SP-172 1-Jan-92 57-50-07

57-50-10 

NDI Outer Wing Rear Beam Lower Cap and Web at OWS 72 and 90, L/R LM 3609 - 4541 LM 4542 and up and Aircraft With MEP Type Replacement Outer Wings 

7,000 T30,000 

A P 

SP-174 1-Dec-85 57-30-02

57-30-05 

NDI Lower Aft Beam Cap and Web CWS 199 and 203 15,000 

A P 

SP-176 1-Dec-04 57-30-17 NDI Center Wing Upper Rainbow Fitting Access Cutouts CWS 217 

and 219 

15,000 

A SP-177 1-Jun-94 57-30-17 NDI Center Wing Upper Rainbow Fitting Vertical Legs, Forward and 

Aft 

25,200 

A SP-178 1-Jun-94 57-50-01 NDI Outer Wing Upper Rainbow Fitting Vertical Legs, Forward and

Aft 

25,200 

Change 1 - 

Use and/or disclosure is governed by statement on the title page of this document. 
SECTION 6 

STRUCTURAL INSPECTION REQUIREMENTS 

 INSPE

SB/CARD

NUMBER

REVISION

DATE

PSE

NUMBER TITLE INITIAL 

G 

P 

SP-183 1-Nov-95 57-50-12 NDI Outer Wing Lower Surface Skin Panels Number 1, 2 and 3 

Around Lockheed Doubler Installation per SB 382-152, (Dwg. 3307167) OWS 144 and OWS 214 LM 3501 - LM 4298 NDI Ultrasonic ProcedureVisual Inspection Procedure (Alternate)LM 4299 - LM 4541 NDI Ultrasonic ProcedureVisual Inspection Procedure (Alternate)NDI Outer Wing Lower Surface Skin Panels Number 3 and 4 Around Perimeter of Doubler Installation per SB 382-57-73 (Applicable Aircraft) (Dwg. 3335100) LM 3501 - LM 4298 NDI Ultrasonic ProcedureVisual Inspection Procedure (Alternate)LM 4299-4541 NDI Ultrasonic ProcedureVisual Inspection Procedure (Alternate)

Inspection not applicable to LM 4542 up and Aircraft with MEP Type Replacement Outer Wings

5,000 T5,000 T9,300 T9,300 T5,000 T5,000 T9,300 T9,300 T

G 

P 

SP-184 1-Aug-86 57-50-12 NDI Outer Wing Lower Surface Skin Panels at NWI Doubler 

Installation per NWI Dwg. 3609103 OWS 144 and OWS 214 LM 3501 - 4298 NDI Ultrasonic ProcedureVisual Inspection Procedure (Alternate)LM 4299- 4541 NDI Ultrasonic ProcedureVisual Inspection Procedure (Alternate)

Inspection not applicable to LM 4542 up and Aircraft with MEP Type Replacement Outer Wings

6,000 T6,000 T11,300 11,300 

6-24 Change 1 - 10 September 2007 

Use and/or disclosure is governed by statement on the title page of this document. 
SECTION 6 

STRUCTURAL INSPECTION REQUIREMENTS 

 INSPE

SB/CARD

NUMBER

REVISION

DATE

PSE

NUMBER TITLE INITIAL 

A P 

SP-195 (See SP61) 

1-Jan-92 57-50-12 NDI Outer Wing Exterior Lower Surface King Pin Riser - External 

Surface Eddy Current Procedure LM 3501 - LM 4298 with SB 382-57-43 IncorporatedLM 4299 - LM 4541 LM 4542 and Aircraft With MEP Type Replacement Outer Wings 

6,000 T7,800 T20,000 

G 

P 

SP-196 (See SP62) 

1-Dec-86 57-50-06

57-50-12 

NDI Outer Wing Lower Surface Panel Number 1 at OWS 54 and 108 With SB 382-187 Dwg. 3312391 (Doublers and Strap Installation onAft Portion of Wing) LM 3501 - LM 4541

Inspection not applicable to LM 4542 up and Aircraft with MEP Type Replacement Outer Wings

6,000 T

G 

P 

SP-197 (See SP62) 

1-Dec-86 57-50-06

57-50-07 57-50-12 

NDI Lockheed Modified Outer Wing Lower Surface Panel Number 1 Front Beam Lower Cap Forward Flange and Rear Beam Lower Cap Aft Flange at OWS 54 and 108 With SB 382-187 Dwg. 3312416 (Stiffener Replacement on Forward Portion of Wing) LM 3501 - LM4541 

Inspection not applicable to LM 4542 up and Aircraft with MEP Type Replacement Outer Wings

6,000 T

G 

P 

SP-198 1-Dec-86 57-50-06 NDI NWI Modified Outer Wing Front Beam Lower Cap Aft Flange

and Angle Stiffener at OWS 38 and 123 With NWI Dwg. 3609057 (Angle Installation on Forward Portion of Wing) LM 3501 - LM 4541

Inspection not applicable to LM 4542 up and Aircraft with MEP Type Replacement Outer Wings

6,000 T

D 

P 

SP-199 (See SP61) 

1-Jan-92 57-50-12 NDI Outer Wing Lower Surface Skin Panels at King Pin Riser OWS 

35 - Internal Surface Eddy Current Procedure LM 4542 - up and Aircraft With MEP Type Replacement Outer Wings

20,000 

Change 1 - 

Use and/or disclosure is governed by statement on the title page of this document. 
SECTION 6 

STRUCTURAL INSPECTION REQUIREMENTS 

 INSPE

SB/CARD

NUMBER

REVISION

DATE

PSE

NUMBER TITLE INITIAL 

G SP-202

(See SP124) 

1-Aug-86 57-50-12 NDI Outer Wing Lower Surface Panels Around Fastener Holes at 

Heat Shields and Aft Nacelle Fairings OWS 161 to 195 (If Cracking is Found By SP-124) 

Inspection not applicable After Incorporation of SB 382-152 and SB382-57-73 or NWI Dwg 3609103

See SP

A P 

SP-203 1-Jun-94 57-50-07 NDI Outer Wing Lower Aft Beam Cap at Panel Number 4 - OWS 144

to 214 LM 3501 - LM 4298 LM 4299 - LM 4541 Incorporation of SB A382-57-65 Meets Intent of Initial InspectionLM 4542 up and Aircraft With Replacement MEP Outer Wings 

5,500 T8,000 T35,000 

D 

P 

SP-204 1-Dec-86 57-50-07

57-50-12 

NDI Outer Wing Panel Number 4 and Lower Aft Beam Cap with SB382-187 (Dwg. 3312391) (Doublers and Strap Installation on Aft Portion of Wing) LM 3609 - 4541 NOTE: Combination of SP-204, SP-205, and SP-206 may be required dependent upon modified configuration. Incorporation of SB A382-57-65 Meets Intent of Initial Inspection

Inspection not applicable to LM 4542 up and Aircraft with MEP Type Replacement Outer Wings

8,700 T

D 

P 

SP-205 1-Dec-86 57-50-07

57-50-12 

NDI Outer Wing Panel Number 4 and Lower Aft Beam Cap With SB 382-187 Dwg. 3312419 (Stiffener Replacement on Aft Portion of Wing) LM 3609 - 4541 NOTE: Combination of SP-204, SP-205 and SP-206 may be required dependent upon modified configuration. Incorporation of SB A382-57-65 Meets Intent of Initial Inspection

Inspection not applicable to LM 4542 up and Aircraft with MEP Type Replacement Outer Wings

8,700 T

6-26 Change 1 - 10 September 2007 

Use and/or disclosure is governed by statement on the title page of this document. 
SECTION 6 

STRUCTURAL INSPECTION REQUIREMENTS 

 INSPE

SB/CARD

NUMBER

REVISION

DATE

PSE

NUMBER TITLE INITIAL 

D 

P 

SP-206 1-Dec-86 57-50-07 NDI Outer Wing Panel Number 4 and Lower Aft Beam Cap with NWI 

Dwg. 3609051 (Angle Installation on Aft Portion of Wing) LM 3609-4541 NOTE: Combination of SP-204, SP-205 and SP-206 may be required dependent upon modified configuration. Incorporation of SB A382-57-65 Meets Intent of Initial Inspection

Inspection not applicable to LM 4542 up and Aircraft with MEP Type Replacement Outer Wings

8,700 T

G 

P 

SP-207 1-Dec-86 57-50-06 NDI Outer Wing Lower Forward Beam Cap, Web and Panel at 

Inboard and Outboard Ends of Straps Incorporated per LockheedSBs: A382-169 Kit A (Aluminum Straps) Dwg. 3312301 (Equivalent to ECP 954) Dwg. 3304406 A382-169 Kit B (Steel Straps) Dwg. 3312308 Incorporation of SB A382-57-65 Meets the Intent of the Initial Inspection 

Inspection not applicable to LM 4542 up and Aircraft with MEP Type Replacement Outer Wings

3,400 T3,400 T

G SP-209 1-Jan-88 57-50-12 NDI Outer Wing Lower Surface Panel Repairs OWS 0 to OWS 360 

LM 3501 - LM 4541 No further inspection following Incorporation of SB 382-57-70 

Inspection not applicable to LM 4542 up and Aircraft with MEP Type Replacement Outer Wings

Special Conditio

G 

D 

SP-215 1-Dec-89 57-50-12 NDI Outer Wing Lower Surface Repairs Modified By SB 382-57-70 or 

SK 382-57-110, OWS 0 to OWS 360 

Special Conditio

A P 

SP-216 1-Dec-04 57-30-07 NDI Center Wing Lower Surface Skin Panels at Cutout Corners, 

CWS 216 

15,000 

Change 1 - 

Use and/or disclosure is governed by statement on the title page of this document. 
SECTION 6 

STRUCTURAL INSPECTION REQUIREMENTS 

 INSPE

SB/CARD

NUMBER

REVISION

DATE

PSE

NUMBER TITLE INITIAL 

A P 

SP-217 1-Dec-04 57-30-07 NDI Center Wing Lower Surface Panel at the Wing Joint (Rainbow) 

Fitting at CWS 214 

15,000 

A 

D 

P 

SP-218 1-Jan-92 57-30-18 NDI Center Wing Lower Surface Wing Joint (Rainbow) Fitting 

Reinforcing Angles CWS 214 

Inspection not applicable to Aircraft With Flat Plate Doublers Over All horizontal Legs of Reinforcing Angles

15,000 

A 

D 

SP-219 1-Jan-92 57-50-17 NDI External Tank Pylon, Front and Rear Beam Fittings P/N 388090-

1/388090-3 (Aircraft through LM 4983) Incorporation of SB 382-57-54 Accomplishes the Intent of the Initial Inspection 

Inspection not applicable to LM 4984 up and Aircraft Through LM 4983 with P/N 3326727-5/7 or Later Beam Fittings Installed

6 Years 

A P 

SP-222 1-Apr-93 57-30-01 Center Wing Front Beam Lower Cap at WS 174 to WS 210 15,000 

A P 

SP-253 1-Jan-93 57-30-07 NDI CW Lower Surface Spanwise Splice at WS 185.5 20,000 

A P 

SP-254 1-Jan-93 57-30-01

57-30-07 

NDI CW Lower Surface Panel No. 1at Engine Drag Fitting, WS 178 & WS 213 NDI X-Ray Procedure. 20,000 

A P 

SP-255 1-Jan-93 57-30-07 NDI CW Lower Surface Panel No. 1 at Corner Fitting, WS 214 15,000 

A P 

SP-257 1-Dec-04 57-30-18 NDI Center Wing Lower Surface Rainbow Fitting, WS 220 15,000 

A P 

SP-258 1-May-93 57-30-03 NDI Center Wing Upper Surface Front Beam Cap Vertical Flange,

WS 97 

30,000 

6-28 Change 1 - 10 September 2007 

Use and/or disclosure is governed by statement on the title page of this document. 
SECTION 6 

STRUCTURAL INSPECTION REQUIREMENTS 

 INSPE

SB/CARD

NUMBER

REVISION

DATE

PSE

NUMBER TITLE INITIAL 

G 

P 

SP-259 1-Jul-99 57-50-12 NDI Outer Wing Lower Surface Typical Rib/Riser Attachment, OWS 

36, 54, 108, 126 and 249 LM 3501- 4298, 4304, 4306-4313 LM 4299-4303, 4305, 4314-4541 

Inspection not applicable to LM 4542 up and Aircraft with MEP Type Replacement Outer Wings

18,000 32,000 

G 

P 

SP-260 1-Jul-99 57-50-12 NDI Outer Wing Lower Surface Skin Panel No. 4 at the Fuel Boost 

Pump Attachment LM 3501-4298, 4304, 4306-4313 LM 4299-4303, 4305, 4314-4541 

Inspection not applicable to Aircraft with MEP Type Replacement Outer Wings and LM 4542 up

4,500 T18,000 

G SP-261 1-Apr-93 57-50-13 NDI Outer Wing Upper Surface Dry Bay Access Door Cutout, OWS

180 LM 3501-4541 Inspection not applicable to LM 4542 up and Aircraft with MEP Type 

Replacement Outer Wings

31,000 

D SP-265 1-Jun-94 57-50-12 NDI of Outer Wing Lower Surface Skin Panel Riser Number 18 at 

Termination of Kingpin Riser - OWS 35 Incorporation of SB 382-57-74 Establishes the Initial and Recurring Inspection Interval Based on the Measured Distance Between Center of Outermost fastener on Kingpin Riser and Edge of Riser. Measure Distance(inches)Between Center of Outermost Fastener on Kingpin Riser and Edge of Riser (Ref SB 382-57-74). Results Obtained Determines Initial and Recurring Inspection Intervals asListed in Table 1. 

Change 1 - 

Use and/or disclosure is governed by statement on the title page of this document. 
SECTION 6 

STRUCTURAL INSPECTION REQUIREMENTS 

 INSPE

SB/CARD

NUMBER

REVISION

DATE

PSE

NUMBER TITLE INITIAL 

SP-265

(Cont’d) 

LM 4992 - 5320 (FAA Certified Aircraft) 

LM 4301, 3946 - 4960 (FAA Certified Aircraft) With Replacement Outer Wings-MEP 1T/2T,MEP 12R/13R or MEP 9T/10T 

Table 1 Table 1 

TABLE 1 

GROUP A AIRCRAFT 

Measurement* 

(Inch)

Initial Inspection 

Flight Hours** 

Flight Hours 

between 

Reinspection

Less than 0.190 18,000 7,400 

0.190 to 0.230 20,000 7,400 

0.231 to .309 22,000 7,400 

D SP-268

(See SP-85) 

1-Mar-94 57-50-19 NDI Number 1 and Number 4 Engine Truss Mount Lugs 

NOTE: Perform the Inspections Outlined on this workcard in conjunction with SP-85 whenever both inspections are required. Incorporation of SB 382-71-20 Meets Intent of Initial Inspection

LM 4561 - LM 5225 (FAA Certified Aircraft) 

LM 3946 - LM 4512 (FAA Certified Aircraft) With Replacement Outer Wings - MEP 12R/13R or MEP 9T/10TInspection not applicable to LM 4542 - LM 5256 With P/N 360013-31 

or Later and P/N 360017-31 or Later Truss Mounts

Inspection not applicable to MEP Replacement Outer Wings With 

P/N 360013-31 or Later and P/N 360017-31 or Later Truss Mount Lugs and LM 5257 and Up

15,000 15,000 

A SP-310 1-Oct-01 57-30-08 NDI Center Wing Upper Surface Wing Panel Number 1, 2, and 3 at 

CWS 214 – 220 L/R 

15,000 

A SP-312 1-Oct-01 57-30-06 Visual Inspection of Center Wing Front Beam Web 15,000 A P 

SP-313 1-Oct-01 57-30-04 NDI Center Wing Aft Upper Beam Cap CWS 20 and CWS 61 L/R 34,000 

6-30 Change 1 - 10 September 2007 

Use and/or disclosure is governed by statement on the title page of this document. 
SECTION 6 

STRUCTURAL INSPECTION REQUIREMENTS 

 INSPE

SB/CARD

NUMBER

REVISION

DATE

PSE

NUMBER TITLE INITIAL 

A P 

SP-314 1-Aug-02 57-30-07 NDI Center Wing Lower Surface Wing Panels Number 1, 2 and 3 at 

Drain Holes CWS 56 and 174 and at Fastener Holes CWS 62 – 68 L/R 

25,000 

A SP-315 1-Oct-01 57-50-03 NDI Outer Wing Joint Attach Bolts and Barrel Nuts 12 Year

D SP-316 1-Oct-01 57-50-11

57-50-17 

NDI Outer Wing Forward Beam Web OWS 72 and OWS 90, Forward/Aft Pylon Attach Fittings and Pylon Attach Bolts and Barrel NutsLM 4542 up and Aircraft with MEP Replacement Outer Wings. Note: Perform SP-123 Inspection of the beam cap in the event web 

cracks are found. 

12,200 

A SP-317 1-Oct-01 57-50-16 NDI Outer Wing Flap Track Stiffener Lower Ends and Braces OW

Flap Station 28, 100, 173, 241 and 303 L/R 

12 Year

A SP-318 1-Oct-01 57-50-07

57-50-10 

NDI Outer Wing Rear Beam Lower Cap and Web at Flap Track Fitting OWS 293 L/R 

15,500 

CHAPTER 71 - POWER PLANT

A SP-80 1-Jan-92 71-10-01

71-10-02 

Visual Inspection of QEC Upper and Lower Longerons QEC Serial Number: LM-G 1369-001 and up, LM-G 1869-001 and up, LM-G 2969-001 and up, LM-G 3269-001 and up, LM-G 3769-001 and up, LM-G 4069-001 and up, LM-G 4569-001 thru 004 

3 Years 

Inspection not applicable After SB 382-71-12 Incorporation

Inspection not applicable to QEC Reworked With Longerons P/N 

362501-5, 362501-6, 362502-9 and 362502-10 or Later, or Earlier QEC With P/N 362531-3 Power Plant Mount Assembly Installed orEarlier QEC With P/N 362531-1 Power Plant Mount Assembly S/N 0001 LK and up Installed

Change 1 - 

Use and/or disclosure is governed by statement on the title page of this document. 
SECTION 6 

STRUCTURAL INSPECTION REQUIREMENTS 

 INSPE

SB/CARD

NUMBER

REVISION

DATE

PSE

NUMBER TITLE INITIAL 

SP-80

(Cont’d) 

Inspection not applicable to QEC Serial Number LM-G 4669-001 and 

up or Later QEC Serials

D SP-187 1-Jan-92 71-10-01 NDI QEC Lower Longerons (Certain Serial Numbers) Longeron P/N 

362501-1 thru 362501-6 Incorporation of SB A382-54-7 Meets Intent of Initial Inspection

Inspection Condition And Longeron Condition

Forward Engine Mount Removed - No Crack Forward Engine Mount Removed - Crack Less Than 2.0 inchesForward Engine Mount Installed - No Crack Forward Engine Mount Installed - Crack Less Than 2.0 inchesForward Engine Mount Removed - Crack 2.0 Inches or Installed - but less than 2.5 inches Forward Engine Mount Removed - Crack 2.5 Inches or Installed - but less than 3.0 inches 

3 Years 3 Years 3 Years 3 Years 3 Years 3 Years 

Crack 3.0 Inches or Longer - Replace Longeron 

Crack Dimension is measured aft from forward face of mounting flange of Longeron

Inspection not applicable to QEC Serial Number LM-G-3569-013 and 

up, LM-G-4469-129 and up, LM-G-4569-045 and up, LM-G-4869-053 and up, and All Subsequent LM-G Numbers, or QEC With LongeronP/N 362501-7/-8 or Later, or Earlier QEC With P/N 362531-3 Power Plant Mount Assembly Installed or Earlier QEC With P/N 362531-1 Power Plant Mount Assembly S/N 0001 LK and up Installed

D SP-189 1-Jun-94 71-10-02

71-10-03 

NDI QEC Upper Longerons and Support Fittings at Aft Engine Mount Beam (Certain Serial Numbers) Upper Sloping Longeron - P/N 362502-1 through -12 Support Fitting - P/N 363801-1 through -4 Outside Skins - All Incorporation of SB 382-54-9 Meets Intent of Initial Inspection 

2 Years 

6-32 Change 1 - 10 September 2007 

Use and/or disclosure is governed by statement on the title page of this document. 
SECTION 6 

STRUCTURAL INSPECTION REQUIREMENTS 

Change 1 - 

Use and/or disclosure is governed by statement on the title page of this document. 

 INSPE

SB/CARD 

NUMBER

REVISION

DATE

PSE

NUMBER TITLE INITIAL 

SP-189

(Cont’d) 

Inspection not applicable to Upper Longeron QEC Serial Number 

LM-G-3569-013 and up, LM-G-4469-125 and up, LM-G-4569-045 and up, LM-G-4869-053 and up, LM-G-4969-001 and up, and All Subsequent LM-G Numbers or QEC With Longeron P/N 362502-13/-14 or Earlier, QEC With P/N 362531-3 Power Plant Mount Assembly Installed or Earlier QEC With P/N 362531-1 Power Plant Mount Assembly S/N 0001 LK and up Installed

Inspection not applicable to Support Fitting QEC Serial Number LMG-5669-005 and up, LM-G-5769-001 and up, LM-G-5869-013 and 

up, LM-G-5969-049 and up, LM-G-6069-025 and up, LM-G-6169-001 and up, and All Subsequent LM-G Numbers, or QEC With P/N 3331795-1, through -4 or Earlier QEC With, P/N 362531-3 Power Plant Mount, Assembly Installed or Earlier, QEC With P/N 362531-1 Power, Plant Mount Assembly S/N 0001 LK and up Installed

A SP-190 1-Jun-94 71-10-03 NDI QEC Aft Engine Mount Fastener Holes on P/N 363803 Steel 

Beam at each Aft Lord Mount Change Inspection not applicable to QEC Serial Number LM-G-5669-005 and 

up, LM-G-5769-001 and up, LM-G-5869-013 and up, LM-G-6069-025 and up, or QEC with P/N 3331871-1 or Later Steel Beam, or QEC With P/N 362531-3 Power Plant Mount Assembly or Earlier QEC With P/N 362531-1 Power Plant Mount Assembly S/N 0001 LK and up Installed

Aft Lord Change 
SMP 515-C-SSID 

SECTION 6 

STRUCTURAL INSPECTION REQUIREMENTS 

This Page Intentionally Blank 

6-34 

Change 1 - 10 September 2007 Use and/or disclosure is governed by statement on the title page of this document. 
SMP 515-C-SSID 

SECTION 7 

DISCREPANCY REPORTING 

7.0 DISCREPANCY REPORTING 

7.1 Fatigue and Corrosion Damage Reporting 

Fatigue cracking, significant corrosion and/or stress corrosion cracking affecting any of the PSEs

identified in Section 4 is to be reported to LM Aero within 10 working days of detecting the 

damage. The report shall contain the following information: 

• LM Aircraft Serial Number 

• Operator Registration Number 

• Aircraft Flight Hours and Cycles 

• Major Component Flight Hours and Cycles (if different from aircraft) 

• PSE Number and Description from Section 4 of this document 

• Inspection Zone Number (From Section 8) 

• Part Number or Description of Structural Item

• Location and of damage (WS, FS, WL) 

• Length of damage (i.e. crack length) and orientation (i.e. spanwise, chordwise) 

• How damage was found (Inspection Procedure reference and Procedure Number or 

description)

Provide the report to a LM Aero field service representative or to LM Aero directly via email to 

hercules.support@lmco.com with an email title of SMP 515-C-SSID Inspection Findings. 

Alternatively, mail the information to: 

Lockheed Martin Aeronautics Company 

86 South Cobb Drive 

Department 3E1M, Zone 0591 

Marietta, GA 30063-0591, USA 

7-1 

Change 1 - 10 September 2007 Use and/or disclosure is governed by statement on the title page of this document. 
SMP 515-C-SSID 

SECTION 7 

DISCREPANCY REPORTING 

7.2 Reporting of Significant Repairs 

Detection of significant structural repairs to PSEs should also be reported to LM Aero to the 

above address. This information will be used to determine if additional inspection requirements 

are necessary to adequately address the inspection of the PSE. Future revisions to this SMP will

include incorporation of PSE inspection requirements for repairs, alterations and modifications. 

7-2 

Change 1 - 10 September 2007 Use and/or disclosure is governed by statement on the title page of this document. 
SMP 515-C-SSID 

SECTION 8 

INSPECTION ZONE DESCRIPTION 

Zone No. AREA

100 LOWER FUSELAGE: Interior and exterior below flight deck floor and below cargo 

floor, forward of ramp hinge bulkhead. 

110 Nose to FS 93: Includes area forward of canted bulkhead, radome and 

equipment. 

120 FS 93 to FS 245 (382B), FS 93 to FS 245E (382, 382 E/F, 382 G/T): Includes 

area and equipment below flight deck floor. 

121 Battery compartment.

130 FS 245 to FS 737 (382B), FS 245E to FS 777E (382, 382 E/F), 

FS 245E to FS 817E (382 G/T): Includes area under cargo floor aft to ramp hinge 

bulkhead. 

200 UPPER FUSELAGE: Interior and exterior above flight deck floor and above cargo 

floor, aft to FS 1041 bulkhead. 

210 FS 93 to FS 245 (382B), FS 93 to FS 245E (382, 382 E/F, 382 G/T): Includes 

area aft of canted bulkhead and above flight deck floor. 

220 FS 245 to FS 477 (382B) FS 245E to FS 477 (382, 382 E/F, 382 G/T): Above 

cargo floor. 

230 FS 477 to FS 617: Above cargo floor including equipment mounted on front and 

rear center wing beams. 

231 Left Wing Fillet Area: Includes area under leading edge fillet, under wing and 

trailing edge fillets, and upper wheel well. 

232 Right Wing Fillet Area: Includes area under leading edge fillet, under wing and 

trailing edge fillets, and upper wheel well. 

233 GTC/APU Compartment.

234 Cargo Air Conditioner Compartment. 

235 Left Aft Main Landing Gear Fairing: Includes air deflector door, where installed, 

and equipment behind it. 

236 Right Aft Main Landing Gear Fairing: Includes SPR Panel, air deflector door, 

where installed, and equipment behind it. 

240 FS 617 to FS 737 (382B), FS 617 to FS 777E (382, 382 E/F), FS 617 to FS 817E 

(382 G/T): Above cargo floor. 

250 FS 737 to FS 1041 (382B), FS 777 to FS 1041 (382, 382 E/F), 

FS 817E to FS 1041 (382 G/T): Above ramp and cargo doors. 

251 Left Aft Fuselage: Includes area above ramp and cargo doors outboard of LBL 

61.625. 

252 Right Aft Fuselage: Includes area above ramp and cargo doors outboard of RBL 

61.625. 

253 Center Aft Fuselage: Includes area above ramp and cargo doors. 

8-1 

Change 1 - 10 September 2007 Use and/or disclosure is governed by statement on the title page of this document. 
SMP 515-C-SSID 

SECTION 8 

INSPECTION ZONE DESCRIPTION 

Zone No. AREA

260 Wing Root Fillets, includes removable fillets.

261 Left Forward Wing Fillet.

262 Right Forward Wing Fillet. 

263 Left Under Wing Fillet. 

264 Right Under Wing Fillet.

265 Left Aft Wing Fillet. 

266 Right Aft Wing Fillet. 

270 Fuselage Fuel Tank (Aerial Refueling) (Not shown). 

300 EMPENNAGE: Horizontal Stabilizer, including tail cone and elevators and vertical 

fin, dorsal fin and rudder. 

310 Dorsal Fin, FS 759 to FS 946 above the fuselage. 

320 Vertical Stabilizer: FS 946 aft to tip of rudder above Horizontal Stabilizer. 

321 Vertical Stabilizer Leading Edge. 

322 Vertical Stabilizer Main Structure: Includes tip. 

323 Rudder: Includes trim tab. 

324 HF antenna and access (where installed). 

325 VOR antenna and access (where installed). 

330 Horizontal fin: FS 1041 to FS 1138. 

331 Left Horizontal Stabilizer Leading Edge. 

332 Right Horizontal Stabilizer Leading Edge. 

333 Horizontal Stabilizer Box Beam, Front spar to rear spar and aft to 

FS 1138, Includes Tips.

334 Strakes (where installed). 

335 Left Elevator.

336 Right Elevator.

340 Tail Cone: FS 1138 to FS 1202.1. 

400 POWER PLANTS: Includes propeller and QEC forward of vertical firewall, turbine 

and tailpipe.

410 Number 1 Power Plant. 

411 Number 1 Propeller. 

412 Number 1 Quick Engine Change (QEC) Unit. 

413 Number 1 Aft Nacelle: Includes area aft of vertical firewall, below horizontal 

firewall and aft nacelle fairing on wing. 

420 Number 2 Power Plant. 

8-2 

Change 1 - 10 September 2007 Use and/or disclosure is governed by statement on the title page of this document. 
SMP 515-C-SSID 

SECTION 8 

INSPECTION ZONE DESCRIPTION 

Zone No. AREA

421 Number 2 Propeller. 

422 Number 2 Quick Engine Change (QEC) Unit. 

423 Number 2 Aft Nacelle: Includes area aft of vertical firewall, below horizontal 

firewall and aft nacelle fairing on wing. 

430 Number 3 Power Plant. 

431 Number 3 Propeller. 

432 Number 3 Quick Engine Change (QEC) Unit. 

433 Number 3 Aft Nacelle: Includes area aft of vertical firewall, below horizontal 

firewall and aft nacelle fairing on wing. 

440 Number 4 Power Plant. 

441 Number 4 Propeller. 

442 Number 4 Quick Engine Change (QEC) Unit. 

443 Number 4 Aft Nacelle: Includes area aft of vertical firewall, below 

horizontal firewall and aft nacelle fairing on wing.

500 LEFT WING: Includes outer wing, center wing interior and exterior, flaps, aileron, 

pylons, and external tank. 

510 Left Center Wing: CWS 0 to CWS 220. 

511 Left Center Wing Leading Edge. 

512 Number 2 “Horse Collar”: Front beam to vertical firewall, above horizontal firewall 

and CWS 178 to CWS 220. 

513 Left Center Section Dry Bay: Front beam to rear beam, CWS 0 to 

CWS 108. 

514 Left Auxiliary Fuel Cell: Front beam to rear beam, CWS 108 to CWS 

178. 

515 Number 2 Dry Bay: Front beam to rear beam, CWS 178 to CWS 220. 

516 Left Center Wing Trailing: Rear beam to trailing edge, CWS 84.3 to CWS 220. 

517 Left Center Wing Flap. 

520 Left Outer Wing Leading Edge: To front beam, OWS 0 to wing tip (OWS 562.5). 

521 Left Outer Wing Leading Edge: To front beam, OWS 0 to OWS 144.5. 

522 Number 1 "Horsecollar": Front beam to vertical firewall above horizontal firewall, 

OWS 144.5 to OWS 214.2. 

523 Left Outer Wing Leading Edge: To front beam, OWS 214.2 to wing tip (OWS 

562.5). 

530 Left Outer Wing Box Beam: Front beam to rear beam, OWS 0 to tip (OWS 562.5). 

531 Number 2 Main Fuel Tank: Front to rear beam, OWS 0 to OWS 144.5. 

532 Number 1 Dry Bay: Front to rear beam, OWS 144.5 to OWS 214.2. 

8-3 

Change 1 - 10 September 2007 Use and/or disclosure is governed by statement on the title page of this document. 
SMP 515-C-SSID 

SECTION 8 

INSPECTION ZONE DESCRIPTION 

Zone No. AREA

533 Number 1 Main Fuel Tank: Front to rear beam, OWS 214.2 to tip 

(OWS 562.5). 

534 Left Wing Tip. 

540 Outer Wing Trailing Edge: Rear beam to trailing edge, OWS 0. to tip (OWS 

563.0). 

541 Left Outer Wing Trailing Edge: Rear beam to trailing edge, Outer Wing Flap 

Station 0 to Aileron Station 0. 

542 Left Outer Wing Trailing Edge: Rear beam to trailing edge, Aileron Station 0 to 

OWS 563.0.

543 Left Outer Wing Flap. 

544 Left Aileron.

550 Left Pylon Tank: Includes pylon (where installed). 

560 Left Refueling Pod: Includes pylon (where installed). 

600 RIGHT WING: Includes outer wing, center wing inside fuselage, flaps, aileron, 

pylons external tank. 

610 Right Center Wing: CWS 0 to CWS 220. 

611 Right Center Wing Leading Edge. 

612 Number 3 “Horsecollar”: Front beam to vertical firewall above horizontal firewall 

and CWS 178 to CWS 220. 

613 Right Center Section Dry Bay: Front beam to rear beam, CWS 0 to CWS 108. 

614 Right Auxiliary Fuel Cell: Front beam to rear beam, CWS 108 to 

CWS 178. 

615 Number 3 Dry Bay: Front beam to rear beam, CWS 178 to CWS 220 (CWS.0). 

616 Right Center Wing Trailing Edge: Rear beam to trailing edge, 

CWS 84.3 to CWS 220. 

617 Right Center Wing Flap.

620 Right Outer Wing Leading Edge: To front beam, OWS 0 to Wing tip (OWS 562.5). 

621 Right Outer Wing Leading Edge: To front beam, OWS 0 to OWS 144.5. 

622 Number 4 “Horsecollar”: Front beam to vertical firewall above horizontal firewall, 

OWS 144.5 to OWS 214.2. 

623 Right Outer Wing Leading Edge: To front beam, OWS 214.2 to wing tip (OWS 

562.5). 

630 Right Outer Wing Box Beam: Front beam to rear beam, OWS 0 to tip (OWS 

562.5). 

631 Number 3 Main Fuel Tank: Front to rear beam, OWS to CWS 144.5. 

632 Number 4 Dry Bay: Front to rear beam, OWS 144.5 to OWS 214.2. 

8-4 

Change 1 - 10 September 2007 Use and/or disclosure is governed by statement on the title page of this document. 
SMP 515-C-SSID 

SECTION 8 

INSPECTION ZONE DESCRIPTION 

Zone No. AREA

633 Number 4 Main Fuel Tank: Front to rear beam, OWS 214.2 to tip 

(OWS 562.5). 634 Right Wing Tip. 

634 Right Wing Tip. 

640 Right Outer Wing Trailing Edge: Rear beam to trailing edge, OWS 0. to tip (OWS 

563.0). 

641 Right Outer Wing Trailing Edge: Rear beam to trailing edge, Outer Wing Flap 

Station 0 to Aileron Station 0. 

642 Right Outer Wing Trailing Edge: Rear beam to trailing edge, Aileron Station 0 to 

OWS 563.0.

643 Right Outer Wing Flap. 

644 Right Aileron.

650 Right Pylon Tank: Includes pylon (where installed). 

660 Right Refueling Pod: Includes pylon (where installed). 

700 LANDING GEAR AND LANDING GEAR DOORS: Includes nose and main 

landing gear wheels, nose and main landing gear, and nose and main landing 

gear doors.

710 Nose Landing Gear and Doors. 

711 Nose Landing Gear Assembly: Includes actuator, struts, wheels and tires. 

712 Forward Nose Landing Gear Door. 

713 Aft Nose Landing Gear Door. 

714 Nose Landing Gear Wheel Well Compartment.

720 Left MLG and Doors. 

721 Left Forward MLG Assembly: Includes strut, wheel, brake and tire. 

722 Left Aft MLG Assembly: Includes strut, wheel, brake and tire. 

723 Left Torque Strut. 

724 Left Outboard MLG Door. 

725 Left Inboard MLG Door. 

726 Left MLG Wheel Well Compartment: Includes actuator screws, motor, gear box 

and ATM where installed. 

730 Right MLG and Doors. 

731 Right Forward MLG Assembly: Includes strut, wheel, brake and tire. 

732 Right Aft MLG Assembly: Includes strut, wheel, brake and tire. 

733 Right Torque Strut. 

734 Right Outboard MLG Door. 

735 Right Inboard MLG Door. 

8-5 

Change 1 - 10 September 2007 Use and/or disclosure is governed by statement on the title page of this document. 
SMP 515-C-SSID 

SECTION 8 

INSPECTION ZONE DESCRIPTION 

Zone No. AREA

736 Right MLG Wheel Well Compartment: Includes actuator screws, motor, and 

gearbox. 

800 DOORS: Includes crew entry door, aft entry doors, ramp and cargo doors and 

emergency exits. 

810 Crew Entry Door.

820 Left Aft Entry Door (where installed).

830 Right Aft Entry Door (where installed). 

831 Emergency exits (Left side fuselage). 

831 Emergency exit flight station top. 

831 Emergency exit aft fuselage top. 

840 Ramp.

841 Emergency exits (Right side fuselage). 

841 Emergency exit center fuselage top.

850 Cargo Door.

8-6 

Change 1 - 10 September 2007 Use and/or disclosure is governed by statement on the title page of this document. 
SMP 515-C-SSID 

SECTION 8 

INSPECTION ZONE DESCRIPTION 

(Sheet 1 of 12) 

8-7 

Change 1 - 10 September 2007 Use and/or disclosure is governed by statement on the title page of this document. 
SMP 515-C-SSID 

SECTION 8 

INSPECTION ZONE DESCRIPTION 

 (Sheet 2 of 12) 

8-8 

Change 1 - 10 September 2007 Use and/or disclosure is governed by statement on the title page of this document. 
SMP 515-C-SSID 

SECTION 8 

INSPECTION ZONE DESCRIPTION 

(Sheet 3 of 12) 

8-9 

Change 1 - 10 September 2007 Use and/or disclosure is governed by statement on the title page of this document. 
SMP 515-C-SSID 

SECTION 8 

INSPECTION ZONE DESCRIPTION 

(Sheet 4 of 12) 

8-10 

Change 1 - 10 September 2007 Use and/or disclosure is governed by statement on the title page of this document. 
SMP 515-C-SSID 

SECTION 8 

INSPECTION ZONE DESCRIPTION 

(Sheet 5 of 12) 

8-11 

Change 1 - 10 September 2007 Use and/or disclosure is governed by statement on the title page of this document. 
SMP 515-C-SSID 

SECTION 8 

INSPECTION ZONE DESCRIPTION 

(Sheet 6 of 12) 

8-12 

Change 1 - 10 September 2007 Use and/or disclosure is governed by statement on the title page of this document. 
SMP 515-C-SSID 

SECTION 8 

INSPECTION ZONE DESCRIPTION 

(Sheet 7 of 12) 

8-13 

Change 1 - 10 September 2007 Use and/or disclosure is governed by statement on the title page of this document. 
SMP 515-C-SSID 

SECTION 8 

INSPECTION ZONE DESCRIPTION 

(Sheet 8 of 12) 

8-14 

Change 1 - 10 September 2007 Use and/or disclosure is governed by statement on the title page of this document. 
SMP 515-C-SSID 

SECTION 8 

INSPECTION ZONE DESCRIPTION 

(Sheet 9 of 12) 

8-15 

Change 1 - 10 September 2007 Use and/or disclosure is governed by statement on the title page of this document. 
SMP 515-C-SSID 

SECTION 8 

INSPECTION ZONE DESCRIPTION 

(Sheet 10 of 12) 

8-16 

Change 1 - 10 September 2007 Use and/or disclosure is governed by statement on the title page of this document. 
SMP 515-C-SSID 

SECTION 8 

INSPECTION ZONE DESCRIPTION 

(Sheet 11 of 12) 

8-17 

Change 1 - 10 September 2007 Use and/or disclosure is governed by statement on the title page of this document. 
SMP 515-C-SSID 

SECTION 8 

INSPECTION ZONE DESCRIPTION 

8-18 

Change 1 - 10 September 2007 Use and/or disclosure is governed by statement on the title page of this document. 

(Sheet 12 of 12)