# 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 Inform ation



# L OCKHEED 

# M ARTIN 

# A ERONAUT I

CS 

# C OM PANY

A Division of Lockhee d Marti n C o rpor ation 

# Marietta, Georgia 30063

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# SMP 515-C-SSID

Revisions P age

Date By

Whom Description Page

Revised

Aug 07

- Change 0 - Original Issue.

-

Sep 07 S. F.

Ra m e y Change 1 (Incorporates FAA Comments dated 7

Septem ber 2007) -

Added 382F applicability Title Pag e

Updated Lis t of Acronym s vii th rough viii

Deleted Section 6 - INDEX OF S T R U CTURAL

INSPECTION PROCEDURES Origina l 6-1

through 6-8

Renum b ered 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

Num b ering 6 through 8 1-1, 2-2, 5-6, 7-1

Corrected misspelling and revised m odel

num b ers 3-1

Revised to include revi sion date in list of

supplied data in Section 6.3 Table of PSE

Inspection R e quirem e nts 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

num b ers ending in “XX” 6-3

Deleted ref e rence to Original Sec tio n 6 f o r

applicable revision date of inspection procedure 6-3

Clarified 10% m a xi m u m allowable extension 6-3

Revised Section 6.3 to include:

• Revision Date of Inspection Procedure in

Table of PSE Inspection Requirem e nts and

Interv als

• Total Flight Hours (TFH) f o r initia l

inspection intervals and Flight Hours (FH)

for recurring inte rvals 6-4 through 6-33

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# SMP 515-C-SSID

Date By

Whom Description Page

Revised

Deleted ref e rence to Milita ry 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

m i sspellings v

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# SMP 515-C-SSID

Table of Contents

Section Item Page

TITLE PAGE

------------------------------------------------------------------------------------ i

REVISION S PAGE

--------------------------------------------------------------------------- iii

TABLE OF C ONTENTS --------------------------------------------------------------------- v

LIST OF A CRONYMS

----------------------------------------------------------------------- vii

REFERE NCES ---------------------------------------------------------------------------------ix

1.0 PURPOS E ------------------------------------------------------------------------------------ 1-1

2.0 INTRODUC TION --------------------------------------------------------------------------- 2-1

3.0 AFFECTED AI RCRAFT

-------------------------------------------------------------------- 3-1

4.0 PRINCIPLE STRUCT URAL ELEM EN TS

---------------------------------------------- 4-1

4.1 CHAPTER 53 – FUSELAGE

--------------------------------------------------------- 4-2

4.2 CHAPTER 55 – EMPENN AGE

------------------------------------------------------ 4-4

4.3 CHAPTER 57 – W I NGS

--------------------------------------------------------------- 4-5

4.4 CHAPTER 71 – POWER PL ANT

---------------------------------------------------- 4-6

5.0 DAMAGE TOLERANCE ANAL YSIS METHODOLOGY

--------------------------- 5-1

5.1 SAFETY LIMIT

------------------------------------------------------------------------- 5-1

5.2 INITIAL FL AW CRITER IA

---------------------------------------------------------- 5-2

5.3 INSPECTION CRITERIA

------------------------------------------------------------- 5-6

6.0 STRUCTURAL INSPEC TION REQUIREME NTS

------------------------------------- 6-1

6.1 APPLI C AB ILITY C ODE

-------------------------------------------------------------- 6-1

6.2 INSPE CTION INT E RVALS AND OPERATIONAL USAGE SEVERITY

--- 6-2

6.3 PSE INSPECTION REQUIRE MENTS AND IN TERVALS

--------------------- 6-3

7.0 DISCREPANCY REPORTIN G

------------------------------------------------------------ 7-1

7.1 FATIGUE AND CORROS ION DAMAGE REPO RTING

------------------------ 7-1

7.2 REPORTING OF SI GNI FICANT REPAIRS

--------------------------------------- 7-2

8.0 INSPECTION ZONE DESCRIPTIO N

---------------------------------------------------- 8-1

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# SMP 515-C-SSID

List of Acronym s

AASR Aging Aircraft Safety Rule

AD Airworthine ss Direc tive

a Crack Length

ASIP Aircraft Stru ctur al Integrity Program

ATA Air Transpo r t Associatio n

BL Butt Line

CAR Civil Airwo r thin ess Reg u lations

DAH Design Approval Holder

DT Da m a ge Tolerance

DTA Da m a ge Tolerance Assessm ent/Analysis

Dwg Drawing

FAA Federal Aviation Adm i nistration

FEM Finite E l ement Mode l

FH Flight Hours

FS Fuselage Station

HSS Horizontal S t abilizer Station

in. inches

LM Aero Lockheed Martin Aeronautics

MED Multip le Ele m ent Dam a ge

MEP Manufacturing End Product

MLG Main Landing Gear

MSD Multip le Site Dam a ge

NDI Non-Destructive Inspection

OUE Operation a l Usage Evalu a tion

OW S Outer W i ng Station

P/N Part Num b e r

POD Probability of Detection

PSE Princip l e Structural Elem ent

QECU Quick Engine Change Unit

SB, S/B Service Bulletin

SEC Surface Eddy Current

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# SMP 515-C-SSID

List of Acronym s (Cont’d)

SCC Stress Corrosion Cracking

SMP Service Manual Publication

SSI Structu r ally Significant Item

SSID Supplem ental Structur al Inspection Docum e nt

TFH Total Flight Hours

USAF United States Air Force

VSS Vertical Stabilizer Station

WFD W i despread Fatigue Dam a ge

WL Wat e r Li ne

WS W i ng Station

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# SMP 515-C-SSID

References

1. SMP 515-C-MASTER, Hercules Airfreighter In spection Program

, Lockheed Martin Model

282, 382B/C/D/E/F and G Series Aircraft, 1 Decem b er 2004

2. LG82ER0147, “C-130 A/B/E/H Durability an d Da m a ge Tolerance Assessm ent (DADTA):

General Methodology and Basic Data,” Loc kheed-Georgia Company, Septem ber 1981.

3. FAA Aging Airplane Saf e ty, 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 C o rrosion P r evention 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 comm ercial operators of the

L-382 Series aircraft with a Supplem ental Stru ctural Inspection Docum e nt (SSID). The SSID

def i nes the struc t ura l in spection req u irem ents c onsidered to be essen tia l to m a intain continu i ng

airworth iness in accord ance with FAA require m e nts specified in 14 CFR Part 121.370a. In

subsequent revisions to this SSID, additional supplem ental in spection requirem ents m a y be

identified for repairs and m odi fications that ar e contained in the Lockheed Martin 382 Series

Aircraft Structural Repair Manua l and previously issued L o ckh eed Martin 382 Series Aircraft

Service Bulletins.

It is anticip a ted tha t th e FAA will is sue an Airw orthin ess Directive (AD ) in ac corda n ce with the

inspection requirem e nts identi f i ed in this SSID.

Thi s document i d enti fi es Pr i n ci ple St r u ct ur al El em ents (PSE) of the L

- 382 m odel aircraft th at are

susceptible to fatigue cracking, co rrosion and/or stress corrosion cr acking and if not detected and

repaired in a tim ely m a nner could eventually lead to the catastr ophic loss of the aircraft .

The inspec tion procedu r es iden tif ied in this SSI D are drawn from existing procedures developed

by LM Aero for the SMP 515-C Hercules Airfrei ghter Inspection Program (Refer ence 1) and

from Lockheed Martin 382 Series Aircraft Servi ce Bulletins. L-382 oper ators who have had LM

Aero develop a custom ized SMP 515-C-X inspect ion program (“X” denotes the particular

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

Section 6 of this SMP. These in spe c tion proced ures have been develope d, in part, from Da m a ge

Tolerance requirem e nts. Full scale fatigue test and service corrosion and cracking data has been

used to de ter m ine the m a jority of the locat ions that require con tinuing inspections.

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

crack growth analysis o f typical C-130E m ilitary transpo r t usage in the late 1970’s consisting

prim arily of training and logistics (cargo transpo r t) operations . Recent analysis of usage data has

shown that typical comm ercial operations of th e L-382 aircraft are at higher payloads than

m ilitary ope rations with signif i can tly less tim e in p ilot tra i nin g. Analysis and in serv ice crack ing

data has also shown that the crack growth rate severity of typical co mmercial us age is very

sim ilar to th e baseline military u s age, pa rticularly in wing lower surface s t ructure.

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# SMP 515-C-SSID

SECTION 2

INTRODUCTION

2.0 INTRODUCTION

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

part, operators to have a m a intenance program consisting of FAA a pproved dam a ge tolerant

based structural inspection proce dures. These inspections are requ ired f o r the baseline stru cture

and also m u st consider the adverse affects of repairs, alterations and m o difications. Although no

specific requirem ent was identified for a Supplem ental Structural Inspection Docum e nt to be

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

successf ully im plem ented by issu ing an Airwor th iness Directive (AD) against an F AA approved

dam a ge tolerant based inspection program

. Lockheed Martin Aeronautic s (L M Aero) h a s

prepar ed th is SMP in o r der to p r ov ide a sing le docum ent that spe c if ie s the cr itica l structu r a l

inspections required to ensure continued airworthiness.

The prim ary m eans that LM Aero has provide d L-382 operators with structural inspection

requirem e nts is through the SMP 515-C Hercules Ai rfreighter Inspection Program (Reference 1).

This program contains scheduled inspection requir em ents f o r the com p lete airc raf t , in cluding th e

structure. SMP 515-C program s have been de veloped specific to th e custom er aircraft

configuration which includes m odified structur e by Serv ice Bulle tins

. Custom er par ticu l ar

program s are identified with a num e r ic character “X” (SMP 515-C-X).

Where service crack ing data has sho w n that there are additio nal are a s tha t warrant ins p ection that

are no t ad dressed in the m a inten a nce prog ra m, or where currently requirem e nts do not

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

operator requests updates to their SMP 515-C-X inspection program , the inspection requirem e nts

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

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

updates in num e rous years. Ther e m a y also be som e foreign comm ercially certified aircraft that

do not have the SMP 515-C program.

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

in Service Bulle tins ar e in part based on Dam a ge Tolerance Assessm ents. Where the princip a l

m echanism t h at propagates a crack h a s been iden tified as fatigue, crack g r owth analy s is has been

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# SMP 515-C-SSID

SECTION 2

INTRODUCTION

perf orm e d to initially es tablish the inspection in terva l s. In s o m e cases, these in terva l s have been

modified based on test and in service cracki ng data or by risk anal ysis m e thodologies.

The key elem ents of the dam a ge tolerance analysis are:

• Generation of operational stress spectr a for a ll s i gnificant load sources

• Determ ination of fatigue crack geom etric correction factors

• Residual Strength Analysis of cracked stru cture to determ ine critical crack size

• Establishing initial f l aw sizes and continuing dam a ge criteria

• Fatigue crack growth analysis

• Determ ination of detectable and non-detectable crack sizes

• Establishing operational lim its of time between sc he duled inspection

PSEs that are also su sceptible to corrosio n and/or Stre ss Corros i o n Cracking (SCC) are

addressed in this docum ent by a pplicable inspection procedures. The L-382 structure contains

nu m e rous PSEs that are m a nufactured fro m 2 X XX- T6 and 7XXX-T6 t e m p er alloys that have a

known service history of corrosion and SCC. SM P 515-B ( R eference 5) provides operators with

detailed inform ation for preventing and controlli ng corrosion . Inspection interva l s f o r detec ting

corrosion and SCC are based on serv ice experien ce.

This SSID also contain s inspect ion requirem e nts for structure that has been m odified by LM

Aero Service Bulletins. These m o difications include fatig u e preven tative repairs and m a jor

com ponent replacem ents. W h ere the Reference 4 st ructural repairs affect PSE inspections, these

are also identified in Section 6.

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

identif i ed in Section 4. These ADs rela te to LM Aero pre v iously issu ed Servic e Bulletins th at

contain ins p ection s to prim ary structure. Wh ere LM Aero has determ ined that recu rring

inspec tion a r e requ ired, these h a ve been inc l u d ed in Sec t ion 6 along with the a pplicab le

inspection procedure ref e rence. The list of appli cable ADs are contained in Table 2.1 below.

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# SMP 515-C-SSID

SECTION 2

INTRODUCTION

Table 2.1 – L-382 ADs Affecting PSEs

AD Numbe r SB Numbe r SB Title SP Numbe r

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

Truss Mount Tangs N/A

94-26-15 382-57-74 Wing – Insp ection of Kin gpin Riser No. 18 on

Outer Wing Lower Surface SP-265

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

Pressurized Fairing Sup port Structure SP-126

SP-224

8 8

- 1 0

- 0 6 3 8 2

- 5 7

- 7 0 /

A82-608 Wing – Modification and Inspection o f Lower

Surface Panel Riser Repairs SP-209

8 8

- 1 0

- 0 5 A 3 8 2

- 5 7

- 7 1

A82-612 Wing – Insp ection of He at Shield an d Aft

Nacelle Fairing Nut Plate Holes SP-202

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

Beam Caps/ S kin Panels at Termination of

Pylon Reinforcing Stiffe ner SP-76

75-17-04 A82-374 Fuselage – I n spection of Main Frame at FS

517 for Cracks and Insta llation of Pre v ent

Repair N/A

74-12-06 A82-346 Wing – Insp ection of Outer Wing Fro n t 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 im portant to recognize th at the supplem ental structural in spection program defined in this

SMP does not take into account the affects of W i despread Fatigue D a m a ge ( W FD). Fatigue

crack intera ction ef f ects due to Mu ltip le S ite Dam a ge (M SD) and M u ltip le E l ement Dam a ge

(MED) are not m odeled in the st andard dam a ge tolerance analys is procedure. L M Aero has

com p leted a W F D assessm ent of the center wing lower surface stru ctu r e using a p r obabilis tic

risk analysis m e thodology and has issued tw o Service Bulletins to address W F D:

• 382-57-82 Rev 2 - Center W i ng Upper and Lower Rain bow Fitting Inspection for

Cracks and Replacem ent

• 382-57-85 Rev 3 - Center W i ng Lower Surface Generalized C r acking an d

W i despread Fatigue Dam a ge Inspection Requirem e nts

It is an ticip a ted that the FAA will issue sep a ra te ADs against th e abov e two Serv ice Bulletin s.

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SECTION 2

INTRODUCTION

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# SMP 515-C-SSID

SECTION 3

AFFE CTE D AIRCRAFT

3.0 AFFECTED AIRCRAFT

The struc t ur al insp ectio n requirem e nts iden tif ie d in this S M P are in te nded f o r all commercially

certified 38 2, 382B/E/F and G s e ries aircraft. D u e to sim ilarities in the m ilitary C-1 30 vers ions,

they can als o be applied to m ilitary 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. Som e of the aircraf t listed below are currently being operated by

f o reign m ilitary organ i za tions.

Table 3.1 – Civil Certified 382, 382B/E/F an d G Series Aircraft Manufactured b y

Lockheed Martin Aeronautics Compan y

3946 4248 4450 4691 4839 4956

4101 4250 4472 4695 4850 4957

4109 4299 4475 4698 4851 4960

4129 4300 4 4 7 7 4 7 0 1 4853 4992

4134 4301 4512 4706 4880 5000

4137 4302 4 5 5 8 4 7 0 8 4 8 8 3 5022

4144 4 3 0 3 4 5 6 1 4710 4886 5024

4 1 4 5 4 3 3 3 4562 4715 4889 5025

4 1 4 6 4 3 5 0 4565 4763 4891 5027

4147 4355 4582 4796 4893 5029

4170 4358 4586 4798 4895 5032

4 1 7 6 4 3 6 1 4590 4799 4917 5048

4 1 9 7 4 3 6 2 4593 4800 4923 5055

4208 4364 4600 4 8 2 4 4 9 4 9 5056

4209 4383 4606 4826 4950 5225

4 2 2 1 4 3 8 4 4610 4828 4951 5306

4222 4385 4673 4830 4952 5307

4225 4388 4676 4832 4953 5320

4 2 2 9 4 3 9 1 4 6 7 9 4 8 3 3 4 9 5 4

4 2 3 4 4 4 1 2 4684 4834 4955

Foreign Commercial (61 Aircra ft)

Domestic Commercial (14 Airc raft)

RED Attrited Commercial (4 3 Aircraft)

TOTAL 118 Commercial Aircraft

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# SMP 515-C-SSID

SECTION 3

AFFE CTE D AIRCRAFT

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# SMP 515-C-SSID

SECTION 4

PRINCIPL E STRUCT URAL E L E M ENTS

4.0 PRINCIPLE STRUCTURAL ELEMENTS

This SMP identif ies s t r u ctura l insp ection requirem e nts of Princip l e Struct ural Elem ents (PSEs)

only. PSEs are defined as primary structural el em ents that con t r i bute sign if icantly to th e

carrying of flight, ground or pre ssur i zation loads and whose integ r ity is e ssential in m a intaining

the overall structural integrity of the aircraft. T h e te rm Structura lly Significant Ite m (SSI) has

also been us ed to iden tify critical prim ary structu r e. LM Aero has identified SSIs in Section V of

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

program s, however, the PSEs identif ied in this docum e nt supersede the S S I definitions.

The L-382 was originally civil certified under C A R 4b failsafe requirem e nts in that design lim it

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

substantiation analysis reports were com p le ted during the L-382 commercial certification

program . During the early 1980’s, Da m a ge Toleranc e was introduced into th e United States Air

Force (USAF) Aircraft Structu r al Integrity Program (ASIP) and the principles of slow crack

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

accordan ce with MIL-A

- 83444 requ irem ents for esta b lish i ng safe period s of operation between

scheduled inspections. The DADT Analysis wa s docum ented in num erous reports provided to

the USAF. These in spection re quirem e nts and intervals for the PSEs were subsequently

incorporated into the SMP 515-C-X Herc ules Series Inspection Program s

.

Detection of a failed or partially failed PSE can be accom p lished by num e rous m e thods

including detection of fuel tank leak age and cab in pressu rization leakag e. These co nditions are

readily apparent to flight and ground crews as pa rt of nor m a l operations and m a intenance. There

are PSEs w h ere routine visual in spection m e thods are inadequate to detect the damage and NonDestructive Inspection (NDI) proce dures m u st be used. Even though the structure is failsafe for

a single PSE for a short period of tim e (typically at leas t for the rem a inder of the flight), a

direc t ed ins p ection is r e quired to detec t the d a m a ge and ensure th at the Ultim ate Strength

capability is resto r ed in a tim ely m a nner. For this reason, all NDI requ irem ents affe cting PSEs

are id entif ie d in this SM P.

Certain PSEs are failsafe by crack ar rest featu r es. An exam pl e is the upper and lower wing joint

fittings. Th ese are s i ngle piece pa rts which have m u ltiple load path features such that cra c king

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# SMP 515-C-SSID

SECTION 4

PRINCIPL E STRUCT URAL E L E M ENTS

will arrest b e tween individual load paths. These features provide opportunities to d e tect fatigue

dam a ge prior to a catas t rophic m u ltiple load p a th failure.

The PSEs ar e listed in T a ble 1 b e lo w. Note tha t seve ral ind i vidua l par t s m a y be identif ied a s a

single PSE, for exam ple, the BL 61 Longeron Splice Fittings. Sim ilar stru ctural parts are also

identified as a single PSE, for example, th ere are three center wing lower surface pan e ls.

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

Structural R e pair Manual, Reference 4.

4.1 CHAPTER 53 – FUSELAGE

Chapter 53 lists the PSEs identif ie d for the For w ard Fusel a ge , Ce nt er Fus e lage , Aft Fusela ge , and

Main Landing Gear W h eel W e ll Struct ure i n Ta ble s 4.1.1 thr o ugh 4.1.3.

Table 4.1.1 - Forward Fuselage Principle Structural Elem ents

PSE Number Description

53-3 0 -01 Wind shi e ld Double r s, Po sts, and Sills

53-3 0 -02 Forward Fu selage Uppe r BL 20 Long eron

53-3 0 -03 Forward Fu selage Uppe r BL 20 Long eron Splice Fitti ngs

53-3 0 -04 Forward Fu selage Uppe r BL 61 Long eron

53-3 0 -05 Forward Fu selage Uppe r BL 61 Long eron Splice Fitti ngs

53-3 0 -06 Forward Fu selage L o we r BL 61 Long eron

53-3 0 -07 Forward Fu selage L o we r BL 61 Long eron Splice Fitti ngs

53-3 0 -08 Skins a nd Frames

53-3 0 -09 FS 165 Bulkh ead Lo we r Cap and Diap h r agm Attach Angle

53-3 0 -10 FS 180 Bulkh ead

53-3 0 -11 FS 196 Bulkh ead WL 145 Reinfo rci ng S t rap and Web

53-3 0 -12 Cre w Entry Door Ski n , WL 195 Lo nge ro n, and FS 24 5 Long ero n F i tting

5 3

- 30 -1 3 U n de r f lo or Str u c t ur e

53-3 0 -14 Forward Fu selage Chine Cap s an d Plates



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SECTION 4

PRINCIPL E STRUCT URAL E L E M ENTS

Table 4.1.2 - Center Fuselage Pr inciple Structural Elem ents

PSE Number Description

53-4 0 -01 Fusel age Pro ductio n Joi n t Mounting Rin g s, FS 245 a nd 737

53-4 0 -02 Cente r Fu sel age Uppe r BL 20 Lon gero n

53-4 0 -03 Cente r Fu sel age Uppe r BL 20 Lon gero n Splice Fittin g s

53-4 0 -04 Cente r Fu sel age Uppe r BL 61 Lon gero n

53-4 0 -05 Cente r Fu sel age Uppe r BL 61 Lon gero n Splice Fittin g s

53-4 0 -06 Cente r Fu sel age Lo we r BL 61 Lon gero n Splice Fittin g s

53-4 0 -07 Upp e r BL 61 L to R Skin s and Ri ng Seg m ents

53-4 0 -08 BL 61 Upp e r to Lowe r Side Skins an d Ri ng Segme n ts

53-4 0 -09 BL 61L to R L o we r (Belly) Skins

53-4 0 -10 Chin e Ca ps a nd Angle s , FS 245 to 737

53-4 0 -11 Cargo Comp artment an d Ramp Und e rf loor Stru cture

, FS 245 to 737

53-4 0 -12 Upp e r BL 61 Ring Spli ce G u sset Fittings, FS 245 to 737

53-4 0 -13 BL 61 Wing A ttach Angle

53-4 0 -14 MLG Bow Be ams an d Fittings, FS 497, 537, and 5 5 7

53-4 0 -15 MLG Track Suppo rt Beam s and Mai n Frames, FS 51 7, 528, 577, 5 88, and 59 7

53-4 0 -16 WL 20 0 Shelf and Suppo rt Attachment s, FS 477 to 59 7

53-4 0 -17 BL 61 Sidewall Panel at Access Op enin g s, FS 477 to 617

53-4 0 -18 Floor Bea m End Fittings an d MLG Shel f Bracket Bolts, FS 517, 528, 577, 588, an d 597

53-4 0 -19 FS 477, 497, and 61 7 Overhead Bul k he a d s

53-4 0 -20 BL 61 Pressu rize d Fairi ng Attachment s, FS 477 to 51 7 and FS 597 to 617

53-4 0 -21 FS 477 and 6 17 Bulkh ead Tensi on Tie F i ttings

53-4 0 -22 FS 477 and 6 17 BL 61 External Ring Sp lice Fittings

53-4 0 -23 FS 477 and 6 17 Tie Do wn Fittings, Struts and Strut S uppo rt Fittings

53-4 0 -24 Paratro op Do or Lon ge ron, FS 697 to 73 7

53-4 0 -25 Paratro op Do or Cuto ut Structure

53-4 0 -26 FS 245 and 7 37 Splice Fitti ng Bolts



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SECTION 4

PRINCIPL E STRUCT URAL E L E M ENTS

Table 4.1.3 - Aft Fuselage Prin ciple S t ructural Elem ents

PSE Number Description

53-5 0 -01 Aft Fuselage Upp e r BL 20 Long ero n

53-5 0 -02 Aft Fuselage Upp e r BL 20 FS 737 Lon g e ron Spli ce Fi ttings

53-5 0 -03 Aft Fuselage Upp e r BL 61 Long ero n

53-5 0 -04 Aft Fuselage Upp e r BL 61 FS 737 Lon g e ron Spli ce Fi tting

53-5 0 -05 Upp e r BL 61 L to R Skin s and Ri ng Seg m ents

53-5 0 -06 BL 61 Upp e r to Lowe r Side Skins an d Ri ng Segme n ts

53-5 0 -07 Aft Fuselage Side Bulkh e a d s an d Struts

53-5 0 -08 Aft Bulkhead and Strut Lo wer Attach Fittings

53-5 0 -09 Aft Fuselage Overhe ad Bul k he ad s and F i ttings

53-5 0 -10 FS 737 Rin g , Ring Seg m en t and Floor B eam End Fitting

53-5 0 -11 FS 737 Bulkh ead Struts a n d Attach Angl es

53-5 0 -12 FS 737 and 1 041 Slopin g L onge ron Spli ce Fittings

53-5 0 -13 BL 61 Aft Fuselage Slopi ng Longe ron

53-5 0 -14 Aft Cargo Do or Beam s an d Skin

53-5 0 -15 Ramp Sid e Beams

53-5 0 -16 Ramp S k in a nd Floo r Bea m s

53-5 0 -17 BL 61 Upp e r Long ero n FS 1041 End Fitt ing and Hori zontal Stabilizer Attachm e n t s

Bolts



# 4.2 CHAPTER 55 - EMPENNAGE

Tabl e 4.2.1 l i sts t h e PSEs ide n ti fie d for the Verti cal and Horizontal Stabilizer s.

Table 4.2.1 - Vertical and Horizontal Stab ilizer Principle Structural Elem ents

PSE Number Description

55-1 0 -01 FS 1041 Bulkhead

55-1 0 -02 Upp e r Surfa c e Skin Panel s

55-1 0 -03 Lower Surfa c e Skin Panel s

55-1 0 -04 Front an d Re ar Beam Cap s and Web s

55-1 0 -05 Typical Ski n to Beam Ca p Splice, HSS 69-1 80

55-1 0 -06 Vertical Stabil i zer Attach Angle

55-1 0 -07 Vertical Stabil i zer L o wer Su pport Fitting s

55-1 0 -08 Vertical Stabil i zer Upp e r Su pport Fitting s and Attach B o lts

55-1 0 -09 Rud der, Elev ators, a nd Ru dder a nd Ele v ator Hing es



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SECTION 4

PRINCIPL E STRUCT URAL E L E M ENTS

4.3 CHAPTER 57 - WINGS

T a bles 4.3.1 and 4.3.2 pr ovide the PSEs identif i ed for t h e Cente r and Outer Wi ng, r e s p e c tivel y.

Table 4.3.1 - Center W i ng Princi ple Structural E l em ents

PSE Number Description

57-3 0 -01 Front Beam L o we r Ca p

57-3 0 -02 Rea r Beam L o we r Ca p

57-3 0 -03 Front Beam Upp e r Cap

57-3 0 -04 Rea r Beam Upper Cap

57-3 0

- 0 5 R e a r Beam W e b

57-3 0

- 0 6 F r o n t Beam W e b

57-3 0 -07 Lower Surfa c e Skin Panel s

57-3 0 -08 Upp e r Surfa c e Skin Panel s

57-3 0 -09 Lower Surfa c e Skin Panel Stringers

57-3 0 -10 Upp e r Surfa c e Skin Panel Stringers

57-3 0 -11 Diag onal Ri b Upp e r an d Lo wer Cap, WS 62 to WS 92

57-3 0 -12 No. 2 and 3 E ngine Na celle Truss

57-3 0 -13 No. 2 and 3 E ngine Na celle Rib Ca p and Attach Fittings

57-3 0 -14 Lower Front and Rear Be am Co rne r Fittings

57-3 0 -15 Upp e r Front and Rear Be am Co rne r Fittings

57-3 0 -16 Wing Joint Front and Rear Beam Vertica l Attach Angles

57-3 0 -17 Upp e r Wi ng Joint Rain bow Fitting

57-3 0 -18 Lower Wi ng Joint Rain bow Fitting



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SECTION 4

PRINCIPL E STRUCT URAL E L E M ENTS

Table 4.3.2 - Outer W i ng Principle Structural Elem ents

PSE Number Description

57-5 0 -01 Upp e r Wi ng Joint Rain bow Fitting

57-5 0 -02 Lower Wi ng Joint Rain bow Fitting

57-5 0 -03 Wing Joint an d Corne r Fitting Attach Bol t s

57-5 0 -04 Lower Front and Rear Be am Co rne r Fittings

57-5 0 -05 Upp e r Front and Rear Be am Co rne r Fittings

57-5 0 -06 Front Beam L o we r Ca p

57-5 0 -07 Rea r Beam L o we r Ca p

57-5 0 -08 Front Beam Upp e r Cap

57-5 0 -09 Rea r Beam Upper Cap

57-5 0

- 1 0 R e a r Beam W e b

57-5 0

- 1 1 F r o n t Beam W e b

57-5 0 -12 Lower Surfa c e Skin Panel s

57-5 0 -13 Upp e r Surfa c e Skin Panel s

57-5 0 -14 Rib Cap s and Brace s

57-5 0 -15 King Pin Rise r Fittings

57-5 0 -16 Flap Track Stiffeners a nd Br aces, O W S 28, 100, 173, 241, and 30 3

57-5 0 -17 Pylon Attach Fittings, OWS 72 and 92

57-5 0 -18 Web Spli ce T ees, O W S 15 8 and 20 1

57-5 0 -19 No. 1 and 4 E ngine Na celle Truss

57-5 0 -20 No. 1 and 4 E ngine Na celle Rib Ca p and Attach Fittings

57-5 0 -21 Aileron a nd Aileron Hing es



# 4

. 4 CHAPTER 71 – POWER PLANT

Chapter 71 lists the structural inspection re qui re ment s PSEs i d en ti fie d for t h e Engi ne Nac e l l e

(Quick Engi ne Change Unit) i n Ta ble 4.4.1.

Table 4.4.1 - Engine Nacelle P r in ciple Structural Elem ents

PSE Number Description

71-1 0

- 0 1 Q E C U Lower Longe ron s

71-1 0

- 0 2 Q E C U Upp e r Longe ron s

71-1 0 -03 Aft Engine Mount Beam a nd Suppo rt Fittings



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# SMP 515-C-SSID

SECTION 5

DAMAGE TOLERANCE ANALY S IS METHODOLOGY

5.0 DAMAGE TOLERANCE A NALYSIS METHODOLOGY

This section defines the criter ia and m e thodology used for crack growth analysis of the L-382

prim ary airf ram e structure. The m e thodology wa s originally developed and docum e nted in

Reference 2 to m eet the United States Air Fo rce (USAF) DADTA standa rds and specifications

defined in MIL-A-83444. Since th ese requirem e nts were directed towards the design and testing

of new aircraft, they were not necessarily app lied “in total” to the L-382, which had m a ny years

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

contained in the following subsections.

The current FAA da m a ge tolerance guidelines perm it the us e of eithe r a

f

a il saf e o r slow cra c k

growth approach to achieve the required da m a ge tolerance. Although the L-382 prim ar y

structural airfram e is inherently failsafe, m a jor em phasis is on using the slow crack growth

approach to evaluate the dam a ge tolerance of the L-382 structure.

The slow crack growth analytic al approach provides for airfr a m e safety through a com b ination

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

com ponents or elem ents such as an individual b eam cap or fitting. The safe extent of crack

growth of a single e l e m ent is m a intained by r e quir i ng m u ltip le inspec tions with a given ND I

techniqu e su ch that the theoretical crack growth or final crack length be tween inspection periods

never b eco m e s larger than the stab le crack len g th if lim it tension s t r e s s were to b e applied, with

lim it defined as the m a xim u m design tension stress value for the structure.

As necessary and appropriate, the inherent fail sa f e ty of the structu r e is recog n ized in th e

establishm ent of recomm ended actions related to structural safety.

5.1 Safety Limit

In the DT Analysis, operational lim its are de term ined which address the safety of the L-382

struc t ure. T h ese lim its a r e the saf e ty lim its, def i ned as the tim e (f light h ours or pre s suriza tion s )

beyond which it is recomm ended not to operate the aircraft without a ppropriate inspections,

repairs or modif i cation s . The saf e ty lim it is used as a b a sis for con ducting in sp ection s and

establishing safe-use intervals of operation.

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SECTION 5

DAMAGE TOLERANCE ASSESSMENT METHODOL OGY

For each critical area, the safety lim it is the calcu la ted fligh t h our interval (for a specific location

within a PS E) for an ass u m e d “worst” in itial flaw size (a i 

# ) to grow to an unstable length (a CR 

# ) at

lim it load, when subjec te d to the an alytic al operational loads/environm ent spectra.

This initia l f l aw is assum e d to exist in the m o st unfavorable location and orien t ation with respe c t

to the app lie d stres s es an d m a teri al properties. Th e assum e d size is sufficiently large su ch that it

is unlik ely that a c r itica l f a stener ho le loca tion in a fleet of aircraft contain s an initial flaw greater

than a i 

# . Figure 5.1.1 presents the safety lim it w ith respect to the cr ack growth curve.

Figure 5.1.1 S a f e t y L i m i t R e p r e s e n t a t i o n

5.2 Initial Flaw Criteria

The initial flaw size and fl aw shape assum p tions as well as th e structural flaw configuration used

in the DTA crack grow th analysis is based on those determ ined in Reference 2. The type of

fastener (interference or non-interf erence), the fastener m a terial and the m e thod of hole

prepar ation (autom ated or sem i -auto m ated hole dril ling v e rs us hand-he ld drilling ) a r e all f eatu r e s

that inf l uenc e the se lec t ion of initia l f l aw sizes.

The m a jority of the structura l loca tions to be an alyzed invo lve two structural elem ents joined by

a common fastener. The selected flaw m o del fo r th is genera l str u ctur al conf iguration is

illus t rated in Figure 5.2.1

.

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SECTION 5

DAMAGE TOLERANCE ASSESSMENT METHODOL OGY

Figure 5.2.1. G e n e r a l S t r u c t u r a l C o n f i g u r a t i o n I n i t i a l F l a w M o d e l

From Figure 5.2.1, note that in Part N o. 1:

• Flaws are lo cated at the faying surface

• The fi rst fl aw, (a) 1 

# , is oriented toward the ligam e nt

• The second flaw, (a) 2 

# , is located diam etrically opposite to the first flaw

The fi rst flaw, (a) 1 

# , is term ed the initial flaw, a i 

# , and is lo cated in the m o st adverse structu r al

location within the m odel. The second flaw, (a) 2 

# , is located on the diam etrically opposite side of

the hole to perm it continuing dam a ge. Continuing da m a ge allows c r ack growth to co ntinue af ter

the pr im ary growth f r om the initia l f l aw has term inated d u e to s t ruc t ural d i scon tinuities o r

ligam ent f a ilure.

After l o cati n g the flaws i n the mode l

, the fl a w

siz e s and fl a w

sha p es have to be esta bl ishe d. As

previ o usly st ated, the type of fast ener and hol e pr eparat ion must be id e n tif i ed in o r d e r to s e le c t th e

flaw si zes. A flaw size selection summary for safety li mit c a lc ulations is pr ovi ded in Fi gure 5.2.2.

It is not ed i n Figure 5.2.2 t h at under the Continuing D a m a ge colu mn, t h e flaw size i s quote d as

0.005” af ter ligament f a ilure or 0.005” + ∆ a fro m ti m e zer o. The ter m ∆ a repre s ent s t h e le ngt h a

crack will propagate f r om the 0. 005” f l aw during the time th e primary crack has grown from a i



# through ligament f a ilure. These t w o type s of continui ng da mage as sumpt i ons a nd thei r effe cts on

crack growth are illustrate d in Figure 5.2.3.

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SECTION 5

DAMAGE TOLERANCE ASSESSMENT METHODOL OGY

All cra c k gr owt h

calc u la tions for the deter m inati on of the safety limits use crack gr owth rat e dat a

consistent w i th an environm en t of 90% relati ve humidity.HolePrep’n 

# T y pe of

Fastener or

Structure Assum e d

Initial

Fla w , a i 

# Fla w Sh ape En v i ronment Con t inuing Damag e

Gene ral

Tape rlo k 0.03 in. 1⁄4 Circular

Cor n e r Flaw 90% Relative

Humidity 0.005” Oppo site Side of

Fasten er Hol e After

Ligame n t Fail ure

Gene ral

Hi-L ok s,

Hi-Ti gue s 0.05 in. 1⁄4 Circular

Cor n e r Flaw 90% Relative

Humidity 0.005” Oppo site Side of

Fasten er Hol e After

Ligame n t Fail ure

Joint Taperl o k 0.05 in. 1⁄4 Circular

Cor n e r Flaw 90% Relative

Humidity 0.005” + ∆ a Oppo site

Side of Hole from Time

Zero

Hi-Loks

, HiTigue s, B o lt s,

Rivets, and CutOuts 0.05 in. 1⁄4 Circular

Cor n e r Flaw 90% Relative

Humidity 0.005” + ∆ a Oppo site

Side of Hole from Time

Zero

No H o le 0.125 in.

Dee p Semi-Circ u lar

Surface Flaw 90% Relative

Humidity N/A

Au toma te d or Semi-Automa t ed Ho le Drilling



# * Hand-Held Drilling

1

2 2 1



# Figure 5.2.2: Initial Flaw Si z e Selection Summary

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SECTION 5

DAMAGE TOLERANCE ASSESSMENT METHODOL OGY

Figure 5.2.3 Continuing Damage

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# SMP 515-C-SSID

SECTION 5

DAMAGE TOLERANCE ASSESSMENT METHODOL OGY

5.3 Inspection Criteria

In order to devel op sa fe- u se int e rvals through a st ructural ins p ection pla n, i t is nece ssar y

to de vel o p

inspecti on i n terval s ba sed on oper atio nal fli ght hours. I n s p ecti on i n tervals are det e r m ined fro m the

Sa fet y

Li mi t. T h e a ssi gn me nt of Non- De struc tive I n s p ecti on ( N DI ) proce dure s t o PSEs a r e

provided in S ection 6.

5.3.1 Initial Inspection Interval

The recommended initial inspection o ccurs at one-half the Sa f e ty Li mit. Figure 5.3.1 illustrates the

initial inspection time in relatio n to the Safety Limit on a st andard crack growth curve.

Figure 5.3.1 Initial Inspection Representation

5.3.2 Recurring Inspection Interval

The r ecurr ing inspecti o n occur s at one- h al f t h e ti m e for a crack to gr ow fr om the m a xi mu m

undetect abl e flaw size (a ND I 

# ) t o a n

unstable le ngt h at desi gn li mit loa d (a CR 

# ), as descri bed in Figure

5.3.2. It s h oul d be not e d t h at sa fe- u se i n ter v al s of operati o n, equal t o t h e recurr ing inspecti on

interval, can conti n ue up to and be yond the calc u late d Sa fet y

Li mit for a spe c i f ic st ructural part,

provided that no cracking is detected by the speci fie d No n- De structi v e In s p ection technique at the

ti m e of re cur r ing inspe c ti on.

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SECTION 5

DAMAGE TOLERANCE ASSESSMENT METHODOL OGY

Figure 5.3.2 Recurring Inspection Intervals

5.3.3 Non-Destructive Inspection Techniques

In order to e s tabli s h the r ecurri ng i n spection inter v al for a gi ve n structural l o cati on, it is nece ssar y

to

establ ish a maxi mu m undet ectable flaw si ze (a NDI 

# ). This is the largest cr ack that can be missed by

an inspector usually with a 90% reliability and 95% conf idence. The value of a

ND I 

# i s base d on the

capabilities of the techni que and t h e accessibili ty of the str u ct ure. In some cases, the geometry of

the struc t ure will si gni fi cantl y hinde r re liable det ection and i n these cases, t h e a NDI 

# is suff iciently

large to account for crac ks that will be hi dde n by ot her structur e.

Table 5.3.1 below iden tif i es the basic capa bilities of each of the common Non-Destructive

Inspection methods.

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SECTION 5

DAMAGE TOLERANCE ASSESSMENT METHODOL OGY

Table 5.3.1: Summary of NDI Techniques

Non-Destru ctive Inspection Technique NDI

Abbreviation Maximum

Undetectable Fla w

Length a NDI 

# (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 S u rface Scan US or USSS 0.20

R a d i o g r a p h y X

- R a y 1

. 0 0

Liquid Fluor escent Pene trant LPI or LP 0.25

Directed Visual V or Vis 1.00

Magnetic Particle MPI or Mag 0.25



# Not e : The a ND I 

# val u es shown are t h e m i ni mu m and are i n cr eased as required to account f o r the

structural accessibilit y and geometry.

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# SMP 515-C-SSID

SECTION 6

STRUCTURAL INSPECTION REQUIREMENTS

6.0 STRUCTURAL I N SPECTION REQUIREM ENTS

The PSE structural ins p ection req u irem ents ar e iden tified in th is S ection. For each AT A

Chapter, the SMP 515-C inspection procedure car d num ber, or Service Bulletin num b er is

identified along with the inspection title, the ai rcraft m odel applicability code, the associated

PSE num b er, the latest r e vision da te and the initial insp ectio n interv al a nd recurr ing inspection

inte rval.

Inspection interva l s co ntained in this Sec tio n are derived from a co m b ination of Da m a ge

Tolerance Analysis as defined in Section 5 and from full scale du ra bility test ing and service

crack ing experien ce. Lockheed Martin m a intains a crack history database of operator reported

structural service crack s.

Comm ercial operators who have an up to date S M P 515-C program and who also complete LM

Aero Servic e Bulletin s m a y currently be com p lyi ng with the intent of this SSID. Inspectio n

intervals provided in this docum ent should be co m p ared to their current m a intenance program

and if neces sary, adju sted to m eet these m i ni m u m requirem e nts.

6.1 Applicability Code

The applicability of the inspectio n procedures to L-3 82 Serial Numbers is identified by the

following applicab ility codes (shown on the lef t colu mn of the Sectio n 6.3 Inspection

Re quir e ment s):

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 num b ers. St ructural redesigns and

im prove m e nts to a PSE can either m a ke a partic ular inspection procedur e not ap plicab le o r

extend the required insp ection interval.

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SECTION 6

STRUCTURAL INSPECTION REQUIREMENTS

6.2 Inspection Intervals an d Operational Usage Severity

The initia l and recu rring inspec tion inte rvals pr ovided in this secti on are based on typical

m ilitary tran sport us age in the late 1 970’s. This has been referred to as “Baselin e Usage”, o r

“Baselin e Military Usage”. Crack growth an alys is of operational usage that dif f ers from the

baseline can be expressed as a crack growth rate se verity f actor rela tiv e to the baseline. The term

“Equivalent Baseline Hours” has b een used to define an equiva lent state of fatigue dam a ge

between different operators with di fferent operational usage severity facto r s. Recent analysis of

commercial operational usage indicates that the sever ity rela tive to the base line usage is

approxim a tely 1.0. Some custom er specific SM P 515-C program s have included an adjustm e nt

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

Da m a ge Tolerance Analysis program. Inspecti on proc edu r es that are subject to operational

usage severity are identified by the applicab ility code “P”.

The inspection intervals provided in this Sect ion should be taken as the m i ni mum required

inte rvals f o r a typ i ca l c a rgo transp ort ope ratio n al usag e with av erag e payloads no t exceedin g

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

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

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

PSEs which requires reduced insp e c tion interv als. LM Aero has recomm ended in Service

Bulletin 382-57-84 that all comm erci al operators have their usage a sse ss ed to es tablish the ra tes

of fatigue crack growth such that appropriate inte rvals of insp ection can b e estab lish e d.

In no circum stances should the operator exte nd these inspection intervals without having

com p leted an LM Aero Operational Usage Ev aluation and obtaining FAA appr oval for an

updated SMP 515-C inspection program

.

6-2

Change 1 - 10 September 2007

U s e an d/or di scl os ur e i s g o v e r ned by state m e n t o n th e ti tl e pag e o f t h i s doc u m e nt.

# 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 interv als provided in this section are related to the PSEs identified

in Section 4. In the majority of cases, there ar e numerous inspection proce dures that relate to a

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

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

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

this section are required to c over the PSEs unless otherwise stat ed 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 To tal 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 cont ained in this section shall be accomplished not

later than +10% of the specified interval. Where intervals ar e 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 airc raft 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.SMP 515-C-SSIDSECTION 6STRUCTURAL INSPECTION REQUIREMENTSINSPECTION FREQUENCYSB/CARDNUMBERREVISIONDATEPSENUMBERTITLEINITIALRECURRINGCHAPTER 52- DOORSAST-201-Jan-9353-50-16InspectionDiagonal Truss Member, Cargo RampBulkheads6 Years6 YearsASP-1121-Nov-8653-50-14VisualInspection Aft CargoDoor SideBeams25,200 TFHor 12 Years6,300 FHor 6 YearsCHAPTER 53- FUSELAGEASBA382-53-51Rev16-Nov-9053-30-10Fuselage-Inspectionof Forward Fuselage CabinUnderfloorBulkhead Structure at FS180.5, WL170,Between BL18 to BL27, Leftand Right Side for Cracks10,000 TFH3,000 FHDSB382-53-61Rev41-May-0753-40-13Fuselage – Inspection of Wing to Fuselage Attach AngleLM 4383 – LM5252 and Aircraft Modified to Include Attach AngleStraps, P/N 3305081-1/-2,3305082-1/-2,3313369-1/-2, 3313369-3/-4, and 3313369-5/-612 Years1 YearAST-11-Jul-9953-30-XX53-40-XX53-50-XXVisual Inspection Exterior Fuselage Structure6 Years6 YearsAST-41-Jul-9953-40-26Check Fuselage LongeronSplice FittingTension Bolts12 Years12 YearsAST-141-Jan-9353-40-14through53-40-18Visual Inspection of Main LandingGearand WheelWell3 Years3 YearsAST-151-Jun-9153-40-1453-40-15Inspection Main LandingGear VerticalBeam Bolts3 Years3 YearsAST-161-Jan-9353-40-15Visual Inspection Main Landing Gear Vertical Beams3 Years3 YearsAST-181-Jul-9153-40-18Check Main LandingGearShelf BracketBolt Torque3 Years3 YearsAST-191-Jan-9353-40-15Inspection MLG Wheel Well FS 597 Beams3 Years3 YearsAST-221-Jul-9953-40-0353-40-0553-40-06Check Fuselage Splice Bolts for Specified Torque.12,600 TFHor 12 Years12,600 FHor 12 Years6-4Change 1 - 10 September 2007Use and/ordisclosure isgoverned bystatement onthe titlepageofthisdocument.SMP 515-C-SSIDSECTION 6STRUCTURAL INSPECTION REQUIREMENTSINSPECTION FREQUENCYSB/CARDNUMBERREVISIONDATEPSENUMBERTITLEINITIALRECURRINGAST-251-Jul-9953-30-0853-30-1053-30-14Visual Inspection of Flight Deck and Under Deck ElectronicEquipment Area6 Years6 YearsASP-291-May-8753-40-13Visual Inspection ofFS 477 to FS 617 Attach Angle12,600 TFHor 12 Years3,400 FHor 3 YearsAPSP-301-Mar-9353-50-0753-50-0853-50-09Visual Inspection FuselageSide Frame(Vertical Strut)Attach Fittings16,000 TFHor 12 Years3,400 FHor 3 YearsASP-321-May-8753-40-12Visual Inspection Gusset Fittings BL 61 L/R FS 245 to 73720,000 TFHor 12 Years6,300 FHor 6 YearsAPSP-341-Mar-9353-40-1953-40-22Visual Inspection BulkheadOutboard Cap Flanges and ExternalSplice Fittings FS 477, FS 617, WL 258to 22012,600 TFHor 12 Years3,400 FHor 3 YearsASP-351-Jan-8653-40-03Visual Inspection FuselageSplice Fittings12,600 TFHor 12 Years3,400 FHor 3 YearsAPSP-361-Jan-8653-50-07Visual Inspection FS 880 Cap andWeb12,600 TFHor 12 Years3,600 FHor 3 YearsAPSP-371-Dec-8553-30-01Visual Inspection WindowAreas and ExternalWindshield DoublersLM 3501- 4568LM 4569- LM4760LM 4761 andup12,600 TFHor 6 Years12,600 TFHor 12 Years30,000 TFHor 18 Years600 FHor 1 Year5,000 FHor 6 Years15,000 FHor 12 Years6-5Change 1 - 10 September 2007Use and/ordisclosure isgoverned bystatement onthe titlepageofthisdocument.SMP 515-C-SSIDSECTION 6STRUCTURAL INSPECTION REQUIREMENTSINSPECTION FREQUENCYSB/CARDNUMBERREVISIONDATEPSENUMBERTITLEINITIALRECURRINGAPSP-381-May-8753-50-11VisualInspection FuselageBulkhead StrutsLM 3946- LM4340After S/B 382-044 and 382-070 Incorporation and onLM 4341 – LM4966LM 4967 andup3,400 TFHor 3 Years3,400 TFHor 3 Years12,000 TFHor 9 Years3,400 FHor 1 Year3,400 FHor 3 Years6,800 FHor 6 YearsAPSP-681-May-8753-30-09Visual/NDI Inspection FS165 Structure– NDI AsRequired(LM 3501– LM 4760) (Visual Inspection only Aircraft with Steel Inner and OuterAttach Anglesand LM 4761and up)12,600 TFH3,600 FHAPSP-691-Jan-8653-40-14Visual Inspection FS497, FS 537, andFS 557 Structure9,450 TFHor 9 Years3,400 FHor 3 YearsASP-701-Jan-8653-40-16Visual Inspection of MLG Wheel Well Structure, WL200 FS 517 andFS 59720,000 TFHor 12 Years3,400 FHor 3 YearsASP-711-Jan-8653-40-16Visual Inspection of MLG Wheel Well Structure, WL200 FS 47718,000 TFHor 12 Years3,400 FHor 3 YearsAPSP-721-Jan-8653-40-23Visual Inspection FS 477 and FS 617 MLG Wheel Well Fittings16,000 TFHor 12 Years3,400 FHor 3 YearsDPSP-78(See SP114)1-Jul-8753-40-18NDI Cargo Floor BulkheadEnd (Aluminum Pork Chop) FS 597(LM 3501 - LM4712)Inspection notapplicable to LM 4713 andup or Aircraft with P/N3313808 or3314760 SteelPork Chop Fittings6,300 TFH1,200 FHASP-861-Nov-9453-40-01Visual Inspection FuselageMounting Rings FS 245 and FS 73712,600 TFHor 12 Years3,400 FHor 3 Years6-6Change 1 - 10 September 2007Use and/ordisclosure isgoverned bystatement onthe titlepageofthisdocument.SMP 515-C-SSIDSECTION 6STRUCTURAL INSPECTION REQUIREMENTSINSPECTION FREQUENCYSB/CARDNUMBERREVISIONDATEPSENUMBERTITLEINITIALRECURRINGASP-871-Nov-9453-30-02through53-30-0753-40-02through53-40-0653-50-01through53-50-0453-50-1253-50-13Visual Inspection FuselageSplice Attachment FittingsFS 245 andFS 73712,600 TFHor 12 Years3,400 FHor 3 YearsDSP-951-May-8953-40-15NDI Main Frame and CapFS 517, WL 215 and BL 67LM 3501 - LM4751Inspection notapplicable After Incorporation of S/B 382-53-19 (A382-189) and LM4752 and up10,000 TFH1,200 FHDPSP-961-Oct-9853-30-12NDI AreaAbove CrewEntry DoorLM 3501 – LM 4871Visual Inspection Only for Aircraft Modified per SMP 583 Figure53-30-30 (SeeSP-274)6,300 TFH3,400 FHAPSP-991-Jan-8653-40-21Visual Inspection of Upper Bulkhead Tension Tie Fittings FS 477 and617, BL 61 L/R12,600 TFHor 12 Years6,300 FHor 6 YearsDSP-1071-Nov-9553-40-24VisualInspectionof Longeron Below Personnel Doors FS 697LM 3501- LM4568Inspection notapplicable After S/B 382-53-21Incorporation and LM4569 and up20,000 TFHor 12 Years6,300 FHor 6 YearsDSP-1081-Jan-8653-40-17Visual Inspection of MLG Access PanelOpenings FS 522 and 583LM 3501- LM4673Inspection notapplicable to Aircraft withSteel DoublerInstallationand LM 4674and up16,000 TFHor 12 Years3,600 FHor 3 Years6-7Change 1 - 10 September 2007Use and/ordisclosure isgoverned bystatement onthe titlepageofthisdocument.SMP 515-C-SSIDSECTION 6STRUCTURAL INSPECTION REQUIREMENTSINSPECTION FREQUENCYSB/CARDNUMBERREVISIONDATEPSENUMBERTITLEINITIALRECURRINGDSP-1091-Nov-9253-50-1253-50-13Visual and NDI longeron Fittings LowerBL 61 at FS 737 and 1041LM 3501- LM4583With P/N 356198-2L/2R or-3/-4Visual Only atFS 737 LM 3501 - LM4583 With P/N356198-5/-6orLater Fittings and LM 4584and upAt FS 1041 LM 3501 - LM4586WithP/N 337426-L/-RVisual Only atFS 1041 LM3501 - LM 4586 With P/N 337426-5/-6orLater Fittings and LM 4587and up5 Years5 Years5 Years5 Years1 Year3 Years1 Year3 YearsASP-1101-Jul-9953-50-0955-10-06Visual Inspection of Aft Fuselage Top Bulkhead Frames16,000 TFHor 12 Years3,600 FHor 3 YearsASP-1131-Jul-8753-50-13NDI Longeron if FittingatFS 1041 is Being ReplacedFS 1041 FittingReplacementFS 1041 FittingReplacementDSP-114(SeeSP-78)1-Jun-9453-40-18NDI Cargo Floor BulkheadEnd Fittings (P/N 371603Aluminum PorkChop) FS 597- After Repair ActionLM 3501- LM4712SpecialConditionN/AASP-1151-Jul-8753-40-15NDI FS 597Main FrameInspection notapplicable to FS 597 MainFrames repaired per SMP583, Figure 53-40-316,300 TFH1,200 FHASP-1211-Jan-8653-40-18Visual Inspection of Cargo Floor Bulkhead End Fittings25,200 TFHor 12 Years3,400 FHor 3 Years6-8Change 1 - 10 September 2007Use and/ordisclosure isgoverned bystatement onthe titlepageofthisdocument.SMP 515-C-SSIDSECTION 6STRUCTURAL INSPECTION REQUIREMENTSINSPECTION FREQUENCYSB/CARDNUMBERREVISIONDATEPSENUMBERTITLEINITIALRECURRINGAPSP-126(SeeSP-224)1-Dec-9553-40-1953-40-20Visual Inspection of Area Between FS 477 and FS 517, BL 61 L/R,Above WL 256 and FairingAttach Anglesat FS 477LM 3501 – LM4932LM 4933- 5305Incorporationof SB A382-53-49/382-53-50 Accomplishes the intentof the Initial Inspection.No inspectionto Fairing Attach Angles P/N 340043-9L/9R is requiredafter SB 382-53-27incorporation and onLM 4761- LM5305Inspection notapplicable to LM 5306 andup6,300 TFH6,300 TFH1,800 FH3,600 FHAPSP-1271-Dec-8553-40-1953-40-20Visual Inspection of Area Between FS 596 and FS 617, BL 61 L/R,Above WL 256 and FairingAttach Anglesat FS 617No inspectionto Fairing Attach Angles P/N 343067-9 L/R after SB382-53-27 andon LM 4968and up12,600 TFH6,300 FHASP-1611-May-9353-40-1153-50-1553-50-16Inspection ofCargo Compartment and RampUnderfloor Areas LM3501 - LM4991LM 4992 andup3 Years6 Years3 Years6 YearsASP-1921-Dec-8553-40-15Visual Inspection Left and Right Fuselage BL 61 L/RVertical MainFrames, FS 517 and FS 597 at WL 25610,000 TFHor 12 Years5,000 FH6 YearsAPSP-2001-Dec-8653-40-15NDI MLG Vertical Beam at FS 517, 528, 577, and 588Inspection not applicable to Vertical BeamsWith Steel Doublers12,600 TFH3,600 FHDSP-2011-Apr-9353-40-13NDI CenterWing toFuselage Drag Angle InnerRadius BetweenFS477 and 617(Aircraft Without Strap Doublers onHorizontal andVertical Legsof Drag Angle)LM 3501-4382 and Aircraft WithReplacementMEP Wingswithout StrapDoublersRefer to SB 382-53-61 for inspectionof attach anglewith StrapDoublersInspection notapplicable to 382G Series16,000 TFHor 12 Years4,000 FHor 3 Years6-9Change 1 - 10 September 2007Use and/ordisclosure isgoverned bystatement onthe titlepageofthisdocument.SMP 515-C-SSIDSECTION 6STRUCTURAL INSPECTION REQUIREMENTSINSPECTION FREQUENCYSB/CARDNUMBERREVISIONDATEPSENUMBERTITLEINITIALRECURRINGASP-224(See SP126)1-Jan-9353-40-19NDI FuselagePressurizedFairing Support Structure, FS 477 to FS517, BL 61 L/R Above WL256Incorporationof SB A382-53-49 Accomplishesthe Intent of the InitialInspection.Incorporationof SB 382-53-50 Accomplishesthe Intent of the InitialInspection.Inspection notapplicable to LM 5306 andup6,300 TFH3,600 FHASP-2621-Apr-9353-40-23NDI Lower Strut AttachmentFitting at FS477 and FS617 Frames8,000 TFH1,000 FHASP-2711-Jul-9953-50-10NDI Inspectionof FS737, 777E or 817EFloor to RingBulkheadFittingFuselage Maximum Pressure DifferentialHGPSIG14.3 - 15.37.0 - 7.513.2 - 14.36.5 - 7.012.2 - 13.26.0 - 6.510.2 - 12.25.0 - 6.08.1 - 10.24.0 - 5.0Less than 8.1Less than 4.0Inspection not applicable to Aircraft with Original or ReplacementFittings withColdWorkedHoles (SB 382-53-53)8,000 TFH12,000 TFH14,400 TFH20,000 TFH36,000 TFH45,000 TFH700 FH1,050 FH1,300 FH1,750 FH3,150 FH4,000 FHAPSP-2741-Jul-9953-30-12Visual Inspection Above Crew Entry Door(LM 4872 and up andAircraft Modified per SMP 583, Figure 53-30-30)12,600 TFH1,200 FHASP-2971-Oct-0153-30-08NDI FuselageFramesFS 132 L/R24,000 TFH9,000 FHASP-2981-Oct-0153-30-08NDI FuselageFrames, FS 212 and 228Lat WL 19512 Years6 Years6-10Change 1 - 10 September 2007Use and/ordisclosure isgoverned bystatement onthe titlepageofthisdocument.SMP 515-C-SSIDSECTION 6STRUCTURAL INSPECTION REQUIREMENTSINSPECTION FREQUENCYSB/CARDNUMBERREVISIONDATEPSENUMBERTITLEINITIALRECURRINGASP-2991-Oct-0153-30-0953-40-01NDI DiaphragmAttach Angle FS 165 BL 18L/R, Bulkhead Lower CapFS 245 WL 126 - 146 BL 50L/R and Bulkhead Lower Cap FS 165,WL 168 BL 18 – 27.512 Years6 YearsASP-3001-Oct-0153-30-11NDI NLG StructureFS 196 L/R at WL 14512 Years6 YearsASP-3031-Oct-0153-40-10NDI Center FuselageLower Chine Angles FS 517 –597 L/R, ChineCapsFS 245– 737 L/R andCargo RampOutboard Floor PlatesL/R12 Years6 YearsASP-3041-Oct-0153-40-16NDI Horizontal BeamAssembly and Fittings FS 517– 597 L/R atWL20012 Years6 YearsASP-3051-Oct-0153-50-1253-50-13NDI Aft Fuselage Lower (Sloping) Longeron FS 737(FS 817E on382G) to FS 1041 L/R andAttach Fittings at FS 737 L/R (FS 817EL/R on 382G)12 Years6 YearsASP-3061-Oct-0153-50-10NDI FuselageRing and RingSegment FS737 L/R at WL14812 Years6 YearsASP-3081-Oct-0153-40-25NDI Paratroop DoorFrame Structure12 Years6 YearsASP-3091-Oct-0153-40-15NDI MLG Beam FS517 –597 L/R, WL 140 – 16812 Years6 YearsCHAPTER 54- NACELLESASP-211-Jul-9957-30-1257-50-19Power Plant to TrussMount AttachmentEngine ChangeEngine ChangeASP-1201-Nov-8657-30-1257-50-19NDI EngineTruss Mount Lugs at Diagonal Tube Attachment DuringInstallation ofPress Fit Steel Bushing RepairSee SP-118N/ACHAPTER 55- STABILIZERSAST-51-May-9355-10-02through55-10-04Visual Inspection of Verticaland Horizontal Stabilizer6 Years6 YearsAST-61-Sep-9153-50-1253-50-1755-10-08Visual Inspection Empennage Attachment Fittings6 Years6 YearsAST-71-Apr-9353-50-1755-10-08Check DorsalFin, VerticalStabilizerand Horizontal Attachment Boltsfor Torque12,600 TFHor 12 Years12,600 FHor 12 Years6-11Change 1 - 10 September 2007Use and/ordisclosure isgoverned bystatement onthe titlepageofthisdocument.SMP 515-C-SSIDSECTION 6STRUCTURAL INSPECTION REQUIREMENTSINSPECTION FREQUENCYSB/CARDNUMBERREVISIONDATEPSENUMBERTITLEINITIALRECURRINGAST-81-Jul-9955-10-09Inspection Elevators andRudder6 Years6 YearsAST-241-Jul-9955-10-XXVisual Inspection of Verticaland Horizontal Stabilizer,Attach Fittingsand Mating Surfaces24 Years6 YearsASP-391-Jan-9055-10-07VisualInspection VerticalStabilizerFittings9,450 TFHor 9 Years3,400 FHor 3 YearsCHAPTER 57- WINGSDSB382-57-7814-May-0357-30-01Wings – Inspection of Center WingLower Forward Spar Cap at CWS168 to CWS 177 (LM 3501 – LM 5305)Internal SECExternal SEC10,000 TFH10,000 TFH3,400 FH300 FHDSB382-57-7703-Oct-0157-30-15Wing – Inspection of Center WingUpper Forward and Aft CornerFittings Manufactured From7075-T6 Material12 Years6 YearsDSB382-71-23Rev128-Aug-0657-30-1257-50-19Power Plant – Inspectionof Engine Truss Mount forCracking of theDiagonal Brace Lugswith the Press FitSteel Bushing InstalledLM 4801 andup and Aircraft with Diagonal Lugs Modified bySB 382-71-13 and/orRepaired by SMP583 to InstallPress FitBushing orReplacedwith Current ProductionConfiguration TrussMounts12,000 TFH2,400 FHAST-91-Jul-9957-30-1257-50-19Inspection ofNacelle to Wing TrussMountsAircraft with truss mount(s)P/N 360013-23, 360014-23, 360015-19,360016-19, 360017-23, 360018-23 andsubsequent, installed in anyengineposition do not require an inspection at the affected engineposition3 Years3 YearsAST-101-May-9357-30-XX57-50-XXVisual Inspection of WingExterior Surfaces6 Years6 YearsAST-111-May-9357-50-XXVisual Inspection of OuterWings InteriorStructure6 Years6 YearsAST-121-Jul-9957-50-21InspectionAileronsandAileron Control System6 Years6 Years6-12Change 1 - 10 September 2007Use and/ordisclosure isgoverned bystatement onthe titlepageofthisdocument.SMP 515-C-SSIDSECTION 6STRUCTURAL INSPECTION REQUIREMENTSINSPECTION FREQUENCYSB/CARDNUMBERREVISIONDATEPSENUMBERTITLEINITIALRECURRINGAST-131-Apr-9357-50-03Check WS 220 WingJointBolts for Specified Torque12,600 TFHor 12 Years12,600 FHor 12 YearsAPSP-61(See SP195/ SP199)1-Jun-9457-50-12NDI Outer Wing Lower Surface Kingpin Risers OWS 35 ExternalUltrasonic InspectionProcedureNote:Only one InspectionWorkcard shall beused; howeverrecurring interval is dependent on NDI technique selectedLM 3501- LM4298LM 4299- LM4541LM 4542 upand Aircraft withMEP Type ReplacementOuter Wings6,000 TFH7,800 TFH20,000 TFH1,800 FH2,400 FH6,000 FHDPSP-62(SeeSP-196/SP-197)1-Dec-8657-50-0657-50-12NDI Lower Forward WingPanel BeamCap OWS 54and 108LM 3609- LM4298LM 3609- LM4298 AfterDwg. 3304454 External Strap Installation(ECP 954)LM 4299- LM4541LM 4299- LM4541 AfterDwg 3304454Inspection notapplicable to LM 3609- 4541 After Incorporation ofDwg. 3312391 or Dwg. 3312416 of SB382-187Inspection notApplicable toLM 4542 upand Aircraft with MEP TypeReplacementOuter Wings3,500 TFH3,500 TFH3,900 TFH3,900 TFH2,700 FH2,700 FH3,200 FH3,200 FHGSP-641-Aug-8457-50-20Visual Inspection of OuterWingUpperRib Cap, OWS 162 and 197LM 3501- LM4298After SB 382-051 IncorporationLM 4299- LM4541Inspection notapplicable to LM 4542 upand Aircraft with MEP TypeReplacementOuter Wings3,400 TFH12,600 TFH12,600 TFH3,400 FH6,300 FH6,300 FH6-13Change 1 - 10 September 2007Use and/ordisclosure isgoverned bystatement onthe titlepageofthisdocument.SMP 515-C-SSIDSECTION 6STRUCTURAL INSPECTION REQUIREMENTSINSPECTION FREQUENCYSB/CARDNUMBERREVISIONDATEPSENUMBERTITLEINITIALRECURRINGAPSP-661-Aug-8457-50-02NDI Lower Outer Wing Attach Fitting (Rainbow)LM 3501 – LM4333LM 3501- LM4333 NewRainbow Fitting Installation(Dwg. 3302624)LM 4334- LM4454LM 4334- LM4454 AfterSB 382-145 IncorporationLM 4455- LM4541LM 4542 upand Aircraft withMEP Type ReplacementOuter Wings6,300 TFH12,600 TFH6,300 TFH12,600 TFH12,600 TFH30,000 TFH3,400 FH6,300 FH6,300 FH6,300 FH6,300 FH12,000 FHASP-671-Aug-8657-50-01Visual Inspection of Upper OuterWing Attach Fitting (Rainbow)LM 3501- LM4333LM 4334- LM4541 and LM3501 - LM4333With Dwg. 3302624(NewRainbowFitting)NOTE:Ultrasonic InspectionRequired if FailsafeStraps areIncorporatedLM 4542 upand Aircraft withMEP Type ReplacementOuter Wings6,300 TFH15,000 TFH30,000 TFH3,400 FH6,300 FH6,300 FHAPSP-731-Jan-9257-50-12NDI Outer Wing Lower Surface Skin Panels OWS 18, 72, 90 and 231LM 3501- 4298NOTE:Inspection notapplicable atOWS 72 and 90 on LM 3501 -LM 3608With Original Outer WingsWithout Provisions forExternal TanksAfter Dwg. 3304473 and 3304557 (Fastener Replacement)IncorporationLM 4299- 4541Aircraft with MEP Type Replacement OuterWingsand LM 4542up6,300 TFH12,600 TFH18,900 TFH47,200 TFH6,000 FH3,600 FH6,300 FH12,000 FH6-14Change 1 - 10 September 2007Use and/ordisclosure isgoverned bystatement onthe titlepageofthisdocument.SMP 515-C-SSIDSECTION 6STRUCTURAL INSPECTION REQUIREMENTSINSPECTION FREQUENCYSB/CARDNUMBERREVISIONDATEPSENUMBERTITLEINITIALRECURRINGASP-741-Aug-8457-50-01NDI Outer Wing Upper Attach Fittings (Rainbow)LM 3501- LM4454LM 3501- LM4333 AfterIncorporationof SB 382-145 and NewRainbow Fitting Installation(Dwg. 3302624)LM 4334 – LM4454 AfterIncorporationof SB 382-145LM 4455- LM4541LM 4542 upand Aircraft withMEP Type ReplacementOuter Wings6,300 TFH12,600 TFH12,600 TFH12,600 TFH30,000 TFH6,300 FH6,300 FH6,300 FH6,300 FH12,000 FHGPSP-751-Dec-8657-50-0657-50-1157-50-12NDI Outer Wing Forward Lower SurfaceSkin Panel, Beam Cap andBeam Web (VariousOWS)OWS 144 to 165 and OWS 195 to 214(X-Ray/Eddy Current) OWS144 to 159 andOWS 200 to 214 (VisualWeb only)After SB A382-169 Kit A Incorporation -(SP 207 also required)After SB A382-169 Kit B Incorporation OWS 144 to 159 and OWS200 to 214 (Visual -Web only) - (SP 207also required)After SB A382-169 Kit A and SB 382-152Dwg. 3307167Incorporation5,000 TFH5,400 TFH5,400 TFH5,400 TFH1,000 FH1,600 FH1,600 FH1,600 FHOWS 153 to 159 and OWS 200 to 206(X-Ray) Dwg.144 to 159 andOWS 200 to 214 (Visual -Web)- (SP 207 also required)After SB A382-169 or Kit B and SB 382-152 Dwg. 3307167IncorporationOWS 144 to 159 and OWS 200 to 214(Visual - WebOnly) - (SP 207 also required)After SB A382-169, Kit A orB, and NWIDwg. 3609103 IncorporationOWS 144 to 159 and OWS 200 to 214(Visual - WebOnly)(SP 207 also required)Inspection notapplicable to LM 4542 upand Aircraft with MEP TypeReplacementOuter Wings5,400 TFH5,400 TFH5,400 TFH1,600 FH1,600 FH1,600 FH6-15Change 1 - 10 September 2007Use and/ordisclosure isgoverned bystatement onthe titlepageofthisdocument.SMP 515-C-SSIDSECTION 6STRUCTURAL INSPECTION REQUIREMENTSINSPECTION FREQUENCYSB/CARDNUMBERREVISIONDATEPSENUMBERTITLEINITIALRECURRINGAPSP-761-Jul-9957-50-12NDI Outer Wing Lower Surface Skin Panels OWS 162 and 197(Optional InspectionTechniques)OuterWing Panel Number1, 2, 3 and 4 LM 3501 to LM4541X-RayUltrasonicAfter SB 382-152 Outer Wing Panel Number 3 and 4Only LM 3501to LM 4541 Dwg. 3307167X-RayUltrasonicInspection notapplicable After NWI Drawing. 3609103or SB 382-57-73 Incorporation LM 3501 to LM 4541Aircraft With MEP Type Replacement OuterWingsand LM 4542upX-RayUltrasonic10,000 TFH10,000 TFH10,000 TFH10,000 TFH45,000 TFH45,000 TFH1,800 FH5,000 FH1,800 FH5,000 FH2,700 FH27,000 FHASP-821-Aug-8457-50-13NDI Outer Wing Upper Surface PanelNumbers 2 and3 OWS 6LM 3501- LM4541LM 4542 upand Aircraft withMEP Type ReplacementOuter Wings30,000 TFH60,000 TFH15,000 FH15,000 FHDPSP-831-Sep-8957-50-13NDI Outer Wing UpperSurface at PanelAttachment HolesLM 3609- LM4541After Dwg. 3304473 (Fastener Replacement) IncorporationInspection notapplicable to LM 4542 upand Aircraft with MEP TypeReplacementOuter Wings6,300 TFH6,300 TFH6,300 FH thenallsubsequent at3,400 FH6,300 FH6-16Change 1 - 10 September 2007Use and/ordisclosure isgoverned bystatement onthe titlepageofthisdocument.SMP 515-C-SSIDSECTION 6STRUCTURAL INSPECTION REQUIREMENTSINSPECTION FREQUENCYSB/CARDNUMBERREVISIONDATEPSENUMBERTITLEINITIALRECURRINGAPSP-851-Mar-9457-50-19NDI Number1 and Number4 Engine Truss Mount LugsLM 3501- LM4541After Dwg. 3304390 IncorporationAircraft with ReplacementMEP Outer Wings and LM4542 up6,300 TFH6,300 TFH23,000 TFH6,300 FH thenallsubsequent at3,400 FH3,400 FH17,000 FHGPSP-881-Dec-8657-50-0757-50-1057-50-12NDI Outer Wing Lower Surface PanelNumber4, Lower Aft BeamCap and BeamWeb OWS 54 and 108LM 3501- LM4298After Dwg 3304454 Incorporation External Strap Installation (ECP954)LM 4299- LM4541After Dwg. 3304454 Incorporation External Strap Installation (ECP954)Inspection notapplicable After Incorporation of Dwg. 3312419 orDwg. 3312391 of SB 382-187Inspection notapplicable to LM 4542 upand Aircraft with MEP TypeReplacementOuter Wings6,550 TFH6,550 TFH7,760 TFH7,760 TFH4,900 FH4,900 FH5,800 FH5,800 FHAPSP-891-Jan-9257-50-12NDI Outer Wing Lower Surface Panels atOWS 6LM 3501- LM4298LM 4299- LM4541Aircraft With MEP Type Replacement OuterWingsand LM 4542up6,300 TFH12,600 TFH40,000 TFH3,400 FH6,300 FH12,000 FHAPSP-901-Jan-9257-50-12NDI Outer Wing Lower Surface Panel SplicesLM 3501- LM4298LM 4299- LM4541Aircraft With MEP Type Replacement OuterWingsand LM 4542up6,300 TFH8,400 TFH40,000 TFH3,600 FH4,800 FH12,000 FH6-17Change 1 - 10 September 2007Use and/ordisclosure isgoverned bystatement onthe titlepageofthisdocument.SMP 515-C-SSIDSECTION 6STRUCTURAL INSPECTION REQUIREMENTSINSPECTION FREQUENCYSB/CARDNUMBERREVISIONDATEPSENUMBERTITLEINITIALRECURRINGASP-921-Aug-8657-50-18Visual Inspection OuterWing Front Beam Splice TeeOWS 158 andOWS 2019,450 TFH3,400 FHAPSP-1031-Jul-9957-50-0457-50-0657-50-1157-50-12NDI Outer Wing Lower Forward BeamCap, Web, Corner Fitting andSkin PanelNumber1, OWS 0 to 20, LM 3501 - LM 4541Aircraft With MEP Type Replacement OuterWingsand LM 4542up20,000 TFH40,000 TFH10,000 FH15,000 FHDSP-1041-Jul-9957-50-12NDI Outer Wing LowerSkinPanels at Forward and Aft Beam CapsOWS 0 to OWS 300 LM 3501 - LM 4347Inspection notapplicable After Incorporation of SB 382-57-44 orDwg. 3306902-1/-2Inspection notapplicable to LM 4542 upand Aircraft with MEP TypeReplacementOuter Wings15,000 TFH3,600 FHDSP-1161-Aug-8457-30-16Visual Inspection CenterWing Vertical Attach Angles(CWS 220)LM 3501- LM4910 and Aircraft With ReplacementMEP CenterWingsInspection notapplicable to CenterWingAttach Angles ReplacedorRepairedperSMP 583, Figure 57-30-23Inspection notapplicable to LM 4911 andup12 Months12 MonthsAPSP-1181-Jul-9957-30-1257-50-19NDI EngineTruss Mount Lugs at Diagonal Tube AttachmentLM 3501 – LM4800 (non-bushed)Refer to SB 382-71-23 for inspectionrequirements ofdiagonal lugsmodified by SB 382-71-13 and/orrepaired by installing a press fitbushing perSMP 583 andLM 4801 andup.4,000 TFH1,200 FHASP-1191-Mar-9357-30-XXVisual Inspection CenterWing InteriorStructure12 Years6 Years6-18Change 1 - 10 September 2007Use and/ordisclosure isgoverned bystatement onthe titlepageofthisdocument.SMP 515-C-SSIDSECTION 6STRUCTURAL INSPECTION REQUIREMENTSINSPECTION FREQUENCYSB/CARDNUMBERREVISIONDATEPSENUMBERTITLEINITIALRECURRINGDPSP-1231-Aug-8657-50-0657-50-11NDI Outer Wing Lower Forward Beam Cap OWS 72and 90LM 3609- LM4347LM 4348- LM4541LM 4542 upand Aircraft withMEP Type ReplacementOuter Wings(Note: See SP-316)Inspection notapplicable After Incorporation of SB 382-187 Dwg.3312416 andSteel Web per Dwg. 3312417Inspection notapplicable After Incorporation of NWI Dwg. 3609057and Steel Web per Dwg. 33124178,500 TFH10,000 TFH24,000 TFH5,800 FH7,400 FH12,000 FHGPSP-1241-Aug-8657-50-12NDI Outer Wing Lower Surface Skin Panels Around Drain HolesOWS 170LM 3501- LM4298LM 3501- LM4298 AfterSB 382-152 (Dwg. 3307167) Only InspectPanel Number3 and 4LM 4299- LM4541 (Referto SP-202 inEvent of Cracks)Inspection notapplicable to LM 3501- LM 4541 After Incorporation ofNWI Dwg. 3609103 or SB 382-57-73Inspection not applicable to Aircraft withMEP Type ReplacementOuter Wings andLM4542 up9,000 TFH12,000 TFH13,400 TFH4,000 FH6,000 FH6,000 FHAPSP-1281-Dec-8557-50-0457-50-0757-50-1057-50-12NDI Outer Wing LowerRear Beam Cap,Web, CornerFitting andSkin PanelNumber4, OWS 0 to 20LM 3501- LM4541.LM 4542 upand Aircraft withMEP Type ReplacementOuter Wings20,000 TFH40,000 TFH12,000 FH20,000 FH6-19Change 1 - 10 September 2007Use and/ordisclosure isgoverned bystatement onthe titlepageofthisdocument.SMP 515-C-SSIDSECTION 6STRUCTURAL INSPECTION REQUIREMENTSINSPECTION FREQUENCYSB/CARDNUMBERREVISIONDATEPSENUMBERTITLEINITIALRECURRINGASP-1291-Aug-8457-50-13Visual Inspection OuterWing Upper Surface PanelsLM 3501- LM4541.LM 4542Upand MEP Type Replacement Outer Wings25,200 TFHor 12 Years30,000 TFHor 12 Years2,000 FHor 2 Years4,000 FHor 4 YearsAPSP-1311-Mar-9457-30-12NDI Number2 and Number3 Engine Truss Mount Lugs17,000 TFH6,400 FHGPSP-1331-Aug-8657-50-12NDI Outer Wing Lower Surface Skin Panels in Areas of Riser DrainHoles OWS 250, 253 and 256 LM 3501 - LM 4541.Inspection notapplicable to LM 4542 upand Aircraft with MEP TypeReplacementOuter Wings20,000 TFH1,800 FHGPSP-1341-Aug-8657-50-12NDI Outer Wing Lower Surface Skin Panels in Areas Where BracketsAttach to Risers, OWS 120 to 124 LM 3501 - LM4541.Inspection notapplicable to LM 4542 upand Aircraft with MEP TypeReplacementOuter Wings20,000 TFH1,800 FHGPSP-1351-Nov-9557-50-12NDI Outer Wing Lower Surface PanelRisers at RibClip AttachmentsOWS 162 and 197LM 3501- LM4298 -(After Incorporation of SB 382-152 No FurtherInspection ofForward Clips Required)Inspection notapplicable After Incorporation of NWI Dwg. 3609103or SB 382-57-73LM 4299- LM4541 -(After Incorporation of SB 382-152 No FurtherInspection ofForward Clips Required)Inspection notapplicable to LM 4542 upand Aircraft with MEP TypeReplacementOuter Wings9,000 TFH16,000 TFH5,000 FH10,000 FH6-20Change 1 - 10 September 2007Use and/ordisclosure isgoverned bystatement onthe titlepageofthisdocument.SMP 515-C-SSIDSECTION 6STRUCTURAL INSPECTION REQUIREMENTSINSPECTION FREQUENCYSB/CARDNUMBERREVISIONDATEPSENUMBERTITLEINITIALRECURRINGAPSP-1361-Aug-8657-50-12NDI Outer Wing Lower Surface Skin Panels in AreaWhere SurgeBox Attaches to Panel Riser OWS 246LM 3501- LM4541LM 4542 upand Aircraft withMEP Type ReplacementOuter Wings20,000 TFH40,000 TFH1,800 FH3,600 FHGPSP-1371-Aug-8457-50-12NDI Outer Wing Lower Surface Skin Panels 3 and 4 inAreas of RiserDrain HolesOWS 38, 41and 44 LM 3501 - LM 4541Inspection notapplicable to LM 4542 upand Aircraft with MEP TypeReplacementOuter Wings14,000 TFH1,700 FHAPSP-1381-Dec-8657-30-07NDI CenterWing LowerSurfacePanels, BL 61, FS 517 to FS 59720,000 TFH6,700 FHAPSP-1391-Oct-9657-50-15NDI Outer Wing Lower Surface Kingpin Riser Stiffeners OWS 14 to22LM 3501- LM4541LM 4542 upand Aircraft withMEP Type ReplacementOuter Wings24,000 TFH48,000 TFH6,300 FH12,000 FHAPSP-1411-Aug-8657-30-07NDI Lower Surface Skin Panel At FS 597 From BL 58to BL 61Incorporationof SB 382-57-50 Meets theIntent of the InitialInspectionAfter Incorporation of SMP 583 Figure 57-30-26, Perform DetailedVisual Inspection Around Periphery of Repair20,000 TFH1,800 TFH14,000 FH1,800 FHASP-1581-May-9357-30-0757-50-1257-50-17Visual Inspection Under Engine Heat Shields -WingUpper andLower Trailing Edge Surface1 Year1 YearASP-1601-Dec-9857-50-XXVisual Inspection Fuel TanksLM 3501- LM4991 and Aircraft with ReplacementMEP 12R/13/ROuter WingsLM 4992 andup and Aircraft with Replacement MEP 1T/2T, 9T/10TOuter Wings3 Years6 Years3 Years6 Years6-21Change 1 - 10 September 2007Use and/ordisclosure isgoverned bystatement onthe titlepageofthisdocument.SMP 515-C-SSIDSECTION 6STRUCTURAL INSPECTION REQUIREMENTSINSPECTION FREQUENCYSB/CARDNUMBERREVISIONDATEPSENUMBERTITLEINITIALRECURRINGAPSP-1631-Jan-9257-30-14NDICenterWing Forward Lower Corner FittingsLM 3501- 4298, 4304 andup 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 LongFittings)15,000 TFH10,000 TFH15,000 TFH6,300 FH4,700 FH6,300 FHASP-1651-Jun-9457-50-14NDI Outer Wing RibCapsand BracesLM 3501- 4991 and Aircraft With Replacement MEP 12R/13R OuterWingsIncorporationof SB 382-57-51 Meets theIntent of the InitialInspectionLM 4992 andup and Aircraft With Replacement MEP 1T/2T, 9T/10TOuter Wings12,000 TFH30,000 TFH6,300 FH12,000 FHDPSP-1681-Aug-8457-30-07NDI CenterWing LowerSurface Rectangular Fuel Tank AccessPanel at CWS 120, Left and Right LM 4299 - 4313After Incorporation of LM Repair Sketch SK 382-57-044, PerformDetailed Visual InspectionAround Periphery of Repair15,000 TFH1,800 TFH6,300 FH1,800 FHAPSP-1691-Dec-8657-30-0157-30-06NDI CenterWing Front Beam Web and Lower CapBetweenCWS 77and 81, Left and Right20,000 TFH10,000 FHAPSP-1701-Jun-9457-30-0257-30-05NDI CenterWingRearBeam Web and Lower CapBetweenCWS 76and 82, Left and Right20,000 TFH10,000 FH6-22Change 1 - 10 September 2007Use and/ordisclosure isgoverned bystatement onthe titlepageofthisdocument.SMP 515-C-SSIDSECTION 6STRUCTURAL INSPECTION REQUIREMENTSINSPECTION FREQUENCYSB/CARDNUMBERREVISIONDATEPSENUMBERTITLEINITIALRECURRINGAPSP-1711-Dec-0557-50-12NDI Outer Wing LowerSurface Forwardand Aft Panel to Beam CapSpanwise Splices OWS 7 to300Aircraft with SB 382-152 and 382-57-73or NWI Dwg 3609103IncorporatedDo Not Require Inspectionof the PanelsBetween OWS144 and 214LM 3501- LM4298LM 4299- LM4541LM 4542 andup and Aircraft With MEPType Replacement OuterWings5,500 TFH8,000 TFH35,000 TFH2,700 FH4,500 FH12,000 FHAPSP-1721-Jan-9257-50-0757-50-10NDI Outer Wing Rear BeamLowerCapand Web at OWS 72 and90,L/RLM 3609- 4541LM 4542 andup and Aircraft With MEPType Replacement OuterWings7,000 TFH30,000 TFH6,300 FH12,000 FHAPSP-1741-Dec-8557-30-0257-30-05NDI Lower Aft Beam Cap and Web CWS199 and 20315,000 TFH6,300 FHAPSP-1761-Dec-0457-30-17NDICenter Wing UpperRainbow Fitting Access Cutouts CWS217and 21915,000 TFH3,600 FHASP-1771-Jun-9457-30-17NDICenter Wing UpperRainbow Fitting Vertical Legs, Forward andAft25,200 TFH8,400 FHASP-1781-Jun-9457-50-01NDI Outer Wing UpperRainbow Fitting Vertical Legs, Forward andAft25,200 TFH8,400 FH6-23Change 1 - 10 September 2007Use and/ordisclosure isgoverned bystatement onthe titlepageofthisdocument.SMP 515-C-SSIDSECTION 6STRUCTURAL INSPECTION REQUIREMENTSINSPECTION FREQUENCYSB/CARDNUMBERREVISIONDATEPSENUMBERTITLEINITIALRECURRINGGPSP-1831-Nov-9557-50-12NDI Outer Wing Lower Surface Skin PanelsNumber1, 2 and 3Around LockheedDoubler Installation per SB 382-152, (Dwg.3307167) OWS 144 and OWS 214LM 3501- LM4298NDI Ultrasonic ProcedureVisual Inspection Procedure (Alternate)LM 4299- LM4541NDI Ultrasonic ProcedureVisual Inspection Procedure (Alternate)NDI Outer Wing Lower Surface Skin PanelsNumber3 and 4 AroundPerimeter of Doubler Installation per SB382-57-73 (ApplicableAircraft) (Dwg. 3335100)LM 3501- LM4298NDI Ultrasonic ProcedureVisual Inspection Procedure (Alternate)LM 4299-4541NDI Ultrasonic ProcedureVisual Inspection Procedure (Alternate)Inspection notapplicable to LM 4542 upand Aircraft with MEP TypeReplacementOuter Wings5,000 TFH5,000 TFH9,300 TFH9,300 TFH5,000 TFH5,000 TFH9,300 TFH9,300 TFH2,400 FH900 FH3,200 FH1,200 FH2,400 FH900 FH3,200 FH1,200 FHGPSP-1841-Aug-8657-50-12NDI Outer Wing Lower Surface Skin Panels at NWI DoublerInstallation per NWI Dwg. 3609103 OWS 144 and OWS 214LM 3501- 4298NDI Ultrasonic ProcedureVisual Inspection Procedure (Alternate)LM 4299- 4541NDI Ultrasonic ProcedureVisual Inspection Procedure (Alternate)Inspection notapplicable to LM 4542 upand Aircraft with MEP TypeReplacementOuter Wings6,000 TFH6,000 TFH11,300 TFH11,300 TFH3,600 FH1,500 FH4,800 FH2,000 FH6-24Change 1 - 10 September 2007Use and/ordisclosure isgoverned bystatement onthe titlepageofthisdocument.SMP 515-C-SSIDSECTION 6STRUCTURAL INSPECTION REQUIREMENTSINSPECTION FREQUENCYSB/CARDNUMBERREVISIONDATEPSENUMBERTITLEINITIALRECURRINGAPSP-195(See SP61)1-Jan-9257-50-12NDI Outer Wing ExteriorLower SurfaceKing Pin Riser - ExternalSurface Eddy Current ProcedureLM 3501- LM4298 withSB 382-57-43 IncorporatedLM 4299- LM4541LM 4542 andAircraft With MEP Type Replacement OuterWings6,000 TFH7,800 TFH20,000 TFH350 FH350 FH3,400 FHGPSP-196(See SP62)1-Dec-8657-50-0657-50-12NDI Outer Wing Lower Surface PanelNumber1 at OWS 54 and 108With SB 382-187 Dwg. 3312391 (Doublers and StrapInstallation onAft Portion ofWing) LM 3501 - LM 4541Inspection notapplicable to LM 4542 upand Aircraft with MEP TypeReplacementOuter Wings6,000 TFH5,500 FHGPSP-197(See SP62)1-Dec-8657-50-0657-50-0757-50-12NDI LockheedModified Outer Wing Lower Surface Panel Number1Front Beam Lower Cap Forward Flangeand Rear Beam LowerCapAft Flange at OWS 54 and108 With SB 382-187Dwg.3312416(Stiffener Replacement onForward Portion of Wing) LM 3501- LM4541Inspection notapplicable to LM 4542 upand Aircraft with MEP TypeReplacementOuter Wings6,000 TFH5,500 FHGPSP-1981-Dec-8657-50-06NDI NWI Modified OuterWing Front Beam Lower Cap Aft Flangeand Angle Stiffener at OWS 38 and 123With NWI Dwg. 3609057(Angle Installation on Forward Portion of Wing)LM 3501 - LM 4541Inspection notapplicable to LM 4542 upand Aircraft with MEP TypeReplacementOuter Wings6,000 TFH5,500 FHDPSP-199(See SP61)1-Jan-9257-50-12NDI Outer Wing Lower Surface Skin Panels at KingPin Riser OWS35 - Internal Surface Eddy Current Procedure LM 4542 - up andAircraft With MEP Type Replacement OuterWings20,000 TFH4,300 FH6-25Change 1 - 10 September 2007Use and/ordisclosure isgoverned bystatement onthe titlepageofthisdocument.SMP 515-C-SSIDSECTION 6STRUCTURAL INSPECTION REQUIREMENTSINSPECTION FREQUENCYSB/CARDNUMBERREVISIONDATEPSENUMBERTITLEINITIALRECURRINGGSP-202(See SP124)1-Aug-8657-50-12NDI Outer Wing Lower Surface PanelsAround Fastener Holes atHeat Shieldsand Aft Nacelle Fairings OWS 161 to 195 (If CrackingisFound By SP-124)Inspection notapplicable After Incorporation of SB 382-152 and SB382-57-73 orNWI Dwg 3609103See SP-124N/AAPSP-2031-Jun-9457-50-07NDI Outer Wing Lower Aft Beam Cap at Panel Number4 - OWS 144to 214LM 3501- LM4298LM 4299- LM4541Incorporationof SB A382-57-65 Meets Intent of Initial InspectionLM 4542 upand Aircraft With Replacement MEP Outer Wings5,500 TFH8,000 TFH35,000 TFH2,700 FH4,500 FH12,000 FHDPSP-2041-Dec-8657-50-0757-50-12NDI Outer Wing Panel Number 4 and Lower Aft Beam Cap with SB382-187(Dwg. 3312391)(Doublers andStrap Installation on AftPortion of Wing) LM 3609- 4541NOTE: Combination of SP-204, SP-205, and SP-206 may berequired dependent uponmodified configuration.Incorporationof SB A382-57-65 Meets Intent of Initial InspectionInspection notapplicable to LM 4542 upand Aircraft with MEP TypeReplacementOuter Wings8,700 TFH5,700 FHDPSP-2051-Dec-8657-50-0757-50-12NDI Outer Wing Panel Number 4 and Lower Aft Beam CapWith SB382-187Dwg.3312419 (Stiffener Replacement on Aft Portion ofWing) LM 3609 - 4541NOTE: Combination of SP-204, SP-205 and SP-206may berequired dependent uponmodified configuration.Incorporationof SB A382-57-65 Meets Intent of Initial InspectionInspection notapplicable to LM 4542 upand Aircraft with MEP TypeReplacementOuter Wings8,700 TFH5,700 FH6-26Change 1 - 10 September 2007Use and/ordisclosure isgoverned bystatement onthe titlepageofthisdocument.SMP 515-C-SSIDSECTION 6STRUCTURAL INSPECTION REQUIREMENTSINSPECTION FREQUENCYSB/CARDNUMBERREVISIONDATEPSENUMBERTITLEINITIALRECURRINGDPSP-2061-Dec-8657-50-07NDI Outer Wing Panel Number 4 and Lower Aft Beam Cap withNWIDwg. 3609051 (Angle Installation on Aft Portion of Wing) LM 3609-4541NOTE: Combination of SP-204, SP-205 and SP-206may berequired dependent uponmodified configuration.Incorporationof SB A382-57-65 Meets Intent of Initial InspectionInspection notapplicable to LM 4542 upand Aircraft with MEP TypeReplacementOuter Wings8,700 TFH5,700 FHGPSP-2071-Dec-8657-50-06NDI Outer Wing Lower Forward Beam Cap, Web andPanel atInboard andOutboard Ends of StrapsIncorporatedper LockheedSBs:A382-169 Kit A (AluminumStraps) Dwg.3312301 (Equivalent toECP 954)Dwg. 3304406A382-169 Kit B (Steel Straps)Dwg. 3312308Incorporationof SB A382-57-65 Meets the Intent of the InitialInspectionInspection notapplicable to LM 4542 upand Aircraft with MEP TypeReplacementOuter Wings3,400 TFH3,400 TFH2,800 FH2,800 FHGSP-2091-Jan-8857-50-12NDI Outer Wing Lower Surface PanelRepairs OWS 0 to OWS 360LM 3501- LM4541No further inspectionfollowing Incorporation of SB 382-57-70Inspection notapplicable to LM 4542 upand Aircraft with MEP TypeReplacementOuter WingsSpecialCondition450 FHGDSP-2151-Dec-8957-50-12NDI Outer Wing Lower Surface RepairsModified By SB 382-57-70 orSK 382-57-110, OWS 0 toOWS 360SpecialCondition2,400 FHAPSP-2161-Dec-0457-30-07NDI CenterWing LowerSurface SkinPanels at Cutout Corners,CWS 21615,000 TFH6,300 FH6-27Change 1 - 10 September 2007Use and/ordisclosure isgoverned bystatement onthe titlepageofthisdocument.SMP 515-C-SSIDSECTION 6STRUCTURAL INSPECTION REQUIREMENTSINSPECTION FREQUENCYSB/CARDNUMBERREVISIONDATEPSENUMBERTITLEINITIALRECURRINGAPSP-2171-Dec-0457-30-07NDI CenterWing LowerSurface Panel at the Wing Joint (Rainbow)Fitting at CWS 21415,000 TFH6,300 FHADPSP-2181-Jan-9257-30-18NDI CenterWing LowerSurface WingJoint (Rainbow) FittingReinforcing AnglesCWS 214Inspection notapplicable to Aircraft With Flat Plate Doublers OverAllhorizontal Legs of Reinforcing Angles15,000 TFH7,200 FHADSP-2191-Jan-9257-50-17NDI ExternalTank Pylon,Front and Rear Beam Fittings P/N 388090-1/388090-3 (Aircraft through LM 4983)Incorporationof SB 382-57-54 Accomplishesthe Intent of the InitialInspectionInspection notapplicable to LM 4984 upand Aircraft Through LM4983with P/N 3326727-5/7 or LaterBeam Fittings Installed6 Years6 YearsAPSP-2221-Apr-9357-30-01CenterWingFront BeamLower Cap at WS 174 to WS 21015,000 TFH6,300 FHAPSP-2531-Jan-9357-30-07NDI CW Lower Surface Spanwise Spliceat WS 185.520,000 TFH7,200 FHAPSP-2541-Jan-9357-30-0157-30-07NDI CW Lower Surface Panel No. 1at EngineDragFitting, WS 178&WS 213NDI X-Ray Procedure.20,000 TFH3,600 FHAPSP-2551-Jan-9357-30-07NDI CW Lower Surface PanelNo. 1 at CornerFitting, WS 21415,000 TFH8,400 FHAPSP-2571-Dec-0457-30-18NDI CenterWing LowerSurface Rainbow Fitting,WS 22015,000 TFH3,600 FHAPSP-2581-May-9357-30-03NDICenter Wing UpperSurface Front Beam Cap Vertical Flange,WS 9730,000 TFH12,000 FH6-28Change 1 - 10 September 2007Use and/ordisclosure isgoverned bystatement onthe titlepageofthisdocument.SMP 515-C-SSIDSECTION 6STRUCTURAL INSPECTION REQUIREMENTSINSPECTION FREQUENCYSB/CARDNUMBERREVISIONDATEPSENUMBERTITLEINITIALRECURRINGGPSP-2591-Jul-9957-50-12NDI Outer Wing Lower Surface Typical Rib/Riser Attachment, OWS36, 54, 108, 126 and 249LM 3501- 4298, 4304, 4306-4313LM 4299-4303, 4305, 4314-4541Inspection notapplicable to LM 4542 upand Aircraft with MEP TypeReplacementOuter Wings18,000 TFH32,000 TFH5,000 FH9,000 FHGPSP-2601-Jul-9957-50-12NDI Outer Wing Lower Surface Skin Panel No. 4 at the Fuel BoostPump AttachmentLM 3501-4298, 4304, 4306-4313LM 4299-4303, 4305, 4314-4541Inspection not applicable to Aircraft withMEP Type ReplacementOuter Wings andLM4542 up4,500 TFH18,000 TFH3,200 FH12,800 FHGSP-2611-Apr-9357-50-13NDI Outer Wing UpperSurface Dry Bay Access DoorCutout, OWS180 LM 3501-4541Inspection notapplicable to LM 4542 upand Aircraft with MEP TypeReplacementOuter Wings31,000 TFH14,000 FHDSP-2651-Jun-9457-50-12NDI of Outer Wing LowerSurface SkinPanel Riser Number 18atTermination ofKingpin Riser - OWS 35Incorporationof SB 382-57-74 Establishes the Initial and RecurringInspection Interval Based ontheMeasuredDistance Between Centerof Outermost fastener on KingpinRiser and Edge of Riser.Measure Distance(inches)BetweenCenter of Outermost Fastener onKingpin Riser and Edge ofRiser (Ref SB 382-57-74).ResultsObtainedDetermines Initial and Recurring InspectionIntervals asListed in Table 1.6-29Change 1 - 10 September 2007Use and/ordisclosure isgoverned bystatement onthe titlepageofthisdocument.SMP 515-C-SSIDSECTION 6STRUCTURAL INSPECTION REQUIREMENTSINSPECTION FREQUENCYSB/CARDNUMBERREVISIONDATEPSENUMBERTITLEINITIALRECURRINGSP-265(Cont’d)LM 4992- 5320 (FAA Certified Aircraft)LM 4301, 3946- 4960(FAACertified Aircraft) WithReplacementOuterWings-MEP 1T/2T,MEP 12R/13Ror MEP 9T/10TTable 1Table 17,400 FH7,400 FHTABLE 1GROUP A AIRCRAFTMeasurement*(Inch)Initial InspectionFlight Hours**Flight HoursbetweenReinspectionLess than 0.19018,0007,4000.190 to 0.23020,0007,4000.231 to .30922,0007,400DSP-268(SeeSP-85)1-Mar-9457-50-19NDI Number1 and Number4 Engine Truss Mount LugsNOTE: Perform the InspectionsOutlined on this workcard inconjunction with SP-85 whenever both inspections are required.Incorporationof SB 382-71-20 Meets Intent of Initial InspectionLM 4561- LM5225 (FAA Certified Aircraft)LM 3946- LM4512 (FAA Certified Aircraft) With Replacement OuterWings - MEP 12R/13R orMEP 9T/10TInspection notapplicable to LM 4542- LM 5256With P/N 360013-31or LaterandP/N 360017-31 or LaterTruss MountsInspection not applicable to MEPReplacement Outer Wings WithP/N 360013-31 or Laterand P/N 360017-31 orLaterTruss MountLugs and LM5257 and Up15,000 TFH15,000 TFH5,200 FH5,200 FHASP-3101-Oct-0157-30-08NDICenter Wing UpperSurface WingPanel Number 1, 2, and 3atCWS 214 – 220 L/R15,000 TFH3,600 FHASP-3121-Oct-0157-30-06Visual Inspection ofCenter Wing Front BeamWeb15,000 TFH3,600 FHAPSP-3131-Oct-0157-30-04NDI CenterWing Aft UpperBeam CapCWS 20 andCWS 61 L/R34,000 TFH12,000 FH6-30Change 1 - 10 September 2007Use and/ordisclosure isgoverned bystatement onthe titlepageofthisdocument.SMP 515-C-SSIDSECTION 6STRUCTURAL INSPECTION REQUIREMENTSINSPECTION FREQUENCYSB/CARDNUMBERREVISIONDATEPSENUMBERTITLEINITIALRECURRINGAPSP-3141-Aug-0257-30-07NDI CenterWing LowerSurface WingPanels Number 1, 2 and3 atDrain HolesCWS 56and174 and at Fastener Holes CWS 62 –68L/R25,000 TFH3,600 FHASP-3151-Oct-0157-50-03NDI Outer Wing Joint Attach Bolts and Barrel Nuts12 Years10 YearsDSP-3161-Oct-0157-50-1157-50-17NDI Outer Wing Forward Beam Web OWS 72 andOWS 90,Forward/Aft Pylon Attach Fittings and Pylon Attach Bolts and BarrelNutsLM 4542 upand Aircraft withMEP Replacement Outer Wings.Note:Perform SP-123 Inspectionof the beam cap in the event webcracks arefound.12,200 TFH10,200 FHASP-3171-Oct-0157-50-16NDI Outer Wing FlapTrack Stiffener Lower EndsandBraces OWFlap Station 28, 100, 173,241 and 303L/R12 Years6 YearsASP-3181-Oct-0157-50-0757-50-10NDI Outer Wing Rear BeamLowerCapand Web at Flap TrackFitting OWS 293 L/R15,500 TFH5,000 FHCHAPTER 71- POWER PLANTASP-801-Jan-9271-10-0171-10-02Visual Inspection of QEC Upper and Lower Longerons QEC SerialNumber: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 0043 Years3 YearsInspection notapplicable After SB 382-71-12 IncorporationInspection notapplicable to QEC ReworkedWith Longerons P/N362501-5, 362501-6, 362502-9 and 362502-10 orLater, or EarlierQEC With P/N 362531-3Power PlantMount Assembly Installed orEarlier QECWith P/N 362531-1 PowerPlant Mount Assembly S/N0001 LK and up Installed6-31Change 1 - 10 September 2007Use and/ordisclosure isgoverned bystatement onthe titlepageofthisdocument.SMP 515-C-SSIDSECTION 6STRUCTURAL INSPECTION REQUIREMENTSINSPECTION FREQUENCYSB/CARDNUMBERREVISIONDATEPSENUMBERTITLEINITIALRECURRINGSP-80(Cont’d)Inspection notapplicable to QEC SerialNumber LM-G 4669-001andup or LaterQEC SerialsDSP-1871-Jan-9271-10-01NDI QEC Lower Longerons (CertainSerial Numbers) Longeron P/N362501-1 thru 362501-6Incorporationof SB A382-54-7 Meets Intent of Initial InspectionInspectionCondition And LongeronConditionForward Engine Mount Removed -No CrackForward Engine Mount Removed -Crack Less Than 2.0 inchesForward Engine Mount Installed -No CrackForward Engine Mount Installed -Crack Less Than 2.0 inchesForward Engine Mount Removed -Crack 2.0 Inchesor Installed -but less than2.5 inchesForward Engine Mount Removed -Crack 2.5 Inchesor Installed -but less than3.0 inches3 Years3 Years3 Years3 Years3 Years3 Years2 Years1 Year1 Year1 Year6 Months60 DaysCrack 3.0 Inches orLonger - Replace LongeronCrack Dimension ismeasured aft from forward face ofmountingflange of LongeronInspection notapplicable to QEC SerialNumber LM-G-3569-013 andup, LM-G-4469-129 and up, LM-G-4569-045 and up,LM-G-4869-053and 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 PowerPlant Mount Assembly Installedor Earlier QECWith P/N 362531-1Power Plant Mount Assembly S/N 0001 LK and up InstalledDSP-1891-Jun-9471-10-0271-10-03NDI QEC Upper Longeronsand Support Fittings at Aft Engine MountBeam (CertainSerial Numbers)Upper SlopingLongeron-P/N 362502-1 through -12Support Fitting -P/N 363801-1 through -4Outside Skins - AllIncorporationof SB 382-54-9 Meets Intent of Initial Inspection2 Years2 Years6-32Change 1 - 10 September 2007Use and/ordisclosure isgoverned bystatement onthe titlepageofthisdocument.SMP 515-C-SSIDSECTION 6STRUCTURAL INSPECTION REQUIREMENTS6-33Change 1 - 10 September 2007Use and/or disclosure is governed by statement on the title page of this document.INSPECTION FREQUENCYSB/CARDNUMBERREVISIONDATEPSENUMBERTITLEINITIALRECURRINGSP-189(Cont’d)Inspection not applicable to Upper Longeron QEC Serial NumberLM-G-3569-013 and up, LM-G-4469-125 and up, LM-G-4569-045and up, LM-G-4869-053 and up, LM-G-4969-001 and up, and AllSubsequent LM-G Numbers orQEC With Longeron P/N 362502-13/-14 or Earlier, QEC With P/N 362531-3 Power Plant Mount AssemblyInstalled or Earlier QEC With P/N 362531-1 Power Plant MountAssembly S/N 0001 LK and up InstalledInspection not applicable to Support Fitting QEC Serial Number LMG-5669-005 and up, LM-G-5769-001 and up, LM-G-5869-013 andup, LM-G-5969-049 and up, LM-G-6069-025 and up, LM-G-6169-001and up, and All Subsequent LM-G Numbers, or QEC With P/N3331795-1, through -4 or Earlier QEC With, P/N 362531-3 PowerPlant Mount, Assembly Installed or Earlier, QEC With P/N 362531-1Power, Plant Mount Assembly S/N 0001 LK and up InstalledASP-1901-Jun-9471-10-03NDI QEC Aft Engine Mount Fastener Holes on P/N 363803 SteelBeam at each Aft Lord Mount ChangeInspection not applicable to QEC Serial Number LM-G-5669-005 andup, LM-G-5769-001 and up, LM-G-5869-013 and up, LM-G-6069-025and up, or QEC with P/N 3331871-1 or Later Steel Beam, or QECWith P/N 362531-3 Power Plant Mount Assembly or Earlier QECWith P/N 362531-1 Power Plant Mount Assembly S/N 0001 LK andup InstalledAft Lord MountChangeAft Lord MountChange

# SMP 515-C-SSID

SECTION 6

STRUCTURAL INSPECTION REQUIREMENTS

This Page Intentionally Blank

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# SMP 515-C-SSID

SECTION 7

DISCREP ANCY RE PORTING

7.0 DISCREPANCY REP O RTING

7.1 Fatigue and Corrosion Damage Reporting

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

identif i ed in Section 4 is to be repo rted to LM Aero within 10 working days of detecting the

dam a ge. The report shall contain the following infor m ation:

• LM Aircraft Seria l Number

• Operator Registration Num b er

• Aircraft Flight Hours and Cycles

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

• PSE Number and Description from Section 4 of this docum ent

• Inspection Z one Num b er (From Section 8)

• Part Num b e r or Description of Structural Item

• Location and of da m a ge (WS, FS, WL)

• Length of dam a ge (i.e. crack length) and orientation (i.e. spanwise, chordwise)

• How da m a ge was found (Inspection Procedur e reference and Pro cedure Num b er or

descrip tion )

Provide the report to a L M Aero fi eld service representative or to LM A e ro direc tly via em ail to

hercules.support@lm co.com with an em ail title of SMP 515-C-SSID Inspection Findings

.

Alterna tive l y, m a il the inf o rm ation to:

Lockheed Martin Aeronautics Com p any

86 South Cobb Drive

Departm e nt 3E1M, Zone 0591

Marietta, GA 30063-0591, USA

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# SMP 515-C-SSID

SECTION 7

DISCREP ANCY RE PORTING

7.2 Reporting of Significan t Repairs

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

above address. This inf o rm ation will be used to determ ine if additiona l inspection requirem e nts

are neces sary to adequately addres s the inspectio n of the PSE. Future rev i sions to this SMP will

include incorporation of PSE in spection requirements for repairs, alterations and m odi fications.

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# SMP 515-C-SSID

SECTION 8

INSPECTION ZONE DESCRIPTION

Zone No. A R E A

100 LOWER F U SELAGE : In terior and exterior below flight deck floor and belo w cargo

floor, forward of ramp hinge bulkhea d.

110 Nose to FS 93: Includes area forward of canted bulkhead, ra dome 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.

1 2 1 B a t t e r y c o m p a r t m e n t

.

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 u nder cargo floor aft to ra mp hinge

bulkhead.

200 UPPE R FUSELAGE : In terior and exterior above f light 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 bulkh ead and abo ve 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 e quipment mounted on fr ont and

rear center wing beams.

231 Left Wing Fil l et Area: Incl udes area u nder leading edge fillet, under wing and

trailing edge fillets, and upper wheel well.

232 Right Wing Fillet Area: I n cludes are a under lead ing edge fil l e t, under wing and

trailing edge fillets, and upper wheel well.

2 3 3 G T C / A P U Compartment

.

234 Cargo Air Conditioner Compartment

.

235 Left Aft Main Landing Gear Fairing: Includes a i r deflector do or, where installed,

and equipment behind it

.

236 Right Aft Ma in Landing Gear Fairing: Includes S P R Panel, air deflector d oor,

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): Abo v e ramp and cargo doors.

251 Left Aft Fuselage: Inclu des area ab ove ramp an d cargo doo rs outboard of LBL

61.625.

252 Right Aft Fuselage: Includes area a bove ramp a nd cargo do ors outboar d of RBL

61.625.

253 Center Aft Fuselage: Includes area a bove ramp a nd cargo do ors.



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# SMP 515-C-SSID

SECTION 8

INSPECTION ZONE DESCRIPTION

Zone No. A R E A

260 Wing Root Fillets, includ es removabl e fillets.

261 Left Forward Wing Fillet

.

262 Right Forward Wing Fille t.

263 Left Under Wing Fillet.

264 Right Under Wing Fillet.

265 Left Aft Wing Fillet.

266 Right Aft Wing Fillet.

270 Fuselage Fu el Tank (Aer ial Refueling ) (Not shown).

300 EM PEN NAG E : Horizon t al Stabilizer, including t a il cone and elevators and vertical

fin, dorsal f i n and rudder.

310 Dorsal Fin, FS 759 to FS 946 above the fusela ge.

320 Vertical Sta b ilizer: FS 9 46 aft to tip of rudder above Horizontal Stabilizer.

321 Vertical Sta b ilizer Lead i ng Edge.

322 Vertical Sta b ilizer Main Structure: Includes ti p.

323 Rudder: Includes trim tab.

324 HF antenna and access (where installed).

325 VOR antenn a and access (where installed).

330 Horizontal fin: FS 1041 to FS 1138.

331 Left Horizon t al Stabilizer Leading Edge.

332 Right Horizontal Stabilizer Leading Edge.

333 Horizontal Stabilizer Box Beam, Fron t spar to rea r spar and a ft to

FS 1138, Includes Tip s

.

334 Strakes (where installed )

.

3 3 5 L e f t E l e v a t o r

.

3 3 6 R i g h t E l e v a t o r

.

340 Tail Cone: F S 1138 to FS 1202.1.

400 POWE R PL ANTS : Includes propelle r and QEC f o rward of ve rtical 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: In cludes area aft of vertical firewall, below horizont al

firewall and aft nacelle f a iring on wing.

420 Number 2 Power Plant.



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# SMP 515-C-SSID

SECTION 8

INSPECTION ZONE DESCRIPTION

Zone No. A R E A

421 Number 2 Propeller.

422 Number 2 Quick Engine Change (QEC) Unit.

423 Number 2 Aft Nacelle: In cludes area aft of vertical firewall, below horizont al

firewall and aft nacelle f a iring on wing.

430 Number 3 Power Plant.

431 Number 3 Propeller.

432 Number 3 Quick Engine Change (QEC) Unit.

433 Number 3 Aft Nacelle: In cludes area aft of vertical firewall, below horizont al

firewall and aft nacelle f a iring on wing.

440 Number 4 Power Plant.

441 Number 4 Propeller.

442 Number 4 Quick Engine Change (QEC) Unit.

443 Num ber 4 Aft Nacelle: Includes area aft of v e rtical firewall, below

horizontal f i rewall and af t nacelle fa ir ing on wing.

500 LEFT WING : Includes o u ter 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 Leadin g Edge.

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

and CWS 178 to CWS 220.

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

CWS 108.

514 Left Aux iliary Fuel C e ll: Front beam to rear beam

, C W S 108 to C W S

178.

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

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

517 Left Center Wing Flap.

520 Left Outer Wing Leadin g Edge: To front beam, OWS 0 to wi ng tip (OWS 562.5).

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

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

OWS 144.5 to OWS 214 .2.

523 Left Outer Wing Leadin g Edge: To front beam, OWS 214.2 to wing tip ( O WS

562.5).

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

531 Number 2 Main Fuel Tan k: Front to r ear beam, OWS 0 to OW S 144.5.

532 Number 1 Dry Ba y: Front to rear beam, OWS 14 4.5 to OWS 214.2.



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# SMP 515-C-SSID

SECTION 8

INSPECTION ZONE DESCRIPTION

Zone No. A R E A

533 Number 1 Main Fuel Tan k: Front to r ear beam, OWS 214.2 to tip

(OWS 562.5 )

.

534 Left Wing Tip.

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

563.0).

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

Station 0 to Aileron Station 0.

542 Left Outer Wing Trailin g Edge: Rear beam to trailing edge, Aileron Stati on 0 to

OWS 563.0.

543 Left Outer Wing Flap.

5 4 4 L e f t Aileron.

550 Left Pylon Tank: Include s pylon (where installed )

.

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

600 RIGHT WI N G : Includes outer wing, center wing inside fu sela ge, flaps, aileron,

pylons external tank.

610 Right Center Wing: CWS 0 to CWS 220.

611 Right Center Wing Lead ing Edge.

612 Number 3 “Horsecollar” : Front beam to vertical firewall abo ve 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 10 8 to

CWS 178.

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

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

CWS 84.3 to CWS 220.

617 Right Center Wing Flap.

620 Right Outer Wing Leadin g Edge: To front beam, OWS 0 to W i ng tip (OWS 562.5).

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

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

OWS 144.5 to OWS 214 .2.

623 Right Outer Wing Leadin g Edge: To front beam, OWS 214.2 to wing tip ( O WS

562.5).

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

562.5).

631 Number 3 Main Fuel Tan k: Front to r ear beam, OWS to CWS 144.5.

632 Number 4 Dry Ba y: Front to rear beam, OWS 14 4.5 to OWS 214.2.



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# SMP 515-C-SSID

SECTION 8

INSPECTION ZONE DESCRIPTION

Zone No. A R E A

633 Number 4 Main Fuel Tan k: Front to r ear beam, OWS 214.2 to tip

(OWS 562.5 ) . 634 Right Wing Tip.

634 Right Wing Tip.

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

563.0).

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

Station 0 to Aileron Station 0.

642 Right Outer Wing Trailin g Edge: Rear beam to trailing edge, Aileron Stati on 0 to

OWS 563.0.

643 Right Outer Wing Flap.

6 4 4 R i g h t A i l e r o n

.

650 Right Pylon Tank: Includ es pylon (where installe d).

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

700 LANDIN G GEA R AN D LANDIN G GEA R D O ORS : Includes nose and main

landing gear wheels, nose and main landing gear, and nose a nd main landing

gear doors.

710 Nose Landing Gear and Doors.

711 Nose Landing Gear Assembly: Includes actuator , struts, whe e ls and tire s.

712 Forward No se Landing Gear Door.

713 Aft Nose Landing Gear Door.

714 Nose Landing Gear Wheel Well Co mpartment.

720 Left MLG an d Doors.

721 Left Forward MLG Asse mbly: Includes strut, wh eel, brake a nd tire.

722 Left Aft MLG Assembly: Includes st rut, wheel, brake and tire

.

723 Left Torque Strut.

724 Left Outboard MLG Door.

725 Left Inboard MLG Door.

726 Left MLG W heel Well C o mpartment : Includes a c tuator scre w s, motor, gear box

and ATM where installe d.

730 Right MLG and Doors.

731 Right Forward MLG Ass e mbly: Includes strut, w heel, brake and tire.

732 Right Aft ML G Assembly: Includes st rut, wheel, brake and tire

.

733 Right Torque Strut.

734 Right Outboard MLG Do or.

735 Right Inboard MLG Door.



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# SMP 515-C-SSID

SECTION 8

INSPECTION ZONE DESCRIPTION

Zone No. A R E A

736 Right MLG Wheel Well Compart m e n t: Includes actuator scr ews, motor, and

gearbox.

800 DOORS: In cludes crew entry door, aft entry doors, ramp and cargo doo rs and

emergency exits.

8 1 0 C r e w Entry D o o r

.

820 Left Aft Entry Door (whe re installed).

830 Right Aft Entry Door (wh e re installed )

.

831 Emergency exits (Left side fuselage)

.

831 Emergency exit flight sta t ion top.

831 Emergency exit aft fuselage top.

8 4 0 R a m p

.

841 Emergency exits (Right side fuse lag e ).

841 Emergency exit center fuselage top.

8 5 0 C a r g o Door.



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# SMP 515-C-SSID

SECTION 8

INSPECTION ZONE DESCRIPTION

(Sheet 1 of 12)

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# SMP 515-C-SSID

SECTION 8

INSPECTION ZONE DESCRIPTION

(Sheet 2 of 12)

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U s e an d/or di scl os ur e i s g o v e r ned by state m e n t o n th e ti tl e pag e o f t h i s doc u m e nt.

# SMP 515-C-SSID

SECTION 8

INSPECTION ZONE DESCRIPTION

(Sheet 3 of 12)

8-9

Change 1 - 10 September 2007

U s e an d/or di scl os ur e i s g o v e r ned by state m e n t o n th e ti tl e pag e o f t h i s doc um ent.

# SMP 515-C-SSID

SECTION 8

INSPECTION ZONE DESCRIPTION

(Sheet 4 of 12)

8-10

Change 1 - 10 September 2007

U s e an d/or di scl os ur e i s g o v e r ned by state m e n t o n th e ti tl e pag e o f t h i s doc u m e nt.

# SMP 515-C-SSID

SECTION 8

INSPECTION ZONE DESCRIPTION

(Sheet 5 of 12)

8-11

Change 1 - 10 September 2007

U s e an d/or di scl os ur e i s g o v e r ned by state m e n t o n th e ti tl e pag e o f t h i s doc um ent.

# SMP 515-C-SSID

SECTION 8

INSPECTION ZONE DESCRIPTION

(Sheet 6 of 12)

8-12

Change 1 - 10 September 2007

U s e an d/or di scl os ur e i s g o v e r ned by state m e n t o n th e ti tl e pag e o f t h i s doc u m e nt.

# SMP 515-C-SSID

SECTION 8

INSPECTION ZONE DESCRIPTION

(Sheet 7 of 12)

8-13

Change 1 - 10 September 2007

U s e an d/or di scl os ur e i s g o v e r ned by state m e n t o n th e ti tl e pag e o f t h i s doc um ent.

# SMP 515-C-SSID

SECTION 8

INSPECTION ZONE DESCRIPTION

(Sheet 8 of 12)

8-14

Change 1 - 10 September 2007

U s e an d/or di scl os ur e i s g o v e r ned by state m e n t o n th e ti tl e pag e o f t h i s doc u m e nt.

# SMP 515-C-SSID

SECTION 8

INSPECTION ZONE DESCRIPTION

(Sheet 9 of 12)

8-15

Change 1 - 10 September 2007

U s e an d/or di scl os ur e i s g o v e r ned by state m e n t o n th e ti tl e pag e o f t h i s doc um ent.

# SMP 515-C-SSID

SECTION 8

INSPECTION ZONE DESCRIPTION

(Sheet 10 of 12)

8-16

Change 1 - 10 September 2007

U s e an d/or di scl os ur e i s g o v e r ned by state m e n t o n th e ti tl e pag e o f t h i s doc u m e nt.

# SMP 515-C-SSID

SECTION 8

INSPECTION ZONE DESCRIPTION

(Sheet 11 of 12)

8-17

Change 1 - 10 September 2007

U s e an d/or di scl os ur e i s g o v e r ned by state m e n t o n th e ti tl e pag e o f t h i s doc um ent.

# SMP 515-C-SSID

SECTION 8

INSPECTION ZONE DESCRIPTION

8-18

Change 1 - 10 September 2007

U s e an d/or di scl os ur e i s g o v e r ned by state m e n t o n th e ti tl e pag e o f t h i s doc u m e nt. 

# (Sheet 12 of 12)