Commercial 

Airplanes MD80

Service Bulletin

ALERT

Number: MD80-55A070

Original Issue: May 22, 2013

Revision 1: December 17, 2013

ATA System: 5510

SUBJECT: STABILIZERS - Horizontal Stabilizer - Inspect/Replace Upper Rear Spar Cap at Aft

Barrel Nut Holes

Export of this technology is controlled under the United States Export Administration Regulations (EAR) (15

CFR 300-774). An export license may be required before it is used for development, production or use by foreign

persons from specific countries. The controller of this data has the individual responsibility to abide by all export

laws.

ECCN: 9E991

BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET

Copyright © 2013 Boeing.

Unpublished Work. All Rights Reserved.

Treatment of this document and its content is governed by contract with Boeing. Rights to use this document

are licensed on a per aircraft basis and such rights may not be transferable. For more information, contact The

Boeing Company.

Boeing, the Boeing signature, the Boeing symbol, 707, 717, 727, 737, 747, 757, 767, 777, 787, Dreamliner,

BBJ, DC-8, DC-9, DC-10, KC-10, KC-46, KDC-10, MD-10, MD-11, MD-80, MD-88, MD-90, P-8, Poseidon and

Boeing liveries are all trademarks owned by The Boeing Company; and no trademark license is granted in

connection with this document unless provided in writing by Boeing.

Original Issue: May 22, 2013

Revision 1: December 17, 2013 MD80-55A070

1 of 53

3.0
Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: May 22, 2013

Revision 1: December 17, 2013 MD80-55A070

2 of 53

BOEING SERVICE BULLETIN MD80-55A070

ALERT ALERT

BLANK PAGE
Table of Contents

Revision Transmittal Sheet ............................................ 5

Summary ...................................................... 7

1. PLANNING INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11

A. Effectivity . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11

1. Airplanes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11

2. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

B. Concurrent Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16

C. Reason . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16

D. Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16

E. Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22

G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22

H. Weight and Balance Changes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25

I. Electrical Load Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25

J. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25

1. Existing Data: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25

2. Data Supplied with this Service Bulletin: . . . . . . . . . . . . . . . . . . . . . . . . . . . 25

3. Installation Drawings Used in the Preparation of this Service Bulletin: . . . . . . . . . . . 26

4. Process Data: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 26

K. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 26

L. Interchangeability and Intermixability of Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . 26

M. Software Accomplishment Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 26

2. MATERIAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27

A. Material - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27

B. Industry Support Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27

C. Parts Necessary for Each Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27

1. Kits/Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27

2. Parts and Materials Supplied by the Operator . . . . . . . . . . . . . . . . . . . . . . . . 36

3. Parts Modified and Reidentified . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 36

4. Parts Removed and Not Replaced . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 36

D. Parts Necessary to Change Spares . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 37

E. Special Tooling - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 37

F. Special Tooling Necessary to do this Service Bulletin . . . . . . . . . . . . . . . . . . . . . . . 37

3. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 39

A. GENERAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 39

B. WORK INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 40

FIGURE 1: REMOVE SKIN FILLER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 45

FIGURE 2: INSPECTION SURFACE AREA - PREPARATION . . . . . . . . . . . . . . . . . . . . . . 48

FIGURE 3: HIGH FREQUENCY EDDY CURRENT INSPECTION . . . . . . . . . . . . . . . . . . . . 51

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: May 22, 2013

Revision 1: December 17, 2013 MD80-55A070

3 of 53

BOEING SERVICE BULLETIN MD80-55A070

ALERT ALERT
Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: May 22, 2013

Revision 1: December 17, 2013 MD80-55A070

4 of 53

BOEING SERVICE BULLETIN MD80-55A070

ALERT ALERT

BLANK PAGE
Commercial 

Airplanes MD80

Service Bulletin

ALERT

Revision Transmittal Sheet Number: MD80-55A070

Original Issue: May 22, 2013

Revision 1: December 17, 2013

ATA System: 5510

SUBJECT: STABILIZERS - Horizontal Stabilizer - Inspect/Replace Upper Rear Spar Cap at Aft

Barrel Nut Holes

This revision includes all pages of the service bulletin.

COMPLIANCE INFORMATION RELATED TO THIS REVISION

The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to this service

bulletin. The Airworthiness Directive will make the compliance tasks and times given in this service bulletin

mandatory.

No more work is necessary on the airplane(s) changed or inspected in accordance with the original issue of this

service bulletin.

REASON FOR REVISION

Revision 1 is sent to correct Paragraph 1.E., Compliance Tables 1 and 2 group configuration headings and

Table 1 initial inspections thresholds.

Terminology has been changed in the Work Instructions to agree with the terminology defined in Paragraph

3.A., General Information - Notes.

These sections were changed:

1. In Paragraph 1.E., Compliance, changed Table 1 and Table 2 group configuration headings and Table

1 initial inspection thresholds.

2. Figure 2, changed art and split footnote (a) into footnote (a) and (b).

3. Figure 3, changed art and footnoe (c).

Vertical lines are put on the left edge of each page, except in Paragraph 1.A., Effectivity and format changes,

to show the location of all content changes.

Pages with no vertical lines have no changes.

REVISION HISTORY

Original Issue: May 22, 2013

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: May 22, 2013

Revision 1: December 17, 2013 MD80-55A070

5 of 53
Revision 1: December 17, 2013

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: May 22, 2013

Revision 1: December 17, 2013 MD80-55A070

6 of 53

BOEING SERVICE BULLETIN MD80-55A070

ALERT ALERT
Commercial 

Airplanes MD80

Service Bulletin

ALERT

Summary Number: MD80-55A070

Original Issue: May 22, 2013

Revision 1: December 17, 2013

ATA System: 5510

SUBJECT: STABILIZERS - Horizontal Stabilizer - Inspect/Replace Upper Rear Spar Cap at Aft

Barrel Nut Holes

THIS BULLETIN IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN PARAGRAPH

1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS SERVICE BULLETIN TO

THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE BULLETIN TO

THE NEW OWNER.

CONCURRENT REQUIREMENTS

None

BACKGROUND

During the inspections called for in Service Bulletin MD80-55A065, two operators reported finding cracks

emanating from the left and right upper rear spar cap aft-most barrel nut holes of the horizontal stabilizer. One

airplane had accumulated 40,144 flight hours and 32,253 landing cycles, while the other airplane had accumulated

58,296 flight hours and 43,512 landing cycles. In both cases, the affected part was removed from the airplane

and submitted to Boeing for evaluation. Investigation by Boeing has determined that the cracks are caused by

fatigue. In both cases, the cracks originated inside the barrel nut holes, and radiated vertically and in the aft

direction from the barrel nut holes. If not corrected, these cracks may propagate until it severs the upper rear

spar cap which may result in the failure of the horizontal stabilizer upper center or aft skin panel, adversely

affecting the structural integrity of the airplane.

Boeing Fleet Team Digest (FTD) MD-80 FTD 55-12002 is related to this service bulletin.

ACTION

This service bulletin provides instructions to perform a High Frequency Eddy Current (ETHF) inspection on the

left and right upper rear spar cap aft-most barrel nut holes for crack(s), and does as follows:

Group 1, Configuration 1, 3:

Condition 1 - No Crack Found

Repeats ETHF inspection at defined intervals.

Condition 2 - Any Crack Found

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: May 22, 2013

Revision 1: December 17, 2013 MD80-55A070

7 of 53
NOTE: Both Options affect the inspection requirements contained in Service Bulletin MD80-55A065, and will

affect compliance with Federal Aviation Administration Airworthiness Directive AD 2007-10-04 as it

relates to the upper rear spar cap. Operators are urged to consider both this service bulletin and Service

Bulletin MD80-55A065 while choosing an option.

Option 1

1) Does a splice repair of the horizontal stabilizer upper rear spar cap.

2) Repeats ETHF inspection at defined intervals until replacement of upper rear spar cap.

Option 2

1) Replaces the horizontal stabilizer upper rear spar cap.

2) Repeats ETHF inspection at defined intervals.

Group 1, Configuration 2, 4:

Condition 1 - No Crack Found

Repeats ETHF inspection at defined intervals.

Condition 2 - Any Crack Found

NOTE: Both Options affect the inspection requirements contained in Service Bulletin MD80-55A065, and will

affect compliance with FAA AD 2007-10-04 as it relates to the upper rear spar cap. Operators are urged

to consider both this service bulletin and Service Bulletin MD80-55A065 while choosing an option.

Option 1

1) Does a splice repair of the horizontal stabilizer upper rear spar cap.

2) Installs new Forcemate bushing

3) Repeats ETHF inspection at defined intervals until replacement of upper rear spar cap.

Option 2

1) Replaces the horizontal stabilizer upper rear spar cap.

2) Installs new Forcemate bushing

3) Repeats ETHF inspection at defined intervals.

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: May 22, 2013

Revision 1: December 17, 2013 MD80-55A070

8 of 53

BOEING SERVICE BULLETIN MD80-55A070

ALERT ALERT
EFFECTIVITY

All DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83), DC-9-87 (MD-87), MD-88 Airplane(s). Refer to

Paragraph 1.A.1., Airplanes, for the list of affected airplane(s).

COMPLIANCE

The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to this service

bulletin. The Airworthiness Directive will make the compliance tasks and times given in this service bulletin

mandatory.

Refer to Paragraph 1.E., Compliance.

INDUSTRY SUPPORT INFORMATION

Boeing warranty remedies are not available for the inspection and/or repair procedures given in this service

bulletin.

MANPOWER

Refer to Paragraph 1.G., Manpower.

MATERIAL INFORMATION

Boeing Supplied Kits/Parts.

Refer to Paragraph 2.A., Material - Price and Availability.

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: May 22, 2013

Revision 1: December 17, 2013 MD80-55A070

9 of 53

BOEING SERVICE BULLETIN MD80-55A070

ALERT ALERT
Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: May 22, 2013

Revision 1: December 17, 2013 MD80-55A070

10 of 53

BOEING SERVICE BULLETIN MD80-55A070

ALERT ALERT
Commercial 

Airplanes MD80

Service Bulletin

ALERT

Number: MD80-55A070

Original Issue: May 22, 2013

Revision 1: December 17, 2013

ATA System: 5510

SUBJECT: STABILIZERS - Horizontal Stabilizer - Inspect/Replace Upper Rear Spar Cap at Aft

Barrel Nut Holes

THIS BULLETIN IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN PARAGRAPH

1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS SERVICE BULLETIN TO

THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE BULLETIN TO

THE NEW OWNER.

1. PLANNING INFORMATION

A. Effectivity

1. Airplanes

This service bulletin is for the airplanes shown below.

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: May 22, 2013

Revision 1: December 17, 2013 MD80-55A070

11 of 53
GROUP CONFIGURATION DESCRIPTION

1 - All Airplanes

Airplanes Not Having Accomplished an Upper Rear Spar Cap Splice

Repair or Upper Rear Spar Cap Replacement in Accordance With

Service Bulletin MD80-55A065 or other service action

1

Airplanes Not Having Accomplished an Upper Rear Spar Cap Splice

Repair or Upper Rear Spar Cap Replacement And Having Forcemate

Bushings Installed in Spar Web in Accordance With Service Bulletin

MD80-55A065 Revision 1 or other service action

2

Airplanes Having Accomplished an Upper Rear Spar Cap Splice

Repair or Upper Rear Spar Cap Replacement in Accordance With

Service Bulletin MD80-55A065 or other service action

3

Airplanes Having Accomplished an Upper Rear Spar Cap Splice

Repair or Upper Rear Spar Cap Replacement And Having Forcemate

Bushings Installed in Spar Web in Accordance With Service Bulletin

MD80-55A065 Revision 1 or other service action

4

Airplane Models:

DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83), DC-9-87 (MD-87), MD-88

Fuselage Num- Group

ber

909 1

917 1

924 1

938 1

941 1

944 1

946 1

948 1

950 1

952 - 953 1

955 1

957 - 958 1

960 1

962 - 963 1

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: May 22, 2013

Revision 1: December 17, 2013 MD80-55A070

12 of 53

BOEING SERVICE BULLETIN MD80-55A070

ALERT ALERT
Fuselage Num- Group

ber

965 - 967 1

969 1

970 - 971 1

973 - 975 1

977 - 979 1

981 1

983 1

985 - 986 1

988 - 989 1

991 - 992 1

994 - 999 1

1000 - 1013 1

1015 - 1016 1

1018 - 1020 1

1022 - 1023 1

1025 - 1026 1

1028 - 1029 1

1031 - 1032 1

1034 - 1035 1

1037 - 1038 1

1040 - 1041 1

1043 1

1045 1

1047 1

1049 1

1051 1

1053 1

1055 1

1057 1

1059 - 1080 1

1082 - 1083 1

1085 - 1099 1

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: May 22, 2013

Revision 1: December 17, 2013 MD80-55A070

13 of 53

BOEING SERVICE BULLETIN MD80-55A070

ALERT ALERT
Fuselage Num- Group

ber

1100 - 1199 1

1200 - 1299 1

1300 - 1399 1

1400 - 1499 1

1500 - 1599 1

1600 - 1699 1

1700 - 1799 1

1800 - 1899 1

1900 - 1999 1

2000 - 2007 1

2009 - 2016 1

2019 - 2034 1

2036 - 2069 1

2071 - 2093 1

2101 - 2114 1

2116 1

2118 - 2119 1

2121 1

2124 1

2127 - 2128 1

2130 1

2132 1

2134 - 2135 1

2137 1

2139 1

2145 1

2148 1

2151 - 2152 1

2155 1

2167 1

2174 1

2176 1

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: May 22, 2013

Revision 1: December 17, 2013 MD80-55A070

14 of 53

BOEING SERVICE BULLETIN MD80-55A070

ALERT ALERT
Fuselage Num- Group

ber

2178 1

2180 1

2183 1

2185 1

2187 1

2189 1

2192 1

2196 1

2199 1

2201 1

2204 1

2206 1

2208 1

2214 1

2218 1

2234 1

2239 1

2241 1

2244 1

2247 1

2249 1

2252 1

2254 1

2264 - 2287 1

2. Spares Affected

Examine your spares supply for the parts or components identified below. If any parts or components

are found, refer to Paragraph 3.B., Work Instructions for the recommended action.

Part Number

5930603-(xxx) Stabilizer Assembly, Complete

(xxx) denotes any configuration.

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: May 22, 2013

Revision 1: December 17, 2013 MD80-55A070

15 of 53

BOEING SERVICE BULLETIN MD80-55A070

ALERT ALERT
B. Concurrent Requirements

None.

C. Reason

During the inspections called for in Service Bulletin MD80-55A065, two operators reported finding

cracks emanating from the two upper rear spar cap aft-most barrel nut holes of the horizontal stabilizer.

One airplane had accumulated 40,144 flight hours and 32,253 landing cycles, while the other airplane

had accumulated 58,296 flight hours and 43,512 landing cycles. In both cases, the affected part was

removed from the airplane and submitted to Boeing for evaluation. Investigation by Boeing has

determined that the cracks are caused by fatigue. In both cases, the cracks originated inside the barrel

nut holes, and radiated vertically and in the aft direction from the barrel nut holes. If not corrected, these

cracks may propagate until it severs the upper rear spar cap which may result in the failure of the

horizontal stabilizer upper center or aft skin panel, adversely affecting the structural integrity of the

airplane.

Boeing Fleet Team Digest (FTD) MD-80 FTD 55-12002 is related to this service bulletin.

Revision 1 is sent to correct Paragraph 1.E., Compliance Tables 1 and 2 group configuration headings

and Table 1 initial inspections thresholds.

D. Description

This service bulletin provides instructions to perform a High Frequency Eddy Current (ETHF) inspection

on the left and right upper rear spar cap aft-most barrel nut holes for crack(s), and does as follows:

Group 1, Configuration 1, 3:

Condition 1 - No Crack Found

Repeats ETHF inspection at defined intervals.

Condition 2 - Any Crack Found

NOTE: Both Options affect the inspection requirements contained in Service Bulletin MD80-55A065,

and will affect compliance with Federal Aviation Administration Airworthiness Directive AD

2007-10-04 as it relates to the upper rear spar cap. Operators are urged to consider both this

service bulletin and Service Bulletin MD80-55A065 while choosing an option.

Option 1

1) Does a splice repair of the horizontal stabilizer upper rear spar cap.

2) Repeats ETHF inspection at defined intervals until replacement of upper rear spar cap.

Option 2

1) Replaces the horizontal stabilizer upper rear spar cap.

2) Repeats ETHF inspection at defined intervals.

Group 1, Configuration 2, 4:

Condition 1 - No Crack Found

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: May 22, 2013

Revision 1: December 17, 2013 MD80-55A070

16 of 53

BOEING SERVICE BULLETIN MD80-55A070

ALERT ALERT
Repeats ETHF inspections at defined intervals.

Condition 2 - Any Crack Found

NOTE: Both Options affect the inspection requirements contained in Service Bulletin MD80-55A065,

and will affect compliance with FAA AD 2007-10-04 as it relates to the upper rear spar cap.

Operators are urged to consider both this service bulletin and Service Bulletin MD80-55A065

while choosing an option.

Option 1

1) Does a splice repair of the horizontal stabilizer upper rear spar cap.

2) Installs new Forcemate bushing

3) Repeats ETHF inspection at defined intervals until replacement of upper rear spar cap.

Option 2

1) Replaces the horizontal stabilizer upper rear spar cap.

2) Installs new Forcemate bushing

3) Repeats ETHF inspection at defined intervals.

No more work is necessary on the airplane(s) changed or inspected in accordance with the original

issue of this service bulletin.

The work in this service bulletin is done in the maintenance zone(s) given below.

Affected Maintenance Zones

Model Zone

DC-9-81 (MD-81), DC-9-82 33, 34

(MD-82), DC-9-83 (MD-83), DC9-87 (MD-87), MD-88

E. Compliance

The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to

this service bulletin. The Airworthiness Directive will make the compliance tasks and times given in this

service bulletin mandatory.

When more than one OPTION is given for a CONDITION, do only one of the OPTION numbers. When

more than one ACTION is given for a CONDITION number or an OPTION number, do all of the ACTION

numbers for that CONDITION number or OPTION number.

Accomplish the required action(s), based on the applicable condition(s), in Tables 1 or 2, in accordance

with Paragraph 3. Accomplishment Instructions.

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: May 22, 2013

Revision 1: December 17, 2013 MD80-55A070

17 of 53

BOEING SERVICE BULLETIN MD80-55A070

ALERT ALERT
Group 1, Configuration 1-2:

Table 1: Airplanes Not Having Accomplished an Upper Rear Spar Cap Splice Repair or Upper Rear Spar

Cap Replacement Barrel Nut Hole Inspection

Repeat Interval

(Not to Exceed)

Compliance Time (Whichever

Occurs Later )

Condition Action

Within 2,768 -

flight cycles after the original

issue date of

this service bulletin.

Before 22,000

total flight cycles.

Do Eddy Current, High

Frequency (ETHF) inspection of left and right upper

rear spar caps at the two

aft-most barrel nut holes

and do the work of the

applicable condition that

follows:

All Airplanes not having

accomplished an upper

rear spar cap splice repair

or upper rear spar cap replaced in accordance with

Service Bulletin MD80-

55A065 or other service

action

Do Eddy Current, High - - 4,500 flight cycles.

Frequency (ETHF) inspection of left and right upper

rear spar caps at the two

aft-most barrel nut holes

Condition 1 (No Crack

Found) (a) (b)

(a) (b)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: May 22, 2013

Revision 1: December 17, 2013 MD80-55A070

18 of 53

BOEING SERVICE BULLETIN MD80-55A070

ALERT ALERT
Group 1, Configuration 1-2:

Table 1: Airplanes Not Having Accomplished an Upper Rear Spar Cap Splice Repair or Upper Rear Spar

Cap Replacement Barrel Nut Hole Inspection

Repeat Interval

(Not to Exceed)

Compliance Time (Whichever

Occurs Later )

Condition Action

Before further - -

flight.

Option 1

Splice repair the affected

upper aft spar cap.

Condition 2 (Any Crack

Found)

AND - - -

Before 22,000 - 4,500 flight cycles.

flight cycles after repair.

Do Eddy Current, High

Frequency (ETHF) inspection of the splice repaired

upper rear spar cap at the

two aft-most barrel nut

holes

(a) (b)

(a) (b)

AND - - -

Before 97,000 - -

flight cycles after repair.

Replace the spliced repaired horizontal stabilizer upper rear spar cap.

AND - - -

Before 22,000 - 4,500 flight cycles.

flight cycles after replacement.

Do Eddy Current, High

Frequency (ETHF) inspection of the replaced upper

rear spar cap at the two

aft-most barrel nut holes

(a) (b)

(a) (b)

OR

Before further - -

flight.

Option 2

Replace the horizontal

stabilizer upper rear spar

cap.

AND - - -

Before 22,000 - 4,500 flight cycles.

flight cycles after replacement.

Do Eddy Current, High

Frequency (ETHF) inspection of the replaced upper

rear spar cap at the two

aft-most barrel nut holes

(a) (b)

(a) (b)

(a) If any crack is found, do Option 1 or Option 2 before further flight.

(b) If no crack is found, repeat inspect upper aft spar caps at noted interval.

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: May 22, 2013

Revision 1: December 17, 2013 MD80-55A070

19 of 53

BOEING SERVICE BULLETIN MD80-55A070

ALERT ALERT
Group 1, Configuration 3-4:

Table 2: Airplanes Having Accomplished an Upper Rear Spar Cap Splice Repair or Upper Rear Spar

Cap Replacement Barrel Nut Hole Inspection

Repeat Interval

(Not to Exceed)

Compliance Time (Whichever

Occurs Later )

Condition Action

Before 22,000 - -

total flight cycles

after repair or

replacement.

Do Eddy Current, High

Frequency (ETHF) inspection of original upper rear

spar cap at the two aftmost barrel nut holes and

do the work of the applicable condition that follows:

All Airplanes having accomplished an upper rear spar

cap splice repair or upper

rear spar cap replaced in

accordance with Service

Bulletin MD80-55A065 or

other service action

Do Eddy Current, High - - 4,500 flight cycles.

Frequency (ETHF) inspection of left and right upper

rear spar cap at the two

aft-most barrel nut holes

Condition 1 (No Crack

Found) (a) (b)

(a) (b)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: May 22, 2013

Revision 1: December 17, 2013 MD80-55A070

20 of 53

BOEING SERVICE BULLETIN MD80-55A070

ALERT ALERT
Group 1, Configuration 3-4:

Table 2: Airplanes Having Accomplished an Upper Rear Spar Cap Splice Repair or Upper Rear Spar

Cap Replacement Barrel Nut Hole Inspection

Repeat Interval

(Not to Exceed)

Compliance Time (Whichever

Occurs Later )

Condition Action

Before further - -

flight.

Option 1

Splice repair the affected

upper aft spar cap.

Condition 2 (Any Crack

Found)

AND - - -

Before 22,000 - 4,500 flight cycles.

flight cycles after splice repair.

Do Eddy Current, High

Frequency (ETHF) inspection splice repaired upper

rear spar cap at the two

aft-most barrel nut holes

(a) (b)

(a) (b)

AND - - -

Before 97,000 - -

flight cycles after repair.

Replace the splice repaired horizontal stabilizer upper rear spar cap.

AND - - -

Before 22,000 - 4,500 flight cycles.

flight cycles after replacement.

Do Eddy Current, High

Frequency (ETHF) inspection of the replaced upper

rear spar cap at the two

aft-most barrel nut holes

(a) (b)

(a) (b)

OR

Before further - -

flight.

Option 2

Replace the affected horizontal stabilizer upper

rear spar cap.

AND - - -

Before 22,000 - 4,500 flight cycles.

flight cycles after replacement.

Do ETHF inspection of

the replaced upper rear

spar cap at the two aftmost barrel nut holes

(a) (b)

(a) (b)

(a) If any crack is found, do Option 1 or Option 2 before further flight.

(b) If no crack is found, repeat inspect upper aft spar caps at noted interval.

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: May 22, 2013

Revision 1: December 17, 2013 MD80-55A070

21 of 53

BOEING SERVICE BULLETIN MD80-55A070

ALERT ALERT
F. Approval

This service bulletin was examined by the Federal Aviation Administration (FAA). The changes specified

in this service bulletin comply with the applicable regulations and are FAA approved, as well as European

Aviation Safety Agency (EASA)/Joint Aviation Authorities (JAA) approved for all EASA/JAA approved

airplanes listed in the service bulletin effectivity. This service bulletin and its approval were based on

the airplane in its original Boeing delivery configuration or as modified by other approved Boeing

changes.

If an airplane has a non-Boeing modification or repair that affects a component or system also affected

by this service bulletin, the operator is responsible for obtaining appropriate regulatory agency approval

before incorporating this service bulletin.

G. Manpower

The table below shows an estimate of the task hours necessary to do this inspection (and repair, if

required) for each airplane. This estimate is for direct labor only, done by an experienced crew. Adjust

the estimate with operator task hour data if necessary. The estimate does not include lost time. These

are some examples of lost time:

• Time to adjust to the workplace

• Time to schedule the work

• Time to inspect the work

• Time to cure the materials

• Time to make the parts

• Time to find the tools.

Inspect Upper Rear Spar Aft Spar Cap Barrel Nut Holes

Task Number of Persons Task Hours Elapsed Hours

Open Access (FIG- 1 1.5 1.5

URE 1)

FIGURE 2 1 1.5 1.5

FIGURE 3

Close Access 1 1.5 1.5

TOTAL FOR EACH SPAR CAP 4.5 4.5

Group 1, Configuration 1, 3:

Option 1 - Upper Spar Cap Splice Repair

Task Number of Persons Task Hours Elapsed Hours

Remove - Horizon- 6 48.0 8.0

tal Stabilizer

Remove - Elevators 2 16.0 8.0

Remove - Leading 2 12.0 6.0

Edge

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: May 22, 2013

Revision 1: December 17, 2013 MD80-55A070

22 of 53

BOEING SERVICE BULLETIN MD80-55A070

ALERT ALERT
Group 1, Configuration 1, 3:

Option 1 - Upper Spar Cap Splice Repair

Task Number of Persons Task Hours Elapsed Hours

Install Horizontal 3 216.0 72.0

Stabilizer Rear Spar

Upper Cap Splice

Install - Leading 2 12.0 6.0

Edge

Install - Elevators 2 16.0 8.0

Install - Horizontal 6 48.0 8.0

Stabilizer

TOTAL FOR EACH SPAR CAP 368.0 116.0

Group 1, Configuration 2, 4:

Option 1 - Upper Spar Cap Splice Repair

Task Number of Persons Task Hours Elapsed Hours

Remove - Horizon- 6 48.0 8.0

tal Stabilizer

Remove - Elevators 2 16.0 8.0

Remove - Leading 2 12.0 6.0

Edge

Install Horizontal 3 216.0 72.0

Stabilizer Rear Spar

Upper Cap Splice

Install Bushing/Cold 2 26.0 13.0

Work Hole

Install - Leading 2 12.0 6.0

Edge

Install - Elevators 2 16.0 8.0

Install - Horizontal 6 48.0 8.0

Stabilizer

TOTAL FOR EACH SPAR CAP 394.0 129.0

Group 1, Configuration 1, 3:

Option 2 - Upper Spar Cap Replacement

Task Number of Persons Task Hours Elapsed Hours

Remove - Horizon- 6 48.0 8.0

tal Stabilizer

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: May 22, 2013

Revision 1: December 17, 2013 MD80-55A070

23 of 53

BOEING SERVICE BULLETIN MD80-55A070

ALERT ALERT
Group 1, Configuration 1, 3:

Option 2 - Upper Spar Cap Replacement

Task Number of Persons Task Hours Elapsed Hours

Remove - Elevators 2 16.0 8.0

Remove - Leading 2 12.0 6.0

Edge

Replace Horizontal 3 216.0 72.0

Stabilizer Rear Spar

Upper Cap

Install - Leading 2 12.0 6.0

Edge

Install - Elevators 2 16.0 8.0

Install - Horizontal 6 48.0 8.0

Stabilizer

TOTAL FOR EACH SPAR CAP 368.0 116.0

Group 1, Configuration 2, 4:

Option 2 - Upper Spar Cap Replacement

Task Number of Persons Task Hours Elapsed Hours

Remove - Horizon- 6 48.0 8.0

tal Stabilizer

Remove - Elevators 2 16.0 8.0

Remove - Leading 2 12.0 6.0

Edge

Replace Horizontal 3 216.0 72.0

Stabilizer Rear Spar

Upper Cap

Install Bushing/Cold 2 26.0 13.0

Work Hole

Install - Leading 2 12.0 6.0

Edge

Install - Elevators 2 16.0 8.0

Install - Horizontal 6 48.0 8.0

Stabilizer

TOTAL FOR EACH SPAR CAP 394.0 129

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: May 22, 2013

Revision 1: December 17, 2013 MD80-55A070

24 of 53

BOEING SERVICE BULLETIN MD80-55A070

ALERT ALERT
H. Weight and Balance Changes

Condition 2, Option 1 Only

Moment

Change (MEW)

IN.-LBS

Mfr's Empty

Weight (MEW)

LBS

Approximate

Station (Inches)

Configuration Airplane

DC-9-81 (MD-81) 1660.1 +3.2 +5312.3

DC-9-82 (MD-82)

DC-9-83 (MD-83)

MD-88

SR09550027-7001

or

SR09550027-7003

or

SR09550027-7013

or

SR09550027-7015

SR09550027-7001 DC-9-87 (MD-87) 1451.1 +3.2 +4643.5

or

SR09550027-7003

or

SR09550027-7013

or

SR09550027-7015

Condition 2, Option 2 Only

None.

I. Electrical Load Data

Not changed.

J. References

1. Existing Data:

a. Boeing Service Bulletin MD80-55A065.

b. Federal Aviation Administration (FAA) Airworthiness Directive (AD) 2007-10-04.

c. Non-Destructive Test Standard Practices Manual (NDTSPM) 06-00-02, 06-10-01.001.

d. MD-80 Aircraft Maintenance Manual (AMM) 20-20-01, 27-30-02, 55-10-00, 55-10-01.

e. MD-80 Fleet Team Digest (FTD) 55-12002

f. MD-80 Structural Repair Manual (SRM) 51, 51-10-02, 51-10-03, 51-10-04, 51-20-00, 51-30-01,

51-30-02, 51-30-03, 51-30-05, 51-30-09, 51-30-11, 51-70-02.

2. Data Supplied with this Service Bulletin:

No data is supplied with this service bulletin. To obtain the data necessary to support this service

bulletin submit a data request to:

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: May 22, 2013

Revision 1: December 17, 2013 MD80-55A070

25 of 53

BOEING SERVICE BULLETIN MD80-55A070

ALERT ALERT
Data and Services Management

MS D800-0019

3855 Lakewood Boulevard

Long Beach, California 90846

Phone: (562) 593-6996

Fax: (562) 593-2001

E-mail: dse.boecom@boeing.com

a. Drawings:

Drawing No Title Sheet DCN/REV ADCN

SR09550027 Rear Spar Repair - Inboard Upper DWG E -

SR09550030 Rear Spar Replacement Horizontal DWG C -

SR09550032 Fatigue Life Enhancement - Upper Rear DWG B -

3. Installation Drawings Used in the Preparation of this Service Bulletin:

Drawing Number Title Change

Structural Assembly - Horizontal Stabilizer Outer Panel, Front DD

Spar to Rear Spar

5922575

5930603 Stabilizer Assembly - Complete Horizontal BJ

9918401 Spar Assembly - Horizontal Stabilizer, Rear DC

4. Process Data:

Douglas Process Specifications referred to on the drawings are not given in this service bulletin

since these procedures are frequently used as standard shop practices.

K. Publications Affected

1. Publications:

None.

2. Damage Tolerance Based Structural Inspections:

Boeing has evaluated the repairs and/or changes in this service bulletin for effects on Fatigue

Critical Structure (FCS) and for changes to Damage Tolerance Inspections (DTI) required in the

Maintenance Program. This service bulletin affects FCS. DTI requirements for the structure affected

are contained in Paragraph 1.E., Compliance of this service bulletin.

L. Interchangeability and Intermixability of Parts

Accomplishment of this service bulletin does not affect interchangeability or intermixability of parts.

M. Software Accomplishment Summary

Not affected.

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: May 22, 2013

Revision 1: December 17, 2013 MD80-55A070

26 of 53

BOEING SERVICE BULLETIN MD80-55A070

ALERT ALERT
2. MATERIAL INFORMATION

A. Material - Price and Availability

Boeing can supply the kits/parts shown in Paragraph 2.C., Parts Necessary for Each Airplane. Operators

are encouraged to share schedule requirements with Boeing for incorporation of the service bulletin.

The kits are subject to the terms and conditions of the Boeing standard purchase order acknowledgment.

Prices are in United States Dollars. Terms: Net 30 days.

Reference this service bulletin and submit your purchase order by one of these methods:

1. Order on-line via ATA Spec 2000 or The Boeing PART Page

2. Fax to (206) 662-7145

REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER

AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION

Unit Price as of

the Original Issue

of this Service

Bulletin (US Dollars)

ROLT as of the

Original Issue of

this Service Bulletin (Calendar

Days)

Kit Number Name Date QTY

SA09550070-3 SERVICE KIT June 15, 2013 1 90 $3,014.00

FULL SPAR SPLICE June 15, 2013 1 90 $32,440.00

KIT - UPPER LEFT

SA09550065-3

FULL SPAR SPLICE June 15, 2013 1 90 $29,304.00

KIT - UPPER RIGHT

SA09550065-5

FULL SPAR CAP RE- June 15, 2013 1 90 $60,222.00

PLACEMENT KIT -

UPPER LEFT

SA09550065-53

FULL SPAR CAP RE- June 15, 2013 1 90 $60,074.00

PLACEMENT KIT -

UPPER RIGHT

SA09550065-55

FORCEMATE BUSH- June 15, 2013 1 90 $1,269.00

ING KIT- NOMINAL

SA09550065-61

B. Industry Support Information

Boeing warranty remedies are not available for the inspection and/or repair procedures given in this

service bulletin.

C. Parts Necessary for Each Airplane

1. Kits/Parts

To get the kits/parts shown below, refer to Paragraph 2.A., Material - Price and Availability.

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: May 22, 2013

Revision 1: December 17, 2013 MD80-55A070

27 of 53

BOEING SERVICE BULLETIN MD80-55A070

ALERT ALERT
NOTE: One top kit and the items shown in Paragraph 2.C.2., Parts and Materials Supplied by

the Operator, are necessary based on inspection results and operators choice of the

required change.

Configuration and Option Parts Kits Required

All Configurations, All Conditions SA09550070-3

Configurations 1 and 3, Condition 2, Option 1 SA09550065-3 (Left Side)

SA09550065-5 (Right Side)

Configurations 2 and 4, Condition 2, Option 1 SA09550065-3 and SA09550065-61 (Left Side)

SA09550065-5 and SA09550065-61 (Right Side)

Configurations 1 and 3, Condition 2, Option 2 SA09550065-53 (Left Side)

SA09550065-55 (Right Side)

Configurations 2 and 4, Condition 2, Option 2 SA09550065-53 and SA09550065-61 (Left Side)

SA09550065-55 and SA09550065-61 (Right Side)

Group 1, Configuration 1, 3:

Condition 2, Option 1:

Kit SA09550065

New Part Number QTY Name Notes

-3 -5

SA09550065-7 1 - SPAR SPLICE KIT-LH (a)

SA09550065-9 - 1 SPAR SPLICE KIT-RH (b)

SR09550027-13 1 - SPAR CAP (STUB) (c)

SR09550027-14 - 1 SPAR CAP (STUB) (d)

(a) SA09550065-7 is a sub kit of SA09550065-3.

(b) SA09550065-9 is a sub kit of SA09550065-5.

(c) May be made from 5918000-526.

(d) May be made from 5918000-525.

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: May 22, 2013

Revision 1: December 17, 2013 MD80-55A070

28 of 53

BOEING SERVICE BULLETIN MD80-55A070

ALERT ALERT
Group 1, Configuration 2, 4:

Condition 2, Option 1:

Kit SA09550065

New Part Number QTY Name Notes

-3 -5 -61

7090-040 - - 2 BUSHING -

7090-043 - - 2 BUSHING -

HLT434-8-13 - - 1 HILOK -

HLT634-8-13 - - 1 PIN -

MS21042L4 - - 1 NUT -

NAS1252-416L - - 1 WASHER -

NAS620-416L - - 2 WASHER -

NAS6204-13 - - 2 BOLT -

NAS679A4 - - 2 NUT -

SA09550065-7 1 - - SPAR SPLICE KIT-LH (a)

SA09550065-9 - 1 - SPAR SPLICE KIT-RH (b)

SR09550027-13 1 - - SPAR CAP (STUB) (c)

SR09550027-14 - 1 - SPAR CAP (STUB) (d)

(a) SA09550065-7 is a sub kit of SA09550065-3.

(b) SA09550065-9 is a sub kit of SA09550065-5.

(c) May be made from 5918000-526.

(d) May be made from 5918000-525.

Group 1, Configuration 1, 3:

Condition 2, Option 2:

Kit SA09550065

Existing Part Notes

Number

New Part Number QTY Name

-53 -55

113LH7940T064 3 3 NUT - -

113LH7940T070 4 4 NUT - -

113LH7940T080 1 1 BARREL NUT - -

117LH7940T-098 2 2 NUT BARREL - -

3D0006-3 99 99 NUT ASSY - -

3D0006-4 5 5 NUT ASSY - -

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: May 22, 2013

Revision 1: December 17, 2013 MD80-55A070

29 of 53

BOEING SERVICE BULLETIN MD80-55A070

ALERT ALERT
Group 1, Configuration 1, 3:

Condition 2, Option 2:

Kit SA09550065

Existing Part Notes

Number

New Part Number QTY Name

-53 -55

3D0011-9 SUB SUB BARREL NUT - (a)

3D0012-9 SUB SUB RETAINER -

3D0031-9-34 2 2 BOLT - -

5918000-525 - 1 SPAR CAP 5918000-525 -

5918000-529

5918000-526 1 - SPAR CAP 5918000-526 -

5918000-530

73232-9-28.7 2 2 WASHER - -

HLT434-6-3 5 5 PIN - -

HLT434-6-4 72 72 PIN - -

HLT434-6-5 32 32 PIN - -

HLT434-6-6 18 18 PIN - -

HLT434-6-7 18 18 PIN - -

HLT434-6-8 25 25 PIN - -

HLT434-6-9 2 2 PIN - -

HLT434-6-11 5 5 PIN - -

HLT434-8-8 1 1 HILOK - -

HLT434-8-13 3 3 HILOK - -

HLT434-8-16 2 2 HILOK - -

HLT435-6-4 84 84 PIN - -

HLT435-6-5 77 77 PIN - -

HLT435-6-6 9 9 PIN - -

HLT435-6-7 13 13 PIN - -

HLT435-6-8 4 4 PIN - -

MS20002-5 2 2 WASHER - -

MS20002-6 1 1 WASHER - -

MS20002-7 1 1 WASHER - -

MS20002C5 2 2 WASHER - -

MS20002C6 3 3 WASHER - -

MS20002C7 4 4 WASHER - -

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: May 22, 2013

Revision 1: December 17, 2013 MD80-55A070

30 of 53

BOEING SERVICE BULLETIN MD80-55A070

ALERT ALERT
Group 1, Configuration 1, 3:

Condition 2, Option 2:

Kit SA09550065

Existing Part Notes

Number

New Part Number QTY Name

-53 -55

MS20002C8 1 1 WASHER - -

MS20426AD3-4D 6 6 RIVET - -

MS20426AD5-8D 1 1 RIVET - -

MS20426AD5-9D 45 45 RIVET - -

MS20426AD6-8D 95 95 RIVET - -

MS20426AD6-9D 57 57 RIVET - -

MS20426AD6-10D 4 4 RIVET - -

MS20470AD5-8D 20 20 RIVET - -

MS20470E5-6D 106 106 RIVET - -

MS20470E5-7D 20 20 RIVET - -

MS20470E6-7D 52 52 RIVET - -

MS20470E6-8D 26 26 RIVET - -

MS21042L3 291 291 NUT - -

MS21075L3 5 5 NUTPLATE - -

MS21250-05018 2 2 BOLT - -

MS21250-06020 1 1 BOLT - -

MS21250-06022 1 1 BOLT - -

MS21250-06024 1 1 BOLT - -

MS21250-07020 1 1 BOLT - -

MS21250-07024 1 1 BOLT - -

MS21250-07026 1 1 BOLT - -

MS21250-08028 1 1 BOLT - -

MS21250H07060 1 . BOLT - -

NAS1097KE5-8D 8 8 RIVET - -

NAS1097KE5-9D 7 7 RIVET - -

NAS1097KE6-8D 44 44 RIVET - -

NAS1097KE6-9D 59 59 RIVET - -

NAS1097KE6-11D 4 4 RIVET - -

NAS1149F0332P 78 78 WASHER - -

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: May 22, 2013

Revision 1: December 17, 2013 MD80-55A070

31 of 53

BOEING SERVICE BULLETIN MD80-55A070

ALERT ALERT
Group 1, Configuration 1, 3:

Condition 2, Option 2:

Kit SA09550065

Existing Part Notes

Number

New Part Number QTY Name

-53 -55

NAS1149F0463P 24 24 WASHER - -

NAS1149FN816P 14 14 WASHER - -

NAS1252-10L 316 316 WASHER - -

NAS1403-2 14 14 SCREW - -

NAS1403-4 20 20 SCREW - -

NAS1403-5 30 30 SCREW - -

NAS1403-8 4 4 SCREW - -

NAS1587A3C 23 23 WASHER - -

NAS333CPA4-5 1 1 SCREW - -

NAS578-6B 3 3 RETAINER - -

NAS578-7B 4 4 RETAINER - -

NAS578-8B 1 1 RETAINER - -

NAS602-7P 24 24 SCREW - -

NAS620-416L 6 6 WASHER - -

NAS6203-10 6 6 BOLT - -

NAS6203-6 8 8 BOLT - -

NAS6204-13 6 6 BOLT - -

NAS6204-4 24 24 BOLT - -

NAS679A3 31 31 NUT - -

NAS679A4 7 7 NUT - -

PIC239-3-4 1 1 BOLT - -

PIC239-4-4 2 2 BOLT - -

S4931919-6-5 4 4 PIN - -

S4931920-6-4 8 8 PIN - -

S4931920-6-5 10 10 PIN - -

S4931920-6-6 14 14 PIN - -

S4931920-6-7 4 4 PIN - -

S4931920-6-8 6 6 PIN - -

(a) May be substituted for 117LH7940T-098 barrel nut assembly.

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: May 22, 2013

Revision 1: December 17, 2013 MD80-55A070

32 of 53

BOEING SERVICE BULLETIN MD80-55A070

ALERT ALERT
Group 1, Configuration 2, 4:

Condition 2, Option 2:

Kit SA09550065

Existing Part Notes

Number

New Part Number QTY Name

-53 -55 -61

113LH7940T064 3 3 - NUT - -

113LH7940T070 4 4 - NUT - -

113LH7940T080 1 1 - BARREL NUT - -

117LH7940T-098 2 2 - NUT BARREL - -

3D0006-3 99 99 - NUT ASSY - -

3D0006-4 5 5 - NUT ASSY - -

3D0011-9 SUB SUB - BARREL NUT - (a)

3D0012-9 SUB SUB - RETAINER -

3D0031-9-34 2 2 - BOLT - -

5918000-525 - 1 - SPAR CAP 5918000-525 -

5918000-529

5918000-526 1 - - SPAR CAP 5918000-526 -

5918000-530

73232-9-28.7 2 2 - WASHER - -

7090-040 - - 2 BUSHING - -

7090-043 - - 2 BUSHING - -

HLT434-6-3 5 5 - PIN - -

HLT434-6-4 72 72 - PIN - -

HLT434-6-5 32 32 - PIN - -

HLT434-6-6 18 18 - PIN - -

HLT434-6-7 18 18 - PIN - -

HLT434-6-8 25 25 - PIN - -

HLT434-6-9 2 2 - PIN - -

HLT434-6-11 5 5 - PIN - -

HLT434-8-8 1 1 - HILOK - -

HLT434-8-13 3 3 1 HILOK - -

HLT434-8-16 2 2 - HILOK - -

HLT435-6-4 84 84 - PIN - -

HLT435-6-5 77 77 - PIN - -

HLT435-6-6 9 9 - PIN - -

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: May 22, 2013

Revision 1: December 17, 2013 MD80-55A070

33 of 53

BOEING SERVICE BULLETIN MD80-55A070

ALERT ALERT
Group 1, Configuration 2, 4:

Condition 2, Option 2:

Kit SA09550065

Existing Part Notes

Number

New Part Number QTY Name

-53 -55 -61

HLT435-6-7 13 13 - PIN - -

HLT435-6-8 4 4 - PIN - -

HLT634-8-13 - - 1 PIN - -

MS20002-5 2 2 - WASHER - -

MS20002-6 1 1 - WASHER - -

MS20002-7 1 1 - WASHER - -

MS20002C5 2 2 - WASHER - -

MS20002C6 3 3 - WASHER - -

MS20002C7 4 4 - WASHER - -

MS20002C8 1 1 - WASHER - -

MS20426AD3-4D 6 6 - RIVET - -

MS20426AD5-8D 1 1 - RIVET - -

MS20426AD5-9D 45 45 - RIVET - -

MS20426AD6-8D 95 95 - RIVET - -

MS20426AD6-9D 57 57 - RIVET - -

MS20426AD6-10D 4 4 - RIVET - -

MS20470AD5-8D 20 20 - RIVET - -

MS20470E5-6D 106 106 - RIVET - -

MS20470E5-7D 20 20 - RIVET - -

MS20470E6-7D 52 52 - RIVET - -

MS20470E6-8D 26 26 - RIVET - -

MS21042L3 291 291 - NUT - -

MS21042L4 - - 1 NUT - -

MS21075L3 5 5 - NUTPLATE - -

MS21250-05018 2 2 - BOLT - -

MS21250-06020 1 1 - BOLT - -

MS21250-06022 1 1 - BOLT - -

MS21250-06024 1 1 - BOLT - -

MS21250-07020 1 1 - BOLT - -

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: May 22, 2013

Revision 1: December 17, 2013 MD80-55A070

34 of 53

BOEING SERVICE BULLETIN MD80-55A070

ALERT ALERT
Group 1, Configuration 2, 4:

Condition 2, Option 2:

Kit SA09550065

Existing Part Notes

Number

New Part Number QTY Name

-53 -55 -61

MS21250-07024 1 1 - BOLT - -

MS21250-07026 1 1 - BOLT - -

MS21250-08028 1 1 - BOLT - -

MS21250H07060 1 . - BOLT - -

NAS1097KE5-8D 8 8 - RIVET - -

NAS1097KE5-9D 7 7 - RIVET - -

NAS1097KE6-8D 44 44 - RIVET - -

NAS1097KE6-9D 59 59 - RIVET - -

NAS1097KE6-11D 4 4 - RIVET - -

NAS1149F0332P 78 78 - WASHER - -

NAS1149F0463P 24 24 - WASHER - -

NAS1149FN816P 14 14 - WASHER - -

NAS1252-10L 316 316 - WASHER - -

NAS1252-416L - - 1 WASHER - -

NAS1403-2 14 14 - SCREW - -

NAS1403-4 20 20 - SCREW - -

NAS1403-5 30 30 - SCREW - -

NAS1403-8 4 4 - SCREW - -

NAS1587A3C 23 23 - WASHER - -

NAS333CPA4-5 1 1 - SCREW - -

NAS578-6B 3 3 - RETAINER - -

NAS578-7B 4 4 - RETAINER - -

NAS578-8B 1 1 - RETAINER - -

NAS602-7P 24 24 - SCREW - -

NAS620-416L 6 6 2 WASHER - -

NAS6203-10 6 6 - BOLT - -

NAS6203-6 8 8 - BOLT - -

NAS6204-13 6 6 2 BOLT - -

NAS6204-4 24 24 - BOLT - -

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: May 22, 2013

Revision 1: December 17, 2013 MD80-55A070

35 of 53

BOEING SERVICE BULLETIN MD80-55A070

ALERT ALERT
Group 1, Configuration 2, 4:

Condition 2, Option 2:

Kit SA09550065

Existing Part Notes

Number

New Part Number QTY Name

-53 -55 -61

NAS679A3 31 31 - NUT - -

NAS679A4 7 7 2 NUT - -

PIC239-3-4 1 1 - BOLT - -

PIC239-4-4 2 2 - BOLT - -

S4931919-6-5 4 4 - PIN - -

S4931920-6-4 8 8 - PIN - -

S4931920-6-5 10 10 - PIN - -

S4931920-6-6 14 14 - PIN - -

S4931920-6-7 4 4 - PIN - -

S4931920-6-8 6 6 - PIN - -

(a) May be substituted for 117LH7940T-098 barrel nut assembly.

Kit SA09550070

New Part Number QTY Name Notes

-3

5930603-17 2 FILLER -

2. Parts and Materials Supplied by the Operator

Part Number/Specification QTY Supplier CAGE

PRC-DeSoto International, 92108

Incorporated

As RequiredPR-1422 B-2 Sealant

(DMS 2082

or Equivalent) P.O. Box 1800

Sylmar, California 91342

3. Parts Modified and Reidentified

None

4. Parts Removed and Not Replaced

None

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: May 22, 2013

Revision 1: December 17, 2013 MD80-55A070

36 of 53

BOEING SERVICE BULLETIN MD80-55A070

ALERT ALERT
D. Parts Necessary to Change Spares

To get the kits shown below, refer to Paragraph 2.A., Material - Price and Availability.

E. Special Tooling - Price and Availability

The operator can supply the tools shown in Paragraph 2.F., Special Tooling Necessary to do this

Service Bulletin. Tool price and supply data are not given.

F. Special Tooling Necessary to do this Service Bulletin

To get the tools shown below, refer to Paragraph 2.E., Special Tooling - Price and Availability.

Maintenance and overhaul tools in the manuals shown in Paragraph 1.J., References, can also be

necessary. Examine operator tool supply to make sure all necessary tools are available.

Tool Number Name Supplier CAGE Notes

Horizontal Stabiliz- The Boeing Company 81205 (a)

er Hinge Alignment

Tool

C652-5922575 ATP3

Stress Coin Coun- The Boeing Company 81205

tersink Die Tool

C652-74956-165B-GT

(a) Horizontal Stabilizer Hinge Alignment Tool is optional, not mandatory, and may be obtained

from Boeing.

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: May 22, 2013

Revision 1: December 17, 2013 MD80-55A070

37 of 53

BOEING SERVICE BULLETIN MD80-55A070

ALERT ALERT
Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: May 22, 2013

Revision 1: December 17, 2013 MD80-55A070

38 of 53

BOEING SERVICE BULLETIN MD80-55A070

ALERT ALERT

BLANK PAGE
3. ACCOMPLISHMENT INSTRUCTIONS

A. GENERAL INFORMATION

WARNING: IF ELECTRICAL POWER IS APPLIED TO THE AIRPLANE, MAKE SURE YOU OBEY

ALL PRECAUTIONS WHILE YOU DO WORK. IF YOU DO NOT OBEY THE

PRECAUTIONS, DEATH OR INJURY TO PERSONS, AND DAMAGE TO THE AIRPLANE

CAN OCCUR.

CAUTION: ELECTRICALLY GROUND THE AIRPLANE. THIS WILL HELP TO PREVENT DAMAGE

TO THE AIRPLANE OR EQUIPMENT.

CAUTION: KEEP THE WORK AREA, WIRES AND ELECTRICAL BUNDLES CLEAN OF METAL

PARTICLES OR CONTAMINATION WHEN YOU USE TOOLS. UNWANTED MATERIAL,

METAL PARTICLES OR CONTAMINATION CAUGHT IN WIRE BUNDLES CAN CAUSE

DAMAGE TO THE BUNDLES. DAMAGED WIRE BUNDLES CAN CAUSE SPARKS OR

OTHER ELECTRICAL DAMAGE.

NOTE: 1. Manual titles are referred to by acronyms. Refer to Paragraph 1.J., References, for

definition of the acronyms.

2. Equivalent parts are listed in the AEPL, Drawing 7595071.

3. Use the approved fastener and process material substitutions, in accordance with

MD-80 SRM 51.

4. If the length of any fastener specified in this service bulletin does not meet installation

standards given in Structural Repair Manual (SRM) Chapter 51, then a fastener of

the same specification, or an approved substitute, with a length which meets the

installation standards given in SRM Chapter 51 may be used. In addition, washers

may be installed for fastener grip length in accordance with SRM Chapter 51.

5. A 1/8-inch thick stack of the same type washers called for in this service bulletin is

the maximum thickness which may be used under fastener head or nut to counteract

accumulation of tolerances.

EXCEPTION: When the available fastener length increments are greater than

1/16-inch, a 3/16-inch thick stack of the same type washers may be used.

6. Unless shown differently, these dimensions and tolerances are used:

– Linear dimensions are in inches

– Tolerance on linear dimensions, other than rivet and bolt edge margins, is plus

or minus 0.03 inch.

– Tolerance on rivet and bolt edge margin is plus or minus 0.05 inch

– Angular tolerance is plus or minus 2 degrees

– Hole dimensions for standard solid rivets are in MD-80 SRM 51.

– Torque limits to tighten nuts and bolts are in MD-80 SRM 51.

7. Refer to these chapters for the applicable operations as accepted procedures:

– MD-80 SRM 51-10-02 - Forming, Heat Treatment, and Metal Handling

– MD-80 SRM 51-10-03 - Corrosion and Dissimilar Metals Protection

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: May 22, 2013

Revision 1: December 17, 2013 MD80-55A070

39 of 53

BOEING SERVICE BULLETIN MD80-55A070

ALERT ALERT
– MD-80 SRM 51-10-04 - Drilling and Countersinking

– MD-80 SRM 51-20-00 - Repair Sealing

– MD-80 SRM 51-30-01 - Installing Bolts, Screws, and Washers

– MD-80 SRM 51-30-02 - Removing and Installing Rivets

– MD-80 SRM 51-30-03 - Removing and Installing Lockbolts

– MD-80 SRM 51-30-05 - Installing Hi-Lok Attachments

– MD-80 SRM 51-30-09 - Split Sleeve Cold Work

– MD-80 SRM 51-30-11 - Conical Spacers (Countersink Washers)

– MD-80 SRM 51-70-02 - Repair of Bonded Aluminum Assemblies

– MD-80 AMM 20-20-01 - Cementing - Maintenance Practices

8. Obey all of the warnings and cautions given in the specified manual sections.

9. These work instructions refer to procedures included in other Boeing documents.

When the words "refer to" are used and the operator has an accepted alternative

procedure, the accepted alternative procedure can be used. When the words "in

accordance with" are included in the instruction, the procedure in the Boeing document

must be used.

10. Some Boeing parts are supplied in a temporary configuration. Those parts are

identified with a 'U' or 'Y' in place of the '-' (dash) in the part number. It is permitted

to install parts identified with a 'U' or 'Y' as an alternative to the '-' (dash) number

part. Boeing Drawing SE10000000, Sheets 5.0 and 6.0 contain more data.

11. If it is necessary to remove more parts for access, you can remove those parts. If

you can get access without removing identified parts, it is not necessary to remove

all of the identified parts. Jacking and shoring limitations must be observed.

12. Where the work instructions include installation of a kept part, a new or serviceable

part with the same part number can be installed as an alternative to the kept part.

13. This service bulletin includes functional test procedures for the systems changed by

this service bulletin. More functional tests can possibly be necessary in accordance

with standard maintenance practices because of interruption to other airplane systems.

14. Shaded areas in Figures are reference only. Shaded areas in Figures may look

different than your airplane.

15. When more than one OPTION is given for a CONDITION, do only one of the OPTION

numbers. When more than one ACTION is given for a CONDITION number or an

OPTION number, do all of the ACTION numbers for that CONDITION number or

OPTION number.

16. The compliance times for the actions in Paragraph 3.B., WORK INSTRUCTIONS

are in Paragraph 1.E., Compliance.

B. WORK INSTRUCTIONS

Group 1, Configuration 1, 3:

1. Remove the left and right horizontal stabilizer skin filler. Refer to Figure 1 for location of skin fillers.

NOTE: The skin fillers are bonded to the airplane structure with DMS 2082 adhesive.

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: May 22, 2013

Revision 1: December 17, 2013 MD80-55A070

40 of 53

BOEING SERVICE BULLETIN MD80-55A070

ALERT ALERT
2. Prepare the surface area to be inspected in accordance with Figure 2.

3. Do a High Frequency Eddy Current (ETHF) inspection of the areas around the upper rear spar

cap two aft-most barrel nut holes in accordance with Figure 3 and based on inspection results do

the work of the applicable condition that follows:

Condition 1 - No Crack Found

a. If required, fill area of forward barrel nut hole sealant removed for ETHF inspection in

accordance with Figure 2 with DMS 2082 sealant.

b. Install a new or serviceable 5930603-17 filler using DMS 2082 sealant. Refer to MD-80 AMM

20-20-01 as an acceptable procedure.

c. Put the airplane back in serviceable condition.

d. Repeat ETHF inspection at intervals specified in Paragraph 1.E., Compliance.

Condition 2 - Any Crack Found

a. Do Option 1 or Option 2

NOTE: Both Options affect the inspection requirements contained in Service Bulletin

MD80-55A065, and will affect compliance with FAA AD 2007-10-04 as it relates to

the upper rear spar cap. Operators are urged to consider both this service bulletin

and Service Bulletin MD80-55A065 while choosing an option.

Option 1:

(1) Remove and keep horizontal stabilizer. Refer to MD-80 AMM 55-10-00 as an acceptable

procedure.

(2) Remove and keep elevator from affected side. Refer to MD-80 AMM 27-30-02 as an

acceptable procedure.

(3) Remove and keep horizontal stabilizer leading edge from affected side. Refer to MD-80

AMM 55-10-01 as an acceptable procedure.

(4) Splice horizontal stabilizer upper rear spar in accordance with Service Rework Drawing

SR09550027-7001 (left side) or -7003 (right side).

(5) Install kept horizontal stabilizer leading edge on affected side. Refer to MD-80 AMM

55-10-01 as an acceptable procedure.

(6) Install kept elevator on affected side. Refer to MD-80 AMM 27-30-02 as an acceptable

procedure.

(7) Install a new or serviceable 5930603-17 filler using DMS 2082 sealant. Refer to MD-80

AMM 20-20-01 as an acceptable procedure.

(8) Install kept horizontal stabilizer. Refer to MD-80 AMM 55-10-00 as an acceptable

procedure.

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: May 22, 2013

Revision 1: December 17, 2013 MD80-55A070

41 of 53

BOEING SERVICE BULLETIN MD80-55A070

ALERT ALERT
(9) Put the airplane back in serviceable condition.

(10) Repeat ETHF inspection at intervals specified in Paragraph 1.E., Compliance.

(11) Replace horizontal stabilizer upper rear spar cap in accordance with Service Rework

Drawing SR09550030-7001 (left side) or -7005 (right side) as specified in Paragraph 1.E.,

Compliance.

Option 2:

(1) Remove and keep horizontal stabilizer. Refer to MD-80 AMM 55-10-00 as an acceptable

procedure.

(2) Remove and keep elevator from affected side. Refer to MD-80 AMM 27-30-02 as an

acceptable procedure.

(3) Remove and keep horizontal stabilizer leading edge from affected side. Refer to MD-80

AMM 55-10-01 as an acceptable procedure.

(4) Install new horizontal stabilizer upper rear spar cap in accordance with Service Rework

Drawing SR09550030-7001 (left side) or -7005 (right side).

(5) Install kept horizontal stabilizer leading edge on affected side. Refer to MD-80 AMM

55-10-01 as an acceptable procedure.

(6) Install kept elevator on affected side. Refer to MD-80 AMM 27-30-02 as an acceptable

procedure.

(7) Install a new or serviceable 5930603-17 filler using DMS 2082 sealant. Refer to MD-80

AMM 20-20-01 as an acceptable procedure.

(8) Install kept horizontal stabilizer. Refer to MD-80 AMM 55-10-00 as an acceptable

procedure.

(9) Put the airplane back in serviceable condition.

(10) Repeat ETHF inspection at intervals specified in Paragraph 1.E., Compliance.

Group 1, Configuration 2, 4:

1. Remove the left and right horizontal stabilizer skin filler. Refer to Figure 1 for location of skin fillers.

NOTE: The skin fillers are bonded to the airplane structure with DMS 2082 adhesive.

2. Prepare the surface area to be inspected in accordance with Figure 2.

3. Do a High Frequency Eddy Current (ETHF) inspection of the areas around the upper rear spar

cap two aft-most barrel nut holes in accordance with Figure 3 and based on inspection results do

the work of the applicable condition that follows:

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: May 22, 2013

Revision 1: December 17, 2013 MD80-55A070

42 of 53

BOEING SERVICE BULLETIN MD80-55A070

ALERT ALERT
Condition 1 - No Crack Found

a. If required, fill area of forward barrel nut hole sealant removed for ETHF inspection in

accordance with Figure 2 with DMS 2082 sealant.

b. Install a new or serviceable 5930603-17 filler using DMS 2082 sealant. Refer to MD-80 AMM

20-20-01 as an acceptable procedure.

c. Put the airplane back in serviceable condition

d. Repeat ETHF inspection at intervals specified in Paragraph 1.E., Compliance.

Condition 2 - Any Crack Found

a. Do Option 1 or Option 2

NOTE: Both Options affect the inspection requirements contained in Service Bulletin

MD80-55A065, and will affect compliance with FAA AD 2007-10-04 as it relates to

the upper rear spar cap. Operators are urged to consider both this service bulletin

and Service Bulletin MD80-55A065 while choosing an option.

Option 1:

(1) Remove and keep horizontal stabilizer. Refer to MD-80 AMM 55-10-00 as an acceptable

procedure.

(2) Remove and keep elevator from affected side. Refer to MD-80 AMM 27-30-02 as an

acceptable procedure.

(3) Remove and keep horizontal stabilizer leading edge from affected side. Refer to MD-80

AMM 55-10-01 as an acceptable procedure..

(4) Splice horizontal stabilizer upper rear spar cap in accordance with Service Rework Drawing

SR09550027-7013 (left side) or -7015 (right side).

(5) Install kept horizontal stabilizer leading edge on affected side. Refer to MD-80 AMM

55-10-01 as an acceptable procedure.

(6) Install kept elevator on affected side. Refer to MD-80 AMM 27-30-02 as an acceptable

procedure.

(7) Install a new or serviceable 5930603-17 filler using DMS 2082 sealant. Refer to MD-80

AMM 20-20-01 as an acceptable procedure.

(8) Install kept horizontal stabilizer. Refer to MD-80 AMM 55-10-00 as an acceptable

procedure.

(9) Put the airplane back in serviceable condition.

(10) Repeat ETHF inspection at intervals specified in Paragraph 1.E., Compliance.

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: May 22, 2013

Revision 1: December 17, 2013 MD80-55A070

43 of 53

BOEING SERVICE BULLETIN MD80-55A070

ALERT ALERT
(11) Replace horizontal stabilizer upper rear spar cap in accordance with Service Rework

Drawing SR09550030-7017 (left side) or -7019 (right side) as specified in Paragraph 1.E.,

Compliance.

Option 2:

(1) Remove and keep horizontal stabilizer. Refer to MD-80 AMM 55-10-00 as an acceptable

procedure.

(2) Remove and keep elevator from affected side. Refer to MD-80 AMM 27-30-02 as an

acceptable procedure.

(3) Remove and keep horizontal stabilizer leading edge from affected side. Refer to MD-80

AMM 55-10-01 as an acceptable procedure.

(4) Install new horizontal stabilizer upper rear spar cap in accordance with Service Rework

Drawing SR09550030-7017 (left side) or -7019 (right side).

(5) Install kept horizontal stabilizer leading edge on affected side. Refer to MD-80 AMM

55-10-01 as an acceptable procedure.

(6) Install kept elevator on affected side. Refer to MD-80 AMM 27-30-02 as an acceptable

procedure.

(7) Install a new or serviceable 5930603-17 filler using DMS 2082 sealant. Refer to MD-80

AMM 20-20-01 as an acceptable procedure.

(8) Install kept horizontal stabilizer. Refer to MD-80 AMM 55-10-00 as an acceptable

procedure.

(9) Put the airplane back in serviceable condition.

(10) Repeat ETHF inspection at intervals specified in Paragraph 1.E., Compliance.

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: May 22, 2013

Revision 1: December 17, 2013 MD80-55A070

44 of 53

BOEING SERVICE BULLETIN MD80-55A070

ALERT ALERT
FIGURE 1: REMOVE SKIN FILLER

(SHEET 1 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: May 22, 2013

Revision 1 December 17, 2013 MD80-55A070

45 of 53

BOEING SERVICE BULLETIN MD80-55A070

ALERT ALERT
FIGURE 1: REMOVE SKIN FILLER

(SHEET 2 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: May 22, 2013

Revision 1 December 17, 2013 MD80-55A070

46 of 53

BOEING SERVICE BULLETIN MD80-55A070

ALERT ALERT
The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY

numbers shown below are the number of parts necessary for each airplane.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

Horizontal Stabiliz- 5930603-17 2 (a)

er Upper Skin Filler

1 Remove

(a) Filler is attached with DMS 2082 sealant.

FIGURE 1: REMOVE SKIN FILLER

(SHEET 3 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: May 22, 2013

Revision 1 December 17, 2013 MD80-55A070

47 of 53

BOEING SERVICE BULLETIN MD80-55A070

ALERT ALERT
FIGURE 2: INSPECTION SURFACE AREA - PREPARATION

(SHEET 1 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: May 22, 2013

Revision 1 December 17, 2013 MD80-55A070

48 of 53

BOEING SERVICE BULLETIN MD80-55A070

ALERT ALERT
FIGURE 2: INSPECTION SURFACE AREA - PREPARATION

(SHEET 2 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: May 22, 2013

Revision 1 December 17, 2013 MD80-55A070

49 of 53

BOEING SERVICE BULLETIN MD80-55A070

ALERT ALERT
The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY

numbers shown below are the number of parts necessary for each airplane.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

5918000-525 1 (a) (b)

5918000-526

Horizontal Stabilizer Upper Spar Cap1 Prepare

(a) Make sure that the horizontal stabilizer skin does not interfere with the test probe in the areas that require

inspection. The distance between the edge of the forward barrel nut hole and the skin at the closest point

must be greater than the diameter of the probe coil plus 0.010 inch.

(b) If the horizontal stabilizer skin interferes with the test probe, remove enough sealant from the forward

face of the forward barrel nut hole to allow for the diameter of the probe plus 0.010 inch minimum in the

inspection area.

FIGURE 2: INSPECTION SURFACE AREA - PREPARATION

(SHEET 3 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: May 22, 2013

Revision 1 December 17, 2013 MD80-55A070

50 of 53

BOEING SERVICE BULLETIN MD80-55A070

ALERT ALERT
FIGURE 3: HIGH FREQUENCY EDDY CURRENT INSPECTION

(SHEET 1 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: May 22, 2013

Revision 1 December 17, 2013 MD80-55A070

51 of 53

BOEING SERVICE BULLETIN MD80-55A070

ALERT ALERT
FIGURE 3: HIGH FREQUENCY EDDY CURRENT INSPECTION

(SHEET 2 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: May 22, 2013

Revision 1 December 17, 2013 MD80-55A070

52 of 53

BOEING SERVICE BULLETIN MD80-55A070

ALERT ALERT
The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY

numbers shown below are the number of parts necessary for.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

5918000-525 1 (a) (b) (c)

5918000-526

Horizontal Stabilizer Upper Spar CapInspect High Frequency Eddy Current (ETHF)1

Make sure the surfaces to be inspected are clean. Refer to NDTSPM 06-00-02 as an acceptable

procedure.

(a)

Perform a High Frequency Eddy Current surface inspection of the horizontal stabilizer rear spar upper

cap adjacent to the two barrel nut holes at the inspection area. Scan around the barrel nut holes

looking for cracks propagating in the forward and aft direction initiating at the barrel nut holes following

the instructions found in the Nondestructive Testing Standard Practice Manual NDTSPM 06-10-

01.001 (ETHF - Procedure 1). Use Calibration Method "A" and Scan Method "79".

(b)

If the horizontal stabilizer skin interferes with the test probe, inspect by scanning the forward face of

the forward barrel nut holes following the instructions found in the Nondestructive Testing Standard

Practice Manual NDTSPM 06-10-01.001 (ETHF - Procedure 1). Use calibration Method "A" and Scan

Method "79".

(c)

FIGURE 3: HIGH FREQUENCY EDDY CURRENT INSPECTION

(SHEET 3 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: May 22, 2013

Revision 1 December 17, 2013 MD80-55A070

53 of 53

BOEING SERVICE BULLETIN MD80-55A070

ALERT ALERT