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Commercial Airplanes MD80 Service Bulletin ALERT Number: MD80-55A068 Original Issue: July 16, 2010 ATA System: 5510 SUBJECT: STABILIZERS - Horizontal Stabilizer - Inspect/Replace Upper Center Skin Panels Export of this technology is controlled under the United States Export Administration Regulations (EAR) (15 CFR 730-774). An export license may be required before it is used for development, production or use by foreign persons from specific countries. The controller of this data has the individual responsibility to abide by all export laws.
9E991ECCN:
BOEING PROPRIETARY, CONFIDENTIAL, AND/OR TRADE SECRET Copyright © 2010 The Boeing Company Unpublished Work - All Rights Reserved Boeing claims copyright in each page of this document only to the extent that the page contains copyrightable subject matter. Boeing also claims copyright in this document as a compilation and/or collective work.
This document includes proprietary information owned by The Boeing Company and/or one or more third parties.
Treatment of the document and the information it contains is governed by contract with Boeing. For more information, contact The Boeing Company, P.O. Box 3707, Seattle, Washington 98124.
Boeing, the Boeing signature, the Boeing symbol, 707, 717, 727, 737, 747, 757, 767, 777, 787, Dreamliner, BBJ, DC-8, DC-9, DC-10, KC-10, KDC-10, MD-10, MD-11, MD-80, MD-88, MD-90, P-8A, Poseidon and the Boeing livery are all trademarks owned by The Boeing Company; and no trademark license is granted in connection with this document unless provided in writing by Boeing.
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2.0
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Table of Contents
Summary5
1. PLANNING INFORMATION7
A. Effectivity7
1. Airplanes7
2. Spares Affected ........................................ 1 0 B. Concurrent Requirements ...................................... 1 0 C. Reason ................................................ 1 1 D. Description .............................................. 1 1 E. Compliance .............................................. 1 1 F. Approval ............................................... 1 5 G. Manpower .............................................. 1 6 H. Weight and Balance Changes .................................... 1 7 I. Electrical Load Data ......................................... 1 8 J. References .............................................. 1 9
1. Existing Data: ......................................... 1 9
2. Data supplied with this Service Bulletin: ........................... 1 9
3. Installation Drawings Used in the Preparation of this Service Bulletin: ........... 1 9 K. Publications Affected ........................................ 1 9 L. Interchangeability and Intermixability of Parts ........................... 2 0
2. MATERIAL INFORMATION ........................................ 2 1 A. Material - Price and Availability ................................... 2 1 B. Industry Support Information .................................... 2 2 C. Parts Necessary For Each Airplane ................................. 2 2
1. Kits/Parts: ........................................... 2 2
2. Parts and Materials Supplied by the Operator: ........................ 2 6
3. Parts Modified and Reidentified: ............................... 2 6
4. Parts Removed and Not Replaced: .............................. 2 6 D. Parts Necessary to Change Spares ................................. 2 6 E. Special Tooling - Price and Availability ............................... 2 7 F. Special Tooling Necessary to do this Service Bulletin ....................... 2 7
3. ACCOMPLISHMENT INSTRUCTIONS .................................. 2 9 A. GENERAL INFORMATION ..................................... 2 9 B. WORK INSTRUCTIONS ....................................... 3 0 FIGURE 1: HORIZONTAL STABILIZER LEFT AND RIGHT UPPER CENTER SKIN PANELS - EDDY CURRENT INSPECTION ................................... 3 3
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Commercial Airplanes MD80 Service Bulletin ALERT SummaryNumber: MD80-55A068Original Issue: July 16, 2010 ATA System: 5510 SUBJECT: STABILIZERS - Horizontal Stabilizer - Inspect/Replace Upper Center Skin Panels
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 inspection of the horizontal stabilizer upper aft skin panel in accordance with Service Bulletin MD80-55A065, one operator reported finding a crack in the right horizontal stabilizer upper center skin panel at the aft inboard corner. The airplane had accumulated 47,146 flight-hours and 26,490 flight cycles when the crack was found. The cause of the horizontal stabilizer upper center skin panel cracking is suspected to be fatigue. If undetected, a crack in the upper center skin panel may transfer load to the upper aft skin panel. This may result in the upper aft skin panel cracking faster than the existing inspection intervals, defined in Service Bulletin MD80-55A065, will detect. Inspection of the affected areas will determine the condition of the horizontal stabilizer upper center skin panels. If not corrected, undetected cracks may ultimately lead to the loss of overall structural integrity of the horizontal stabilizer.
ACTION Refer to Paragraph 1.D., Description.
EFFECTIVITY DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83), DC-9-87 (MD-87), MD-88 Airplanes. Refer to Paragraph
1.A.1., Airplanes, for the list of affected airplanes.
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.
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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.
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Commercial Airplanes MD80 Service Bulletin ALERT Number: MD80-55A068 Original Issue: July 16, 2010 ATA System: 5510 SUBJECT: STABILIZERS - Horizontal Stabilizer - Inspect/Replace Upper Center Skin Panels
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.
DESCRIPTIONCONFIGURATIONGROUP MD-80 Series Airplanes (Fuselage Numbers 909 Thru 1614)-1 MD-80 Series Airplanes (Fuselage Numbers 1615 Thru 2287)-2 Airplane Models:
DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83), DC-9-87 (MD-87), MD-88 GroupFuselage Number 1909 1917 1924 1938 1941 1944 1946
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GroupFuselage Number 1948 1950 1952 - 953 1955 1957 - 958 1960 1962 - 963 1965 - 967 1969 - 971 1973 - 975 1977 - 979 1981 1983 1985 - 986 1988 - 989 1991 - 992 1994 - 1013 11015 - 1016 11018 - 1020 11022 - 1023 11025 - 1026 11028 - 1029 11031 - 1032 11034 - 1035 11037 - 1038 11040 - 1041 11043 11045 11047 11049 11051 11053
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GroupFuselage Number 11055 11057 11059 - 1080 11082 - 1083 11085 - 1614 21615 - 2007 22009 - 2016 22019 - 2034 22036 - 2069 22071 - 2093 22101 - 2114 22116 22118 - 2119 22121 22124 22127 - 2128 22130 22132 22134 - 2135 22137 22139 22145 22148 22151 - 2152 22155 22167 22174 22176 22178 22180 22183 22185
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GroupFuselage Number 22187 22189 22192 22196 22199 22201 22204 22206 22208 22214 22218 22234 22239 22241 22244 22247 22249 22252 22254 22264 - 2287
2. Spares Affected None.
B. Concurrent Requirements None.
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C. Reason During inspection of the horizontal stabilizer upper aft skin panel in accordance with Service Bulletin MD80-55A065, one operator reported finding a crack in the right horizontal stabilizer upper center skin panel at the aft inboard corner. The airplane had accumulated 47,146 flight-hours and 26,490 flight cycles when the crack was found. The cause of the horizontal stabilizer upper center skin panel cracking is suspected to be fatigue. If undetected, a crack in the upper center skin panel may transfer load to the upper aft skin panel. This may result in the upper aft skin panel cracking faster than the existing inspection intervals, defined in Service Bulletin MD80-55A065, will detect. Inspection of the affected areas will determine the condition of the horizontal stabilizer upper center skin panels. If not corrected, undetected cracks may ultimately lead to the loss of overall structural integrity of the horizontal stabilizer.
D. Description This service bulletin provides instructions to do an eddy current inspection of the horizontal stabilizer left and right upper center skin panels for cracks, and based on inspection results for each panel, does as follows:
Condition 1 (No Crack Found)
1. Does repetitive eddy current inspections of the horizontal stabilizer upper center skin panel.
Condition 2 (Crack Found)
1. OPTION 1:
a. Replaces the cracked horizontal stabilizer upper center skin panel.
b. Does repetitive eddy current inspection of the replacement horizontal stabilizer upper center skin panel.
2. OPTION 2:
a. Contacts Boeing for possible temporary repair of crack and does the repair in accordance with Boeing's instructions.
The work in this service bulletin is done in the maintenance zone(s) given below.
Affected Maintenance Zones ZoneModel 33, 34DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83), DC- 9-87 (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.
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Table 1: Inspect Horizontal Stabilizer Left and Right Upper Center Skin Panels for Cracks Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition -Within 4,379 flight cycles after the original issue date on this service bulletin.
Before the accumulation of 20,000 total flight cycles.
Do initial eddy current inspection of the horizontal stabilizer left and right upper center skin panels in accordance with Paragraph 3.B., Work Instructions, using one of the options as follows:
All Airplanes OPTION 1:
Scan 1 - Eddy Current, High Frequency (ETHF) Scan 2 - Eddy Current, High Frequency (ETHF) Scan 3 - Eddy Current, Low Frequency (ETLF) OR OPTION 2:
Scan 1 - Eddy Current, High Frequency (ETHF) Scan 2 - Eddy Current, High Frequency (ETHF) Scan 3 - Eddy Current, High Frequency (ETHF)
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