### 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. 9E991 ECCN: 

## BOEING PROPRIETARY, CONFIDENTIAL, AND/OR TRADE SECRET Copyright © 2010 The Boeing Company Unpublished Work - All Rights Reserved Boeing claims copyright in each page of this document only to the extent that the page contains copyrightable subject matter.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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 16, 2010 MD80-55A068 1 of 38 2.0BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 16, 2010 MD80-55A068 2 of 38 **BOEING SERVICE BULLETIN MD80-55A068 ALERT**  **ALERT**

BLANK PAGE**Table of Contents** Summary...................................................... 5 1. PLANNING INFORMATION........................................ 7 A. Effectivity................................................ 7 1. Airplanes............................................. 7 2. Spares Affected. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10 B. Concurrent Requirements. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10 C. Reason. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11 D. Description. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11 E. Compliance. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11 F. Approval. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15 G. Manpower. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16 H. Weight and Balance Changes. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17 I. Electrical Load Data. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18 J. References. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19 1. Existing Data:. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19 2. Data supplied with this Service Bulletin:. . . . . . . . . . . . . . . . . . . . . . . . . . . 19 3. Installation Drawings Used in the Preparation of this Service Bulletin:. . . . . . . . . . . 19 K. Publications Affected. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19 L. Interchangeability and Intermixability of Parts. . . . . . . . . . . . . . . . . . . . . . . . . . . 20 2. MATERIAL INFORMATION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21 A. Material - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21 B. Industry Support Information. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22 C. Parts Necessary For Each Airplane. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22 1. Kits/Parts:. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22 2. Parts and Materials Supplied by the Operator:. . . . . . . . . . . . . . . . . . . . . . . . 26 3. Parts Modified and Reidentified:. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 26 4. Parts Removed and Not Replaced:. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 26 D. Parts Necessary to Change Spares. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 26 E. Special Tooling - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27 F. Special Tooling Necessary to do this Service Bulletin. . . . . . . . . . . . . . . . . . . . . . . 27 3. ACCOMPLISHMENT INSTRUCTIONS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29 A. GENERAL INFORMATION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29 B. WORK INSTRUCTIONS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 30 FIGURE 1: HORIZONTAL STABILIZER LEFT AND RIGHT UPPER CENTER SKIN PANELS - EDDY CURRENT INSPECTION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 33

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 16, 2010 MD80-55A068 3 of 38 **BOEING SERVICE BULLETIN MD80-55A068 ALERT**  **ALERT**BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 16, 2010 MD80-55A068 4 of 38 **BOEING SERVICE BULLETIN MD80-55A068 ALERT**  **ALERT**

BLANK PAGE

### Commercial **Airplanes** 

# MD80 Service Bulletin **ALERT Summary**  **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. **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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 16, 2010 MD80-55A068 5 of 38**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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 16, 2010 MD80-55A068 6 of 38 **BOEING SERVICE BULLETIN MD80-55A068 ALERT**  **ALERT**

### 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.
**DESCRIPTION CONFIGURATION**  **GROUP** 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 **Group Fuselage Num-**  **ber** 1 909 1 917 1 924 1 938 1 941 1 944 1 946

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 16, 2010 MD80-55A068 7 of 38**Group Fuselage Num-**  **ber** 1 948 1 950 1 952 - 953 1 955 1 957 - 958 1 960 1 962 - 963 1 965 - 967 1 969 - 971 1 973 - 975 1 977 - 979 1 981 1 983 1 985 - 986 1 988 - 989 1 991 - 992 1 994 - 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

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 16, 2010 MD80-55A068 8 of 38 **BOEING SERVICE BULLETIN MD80-55A068 ALERT**  **ALERT Group**  **Fuselage Num- ber**  1 1055 1 1057 1 1059 - 1080 1 1082 - 1083 1 1085 - 1614 2 1615 - 2007 2 2009 - 2016 2 2019 - 2034 2 2036 - 2069 2 2071 - 2093 2 2101 - 2114 2 2116 2 2118 - 2119 2 2121 2 2124 2 2127 - 2128 2 2130 2 2132 2 2134 - 2135 2 2137 2 2139 2 2145 2 2148 2 2151 - 2152 2 2155 2 2167 2 2174 2 2176 2 2178 2 2180 2 2183 2 2185

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 16, 2010 MD80-55A068 9 of 38 **BOEING SERVICE BULLETIN MD80-55A068 ALERT**  **ALERT Group**  **Fuselage Num- ber**  2 2187 2 2189 2 2192 2 2196 2 2199 2 2201 2 2204 2 2206 2 2208 2 2214 2 2218 2 2234 2 2239 2 2241 2 2244 2 2247 2 2249 2 2252 2 2254 2 2264 - 2287 2. Spares Affected None. **B. Concurrent Requirements** None.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 16, 2010 MD80-55A068 10 of 38 **BOEING SERVICE BULLETIN MD80-55A068 ALERT**  **ALERT 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 Zone**  **Model** 33, 34 DC-9-81 (MD-81), DC-9-82(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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 16, 2010 MD80-55A068 11 of 38 **BOEING SERVICE BULLETIN MD80-55A068 ALERT**  **ALERT Table 1: Inspect Horizontal Stabilizer Left and Right Upper Center Skin Panels for Cracks**  **Repeat Interval (Not to Exceed)**  **Compliance Time (Whichever Occurs Later)**  **Action Condition** 

- Within 4,379flight cycles after the original issue date onthis 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 panelsin 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)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 16, 2010 MD80-55A068 12 of 38 **BOEING SERVICE BULLETIN MD80-55A068 ALERT**  **ALERT Table 1: Inspect Horizontal Stabilizer Left and Right Upper Center Skin Panels for Cracks**  **Repeat Interval (Not to Exceed)**  **Compliance Time (Whichever Occurs Later)**  **Action Condition** 

- - - Do repetitive eddy currentinspection of the horizontal stabilizer left and right upper center skin panelsin accordance with Paragraph 3.B., Work Instructions, using one of the options as follows: Condition 1 (No Crack Found)

5,200 flight cycles

- Within 5,200flight cycles after doing the initial eddy current inspection. OPTION 1: Scan 1 - Eddy Current, High Frequency (ETHF) Scan 2 - Eddy Current, High Frequency (ETHF) (a)

(a) Scan 3 - Eddy Current, Low Frequency (ETLF) OR 2,500 flight cycles

- Within 2,500flight cycles after doing the initial eddy current inspection. OPTION 2: Scan 1 - Eddy Current, High Frequency (ETHF) Scan 2 - Eddy Current, High Frequency (ETHF) (a)

(a) Scan 3 - Eddy Current, High Frequency (ETHF)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 16, 2010 MD80-55A068 13 of 38 **BOEING SERVICE BULLETIN MD80-55A068 ALERT**  **ALERT Table 1: Inspect Horizontal Stabilizer Left and Right Upper Center Skin Panels for Cracks**  **Repeat Interval (Not to Exceed)**  **Compliance Time (Whichever Occurs Later)**  **Action Condition** 

- - - OPTION 1: Do items (1), (2), and (3) as follows: Condition 2 (Crack Found)

- - Before further flight (1) Replace the cracked horizontal stabilizer uppercenter skin panel in accordance with Paragraph 3.B., Work Instructions AND

- - Within 20,000flight cycles after installation of the replacementhorizontal stabilizer upper center skin panel. (2) Do initial eddy currentinspection of the replacement horizontal stabilizer upper center skin panelin accordance with Paragraph 3.B., Work Instructions, using one of the options as follows: 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) AND

- - - (3) Do repetitive eddy current inspection of the horizontal stabilizer left and right upper center skin panels in accordance with Paragraph 3.B., Work Instructions, usingone of the options as follows: 5,200 flight cycles

- OPTION 1: (a)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 16, 2010 MD80-55A068 14 of 38 **BOEING SERVICE BULLETIN MD80-55A068 ALERT**  **ALERT Table 1: Inspect Horizontal Stabilizer Left and Right Upper Center Skin Panels for Cracks**  **Repeat Interval (Not to Exceed)**  **Compliance Time (Whichever Occurs Later)**  **Action Condition**  Scan 1 - Eddy Current, High Frequency (ETHF) Within 5,200flight cycles after doing the eddy current inspection. Scan 2 - Eddy Current, High Frequency (ETHF) Scan 3 - Eddy Current, Low Frequency (ETLF) (a) OR 2,500 flight cycles

- Within 2,500flight cycles after doing the eddy current inspection. OPTION 2: Scan 1 - Eddy Current, High Frequency (ETHF) Scan 2 - Eddy Current, High Frequency (ETHF) (a)

(a) Scan 3 - Eddy Current, High Frequency (ETHF) OR

- - Before further flight OPTION 2:Contact Boeing for possible temporary repair of crack and do the repair in accordance with Boeing's instructions. Condition 2 (Crack Found)

(a) It is acceptable to change inspection procedures from Option 1 to Option 2 or from Option 2 to Option 1 if you do as follows: 1. If the inspection procedure is being changed from Option 1 to Option 2, the first Option 2 inspection must be done within 5,200 flight cycles after the Option 1 inspection. The Option 2 inspections that follows must be done within 2,500 flight cycle repeat intervals 2. If the inspection procedure is being changed from Option 2 to Option 1, the first Option 1 inspection must be done within 2,500 flight cycles after the Option 2 inspection. The Option 1 inspections that follows must be done within 5,200 flight cycle repeat intervals **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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 16, 2010 MD80-55A068 15 of 38 **BOEING SERVICE BULLETIN MD80-55A068 ALERT**  **ALERT G. Manpower**  The table below shows an estimate of the task hours necessary to do the inspection and/or configuration changes for each horizontal stabilizer upper center skin panel. 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. **All Airplanes: Horizontal Stabilizer Upper Center Skin Panel Initial Inspection Elapsed Hours**  **Task Hours Number of Persons**  **Task** 2.0 4.0 2 Figure 1 - Inspection 2.0 4.0 TOTAL FOR EACH UPPER CENTER SKIN PANEL **Condition 1: Horizontal Stabilizer Upper Center Skin Panel Repetitive Inspection Elapsed Hours**  **Task Hours Number of Persons**  **Task** 2.0 4.0 2 Figure 1 - Inspection 2.0 4.0 TOTAL FOR EACH UPPER CENTER SKIN PANEL **Condition 2, Option 1: Horizontal Stabilizer Upper Center Skin Panel Replacement Elapsed Hours**  **Task Hours Number of Persons**  **Task** 8.0 48.0 6 Remove Horizontal Stabilizer 12.0 24.0 2 Remove LeadingEdge and Upper Forward Skin Panel 168.0 504.0 3 Replace Horizontal Stabilizer Upper Center Skin Panel 12.0 24.0 2 Install Leading Edge and Upper Forward Skin Panel 8.0 48.0 6 Install Horizontal Stabilizer 208.0 648.0 TOTAL FOR EACH UPPER CENTER SKIN PANEL

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 16, 2010 MD80-55A068 16 of 38 **BOEING SERVICE BULLETIN MD80-55A068 ALERT**  **ALERT H. Weight and Balance Changes**  **Group 1: Condition 1:**  1. None **Group 1: Condition 2, Option 1:**  1. Replacement of 5922577-501 or 5922577-502 Upper Center Skin Panel
a. DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83), and MD-88 Airplanes

**Moment Change (MEW) IN.-LBS**  **Mfr's Empty Weight (MEW)**  **LBS Approximate Sta**  **tion (Inches) SR09550033 Con**  **figuration** 3117.0 + 1.9 + 1640.5 SR09550033-7005 SR09550033-7006 3117.0 + 1.9 + 1640.5 SR09550033-7007 SR09550033-7008 b. DC-9-87 (MD-87) Airplanes

**Moment Change (MEW) IN.-LBS**  **Mfr's Empty Weight (MEW)**  **LBS Approximate Sta**  **tion (Inches) SR09550033 Con**  **figuration** 2719.9 + 1.9 + 1431.5 SR09550033-7005 SR09550033-7006 2719.9 + 1.9 + 1431.5 SR09550033-7007 SR09550033-7008 2. Replacement of 5922577-507 or 5922577-508 Upper Center Skin Panel
a. DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83), and MD-88 Airplanes

**Moment Change (MEW) IN.-LBS**  **Mfr's Empty Weight (MEW)**  **LBS Approximate Sta**  **tion (Inches) SR09550033 Con**  **figuration** 1804.6 + 1.1 + 1640.5 SR09550033-7005 SR09550033-7006 1804.6 + 1.1 + 1640.5 SR09550033-7007 SR09550033-7008 b. DC-9-87 (MD-87) Airplanes

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 16, 2010 MD80-55A068 17 of 38 **BOEING SERVICE BULLETIN MD80-55A068 ALERT**  **ALERT Moment Change**  **(MEW) IN.-LBS Mfr's Empty**  **Weight (MEW) LBS** **Approximate Sta tion (Inches)** **SR09550033 Con figuration**  1574.7 + 1.1 + 1431.5 SR09550033-7005 SR09550033-7006 1574.7 + 1.1 + 1431.5 SR09550033-7007 SR09550033-7008 **Group 2: Condition 1:**  1. None **Group 2: Condition 2, Option 1:**  1. Replacement of 5922577-507 or 5922577-508 Upper Center Skin Panel
a. DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83), and MD-88 Airplanes

**Moment Change (MEW) IN.-LBS**  **Mfr's Empty Weight (MEW)**  **LBS Approximate Sta**  **tion (Inches) SR09550033 Con**  **figuration** 1804.6 + 1.1 + 1640.5 SR09550033-7001 SR09550033-7002 1804.6 + 1.1 + 1640.5 SR09550033-7003 SR09550033-7004 b. DC-9-87 (MD-87) Airplanes

**Moment Change (MEW) IN.-LBS**  **Mfr's Empty Weight (MEW)**  **LBS Approximate Sta**  **tion (Inches) SR09550033 Con**  **figuration** 1574.7 + 1.1 + 1431.5 SR09550033-7001 SR09550033-7002 1574.7 + 1.1 + 1431.5 SR09550033-7003 SR09550033-7004
**I. Electrical Load Data** Not changed.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 16, 2010 MD80-55A068 18 of 38 **BOEING SERVICE BULLETIN MD80-55A068 ALERT**  **ALERT J. References**  1. Existing Data: a. Non-Destructive Test Standard Practices Manual (NDTSPM) 06-00-07, 06-10-01.001, 06-10-02.005. b. MD80 Aircraft Maintenance Manual (AMM) 55-10-00, 55-10-01. 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: 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:
**ADCN DCN/REV**  **Sheet Title**  **Drawing No**

- - DWG PANEL INSTL-UPPER & LOWER CTR PANEL, HORIZONTAL STABILIZER SR09550033

3. Installation Drawings Used in the Preparation of this Service Bulletin: **Change Title**  **Document Number** T PANEL-SKIN AND STGR, HORIZ STAB, CTR 5922577

DA STRUCT ASSEM-HORIZ STAB OUTER PANEL FRONT TO REAR SPAR 5922575

BF STABILIZER ASSY-COMPLETE HORIZONTAL 5930603

These drawings were used to prepare this service bulletin. These drawings are not necessary to make the specified changes, and are not supplied with this service bulletin. These drawings may not be applicable to all airplane configurations or operators. **K. Publications Affected** 1. Publications:

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 16, 2010 MD80-55A068 19 of 38 **BOEING SERVICE BULLETIN MD80-55A068 ALERT**  **ALERT**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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 16, 2010 MD80-55A068 20 of 38 **BOEING SERVICE BULLETIN MD80-55A068 ALERT**  **ALERT 2. MATERIAL INFORMATION**  **A. Material - Price and Availability** Boeing can supply the kits shown below which contain the parts listed 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

**Group 1: REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RE**  **SPONDER AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION** 
**Unit Price as of the original issue** **date of this Ser vice Bulletin (US**  **Dollars) ROLT as of the**  **original issue date of this Ser** **vice Bulletin (Cal endar Days)**  **Name Kit Number** 

$36,405.00 120 Service Kit - Upper Center SA09550068-3 Skin Panel (Left) $36,405.00 120 Service Kit - Upper Center SA09550068-5 Skin Panel (Right) **Group 2: REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RE**  **SPONDER AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION** 
**Unit Price as of the original issue** **date of this Ser vice Bulletin (US**  **Dollars) ROLT as of the**  **original issue date of this Ser** **vice Bulletin (Cal endar Days)**  **Name Kit Number** 

$54,071.00 120 Service Kit - Upper Center SA09550068-7 Skin Panel (Left) $54,071.00 120 Service Kit - Upper Center SA09550068-9 Skin Panel (Right)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 16, 2010 MD80-55A068 21 of 38 **BOEING SERVICE BULLETIN MD80-55A068 ALERT**  **ALERT**Boeing can supply the parts shown below as end item spares. Operators are encouraged to share schedule requirements with Boeing for incorporation of the service bulletin. The parts 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** **date of this Ser vice Bulletin (US**  **Dollars) ROLT as of the**  **original issue date of this Ser** **vice Bulletin (Cal endar Days)**  **Name Part Number** 

$23,995.00 120 Upper Center Skin Panel (Left) SE09550017-6 (a) (5922577-508) $23,995.00 120 Upper Center Skin Panel (Right) SE09550017-5 (a) (5922577-507) (a) A limited quantity of parts are available. Please contact spares for parts availability. Once the supply is exhausted this part will no longer be available. **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. **NOTE:** One top kit per panel location (left or right) and the items shown in Paragraph 2.C.2., Parts and Materials Supplied by the Operator, are necessary for each airplane. **Group 1: SERVICE KIT APPLICABILITY**  **SR Drawing Configuration Name**  **SA Kit Number** SR09550033-7005 Service Kit - Upper Center SA09550068-3 Skin Panel (Left) SR09550033-7007 Service Kit - Upper Center SA09550068-5 Skin Panel (Right)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 16, 2010 MD80-55A068 22 of 38 **BOEING SERVICE BULLETIN MD80-55A068 ALERT**  **ALERT Group 2:**  **SERVICE KIT APPLICABILITY SR Drawing Configuration**  **Name SA Kit Number**  SR09550033-7001 Service Kit - Upper Center SA09550068-7 Skin Panel (Left) SR09550033-7003 Service Kit - Upper Center SA09550068-9 Skin Panel (Right) **Group 1:**
**Kit SA09550068 Notes**  **Existing Part Number**  **Name QTY**  **New Part Number -5**  **-3** (a)

. - SA09550068-3 (a)

- . SA09550068-5 NUT BARREL 7 7 117LH7940T-054 (b) 5930603-9 FILLER 14 14 3964835-511 NUT ASSEMBLY 1 1 3D0006-3 NUT ASSEMBLY 1 1 3D0006-4 BOLT 6 6 3D0031-5-22 BOLT 1 1 3D0031-5-24 (c) 5922577-501 UPPER PANEL (RIGHT) 1

. 5922577-511 or 5922577-507 (d) 5922577-502 UPPER PANEL (LEFT) . 1 5922577-512 or 5922577-508 WASHER 7 7 73232-5-8.1 PIN 14 14 HLT435-6-3 PIN 27 27 HLT435-6-4 PIN 7 7 HLT435-6-5 PIN 5 5 HLT435-6-6 PIN 2 2 HLT435-6-8 PIN 15 15 HLT435-8-3 PIN 43 43 HLT435-8-4 PIN 1 1 HLT435-8-5 PIN 58 58 HLT439-8-3

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 16, 2010 MD80-55A068 23 of 38 **BOEING SERVICE BULLETIN MD80-55A068 ALERT**  **ALERT Group 1:** 
**Kit SA09550068 Notes**  **Existing Part Number**  **Name QTY**  **New Part Number -5**  **-3** RIVET 12 12 MS20426AD5-6D RIVET 44 44 MS20426AD5-7D RIVET 6 6 MS20426AD5-8D RIVET 8 8 MS20426AD6-8D RIVET 7 7 MS20426E8-12D RIVET 37 37 MS20426E8-9D RIVET 16 16 MS20470AD6-7D RIVET 22 22 MS20470AD6-8D NUT 58 58 MS21042L3 NUT 116 116 MS21042L4 RIVET 54 54 NAS1097KE8-10D RIVET 2 2 NAS1097KE8-11D RIVET 11 11 NAS1097KE8-12D RIVET 110 110 NAS1097KE8-9D WASHER 58 58 NAS1252-10L WASHER 116 116 NAS1252-416L PIN 4 4 S4931919-6-5 (a) If grip length shown is not available at Boeing, fasteners supplied in kits may be one grip length longer than indicated. Also, if any fasteners part numbers listed are not available or have been superseded, substitute fasteners may be supplied in kits. (b) 5930603-9 Filler may be used in lieu of 3964835-511 Filler. (c) 5922577-507 Upper Center Skin Panel may be used in lieu of 5922577-511 Upper Center Skin Panel. (d) 5922577-508 Upper Center Skin Panel may be used in lieu of 5922577-512 Upper Center Skin Panel. **Group 2:**
**Kit SA09550068 Notes**  **Existing Part Number**  **Name QTY**  **New Part Number -9**  **-7** (a)

. - SA09550068-7

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 16, 2010 MD80-55A068 24 of 38 **BOEING SERVICE BULLETIN MD80-55A068 ALERT**  **ALERT Group 2:** 
**Kit SA09550068 Notes**  **Existing Part Number**  **Name QTY**  **New Part Number -9**  **-7** (a)

- . SA09550068-9 NUT BARREL 7 7 117LH7940T-054 (b) 5930603-9 FILLER 14 14 3964835-511 NUT ASSEMBLY 1 1 3D0006-3 BOLT 6 6 3D0031-5-22 BOLT 1 1 3D0031-5-24 (c) 5922577-507 UPPER PANEL (RIGHT) 1

. 5922577-511 (d) 5922577-508 UPPER PANEL (LEFT) . 1 5922577-512

WASHER 7 7 73232-5-8.1 PIN 14 14 HLT435-6-3 PIN 27 27 HLT435-6-4 PIN 7 7 HLT435-6-5 PIN 5 5 HLT435-6-6 PIN 2 2 HLT435-6-8 PIN 73 73 HLT435-8-3 PIN 43 43 HLT435-8-4 RIVET 12 12 MS20426AD5-6D RIVET 44 44 MS20426AD5-7D RIVET 6 6 MS20426AD5-8D RIVET 8 8 MS20426AD6-8D RIVET 16 16 MS20470AD6-7D RIVET 22 22 MS20470AD6-8D NUT 58 58 MS21042L3 NUT 116 116 MS21042L4 RIVET 54 54 NAS1097KE8-10D RIVET 2 2 NAS1097KE8-11D RIVET 18 18 NAS1097KE8-12D RIVET 147 147 NAS1097KE8-9D

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 16, 2010 MD80-55A068 25 of 38 **BOEING SERVICE BULLETIN MD80-55A068 ALERT**  **ALERT Group 2:** 
**Kit SA09550068 Notes**  **Existing Part Number**  **Name QTY**  **New Part Number -9**  **-7** WASHER 58 58 NAS1252-10L WASHER 116 116 NAS1252-416L PIN 4 4 S4931919-6-5 (a) If grip length shown is not available at Boeing, fasteners supplied in kits may be one grip length longer than indicated. Also, if any fasteners part numbers listed are not available or have been superseded, substitute fasteners may be supplied in kits. (b) 5930603-9 Filler may be used in lieu of 3964835-511 Filler. (c) 5922577-507 Upper Center Skin Panel may be used in lieu of 5922577-511 Upper Center Skin Panel. (d) 5922577-508 Upper Center Skin Panel may be used in lieu of 5922577-512 Upper Center Skin Panel.

2. Parts and Materials Supplied by the Operator:
**Notes QTY**  **Name Part Number/Specification**  (a) As Required Sealant PR-1422 B-2 (DMS 2082) or Equivalent

**CAGE Supplier**  83574 PRC - DeSoto International, Incorporated (a) Can be purchased from: 24811 Avenue Rockefeller Valencia, California 91355 -3468
3. Parts Modified and Reidentified: None. 4. Parts Removed and Not Replaced: None. **D. Parts Necessary to Change Spares** None.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 16, 2010 MD80-55A068 26 of 38 **BOEING SERVICE BULLETIN MD80-55A068 ALERT**  **ALERT E. Special Tooling - Price and Availability**  None. **F. Special Tooling Necessary to do this Service Bulletin** No special tools or equipment are necessary to do the change in this service bulletin. But, maintenance and overhaul tools in the manuals given in Paragraph 1.J., References, can be necessary. Examine operator tool supply to make sure all necessary tools are available.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 16, 2010 MD80-55A068 27 of 38 **BOEING SERVICE BULLETIN MD80-55A068 ALERT**  **ALERT**BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 16, 2010 MD80-55A068 28 of 38 **BOEING SERVICE BULLETIN MD80-55A068 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. The instructions identified in Paragraph 3.B., Work Instructions, and the Figure(s) give the recommended sequence of steps. The sequence of steps to do this service bulletin can be changed. 2. Manual titles are referred to by acronyms. Refer to Paragraph 1.J., References, for definition of the acronyms. 3. Equivalent parts are listed in the AEPL, Drawing 7595071. 4. Use the approved fastener substitutions and process material substitutions, in accordance with MD-80 Structural Repair Manual (SRM) 51. 5. If the length of any fastener specified in this service bulletin does not meet the installation standards in MD-80 SRM 51, then a fastener of the same specification, or an approved substitute, with a length which meets the installation standards in MD-80 SRM 51 may be used. 6. 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. 7. 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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 16, 2010 MD80-55A068 29 of 38 **BOEING SERVICE BULLETIN MD80-55A068 ALERT**  **ALERT**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. **B. WORK INSTRUCTIONS GROUP 1:**  1. Do an eddy current inspection of the horizontal stabilizer left and right upper center skin panels in accordance with FIGURE 1 and based on inspection results for each panel, do as follows:
**Condition 1 (No Crack Found)** a. Do repetitive eddy current inspections of the horizontal stabilizer upper center skin panel in accordance with FIGURE 1, at intervals specified in Paragraph 1.E., Compliance. **Condition 2 (Crack Found)** a. OPTION 1: (1) Remove and keep horizontal stabilizer. Refer to MD80 AMM 55-10-00. (2) Remove and keep horizontal stabilizer leading edge. Refer to MD80 AMM 55-10-01. (3) Remove and keep horizontal stabilizer upper forward skin panel to gain access to the cracked horizontal stabilizer upper center skin panel. Refer to drawing 5922575. (4) Remove and replace the cracked horizontal stabilizer upper center skin panel in accordance with the applicable configuration of Service Rework Drawing SR09550033 using the applicable kit as follows:
**KIT SA09550068**  **CENTER SKIN PANEL LOCATION**  **DRAWING SR09550033**  -3 UPPER LEFT -7005 -5 UPPER RIGHT -7007 (5) Install kept horizontal stabilizer upper forward skin panel. Refer to drawing 5922575 and MD80 SRM 51.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 16, 2010 MD80-55A068 30 of 38 **BOEING SERVICE BULLETIN MD80-55A068 ALERT**  **ALERT**(6) Install kept horizontal stabilizer leading edge. Refer to MD80 AMM 55-10-01. (7) Install kept horizontal stabilizer. Refer to MD80 AMM 55-10-00. (8) Do repeat eddy current inspection of the replacement horizontal stabilizer upper center skin panel in accordance with FIGURE 1, at intervals specified in Paragraph 1.E., Compliance. b. OPTION 2: (1) Contact Boeing for possible temporary repair of crack and do the repair in accordance with Boeing's instructions. 2. Put the airplane back to serviceable condition. **GROUP 2:** 1. Do an eddy current inspection of the horizontal stabilizer left and right upper center skin panels in accordance with FIGURE 1 and based on inspection results for each panel, do as follows:
**Condition 1 (No Crack Found)** a. Do repeat eddy current inspections of the horizontal stabilizer upper center skin panel in accordance with FIGURE 1, at intervals specified in Paragraph 1.E., Compliance. **Condition 2 (Crack Found)** a. OPTION 1: (1) Remove and keep horizontal stabilizer. Refer to MD80 AMM 55-10-00. (2) Remove and keep horizontal stabilizer leading edge. Refer to MD80 AMM 55-10-01. (3) Remove and keep horizontal stabilizer upper forward skin panel to gain access to the cracked horizontal stabilizer upper center skin panel. Refer to drawing 5922575. (4) Remove and replace the cracked horizontal stabilizer upper center skin panel in accordance with the applicable configuration of Service Rework Drawing SR09550033 using the applicable kit as follows:
**KIT SA09550068**  **CENTER SKIN PANEL LOCATION**  **DRAWING SR09550033**  -7 UPPER LEFT -7001 -9 UPPER RIGHT -7003 (5) Install kept horizontal stabilizer upper forward skin panel. Refer to drawing 5922575 and MD80 SRM 51.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 16, 2010 MD80-55A068 31 of 38 **BOEING SERVICE BULLETIN MD80-55A068 ALERT**  **ALERT**(6) Install kept horizontal stabilizer leading edge. Refer to MD80 AMM 55-10-01. (7) Install kept horizontal stabilizer. Refer to MD80 AMM 55-10-00. (8) Do repeat eddy current inspection of the replacement horizontal stabilizer upper center skin panel in accordance with FIGURE 1, at intervals specified in Paragraph 1.E., Compliance. b. OPTION 2: (1) Contact Boeing for possible temporary repair of crack and do the repair in accordance with Boeing's instructions. 2. Put the airplane back to serviceable condition.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 16, 2010 MD80-55A068 32 of 38 **BOEING SERVICE BULLETIN MD80-55A068 ALERT**  **ALERT FIGURE 1: HORIZONTAL STABILIZER LEFT AND RIGHT UPPER CENTER SKIN PANELS - EDDY CURRENT**  **INSPECTION (SHEET 1 OF 6)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 16, 2010 MD80-55A068 33 of 38 **BOEING SERVICE BULLETIN MD80-55A068 ALERT**  **ALERT FIGURE 1: HORIZONTAL STABILIZER LEFT AND RIGHT UPPER CENTER SKIN PANELS - EDDY CURRENT**  **INSPECTION (SHEET 2 OF 6)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 16, 2010 MD80-55A068 34 of 38 **BOEING SERVICE BULLETIN MD80-55A068 ALERT**  **ALERT FIGURE 1: HORIZONTAL STABILIZER LEFT AND RIGHT UPPER CENTER SKIN PANELS - EDDY CURRENT**  **INSPECTION (SHEET 3 OF 6)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 16, 2010 MD80-55A068 35 of 38 **BOEING SERVICE BULLETIN MD80-55A068 ALERT**  **ALERT FIGURE 1: HORIZONTAL STABILIZER LEFT AND RIGHT UPPER CENTER SKIN PANELS - EDDY CURRENT**  **INSPECTION (SHEET 4 OF 6)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 16, 2010 MD80-55A068 36 of 38 **BOEING SERVICE BULLETIN MD80-55A068 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.
**MORE DATA QTY**  **IDENTIFICATION NAME**  **TASK STEP**  (a) (e) 1 5922577-501 Upper Center Skin Panel - Right Inspect - (Scan 1) OPTION 1, 2: 1 or Eddy Current, High Frequency (ETHF) 5922577-507 or 5922577-511 or SE09550017-5 5922577-502 Upper Center Skin Panel - Left or 5922577-508 or 5922577-512 or SE09550017-6 (b) (e) 1 5922577-501 Upper Center Skin Panel - Right Inspect - (Scan 2) OPTION 1, 2: 2 or Eddy Current, High Frequency (ETHF) 5922577-507 or 5922577-511 or SE09550017-5 5922577-502 Upper Center Skin Panel - Left or 5922577-508 or 5922577-512 or SE09550017-6 (c) (e) 1 5922577-501 Upper Center Skin Panel - Right Inspect - (Scan 3) OPTION 1: 3 or Eddy Current, Low Frequency (ETLF) 5922577-507 or 5922577-511 or SE09550017-5 5922577-502 Upper Center Skin Panel - Left or 5922577-508 or 5922577-512 or SE09550017-6

**FIGURE 1: HORIZONTAL STABILIZER LEFT AND RIGHT UPPER CENTER SKIN PANELS - EDDY CURRENT INSPECTION**  **(SHEET 5 OF 6)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 16, 2010 MD80-55A068 37 of 38 **BOEING SERVICE BULLETIN MD80-55A068 ALERT**  **ALERT MORE DATA**  **QTY IDENTIFICATION**  **NAME TASK**  **STEP** Inspect - (Scan 3) (d) (e) 1 5922577-501 Upper Center Skin Panel - Right or OPTION 2: 5922577-507 Eddy Current, High Frequency (ETHF) or 5922577-511 or SE09550017-5 5922577-502 Upper Center Skin Panel - Left or 5922577-508 or 5922577-512 or SE09550017-6 Do an Eddy Current, High Frequency surface inspection of the horizontal stabilizer upper centerskin panels around the fastener in the inspection area. Scan around the fastener using a nonconductive circle template looking for cracks propagating from the fastener hole. Refer to NDTSPM 06-10- 01.001 (ETHF - Procedure 1). Use Calibration Method "P" and Scan Method "47". (a)

Do an Eddy Current, High Frequency surface inspection of the horizontal stabilizer upper center skin panels along the inboard portion of the aft edge as shown in the inspection area. Scan the edgeslooking for cracks propagating from the panel edge. Refer to NDTSPM 06-10-01.001 (ETHF - Procedure 1). Use Calibration Method "A" and Scan Method "79". (b)

Do an Eddy Current, Low Frequency sub-surface inspection of the horizontal stabilizer upper center skin panels at all other areas in the rectangular shaped inspection area not inspected by Scan 1 or 2. Scan the noted area of the upper surface of the upper panels. Refer to NDTSPM 06-10-02.005 (ETLF - Procedure 5). (c)

NOTE: Space each scan approximately 1/2 probe coil diameter apart. Do an Eddy Current, High Frequency surface inspection of the horizontal stabilizer upper center skin panels at all other areas in the rectangular shaped inspection area not inspected by Scan 1 or 2. Scan the noted area of the upper surface of the upper panels. Refer to NDTSPM 06-10-01.001 (ETHF - Procedure 1).Use Calibration Method "C" and Scan Method "61". (d)

NOTE: Space each scan approximately 1/2 probe coil diameter apart. Evaluate and verify crack indications found during inspection. Refer to NDTSPM 06-00-07. (e)

**FIGURE 1: HORIZONTAL STABILIZER LEFT AND RIGHT UPPER CENTER SKIN PANELS - EDDY CURRENT INSPECTION**  **(SHEET 6 OF 6)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 16, 2010 MD80-55A068 38 of 38 **BOEING SERVICE BULLETIN MD80-55A068 ALERT**  **ALERT**