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Commercial Airplanes 717 Service Bulletin ALERT Number: 717-55A0011 Original Issue: May 17, 2011 ATA System: 5510 SUBJECT: STABILIZERS - Horizontal Stabilizer - Inspect/Repair/Replace Horizontal Stabilizer Center Section Left and Right Rib Hinge Bearing Lugs 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BOEING PROPRIETARY, CONFIDENTIAL, AND/OR TRADE SECRET Copyright © 2011 The Boeing Company Unpublished Work - All Rights Reserved Boeing claims copyright in each page of this document only to the extent that the page contains copyrightable subject matter.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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Table of Contents

Summary5

1. PLANNING INFORMATION9

A. Effectivity9

1. Airplanes9

2. Spares Affected9

B. Concurrent Requirements9

C. Reason ................................................ 1 0 D. Description .............................................. 1 0 E. Compliance .............................................. 1 1 F. Approval ............................................... 1 4 G. Manpower .............................................. 1 4 H. Weight and Balance Changes .................................... 1 4 I. Electrical Load Data ......................................... 1 4 J. References .............................................. 1 5

1. Existing Data .......................................... 1 5

2. Data supplied with this Service Bulletin ............................ 1 5

3. Installation Drawings Used in the Preparation of this Service Bulletin ............ 1 5 K. Publications Affected ........................................ 1 5 L. Interchangeability and Intermixability of Parts ........................... 1 5

2. MATERIAL INFORMATION ........................................ 1 7 A. Material - Price and Availability ................................... 1 7 B. Industry Support Information .................................... 1 7 C. Parts Necessary For Each Airplane ................................. 1 7

1. Kits/Parts ............................................ 1 7

2. Parts and Materials Supplied by the Operator ........................ 1 8

3. Parts Modified and Reidentified ................................ 1 8

4. Parts Removed and Not Replaced .............................. 1 8 D. Parts Necessary to Change Spares ................................. 1 8 E. Special Tooling - Price and Availability ............................... 1 8 F. Special Tooling Necessary to do this Service Bulletin ....................... 1 8

3. ACCOMPLISHMENT INSTRUCTIONS .................................. 1 9 A. GENERAL INFORMATION ..................................... 1 9 B. WORK INSTRUCTIONS ....................................... 2 0 FIGURE 1: INSPECT HORIZONTAL STABILIZER CENTER SECTION RIB HINGE BEARING LUGS . 23 FIGURE 2: CRACK LENGTH MEASUREMENT .............................. 2 7 FIGURE 3: BLEND OUT REPAIR ..................................... 3 0 FIGURE 4: INSPECT HORIZONTAL STABILIZER CENTER SECTION RIB HINGE BEARING LUGS . 40 APPENDIX A: TEMPLATE/SHIELD SHOP AID ................................ 4 2

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Commercial Airplanes 717 Service Bulletin ALERT SummaryNumber: 717-55A0011Original Issue: May 17, 2011 ATA System: 5510 SUBJECT: STABILIZERS - Horizontal Stabilizer - Inspect/Repair/Replace Horizontal Stabilizer Center Section Left and Right Rib Hinge Bearing Lugs

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 Boeing has received reports of cracks found on either the left, right, or in few instances both, of the horizontal stabilizer center section ribs on MD-80 and MD-90 airplanes. Two cracks were reported on MD-80 airplanes with between 23,700 and 41,963 flight-hours and 23,300 and 35,294 flight cycles. Nine cracks were reported on MD-90 airplanes with between 9,051 and 26,053 flight-hours and 8,939 and 25,260 flight cycles. These cracks were found on the aft face of the horizontal stabilizer hinge bearing lugs. Although there have been no reports of cracks found on 717 airplanes, they utilize the same rib design as the MD-80 and MD-90 airplanes, and are susceptible to the same failure mode. Investigation by Boeing has yet to establish the definitive cause of these cracks. Performing an Eddy Current, High Frequency (ETHF) inspection of the affected area will determine the existence of any crack. Doing a blend out repair of any existing crack within repair limits will help minimize crack growth. If not corrected, undetected cracks in the center section left and right rib hinge bearing lugs could spread at the same time, which would cause both hinge bearing lugs to fail, resulting in the inability of the horizontal stabilizer to sustain flight loads and consequent reduced controllability of the airplane.

ACTION This service bulletin provides instructions to do an ETHF inspection for cracks on the horizontal stabilizer center section left and right rib hinge bearing lugs. Refer to Paragraph 1.D., Description for the required corrective action based on the results of the inspection.

EFFECTIVITY 717-200 Airplanes. Refer to Paragraph 1.A.1., Airplanes, for the list of affected airplanes.

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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, repair and/or replacement 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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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 Inspect Horizontal Stabilizer Center Section Left and Right Rib Hinge Bearing Lugs on 717-200 airplanes.

-1 Airplane Models:

717-200 GroupFuselage Number 15002 - 5156

2. Spares Affected None.

B. Concurrent Requirements None.

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C. Reason Boeing has received reports of cracks found on either the left, right, or in few instances both, of the horizontal stabilizer center section ribs on MD-80 and MD-90 airplanes. Two cracks were reported on MD-80 airplanes with between 23,700 and 41,963 flight-hours and 23,300 and 35,294 flight cycles.

Nine cracks were reported on MD-90 airplanes with between 9,051 and 26,053 flight-hours and 8,939 and 25,260 flight cycles. These cracks were found on the aft face of the horizontal stabilizer hinge bearing lugs. Although there have been no reports of cracks found on 717 airplanes, they utilize the same rib design as the MD-80 and MD-90 airplanes, and are susceptible to the same failure mode.

Investigation by Boeing has yet to establish the definitive cause of these cracks. Performing an Eddy Current, High Frequency (ETHF) inspection of the affected area will determine the existence of any crack. Doing a blend out repair of any existing crack within repair limits will help minimize crack growth.

If not corrected, undetected cracks in the center section left and right rib hinge bearing lugs could spread at the same time, which would cause both hinge bearing lugs to fail, resulting in the inability of the horizontal stabilizer to sustain flight loads and consequent reduced controllability of the airplane.

D. Description This service bulletin provides instructions to do an ETHF inspection for cracks on the horizontal stabilizer center section left and right rib hinge bearing lugs, and does as follows:

CONDITION 1 (No Crack Found in Rib Hinge Bearing Lug)

1. Does repeat ETHF inspection.

CONDITION 2 (Crack Found in Rib Hinge Bearing Lug)

1. Measures the length of the crack and does as follows:

CONDITION 2A (Crack Length Between Points 'A' and 'B' is Less Than or Equal to 0.15 Inch, AND Crack Length Between Points 'C' and 'D' is Less Than or Equal to 0.05 Inch)

a. Does blend out repair to remove crack.

b. Does repeat ETHF inspection of the blend out area.

CONDITION 2B (No Crack Found During ETHF Inspection After Blend Out Repair)

(1) Does repeat ETHF inspection of the blend out area.

CONDITION 2C (Crack Found During ETHF Inspection After Blend Out Repair)

(1) Removes cracked horizontal stabilizer center section rib and installs new horizontal stabilizer center section rib.

(2) Does ETHF inspection of the horizontal stabilizer center section rib hinge bearing lug.

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CONDITION 2D (Crack Length Between Points 'A' and 'B' is Greater Than 0.15 Inch, OR Crack Length Between Points 'C' and 'D' is Greater Than 0.05 Inch)

a. Removes cracked horizontal stabilizer center section rib and installs new horizontal stabilizer center section rib.

b. Does ETHF inspection of the horizontal stabilizer center section rib hinge bearing lug.

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

Affected Maintenance Zones ZoneModel 351, 361717-200 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.

Table 1 - Inspect Horizontal Stabilizer Center Section Left and Right Rib Hinge Bearing Lugs for Cracks:

Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition -Within 8,275 flight cycles after the original issue date on this service bulletin.

Before the accumulation of 35,000 total flight cycles.

Do an ETHF inspection of the aft face of the horizontal stabilizer center section left and right rib hinge bearing lugs in accordance with Paragraph

3.B.2., Work Instructions.

All Airplanes 10,500 flight cycles.

Within 10,500 flight cycles from last inspection.

Do an ETHF inspection of the aft face of the uncracked horizontal stabilizer center section rib hinge bearing lug in accordance with Paragraph 3.B.2., Work Instructions.

CONDITION 1 (No Crack Found in Rib Hinge Bearing Lug) -Before further flight.Measure the length of the crack in accordance with Paragraph 3.B.2., Work Instructions.

CONDITION 2 (Crack Found In Rib Hinge Bearing Lug)

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Table 1 - Inspect Horizontal Stabilizer Center Section Left and Right Rib Hinge Bearing Lugs for Cracks:

Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition -Before further flight.Do blend out repair in accordance with Paragraph

3.B.2., Work Instructions.

CONDITION 2A (Crack Length Between Points 'A' and 'B' is Less Than or Equal to 0.15 Inch, AND Crack Length Between Points 'C' and 'D' is Less Than or Equal to 0.05 Inch.)

AND -Within 14,200 flight cycles after blend out repair.

Do an ETHF inspection of the blend out area on the horizontal stabilizer center section rib hinge bearing lug in accordance with Paragraph 3.B.2., Work Instructions.

5,400 flight cycles.-Do repetitive ETHF inspection of the blend out area on the horizontal stabilizer center section rib hinge bearing lug in accordance with Paragraph 3.B.2., Work Instructions.

CONDITION 2B (No Crack Found During ETHF Inspection After Blend Out Repair)

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