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July 31, 2008 717-29A0009 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 1 of 45
ALERT ALERT Commercial Airplane Group 717
ALERTALERT Service Bulletin Number: 717-29A0009 Date: July 31, 2008 ATA System: 2921 SUBJECT: HYDRAULIC POWER - Pump, Auxiliary Hydraulic - Auxiliary Hydraulic Pump Wire Installation Change
BOEING PROPRIETARY, CONFIDENTIAL, AND/OR TRADE SECRET Copyright © 2008 The Boeing Company Unpublished Work - All Rights Reserved Boeing claims copyright in each page of this document only to the extent that the page contains copyrightable subject matter.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, BBJ, DC-8, DC-9, DC-10, MD-10, MD-11, MD-80, MD-88, MD-90, and the red-white-and-blue 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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ALERT ALERT
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Table of Contents July 31, 2008 717-29A0009 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 3 of 45 BOEING SERVICE BULLETIN 717-29A0009
ALERT ALERT
Table of Contents Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5
1. PLANNING INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7 A. Effectivity . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7
1. Airplanes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7
2. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8 B. Concurrent Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8 C. Reason . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8 D. Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8 E. Compliance. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8 F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9 G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9 H. Weight and Balance Changes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10 I. Electrical Load Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10 J. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10
1. Existing Data: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10
2. Data supplied with this Service Bulletin: . . . . . . . . . . . . . . . . . . . . . . . . . 10
3. Installation Drawings Used in the Preparation of this Service Bulletin: . . . . . . . . . . 10 K. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11 L. Interchangeability and Intermixability of Parts . . . . . . . . . . . . . . . . . . . . . . . . . 11
2. MATERIAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13 A. Material - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13 B. Industry Support Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13 C. Parts Necessary For Each Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13
1. Kits/Parts: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13
2. Parts and Materials Supplied by the Operator: . . . . . . . . . . . . . . . . . . . . . . 16
3. Parts Modified and Reidentified: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16
4. Parts Removed and Not Replaced: . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16 D. Parts Necessary to Change Spares . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16 E. Special Tooling - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16 F. Special Tooling Necessary to do this Service Bulletin . . . . . . . . . . . . . . . . . . . . . 16
3. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17 A. GENERAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17 B. WORK INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18 FIGURE 1: WIRE ASSEMBLY - CHANGE/ROUTE/CLAMP . . . . . . . . . . . . . . . . . . . . . . 20 FIGURE 2: WIRE ASSEMBLY - CHANGE/ROUTE/CLAMP . . . . . . . . . . . . . . . . . . . . . . 33
Table of Contents July 31, 2008 717-29A0009 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 4 of 45 BOEING SERVICE BULLETIN 717-29A0009
ALERT ALERT
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July 31, 2008 717-29A0009 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 5 of 45
ALERT ALERT Commercial Airplane Group 717
ALERTALERT Service Bulletin Number: 717-29A0009 Summary Date: July 31, 2008 ATA System: 2921 SUBJECT: HYDRAULIC POWER - Pump, Auxiliary Hydraulic - Auxiliary Hydraulic Pump Wire Installation Change
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 determined that the auxiliary hydraulic pump wire assembly located in the right wheel well is in immediate proximity to the center wing fuel tank, within the tire burst area. Moving the auxiliary hydraulic pump wire assembly away from the tire burst debris area will minimize the possibility of wire damage and consequent arcing to center wing fuel tank. Additionally, other wire assembly installations affected by this change must be rerouted. If not corrected, in the event of a tire burst, when the Main Landing Gear (MLG) is in the retracted position, the auxiliary hydraulic pump wire assembly could become severely damaged, causing wire-to-wire or wire-to-structure arcing, resulting in a potential ignition source to the center wing fuel tank and consequent fire or explosion.
This service bulletin is the result of the safety assessments conducted by Boeing under a Special Federal Aviation Regulation SFAR 88, Fuel Tank System Fault Tolerance Evaluation Requirements.
ACTION This service bulletin provides instructions to change the auxiliary hydraulic pump wire installation in the right wheel well.
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.
Boeing recommends that the change given in this service bulletin be done within 5 years, after the date on this service bulletin.
INDUSTRY SUPPORT INFORMATION Boeing warranty remedies are not available for the configuration changes given in this service bulletin.
MANPOWER
MATERIAL INFORMATION Boeing Supplied Kits/Parts.
Refer to Paragraph 2.A., Material - Price and Availability.
Airplanes Total Task Hours Elapsed Hours 717-200 12.4 11.9
AUXILIARY HYDRAULIC PUMP
WIRE INSTALLATION CHANGE
July 31, 2008 717-29A0009 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 7 of 45
ALERT ALERT Commercial Airplane Group 717
ALERTALERT Service Bulletin Number: 717-29A0009 Date: July 31, 2008 ATA System: 2921 SUBJECT: HYDRAULIC POWER - Pump, Auxiliary Hydraulic - Auxiliary Hydraulic Pump Wire Installation Change
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. An equivalent change is on 717 production airplanes, fuselage number 5019 and subsequent.
Airplane manufacturer’s fuselage numbers 5004, 5007, and 5018 had an equivalent modification incorporated at the operators facility as an installation verification.
Airplane models:
717-200
IDENTIFICATION BY CUSTOMER, CUSTOMER CODE, GROUP AND FUSELAGE NUMBER
AIRTRAN AIRWAYS (CQT) 1 5005–5006 2 5008–5012 5017
GROUP CONFIGURATION DESCRIPTION 1 - Applicable to airplanes with wire assemblies 7957939620 and 7957939623 routed along the lower aft edge of the center fuel tank.
2 - Applicable to airplanes with wire assemblies 7957939620 and 7957939623 routed along the auxiliary hydraulic pump support.
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NATIONAL JET SYSTEMS (NJS) 1 5002–5003 2 5013–5014
SPANAIR (SPP) 2 5015–5016
IDENTIFICATION BY FUSELAGE NUMBER
2. Spares Affected None.
B. Concurrent Requirements None.
C. Reason Boeing has determined that the auxiliary hydraulic pump wire assembly located in the right wheel well is in immediate proximity to the center wing fuel tank, within the tire burst area. Moving the auxiliary hydraulic pump wire assembly away from the tire burst debris area will minimize the possibility of wire damage and consequent arcing to center wing fuel tank. Additionally, other wire assembly installations affected by this change must be rerouted. If not corrected, in the event of a tire burst, when the Main Landing Gear (MLG) is in the retracted position, the auxiliary hydraulic pump wire assembly could become severely damaged, causing wire-to-wire or wire-to-structure arcing, resulting in a potential ignition source to the center wing fuel tank and consequent fire or explosion.
An equivalent change is on 717 production airplanes, fuselage number 5019 and subsequent.
Airplane manufacturer’s fuselage numbers 5004, 5007, and 5018 had an equivalent modification incorporated at the operators facility as an installation verification.
This service bulletin is the result of the safety assessments conducted by Boeing under a Special Federal Aviation Regulation SFAR 88, Fuel Tank System Fault Tolerance Evaluation Requirements.
D. Description This service bulletin provides instructions to change the auxiliary hydraulic pump wire installation in the right wheel well.
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.
Fuselage Group 5002–5003 1 5005–5006 1 5008–5017 2
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Boeing recommends that the change given in this service bulletin be done within 5 years, after the date on this service bulletin.
F. Approval The resultant modification described in Paragraph 1.D has been shown to comply with the applicable Federal Aviation Regulations and is approved by the Manager, Los Angeles Aircraft Certification Office, FAA Northwest Mountain Region.
G. Manpower The table below shows an estimate of the task hours necessary to do this change 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 examine the work — Time to cure the materials — Time to make the parts — Time to find the tools.
Task Number of Persons Task Hours Elapsed Hours De-energize 1 0.3 0.3 Open Access 1 0.2 0.2 Figure 1 or 2 1 10.4 10.4 Energize 1 0.3 0.3 Check 2 1.0 0.5 Close Access 1 0.2 0.2 TOTAL FOR EACH AIRPLANE 12.4 11.9
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H. Weight and Balance Changes I. Electrical Load Data Not changed.
J. References
1. Existing Data:
a. 717 Aircraft Maintenance Manual (AMM) 20-20-20, 24-00-00, 29-00-00, 32-00-00, and 32-44-01.
b. 717 Structural Repair Manual (SRM) Chapter 51-00-00.
c. Standard Wiring Practices Manual (SWPM) 20-10-01, 20-20-03, and 20-50-01.
2. Data supplied with this Service Bulletin:
None.
3. Installation Drawings Used in the Preparation of this Service Bulletin:
This drawing was used to prepare this service bulletin. This drawing is not necessary to make the specified changes, and is not supplied with this service bulletin. This drawing may not be applicable to all airplane configurations or operators.
Group 1:
Airplane Approximate Station (Inches) Mfr’s Empty Weight (MEW) LBS Moment Change (MEW) IN.-LBS 717-200 750.0 +2.7 +2025.0 Group 2:
Airplane Approximate Station (Inches) Mfr’s Empty Weight (MEW) LBS Moment Change (MEW) IN.-LBS 717-200 750.0 +2.5 +1875.0 Document Number Title Change SR95290009 Reroute Auxiliary Hydraulic Pump Wire Assembly - Right Main Wheel Well K
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K. Publications Affected L. Interchangeability and Intermixability of Parts Accomplishment of this service bulletin does not affect interchangeability or intermixability of parts.
Publication Chapter-Section Illustrated Parts Catalog 29-21 Aircraft Maintenance Manual 29-21
July 31, 2008 717-29A0009 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 12 of 45 BOEING SERVICE BULLETIN 717-29A0009