Airworthiness Directives; Boeing Model 757 Airplanes, 41963-41968 [E7-14867]

Download as PDF Federal Register / Vol. 72, No. 147 / Wednesday, August 1, 2007 / Proposed Rules (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO. Issued in Renton, Washington, on July 18, 2007. Stephen P. Boyd, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 07–3712 Filed 7–31–07; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2006–26710; Directorate Identifier 2006–NM–147–AD] RIN 2120–AA64 Airworthiness Directives; Boeing Model 757 Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Supplemental notice of proposed rulemaking (NPRM); reopening of comment period. pwalker on PROD1PC71 with PROPOSALS AGENCY: SUMMARY: The FAA is revising an earlier proposed airworthiness directive (AD) for all Boeing Model 757 airplanes. The original NPRM would have required revising the Airworthiness Limitations (AWLs) section of the Instructions for Continued Airworthiness by incorporating new limitations for fuel tank systems to satisfy Special Federal Aviation Regulation No. 88 requirements. The original NPRM also would have required the initial inspection of certain repetitive inspections specified in the AWLs to phase-in those inspections, and repair if necessary. The original NPRM resulted from a design review of the fuel tank systems. This action revises the original NPRM by aligning the compliance time for revising the AWLs section with the compliance date of the special maintenance program requirements, updating the listing of applicable airplane maintenance manuals in Appendix 1, and clarifying certain actions. We are proposing this supplemental NPRM to prevent the potential for ignition sources inside fuel tanks caused by latent failures, alterations, repairs, or maintenance actions, which, in combination with flammable fuel vapors, could result in a fuel tank explosion and consequent loss of the airplane. DATES: We must receive comments on this supplemental NPRM by August 27, 2007. VerDate Aug<31>2005 18:58 Jul 31, 2007 Jkt 211001 Use one of the following addresses to submit comments on this supplemental NPRM. • DOT Docket Web site: Go to https:// dms.dot.gov and follow the instructions for sending your comments electronically. • Government-wide rulemaking Web site: Go to https://www.regulations.gov and follow the instructions for sending your comments electronically. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590. • Fax: (202) 493–2251. • Hand Delivery: Room W12–140 on the ground floor of the West Building, 1200 New Jersey Avenue, SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124–2207, for service information identified in this proposed AD. FOR FURTHER INFORMATION CONTACT: Kathrine Rask, Aerospace Engineer, Propulsion Branch, ANM–140S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 917–6505; fax (425) 917–6590. SUPPLEMENTARY INFORMATION: ADDRESSES: Comments Invited We invite you to submit any relevant written data, views, or arguments regarding this supplemental NPRM. Send your comments to an address listed in the ADDRESSES section. Include the docket number ‘‘Docket No. FAA– 2006–26710; Directorate Identifier 2006–NM–147–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this supplemental NPRM. We will consider all comments received by the closing date and may amend this supplemental NPRM in light of those comments. We will post all comments submitted, without change, to https://dms.dot.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact with FAA personnel concerning this supplemental NPRM. Using the search function of that web site, anyone can find and read the comments in any of our dockets, including the name of the individual who sent the comment (or signed the comment on behalf of an association, business, labor union, etc.). You may review the DOT’s complete PO 00000 Frm 00016 Fmt 4702 Sfmt 4702 41963 Privacy Act Statement in the Federal Register published on April 11, 2000 (65 FR 19477–78), or you may visit https://dms.dot.gov. Examining the Docket You may examine the AD docket on the Internet at https://dms.dot.gov, or in person at the Docket Operations office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Operations office (telephone (800) 647–5527) is located on the ground level of the West Building at the DOT street address stated in the ADDRESSES section. Comments will be available in the AD docket shortly after the Docket Management System receives them. Discussion We proposed to amend 14 CFR part 39 with a notice of proposed rulemaking (NPRM) for an AD (the ‘‘original NPRM’’) for all Boeing Model 757 airplanes. The original NPRM was published in the Federal Register on January 3, 2007 (72 FR 50). The original NPRM proposed to require revising the Airworthiness Limitations (AWLs) section of the Instructions for Continued Airworthiness by incorporating new limitations for fuel tank systems to satisfy Special Federal Aviation Regulation No. 88 (SFAR 88) requirements. The original NPRM also proposed to require the initial inspection of certain repetitive inspections specified in the AWLs to phase-in those inspections, and repair if necessary. Explanation of Change in Compliance Time In most ADs, we adopt a compliance time allowing a specified amount of time after the AD’s effective date. In this case, however, we have already issued regulations that require operators to revise their maintenance/inspection programs to address fuel tank safety issues. The compliance date for these regulations is December 16, 2008. To provide for efficient and coordinated implementation of these regulations and this supplemental NPRM, we are using this same compliance date in this supplemental NPRM, instead of the 18month compliance time recommended by Boeing. Therefore, we have revised the compliance time in paragraph (g) from ‘‘within 18 months after the effective date of this AD’’ to a compliance date of ‘‘no later than December 16, 2008.’’ Comments We have considered the following comments on the original NPRM. E:\FR\FM\01AUP1.SGM 01AUP1 41964 Federal Register / Vol. 72, No. 147 / Wednesday, August 1, 2007 / Proposed Rules Request To Revise Note 1 Boeing requests that the Note 1 of the original NPRM be revised from ‘‘* * * the operator must request approval for revision * * *’’ to ‘‘* * * the operator must request approval for deviation from * * * .’’ Boeing states that, as written, Note 1 would result in modifications, alternations, or repairs being incorporated into the Boeing 757 Maintenance Planning Data (MPD) Document D622N001–9, Revision March 2006 (referred to in the original NPRM as the appropriate source of service information) that are outside of its configuration definition data and responsibility. Boeing also states that the MPD document is intended to reflect the Boeing 757 type design as defined only by Boeing data. We partially agree. We do not agree with Boeing’s suggested change. We find that Boeing is misinterpreting the intent of Note 1, and that clarification is necessary. The sentence in question states, ‘‘In this situation, * * * the operator must request approval for revision to the airworthiness limitations (AWLs) in the Boeing 757 Maintenance Planning Data (MPD) Document D622N001–9 * * * .’’ The term ‘‘revision’’ refers to the ‘‘airworthiness limitations,’’ not to the MPD document. The modification, alteration, or repair would affect only a few airplanes, so a revision to the MPD document, which would affect the whole fleet, would not be appropriate. However, we do agree with Boeing that a revision to the MPD document may not be necessary. We have determined that operators also can request approval for revision to the AWLs in the MPD document according to paragraph (i) of this supplemental NPRM. Therefore, we have revised Note 1 accordingly. pwalker on PROD1PC71 with PROPOSALS Request To Add Procedures of Boeing 757 MPD Document Boeing requests that the original NPRM be revised to contain the procedures specified in Section 9 of Boeing 757 MPD Document D622N001– 9 or an approved equivalent AWL/ Certification Maintenance Requirement (CMR) document, rather than referring to the MPD document as the source for the procedures. Boeing states that it may move Section 9 (airworthiness limitation section) out of the Boeing 757 MPD document, and thus the AD may need to be revised. We do not agree. We have confirmed with Boeing that it has no immediate plans to change the Boeing 757 MPD document. Therefore, until the Boeing 757 MPD Document D622N001–9 is revised, we consider it appropriate that VerDate Aug<31>2005 16:41 Jul 31, 2007 Jkt 211001 this supplemental NPRM refer to it as the appropriate source of service information for accomplishing the proposed actions. We might consider issuing additional rulemaking or approving alternative methods of compliance to address that concern in the future. We have not changed the supplemental NPRM regarding this issue. Request To Extend Compliance Time United Parcel Service (UPS) requests that, for low cycle operators (less than 800 flight cycles per year), the compliance time for the initial inspections in paragraph (h) of the original NPRM be extended from ‘‘10 years or 36,000 flight cycles’’ to ‘‘16 years (8C) or 36,000 flight cycles, whichever occurs first.’’ UPS states that this will not penalize low-utilization operators. UPS states that it has tank entries approximately every 8 years, and that 16 years lines up better with its maintenance program. UPS also states that a compliance time of 10 years would significantly increase its financial burden. UPS did not submit any data with its comment. We do not agree. In developing the compliance time for the original NPRM, we considered not only the risk of creating an ignition source in the tank, but we also considered the practical aspect of accomplishing the proposed inspections within a period of time that corresponds to the major structural inspections or fuel tank entries to limit the impact on operators. With UPS’s tank entries occurring approximately every 8 years, the 36,000 total flight cycles or 120-month proposed compliance time would allow UPS’s entire fleet to be inspected during scheduled maintenance with an additional 2 years to allow for some scheduling flexibility. However, paragraph (i) of the supplemental NPRM provides operators the opportunity to request an extension of the compliance time if data are presented to justify such an extension. Request To Include an Additional Airworthiness Limitation Boeing requests that we revise paragraph (h) of the original NPRM for completeness to include Airworthiness Limitation 28–AWL–25 (Lightning and Fault Current Protection—Motor Operated Valve Actuator). Boeing notes this AWL was added to Section 9 of the Boeing 757 MPD Document D622N001– 9 in October 2006. We agree with Boeing’s intent; however, we do not agree with including Airworthiness Limitation 28– AWL–25 in this supplemental NPRM. PO 00000 Frm 00017 Fmt 4702 Sfmt 4702 We are considering issuing a separate rulemaking action that would propose to require installation of a new actuator and inspections in accordance with Airworthiness Limitation 28–AWL–25. Request To Revise Numbering of Notes Boeing requests that Notes 2 and 3 of the original NPRM be renumbered. Boeing believes that there are only two notes as part of Table 1 of the original NPRM, and that the notes were incorrectly numbered. We understand Boeing’s concern; however, we do not agree that the notes need to be renumbered. There are total of three notes in the supplemental NPRM. All three notes are correctly numbered. In all ADs, notes are numbered sequentially in the regulatory text. Request To Revise Appendix 1 Boeing requests that Appendix 1 of the original NPRM be revised to include missing task titles and numbers. Boeing provided no justification. We partially agree. Since we issued the original NPRM, the modifications of the motor operated valve actuator have been approved, and the associated airplane maintenance manual (AMM) changes have been released. Therefore, we agree with Boeing to revise columns ‘‘Task Title’’ and ‘‘Task #,’’ as applicable, of Appendix 1 of the supplemental NPRM to include the latest information specified in the AMM that is associated with design changes of the fuel tank system changes. However, we do not agree with Boeing to add task titles for the component maintenance manuals (CMM), because the AWLs cover the entire CMM, not just specific tasks. Explanation of Other Changes to Original NPRM We have revised paragraph (g) of this supplemental NPRM to clarify that the exception refers to the ‘‘initial inspections’’ specified in Table 1 of this AD rather than the ‘‘inspections.’’ We have revised paragraph (h) of this supplemental NPRM to allow the use of later revisions of the MPD. FAA’s Determination and Proposed Requirements of the Supplemental NPRM Some of the changes discussed above expand the scope of the original NPRM; therefore, we have determined that it is necessary to reopen the comment period to provide additional opportunity for public comment on this supplemental NPRM. E:\FR\FM\01AUP1.SGM 01AUP1 Federal Register / Vol. 72, No. 147 / Wednesday, August 1, 2007 / Proposed Rules Costs of Compliance There are about 990 airplanes of the affected design in the worldwide fleet. 41965 The following table provides the estimated costs for U.S. operators to comply with this proposed AD. ESTIMATED COSTS Action Average labor rate per hour Work hours Revision of AWLs section of the Instructions for Continued Airworthiness .................................................................... Detailed and special detailed inspections ........................... 8 8 $80 80 pwalker on PROD1PC71 with PROPOSALS Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, Section 106, describes the authority of the FAA Administrator. Subtitle VII, Aviation Programs, describes in more detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III, Section 44701, ‘‘General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. List of Subjects in 14 CFR Part 39 Regulatory Findings We have determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that the proposed regulation: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; 2. Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and 3. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. We prepared a regulatory evaluation of the estimated costs to comply with this supplemental NPRM and placed it in the AD docket. See the ADDRESSES section for a location to examine the regulatory evaluation. Comments Due Date (a) The FAA must receive comments on this AD action by August 27, 2007. VerDate Aug<31>2005 18:58 Jul 31, 2007 Jkt 211001 Air transportation, Aircraft, Aviation safety, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The Federal Aviation Administration (FAA) amends § 39.13 by adding the following new airworthiness directive (AD): Boeing: Docket No. FAA–2006–26710; Directorate Identifier 2006–NM–147–AD. Affected ADs (b) None. Applicability (c) This AD applies to all Boeing Model 757–200, –200PF, –200CB, and –300 series airplanes, certificated in any category. Note 1: This AD requires revisions to certain operator maintenance documents to include new inspections and maintenance actions. Compliance with these limitations is required by 14 CFR 43.16 and 91.403(c). For airplanes that have been previously modified, altered, or repaired in the areas addressed by these limitations, the operator may not be able to accomplish the actions described in the revisions. In this situation, to comply with 14 CFR 43.16 and 91.403(c), the operator must request approval for revision to the airworthiness limitations (AWLs) in the Boeing 757 Maintenance Planning Data (MPD) Document D622N001– 9 according to paragraph (g) or (i) of this AD. Unsafe Condition (d) This AD results from a design review of the fuel tank systems. We are issuing this AD to prevent the potential for ignition PO 00000 Frm 00018 Fmt 4702 Sfmt 4702 Cost per airplane Number of U.S.-registered airplanes $640 640 639 639 Fleet cost $408,960 408,960 sources inside fuel tanks caused by latent failures, alterations, repairs, or maintenance actions, which, in combination with flammable fuel vapors, could result in a fuel tank explosion and consequent loss of the airplane. Compliance (e) You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. Service Information (f) The term ‘‘Revision March 2006 of the MPD’’ as used in this AD, means Section 9 of Boeing 757 MPD Document D622N001–9, Revision March 2006. Revision of AWLs Section (g) No later than December 16, 2008, revise the AWLs section of the Instructions for Continued Airworthiness by incorporating the information in the sections specified in paragraphs (g)(1) through (g)(3) of this AD into the MPD, except that the initial inspections specified in Table 1 of this AD must be done at the compliance times specified in Table 1. Accomplishing the revision in accordance with a later revision of the MPD is an acceptable method of compliance if the revision is approved by the Manager, Seattle Aircraft Certification Office (ACO), FAA. (1) Section E., ‘‘AIRWORTHINESS LIMITATIONS—FUEL SYSTEMS,’’ of Revision March 2006 of the MPD. (2) Section F., ‘‘PAGE FORMAT: SYSTEMS AIRWORTHINESS LIMITATIONS,’’ of Revision March 2006 of the MPD. (3) Section G., ‘‘AIRWORTHINESS LIMITATIONS—FUEL SYSTEM AWLs’’ of Revision March 2006 of the MPD. Initial Inspections and Repair (h) Do the inspections specified in Table 1 of this AD and repair any discrepancy, in accordance with Section G., ‘‘AIRWORTHINESS LIMITATIONS—FUEL SYSTEM AWLs,’’ of Revision March 2006 of the MPD. The repair must be done before further flight. Accomplishing the actions in accordance with a later revision of the MPD is an acceptable method of compliance if the revision is approved by the Manager, Seattle ACO, FAA. E:\FR\FM\01AUP1.SGM 01AUP1 41966 Federal Register / Vol. 72, No. 147 / Wednesday, August 1, 2007 / Proposed Rules TABLE 1.—INITIAL INSPECTIONS Compliance time (whichever occurs later) Airworthiness limitations Description (1) 28–AWL–01 ..... A detailed inspection of external wires over the center fuel tank for damaged clamps, wire chafing, and wire bundles in contact with the surface of the center fuel tank. (2) 28–AWL–03 ..... A special detailed inspection of the lightning shield to ground termination on the out-of-tank fuel quantity indicating system to verify functional integrity. (3) 28–AWL–14 ..... A special detailed inspection of the fault current bond of the fueling shutoff valve actuator of the center wing tank to verify electrical bond. Threshold Grace period Before the accumulation of 36,000 total flight cycles, or within 120 months since the date of issuance of the original standard airworthiness certificate or the date of issuance of the original export certificate of airworthiness, whichever occurs first. Before the accumulation of 36,000 total flight cycles, or within 120 months since the date of issuance of the original standard airworthiness certificate or the date of issuance of the original export certificate of airworthiness, whichever occurs first. Before the accumulation of 36,000 total flight cycles, or within 120 months since the date of issuance of the original standard airworthiness certificate or the date of issuance of the original export certificate of airworthiness, whichever occurs first. Within 72 months after the effective date of this AD. Note 2: For the purposes of this AD, a detailed inspection is: ‘‘An intensive examination of a specific item, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at an intensity deemed appropriate. Inspection aids such as mirror, magnifying lenses, etc., may be necessary. Surface cleaning and elaborate procedures may be required.’’ examination of a specific item, installation, or assembly to detect damage, failure, or irregularity. The examination is likely to make extensive use of specialized inspection techniques and/or equipment. Intricate cleaning and substantial access or disassembly procedure may be required.’’ Note 3: For the purposes of this AD, a special detailed inspection is: ‘‘An intensive (i)(1) The Manager, Seattle ACO has the authority to approve AMOCs for this AD, if Alternative Methods of Compliance (AMOCs) Within 24 months after the effective date of this AD. Within 60 months after the effective date of this AD. requested in accordance with the procedures found in 14 CFR 39.19. (2) To request a different method of compliance or a different compliance time for this AD, follow the procedures in 14 CFR 39.19. Before using any approved AMOC on any airplane to which the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO. APPENDIX 1. FUEL TANK SYSTEM AIRWORTHINESS LIMITATIONS—APPLICABLE MAINTENANCE MANUALS Airworthiness limitation (AWL) Airworthiness limitation instruction (ALI)/ critical design configuration control limitation (CDCCL) 28–AWL–01 .......... ALI ........................... 28–AWL–02 .......... CDCCL .................... 28–AWL–03 .......... Task title ALI ........................... Airplane Maintenance Manual (AMM) 28–11–00/601. Standard Wiring Practices Manual (SWPM) 20–10–11. AMM 20–55–54/601 ........................... 28–AWL–04 .......... 28–AWL–05 .......... CDCCL .................... CDCCL .................... SWPM 20–10–15 ............................... SWPM 20–10–11 ............................... 28–AWL–06 .......... CDCCL .................... CDCCL .................... 28–AWL–08 .......... CDCCL .................... .................................. CMM 28–41–68 Revision 4 or subsequent revisions. CMM 28–40–56, Revision 4; CMM 28–40–62, revision 3; CMM 28–40– 59, revision 5; or subsequent revisions. SWPM 20–14–12 ............................... AMM 28–41–09/401 ........................... External Wires Over the Center Tank Inspection. Wiring Assembly and Installation Configuration. Fuel Quantity Indicating System (FQIS) Connectors—Inspection/ Check. Assembly of Shield Ground Wires ..... Wiring Assembly and Installation Configuration. ............................................................. 28–AWL–07 .......... pwalker on PROD1PC71 with PROPOSALS ATA section or component maintenance manual (CMM) document 28–AWL–09 .......... CDCCL .................... AMM 29–11–26/401 ........................... Install the Heat Exchanger ................. 28–AWL–10 .......... CDCCL .................... AMM 28–22–07/401 ........................... Install the Fuel Line and Fittings ........ 28–AWL–11 .......... CDCCL .................... ............................................................. ............................................................. VerDate Aug<31>2005 18:58 Jul 31, 2007 Jkt 211001 PO 00000 Frm 00019 Fmt 4702 Sfmt 4702 Task # 28–11–00–206– 221 20–55–54–286– 001 ............................................................. Repair of FQIS Wire Harness ............ Install the Tank Wiring Harness ......... E:\FR\FM\01AUP1.SGM 01AUP1 Varies with configuration 29–11–26–404– 012 28–22–07–404– 005 Federal Register / Vol. 72, No. 147 / Wednesday, August 1, 2007 / Proposed Rules 41967 APPENDIX 1. FUEL TANK SYSTEM AIRWORTHINESS LIMITATIONS—APPLICABLE MAINTENANCE MANUALS—Continued Airworthiness limitation (AWL) Airworthiness limitation instruction (ALI)/ critical design configuration control limitation (CDCCL) 28–AWL–12 .......... CDCCL .................... 28–AWL–13 .......... ATA section or component maintenance manual (CMM) document Task title ............................................................. CDCCL .................... CMM 28–22–08, revision 3; CMM 28–20–02, revision 9; or subsequent revisions. AMM 28–22–03/401 ........................... 28–AWL–14 .......... ALI ........................... AMM 28–21–02/401 ........................... 28–AWL–15 .......... CDCCL .................... AMM 28–21–02/401 ........................... .................................. AMM 28–21–12/401 ........................... CDCCL .................... AMM 28–11–01/401 ........................... Install the Actuator of the Fueling Shutoff Valve. Install the Main Tank Access Door .... .................................. AMM 28–11–02/401 ........................... Install the Center Tank Access Door .................................. AMM 28–11–03/401 ........................... Install the Surge Tank Access Door .. CDCCL .................... AMM 28–11–03/401 ........................... Install the Surge Tank Access Door .. .................................. AMM 28–13–04/201 ........................... Install the Pressure Relief Valve ........ CDCCL .................... AMM 28–11–03/401 ........................... Install the Surge Tank Access Door .. .................................. AMM 28–13–05/401 ........................... 28–AWL–19 .......... CDCCL .................... 28–AWL–20 .......... ALI ........................... Fault Isolation Manual (FIM) 28–22– 00/101. AMM 28–22–00/501 ........................... .................................. ............................................................. 28–AWL–21 .......... ALI ........................... AMM 28–22–00/501 ........................... 28–AWL–22 .......... CDCCL .................... AMM 28–41–24/401 ........................... 28–AWL–23 .......... CDCCL .................... AMM 28–22–01/401 ........................... .................................. AMM 28–22–02/401 ........................... .................................. AMM 28–22–11/401 ........................... .................................. AMM 28–22–12/401 ........................... .................................. AMM 28–26–01/401 ........................... .................................. AMM 28–26–02/401 ........................... Install the Housing of the Vent Flame Arrestor. Engine Fuel Feed System—Fault Isolation. Center Tank Fuel Override Pump Auto Shutoff Functional Test. System Test—Engine Fuel Feed System. System Test—Engine Fuel Feed System. Densitometer Hot Short Protector Installation. Install the Adapter Shaft of the Engine Fuel Shutoff Valve (Spar Valve). Install the Engine Fuel Crossfeed Adapter Shaft. Install the Actuator of the Engine Fuel Shutoff Valve (Spar Valve). Install the Actuator of the Engine Fuel Crossfeed Valve. Install the Adapter Shaft for the Defuel Valve. Install the Defueling Valve Actuator ... CDCCL .................... ALI ........................... CMM 28–20–21 .................................. AMM 28–22–01/401 ........................... .................................. AMM 28–022–02/401 ......................... .................................. AMM 28–22–11/401 ........................... .................................. AMM 28–22–12/401 ........................... .................................. AMM 28–26–01/401 ........................... .................................. AMM 28–26–02/401 ........................... .................................. AMM 28–25–11/401 ........................... ALI ........................... AMM 28–22–00/501 ........................... 28–AWL–16 .......... 28–AWL–17 .......... 28–AWL–18 .......... pwalker on PROD1PC71 with PROPOSALS 28–AWL–24 .......... 28–AWL–25 .......... 28–AWL–26 .......... VerDate Aug<31>2005 19:22 Jul 31, 2007 Jkt 211001 PO 00000 Frm 00020 Fmt 4702 Sfmt 4702 Install the Fuel Boost Pump Assembly or the Fuel Override Pump Assembly. Fueling Shutoff Valve Resistance Check. Install the Fueling Shutoff Valve ........ ............................................................. Install the Adapter Shaft of the Engine Fuel Shutoff Valve (Spar Valve). Install the Engine Fuel Crossfeed Adapter Shaft. Install the Actuator of the Engine Fuel Shutoff Valve (Spar Valve). Install the Actuator of the Engine Fuel Crossfeed Valve. Install the Adapter Shaft for the Defuel Valve. Install the Defueling Valve Actuator ... Install the Actuator of the APU Fuel Shutoff Valve. System Test—Engine Fuel Feed System. E:\FR\FM\01AUP1.SGM 01AUP1 Task # 28–22–03–404– 007 28–21–02–764– 047 28–21–02–404– 019 28–21–12–404– 015 28–11–01–404– 014 28–11–02–404– 019 28–11–03–404– 008 28–11–03–404– 008 28–13–04–402– 014 28–11–03–404– 008 28–13–05–404– 004 28–22–00–725– 507 Varies with Configuration Varies with Configuration 28–41–24–404– 006 28–22–01–404–19 28–22–02–404– 041 28–22–11–404– 007 28–22–12–404– 024 28–26–01–404– 035 28–26–02–404– 015 28–22–01–404–19 28–22–02–404– 041 28–22–11–404– 007 28–22–12–404– 024 28–26–01–404– 035 28–26–02–404– 015 28–25–11–404– 010 Varies with Configuration 41968 Federal Register / Vol. 72, No. 147 / Wednesday, August 1, 2007 / Proposed Rules Issued in Renton, Washington, on July 25, 2007. Stephen P. Boyd, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E7–14867 Filed 7–31–07; 8:45 am] BILLING CODE 4910–13–P W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. • Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments. Examining the AD Docket DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2007–28645; Directorate Identifier 2007–CE–059–AD] RIN 2120–AA64 Airworthiness Directives; EADS SOCATA Model TBM 700 Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). AGENCY: SUMMARY: We propose to adopt a new airworthiness directive (AD) for the products listed above. This proposed AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: pwalker on PROD1PC71 with PROPOSALS This Airworthiness Directive (AD) results from one report about imperfect locking on ground of the upper access door opening interior handle which has enabled its opening without actuating unlocking knob. If not corrected an inadvertent action on the handle without actuating the unlocking knob could lead to a door opening. Investigations identified the unsafe condition resulting from interference between the window trim panel and the handle locking mechanism. The proposed AD would require actions that are intended to address the unsafe condition described in the MCAI. DATES: We must receive comments on this proposed AD by August 31, 2007. ADDRESSES: You may send comments by any of the following methods: • DOT Docket Web Site: Go to https://dms.dot.gov and follow the instructions for sending your comments electronically. • Fax: (202) 493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590. • Hand Delivery: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room VerDate Aug<31>2005 16:41 Jul 31, 2007 Jkt 211001 You may examine the AD docket on the Internet at https://dms.dot.gov; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (telephone (800) 647– 5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Albert Mercado, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329– 4119; fax: (816) 329–4090. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2007–28645; Directorate Identifier 2007–CE–059–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD because of those comments. We will post all comments we receive, without change, to https:// dms.dot.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued EASA Emergency Airworthiness (referred to after this as ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The MCAI states: This Airworthiness Directive (AD) results from one report about imperfect locking on ground of the upper access door opening interior handle which has enabled its opening without actuating unlocking knob. PO 00000 Frm 00021 Fmt 4702 Sfmt 4702 If not corrected an inadvertent action on the handle without actuating the unlocking knob could lead to a door opening. Investigations identified the unsafe condition resulting from interference between the window trim panel and the handle locking mechanism. Requirements of this AD are first, check for proper operation the locking handle and secondly modification of the window trim panel. You may obtain further information by examining the MCAI in the AD docket. Relevant Service Information EADS SOCATA has issued Mandatory Service Bulletin TBM Aircraft SB 70– 150, dated May 2007. The actions described in this service information are intended to correct the unsafe condition identified in the MCAI. FAA’s Determination and Requirements of the Proposed AD This product has been approved by the aviation authority of another country, and is approved for operation in the United States. Pursuant to our bilateral agreement with this State of Design Authority, they have notified us of the unsafe condition described in the MCAI and service information referenced above. We are proposing this AD because we evaluated all information and determined the unsafe condition exists and is likely to exist or develop on other products of the same type design. Differences Between This Proposed AD and the MCAI or Service Information We have reviewed the MCAI and related service information and, in general, agree with their substance. But we might have found it necessary to use different words from those in the MCAI to ensure the AD is clear for U.S. operators and is enforceable. In making these changes, we do not intend to differ substantively from the information provided in the MCAI and related service information. We might also have proposed different actions in this AD from those in the MCAI in order to follow FAA policies. Any such differences are highlighted in a NOTE within the proposed AD. Costs of Compliance Based on the service information, we estimate that this proposed AD would affect about 23 products of U.S. registry. We also estimate that it would take about 2 work-hours per product to comply with the basic requirements of this proposed AD. The average labor rate is $80 per work-hour. Required parts would cost about $5 per product. Where the service information lists E:\FR\FM\01AUP1.SGM 01AUP1

Agencies

[Federal Register Volume 72, Number 147 (Wednesday, August 1, 2007)]
[Proposed Rules]
[Pages 41963-41968]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-14867]


-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-26710; Directorate Identifier 2006-NM-147-AD]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 757 Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Supplemental notice of proposed rulemaking (NPRM); reopening of 
comment period.

-----------------------------------------------------------------------

SUMMARY: The FAA is revising an earlier proposed airworthiness 
directive (AD) for all Boeing Model 757 airplanes. The original NPRM 
would have required revising the Airworthiness Limitations (AWLs) 
section of the Instructions for Continued Airworthiness by 
incorporating new limitations for fuel tank systems to satisfy Special 
Federal Aviation Regulation No. 88 requirements. The original NPRM also 
would have required the initial inspection of certain repetitive 
inspections specified in the AWLs to phase-in those inspections, and 
repair if necessary. The original NPRM resulted from a design review of 
the fuel tank systems. This action revises the original NPRM by 
aligning the compliance time for revising the AWLs section with the 
compliance date of the special maintenance program requirements, 
updating the listing of applicable airplane maintenance manuals in 
Appendix 1, and clarifying certain actions. We are proposing this 
supplemental NPRM to prevent the potential for ignition sources inside 
fuel tanks caused by latent failures, alterations, repairs, or 
maintenance actions, which, in combination with flammable fuel vapors, 
could result in a fuel tank explosion and consequent loss of the 
airplane.

DATES: We must receive comments on this supplemental NPRM by August 27, 
2007.

ADDRESSES: Use one of the following addresses to submit comments on 
this supplemental NPRM.
     DOT Docket Web site: Go to https://dms.dot.gov and follow 
the instructions for sending your comments electronically.
     Government-wide rulemaking Web site: Go to https://
www.regulations.gov and follow the instructions for sending your 
comments electronically.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590.
     Fax: (202) 493-2251.
     Hand Delivery: Room W12-140 on the ground floor of the 
West Building, 1200 New Jersey Avenue, SE., Washington, DC, between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, 
Washington 98124-2207, for service information identified in this 
proposed AD.

FOR FURTHER INFORMATION CONTACT: Kathrine Rask, Aerospace Engineer, 
Propulsion Branch, ANM-140S, FAA, Seattle Aircraft Certification 
Office, 1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone 
(425) 917-6505; fax (425) 917-6590.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to submit any relevant written data, views, or 
arguments regarding this supplemental NPRM. Send your comments to an 
address listed in the ADDRESSES section. Include the docket number 
``Docket No. FAA-2006-26710; Directorate Identifier 2006-NM-147-AD'' at 
the beginning of your comments. We specifically invite comments on the 
overall regulatory, economic, environmental, and energy aspects of this 
supplemental NPRM. We will consider all comments received by the 
closing date and may amend this supplemental NPRM in light of those 
comments.
    We will post all comments submitted, without change, to https://
dms.dot.gov, including any personal information you provide. We will 
also post a report summarizing each substantive verbal contact with FAA 
personnel concerning this supplemental NPRM. Using the search function 
of that web site, anyone can find and read the comments in any of our 
dockets, including the name of the individual who sent the comment (or 
signed the comment on behalf of an association, business, labor union, 
etc.). You may review the DOT's complete Privacy Act Statement in the 
Federal Register published on April 11, 2000 (65 FR 19477-78), or you 
may visit https://dms.dot.gov.

Examining the Docket

    You may examine the AD docket on the Internet at https://
dms.dot.gov, or in person at the Docket Operations office between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays. The 
Docket Operations office (telephone (800) 647-5527) is located on the 
ground level of the West Building at the DOT street address stated in 
the ADDRESSES section. Comments will be available in the AD docket 
shortly after the Docket Management System receives them.

Discussion

    We proposed to amend 14 CFR part 39 with a notice of proposed 
rulemaking (NPRM) for an AD (the ``original NPRM'') for all Boeing 
Model 757 airplanes. The original NPRM was published in the Federal 
Register on January 3, 2007 (72 FR 50). The original NPRM proposed to 
require revising the Airworthiness Limitations (AWLs) section of the 
Instructions for Continued Airworthiness by incorporating new 
limitations for fuel tank systems to satisfy Special Federal Aviation 
Regulation No. 88 (SFAR 88) requirements. The original NPRM also 
proposed to require the initial inspection of certain repetitive 
inspections specified in the AWLs to phase-in those inspections, and 
repair if necessary.

Explanation of Change in Compliance Time

    In most ADs, we adopt a compliance time allowing a specified amount 
of time after the AD's effective date. In this case, however, we have 
already issued regulations that require operators to revise their 
maintenance/inspection programs to address fuel tank safety issues. The 
compliance date for these regulations is December 16, 2008. To provide 
for efficient and coordinated implementation of these regulations and 
this supplemental NPRM, we are using this same compliance date in this 
supplemental NPRM, instead of the 18-month compliance time recommended 
by Boeing. Therefore, we have revised the compliance time in paragraph 
(g) from ``within 18 months after the effective date of this AD'' to a 
compliance date of ``no later than December 16, 2008.''

Comments

    We have considered the following comments on the original NPRM.

[[Page 41964]]

Request To Revise Note 1

    Boeing requests that the Note 1 of the original NPRM be revised 
from ``* * * the operator must request approval for revision * * *'' to 
``* * * the operator must request approval for deviation from * * * .'' 
Boeing states that, as written, Note 1 would result in modifications, 
alternations, or repairs being incorporated into the Boeing 757 
Maintenance Planning Data (MPD) Document D622N001-9, Revision March 
2006 (referred to in the original NPRM as the appropriate source of 
service information) that are outside of its configuration definition 
data and responsibility. Boeing also states that the MPD document is 
intended to reflect the Boeing 757 type design as defined only by 
Boeing data.
    We partially agree. We do not agree with Boeing's suggested change. 
We find that Boeing is misinterpreting the intent of Note 1, and that 
clarification is necessary. The sentence in question states, ``In this 
situation, * * * the operator must request approval for revision to the 
airworthiness limitations (AWLs) in the Boeing 757 Maintenance Planning 
Data (MPD) Document D622N001-9 * * * .'' The term ``revision'' refers 
to the ``airworthiness limitations,'' not to the MPD document. The 
modification, alteration, or repair would affect only a few airplanes, 
so a revision to the MPD document, which would affect the whole fleet, 
would not be appropriate. However, we do agree with Boeing that a 
revision to the MPD document may not be necessary. We have determined 
that operators also can request approval for revision to the AWLs in 
the MPD document according to paragraph (i) of this supplemental NPRM. 
Therefore, we have revised Note 1 accordingly.

Request To Add Procedures of Boeing 757 MPD Document

    Boeing requests that the original NPRM be revised to contain the 
procedures specified in Section 9 of Boeing 757 MPD Document D622N001-9 
or an approved equivalent AWL/Certification Maintenance Requirement 
(CMR) document, rather than referring to the MPD document as the source 
for the procedures. Boeing states that it may move Section 9 
(airworthiness limitation section) out of the Boeing 757 MPD document, 
and thus the AD may need to be revised.
    We do not agree. We have confirmed with Boeing that it has no 
immediate plans to change the Boeing 757 MPD document. Therefore, until 
the Boeing 757 MPD Document D622N001-9 is revised, we consider it 
appropriate that this supplemental NPRM refer to it as the appropriate 
source of service information for accomplishing the proposed actions. 
We might consider issuing additional rulemaking or approving 
alternative methods of compliance to address that concern in the 
future. We have not changed the supplemental NPRM regarding this issue.

Request To Extend Compliance Time

    United Parcel Service (UPS) requests that, for low cycle operators 
(less than 800 flight cycles per year), the compliance time for the 
initial inspections in paragraph (h) of the original NPRM be extended 
from ``10 years or 36,000 flight cycles'' to ``16 years (8C) or 36,000 
flight cycles, whichever occurs first.'' UPS states that this will not 
penalize low-utilization operators. UPS states that it has tank entries 
approximately every 8 years, and that 16 years lines up better with its 
maintenance program. UPS also states that a compliance time of 10 years 
would significantly increase its financial burden. UPS did not submit 
any data with its comment.
    We do not agree. In developing the compliance time for the original 
NPRM, we considered not only the risk of creating an ignition source in 
the tank, but we also considered the practical aspect of accomplishing 
the proposed inspections within a period of time that corresponds to 
the major structural inspections or fuel tank entries to limit the 
impact on operators. With UPS's tank entries occurring approximately 
every 8 years, the 36,000 total flight cycles or 120-month proposed 
compliance time would allow UPS's entire fleet to be inspected during 
scheduled maintenance with an additional 2 years to allow for some 
scheduling flexibility. However, paragraph (i) of the supplemental NPRM 
provides operators the opportunity to request an extension of the 
compliance time if data are presented to justify such an extension.

Request To Include an Additional Airworthiness Limitation

    Boeing requests that we revise paragraph (h) of the original NPRM 
for completeness to include Airworthiness Limitation 28-AWL-25 
(Lightning and Fault Current Protection--Motor Operated Valve 
Actuator). Boeing notes this AWL was added to Section 9 of the Boeing 
757 MPD Document D622N001-9 in October 2006.
    We agree with Boeing's intent; however, we do not agree with 
including Airworthiness Limitation 28-AWL-25 in this supplemental NPRM. 
We are considering issuing a separate rulemaking action that would 
propose to require installation of a new actuator and inspections in 
accordance with Airworthiness Limitation 28-AWL-25.

Request To Revise Numbering of Notes

    Boeing requests that Notes 2 and 3 of the original NPRM be 
renumbered. Boeing believes that there are only two notes as part of 
Table 1 of the original NPRM, and that the notes were incorrectly 
numbered.
    We understand Boeing's concern; however, we do not agree that the 
notes need to be renumbered. There are total of three notes in the 
supplemental NPRM. All three notes are correctly numbered. In all ADs, 
notes are numbered sequentially in the regulatory text.

Request To Revise Appendix 1

    Boeing requests that Appendix 1 of the original NPRM be revised to 
include missing task titles and numbers. Boeing provided no 
justification.
    We partially agree. Since we issued the original NPRM, the 
modifications of the motor operated valve actuator have been approved, 
and the associated airplane maintenance manual (AMM) changes have been 
released. Therefore, we agree with Boeing to revise columns ``Task 
Title'' and ``Task ,'' as applicable, of Appendix 1 of the 
supplemental NPRM to include the latest information specified in the 
AMM that is associated with design changes of the fuel tank system 
changes. However, we do not agree with Boeing to add task titles for 
the component maintenance manuals (CMM), because the AWLs cover the 
entire CMM, not just specific tasks.

Explanation of Other Changes to Original NPRM

    We have revised paragraph (g) of this supplemental NPRM to clarify 
that the exception refers to the ``initial inspections'' specified in 
Table 1 of this AD rather than the ``inspections.''
    We have revised paragraph (h) of this supplemental NPRM to allow 
the use of later revisions of the MPD.

FAA's Determination and Proposed Requirements of the Supplemental NPRM

    Some of the changes discussed above expand the scope of the 
original NPRM; therefore, we have determined that it is necessary to 
reopen the comment period to provide additional opportunity for public 
comment on this supplemental NPRM.

[[Page 41965]]

Costs of Compliance

    There are about 990 airplanes of the affected design in the 
worldwide fleet. The following table provides the estimated costs for 
U.S. operators to comply with this proposed AD.

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                  Number of U.S.-
             Action                 Work hours     Average labor     Cost per       registered      Fleet cost
                                                   rate per hour     airplane        airplanes
----------------------------------------------------------------------------------------------------------------
Revision of AWLs section of the                8             $80            $640             639        $408,960
 Instructions for Continued
 Airworthiness..................
Detailed and special detailed                  8              80             640             639         408,960
 inspections....................
----------------------------------------------------------------------------------------------------------------

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, Section 106, describes the 
authority of the FAA Administrator. Subtitle VII, Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
Subtitle VII, Part A, Subpart III, Section 44701, ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We have determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would not 
have a substantial direct effect on the States, on the relationship 
between the national Government and the States, or on the distribution 
of power and responsibilities among the various levels of government.
    For the reasons discussed above, I certify that the proposed 
regulation:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979); and
    3. Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this supplemental NPRM and placed it in the AD docket. See 
the ADDRESSES section for a location to examine the regulatory 
evaluation.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

    1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

    2. The Federal Aviation Administration (FAA) amends Sec.  39.13 by 
adding the following new airworthiness directive (AD):

Boeing: Docket No. FAA-2006-26710; Directorate Identifier 2006-NM-
147-AD.

Comments Due Date

    (a) The FAA must receive comments on this AD action by August 
27, 2007.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to all Boeing Model 757-200, -200PF, -200CB, 
and -300 series airplanes, certificated in any category.

    Note 1: This AD requires revisions to certain operator 
maintenance documents to include new inspections and maintenance 
actions. Compliance with these limitations is required by 14 CFR 
43.16 and 91.403(c). For airplanes that have been previously 
modified, altered, or repaired in the areas addressed by these 
limitations, the operator may not be able to accomplish the actions 
described in the revisions. In this situation, to comply with 14 CFR 
43.16 and 91.403(c), the operator must request approval for revision 
to the airworthiness limitations (AWLs) in the Boeing 757 
Maintenance Planning Data (MPD) Document D622N001-9 according to 
paragraph (g) or (i) of this AD.

Unsafe Condition

    (d) This AD results from a design review of the fuel tank 
systems. We are issuing this AD to prevent the potential for 
ignition sources inside fuel tanks caused by latent failures, 
alterations, repairs, or maintenance actions, which, in combination 
with flammable fuel vapors, could result in a fuel tank explosion 
and consequent loss of the airplane.

Compliance

    (e) You are responsible for having the actions required by this 
AD performed within the compliance times specified, unless the 
actions have already been done.

Service Information

    (f) The term ``Revision March 2006 of the MPD'' as used in this 
AD, means Section 9 of Boeing 757 MPD Document D622N001-9, Revision 
March 2006.

Revision of AWLs Section

    (g) No later than December 16, 2008, revise the AWLs section of 
the Instructions for Continued Airworthiness by incorporating the 
information in the sections specified in paragraphs (g)(1) through 
(g)(3) of this AD into the MPD, except that the initial inspections 
specified in Table 1 of this AD must be done at the compliance times 
specified in Table 1. Accomplishing the revision in accordance with 
a later revision of the MPD is an acceptable method of compliance if 
the revision is approved by the Manager, Seattle Aircraft 
Certification Office (ACO), FAA.
    (1) Section E., ``AIRWORTHINESS LIMITATIONS--FUEL SYSTEMS,'' of 
Revision March 2006 of the MPD.
    (2) Section F., ``PAGE FORMAT: SYSTEMS AIRWORTHINESS 
LIMITATIONS,'' of Revision March 2006 of the MPD.
    (3) Section G., ``AIRWORTHINESS LIMITATIONS--FUEL SYSTEM AWLs'' 
of Revision March 2006 of the MPD.

Initial Inspections and Repair

    (h) Do the inspections specified in Table 1 of this AD and 
repair any discrepancy, in accordance with Section G., 
``AIRWORTHINESS LIMITATIONS--FUEL SYSTEM AWLs,'' of Revision March 
2006 of the MPD. The repair must be done before further flight. 
Accomplishing the actions in accordance with a later revision of the 
MPD is an acceptable method of compliance if the revision is 
approved by the Manager, Seattle ACO, FAA.

[[Page 41966]]



                                          Table 1.--Initial Inspections
----------------------------------------------------------------------------------------------------------------
                                                                    Compliance time (whichever occurs later)
      Airworthiness  limitations             Description       -------------------------------------------------
                                                                       Threshold               Grace period
----------------------------------------------------------------------------------------------------------------
(1) 28-AWL-01........................  A detailed inspection    Before the accumulation  Within 72 months after
                                        of external wires over   of 36,000 total flight   the effective date of
                                        the center fuel tank     cycles, or within 120    this AD.
                                        for damaged clamps,      months since the date
                                        wire chafing, and wire   of issuance of the
                                        bundles in contact       original standard
                                        with the surface of      airworthiness
                                        the center fuel tank.    certificate or the
                                                                 date of issuance of
                                                                 the original export
                                                                 certificate of
                                                                 airworthiness,
                                                                 whichever occurs first.
(2) 28-AWL-03........................  A special detailed       Before the accumulation  Within 24 months after
                                        inspection of the        of 36,000 total flight   the effective date of
                                        lightning shield to      cycles, or within 120    this AD.
                                        ground termination on    months since the date
                                        the out-of-tank fuel     of issuance of the
                                        quantity indicating      original standard
                                        system to verify         airworthiness
                                        functional integrity.    certificate or the
                                                                 date of issuance of
                                                                 the original export
                                                                 certificate of
                                                                 airworthiness,
                                                                 whichever occurs first.
(3) 28-AWL-14........................  A special detailed       Before the accumulation  Within 60 months after
                                        inspection of the        of 36,000 total flight   the effective date of
                                        fault current bond of    cycles, or within 120    this AD.
                                        the fueling shutoff      months since the date
                                        valve actuator of the    of issuance of the
                                        center wing tank to      original standard
                                        verify electrical bond.  airworthiness
                                                                 certificate or the
                                                                 date of issuance of
                                                                 the original export
                                                                 certificate of
                                                                 airworthiness,
                                                                 whichever occurs first.
----------------------------------------------------------------------------------------------------------------


    Note 2: For the purposes of this AD, a detailed inspection is: 
``An intensive examination of a specific item, installation, or 
assembly to detect damage, failure, or irregularity. Available 
lighting is normally supplemented with a direct source of good 
lighting at an intensity deemed appropriate. Inspection aids such as 
mirror, magnifying lenses, etc., may be necessary. Surface cleaning 
and elaborate procedures may be required.''


    Note 3: For the purposes of this AD, a special detailed 
inspection is: ``An intensive examination of a specific item, 
installation, or assembly to detect damage, failure, or 
irregularity. The examination is likely to make extensive use of 
specialized inspection techniques and/or equipment. Intricate 
cleaning and substantial access or disassembly procedure may be 
required.''

Alternative Methods of Compliance (AMOCs)

    (i)(1) The Manager, Seattle ACO has the authority to approve 
AMOCs for this AD, if requested in accordance with the procedures 
found in 14 CFR 39.19.
    (2) To request a different method of compliance or a different 
compliance time for this AD, follow the procedures in 14 CFR 39.19. 
Before using any approved AMOC on any airplane to which the AMOC 
applies, notify your appropriate principal inspector (PI) in the FAA 
Flight Standards District Office (FSDO), or lacking a PI, your local 
FSDO.

             Appendix 1. Fuel Tank System Airworthiness Limitations--Applicable Maintenance Manuals
----------------------------------------------------------------------------------------------------------------
                                     Airworthiness
                                      limitation
                                  instruction (ALI)/    ATA section or
 Airworthiness limitation (AWL)     critical design        component          Task title        Task 
                                     configuration    maintenance manual
                                  control limitation    (CMM) document
                                        (CDCCL)
----------------------------------------------------------------------------------------------------------------
28-AWL-01.......................  ALI...............  Airplane            External Wires      28-11-00-206-221
                                                       Maintenance         Over the Center
                                                       Manual (AMM) 28-    Tank Inspection.
                                                       11-00/601.
28-AWL-02.......................  CDCCL.............  Standard Wiring     Wiring Assembly     ..................
                                                       Practices Manual    and Installation
                                                       (SWPM) 20-10-11.    Configuration.
28-AWL-03.......................  ALI...............  AMM 20-55-54/601..  Fuel Quantity       20-55-54-286-001
                                                                           Indicating System
                                                                           (FQIS)
                                                                           Connectors--Inspe
                                                                           ction/ Check.
28-AWL-04.......................  CDCCL.............  SWPM 20-10-15.....  Assembly of Shield  ..................
                                                                           Ground Wires.
28-AWL-05.......................  CDCCL.............  SWPM 20-10-11.....  Wiring Assembly     ..................
                                                                           and Installation
                                                                           Configuration.
28-AWL-06.......................  CDCCL.............  CMM 28-41-68        ..................  ..................
                                                       Revision 4 or
                                                       subsequent
                                                       revisions.
28-AWL-07.......................  CDCCL.............  CMM 28-40-56,       ..................  ..................
                                                       Revision 4; CMM
                                                       28-40-62,
                                                       revision 3; CMM
                                                       28-40-59,
                                                       revision 5; or
                                                       subsequent
                                                       revisions.
28-AWL-08.......................  CDCCL.............  SWPM 20-14-12.....  Repair of FQIS      ..................
                                                                           Wire Harness.
                                  ..................  AMM 28-41-09/401..  Install the Tank    Varies with
                                                                           Wiring Harness.     configuration
28-AWL-09.......................  CDCCL.............  AMM 29-11-26/401..  Install the Heat    29-11-26-404-012
                                                                           Exchanger.
28-AWL-10.......................  CDCCL.............  AMM 28-22-07/401..  Install the Fuel    28-22-07-404-005
                                                                           Line and Fittings.
28-AWL-11.......................  CDCCL.............  ..................  ..................  ..................

[[Page 41967]]

 
28-AWL-12.......................  CDCCL.............  CMM 28-22-08,       ..................  ..................
                                                       revision 3; CMM
                                                       28-20-02,
                                                       revision 9; or
                                                       subsequent
                                                       revisions.
28-AWL-13.......................  CDCCL.............  AMM 28-22-03/401..  Install the Fuel    28-22-03-404-007
                                                                           Boost Pump
                                                                           Assembly or the
                                                                           Fuel Override
                                                                           Pump Assembly.
28-AWL-14.......................  ALI...............  AMM 28-21-02/401..  Fueling Shutoff     28-21-02-764-047
                                                                           Valve Resistance
                                                                           Check.
28-AWL-15.......................  CDCCL.............  AMM 28-21-02/401..  Install the         28-21-02-404-019
                                                                           Fueling Shutoff
                                                                           Valve.
                                  ..................  AMM 28-21-12/401..  Install the         28-21-12-404-015
                                                                           Actuator of the
                                                                           Fueling Shutoff
                                                                           Valve.
28-AWL-16.......................  CDCCL.............  AMM 28-11-01/401..  Install the Main    28-11-01-404-014
                                                                           Tank Access Door.
                                  ..................  AMM 28-11-02/401..  Install the Center  28-11-02-404-019
                                                                           Tank Access Door.
                                  ..................  AMM 28-11-03/401..  Install the Surge   28-11-03-404-008
                                                                           Tank Access Door.
28-AWL-17.......................  CDCCL.............  AMM 28-11-03/401..  Install the Surge   28-11-03-404-008
                                                                           Tank Access Door.
                                  ..................  AMM 28-13-04/201..  Install the         28-13-04-402-014
                                                                           Pressure Relief
                                                                           Valve.
28-AWL-18.......................  CDCCL.............  AMM 28-11-03/401..  Install the Surge   28-11-03-404-008
                                                                           Tank Access Door.
                                  ..................  AMM 28-13-05/401..  Install the         28-13-05-404-004
                                                                           Housing of the
                                                                           Vent Flame
                                                                           Arrestor.
28-AWL-19.......................  CDCCL.............  Fault Isolation     Engine Fuel Feed    ..................
                                                       Manual (FIM) 28-    System--Fault
                                                       22-00/101.          Isolation.
28-AWL-20.......................  ALI...............  AMM 28-22-00/501..  Center Tank Fuel    28-22-00-725-507
                                                                           Override Pump
                                                                           Auto Shutoff
                                                                           Functional Test.
                                  ..................  ..................  System Test--       Varies with
                                                                           Engine Fuel Feed    Configuration
                                                                           System.
28-AWL-21.......................  ALI...............  AMM 28-22-00/501..  System Test--       Varies with
                                                                           Engine Fuel Feed    Configuration
                                                                           System.
28-AWL-22.......................  CDCCL.............  AMM 28-41-24/401..  Densitometer Hot    28-41-24-404-006
                                                                           Short Protector
                                                                           Installation.
28-AWL-23.......................  CDCCL.............  AMM 28-22-01/401..  Install the         28-22-01-404-19
                                                                           Adapter Shaft of
                                                                           the Engine Fuel
                                                                           Shutoff Valve
                                                                           (Spar Valve).
                                  ..................  AMM 28-22-02/401..  Install the Engine  28-22-02-404-041
                                                                           Fuel Crossfeed
                                                                           Adapter Shaft.
                                  ..................  AMM 28-22-11/401..  Install the         28-22-11-404-007
                                                                           Actuator of the
                                                                           Engine Fuel
                                                                           Shutoff Valve
                                                                           (Spar Valve).
                                  ..................  AMM 28-22-12/401..  Install the         28-22-12-404-024
                                                                           Actuator of the
                                                                           Engine Fuel
                                                                           Crossfeed Valve.
                                  ..................  AMM 28-26-01/401..  Install the         28-26-01-404-035
                                                                           Adapter Shaft for
                                                                           the Defuel Valve.
                                  ..................  AMM 28-26-02/401..  Install the         28-26-02-404-015
                                                                           Defueling Valve
                                                                           Actuator.
28-AWL-24.......................  CDCCL.............  CMM 28-20-21......  ..................  ..................
28-AWL-25.......................  ALI...............  AMM 28-22-01/401..  Install the         28-22-01-404-19
                                                                           Adapter Shaft of
                                                                           the Engine Fuel
                                                                           Shutoff Valve
                                                                           (Spar Valve).
                                  ..................  AMM 28-022-02/401.  Install the Engine  28-22-02-404-041
                                                                           Fuel Crossfeed
                                                                           Adapter Shaft.
                                  ..................  AMM 28-22-11/401..  Install the         28-22-11-404-007
                                                                           Actuator of the
                                                                           Engine Fuel
                                                                           Shutoff Valve
                                                                           (Spar Valve).
                                  ..................  AMM 28-22-12/401..  Install the         28-22-12-404-024
                                                                           Actuator of the
                                                                           Engine Fuel
                                                                           Crossfeed Valve.
                                  ..................  AMM 28-26-01/401..  Install the         28-26-01-404-035
                                                                           Adapter Shaft for
                                                                           the Defuel Valve.
                                  ..................  AMM 28-26-02/401..  Install the         28-26-02-404-015
                                                                           Defueling Valve
                                                                           Actuator.
                                  ..................  AMM 28-25-11/401..  Install the         28-25-11-404-010
                                                                           Actuator of the
                                                                           APU Fuel Shutoff
                                                                           Valve.
28-AWL-26.......................  ALI...............  AMM 28-22-00/501..  System Test--       Varies with
                                                                           Engine Fuel Feed    Configuration
                                                                           System.
----------------------------------------------------------------------------------------------------------------



[[Page 41968]]

    Issued in Renton, Washington, on July 25, 2007.
Stephen P. Boyd,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
 [FR Doc. E7-14867 Filed 7-31-07; 8:45 am]
BILLING CODE 4910-13-P