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

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