Airworthiness Directives; Boeing Model 747-400, -400D, and -400F Series Airplanes, 36385-36391 [E7-12816]

Download as PDF Federal Register / Vol. 72, No. 127 / Tuesday, July 3, 2007 / Proposed Rules 36385 APPENDIX 1.—IMPLEMENTING FUEL TANK SYSTEM AIRWORTHINESS LIMITATIONS ON MODEL 747–100, 747–100B, 747– 100B SUD, 747–200B, 747–200C, 747–200F, 747–300, 747SR, AND 747SP SERIES AIRPLANES—Continued AWL No. ALI/CDCCL ATA section or CMM document 28–AWL–15 ...... CDCCL ............. 28–AWL–16 ...... CDCCL ............. CMM 28–40–10, Revision 13; CMM 28–40–12, Revision 9; CMM 28–40–16, Revision 1; CMM 28– 40–14, Revision 8; CMM 28–40–15, Revision 0; or subsequent revisions. SWPM 20–14–12 ...................................................... 28–AWL–17 ...... CDCCL ............. 28–AWL–18 ...... 28–AWL–19 ...... CDCCL ............. CDCCL. AMM 28–41–09/401 .................................................. CMM 28–31–22, Revision 4; or subsequent revisions. AMM 28–22–00/101 .................................................. Issued in Renton, Washington, on June 22, 2007. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E7–12815 Filed 7–2–07; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2007–28386; Directorate Identifier 2006–NM–162–AD] RIN 2120–AA64 Airworthiness Directives; Boeing Model 747–400, –400D, and –400F Series Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). jlentini on PROD1PC65 with PROPOSALS AGENCY: SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) for certain Boeing Model 747–400, –400D, and –400F series airplanes. This proposed AD would require revising the FAA-approved maintenance program by incorporating new airworthiness limitations (AWLs) for fuel tank systems to satisfy Special Federal Aviation Regulation No. 88 requirements. This proposed AD would also require the initial inspection of certain repetitive AWL inspections to phase in those inspections, and repair if necessary. This proposed AD results from a design review of the fuel tank systems. We are proposing 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 VerDate Aug<31>2005 16:13 Jul 02, 2007 Task title Jkt 211001 Repair of Fuel Quantity Indicator System (FQIS) Wire Harness. Replace the Fuel Tank Wire Bundle. Engine Fuel Feed System—Trouble Shooting. fuel tank explosion and consequent loss of the airplane. DATES: We must receive comments on this proposed AD by August 17, 2007. ADDRESSES: Use one of the following addresses to submit comments on this proposed AD. • 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 the 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 Ave, 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 proposed AD. Send your comments to an address listed in the ADDRESSES section. Include the docket number ‘‘FAA–2007–28386; Directorate Identifier 2006–NM–162–AD’’ at the beginning of your comments. We specifically invite comments on the PO 00000 Frm 00016 Fmt 4702 Sfmt 4702 overall regulatory, economic, environmental, and energy aspects of the proposed AD. We will consider all comments received by the closing date and may amend the proposed AD in light 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 with FAA personnel concerning this proposed AD. 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 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 floor 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 The FAA has examined the underlying safety issues involved in fuel tank explosions on several large transport airplanes, including the adequacy of existing regulations, the service history of airplanes subject to those regulations, and existing maintenance practices for fuel tank systems. As a result of those findings, we issued a regulation titled ‘‘Transport E:\FR\FM\03JYP1.SGM 03JYP1 36386 Federal Register / Vol. 72, No. 127 / Tuesday, July 3, 2007 / Proposed Rules jlentini on PROD1PC65 with PROPOSALS Airplane Fuel Tank System Design Review, Flammability Reduction and Maintenance and Inspection Requirements’’ (67 FR 23086, May 7, 2001). In addition to new airworthiness standards for transport airplanes and new maintenance requirements, this rule included Special Federal Aviation Regulation No. 88 (‘‘SFAR 88,’’ Amendment 21–78, and subsequent Amendments 21–82 and 21–83). Among other actions, SFAR 88 requires certain type design (i.e., type certificate (TC) and supplemental type certificate (STC)) holders to substantiate that their fuel tank systems can prevent ignition sources in the fuel tanks. This requirement applies to type design holders for large turbine-powered transport airplanes and for subsequent modifications to those airplanes. It requires them to perform design reviews and to develop design changes and maintenance procedures if their designs do not meet the new fuel tank safety standards. As explained in the preamble to the rule, we intended to adopt airworthiness directives to mandate any changes found necessary to address unsafe conditions identified as a result of these reviews. In evaluating these design reviews, we have established four criteria intended to define the unsafe conditions associated with fuel tank systems that require corrective actions. The percentage of operating time during which fuel tanks are exposed to flammable conditions is one of these criteria. The other three criteria address the failure types under evaluation: single failures, single failures in combination with another latent condition(s), and in-service failure experience. For all four criteria, the evaluations included consideration of previous actions taken that may mitigate the need for further action. We have determined that the actions identified in this proposed AD are necessary to reduce the potential of ignition sources inside fuel tanks, which, in combination with flammable fuel vapors, could result in a fuel tank explosion and consequent loss of the airplane. Relevant Service Information We have reviewed the following subsections of Boeing 747–400 Maintenance Planning Data (MPD) Document, D621U400–9, Section 9, Revision 23, dated March 2006 (hereafter referred to as ‘‘Revision March 2006 of the MPD’’): • Subsection B, ‘‘AIRWORTHINESS LIMITATIONS (AWLs)—SYSTEMS’’ • Subsection C, ‘‘PAGE FORMAT: AIRWORTHINESS LIMITATIONS’’ VerDate Aug<31>2005 16:13 Jul 02, 2007 Jkt 211001 • Subsection D, ‘‘AIRWORTHINESS LIMITATIONS—FUEL SYSTEMS’’ Those subsections of Revision March 2006 of the MPD describe new AWLs for fuel tank systems. The new AWLs include: • AWL inspections, which are periodic inspections of certain features for latent failures that could contribute to an ignition source; and • Critical design configuration control limitations (CDCCLs), which are limitation requirements to preserve a critical ignition source prevention feature of the fuel tank system design that is necessary to prevent the occurrence of an unsafe condition. The purpose of a CDCCL is to provide instruction to retain the critical ignition source prevention feature during configuration change that may be caused by alterations, repairs, or maintenance actions. A CDCCL is not a periodic inspection. Accomplishing the actions specified in the service information is intended to adequately address the unsafe condition. FAA’s Determination and Requirements of the Proposed AD We have evaluated all pertinent information and identified an unsafe condition that is likely to exist or develop on other airplanes of this same type design. For this reason, we are proposing this AD, which would require revising the FAA-approved maintenance program by incorporating the information in Subsections B, C, and D of Revision March 2006 of the MPD. This proposed AD would also require the initial inspection of certain repetitive AWL inspections to phase in those inspections, and repair if necessary. Explanation of 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, the FAA has 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 proposed AD, we are using this same compliance date in this proposed AD, instead of the 18-month compliance time recommended by Boeing. Rework Required When Implementing AWLs Into an Existing Fleet The maintenance program revision for the fuel tank systems specified in paragraph (g) of this proposed AD, PO 00000 Frm 00017 Fmt 4702 Sfmt 4702 which involves incorporating the information specified in Revision March 2006 of the MPD, would affect how operators maintain their airplanes. After doing that maintenance program revision, operators would need to do any maintenance on the fuel tank system as specified in the CDCCLs. Maintenance done before the maintenance program revision specified in paragraph (g) would not need to be redone in order to comply with paragraph (g). For example, the AWL that requires fuel pumps to be repaired and overhauled per an FAA-approved component maintenance manual (CMM) applies to fuel pumps repaired after the maintenance programs are revised; spare or on-wing fuel pumps do not need to be reworked. For AWLs that require repetitive inspections, the initial inspection interval (threshold) starts from the date the maintenance program revision specified in paragraph (g) is done, except as provided by paragraph (h) of this proposed AD. This proposed AD would require only the maintenance program revision specified in paragraph (g), and initial inspections specified in paragraph (h). No other fleet-wide inspections need to be done. Changes to Fuel Tank System AWLs Paragraph (g) of this proposed AD would require revising the FAAapproved maintenance program by incorporating certain information specified in Revision March 2006 of the MPD. Paragraph (g) allows accomplishing the maintenance program revision in accordance with later revisions of the MPD as an acceptable method of compliance if they are approved by the Manager, Seattle Aircraft Certification Office (ACO), FAA. Paragraph (h) allows accomplishing the initial inspections and repair in accordance with later revisions of the MPD as an acceptable method of compliance if they are approved by the Manager, Seattle ACO. In addition, Subsection B of Revision March 2006 of the MPD specifies that any deviations from the published AWL instructions, including AWL intervals, in that MPD must be approved by the Manager, Seattle ACO. Therefore, after the maintenance program revision, any further revision to an AWL or AWL interval should be done as an AWL change, not as an alternative method of compliance (AMOC). For U.S.-registered airplanes, operators must make requests through an appropriate FAA Principal Maintenance Inspector (PMI) or Principal Avionics Inspector (PAI) for approval by the Manager, Seattle ACO. A non-U.S. operator should coordinate E:\FR\FM\03JYP1.SGM 03JYP1 36387 Federal Register / Vol. 72, No. 127 / Tuesday, July 3, 2007 / Proposed Rules changes with its governing regulatory agency. Exceptional Short-Term Extensions Subsection B of Revision March 2006 of the MPD has provisions for an exceptional short-term extension of 30 days. An exceptional short-term extension is an increase in an AWL interval that may be needed to cover an uncontrollable or unexpected situation. For U.S.-registered airplanes, the FAA PMI or PAI must concur with any exceptional short-term extension before it is used, unless the operator has identified another appropriate procedure with the local regulatory authority. The FAA PMI or PAI may grant the exceptional short-term extensions described in Subsection B without consultation with the Manager, Seattle ACO. A non-U.S. operator should coordinate changes with its governing regulatory agency. As explained in Revision March 2006 of the MPD, exceptional short-term extensions must not be used for fleet AWL extensions. An exceptional short-term extension should not be confused with an operator’s short-term escalation authorization approved in accordance with the Operations Specifications or the operator’s reliability program. Ensuring Compliance With Fuel Tank System AWLs Boeing has revised applicable maintenance manuals and task cards to address AWLs and to include notes about CDCCLs. Operators that do not use Boeing’s revision service should revise their maintenance manuals and task cards to highlight actions tied to CDCCLs to ensure that maintenance personnel are complying with the CDCCLs. Appendix 1 of this proposed AD contains a list of Air Transport Association (ATA) sections for the revised maintenance manuals. Operators might wish to use the appendix as an aid to implement the AWLs. Recording Compliance With Fuel Tank System AWLs The applicable operating rules of the Federal Aviation Regulations (14 CFR parts 91, 121, 125, and 129) require operators to maintain records with the identification of the current inspection status of an airplane. Some of the AWLs contained in Subsection D of Revision March 2006 of the MPD are inspections for which the applicable sections of the operating rules apply. Other AWLs are CDCCLs, which are tied to conditional maintenance actions. An entry into an operator’s existing maintenance record system for corrective action is sufficient for recording compliance with CDCCLs, as long as the applicable maintenance manual and task cards identify actions that are CDCCLs. Changes to CMMs Cited in Fuel Tank System AWLs Some of the AWLs in Subsection D of Revision March 2006 of the MPD refer to specific revision levels of the CMMs as additional sources of service information for doing the AWLs. Boeing is referring to the CMMs by revision level in the applicable AWL for certain components rather than including information directly in the MPD because of the volume of that information. As a result, the Manager, Seattle ACO, must approve the CMMs. Any later revision of those CMMs will be handled like a change to the AWL itself. Any use of parts (including the use of parts manufacturer approval (PMA) approved parts), methods, techniques, and practices not contained in the CMMs need to be approved by the Manager, Seattle ACO, or governing regulatory authority. For example, certain pump repair/overhaul manuals must be approved by the Manager, Seattle ACO. Changes to AMMs Referenced in Fuel Tank System AWLs In other AWLs in Subsection D of Revision March 2006 of the MPD, the AWLs contain all the necessary data. The applicable section of the maintenance manual is usually included in the AWLs. Boeing intended this information to assist operators in maintaining the maintenance manuals. A maintenance manual change to these tasks may be made without approval by the Manager, Seattle ACO, through an appropriate FAA PMI or PAI, by the governing regulatory authority, or by using the operator’s standard process for revising maintenance manuals. An acceptable change would have to maintain the information specified in the AWL such as the pass/fail criteria or special test equipment. Costs of Compliance There are about 596 airplanes of the affected design in the worldwide fleet. The following table provides the estimated costs, at an average labor rate of $80 per hour, for U.S. operators to comply with this proposed AD. ESTIMATED COSTS Work hours Action Maintenance program revision ..................................................................................... Inspections .................................................................................................................... jlentini on PROD1PC65 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 VerDate Aug<31>2005 16:13 Jul 02, 2007 Jkt 211001 8 8 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 PO 00000 Frm 00018 Fmt 4702 Sfmt 4702 Parts Cost per airplane None None $640 640 Number of U.S.registered airplanes 57 57 Fleet cost $36,480 36,480 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; E:\FR\FM\03JYP1.SGM 03JYP1 36388 Federal Register / Vol. 72, No. 127 / Tuesday, July 3, 2007 / Proposed Rules 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 proposed AD 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. § 39.13 [Amended] 2. The Federal Aviation Administration (FAA) amends § 39.13 by adding the following new airworthiness directive (AD): Boeing: Docket No. FAA–2007–28386; Directorate Identifier 2006–NM–162–AD. Comments Due Date (a) The FAA must receive comments on this AD action by August 17, 2007. Affected ADs (b) None. Applicability (c) This AD applies to Boeing Model 747– 400, –400D, and –400F series airplanes, certificated in any category; with an original standard airworthiness certificate or original export certificate of airworthiness issued before April 12, 2006. Note 1: Airplanes with an original standard airworthiness certificate or original export certificate of airworthiness issued on or after April 12, 2006, must be already in compliance with the airworthiness limitations specified in this AD because those limitations were applicable as part of the airworthiness certification of those airplanes. Note 2: 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 747–400 Maintenance Planning Data (MPD) Document, D621U400– 9, according to paragraph (g) or (i) of this AD, as applicable. 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 Reference (f) The term ‘‘Revision March 2006 of the MPD’’ as used in this AD, means Boeing 747– 400 Maintenance Planning Data (MPD) Document, D621U400–9, Section 9, Revision 23, dated March 2006. Maintenance Program Revision (g) Before December 16, 2008, revise the FAA-approved maintenance program by incorporating the information in the subsections specified in paragraphs (g)(1), (g)(2), and (g)(3) of this AD; 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) Subsection B, ‘‘AIRWORTHINESS LIMITATIONS (AWLs)—SYSTEMS,’’ of Revision March 2006 of the MPD. (2) Subsection C, ‘‘PAGE FORMAT: AIRWORTHINESS LIMITATIONS,’’ of Revision March 2006 of the MPD. (3) Subsection D, ‘‘AIRWORTHINESS LIMITATIONS—FUEL SYSTEMS,’’ of Revision March 2006 of the MPD. Initial Inspections and Repair if Necessary (h) Do the inspections specified in Table 1 of this AD and repair any discrepancy, in accordance with Subsection D, ‘‘AIRWORTHINESS LIMITATIONS—FUEL SYSTEMS,’’ of Revision March 2006 of the MPD. The repair must be done before further flight. Accomplishing the actions required by this paragraph 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. Note 3: 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 4: 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.’’ TABLE 1.—INITIAL INSPECTIONS AWL No. Compliance time (whichever occurs later) Description Threshold jlentini on PROD1PC65 with PROPOSALS 28–AWL–01 ............ 28–AWL–03 ............ VerDate Aug<31>2005 A detailed inspection of external wires over the center fuel tank for damaged or loose clamps, wire chafing, and wire bundles in contact with the surface of the center fuel tank. A special detailed inspection of the lightning shield to ground termination on the out-of-tank fuel quantity indicating system to verify functional integrity. 16:13 Jul 02, 2007 Jkt 211001 PO 00000 Frm 00019 Grace period Before the accumulation of 36,000 total flight cycles, or within 144 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 144 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. Fmt 4702 Sfmt 4702 E:\FR\FM\03JYP1.SGM 03JYP1 Within 24 months after the effective date of this AD. 36389 Federal Register / Vol. 72, No. 127 / Tuesday, July 3, 2007 / Proposed Rules TABLE 1.—INITIAL INSPECTIONS—Continued AWL No. Compliance time (whichever occurs later) Description Threshold 28–AWL–10 ............ A special detailed inspection of the fault current bond of the fueling shutoff valve actuator of the center wing tank to verify electrical bond. Alternative Methods of Compliance (AMOCs) (i)(1) The Manager, Seattle ACO, has the authority to approve AMOCs for this AD, if Grace period Before the accumulation of 36,000 total flight cycles, or within 144 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 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.—IMPLEMENTING FUEL TANK SYSTEM AIRWORTHINESS LIMITATIONS ON MODEL 747–400, –400D, AND –400F SERIES AIRPLANES AWL No. ALI/CDCCL ATA section or CMM document Task title 28–AWL–01 ............................. ALI ............... AMM 28–11–00/601 ............... 28–AWL–02 ............................. CDCCL ........ SWPM 20–10–11 ................... 28–AWL–03 ............................. ALI ............... AMM 05–55–54/601 ............... 28–AWL–04 ............................. CDCCL ........ SWPM 20–10–15 ................... 28–AWL–05 ............................. 28–AWL–06 ............................. CDCCL ........ CDCCL ........ AMM 29–11–22/401 ............... CMM 28–22–07, Revision 1; CMM 28–31–03, Revision 3; CMM 28–26–12, Revision 0; CMM 28–26–14, Revision 0; CMM 28–20– 02, Revision 9; or subsequent revisions. External Wires Over the Center Fuel Tank—Inspection. Wiring Assembly and Installation Configuration. FQIS Wiring and Bonding—Inspection. Assembly of Shield Ground Wires. Heat Exchanger Installation ... 28–AWL–07 ............................. 28–AWL–08 ............................. CDCCL. CDCCL ........ SWPM 20–10–11 ................... 28–AWL–09 ............................. CDCCL ........ AMM 28–21–02/401 ............... AMM 28–21–13/401 ............... 28–AWL–10 ............................. ALI ............... AMM 28–21–13/601 ............... 28–AWL–11 ............................. CDCCL ........ 28–AWL–12 ............................. CDCCL ........ 28–AWL–13 ............................. CDCCL ........ 28–AWL–14 ............................. CDCCL ........ 28–AWL–15 ............................. CDCCL ........ CMM 28–41–62, Revision 4 or subsequent revisions. CMM 28–21–02, Revision 2 or subsequent revisions. CMM 28–41–63, Revision 4 or subsequent revisions. CMM 28–40–55, Revision 6; CMM 28–40–56, Revision 4; CMM 28–40–59, Revision 5; or subsequent revisions. SWPM 20–14–12 ................... jlentini on PROD1PC65 with PROPOSALS AMM 28–41–09/401 ............... VerDate Aug<31>2005 16:13 Jul 02, 2007 Jkt 211001 PO 00000 Frm 00020 Fmt 4702 Sfmt 4702 Task No. Wiring Assembly and Installation Configuration.. Refuel Valve Control Unit—Installation. Refuel Valve Control Unit—Installation. Center Wing Tank Refuel Valve—Fault Current Bond Inspection. Repair of Fuel Quantity Indicator System (FQIS) Wire Harness. FQIS Wire Bundle in the Main or Reserve Tank—Installation. FQIS Wire Bundle in the Center Wing Tank Installation. FQIS Wire Bundle in the Horizontal Stabilizer Tank Installation. E:\FR\FM\03JYP1.SGM 03JYP1 28–11–00–210–801. 05–55–54–200–801. 29–11–22–404–014. 28–21–02–401–011. 28–21–13–404–087. 28–21–13–765–801. 28–41–09–404–019. 28–41–09–404–157. 28–41–09–404–176. 36390 Federal Register / Vol. 72, No. 127 / Tuesday, July 3, 2007 / Proposed Rules APPENDIX 1.—IMPLEMENTING FUEL TANK SYSTEM AIRWORTHINESS LIMITATIONS ON MODEL 747–400, –400D, AND –400F SERIES AIRPLANES—Continued AWL No. ALI/CDCCL ATA section or CMM document Task title 28–AWL–16 ............................. CDCCL ........ AMM 28–11–02/401 ............... Reserve and Main Tank Access Door Installation. Access Door for the Wing Surge Tank Installation. Fault Current Detector Operational Test. Fault Current Detector—Operational Test. AMM 28–11–03/401 ............... 28–AWL–17 ............................. ALI ............... AMM 28–31–14/501 ............... AMM 28–17–14/501 ............... CDCCL ........ 28–AWL–19 ............................. jlentini on PROD1PC65 with PROPOSALS 28–AWL–18 ............................. CDCCL ........ VerDate Aug<31>2005 16:13 Jul 02, 2007 Jkt 211001 CMM 28–31–22, Revision 4 or subsequent revisions. FIM 28–22–00/201 ................. PO 00000 Frm 00021 Fmt 4702 Sfmt 4702 Task No. CMCS Message LEFT HORIZONTAL STABILIZER PUMP SYSTEM FAIL— Fault Isolation. CMCS Message RIGHT HORIZONTAL STABILIZER PUMP SYSTEM FAIL— Fault Isolation. CMCS Message MAIN TANK 1 FWD BOOST PUMP SYSTEM FAIL—Fault Isolation. CMCS Message MAIN TANK 1 AFT BOOST PUMP SYSTEM FAIL—Fault Isolation. CMCS Message MAIN TANK 2 FWD BOOST PUMP SYSTEM FAIL—Fault Isolation. CMCS Message MAIN TANK 2 AFT BOOST PUMP SYSTEM FAIL—Fault Isolation. CMCS Message MAIN TANK 3 FWD BOOST PUMP SYSTEM FAIL—Fault Isolation. CMCS Message MAIN TANK 3 AFT BOOST PUMP SYSTEM FAIL—Fault Isolation. CMCS Message MAIN TANK 4 FWD BOOST PUMP SYSTEM FAIL—Fault Isolation. CMCS Message MAIN TANK 4 AFT BOOST PUMP SYSTEM FAIL—Fault Isolation. CMCS Message LEFT CENTER TANK OVERRIDE/ JETTISON PUMP SYSTEM FAIL—Fault Isolation. CMCS Message RIGHT CENTER TANK OVERRIDE/ JETTISON PUMP SYSTEM FAIL—Fault Isolation. CMCS Message MAIN TK 2 AFT OVERRIDE/JETTISON PUMP SYSTEM FAIL— Fault Isolation. CMCS Message MAIN TK 2 FWD OVERRIDE/JETTISON PUMP SYSTEM FAIL—Fault Isolation. CMCS Message MAIN TK 3 AFT OVERRIDE/JETTISON PUMP SYSTEM FAIL— Fault Isolation. E:\FR\FM\03JYP1.SGM 03JYP1 28–11–02–404–011. 28–11–03–404–007. 28–31–14–715–001. 28–17–14–715–001. 28–21 Task 806. 28–21 Task 807. 28–22 Task 860. 28–22 Task 861. 28–22 Task 862. 28–22 Task 863. 28–22 Task 864. 28–22 Task 865. 28–22 Task 866. 28–22 Task 867. 28–31 Task 826. 28–31 Task 827. 28–31 Task 828. 28–31 Task 829. 28–31 Task 830. 36391 Federal Register / Vol. 72, No. 127 / Tuesday, July 3, 2007 / Proposed Rules APPENDIX 1.—IMPLEMENTING FUEL TANK SYSTEM AIRWORTHINESS LIMITATIONS ON MODEL 747–400, –400D, AND –400F SERIES AIRPLANES—Continued AWL No. 28–AWL–20 ............................. ALI/CDCCL CDCCL ........ ATA section or CMM document AMM 28–22–07/401 ............... Task title Task No. CMCS Message MAIN TK 3 FWD OVERRIDE/JETTISON PUMP SYSTEM FAIL—Fault Isolation. Front Spar Bulkhead Fitting— Installation. 28–31 Task 831. 28–22–07–400–805–001. 28–22–07–400–806–002. 28–22–07–400–807–003. 28–22–07–400–808–004. 28–AWL–21 ............................. ALI ............... AMM 28–22–00/501. AMM 28–17–00/501. AMM 28–22–03/401 ............... 28–AWL–22 ............................. CDCCL ........ 28–AWL–23 47–AWL–01 47–AWL–02 47–AWL–03 ............................. ............................. ............................. ............................. CDCCL ........ CDCCL ........ CDCCL. ALI ............... AMM 47–00–01/501 ............... 47–AWL–04 ............................. ALI ............... AMM 47–43–02/501 ............... Main Tank Boost Pump Motor/Impeller Unit Installation. 28–22–03–404–019–001. 28–22–03–404–026–002. 47–AWL–05 ............................. 47–AWL–06 ............................. ALI ............... ALI ............... Issued in Renton, Washington, on June 22, 2007. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E7–12816 Filed 7–2–07; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2007–28388; Directorate Identifier 2006–NM–163–AD] RIN 2120–AA64 Airworthiness Directives; Boeing Model 767–200, –300, –300F, and –400ER Series Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). jlentini on PROD1PC65 with PROPOSALS AGENCY: SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) for certain Boeing Model 767–200, –300, –300F, and –400ER series airplanes. This proposed AD would require revising the FAA-approved maintenance program to incorporate new airworthiness limitations (AWLs) for fuel tank systems to satisfy Special VerDate Aug<31>2005 16:13 Jul 02, 2007 Jkt 211001 AMM 28–41–24/401. AMM 47–21–06/401 ............... Flame Arrestor Installation ..... 47–21–06–400–801. Functional Test of the Nitrogen Generation System. Thermal Switch Functional Test. Thermal Switch Operational Test. 47–00–01–720–801. 47–43–02–700–801. 47–43–02–700–802. AMM 47. AMM 47. Federal Aviation Regulation No. 88 requirements. This proposed AD would also require the initial inspection of certain repetitive AWL inspections to phase in those inspections, and repair if necessary. This proposed AD results from a design review of the fuel tank systems. We are proposing 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. DATES: We must receive comments on this proposed AD by August 17, 2007. ADDRESSES: Use one of the following addresses to submit comments on this proposed AD. • 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, PO 00000 Frm 00022 Fmt 4702 Sfmt 4702 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 the 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 Ave 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 proposed AD. Send your comments to an address listed in the ADDRESSES section. Include the docket number ‘‘FAA–2007–28388; Directorate Identifier 2006–NM–163–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the proposed AD. We will consider all comments received by the closing date and may amend the proposed AD in light of those comments. We will post all comments we receive, without change, to https:// dms.dot.gov, including any personal E:\FR\FM\03JYP1.SGM 03JYP1

Agencies

[Federal Register Volume 72, Number 127 (Tuesday, July 3, 2007)]
[Proposed Rules]
[Pages 36385-36391]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-12816]

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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-28386; Directorate Identifier 2006-NM-162-AD]
RIN 2120-AA64

Airworthiness Directives; Boeing Model 747-400, -400D, and -400F
Series Airplanes

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

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD)
for certain Boeing Model 747-400, -400D, and -400F series airplanes.
This proposed AD would require revising the FAA-approved maintenance
program by incorporating new airworthiness limitations (AWLs) for fuel
tank systems to satisfy Special Federal Aviation Regulation No. 88
requirements. This proposed AD would also require the initial
inspection of certain repetitive AWL inspections to phase in those
inspections, and repair if necessary. This proposed AD results from a
design review of the fuel tank systems. We are proposing 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.

DATES: We must receive comments on this proposed AD by August 17, 2007.

ADDRESSES: Use one of the following addresses to submit comments on
this proposed AD.
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 the 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 Ave, 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 proposed AD. Send your comments to an address
listed in the ADDRESSES section. Include the docket number ``FAA-2007-
28386; Directorate Identifier 2006-NM-162-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of the proposed AD. We will
consider all comments received by the closing date and may amend the
proposed AD in light 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 with FAA
personnel concerning this proposed AD. 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 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 floor 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

The FAA has examined the underlying safety issues involved in fuel
tank explosions on several large transport airplanes, including the
adequacy of existing regulations, the service history of airplanes
subject to those regulations, and existing maintenance practices for
fuel tank systems. As a result of those findings, we issued a
regulation titled ``Transport

[[Page 36386]]

Airplane Fuel Tank System Design Review, Flammability Reduction and
Maintenance and Inspection Requirements'' (67 FR 23086, May 7, 2001).
In addition to new airworthiness standards for transport airplanes and
new maintenance requirements, this rule included Special Federal
Aviation Regulation No. 88 (``SFAR 88,'' Amendment 21-78, and
subsequent Amendments 21-82 and 21-83).
Among other actions, SFAR 88 requires certain type design (i.e.,
type certificate (TC) and supplemental type certificate (STC)) holders
to substantiate that their fuel tank systems can prevent ignition
sources in the fuel tanks. This requirement applies to type design
holders for large turbine-powered transport airplanes and for
subsequent modifications to those airplanes. It requires them to
perform design reviews and to develop design changes and maintenance
procedures if their designs do not meet the new fuel tank safety
standards. As explained in the preamble to the rule, we intended to
adopt airworthiness directives to mandate any changes found necessary
to address unsafe conditions identified as a result of these reviews.
In evaluating these design reviews, we have established four
criteria intended to define the unsafe conditions associated with fuel
tank systems that require corrective actions. The percentage of
operating time during which fuel tanks are exposed to flammable
conditions is one of these criteria. The other three criteria address
the failure types under evaluation: single failures, single failures in
combination with another latent condition(s), and in-service failure
experience. For all four criteria, the evaluations included
consideration of previous actions taken that may mitigate the need for
further action.
We have determined that the actions identified in this proposed AD
are necessary to reduce the potential of ignition sources inside fuel
tanks, which, in combination with flammable fuel vapors, could result
in a fuel tank explosion and consequent loss of the airplane.

Relevant Service Information

We have reviewed the following subsections of Boeing 747-400
Maintenance Planning Data (MPD) Document, D621U400-9, Section 9,
Revision 23, dated March 2006 (hereafter referred to as ``Revision
March 2006 of the MPD''):
Subsection B, ``AIRWORTHINESS LIMITATIONS (AWLs)--
SYSTEMS''
Subsection C, ``PAGE FORMAT: AIRWORTHINESS LIMITATIONS''
Subsection D, ``AIRWORTHINESS LIMITATIONS--FUEL SYSTEMS''
Those subsections of Revision March 2006 of the MPD describe new
AWLs for fuel tank systems. The new AWLs include:
AWL inspections, which are periodic inspections of certain
features for latent failures that could contribute to an ignition
source; and
Critical design configuration control limitations
(CDCCLs), which are limitation requirements to preserve a critical
ignition source prevention feature of the fuel tank system design that
is necessary to prevent the occurrence of an unsafe condition. The
purpose of a CDCCL is to provide instruction to retain the critical
ignition source prevention feature during configuration change that may
be caused by alterations, repairs, or maintenance actions. A CDCCL is
not a periodic inspection.
Accomplishing the actions specified in the service information is
intended to adequately address the unsafe condition.

FAA's Determination and Requirements of the Proposed AD

We have evaluated all pertinent information and identified an
unsafe condition that is likely to exist or develop on other airplanes
of this same type design. For this reason, we are proposing this AD,
which would require revising the FAA-approved maintenance program by
incorporating the information in Subsections B, C, and D of Revision
March 2006 of the MPD. This proposed AD would also require the initial
inspection of certain repetitive AWL inspections to phase in those
inspections, and repair if necessary.

Explanation of 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, the FAA
has 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 proposed AD, we are using this same compliance date in this
proposed AD, instead of the 18-month compliance time recommended by
Boeing.

Rework Required When Implementing AWLs Into an Existing Fleet

The maintenance program revision for the fuel tank systems
specified in paragraph (g) of this proposed AD, which involves
incorporating the information specified in Revision March 2006 of the
MPD, would affect how operators maintain their airplanes. After doing
that maintenance program revision, operators would need to do any
maintenance on the fuel tank system as specified in the CDCCLs.
Maintenance done before the maintenance program revision specified in
paragraph (g) would not need to be redone in order to comply with
paragraph (g). For example, the AWL that requires fuel pumps to be
repaired and overhauled per an FAA-approved component maintenance
manual (CMM) applies to fuel pumps repaired after the maintenance
programs are revised; spare or on-wing fuel pumps do not need to be
reworked. For AWLs that require repetitive inspections, the initial
inspection interval (threshold) starts from the date the maintenance
program revision specified in paragraph (g) is done, except as provided
by paragraph (h) of this proposed AD. This proposed AD would require
only the maintenance program revision specified in paragraph (g), and
initial inspections specified in paragraph (h). No other fleet-wide
inspections need to be done.

Changes to Fuel Tank System AWLs

Paragraph (g) of this proposed AD would require revising the FAA-
approved maintenance program by incorporating certain information
specified in Revision March 2006 of the MPD. Paragraph (g) allows
accomplishing the maintenance program revision in accordance with later
revisions of the MPD as an acceptable method of compliance if they are
approved by the Manager, Seattle Aircraft Certification Office (ACO),
FAA. Paragraph (h) allows accomplishing the initial inspections and
repair in accordance with later revisions of the MPD as an acceptable
method of compliance if they are approved by the Manager, Seattle ACO.
In addition, Subsection B of Revision March 2006 of the MPD specifies
that any deviations from the published AWL instructions, including AWL
intervals, in that MPD must be approved by the Manager, Seattle ACO.
Therefore, after the maintenance program revision, any further revision
to an AWL or AWL interval should be done as an AWL change, not as an
alternative method of compliance (AMOC). For U.S.-registered airplanes,
operators must make requests through an appropriate FAA Principal
Maintenance Inspector (PMI) or Principal Avionics Inspector (PAI) for
approval by the Manager, Seattle ACO. A non-U.S. operator should
coordinate

[[Page 36387]]

changes with its governing regulatory agency.

Exceptional Short-Term Extensions

Subsection B of Revision March 2006 of the MPD has provisions for
an exceptional short-term extension of 30 days. An exceptional short-
term extension is an increase in an AWL interval that may be needed to
cover an uncontrollable or unexpected situation. For U.S.-registered
airplanes, the FAA PMI or PAI must concur with any exceptional short-
term extension before it is used, unless the operator has identified
another appropriate procedure with the local regulatory authority. The
FAA PMI or PAI may grant the exceptional short-term extensions
described in Subsection B without consultation with the Manager,
Seattle ACO. A non-U.S. operator should coordinate changes with its
governing regulatory agency. As explained in Revision March 2006 of the
MPD, exceptional short-term extensions must not be used for fleet AWL
extensions. An exceptional short-term extension should not be confused
with an operator's short-term escalation authorization approved in
accordance with the Operations Specifications or the operator's
reliability program.

Ensuring Compliance With Fuel Tank System AWLs

Boeing has revised applicable maintenance manuals and task cards to
address AWLs and to include notes about CDCCLs. Operators that do not
use Boeing's revision service should revise their maintenance manuals
and task cards to highlight actions tied to CDCCLs to ensure that
maintenance personnel are complying with the CDCCLs. Appendix 1 of this
proposed AD contains a list of Air Transport Association (ATA) sections
for the revised maintenance manuals. Operators might wish to use the
appendix as an aid to implement the AWLs.

Recording Compliance With Fuel Tank System AWLs

The applicable operating rules of the Federal Aviation Regulations
(14 CFR parts 91, 121, 125, and 129) require operators to maintain
records with the identification of the current inspection status of an
airplane. Some of the AWLs contained in Subsection D of Revision March
2006 of the MPD are inspections for which the applicable sections of
the operating rules apply. Other AWLs are CDCCLs, which are tied to
conditional maintenance actions. An entry into an operator's existing
maintenance record system for corrective action is sufficient for
recording compliance with CDCCLs, as long as the applicable maintenance
manual and task cards identify actions that are CDCCLs.

Changes to CMMs Cited in Fuel Tank System AWLs

Some of the AWLs in Subsection D of Revision March 2006 of the MPD
refer to specific revision levels of the CMMs as additional sources of
service information for doing the AWLs. Boeing is referring to the CMMs
by revision level in the applicable AWL for certain components rather
than including information directly in the MPD because of the volume of
that information. As a result, the Manager, Seattle ACO, must approve
the CMMs. Any later revision of those CMMs will be handled like a
change to the AWL itself. Any use of parts (including the use of parts
manufacturer approval (PMA) approved parts), methods, techniques, and
practices not contained in the CMMs need to be approved by the Manager,
Seattle ACO, or governing regulatory authority. For example, certain
pump repair/overhaul manuals must be approved by the Manager, Seattle
ACO.

Changes to AMMs Referenced in Fuel Tank System AWLs

In other AWLs in Subsection D of Revision March 2006 of the MPD,
the AWLs contain all the necessary data. The applicable section of the
maintenance manual is usually included in the AWLs. Boeing intended
this information to assist operators in maintaining the maintenance
manuals. A maintenance manual change to these tasks may be made without
approval by the Manager, Seattle ACO, through an appropriate FAA PMI or
PAI, by the governing regulatory authority, or by using the operator's
standard process for revising maintenance manuals. An acceptable change
would have to maintain the information specified in the AWL such as the
pass/fail criteria or special test equipment.

Costs of Compliance

There are about 596 airplanes of the affected design in the
worldwide fleet. The following table provides the estimated costs, at
an average labor rate of $80 per hour, for U.S. operators to comply
with this proposed AD.

Estimated Costs
----------------------------------------------------------------------------------------------------------------
Number of
Work Cost per U.S.-
Action hours Parts airplane registered Fleet cost
airplanes
----------------------------------------------------------------------------------------------------------------
Maintenance program revision.............. 8 None.................. $640 57 $36,480
Inspections............................... 8 None.................. 640 57 36,480
----------------------------------------------------------------------------------------------------------------

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;

[[Page 36388]]

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 proposed AD 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-2007-28386; Directorate Identifier 2006-NM-
162-AD.

Comments Due Date

(a) The FAA must receive comments on this AD action by August
17, 2007.

Affected ADs

(b) None.

Applicability

(c) This AD applies to Boeing Model 747-400, -400D, and -400F
series airplanes, certificated in any category; with an original
standard airworthiness certificate or original export certificate of
airworthiness issued before April 12, 2006.

Note 1: Airplanes with an original standard airworthiness
certificate or original export certificate of airworthiness issued
on or after April 12, 2006, must be already in compliance with the
airworthiness limitations specified in this AD because those
limitations were applicable as part of the airworthiness
certification of those airplanes.

Note 2: 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 747-400
Maintenance Planning Data (MPD) Document, D621U400-9, according to
paragraph (g) or (i) of this AD, as applicable.

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 Reference

(f) The term ``Revision March 2006 of the MPD'' as used in this
AD, means Boeing 747-400 Maintenance Planning Data (MPD) Document,
D621U400-9, Section 9, Revision 23, dated March 2006.

Maintenance Program Revision

(g) Before December 16, 2008, revise the FAA-approved
maintenance program by incorporating the information in the
subsections specified in paragraphs (g)(1), (g)(2), and (g)(3) of
this AD; 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) Subsection B, ``AIRWORTHINESS LIMITATIONS (AWLs)--SYSTEMS,''
of Revision March 2006 of the MPD.
(2) Subsection C, ``PAGE FORMAT: AIRWORTHINESS LIMITATIONS,'' of
Revision March 2006 of the MPD.
(3) Subsection D, ``AIRWORTHINESS LIMITATIONS--FUEL SYSTEMS,''
of Revision March 2006 of the MPD.

Initial Inspections and Repair if Necessary

(h) Do the inspections specified in Table 1 of this AD and
repair any discrepancy, in accordance with Subsection D,
``AIRWORTHINESS LIMITATIONS--FUEL SYSTEMS,'' of Revision March 2006
of the MPD. The repair must be done before further flight.
Accomplishing the actions required by this paragraph 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.

Note 3: 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 4: 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.''

Table 1.--Initial Inspections
----------------------------------------------------------------------------------------------------------------
Compliance time (whichever occurs later)
AWL No. Description ------------------------------------------------------
Threshold Grace period
----------------------------------------------------------------------------------------------------------------
28-AWL-01....................... A detailed inspection Before the accumulation of 36,000 Within 72 months
of external wires over total flight cycles, or within after the
the center fuel tank 144 months since the date of effective date of
for damaged or loose issuance of the original this AD.
clamps, wire chafing, standard airworthiness
and wire bundles in certificate or the date of
contact with the issuance of the original export
surface of the center certificate of airworthiness,
fuel tank. whichever occurs first.
28-AWL-03....................... A special detailed Before the accumulation of 36,000 Within 24 months
inspection of the total flight cycles, or within after the
lightning shield to 144 months since the date of effective date of
ground termination on issuance of the original this AD.
the out-of-tank fuel standard airworthiness
quantity indicating certificate or the date of
system to verify issuance of the original export
functional integrity. certificate of airworthiness,
whichever occurs first.

[[Page 36389]]

28-AWL-10....................... A special detailed Before the accumulation of 36,000 Within 60 months
inspection of the total flight cycles, or within after the
fault current bond of 144 months since the date of effective date of
the fueling shutoff issuance of the original this AD.
valve actuator of the standard airworthiness
center wing tank to certificate or the date of
verify electrical bond. issuance of the original export
certificate of airworthiness,
whichever occurs first.
----------------------------------------------------------------------------------------------------------------

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.--Implementing Fuel Tank System Airworthiness Limitations on Model 747-400, -400D, and -400F Series
Airplanes
----------------------------------------------------------------------------------------------------------------
ATA section or CMM
AWL No. ALI/CDCCL document Task title Task No.
----------------------------------------------------------------------------------------------------------------
28-AWL-01...................... ALI................ AMM 28-11-00/601.. External Wires 28-11-00-210-801.
Over the Center
Fuel Tank--
Inspection.
28-AWL-02...................... CDCCL.............. SWPM 20-10-11..... Wiring Assembly
and Installation
Configuration.
28-AWL-03...................... ALI................ AMM 05-55-54/601.. FQIS Wiring and 05-55-54-200-801.
Bonding--Inspecti
on.
28-AWL-04...................... CDCCL.............. SWPM 20-10-15..... Assembly of Shield
Ground Wires.
28-AWL-05...................... CDCCL.............. AMM 29-11-22/401.. Heat Exchanger 29-11-22-404-014.
Installation.
28-AWL-06...................... CDCCL.............. CMM 28-22-07,
Revision 1; CMM
28-31-03,
Revision 3; CMM
28-26-12,
Revision 0; CMM
28-26-14,
Revision 0; CMM
28-20-02,
Revision 9; or
subsequent
revisions.
28-AWL-07...................... CDCCL.
28-AWL-08...................... CDCCL.............. SWPM 20-10-11..... Wiring Assembly
and Installation
Configuration..
28-AWL-09...................... CDCCL.............. AMM 28-21-02/401.. Refuel Valve 28-21-02-401-011.
Control Unit--
Installation.
AMM 28-21-13/401.. Refuel Valve 28-21-13-404-087.
Control Unit--
Installation.
28-AWL-10...................... ALI................ AMM 28-21-13/601.. Center Wing Tank 28-21-13-765-801.
Refuel Valve--
Fault Current
Bond Inspection.
28-AWL-11...................... CDCCL.............. CMM 28-41-62,
Revision 4 or
subsequent
revisions.
28-AWL-12...................... CDCCL.............. CMM 28-21-02,
Revision 2 or
subsequent
revisions.
28-AWL-13...................... CDCCL.............. CMM 28-41-63,
Revision 4 or
subsequent
revisions.
28-AWL-14...................... CDCCL.............. CMM 28-40-55,
Revision 6; CMM
28-40-56,
Revision 4; CMM
28-40-59,
Revision 5; or
subsequent
revisions.
28-AWL-15...................... CDCCL.............. SWPM 20-14-12..... Repair of Fuel
Quantity
Indicator System
(FQIS) Wire
Harness.
AMM 28-41-09/401.. FQIS Wire Bundle 28-41-09-404-019.
in the Main or
Reserve Tank--
Installation.
FQIS Wire Bundle 28-41-09-404-157.
in the Center
Wing Tank
Installation.
FQIS Wire Bundle 28-41-09-404-176.
in the Horizontal
Stabilizer Tank
Installation.

[[Page 36390]]

28-AWL-16...................... CDCCL.............. AMM 28-11-02/401.. Reserve and Main 28-11-02-404-011.
Tank Access Door
Installation.
AMM 28-11-03/401.. Access Door for 28-11-03-404-007.
the Wing Surge
Tank Installation.
28-AWL-17...................... ALI................ AMM 28-31-14/501.. Fault Current 28-31-14-715-001.
Detector
Operational Test.
AMM 28-17-14/501.. Fault Current 28-17-14-715-001.
Detector--Operati
onal Test.
28-AWL-18...................... CDCCL.............. CMM 28-31-22,
Revision 4 or
subsequent
revisions.
28-AWL-19...................... CDCCL.............. FIM 28-22-00/201.. CMCS Message LEFT 28-21 Task 806.
HORIZONTAL
STABILIZER PUMP
SYSTEM FAIL--
Fault Isolation.
CMCS Message RIGHT 28-21 Task 807.
HORIZONTAL
STABILIZER PUMP
SYSTEM FAIL--
Fault Isolation.
CMCS Message MAIN 28-22 Task 860.
TANK 1 FWD BOOST
PUMP SYSTEM FAIL--
Fault Isolation.
CMCS Message MAIN 28-22 Task 861.
TANK 1 AFT BOOST
PUMP SYSTEM FAIL--
Fault Isolation.
CMCS Message MAIN 28-22 Task 862.
TANK 2 FWD BOOST
PUMP SYSTEM FAIL--
Fault Isolation.
CMCS Message MAIN 28-22 Task 863.
TANK 2 AFT BOOST
PUMP SYSTEM FAIL--
Fault Isolation.
CMCS Message MAIN 28-22 Task 864.
TANK 3 FWD BOOST
PUMP SYSTEM FAIL--
Fault Isolation.
CMCS Message MAIN 28-22 Task 865.
TANK 3 AFT BOOST
PUMP SYSTEM FAIL--
Fault Isolation.
CMCS Message MAIN 28-22 Task 866.
TANK 4 FWD BOOST
PUMP SYSTEM FAIL--
Fault Isolation.
CMCS Message MAIN 28-22 Task 867.
TANK 4 AFT BOOST
PUMP SYSTEM FAIL--
Fault Isolation.
CMCS Message LEFT 28-31 Task 826.
CENTER TANK
OVERRIDE/JETTISON
PUMP SYSTEM FAIL--
Fault Isolation.
CMCS Message RIGHT 28-31 Task 827.
CENTER TANK
OVERRIDE/JETTISON
PUMP SYSTEM FAIL--
Fault Isolation.
CMCS Message MAIN 28-31 Task 828.
TK 2 AFT OVERRIDE/
JETTISON PUMP
SYSTEM FAIL--
Fault Isolation.
CMCS Message MAIN 28-31 Task 829.
TK 2 FWD OVERRIDE/
JETTISON PUMP
SYSTEM FAIL--
Fault Isolation.
CMCS Message MAIN 28-31 Task 830.
TK 3 AFT OVERRIDE/
JETTISON PUMP
SYSTEM FAIL--
Fault Isolation.

[[Page 36391]]

CMCS Message MAIN 28-31 Task 831.
TK 3 FWD OVERRIDE/
JETTISON PUMP
SYSTEM FAIL--
Fault Isolation.
28-AWL-20...................... CDCCL.............. AMM 28-22-07/401.. Front Spar 28-22-07-400-805-0
Bulkhead Fitting-- 01.
Installation.
28-22-07-400-806-0
02.
28-22-07-400-807-0
03.
28-22-07-400-808-0
04.
28-AWL-21...................... ALI................ AMM 28-22-00/501.
AMM 28-17-00/501.
28-AWL-22...................... CDCCL.............. AMM 28-22-03/401.. Main Tank Boost 28-22-03-404-019-0
Pump Motor/ 01.
Impeller Unit
Installation.
28-22-03-404-026-0
02.
28-AWL-23...................... CDCCL.............. AMM 28-41-24/401.
47-AWL-01...................... CDCCL.............. AMM 47-21-06/401.. Flame Arrestor 47-21-06-400-801.
Installation.
47-AWL-02...................... CDCCL.
47-AWL-03...................... ALI................ AMM 47-00-01/501.. Functional Test of 47-00-01-720-801.
the Nitrogen
Generation System.
47-AWL-04...................... ALI................ AMM 47-43-02/501.. Thermal Switch 47-43-02-700-801.
Functional Test.
Thermal Switch 47-43-02-700-802.
Operational Test.
47-AWL-05...................... ALI................ AMM 47.
47-AWL-06...................... ALI................ AMM 47.
----------------------------------------------------------------------------------------------------------------

Issued in Renton, Washington, on June 22, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E7-12816 Filed 7-2-07; 8:45 am]
BILLING CODE 4910-13-P

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