Airworthiness Directives; Boeing Model 737-100, -200, -200C, -300, -400, and -500 Series Airplanes, 36907-36912 [E7-13107]

Download as PDF Federal Register / Vol. 72, No. 129 / Friday, July 6, 2007 / Proposed Rules Comments Due Date (a) We must receive comments by August 6, 2007. Affected ADs (b) None. Applicability (c) This AD applies to 750XL airplanes, serial numbers 101, 102, 104 through 120, and 122 through 129, certificated in any category. Subject (d) Air Transport Association of America (ATA) Code 27: Flight Controls. Reason (e) The mandatory continuing airworthiness information (MCAI) states: To prevent cracks developing in the aileron spar adjacent to the inboard hinge attachment accomplish the following: Remove both ailerons, inspect and modify the aileron spar at the inboard hinge attachment point in accordance with Pacific Aerospace Ltd Service Bulletin PACSB/XL/ 027. Actions and Compliance (f) Unless already done, within the next 6 months after the effective date of this AD or 150 hours time-in-service (TIS) after the effective date of this AD, whichever occurs first, rework the left and right ailerons in accordance with Pacific Aerospace Ltd drawing number 11–03141/42, drawn March 26, 2007, as specified in Pacific Aerospace Limited Mandatory Service Bulletin PACSB/ XL/027, dated March 27, 2007. (44 U.S.C. 3501 et seq.), the Office of Management and Budget (OMB) has approved the information collection requirements and has assigned OMB Control Number 2120–0056. Related Information (h) Refer to MCAI Civil Aviation Authority of New Zealand AD DCA/750XL/13, effective date April 26, 2007; Pacific Aerospace Limited Mandatory Service Bulletin PACSB/ XL/027, dated March 27, 2007; and Pacific Aerospace Ltd drawing number 11–03141/42, drawn March 26, 2007, for related information. Issued in Kansas City, Missouri, on June 29, 2007. Kim Smith, Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. E7–13092 Filed 7–5–07; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2007–28383; Directorate Identifier 2006–NM–180–AD] RIN 2120–AA64 Airworthiness Directives; Boeing Model 737–100, –200, –200C, –300, –400, and –500 Series Airplanes Note: This AD differs from the MCAI and/ or service information as follows: No differences. Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). Other FAA AD Provisions (g) The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, Standards Staff, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Send information to ATTN: Karl Schletzbaum, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329–4146; fax: (816) 329–4090. 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. (2) Airworthy Product: For any requirement in this AD to obtain corrective actions from a manufacturer or other source, use these actions if they are FAA-approved. Corrective actions are considered FAA-approved if they are approved by the State of Design Authority (or their delegated agent). You are required to assure the product is airworthy before it is returned to service. (3) Reporting Requirements: For any reporting requirement in this AD, under the provisions of the Paperwork Reduction Act SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) for all Boeing Model 737–100, –200, –200C, –300, –400, and –500 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 Federal Aviation Regulation No. 88 requirements. This proposed AD would also require the initial inspection of a certain repetitive AWL inspection to phase in that inspection, 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 20, 2007. rmajette on PROD1PC64 with PROPOSALS FAA AD Differences VerDate Aug<31>2005 15:25 Jul 05, 2007 Jkt 211001 AGENCY: PO 00000 Frm 00008 Fmt 4702 Sfmt 4702 36907 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: ADDRESSES: 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–2007–28383; Directorate Identifier 2006–NM–180–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 E:\FR\FM\06JYP1.SGM 06JYP1 36908 Federal Register / Vol. 72, No. 129 / Friday, July 6, 2007 / Proposed Rules Statement in the Federal Register published on April 11, 2000 (65 FR 19477–78), or you may visit https:// dms.dot.gov. rmajette on PROD1PC64 with PROPOSALS 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 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 VerDate Aug<31>2005 15:25 Jul 05, 2007 Jkt 211001 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 Boeing 737–100/ 200/200C/300/400/500 Airworthiness Limitations (AWLs) and Certification Maintenance Requirements (CMRs), D6– 38278–CMR, Revision May 2006 (hereafter referred to as ‘‘Revision May 2006 of Document D6–38278-CMR’’). Section C of Revision May 2006 of Document D6–38278-CMR describes 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 to incorporate the information in Section C of Revision May 2006 of Document D6–38278–CMR. This proposed AD would also require the initial inspection of a certain repetitive PO 00000 Frm 00009 Fmt 4702 Sfmt 4702 AWL inspection to phase in that inspection, 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 May 2006 of Document D6–38278–CMR, 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 that 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 the initial inspection 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 May 2006 of Document D6–38278–CMR. Paragraph (g) allows accomplishing the maintenance program revision in accordance with later revisions of E:\FR\FM\06JYP1.SGM 06JYP1 36909 Federal Register / Vol. 72, No. 129 / Friday, July 6, 2007 / Proposed Rules Document D6–38278–CMR 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 inspection and repair in accordance with later revisions of Document D6–38278–CMR as an acceptable method of compliance if they are approved by the Manager, Seattle ACO. In addition, Section C of Revision March 2006 of Document D6–38278– CMR specifies that any deviations from the published AWL instructions, including AWL intervals, 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 changes with its governing regulatory agency. Exceptional Short-Term Extensions Section C of Revision March 2006 of Document D6–38278–CMR 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 Section C without consultation with the Manager, Seattle ACO. A non-U.S. operator should coordinate changes with its governing regulatory agency. As explained in Section C, 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 for Model 737–100, –200, and –200C series airplanes. Appendix 2 of this proposed AD contains a list of ATA sections for the revised maintenance manuals for Model 737–300, –400, and –500 series airplanes. Operators might wish to use the appendices 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 Section C of Revision March 2006 of Document D6–38278– CMR 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 Section C of Revision March 2006 of Document D6– 38278–CMR 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 AWL 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 Section C of Revision March 2006 of Document D6– 38278–CMR, 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 2,337 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 rmajette on PROD1PC64 with PROPOSALS Action Work hours Maintenance program revision ................. Inspection .................................................. VerDate Aug<31>2005 15:25 Jul 05, 2007 Jkt 211001 8 8 PO 00000 Cost per airplane Parts None ......................................................... None ......................................................... Frm 00010 Fmt 4702 Sfmt 4702 E:\FR\FM\06JYP1.SGM $640 640 06JYP1 Number of U.S.registered airplanes 672 672 Fleet cost $430,080 430,080 36910 Federal Register / Vol. 72, No. 129 / Friday, July 6, 2007 / Proposed Rules 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 proposed AD and placed it in the AD docket. See the ADDRESSES section for a location to examine the regulatory evaluation. Maintenance Program Revision 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–2007–28383; Directorate Identifier 2006–NM–180–AD. Comments Due Date (a) The FAA must receive comments on this AD action by August 20, 2007. Affected ADs (b) None. Applicability (c) This AD applies to all Boeing Model 737–100, –200, –200C, –300, –400, and –500 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 in the Boeing 737–100/200/200C/300/400/500 Airworthiness Limitations (AWLs) and Certification Maintenance Requirements (CMRs), D6–38278–CMR, 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. rmajette on PROD1PC64 with PROPOSALS List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Safety. 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. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: Service Information Reference (f) The term ‘‘Revision May 2006 of Document D6–38278–CMR’’ as used in this AD, means Boeing 737–100/200/200C/300/ 400/500 AWLs and CMRs, D6–38278–CMR, Revision May 2006. VerDate Aug<31>2005 15:25 Jul 05, 2007 Jkt 211001 PO 00000 Frm 00011 Fmt 4702 Sfmt 4702 (g) Before December 16, 2008, revise the FAA-approved maintenance program to incorporate the information in Section C of Revision May 2006 of Document D6–38278– CMR; except that the initial inspection required by paragraph (h) of this AD must be done at the applicable compliance time specified in that paragraph. Accomplishing the revision in accordance with a later revision of Document D6–38278–CMR is an acceptable method of compliance if the revision is approved by the Manager, Seattle Aircraft Certification Office (ACO), FAA. Initial Inspection and Repair if Necessary (h) At the later of the compliance times specified in paragraphs (h)(1) and (h)(2) of this AD, do a special detailed inspection of the lightning shield to ground termination on the out-of-tank fuel quantity indication system (FQIS) wiring to verify functional integrity, in accordance with AWL Number 28–AWL–03 of Section C of Revision May 2006 of Document D6–38278–CMR. If any discrepancy is found during the inspection, repair the discrepancy before further flight in accordance with AWL Number 28–AWL–03 of Section C of Revision May 2006 of Document D6–38278–CMR. Accomplishing the actions required by this paragraph in accordance with a later revision of Document D6–38278–CMR is an acceptable method of compliance if the revision is approved by the Manager, Seattle ACO. Note 2: 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.’’ (1) Prior to the accumulation of 36,000 total flight hours, or within 120 months since the date of issuance of the original standard airworthiness certification or the date of issuance of the original export certificate of airworthiness, whichever ever occurs first. (2) Within 24 months after the effective date of this AD. Alternative Methods of Compliance (AMOCs) (i)(1) The Manager, Seattle Aircraft Certification Office, 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. E:\FR\FM\06JYP1.SGM 06JYP1 36911 Federal Register / Vol. 72, No. 129 / Friday, July 6, 2007 / Proposed Rules APPENDIX 1.—IMPLEMENTING FUEL TANK SYSTEM AIRWORTHINESS LIMITATIONS ON MODEL 737–100, –200, AND –200C 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 ................. 28–AWL–04 ................. 28–AWL–05 ................. ALI .............................. CDCCL ....................... CDCCL ....................... AMM 20–55–54/601 ........................................ SWPM 20–10–15 ............................................ SWPM 20–10–11 ............................................ External Wires Over the Center Tank Inspection. Wiring Assembly and Installation Configuration. FQIS Connectors—Inspection/Check. Assembly of Shield Ground Wires. Wiring Assembly and Installation Configuration. 28–AWL–06 ................. CDCCL ....................... 28–AWL–07 ................. CDCCL ....................... 28–AWL–08 ................. CDCCL ....................... CMM 28–41–11, Revision 12; CMM 28–41– 13, Revision 11; CMM 28–41–23, Revision 10; or subsequent revisions. CMM 28–40–25, Revision L; CMM 28–41–05, Revision 11; CMM 28–40–58, Revision 4; or subsequent revisions. AMM 28–41–101/401 ...................................... 28–AWL–09 ................. CDCCL ....................... AMM 29–11–53/401 ........................................ 28–AWL–10 ................. 28–AWL–11 ................. 28–AWL–12 ................. CDCCL ....................... CDCCL. CDCCL ....................... AMM 28–22–142/401 ...................................... 28–AWL–13 28–AWL–14 28–AWL–15 28–AWL–16 CDCCL CDCCL CDCCL CDCCL ....................... ....................... ....................... ....................... CMM 28–20–37, Revision 10; CMM 28–20–1, Revision 7; CMM 28–20–5, Revision 6; CMM 28–20–07, Revision 1; or subsequent revisions. AMM 28–22–41/401 ........................................ AMM 28–21–71/401 ........................................ AMM 28–11–13/401 ........................................ AMM 28–11–11/401 ........................................ 28–AWL–17 ................. CDCCL ....................... AMM 28–11–11/401 ........................................ 28–AWL–18 ................. CDCCL ....................... AMM 28–13–31/401 ........................................ AMM 28–22–41/601 ........................................ 28–AWL–19 ................. 28–AWL–20 ................. CDCCL ....................... CDCCL. AMM 28–22–00/101 ........................................ ................. ................. ................. ................. Remove/Install Fuel Tank Bulkhead (Spar) Receptacle Wire Harness. Install System A Hydraulic Fluid Heat Exchanger. Install the Bulkhead Fitting. Install the Boost Pump. Float Switch Installation. Install Center Tank Access Panel. Removal/Installation of Access Panels 1 Thru 13. Removal/Installation of Access Panels No. 14. Install Flame Arrestor. Fuel Boost Pump Wiring and Conduit—Inspection/Check. Troubleshoot the Fuel Feed System APPENDIX 2.—IMPLEMENTING FUEL TANK SYSTEM AIRWORTHINESS LIMITATIONS ON MODEL 737–300, –400, AND –500 SERIES AIRPLANES AWL No. ALI/CDCCL ATA section or CMM document Task title Task No. 28–AWL–01 ........... ALI ......................... AMM 28–11–00/601 ........................... 28–11–00–206–281 28–AWL–02 ........... CDCCL ................... SWPM 20–10–11 ............................... 28–AWL–03 ........... 28–AWL–04 ........... 28–AWL–05 ........... ALI ......................... CDCCL ................... CDCCL ................... AMM 20–55–54/601 ........................... SWPM 20–10–15 ............................... SWPM 20–10–11 ............................... External Wires Over the Center Tank Inspection. Wiring Assembly and Installation Configuration. FQIS Connectors—Inspection/Check Assembly of Shield Ground Wires ..... Wiring Assembly and Installation Configuration. Isolated Fuel Quantity Transmitter (IFQT) Installation. ............................................................ ............................................................ AMM 28–41–72/401 ........................... CDCCL ................... CDCCL ................... 28–AWL–08 ........... rmajette on PROD1PC64 with PROPOSALS 28–AWL–06 ........... 28–AWL–07 ........... CDCCL ................... ............................................................ CMM 28–40–25, Revision L; CMM 28–41–05, Revision 11; CMM 28– 40–58, Revision 4; or subsequent revisions. SWPM 20–14–12 ............................... 28–AWL–09 ........... 28–AWL–10 ........... CDCCL ................... CDCCL ................... AMM 28–41–44/401 ........................... AMM 29–15–04/401 ........................... AMM 28–22–15/401 ........................... 28–AWL–11 ........... 28–AWL–12 ........... CDCCL CDCCL ................... 28–AWL–13 ........... CDCCL ................... VerDate Aug<31>2005 15:25 Jul 05, 2007 Jkt 211001 CMM 28–20–07, Revision 10; CMM 28–20–1, Revision 7; CMM 28–20– 5, Revision 6; CMM 28–20–07, Revision 1; or subsequent revisions. AMM 28–22–41/401 ........................... PO 00000 Frm 00012 Fmt 4702 Sfmt 4702 20–55–54–286–001 ................................ ................................ 28–41–72–404–018 ................................ ................................ Repair of Fuel Quantity Indicator System (FQIS) Wire Harness. Wire Bundle Replacement ................. Heat Exchanger Installation ............... Engine Fuel Feed Tube Bulkhead Fitting Installation. ................................ ............................................................ ................................ Fuel Boost Pump Installation ............. 28–22–41–404–019 E:\FR\FM\06JYP1.SGM 06JYP1 28–41–44–404–001 29–15–04–294–048 28–22–15–404–044 36912 Federal Register / Vol. 72, No. 129 / Friday, July 6, 2007 / Proposed Rules APPENDIX 2.—IMPLEMENTING FUEL TANK SYSTEM AIRWORTHINESS LIMITATIONS ON MODEL 737–300, –400, AND –500 SERIES AIRPLANES—Continued AWL No. ALI/CDCCL ATA section or CMM document Task title Task No. 28–AWL–14 ........... CDCCL ................... AMM 28–21–71/401 ........................... AIRPLANES WITH TYPE I FLOAT SWITCH; Float Switch Installation. AIRPLANES WITH TYPE II FLOAT SWITCH; Float Switch Installation. Center Tank Access Panel Installation. Access Panels No. 1 thru 13 Installation. Pressure Relief Valve Installation ...... Access Panel No. 14 Installation ....... Flame Arrester Installation ................. 28–22–71–404–013 28–AWL–15 ........... CDCCL ................... AMM 28–11–31/401 ........................... 28–AWL–16 ........... CDCCL ................... AMM 28–11–11/401 ........................... 28–AWL–17 ........... CDCCL ................... AMM 28–13–41/401 ........................... AMM 28–13–31/401 ........................... 28–AWL–18 ........... 28–AWL–19 ........... CDCCL ................... AMM 28–22–00/601 ........................... CDCCL ................... AMM 28–22–00/101 ........................... Issued in Renton, Washington, on June 22, 2007. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E7–13107 Filed 7–5–07; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2007–28434; Directorate Identifier 2007–CE–053–AD] RIN 2120–AA64 Airworthiness Directives; Hawker Beechcraft Corporation (Type Certificates No. 3A15 and No. 3A16 Previously Held by Raytheon Aircraft Company) F33 Series and Models G33, V35B, A36, A36TC, B36TC, 95–B55, D55, E55, A56TC, 58, and G58 Airplanes and Raytheon Aircraft Company Models 58P, 58TC, and 77 Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). rmajette on PROD1PC64 with PROPOSALS AGENCY: SUMMARY: We propose to adopt a new airworthiness directive (AD) for certain Hawker Beechcraft Corporation F33 Series and Models G33, V35B, A36, A36TC, B36TC, 95–B55, D55, E55, A56TC, 58, and G58 airplanes and Raytheon Aircraft Company Models 58P, 58TC, and 77 airplanes. This proposed AD would require you to VerDate Aug<31>2005 15:50 Jul 05, 2007 Jkt 211001 Fuel Boost Pump Wiring in Conduit, No. 1 Tank Inspection. Fuel Boost Pump Wiring in Conduit, No. 1 Tank Inspection. Engine Fuel Feed System—Trouble Shooting. replace certain circuit breaker toggle switches with improved design circuit breaker toggle switches. This proposed AD results from reports of certain circuit breaker toggle switches used in various electrical systems throughout the affected airplanes overheating. We are proposing this AD to prevent failure of the circuit breaker toggle switch, which could result in smoke in the cockpit and the inability to turn off the switch. DATES: We must receive comments on this proposed AD by September 4, 2007. ADDRESSES: Use one of the following addresses to comment on this proposed AD: • DOT Docket Web site: Go to https://dms.dot.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: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room 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. For service information identified in this proposed AD, contact Hawker Beechcraft Corporation, 9709 East Central, Wichita, Kansas 67291; telephone: (800) 429–5372 or (316) 676– 3140. FOR FURTHER INFORMATION CONTACT: Jose Flores, Aviation Safety Engineer, PO 00000 Frm 00013 Fmt 4702 Sfmt 4702 28–22–71–424–093 28–11–31–404–008 28–11–11–404–002 28–13–41–404–010 28–11–11–404–004 28–13–31–404– 007, or 28–13–31–404–032 28–22–00–216–033 28–22–00–216–044 ................................ Wichita Aircraft Certification Office, 1801 Airport Road, Room 100, Wichita, Kansas 67209; telephone: (316) 946– 4132; fax: (316) 946–4107. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments regarding this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include the docket number, ‘‘FAA–2007–28434; Directorate Identifier 2007–CE–053–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 we receive concerning this proposed AD. Discussion We have received reports of circuit breaker toggle switch failure on certain Hawker Beechcraft Corporation F33 Series and Models G33, V35B, A36, A36TC, B36TC, 95–B55, D55, E55, A56TC, 58, and G58 airplanes and Raytheon Aircraft Company Models 58P, 58TC, and 77 airplanes. These circuit breaker toggle switches are used in various electrical systems throughout the airplanes, which include but are not limited to anti-ice systems (PITOT, WSHLD, PROP), landing lights, strobe E:\FR\FM\06JYP1.SGM 06JYP1

Agencies

[Federal Register Volume 72, Number 129 (Friday, July 6, 2007)]
[Proposed Rules]
[Pages 36907-36912]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-13107]

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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-28383; Directorate Identifier 2006-NM-180-AD]
RIN 2120-AA64

Airworthiness Directives; Boeing Model 737-100, -200, -200C, -
300, -400, and -500 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 all Boeing Model 737-100, -200, -200C, -300, -400, and -500 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 Federal Aviation Regulation
No. 88 requirements. This proposed AD would also require the initial
inspection of a certain repetitive AWL inspection to phase in that
inspection, 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 20, 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-
28383; Directorate Identifier 2006-NM-180-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

[[Page 36908]]

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 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 Boeing 737-100/200/200C/300/400/500 Airworthiness
Limitations (AWLs) and Certification Maintenance Requirements (CMRs),
D6-38278-CMR, Revision May 2006 (hereafter referred to as ``Revision
May 2006 of Document D6-38278-CMR''). Section C of Revision May 2006 of
Document D6-38278-CMR describes 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 to
incorporate the information in Section C of Revision May 2006 of
Document D6-38278-CMR. This proposed AD would also require the initial
inspection of a certain repetitive AWL inspection to phase in that
inspection, 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 May 2006 of
Document D6-38278-CMR, 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 that 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 the initial inspection 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 May 2006 of Document D6-38278-CMR. Paragraph (g)
allows accomplishing the maintenance program revision in accordance
with later revisions of

[[Page 36909]]

Document D6-38278-CMR 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 inspection and
repair in accordance with later revisions of Document D6-38278-CMR as
an acceptable method of compliance if they are approved by the Manager,
Seattle ACO. In addition, Section C of Revision March 2006 of Document
D6-38278-CMR specifies that any deviations from the published AWL
instructions, including AWL intervals, 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 changes with its governing
regulatory agency.

Exceptional Short-Term Extensions

Section C of Revision March 2006 of Document D6-38278-CMR 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 Section C without consultation with the
Manager, Seattle ACO. A non-U.S. operator should coordinate changes
with its governing regulatory agency. As explained in Section C,
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 for Model 737-100, -200, and -200C
series airplanes. Appendix 2 of this proposed AD contains a list of ATA
sections for the revised maintenance manuals for Model 737-300, -400,
and -500 series airplanes. Operators might wish to use the appendices
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 Section C of Revision March
2006 of Document D6-38278-CMR 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 Section C of Revision March 2006 of Document
D6-38278-CMR 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
AWL 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 Section C of Revision March 2006 of Document D6-
38278-CMR, 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 2,337 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
Cost per U.S.-
Action Work hours Parts airplane registered Fleet cost
airplanes
----------------------------------------------------------------------------------------------------------------
Maintenance program revision........ 8 None.................. $640 672 $430,080
Inspection.......................... 8 None.................. 640 672 430,080
----------------------------------------------------------------------------------------------------------------

[[Page 36910]]

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 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-2007-28383; Directorate Identifier 2006-NM-
180-AD.

Comments Due Date

(a) The FAA must receive comments on this AD action by August
20, 2007.

Affected ADs

(b) None.

Applicability

(c) This AD applies to all Boeing Model 737-100, -200, -200C, -
300, -400, and -500 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 in the Boeing 737-100/200/200C/300/
400/500 Airworthiness Limitations (AWLs) and Certification
Maintenance Requirements (CMRs), D6-38278-CMR, 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 May 2006 of Document D6-38278-CMR'' as
used in this AD, means Boeing 737-100/200/200C/300/400/500 AWLs and
CMRs, D6-38278-CMR, Revision May 2006.

Maintenance Program Revision

(g) Before December 16, 2008, revise the FAA-approved
maintenance program to incorporate the information in Section C of
Revision May 2006 of Document D6-38278-CMR; except that the initial
inspection required by paragraph (h) of this AD must be done at the
applicable compliance time specified in that paragraph.
Accomplishing the revision in accordance with a later revision of
Document D6-38278-CMR is an acceptable method of compliance if the
revision is approved by the Manager, Seattle Aircraft Certification
Office (ACO), FAA.

Initial Inspection and Repair if Necessary

(h) At the later of the compliance times specified in paragraphs
(h)(1) and (h)(2) of this AD, do a special detailed inspection of
the lightning shield to ground termination on the out-of-tank fuel
quantity indication system (FQIS) wiring to verify functional
integrity, in accordance with AWL Number 28-AWL-03 of Section C of
Revision May 2006 of Document D6-38278-CMR. If any discrepancy is
found during the inspection, repair the discrepancy before further
flight in accordance with AWL Number 28-AWL-03 of Section C of
Revision May 2006 of Document D6-38278-CMR. Accomplishing the
actions required by this paragraph in accordance with a later
revision of Document D6-38278-CMR is an acceptable method of
compliance if the revision is approved by the Manager, Seattle ACO.

Note 2: 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.''

(1) Prior to the accumulation of 36,000 total flight hours, or
within 120 months since the date of issuance of the original
standard airworthiness certification or the date of issuance of the
original export certificate of airworthiness, whichever ever occurs
first.
(2) Within 24 months after the effective date of this AD.

Alternative Methods of Compliance (AMOCs)

(i)(1) The Manager, Seattle Aircraft Certification Office, 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.

[[Page 36911]]

Appendix 1.--Implementing Fuel Tank System Airworthiness Limitations on Model 737-100, -200, and -200C Series
Airplanes
----------------------------------------------------------------------------------------------------------------
ATA section or CMM
AWL No. ALI/CDCCL document Task title
----------------------------------------------------------------------------------------------------------------
28-AWL-01......................... ALI.................. AMM 28-11-00/601.......... External Wires Over the
Center Tank Inspection.
28-AWL-02......................... CDCCL................ SWPM 20-10-11............. Wiring Assembly and
Installation
Configuration.
28-AWL-03......................... ALI.................. AMM 20-55-54/601.......... FQIS Connectors--
Inspection/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 28-41-11, Revision 12;
CMM 28-41-13, Revision
11; CMM 28-41-23,
Revision 10; or
subsequent revisions.
28-AWL-07......................... CDCCL................ CMM 28-40-25, Revision L;
CMM 28-41-05, Revision
11; CMM 28-40-58,
Revision 4; or subsequent
revisions.
28-AWL-08......................... CDCCL................ AMM 28-41-101/401......... Remove/Install Fuel Tank
Bulkhead (Spar)
Receptacle Wire Harness.
28-AWL-09......................... CDCCL................ AMM 29-11-53/401.......... Install System A
Hydraulic Fluid Heat
Exchanger.
28-AWL-10......................... CDCCL................ AMM 28-22-142/401......... Install the Bulkhead
Fitting.
28-AWL-11......................... CDCCL................
28-AWL-12......................... CDCCL................ CMM 28-20-37, Revision 10;
CMM 28-20-1, Revision 7;
CMM 28-20-5, Revision 6;
CMM 28-20-07, Revision 1;
or subsequent revisions.
28-AWL-13......................... CDCCL................ AMM 28-22-41/401.......... Install the Boost Pump.
28-AWL-14......................... CDCCL................ AMM 28-21-71/401.......... Float Switch
Installation.
28-AWL-15......................... CDCCL................ AMM 28-11-13/401.......... Install Center Tank
Access Panel.
28-AWL-16......................... CDCCL................ AMM 28-11-11/401.......... Removal/Installation of
Access Panels 1 Thru 13.
28-AWL-17......................... CDCCL................ AMM 28-11-11/401.......... Removal/Installation of
Access Panels No. 14.
AMM 28-13-31/401.......... Install Flame Arrestor.
28-AWL-18......................... CDCCL................ AMM 28-22-41/601.......... Fuel Boost Pump Wiring
and Conduit--Inspection/
Check.
28-AWL-19......................... CDCCL................ AMM 28-22-00/101.......... Troubleshoot the Fuel
Feed System
28-AWL-20......................... CDCCL................
----------------------------------------------------------------------------------------------------------------

Appendix 2.--Implementing Fuel Tank System Airworthiness Limitations on Model 737-300, -400, and -500 Series
Airplanes
----------------------------------------------------------------------------------------------------------------
ATA section or
AWL No. ALI/CDCCL CMM document Task title Task No.
----------------------------------------------------------------------------------------------------------------
28-AWL-01................. ALI....................... AMM 28-11-00/601. External Wires 28-11-00-206-281
Over the Center
Tank Inspection.
28-AWL-02................. CDCCL..................... SWPM 20-10-11.... Wiring Assembly
and Installation
Configuration.
28-AWL-03................. ALI....................... AMM 20-55-54/601. FQIS Connectors-- 20-55-54-286-001
Inspection/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.
AMM 28-41-72/401. Isolated Fuel 28-41-72-404-018
Quantity
Transmitter
(IFQT)
Installation.
28-AWL-06................. CDCCL..................... ................. ................. ..................
28-AWL-07................. CDCCL..................... CMM 28-40-25, ................. ..................
Revision L; CMM
28-41-05,
Revision 11; CMM
28-40-58,
Revision 4; or
subsequent
revisions.
28-AWL-08................. CDCCL..................... SWPM 20-14-12.... Repair of Fuel ..................
Quantity
Indicator System
(FQIS) Wire
Harness.
AMM 28-41-44/401. Wire Bundle 28-41-44-404-001
Replacement.
28-AWL-09................. CDCCL..................... AMM 29-15-04/401. Heat Exchanger 29-15-04-294-048
Installation.
28-AWL-10................. CDCCL..................... AMM 28-22-15/401. Engine Fuel Feed 28-22-15-404-044
Tube Bulkhead
Fitting
Installation.
28-AWL-11................. CDCCL
28-AWL-12................. CDCCL..................... CMM 28-20-07, ................. ..................
Revision 10; CMM
28-20-1,
Revision 7; CMM
28-20-5,
Revision 6; CMM
28-20-07,
Revision 1; or
subsequent
revisions.
28-AWL-13................. CDCCL..................... AMM 28-22-41/401. Fuel Boost Pump 28-22-41-404-019
Installation.

[[Page 36912]]

28-AWL-14................. CDCCL..................... AMM 28-21-71/401. AIRPLANES WITH 28-22-71-404-013
TYPE I FLOAT
SWITCH; Float
Switch
Installation.
AIRPLANES WITH 28-22-71-424-093
TYPE II FLOAT
SWITCH; Float
Switch
Installation.
28-AWL-15................. CDCCL..................... AMM 28-11-31/401. Center Tank 28-11-31-404-008
Access Panel
Installation.
28-AWL-16................. CDCCL..................... AMM 28-11-11/401. Access Panels No. 28-11-11-404-002
1 thru 13
Installation.
28-AWL-17................. CDCCL..................... AMM 28-13-41/401. Pressure Relief 28-13-41-404-010
Valve
Installation.
Access Panel No. 28-11-11-404-004
14 Installation.
AMM 28-13-31/401. Flame Arrester 28-13-31-404-007,
Installation. or
28-13-31-404-032
28-AWL-18................. CDCCL..................... AMM 28-22-00/601. Fuel Boost Pump 28-22-00-216-033
Wiring in
Conduit, No. 1
Tank Inspection.
Fuel Boost Pump 28-22-00-216-044
Wiring in
Conduit, No. 1
Tank Inspection.
28-AWL-19................. CDCCL..................... AMM 28-22-00/101. Engine Fuel Feed ..................
System--Trouble
Shooting.
----------------------------------------------------------------------------------------------------------------

Issued in Renton, Washington, on June 22, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E7-13107 Filed 7-5-07; 8:45 am]
BILLING CODE 4910-13-P

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