Airworthiness Directives; The Boeing Company Model 737-100, -200, -200C, -300, -400, and -500 Series Airplanes, 3856-3859 [2011-1226]

Download as PDF WReier-Aviles on DSKGBLS3C1PROD with PROPOSALS 3856 Federal Register / Vol. 76, No. 14 / Friday, January 21, 2011 / Proposed Rules modified pulley bracket as specified in Reims Aviation Industries Service Bulletin No. F406–58, REV 1, dated October 27, 2006; or Reims Aviation Industries Service Bulletin No. F406–58, REV 2, dated July 27, 2010. This installation terminates the repetitive inspections required in paragraph (f)(1)(ii) of this AD. (iv) Within the next 100 hours TIS or 2 months after February 13, 2007 (the effective date retained from AD 2007–02–12), whichever occurs first, install the modified pulley bracket as specified in Reims Aviation Industries Service Bulletin No. F406–58, REV 1, dated October 27, 2006; or Reims Aviation Industries Service Bulletin No. F406–58, REV 2, dated July 27, 2010. This installation terminates the repetitive inspections required in paragraph (f)(1)(ii) of this AD. (v) The modified pulley bracket specified in Reims Aviation Industries Service Bulletin No. F406–58, REV 1, dated October 27, 2006; or Reims Aviation Industries Service Bulletin No. F406–58, REV 2, dated July 27, 2010, may be installed at any time after the inspection required in paragraph (f)(1)(i) of this AD, as long as no cracking is found, but no later than the compliance time specified in paragraph (f)(1)(iv) of this AD. If cracking is found, it must be replaced before further flight as required in paragraph (f)(1)(iii) of this AD. (2) For serial number F406–0091: (i) Within the next 10 hours TIS after the effective of this AD, perform the initial inspection as specified in Reims Aviation Industries Service Bulletin No. F406–58, REV 2, dated July 27, 2010. (ii) If no cracking is found following the initial inspection required in paragraph (f)(2)(i) of this AD, repetitively thereafter inspect every 50 hours TIS or 1 month, whichever occurs first, until the installation of the modified pulley bracket specified in paragraphs (f)(2)(iii) and (f)(2)(iv) of this AD is done. (iii) If any cracking is found during the inspection required in paragraph (f)(2)(i) of this AD, before further flight, install the modified pulley bracket as specified in Reims Aviation Industries Service Bulletin No. F406–58, REV 2, dated July 27, 2010. This installation terminates the repetitive inspections required in paragraph (f)(2)(ii) of this AD. (iv) Within the next 100 hours TIS or 2 months after the effective of this AD, whichever occurs first, install the modified pulley bracket as specified in Reims Aviation Industries Service Bulletin No. F406–58, REV 2, dated July 27, 2010. This installation terminates the repetitive inspections required in paragraph (f)(2)(ii) of this AD. (v) The modified pulley bracket specified in Reims Aviation Industries Service Bulletin No. F406–58, REV 2, dated July 27, 2010, may be installed at any time after the inspection required in paragraph (f)(2)(i) of this AD as long as no cracking is found, but no later than the compliance time specified in paragraph (f)(2)(iv) of this AD. If cracking is found, it must be replaced before further flight as required in paragraph (f)(2)(iii) of this AD. VerDate Mar<15>2010 12:47 Jan 20, 2011 Jkt 223001 FAA AD Differences Note: This AD differs from the MCAI and/ or service information as follows: No differences. Other FAA AD Provisions (g) The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, Standards Office, 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: Albert Mercado, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329–4119; 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, a federal agency may not conduct or sponsor, and a person is not required to respond to, nor shall a person be subject to a penalty for failure to comply with a collection of information subject to the requirements of the Paperwork Reduction Act unless that collection of information displays a current valid OMB Control Number. The OMB Control Number for this information collection is 2120–0056. Public reporting for this collection of information is estimated to be approximately 5 minutes per response, including the time for reviewing instructions, completing and reviewing the collection of information. All responses to this collection of information are mandatory. Comments concerning the accuracy of this burden and suggestions for reducing the burden should be directed to the FAA at: 800 Independence Ave., SW., Washington, DC 20591, Attn: Information Collection Clearance Officer, AES–200. Related Information (h) Refer to MCAI European Aviation Safety Agency (EASA) AD 2010–0230, dated November 5, 2010; Reims Aviation Industries Service Bulletin No. F406–58, REV 1, dated October 27, 2006; and Reims Aviation Industries Service Bulletin No. F406–58, REV 2, dated July 27, 2010, for related information. For service information related to this AD, contact Reims Aviation ´ Industries, Aerodrome de Reims Prunay, 51360 Prunay, France; telephone + 33 3 26 48 46 65; fax + 33 3 26 49 18 57; e-mail Jn.sirot@reims-aviation.fr. You may review copies of the referenced service information at the FAA, Small Airplane Directorate, 901 Locust, Kansas City, Missouri 64106. For information on the availability of this material at the FAA, call 816–329–4148. PO 00000 Frm 00003 Fmt 4702 Sfmt 4702 Issued in Kansas City, Missouri, on January 14, 2011. John Colomy, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 2011–1221 Filed 1–20–11; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2011–0028; Directorate Identifier 2009–NM–228–AD] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Model 737–100, –200, –200C, –300, –400, and –500 Series Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for certain Model 737–100, –200, –200C, –300, –400, and –500 series airplanes. This proposed AD would result in all airplanes having new relays with a ground fault interrupter (GFI) feature. This proposed AD would require, depending on airplane configuration, doing certain wiring changes, replacing the fuel pump power control relays for the main, center and auxiliary tanks, as applicable, with new relays having a GFI feature, performing certain bonding resistance measurements, and modifying relay module assemblies. The proposed AD also would require revising the maintenance program to incorporate Airworthiness Limitations (AWLs) 28–AWL–23 (for Model 737– 100, 737–200, and 737–200C series airplanes), and 28–AWL–22 (for Model 737–300, 737–400, and 737–500 series airplanes). This proposed AD results from fuel system reviews conducted by the manufacturer. We are proposing this AD to prevent damage to the fuel pumps caused by electrical arcing that could introduce an ignition source in the fuel tank, 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 March 7, 2011. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. SUMMARY: E:\FR\FM\21JAP1.SGM 21JAP1 Federal Register / Vol. 76, No. 14 / Friday, January 21, 2011 / Proposed Rules • Mail: U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590. • Hand Delivery: U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this proposed AD, contact: Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H–65, Seattle, Washington 98124– 2207; telephone 206–544–5000, extension 1; fax 206–766–5680; e-mail me.boecom@boeing.com; Internet https://www.myboeingfleet.com. You may review copies of the referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington. For information on the availability of this material at the FAA, call 425–227– 1221 or 425–227–1152. Examining the AD Docket You may examine the AD docket on the Internet at https:// www.regulations.gov; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (telephone 800–647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Georgios Roussos, Aerospace Engineer, Systems and Equipment Branch, ANM– 130S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 917–6482; fax (425) 917–6590. SUPPLEMENTARY INFORMATION: WReier-Aviles on DSKGBLS3C1PROD with PROPOSALS Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2011–0028; Directorate Identifier 2009–NM–228–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this VerDate Mar<15>2010 12:47 Jan 20, 2011 Jkt 223001 proposed AD because of those comments. We will post all comments we receive, without change, to https:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion The 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’’ (66 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 a 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. PO 00000 Frm 00004 Fmt 4702 Sfmt 4702 3857 We have determined that the actions identified in this 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. As part of an SFAR88 analysis, Boeing determined that the power control relays for the main tank fuel boost pumps, the center tank fuel boost pumps, and for certain airplanes, the auxiliary tank fuel boost pumps should be replaced with new relays having a ground fault interrupter (GFI) feature. The relays are located in the P6 circuit breaker panel in the flight compartment. The GFI relay feature is intended to protect the fuel boost pumps from damage caused from electrical arcing by removing electrical power from the pump if a ground fault is detected. Electrical arcing, if not prevented could introduce an ignition source in the fuel tank 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 Alert Service Bulletin 737–28A1212, Revision 1, dated August 27, 2010. Depending on airplane configuration and on whether the actions in Boeing Alert Service Bulletin 737–28A1212, dated July 23, 2009, were accomplished, Boeing Alert Service Bulletin 737–28A1212, Revision 1, dated August 27, 2010, describes procedures for the following actions, depending on airplane configurations: • Doing wiring changes, • Replacing the fuel pump power control relays for the main, center and auxiliary tanks with new relays having a GFI feature, • Doing certain bonding resistance measurements to verify certain bonding requirements are met, and • Modifying the M181, M182, M183 relay module assemblies. Boeing Alert Service Bulletin 737– 28A1212, Revision 1, dated August 27, 2010, specifies a compliance time of 60 months for replacing the power control relays. For certain airplanes, Boeing Alert Service Bulletin 737–28A1212, Revision 1, dated August 27, 2010, refers to BAE Systems Service Bulletin 65–49808–24– 01, Revision 1, dated July 19, 2010, as an additional source of guidance for doing the modification of the relay module assemblies and bond resistance measurements. In addition, we have reviewed Section 9 of Boeing 737–100/200/200C/300/400/ 500 Airworthiness Limitations (AWLs) and Certification Maintenance E:\FR\FM\21JAP1.SGM 21JAP1 3858 Federal Register / Vol. 76, No. 14 / Friday, January 21, 2011 / Proposed Rules Requirements, D6–38278–CMR, Revision May 2009 (hereafter referred to as ‘‘Document D6–38278–CMR’’). Document D6–38278–CMR describes, among other actions, new AWLs for the applicable fuel boost pumps that incorporate ground fault interrupter relays for certain Model 737–100, –200, and –200C airplanes (i.e., AWL 28– AWL–23), and for certain other Model 737–300, –400, and –500 airplanes (i.e., AWL 28–AWL–22). The AWL reference to boost pumps applies also to all pumps where the GFI has been installed by incorporating Boeing Alert Service Bulletin 737–28A1212. FAA’s Determination and Requirements of This Proposed AD Difference Between the Proposed AD and Service Information We are proposing this AD because we evaluated all relevant information and determined the unsafe condition described previously is likely to exist or develop in other products of the same type design. This proposed AD would require accomplishing the actions specified in the service information described previously, except as described under ‘‘Difference Between the Proposed AD and Service Information.’’ AWL 28–AWL–23 of Section 9 of Boeing 737–100/200/200C/300/400/500 Airworthiness Limitations (AWLs) and Certification Maintenance Requirements (CMRs), Document D6–38278–CMR, Revision May 2009, is applicable to Model 737–100, –200, and –200C airplanes, although it specifies only the Model 737–100 and –200 airplanes. Costs of Compliance We estimate that this proposed AD would affect 750 airplanes of U.S. registry. The following table provides the estimated costs for U.S. operators to comply with this proposed AD. TABLE—ESTIMATED COSTS Work hours Replacement of power control relays. Modification .................... Maintenance program revision. 4 to 9 1 ..... $85 $14,500 $14,840 to $15,265 1 ..... 750 5 ............... 1 ............... 85 85 0 0 $425 ............................... $85 ................................. 750 750 1 Depending Average labor rate per hour Number of U.S.-registered airplanes Action WReier-Aviles on DSKGBLS3C1PROD with PROPOSALS Cost per product Fleet cost $11,130,000 to $11,448,750.1 $318,750. $63,750. on airplane configuration. 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 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. VerDate Mar<15>2010 Parts 12:47 Jan 20, 2011 Jkt 223001 For the reasons discussed above, I certify this 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. You can find our regulatory evaluation and the estimated costs of compliance in the AD Docket. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, 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 Frm 00005 Fmt 4702 Comments Due Date (a) We must receive comments by March 7, 2011. Affected ADs (b) None. Applicability (c) This AD applies to The Boeing Company Model 737–100, –200, –200C, –300, –400, and –500 series airplanes, certificated in any category; as identified in Boeing Alert Service Bulletin 737–28A1212, Revision 1, dated August 27, 2010. Note 1: This AD requires revisions to certain operator maintenance documents to include new inspections. Compliance with these inspections is required by 14 CFR 91.403(c). For airplanes that have been previously modified, altered, or repaired in the areas addressed by these inspections, the operator may not be able to accomplish the inspections described in the revisions. In this situation, to comply with 14 CFR 91.403(c), the operator must request approval for an alternative method of compliance according to paragraph (m) of this AD. The request should include a description of changes to the required inspections that will ensure the continued operational safety of the airplane. Subject [Amended] 2. The FAA amends § 39.13 by adding the following new AD: PO 00000 The Boeing Company: Docket No. FAA– 2011–0028; Directorate Identifier 2009– NM–228–AD. Sfmt 4702 (d) Air Transport Association (ATA) of America Code 28: Fuel. E:\FR\FM\21JAP1.SGM 21JAP1 Federal Register / Vol. 76, No. 14 / Friday, January 21, 2011 / Proposed Rules Unsafe Condition (e) This AD results from fuel system reviews conducted by the manufacturer. The Federal Aviation Administration is issuing this AD to prevent the damage to the fuel pumps caused by electrical arcing that could introduce an ignition source in the fuel tank, which, in combination with flammable fuel vapors, could result in a fuel tank explosion and consequent loss of the airplane. Compliance (f) You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. WReier-Aviles on DSKGBLS3C1PROD with PROPOSALS Part 1: Wiring Changes, Relay Replacements, and Certain Bonding Resistance Measurements for Certain Airplanes (g) For airplanes on which Boeing Alert Service Bulletin 737–28A1212, dated July 23, 2009, has not been incorporated as of the effective date of this AD: Within 60 months after the effective date of this AD, do the applicable action required by paragraph (g)(1) or (g)(2) of this AD. (1) Airplanes without the M181, M182, and M183 supplier relay modules installed: Do the wiring changes; replace the fuel pump power control relays for the main, center, and auxiliary tanks, as applicable, with new relays having a ground fault interrupter (GFI) feature; and do certain bonding resistance measurements to verify that certain bonding requirements are met; in accordance with Part 1 of the Accomplishment Instructions of Boeing Alert Service Bulletin 737–28A1212, Revision 1, dated August 27, 2010. (2) Airplanes with the M181, M182, and M183 supplier relay modules installed: Modify the M181, M182, and M183 relay module assemblies, and do certain bonding resistance measurements to verify that certain bonding requirements are met, in accordance with Part 1 of the Accomplishment Instructions of Boeing Alert Service Bulletin 737–28A1212, Revision 1, dated August 27, 2010. Note 2: Boeing Alert Service Bulletin 737– 28A1212, Revision 1, dated August 27, 2010, refers to BAE Systems Service Bulletin 65– 49808–24–01, Revision 1, dated July 19, 2010, as an additional source of guidance for doing the modification and certain bonding resistance measurements. Part 2: Wiring Changes and Certain Bonding Measurements for Certain Airplanes (h) For airplanes on which Boeing Alert Service Bulletin 737–28A1212, dated July 23, 2009, has been incorporated as of the effective date of this AD, and on which the M181, M182, and M183 supplier relay modules have not been installed: Within 60 months after the effective date of this AD, do the wiring changes and certain bonding measurements to verify that certain bonding requirements are met, in accordance with Part 2 of the Accomplishment Instructions of Boeing Alert Service Bulletin 737–28A1212, Revision 1, dated August 27, 2010. Part 3: Certain Bonding Measurements for Certain Airplanes (i) For airplanes on which Boeing Alert Service Bulletin 737–28A1212, dated July 23, VerDate Mar<15>2010 12:47 Jan 20, 2011 Jkt 223001 2009, has been incorporated as of the effective date of this AD, and that the M181, M182, and M183 supplier relay modules are installed: Within 60 months after the effective date of this AD, do certain bonding measurements to verify that certain bonding requirements are met, in accordance with Part 3 of the Accomplishment Instructions of Boeing Alert Service Bulletin 737–28A1212, Revision 1, dated August 27, 2010. Note 3: Boeing Alert Service Bulletin 737– 28A1212, Revision 1, dated August 27, 2010, refers to BAE Systems Service Bulletin 65– 49808–24–01, Revision 1, dated July 19, 2010, as an additional source of guidance for doing the modification and certain bonding resistance measurements. Maintenance Program Revisions (j) Concurrently with accomplishing the actions required by paragraph (g), (h), or (i) of this AD, as applicable, or within 30 days after the effective date of this AD, whichever occurs later, revise the maintenance program by incorporating the applicable airworthiness limitation (AWL) specified in paragraph (j)(1) or (j)(2) of this AD. (1) For Model 737–100, –200, and –200C series airplanes: Airworthiness Limitation 28–AWL–23 of Section 9 of Boeing 737–100/ 200/200C/300/400/500 AWL and Certification Maintenance Requirements (CMRs), Document D6–38278–CMR, Revision May 2009. The initial compliance time for the actions specified in AWL 28–AWL–23 is within 1 year after accomplishing the installation required by paragraph (g), (h), or (i) of this AD, or within 1 year after the effective date of this AD, whichever occurs later. (2) For Model 737–300, –400, and –500 series airplanes: AWL 28–AWL–22 of Section 9 of Boeing 737–100/200/200C/300/400/500 Airworthiness Limitation (AWL) and Certification Maintenance Requirements (CMRs), Document D6–38278–CMR, Revision May 2009. The initial compliance time for the actions specified in AWL 28–AWL–22 is within 1 year after accomplishing the installation required by paragraph (g), (h), or (i) of this AD, or within 1 year after the effective date of this AD, whichever occurs later. No Alternative Inspections or Inspection Interval (k) After accomplishment of the action required by paragraph (g), (h), or (i) of this AD, as applicable, no alternative inspections or inspection intervals may be used, unless the inspections or intervals are approved as an alternative means of compliance in accordance with the procedures specified in paragraph (m) of this AD. Credit for Actions Accomplished in Accordance With Earlier Revisions of AWLs (l) Revising the maintenance program to incorporate AWLs 28–AWL–22 (for Model 737–300, –400, and –500 airplanes) and 28– AWL–23 (for Model 737–100, –200, and –200C airplanes) in accordance with paragraphs (g)(1) and (g)(2) of AD 2008–10– 09 R1, amendment 39–16148, terminates the requirements of paragraph (j) of this AD. PO 00000 Frm 00006 Fmt 4702 Sfmt 4702 3859 Alternative Methods of Compliance (AMOCs) (m)(1) The Manager, Seattle Aircraft Certification Office, 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: Georgios Roussos, Aerospace Engineer, Systems and Equipment Branch, ANM–130S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue, SW., Renton, Washington 98057– 3356; telephone (425) 917–6482; fax (425) 917–6590. Or, e-mail information to 9-ANMSeattle-ACO-AMOC-Requests@faa.gov. (2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/ certificate holding district office. Issued in Renton, Washington, on January 12, 2011. Jeffrey E. Duven, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2011–1226 Filed 1–20–11; 8:45 am] BILLING CODE 4910–13–P SECURITIES AND EXCHANGE COMMISSION 17 CFR Part 240 [Release No. 34–63727; File No. S7–03–11] RIN 3235–AK91 Trade Acknowledgment and Verification of Security-Based Swap Transactions Securities and Exchange Commission. ACTION: Proposed rule. AGENCY: In accordance with Section 764(a) of Title VII of the Dodd-Frank Wall Street Reform and Consumer Protection Act of 2010 (‘‘Dodd-Frank Act’’), the Securities and Exchange Commission (‘‘Commission’’) is proposing rule 15Fi–1 under the Securities Exchange Act of 1934 (‘‘Exchange Act’’), 15 U.S.C. 78a et seq., which would require security-based swap dealers and major security-based swap participants to provide trade acknowledgments and to verify those trade acknowledgments in securitybased swap transactions. DATES: Comments should be received on or before February 22, 2011. ADDRESSES: Comments may be submitted by any of the following methods: SUMMARY: Electronic Comments • Use the Commission’s Internet comment form (https://www.sec.gov/ rules/proposed.shtml); • Send an e-mail to rulecomments@sec.gov. Please include File E:\FR\FM\21JAP1.SGM 21JAP1

Agencies

[Federal Register Volume 76, Number 14 (Friday, January 21, 2011)]
[Proposed Rules]
[Pages 3856-3859]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2011-1226]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2011-0028; Directorate Identifier 2009-NM-228-AD]
RIN 2120-AA64


Airworthiness Directives; The Boeing Company Model 737-100, -200, 
-200C, -300, -400, and -500 Series Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to adopt a new airworthiness directive (AD) for 
certain Model 737-100, -200, -200C, -300, -400, and -500 series 
airplanes. This proposed AD would result in all airplanes having new 
relays with a ground fault interrupter (GFI) feature. This proposed AD 
would require, depending on airplane configuration, doing certain 
wiring changes, replacing the fuel pump power control relays for the 
main, center and auxiliary tanks, as applicable, with new relays having 
a GFI feature, performing certain bonding resistance measurements, and 
modifying relay module assemblies. The proposed AD also would require 
revising the maintenance program to incorporate Airworthiness 
Limitations (AWLs) 28-AWL-23 (for Model 737-100, 737-200, and 737-200C 
series airplanes), and 28-AWL-22 (for Model 737-300, 737-400, and 737-
500 series airplanes). This proposed AD results from fuel system 
reviews conducted by the manufacturer. We are proposing this AD to 
prevent damage to the fuel pumps caused by electrical arcing that could 
introduce an ignition source in the fuel tank, 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 March 7, 2011.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.

[[Page 3857]]

     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays.
    For service information identified in this proposed AD, contact: 
Boeing Commercial Airplanes, Attention: Data & Services Management, 
P.O. Box 3707, MC 2H-65, Seattle, Washington 98124-2207; telephone 206-
544-5000, extension 1; fax 206-766-5680; e-mail me.boecom@boeing.com; 
Internet https://www.myboeingfleet.com. You may review copies of the 
referenced service information at the FAA, Transport Airplane 
Directorate, 1601 Lind Avenue, SW., Renton, Washington. For information 
on the availability of this material at the FAA, call 425-227-1221 or 
425-227-1152.

Examining the AD Docket

    You may examine the AD docket on the Internet at https://www.regulations.gov; or in person at the Docket Management Facility 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The AD docket contains this proposed AD, the regulatory 
evaluation, any comments received, and other information. The street 
address for the Docket Office (telephone 800-647-5527) is in the 
ADDRESSES section. Comments will be available in the AD docket shortly 
after receipt.

FOR FURTHER INFORMATION CONTACT: Georgios Roussos, Aerospace Engineer, 
Systems and Equipment Branch, ANM-130S, FAA, Seattle Aircraft 
Certification Office (ACO), 1601 Lind Avenue, SW., Renton, Washington 
98057-3356; telephone (425) 917-6482; fax (425) 917-6590.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2011-0028; 
Directorate Identifier 2009-NM-228-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD because of those comments.
    We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    The 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'' 
(66 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 a 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 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.
    As part of an SFAR88 analysis, Boeing determined that the power 
control relays for the main tank fuel boost pumps, the center tank fuel 
boost pumps, and for certain airplanes, the auxiliary tank fuel boost 
pumps should be replaced with new relays having a ground fault 
interrupter (GFI) feature. The relays are located in the P6 circuit 
breaker panel in the flight compartment. The GFI relay feature is 
intended to protect the fuel boost pumps from damage caused from 
electrical arcing by removing electrical power from the pump if a 
ground fault is detected. Electrical arcing, if not prevented could 
introduce an ignition source in the fuel tank 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 Alert Service Bulletin 737-28A1212, 
Revision 1, dated August 27, 2010. Depending on airplane configuration 
and on whether the actions in Boeing Alert Service Bulletin 737-
28A1212, dated July 23, 2009, were accomplished, Boeing Alert Service 
Bulletin 737-28A1212, Revision 1, dated August 27, 2010, describes 
procedures for the following actions, depending on airplane 
configurations:
     Doing wiring changes,
     Replacing the fuel pump power control relays for the main, 
center and auxiliary tanks with new relays having a GFI feature,
     Doing certain bonding resistance measurements to verify 
certain bonding requirements are met, and
     Modifying the M181, M182, M183 relay module assemblies.
    Boeing Alert Service Bulletin 737-28A1212, Revision 1, dated August 
27, 2010, specifies a compliance time of 60 months for replacing the 
power control relays.
    For certain airplanes, Boeing Alert Service Bulletin 737-28A1212, 
Revision 1, dated August 27, 2010, refers to BAE Systems Service 
Bulletin 65-49808-24-01, Revision 1, dated July 19, 2010, as an 
additional source of guidance for doing the modification of the relay 
module assemblies and bond resistance measurements.
    In addition, we have reviewed Section 9 of Boeing 737-100/200/200C/
300/400/500 Airworthiness Limitations (AWLs) and Certification 
Maintenance

[[Page 3858]]

Requirements, D6-38278-CMR, Revision May 2009 (hereafter referred to as 
``Document D6-38278-CMR''). Document D6-38278-CMR describes, among 
other actions, new AWLs for the applicable fuel boost pumps that 
incorporate ground fault interrupter relays for certain Model 737-100, 
-200, and -200C airplanes (i.e., AWL 28-AWL-23), and for certain other 
Model 737-300, -400, and -500 airplanes (i.e., AWL 28-AWL-22). The AWL 
reference to boost pumps applies also to all pumps where the GFI has 
been installed by incorporating Boeing Alert Service Bulletin 737-
28A1212.

FAA's Determination and Requirements of This Proposed AD

    We are proposing this AD because we evaluated all relevant 
information and determined the unsafe condition described previously is 
likely to exist or develop in other products of the same type design. 
This proposed AD would require accomplishing the actions specified in 
the service information described previously, except as described under 
``Difference Between the Proposed AD and Service Information.''

Difference Between the Proposed AD and Service Information

    AWL 28-AWL-23 of Section 9 of Boeing 737-100/200/200C/300/400/500 
Airworthiness Limitations (AWLs) and Certification Maintenance 
Requirements (CMRs), Document D6-38278-CMR, Revision May 2009, is 
applicable to Model 737-100, -200, and -200C airplanes, although it 
specifies only the Model 737-100 and -200 airplanes.

Costs of Compliance

    We estimate that this proposed AD would affect 750 airplanes of 
U.S. registry. The following table provides the estimated costs for 
U.S. operators to comply with this proposed AD.

                                                                 Table--Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
                                                                                                                   Number of U.S.-
               Action                     Work hours        Average labor       Parts         Cost per product       registered          Fleet cost
                                                            rate per hour                                             airplanes
--------------------------------------------------------------------------------------------------------------------------------------------------------
Replacement of power control relays  4 to 9 \1\..........             $85         $14,500  $14,840 to $15,265 \1\             750  $11,130,000 to
                                                                                                                                    $11,448,750.\1\
Modification.......................  5...................              85               0  $425..................             750  $318,750.
Maintenance program revision.......  1...................              85               0  $85...................             750  $63,750.
--------------------------------------------------------------------------------------------------------------------------------------------------------
\1\ Depending on airplane configuration.

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 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 this 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.
    You can find our regulatory evaluation and the estimated costs of 
compliance in the AD Docket.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, 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 FAA amends Sec.  39.13 by adding the following new AD:

The Boeing Company: Docket No. FAA-2011-0028; Directorate Identifier 
2009-NM-228-AD.

Comments Due Date

    (a) We must receive comments by March 7, 2011.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to The Boeing Company Model 737-100, -200, -
200C, -300, -400, and -500 series airplanes, certificated in any 
category; as identified in Boeing Alert Service Bulletin 737-
28A1212, Revision 1, dated August 27, 2010.

    Note 1: This AD requires revisions to certain operator 
maintenance documents to include new inspections. Compliance with 
these inspections is required by 14 CFR 91.403(c). For airplanes 
that have been previously modified, altered, or repaired in the 
areas addressed by these inspections, the operator may not be able 
to accomplish the inspections described in the revisions. In this 
situation, to comply with 14 CFR 91.403(c), the operator must 
request approval for an alternative method of compliance according 
to paragraph (m) of this AD. The request should include a 
description of changes to the required inspections that will ensure 
the continued operational safety of the airplane.

Subject

    (d) Air Transport Association (ATA) of America Code 28: Fuel.

[[Page 3859]]

Unsafe Condition

    (e) This AD results from fuel system reviews conducted by the 
manufacturer. The Federal Aviation Administration is issuing this AD 
to prevent the damage to the fuel pumps caused by electrical arcing 
that could introduce an ignition source in the fuel tank, which, in 
combination with flammable fuel vapors, could result in a fuel tank 
explosion and consequent loss of the airplane.

Compliance

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

Part 1: Wiring Changes, Relay Replacements, and Certain Bonding 
Resistance Measurements for Certain Airplanes

    (g) For airplanes on which Boeing Alert Service Bulletin 737-
28A1212, dated July 23, 2009, has not been incorporated as of the 
effective date of this AD: Within 60 months after the effective date 
of this AD, do the applicable action required by paragraph (g)(1) or 
(g)(2) of this AD.
    (1) Airplanes without the M181, M182, and M183 supplier relay 
modules installed: Do the wiring changes; replace the fuel pump 
power control relays for the main, center, and auxiliary tanks, as 
applicable, with new relays having a ground fault interrupter (GFI) 
feature; and do certain bonding resistance measurements to verify 
that certain bonding requirements are met; in accordance with Part 1 
of the Accomplishment Instructions of Boeing Alert Service Bulletin 
737-28A1212, Revision 1, dated August 27, 2010.
    (2) Airplanes with the M181, M182, and M183 supplier relay 
modules installed: Modify the M181, M182, and M183 relay module 
assemblies, and do certain bonding resistance measurements to verify 
that certain bonding requirements are met, in accordance with Part 1 
of the Accomplishment Instructions of Boeing Alert Service Bulletin 
737-28A1212, Revision 1, dated August 27, 2010.

    Note 2:  Boeing Alert Service Bulletin 737-28A1212, Revision 1, 
dated August 27, 2010, refers to BAE Systems Service Bulletin 65-
49808-24-01, Revision 1, dated July 19, 2010, as an additional 
source of guidance for doing the modification and certain bonding 
resistance measurements.

Part 2: Wiring Changes and Certain Bonding Measurements for Certain 
Airplanes

    (h) For airplanes on which Boeing Alert Service Bulletin 737-
28A1212, dated July 23, 2009, has been incorporated as of the 
effective date of this AD, and on which the M181, M182, and M183 
supplier relay modules have not been installed: Within 60 months 
after the effective date of this AD, do the wiring changes and 
certain bonding measurements to verify that certain bonding 
requirements are met, in accordance with Part 2 of the 
Accomplishment Instructions of Boeing Alert Service Bulletin 737-
28A1212, Revision 1, dated August 27, 2010.

Part 3: Certain Bonding Measurements for Certain Airplanes

    (i) For airplanes on which Boeing Alert Service Bulletin 737-
28A1212, dated July 23, 2009, has been incorporated as of the 
effective date of this AD, and that the M181, M182, and M183 
supplier relay modules are installed: Within 60 months after the 
effective date of this AD, do certain bonding measurements to verify 
that certain bonding requirements are met, in accordance with Part 3 
of the Accomplishment Instructions of Boeing Alert Service Bulletin 
737-28A1212, Revision 1, dated August 27, 2010.

    Note 3:  Boeing Alert Service Bulletin 737-28A1212, Revision 1, 
dated August 27, 2010, refers to BAE Systems Service Bulletin 65-
49808-24-01, Revision 1, dated July 19, 2010, as an additional 
source of guidance for doing the modification and certain bonding 
resistance measurements.

Maintenance Program Revisions

    (j) Concurrently with accomplishing the actions required by 
paragraph (g), (h), or (i) of this AD, as applicable, or within 30 
days after the effective date of this AD, whichever occurs later, 
revise the maintenance program by incorporating the applicable 
airworthiness limitation (AWL) specified in paragraph (j)(1) or 
(j)(2) of this AD.
    (1) For Model 737-100, -200, and -200C series airplanes: 
Airworthiness Limitation 28-AWL-23 of Section 9 of Boeing 737-100/
200/200C/300/400/500 AWL and Certification Maintenance Requirements 
(CMRs), Document D6-38278-CMR, Revision May 2009. The initial 
compliance time for the actions specified in AWL 28-AWL-23 is within 
1 year after accomplishing the installation required by paragraph 
(g), (h), or (i) of this AD, or within 1 year after the effective 
date of this AD, whichever occurs later.
    (2) For Model 737-300, -400, and -500 series airplanes: AWL 28-
AWL-22 of Section 9 of Boeing 737-100/200/200C/300/400/500 
Airworthiness Limitation (AWL) and Certification Maintenance 
Requirements (CMRs), Document D6-38278-CMR, Revision May 2009. The 
initial compliance time for the actions specified in AWL 28-AWL-22 
is within 1 year after accomplishing the installation required by 
paragraph (g), (h), or (i) of this AD, or within 1 year after the 
effective date of this AD, whichever occurs later.

No Alternative Inspections or Inspection Interval

    (k) After accomplishment of the action required by paragraph 
(g), (h), or (i) of this AD, as applicable, no alternative 
inspections or inspection intervals may be used, unless the 
inspections or intervals are approved as an alternative means of 
compliance in accordance with the procedures specified in paragraph 
(m) of this AD.

Credit for Actions Accomplished in Accordance With Earlier Revisions of 
AWLs

    (l) Revising the maintenance program to incorporate AWLs 28-AWL-
22 (for Model 737-300, -400, and -500 airplanes) and 28-AWL-23 (for 
Model 737-100, -200, and -200C airplanes) in accordance with 
paragraphs (g)(1) and (g)(2) of AD 2008-10-09 R1, amendment 39-
16148, terminates the requirements of paragraph (j) of this AD.

Alternative Methods of Compliance (AMOCs)

    (m)(1) The Manager, Seattle Aircraft Certification Office, 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: 
Georgios Roussos, Aerospace Engineer, Systems and Equipment Branch, 
ANM-130S, FAA, Seattle Aircraft Certification Office (ACO), 1601 
Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 
917-6482; fax (425) 917-6590. Or, e-mail information to 9-ANM-Seattle-ACO-AMOC-Requests@faa.gov.
    (2) Before using any approved AMOC, notify your appropriate 
principal inspector, or lacking a principal inspector, the manager 
of the local flight standards district office/certificate holding 
district office.

    Issued in Renton, Washington, on January 12, 2011.
Jeffrey E. Duven,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2011-1226 Filed 1-20-11; 8:45 am]
BILLING CODE 4910-13-P
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