Airworthiness Directives; Bombardier Inc., Airplanes, 60800-60804 [2013-24077]

Download as PDF 60800 Federal Register / Vol. 78, No. 191 / Wednesday, October 2, 2013 / Proposed Rules was increased. We are issuing this AD to prevent reduced control of the airplane. (f) Compliance You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. mstockstill on DSK4VPTVN1PROD with PROPOSALS (g) Airplane Flight Manual Revision For airplanes identified in paragraphs (g)(1) and (g)(2) of this AD, except as provided by paragraph (j) of this AD: Within 10 days after the effective date of this AD, revise the Emergency Procedures of the Airbus A330 and A340 Airplane Flight Manuals (AFMs), as applicable, by incorporating Airbus A330 Temporary Revision TR293, Issue 1.0, dated December 4, 2012; or Airbus A340 Temporary Revision TR294, Issue 1.0, dated December 4, 2012; as applicable; to advise the flight crew of emergency procedures for addressing AOA sensor blockage. This can be done by inserting the Airbus A330 Temporary Revision TR293, Issue 1.0, dated December 4, 2012; or Airbus A340 Temporary Revision TR294, Issue 1.0, dated December 4, 2012; into the applicable AFM. When the information in Airbus A330 Temporary Revision TR293, Issue 1.0, dated December 4, 2012; and Airbus A340 Temporary Revision TR294, Issue 1.0, dated December 4, 2012; is included in the general revisions of the applicable AFM, the general revisions may be incorporated into the AFM, and the temporary revisions may be removed. (1) Model A330–201, –202, –203, –223, 223F, –243, –243F, –301, –302, –303, –321, –322, –323, –341, –342, and –343 airplanes, all manufacturer serial numbers, on which Airbus modification 201609 or 201610 has been embodied in production; or on which Airbus Service Bulletin A330–34–3255 has been embodied in service. (2) Model A340–211, –212, –213, –311, –312, –313, –541, and –642 airplanes, all manufacturer serial numbers, on which Airbus modification 201609 or 201610 has been embodied in production; or on which Airbus Service Bulletin A340–34–4250 or A340–34–5081, as applicable, has been embodied in service. (h) Replacement Except as provided by paragraph (j) of this AD: Within 5 months after the effective date of this AD, replace all AOA sensor conic plates having part number (P/N) F3411060200000 or P/N F3411060900000 with an applicable AOA sensor flat plate identified in paragraph (h)(1) or (h)(2) of this AD. Performing this replacement constitutes terminating action for the AFM revision required by paragraph (g) of this AD; and Airbus A330 Temporary Revision TR293, Issue 1.0, dated December 4, 2012, and Airbus A340 Temporary Revision TR294, Issue 1.0, dated December 4, 2012, to the Airbus A330 and A340 AFMs, as applicable, must be removed from the AFMs before further flight after doing the replacement. (1) Replace with a flat plate having P/N F3411007920200 or P/N F3411007920300, as applicable, in accordance with the applicable service information specified in paragraph (h)(1)(i), (h)(1)(ii), or (h)(1)(iii) of this AD. VerDate Mar<15>2010 17:27 Oct 01, 2013 Jkt 232001 (i) Airbus Mandatory Service Bulletin A330–34–3293, Revision 01, including Appendix 01, dated June 12, 2013. (ii) Airbus Mandatory Service Bulletin A340–34–4273, Revision 01, including Appendix 01, dated June 12, 2013. (iii) Airbus Mandatory Service Bulletin A340–34–5093, Revision 01, including Appendix 01, dated June 12, 2013. (2) Replace with a flat plate having P/N F3411007920000 or P/N F3411007920100, in accordance with a method approved by either the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA) or its delegated agent. (i) Modification of Installation For airplanes on which any AOA sensor conic plate has been replaced with an AOA sensor flat plate, in accordance with the applicable service information specified in paragraph (i)(1)(i), (i)(1)(ii), or (i)(1)(iii) of this AD: Within 5 months after the effective date of this AD, modify the installation of the AOA sensor flat plates so that the plates are flush with the fuselage in accordance with the applicable service information identified in paragraph (h)(1)(i), (h)(1)(ii),or (h)(1)(iii) of this AD. (i) Airbus Mandatory Service Bulletin A330–34–3293, including Appendix 01, dated January 31, 2013. (ii) Airbus Mandatory Service Bulletin A340–34–4273, including Appendix 01, dated January 30, 2013. (iii) Airbus Mandatory Service Bulletin A340–34–5093, including Appendix 01, dated January 30, 2013. (j) Exception to Paragraphs (g) and (h) of This AD For airplanes on which Airbus Modification 203285 (improved AOA flat plate protection treatment) has been embodied in production: The actions specified in paragraphs (g) and (h) of this AD are not required, provided that, since first flight, no AOA probe conic plate having P/ N F3411060200000 or P/N F3411060900000 has been installed. (k) Parts Installation Prohibition As of the effective date of this AD, no person may install, on any airplane, an AOA sensor conic plate having P/N F3411060200000 or P/N F3411060900000 or an AOA protection cover having P/N 98D34203003000. (l) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the International Branch, send it to ATTN: Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind PO 00000 Frm 00017 Fmt 4702 Sfmt 4702 Avenue SW., Renton, Washington 98057– 3356; telephone (425) 227–1138; fax (425) 227–1149. Information may be emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. 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. The AMOC approval letter must specifically reference this AD. (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. (m) Related Information (1) Refer to Mandatory Continuing Airworthiness Information EASA Airworthiness Directive 2013–0023, dated February 1, 2013, for related information, which can be found in the AD docket on the Internet at http://www.regulations.gov. (2) For service information identified in this proposed AD, contact Airbus SAS— Airworthiness Office—EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 80; email airworthiness.A330A340@airbus.com; Internet http:// www.airbus.com. You may review copies of the referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. Issued in Renton, Washington, on September 23, 2013. Jeffrey E. Duven, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2013–24058 Filed 10–1–13; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2013–0835; Directorate Identifier 2013–NM–095–AD] RIN 2120–AA64 Airworthiness Directives; Bombardier Inc., Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for certain Bombardier, Inc. Model DHC–8–102, –103, –106, –201, –202, –301, –311, and –315 airplanes. This proposed AD SUMMARY: E:\FR\FM\02OCP1.SGM 02OCP1 Federal Register / Vol. 78, No. 191 / Wednesday, October 2, 2013 / Proposed Rules mstockstill on DSK4VPTVN1PROD with PROPOSALS results from fuel system reviews conducted by the manufacturer. This proposed AD would require accomplishing modifications to the fuel system. We are proposing this AD to prevent the potential of ignition sources inside fuel tanks, which, in combination with flammable fuel vapors, could result in fuel tank explosions and consequent loss of the airplane. DATES: We must receive comments on this proposed AD by November 18, 2013. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments. • Fax: (202) 493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. • Hand Delivery: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this proposed AD, contact Bombardier, Inc., Q-Series Technical Help Desk, 123 Garratt Boulevard, Toronto, Ontario M3K 1Y5, Canada; telephone 416–375– 4000; fax 416–375–4539; email thd.qseries@aero.bombardier.com; Internet http://www.bombardier.com. You may review copies of the referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227– 1221. Examining the AD Docket You may examine the AD docket on the Internet at http:// www.regulations.gov; or in person at the Docket Operations office 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 Operations 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: Morton Lee, Propulsion Engineer, Propulsion & Services Branch, ANE– 173; FAA, New York Aircraft Certification Office, 1600 Stewart Avenue, Suite 410, Westbury, New York VerDate Mar<15>2010 17:27 Oct 01, 2013 Jkt 232001 11590; telephone 516–228–7355; fax 516–794–5531. 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–2013–0835; Directorate Identifier 2013–NM–095–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 based on those comments. We will post all comments we receive, without change, to http:// 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. PO 00000 Frm 00018 Fmt 4702 Sfmt 4702 60801 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, combination of failures, and unacceptable (failure) experience. For all three failure 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 fuel tank explosions and consequent loss of the airplane. Transport Canada Civil Aviation (TCCA), which is the aviation authority for Canada, has issued Canadian Airworthiness Directive CF–2013–07, dated March 1, 2013 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The MCAI states: Bombardier Aerospace has completed a system safety review of the aeroplane fuel system against fuel tank safety standards * * *. The identified non-compliances were then assessed * * * to determine if mandatory corrective action is required. The assessment showed that a number of modifications to the fuel system are required to mitigate unsafe conditions that could result in potential ignition sources within the fuel system. * * * * * You may obtain further information by examining the MCAI in the AD docket. Relevant Service Information Bombardier Inc. has issued the following service bulletins. The actions described in this service information are intended to correct the unsafe condition identified in the MCAI. • Bombardier Service Bulletin 8–28–35, Revision C, dated January 14, 2013. • Bombardier Service Bulletin 8–28–36, Revision C, dated October 7, 2009. • Bombardier Service Bulletin 8–28–39, Revision B, dated August 19, 2009. • Bombardier Service Bulletin 8–28–41, Revision B, dated August 8, 2012. • Bombardier Service Bulletin 8–28–42, Revision A, dated October 1, 2008. • Bombardier Service Bulletin 8–28–43, Revision A, dated June 25, 2009. • Bombardier Service Bulletin 8–28–44, Revision B, dated July 25, 2009. • Bombardier Service Bulletin 8–28–47, dated May 2, 2008. E:\FR\FM\02OCP1.SGM 02OCP1 60802 Federal Register / Vol. 78, No. 191 / Wednesday, October 2, 2013 / Proposed Rules • Bombardier Service Bulletin 8–28–48, Revision A, dated February 27, 2012. • Bombardier Service Bulletin 8–28–49, Revision A, dated July 23, 2012. • Bombardier Service Bulletin 8–28–52, dated November 3, 2009. • Bombardier Service Bulletin 8–28–53, dated November 3, 2008. • Bombardier Service Bulletin 8–28–55, dated July 23, 2012. • Bombardier Service Bulletin 8–28–56, dated July 23, 2012. • Bombardier Service Bulletin 8–28–58, dated July 25, 2011. • Bombardier Service Bulletin 8–57–44, Revision D, dated October 8, 2008. FAA’s Determination and Requirements of This Proposed AD This product has been approved by the aviation authority of another country, and is approved for operation in the United States. Pursuant to our bilateral agreement with the State of Design Authority, we have been notified of the unsafe condition described in the MCAI and service information referenced above. We are proposing this AD because we evaluated all pertinent information and determined an unsafe condition exists and is likely to exist or develop on other products of the same type design. Costs of Compliance We estimate that this proposed AD affects 94 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: ESTIMATED COSTS Action Labor cost Parts cost Cost per product Cost on U.S. operators Modifications .............................. 519 work-hours × $85 per hour = $44,115 ................................. $58,924 $103,039 $9,685,666 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. 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. 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. mstockstill on DSK4VPTVN1PROD with PROPOSALS Regulatory Findings § 39.13 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); 3. Will not affect intrastate aviation in Alaska; and 4. Will not have a significant economic impact, positive or negative, ■ VerDate Mar<15>2010 17:27 Oct 01, 2013 Jkt 232001 [Amended] 2. The FAA amends § 39.13 by adding the following new AD: Bombardier, Inc.: Docket No. FAA–2013– 0835; Directorate Identifier 2013–NM– 095–AD. (a) Comments Due Date We must receive comments by November 18, 2013. (b) Affected ADs None. (c) Applicability This AD applies to Bombardier, Inc. Model DHC–8–102, –103, –106, –201, –202, –301, –311, and –315 airplanes; certificated in any category; serial numbers (S/Ns) 002 through 672. (d) Subject Air Transport Association (ATA) of America Code 28, Fuel. PO 00000 Frm 00019 Fmt 4702 Sfmt 4702 (e) Reason This AD was prompted by results from fuel system reviews conducted by the manufacturer. We are issuing this AD to prevent the potential of ignition sources inside fuel tanks, which, in combination with flammable fuel vapors, could result in fuel tank explosions and consequent loss of the airplane. (f) Compliance You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. (g) Modifications—Part I Within 6,000 flight hours or 36 months, whichever occurs first, after the effective date of this AD, do the modifications specified in paragraphs (g)(1) through (g)(14) of this AD, as applicable. (1) For airplanes having S/Ns 003 through 624 inclusive: Accomplish Modsum 8Q101512, ‘‘Fuel System—Fuel Tank Mechanical Design, SFAR 88 Compliance (Retrofit),’’ Revision G, in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 8–57–44, Revision D, dated October 8, 2008. (2) For airplanes having S/Ns 003 through 629 inclusive on which a long range fuel system has been installed as specified in Change Request (CR) 828CH00044, CR828SO08061, Special Order Option (SOO) 8061, CR828CH00027, or CF828SO00006: Accomplish Bombardier Modsum 8Q902091, ‘‘Fuel System—Fuel Tank Mech. Design, SFAR 88 Compl.—Extended Range Tank Option (Retrofit),’’ Revision C, in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 8–28–39, Revision B, dated August 19, 2009. (3) For airplanes having S/Ns 003 through 624 inclusive on which SOO 8155, 849SO08155, SOO 8098, SOO 8099, or SOO 6082; or Supplemental Type Certificate SA85–1; or Limited Supplemental Type Certificate W–LSA98–005/D has been incorporated: Accomplish Bombardier Modsum 8Q902144, ‘‘Fuel System—Fuel Tank Mechanical Design, SFAR 88 Compliance—APU Option (Retrofit),’’ E:\FR\FM\02OCP1.SGM 02OCP1 mstockstill on DSK4VPTVN1PROD with PROPOSALS Federal Register / Vol. 78, No. 191 / Wednesday, October 2, 2013 / Proposed Rules Revision E, in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 8–28–44, Revision B, dated July 25, 2009. (4) For airplanes having S/Ns 003 through 624 inclusive: Accomplish Bombardier Modsum 8Q101865, ‘‘Fuel System—Fuel Tank Mechanical Design, SFAR 88 Compliance (Retrofit),’’ Revision B, in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 8–28–47, dated May 2, 2008. (5) For Models DHC–8–102, –103, and –106 having S/Ns 002 through 014 inclusive: Accomplish Bombardier Modsum 8Q101916, ‘‘Fuel System—Fuel Tank Secondary Pressure Relief Valve Rework SFAR 88 Compliance (Retrofit),’’ Revision A, in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 8–28–58, dated July 25, 2011. (6) For airplanes having S/Ns 002 through 629 inclusive on which a long range fuel system has been installed as specified in CR828CH00044, CR828SO08061, SOO 8061, CR828CH00027, or CR828SO00006, including airplanes on which metric refuel/ defuel indicators were installed as specified in CR828CH00029: Accomplish Bombardier Modsum 8Q902122, ‘‘Production/Retrofit— Fuel System—Long Range Wiring Installation—SFAR 88 Compliance,’’ Revision F, in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 8–28–41, Revision B, dated August 8, 2012. (7) For airplanes having S/Ns 002 through 619 inclusive with imperial refuel/defuel indicators, excluding airplanes on which a long range fuel system has been installed as specified in CF828CH00044, CR828SO08061, SOO 0861, CF828CH00027, or CR828SO00006: Accomplish Bombardier Modsum 8Q101511, ‘‘Production/Retrofit— Fuel System—Fuel Tank Wiring Installation—SFAR88 Compliance,’’ Revision C, in accordance with the Accomplishment Instruction of Bombardier Service Bulletin 8– 28–35, Revision C, dated January 14, 2013. (8) For airplanes having S/Ns 002 through 619 inclusive on which metric refuel/defuel indicators have been installed as specified in CR828CH00020, excluding airplanes on which a long range fuel system has been installed as specified in CR828CH00044, CF828SO08061, SOO 8061, CR828CH00027, or CR828SO00006: Accomplish Bombardier Modsum 8Q901117, ‘‘Production/Retrofit— Fuel System—Metric Indication—Fuel Tank Wiring Installation—SFAR 88,’’ Revision C, in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 8–28–43, Revision A, dated June 25, 2009. (9) For airplanes having S/Ns 003 through 619 inclusive, excluding airplanes that have incorporated Modsum 8Q101652 in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 8–28–36, Revision A, dated November 17, 2006; or Revision B, dated February 12, 2008: Accomplish Bombardier Modsum 8Q101652, ‘‘Electrical—Fuel Quantity Indication Wire Routing Segregation and Identification,’’ Revision F, in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 8–28–36, Revision C, dated VerDate Mar<15>2010 17:27 Oct 01, 2013 Jkt 232001 October 7, 2009. In addition, for Models DHC–8–102, –103, –106, –201, and –202 airplanes on which an active noise and vibration suppression (ANVS) system has been installed, and on which Modsum 8Q101652 has been incorporated in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 8–28–36, Revision A, dated November 17, 2006; or Revision B, dated February 12, 2008: Do the actions specified in paragraph (h)(1) of this AD. (10) For airplanes having S/Ns 003 through 672 inclusive on which Modsum 8Q101513 or 8Q101652 has been installed as specified in CR828CH00044, CR828SO08061, SOO 8061, CR828CH00027, or CR828CO00006, excluding airplanes having a long range fuel system: Accomplish Bombardier Modsum 8Q101907, ‘‘Fuel System—Fuel Qty Ind., Wire Routing Segregation, Installation of Top Hat Support—SFAR88 (Standard Aircraft),’’ Revision B, in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 8–28–48, Revision A, dated February 27, 2012. (11) For airplanes having S/Ns 003 through 619, excluding airplanes on which a long range fuel system has been installed as specified in CR828CH00044, CR828SO08061, SOO 8061, CR828CH00027, or CR828SO00006, and excluding airplanes on which Modsum 8Q101652 was incorporated in accordance with the Accomplishment Instructions in Bombardier Service Bulletin 8–28–36, Revision A, dated November 17, 2006; Revision B, dated February 12, 2008, or Revision C, dated October 7, 2009: Accomplish Modsum 8Q101908, ‘‘Fuel System—Fuel Qty Ind., Wire Routing Segregation, Installation of Dual Spacers— SFAR88 (Standard A/C),’’ Revision B, in accordance with the Accomplishment Instruction of Bombardier Service Bulletin 8– 28–55, dated July 23, 2012. In addition, for airplanes on which Modsum 8Q101652 was incorporated in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 8–28–36, dated August 9, 2006; Revision A, dated November 17, 2006; Revision B, dated February 12, 2008; or Revision C, dated October 7, 2009: Do the actions in paragraph (i)(1) of this AD. (12) For airplanes having S/Ns 002 through 629 inclusive, on which a long range fuel system has been installed as specified in CR828CH00044, CR828SO08061, SOO 8061, CF828CH00027, or CR828SO00006, excluding airplanes on which Modsum 8Q902064 has been incorporated in accordance with the Accomplishment Instructions contained in Bombardier Service Bulletin 8–28–42: Accomplish Bombardier Modsum 8Q902064, ‘‘Electrical—Long Range Fuel Quantity Indication Wire Routing Segregation and Identification—SFAR 88,’’ Revision G, in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 8–28–42, Revision A, dated October 1, 2008. (13) For airplanes having S/Ns 003 through 672 inclusive on which a long range fuel system has been installed as specified in CR828CH00044, CR828SO08061, SOO 8061, CR828CH00027, or CR828SO00006; and with Modsum 8Q902064 and either Modsum PO 00000 Frm 00020 Fmt 4702 Sfmt 4702 60803 8Q101513 or Modsum 8Q101652: Accomplish Bombardier Modsum 8Q902382, ‘‘Fuel System—Fuel Qty Ind., Wire Routing Segregation, Installation of Top Hat Support—SFAR88 (Long Range Aircraft),’’ Revision B, in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 8–28–49, Revision A, dated July 23, 2012. (14) For airplanes having S/Ns 003 through 629 inclusive on which a long range fuel system has been installed as specified in CR828CH00044, CR828SO08061, SOO 8061, CR828CH00027, or CR828SO00006, excluding airplanes on which Modsum 8Q902064 has been incorporated in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 8–28–42, dated December 21, 2008 or Revision A, dated October 1, 2008: Accomplish Bombardier Modsum 8Q902383, ‘‘Fuel System—Fuel Qty Ind., Wire Routing Segregation, Installation of Dual Spacers— SFAR88 (Long Range A/C),’’ Revision B, including installing dual spacers inside the center fuselage at certain locations, in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 8–28–56, dated July 23, 2012. (h) Inspections, Modifications, and Corrective Actions—Part II For the airplanes identified in paragraphs (h)(1), (h)(2), or (h)(3) of this AD: Within 12,000 flight hours or 72 months, whichever occurs first, after the effective date of this AD, do the actions specified in paragraphs (h)(1), (h)(2), and (h)(3) of this AD, as applicable. (1) For Model DHC–8–102, –103, –106, –201, and –202 airplanes having S/Ns 003 through 619 inclusive, on which an ANVS system has been installed and on which Modsum 8Q101652 has been incorporated in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 8–28–36, dated August 9, 2006; or Revision A, dated November 17, 2006; or Revision B, dated February 12, 2008: Accomplish Bombardier Modsum 8Q101652, ‘‘Electrical—Fuel Quantity Indication Wire Routing Segregation and Identification,’’ Revision F, in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 8–28–36, Revision C, dated October 7, 2009. (2) For Model DHC–8–102, –103, –106, –201, and –202 airplanes having S/Ns 002 through 629 inclusive, on which an ANVS system has been installed and on which Modsum 8Q902064 has been incorporated in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 8–28–42, dated December 21, 2008: Accomplish Bombardier Modsum 8Q902064, ‘‘Electrical—Long Range Fuel Quantity Indication Wire Routing Segregation and Identification—SFAR 88,’’ Revision G, in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 8–28–42, Revision A, dated October 1, 2008. (3) For Model DHC–8–102, –103, –106, –201, and –202 airplanes having S/Ns 620 through 666 inclusive, on which an ANVS system has been installed: Do a one-time visual inspection to determine whether the E:\FR\FM\02OCP1.SGM 02OCP1 60804 Federal Register / Vol. 78, No. 191 / Wednesday, October 2, 2013 / Proposed Rules fuel quantity indicating system (FQIS) wiring harness is routed correctly and relocate if necessary, in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 8–28–52, dated November 3, 2009. mstockstill on DSK4VPTVN1PROD with PROPOSALS (i) Wire Routing Segregation and Installation of Dual Spacers—Part III Within 18,000 flight hours or 108 months, whichever occurs first, after the effective date of this AD, do the modification specified in paragraphs (i)(1) and (i)(2) of this AD, as applicable. (1) For airplanes having S/Ns 003 through 672 inclusive, on which Modsum 8Q101513 has been incorporated or on which Modsum 8Q101652 has been incorporated in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 8–28–36, dated August 9, 2006; Revision A, dated November 17, 2006; Revision B, dated February 12, 2008; or Revision C, dated October 7, 2009; excluding airplanes on which a long-range fuel system has been installed as specified in CF828CH00044, CR828SO08061, SOO 8061, CR828CH00027, or CR828SO00006: Accomplish Bombardier Modsum 8Q101908, ‘‘Fuel System—Fuel Qty Ind., Wire Routing Segregation, Installation of Dual Spacers—SFAR88 (Standard A/C),’’ Revision B, including installing dual spacers inside certain center fuselage locations, in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 8–28–55, dated July 23, 2012. (2) For airplanes having S/Ns 003 through 672 inclusive on which a long-range fuel system has been installed as specified in CF828CH00044, CR828SO08061, SOO 8061, CR828CH00027, or CR828SO00006, and on which Modsum 8Q902064 has been incorporated, or on which Modsum 8Q902064 has been incorporated in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 8–28–42, dated December 21, 2008; or Revision A, dated October 1, 2008: Accomplish Bombardier Modsum 8Q902383, ‘‘Fuel System—Fuel Qty Ind., Wire routing Segregation, Installation of Dual Spacers— SFAR88 (Long Range A/C),’’ Revision B, including installing dual spacers inside certain center fuselage locations, in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 8–28–56, dated July 23, 2012. (j) Credit for Previous Actions (1) This paragraph provides credit for actions required by paragraph (g)(2) of this AD, if those actions were performed before the effective date of this AD using Bombardier Service Bulletin 8–28–39, Revision A, March 15, 2007. (2) This paragraph provides credit for actions required by paragraph (g)(3) of this AD, if those actions were performed before the effective date of this AD using Bombardier Service Bulletin 8–28–44, dated August 9, 2006; or Revision A, dated November 15, 2006. (3) This paragraph provides credit for actions required by paragraph (g)(6) of this AD, if those actions were performed before the effective date of this AD using VerDate Mar<15>2010 17:27 Oct 01, 2013 Jkt 232001 Bombardier Service Bulletin 8–28–41, Revision A, dated April 11, 2007. (4) This paragraph provides credit for actions required by paragraph (g)(8) of this AD, if those actions were performed before the effective date of this AD using Bombardier Service Bulletin 8–28–43, dated August 10, 2006. (5) This paragraph provides credit for actions required by paragraph (g)(10) of this AD, if those actions were performed before the effective date of this AD using Bombardier Service Bulletin 8–28–48, dated October 1, 2010. (6) This paragraph provides credit for actions required by paragraph (g)(13) of this AD, if those actions were performed before the effective date of this AD using Bombardier Service Bulletin 8–28–49, dated October 1, 2010. (7) This paragraph provides credit for actions required by paragraph (h)(3) of this AD, if those actions were performed before the effective date of this AD using Bombardier Service Bulletin 8–28–53, dated November 3, 2008. (k) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, ANE–170, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the ACO, send it to ATTN: Program Manager, Continuing Operational Safety, FAA, New York ACO, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516–228–7300; fax 516–794–5531. 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. The AMOC approval letter must specifically reference this AD. (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. (l) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) Canadian Airworthiness Directive CF–2013–07, dated March 1, 2013, for related information, which can be found in the AD docket on the internet at http://www.regulations.gov. (2) For service information identified in this AD, contact Bombardier, Inc., Q-Series Technical Help Desk, 123 Garratt Boulevard, Toronto, Ontario M3K 1Y5, Canada; telephone 416–375–4000; fax 416–375–4539; email thd.qseries@aero.bombardier.com; Internet http://www.bombardier.com. You may review copies of this service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For PO 00000 Frm 00021 Fmt 4702 Sfmt 4702 information on the availability of this material at the FAA, call 425–227–1221. Issued in Renton, Washington, on September 19, 2013. Ross Landes, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2013–24077 Filed 10–1–13; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2013–0836; Directorate Identifier 2013–NM–126–AD] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to supersede airworthiness directive (AD) 2005–07– 12 that applies to certain The Boeing Company Model 737–100, –200, –200C, –300, –400, and –500 series airplanes. AD 2005–07–12 requires detailed and eddy current inspections to detect cracking of the frame web around the cutout for the doorstop intercostal strap at the aft side of the station (STA) 291.5 frame at stringer 16R, and corrective action if necessary. Since we issued AD 2005–07–12, we received reports of new findings of cracking at various locations of the STA 277 to STA 291.5 frames and intercostals, including webs, chords, clips, and shear ties, between stringers 7R and 17R. This proposed AD would add new inspections for cracking at the forward galley door cutout, and corrective actions if necessary. This proposed AD would also reduce a certain inspection threshold required by AD 2005–07–12. We are proposing this AD to detect and correct fatigue cracking of the aft frame and frame support structure of the forward galley door, which could result in a severed fuselage frame web, rapid decompression of the airplane, and possible loss of the forward galley door. DATES: We must receive comments on this proposed AD by November 18, 2013. SUMMARY: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods: ADDRESSES: E:\FR\FM\02OCP1.SGM 02OCP1

Agencies

[Federal Register Volume 78, Number 191 (Wednesday, October 2, 2013)]
[Proposed Rules]
[Pages 60800-60804]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-24077]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2013-0835; Directorate Identifier 2013-NM-095-AD]
RIN 2120-AA64


Airworthiness Directives; Bombardier Inc., 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 Bombardier, Inc. Model DHC-8-102, -103, -106, -201, -202, -301, 
-311, and -315 airplanes. This proposed AD

[[Page 60801]]

results from fuel system reviews conducted by the manufacturer. This 
proposed AD would require accomplishing modifications to the fuel 
system. We are proposing this AD to prevent the potential of ignition 
sources inside fuel tanks, which, in combination with flammable fuel 
vapors, could result in fuel tank explosions and consequent loss of the 
airplane.

DATES: We must receive comments on this proposed AD by November 18, 
2013.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: (202) 493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday 
through Friday, except Federal holidays.
    For service information identified in this proposed AD, contact 
Bombardier, Inc., Q-Series Technical Help Desk, 123 Garratt Boulevard, 
Toronto, Ontario M3K 1Y5, Canada; telephone 416-375-4000; fax 416-375-
4539; email thd.qseries@aero.bombardier.com; Internet http://www.bombardier.com. You may review copies of the referenced service 
information at the FAA, Transport Airplane Directorate, 1601 Lind 
Avenue SW., Renton, WA. For information on the availability of this 
material at the FAA, call 425-227-1221.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov; or in person at the Docket Operations office 
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 Operations 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: Morton Lee, Propulsion Engineer, 
Propulsion & Services Branch, ANE-173; FAA, New York Aircraft 
Certification Office, 1600 Stewart Avenue, Suite 410, Westbury, New 
York 11590; telephone 516-228-7355; fax 516-794-5531.

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-2013-0835; 
Directorate Identifier 2013-NM-095-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 based on those comments.
    We will post all comments we receive, without change, to http://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, combination of 
failures, and unacceptable (failure) experience. For all three failure 
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 fuel tank explosions and consequent loss of the airplane.
    Transport Canada Civil Aviation (TCCA), which is the aviation 
authority for Canada, has issued Canadian Airworthiness Directive CF-
2013-07, dated March 1, 2013 (referred to after this as the Mandatory 
Continuing Airworthiness Information, or ``the MCAI''), to correct an 
unsafe condition for the specified products. The MCAI states:

    Bombardier Aerospace has completed a system safety review of the 
aeroplane fuel system against fuel tank safety standards * * *. The 
identified non-compliances were then assessed * * * to determine if 
mandatory corrective action is required.
    The assessment showed that a number of modifications to the fuel 
system are required to mitigate unsafe conditions that could result 
in potential ignition sources within the fuel system.
* * * * *
You may obtain further information by examining the MCAI in the AD 
docket.

Relevant Service Information

    Bombardier Inc. has issued the following service bulletins. The 
actions described in this service information are intended to correct 
the unsafe condition identified in the MCAI.

     Bombardier Service Bulletin 8-28-35, Revision C, dated 
January 14, 2013.
     Bombardier Service Bulletin 8-28-36, Revision C, dated 
October 7, 2009.
     Bombardier Service Bulletin 8-28-39, Revision B, dated 
August 19, 2009.
     Bombardier Service Bulletin 8-28-41, Revision B, dated 
August 8, 2012.
     Bombardier Service Bulletin 8-28-42, Revision A, dated 
October 1, 2008.
     Bombardier Service Bulletin 8-28-43, Revision A, dated 
June 25, 2009.
     Bombardier Service Bulletin 8-28-44, Revision B, dated 
July 25, 2009.
     Bombardier Service Bulletin 8-28-47, dated May 2, 2008.

[[Page 60802]]

     Bombardier Service Bulletin 8-28-48, Revision A, dated 
February 27, 2012.
     Bombardier Service Bulletin 8-28-49, Revision A, dated 
July 23, 2012.
     Bombardier Service Bulletin 8-28-52, dated November 3, 
2009.
     Bombardier Service Bulletin 8-28-53, dated November 3, 
2008.
     Bombardier Service Bulletin 8-28-55, dated July 23, 
2012.
     Bombardier Service Bulletin 8-28-56, dated July 23, 
2012.
     Bombardier Service Bulletin 8-28-58, dated July 25, 
2011.
     Bombardier Service Bulletin 8-57-44, Revision D, dated 
October 8, 2008.

FAA's Determination and Requirements of This Proposed AD

    This product has been approved by the aviation authority of another 
country, and is approved for operation in the United States. Pursuant 
to our bilateral agreement with the State of Design Authority, we have 
been notified of the unsafe condition described in the MCAI and service 
information referenced above. We are proposing this AD because we 
evaluated all pertinent information and determined an unsafe condition 
exists and is likely to exist or develop on other products of the same 
type design.

Costs of Compliance

    We estimate that this proposed AD affects 94 airplanes of U.S. 
registry. We estimate the following costs to comply with this proposed 
AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                    Cost per       Cost on U.S.
               Action                          Labor cost           Parts cost      product         operators
----------------------------------------------------------------------------------------------------------------
Modifications.......................  519 work-hours x $85 per        $58,924         $103,039       $9,685,666
                                       hour = $44,115.
----------------------------------------------------------------------------------------------------------------

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);
    3. Will not affect intrastate aviation in Alaska; and
    4. 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.

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

0
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]

0
2. The FAA amends Sec.  39.13 by adding the following new AD:

Bombardier, Inc.: Docket No. FAA-2013-0835; Directorate Identifier 
2013-NM-095-AD.

(a) Comments Due Date

    We must receive comments by November 18, 2013.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Bombardier, Inc. Model DHC-8-102, -103, -106, 
-201, -202, -301, -311, and -315 airplanes; certificated in any 
category; serial numbers (S/Ns) 002 through 672.

(d) Subject

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

(e) Reason

    This AD was prompted by results from fuel system reviews 
conducted by the manufacturer. We are issuing this AD to prevent the 
potential of ignition sources inside fuel tanks, which, in 
combination with flammable fuel vapors, could result in fuel tank 
explosions and consequent loss of the airplane.

(f) Compliance

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

(g) Modifications--Part I

    Within 6,000 flight hours or 36 months, whichever occurs first, 
after the effective date of this AD, do the modifications specified 
in paragraphs (g)(1) through (g)(14) of this AD, as applicable.
    (1) For airplanes having S/Ns 003 through 624 inclusive: 
Accomplish Modsum 8Q101512, ``Fuel System--Fuel Tank Mechanical 
Design, SFAR 88 Compliance (Retrofit),'' Revision G, in accordance 
with the Accomplishment Instructions of Bombardier Service Bulletin 
8-57-44, Revision D, dated October 8, 2008.
    (2) For airplanes having S/Ns 003 through 629 inclusive on which 
a long range fuel system has been installed as specified in Change 
Request (CR) 828CH00044, CR828SO08061, Special Order Option (SOO) 
8061, CR828CH00027, or CF828SO00006: Accomplish Bombardier Modsum 
8Q902091, ``Fuel System--Fuel Tank Mech. Design, SFAR 88 Compl.--
Extended Range Tank Option (Retrofit),'' Revision C, in accordance 
with the Accomplishment Instructions of Bombardier Service Bulletin 
8-28-39, Revision B, dated August 19, 2009.
    (3) For airplanes having S/Ns 003 through 624 inclusive on which 
SOO 8155, 849SO08155, SOO 8098, SOO 8099, or SOO 6082; or 
Supplemental Type Certificate SA85-1; or Limited Supplemental Type 
Certificate W-LSA98-005/D has been incorporated: Accomplish 
Bombardier Modsum 8Q902144, ``Fuel System--Fuel Tank Mechanical 
Design, SFAR 88 Compliance--APU Option (Retrofit),''

[[Page 60803]]

Revision E, in accordance with the Accomplishment Instructions of 
Bombardier Service Bulletin 8-28-44, Revision B, dated July 25, 
2009.
    (4) For airplanes having S/Ns 003 through 624 inclusive: 
Accomplish Bombardier Modsum 8Q101865, ``Fuel System--Fuel Tank 
Mechanical Design, SFAR 88 Compliance (Retrofit),'' Revision B, in 
accordance with the Accomplishment Instructions of Bombardier 
Service Bulletin 8-28-47, dated May 2, 2008.
    (5) For Models DHC-8-102, -103, and -106 having S/Ns 002 through 
014 inclusive: Accomplish Bombardier Modsum 8Q101916, ``Fuel 
System--Fuel Tank Secondary Pressure Relief Valve Rework SFAR 88 
Compliance (Retrofit),'' Revision A, in accordance with the 
Accomplishment Instructions of Bombardier Service Bulletin 8-28-58, 
dated July 25, 2011.
    (6) For airplanes having S/Ns 002 through 629 inclusive on which 
a long range fuel system has been installed as specified in 
CR828CH00044, CR828SO08061, SOO 8061, CR828CH00027, or CR828SO00006, 
including airplanes on which metric refuel/defuel indicators were 
installed as specified in CR828CH00029: Accomplish Bombardier Modsum 
8Q902122, ``Production/Retrofit--Fuel System--Long Range Wiring 
Installation--SFAR 88 Compliance,'' Revision F, in accordance with 
the Accomplishment Instructions of Bombardier Service Bulletin 8-28-
41, Revision B, dated August 8, 2012.
    (7) For airplanes having S/Ns 002 through 619 inclusive with 
imperial refuel/defuel indicators, excluding airplanes on which a 
long range fuel system has been installed as specified in 
CF828CH00044, CR828SO08061, SOO 0861, CF828CH00027, or CR828SO00006: 
Accomplish Bombardier Modsum 8Q101511, ``Production/Retrofit--Fuel 
System--Fuel Tank Wiring Installation--SFAR88 Compliance,'' Revision 
C, in accordance with the Accomplishment Instruction of Bombardier 
Service Bulletin 8-28-35, Revision C, dated January 14, 2013.
    (8) For airplanes having S/Ns 002 through 619 inclusive on which 
metric refuel/defuel indicators have been installed as specified in 
CR828CH00020, excluding airplanes on which a long range fuel system 
has been installed as specified in CR828CH00044, CF828SO08061, SOO 
8061, CR828CH00027, or CR828SO00006: Accomplish Bombardier Modsum 
8Q901117, ``Production/Retrofit--Fuel System--Metric Indication--
Fuel Tank Wiring Installation--SFAR 88,'' Revision C, in accordance 
with the Accomplishment Instructions of Bombardier Service Bulletin 
8-28-43, Revision A, dated June 25, 2009.
    (9) For airplanes having S/Ns 003 through 619 inclusive, 
excluding airplanes that have incorporated Modsum 8Q101652 in 
accordance with the Accomplishment Instructions of Bombardier 
Service Bulletin 8-28-36, Revision A, dated November 17, 2006; or 
Revision B, dated February 12, 2008: Accomplish Bombardier Modsum 
8Q101652, ``Electrical--Fuel Quantity Indication Wire Routing 
Segregation and Identification,'' Revision F, in accordance with the 
Accomplishment Instructions of Bombardier Service Bulletin 8-28-36, 
Revision C, dated October 7, 2009. In addition, for Models DHC-8-
102, -103, -106, -201, and -202 airplanes on which an active noise 
and vibration suppression (ANVS) system has been installed, and on 
which Modsum 8Q101652 has been incorporated in accordance with the 
Accomplishment Instructions of Bombardier Service Bulletin 8-28-36, 
Revision A, dated November 17, 2006; or Revision B, dated February 
12, 2008: Do the actions specified in paragraph (h)(1) of this AD.
    (10) For airplanes having S/Ns 003 through 672 inclusive on 
which Modsum 8Q101513 or 8Q101652 has been installed as specified in 
CR828CH00044, CR828SO08061, SOO 8061, CR828CH00027, or CR828CO00006, 
excluding airplanes having a long range fuel system: Accomplish 
Bombardier Modsum 8Q101907, ``Fuel System--Fuel Qty Ind., Wire 
Routing Segregation, Installation of Top Hat Support--SFAR88 
(Standard Aircraft),'' Revision B, in accordance with the 
Accomplishment Instructions of Bombardier Service Bulletin 8-28-48, 
Revision A, dated February 27, 2012.
    (11) For airplanes having S/Ns 003 through 619, excluding 
airplanes on which a long range fuel system has been installed as 
specified in CR828CH00044, CR828SO08061, SOO 8061, CR828CH00027, or 
CR828SO00006, and excluding airplanes on which Modsum 8Q101652 was 
incorporated in accordance with the Accomplishment Instructions in 
Bombardier Service Bulletin 8-28-36, Revision A, dated November 17, 
2006; Revision B, dated February 12, 2008, or Revision C, dated 
October 7, 2009: Accomplish Modsum 8Q101908, ``Fuel System--Fuel Qty 
Ind., Wire Routing Segregation, Installation of Dual Spacers--SFAR88 
(Standard A/C),'' Revision B, in accordance with the Accomplishment 
Instruction of Bombardier Service Bulletin 8-28-55, dated July 23, 
2012. In addition, for airplanes on which Modsum 8Q101652 was 
incorporated in accordance with the Accomplishment Instructions of 
Bombardier Service Bulletin 8-28-36, dated August 9, 2006; Revision 
A, dated November 17, 2006; Revision B, dated February 12, 2008; or 
Revision C, dated October 7, 2009: Do the actions in paragraph 
(i)(1) of this AD.
    (12) For airplanes having S/Ns 002 through 629 inclusive, on 
which a long range fuel system has been installed as specified in 
CR828CH00044, CR828SO08061, SOO 8061, CF828CH00027, or CR828SO00006, 
excluding airplanes on which Modsum 8Q902064 has been incorporated 
in accordance with the Accomplishment Instructions contained in 
Bombardier Service Bulletin 8-28-42: Accomplish Bombardier Modsum 
8Q902064, ``Electrical--Long Range Fuel Quantity Indication Wire 
Routing Segregation and Identification--SFAR 88,'' Revision G, in 
accordance with the Accomplishment Instructions of Bombardier 
Service Bulletin 8-28-42, Revision A, dated October 1, 2008.
    (13) For airplanes having S/Ns 003 through 672 inclusive on 
which a long range fuel system has been installed as specified in 
CR828CH00044, CR828SO08061, SOO 8061, CR828CH00027, or CR828SO00006; 
and with Modsum 8Q902064 and either Modsum 8Q101513 or Modsum 
8Q101652: Accomplish Bombardier Modsum 8Q902382, ``Fuel System--Fuel 
Qty Ind., Wire Routing Segregation, Installation of Top Hat 
Support--SFAR88 (Long Range Aircraft),'' Revision B, in accordance 
with the Accomplishment Instructions of Bombardier Service Bulletin 
8-28-49, Revision A, dated July 23, 2012.
    (14) For airplanes having S/Ns 003 through 629 inclusive on 
which a long range fuel system has been installed as specified in 
CR828CH00044, CR828SO08061, SOO 8061, CR828CH00027, or CR828SO00006, 
excluding airplanes on which Modsum 8Q902064 has been incorporated 
in accordance with the Accomplishment Instructions of Bombardier 
Service Bulletin 8-28-42, dated December 21, 2008 or Revision A, 
dated October 1, 2008: Accomplish Bombardier Modsum 8Q902383, ``Fuel 
System--Fuel Qty Ind., Wire Routing Segregation, Installation of 
Dual Spacers--SFAR88 (Long Range A/C),'' Revision B, including 
installing dual spacers inside the center fuselage at certain 
locations, in accordance with the Accomplishment Instructions of 
Bombardier Service Bulletin 8-28-56, dated July 23, 2012.

(h) Inspections, Modifications, and Corrective Actions--Part II

    For the airplanes identified in paragraphs (h)(1), (h)(2), or 
(h)(3) of this AD: Within 12,000 flight hours or 72 months, 
whichever occurs first, after the effective date of this AD, do the 
actions specified in paragraphs (h)(1), (h)(2), and (h)(3) of this 
AD, as applicable.
    (1) For Model DHC-8-102, -103, -106, -201, and -202 airplanes 
having S/Ns 003 through 619 inclusive, on which an ANVS system has 
been installed and on which Modsum 8Q101652 has been incorporated in 
accordance with the Accomplishment Instructions of Bombardier 
Service Bulletin 8-28-36, dated August 9, 2006; or Revision A, dated 
November 17, 2006; or Revision B, dated February 12, 2008: 
Accomplish Bombardier Modsum 8Q101652, ``Electrical--Fuel Quantity 
Indication Wire Routing Segregation and Identification,'' Revision 
F, in accordance with the Accomplishment Instructions of Bombardier 
Service Bulletin 8-28-36, Revision C, dated October 7, 2009.
    (2) For Model DHC-8-102, -103, -106, -201, and -202 airplanes 
having S/Ns 002 through 629 inclusive, on which an ANVS system has 
been installed and on which Modsum 8Q902064 has been incorporated in 
accordance with the Accomplishment Instructions of Bombardier 
Service Bulletin 8-28-42, dated December 21, 2008: Accomplish 
Bombardier Modsum 8Q902064, ``Electrical--Long Range Fuel Quantity 
Indication Wire Routing Segregation and Identification--SFAR 88,'' 
Revision G, in accordance with the Accomplishment Instructions of 
Bombardier Service Bulletin 8-28-42, Revision A, dated October 1, 
2008.
    (3) For Model DHC-8-102, -103, -106, -201, and -202 airplanes 
having S/Ns 620 through 666 inclusive, on which an ANVS system has 
been installed: Do a one-time visual inspection to determine whether 
the

[[Page 60804]]

fuel quantity indicating system (FQIS) wiring harness is routed 
correctly and relocate if necessary, in accordance with the 
Accomplishment Instructions of Bombardier Service Bulletin 8-28-52, 
dated November 3, 2009.

(i) Wire Routing Segregation and Installation of Dual Spacers--Part III

    Within 18,000 flight hours or 108 months, whichever occurs 
first, after the effective date of this AD, do the modification 
specified in paragraphs (i)(1) and (i)(2) of this AD, as applicable.
    (1) For airplanes having S/Ns 003 through 672 inclusive, on 
which Modsum 8Q101513 has been incorporated or on which Modsum 
8Q101652 has been incorporated in accordance with the Accomplishment 
Instructions of Bombardier Service Bulletin 8-28-36, dated August 9, 
2006; Revision A, dated November 17, 2006; Revision B, dated 
February 12, 2008; or Revision C, dated October 7, 2009; excluding 
airplanes on which a long-range fuel system has been installed as 
specified in CF828CH00044, CR828SO08061, SOO 8061, CR828CH00027, or 
CR828SO00006: Accomplish Bombardier Modsum 8Q101908, ``Fuel System--
Fuel Qty Ind., Wire Routing Segregation, Installation of Dual 
Spacers--SFAR88 (Standard A/C),'' Revision B, including installing 
dual spacers inside certain center fuselage locations, in accordance 
with the Accomplishment Instructions of Bombardier Service Bulletin 
8-28-55, dated July 23, 2012.
    (2) For airplanes having S/Ns 003 through 672 inclusive on which 
a long-range fuel system has been installed as specified in 
CF828CH00044, CR828SO08061, SOO 8061, CR828CH00027, or CR828SO00006, 
and on which Modsum 8Q902064 has been incorporated, or on which 
Modsum 8Q902064 has been incorporated in accordance with the 
Accomplishment Instructions of Bombardier Service Bulletin 8-28-42, 
dated December 21, 2008; or Revision A, dated October 1, 2008: 
Accomplish Bombardier Modsum 8Q902383, ``Fuel System--Fuel Qty Ind., 
Wire routing Segregation, Installation of Dual Spacers--SFAR88 (Long 
Range A/C),'' Revision B, including installing dual spacers inside 
certain center fuselage locations, in accordance with the 
Accomplishment Instructions of Bombardier Service Bulletin 8-28-56, 
dated July 23, 2012.

(j) Credit for Previous Actions

    (1) This paragraph provides credit for actions required by 
paragraph (g)(2) of this AD, if those actions were performed before 
the effective date of this AD using Bombardier Service Bulletin 8-
28-39, Revision A, March 15, 2007.
    (2) This paragraph provides credit for actions required by 
paragraph (g)(3) of this AD, if those actions were performed before 
the effective date of this AD using Bombardier Service Bulletin 8-
28-44, dated August 9, 2006; or Revision A, dated November 15, 2006.
    (3) This paragraph provides credit for actions required by 
paragraph (g)(6) of this AD, if those actions were performed before 
the effective date of this AD using Bombardier Service Bulletin 8-
28-41, Revision A, dated April 11, 2007.
    (4) This paragraph provides credit for actions required by 
paragraph (g)(8) of this AD, if those actions were performed before 
the effective date of this AD using Bombardier Service Bulletin 8-
28-43, dated August 10, 2006.
    (5) This paragraph provides credit for actions required by 
paragraph (g)(10) of this AD, if those actions were performed before 
the effective date of this AD using Bombardier Service Bulletin 8-
28-48, dated October 1, 2010.
    (6) This paragraph provides credit for actions required by 
paragraph (g)(13) of this AD, if those actions were performed before 
the effective date of this AD using Bombardier Service Bulletin 8-
28-49, dated October 1, 2010.
    (7) This paragraph provides credit for actions required by 
paragraph (h)(3) of this AD, if those actions were performed before 
the effective date of this AD using Bombardier Service Bulletin 8-
28-53, dated November 3, 2008.

(k) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, ANE-
170, FAA, has the authority to approve AMOCs for this AD, if 
requested using the procedures found in 14 CFR 39.19. In accordance 
with 14 CFR 39.19, send your request to your principal inspector or 
local Flight Standards District Office, as appropriate. If sending 
information directly to the ACO, send it to ATTN: Program Manager, 
Continuing Operational Safety, FAA, New York ACO, 1600 Stewart 
Avenue, Suite 410, Westbury, NY 11590; telephone 516-228-7300; fax 
516-794-5531. 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. The AMOC approval letter must 
specifically reference this AD.
    (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.

(l) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) Canadian Airworthiness Directive CF-2013-07, dated March 1, 
2013, for related information, which can be found in the AD docket 
on the internet at http://www.regulations.gov.
    (2) For service information identified in this AD, contact 
Bombardier, Inc., Q-Series Technical Help Desk, 123 Garratt 
Boulevard, Toronto, Ontario M3K 1Y5, Canada; telephone 416-375-4000; 
fax 416-375-4539; email thd.qseries@aero.bombardier.com; Internet 
http://www.bombardier.com. You may review copies of this service 
information at the FAA, Transport Airplane Directorate, 1601 Lind 
Avenue SW., Renton, WA. For information on the availability of this 
material at the FAA, call 425-227-1221.

    Issued in Renton, Washington, on September 19, 2013.
Ross Landes,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2013-24077 Filed 10-1-13; 8:45 am]
BILLING CODE 4910-13-P