Airworthiness Directives; Bombardier, Inc. Airplanes, 21079-21082 [2013-08205]

Download as PDF Federal Register / Vol. 78, No. 68 / Tuesday, April 9, 2013 / Proposed Rules Bombardier, Inc.: Docket No. FAA–2012– 1003; Directorate Identifier 2012–NM– 064–AD. (a) Comments Due Date We must receive comments by May 24, 2013. (b) Affected ADs None. (c) Applicability This AD applies to Bombardier, Inc. Model DHC–8–400, –401, and –402 airplanes, certificated in any category, serial numbers (S/Ns) 4001 through 4399 inclusive. (d) Subject Air Transport Association (ATA) of America Code 26, Fire protection. (e) Reason This AD was prompted by reports of advance pneumatic detectors (APDs) for engine fire/overheat detector assemblies failing to reset after activation due to permanent deformation of the detector switch diaphragm after being exposed to high temperatures. We are issuing this AD to prevent a continued engine fire indication in the cockpit after the actual fire has been extinguished, which is misleading and might influence the pilot to conduct a potentially hazardous ‘‘off-airport’’ landing. tkelley on DSK3SPTVN1PROD with PROPOSALS (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) Installation Within 6,000 flight hours or 30 months after the effective date of this AD, whichever occurs first, replace the APDs as specified in paragraphs (g)(1), (g)(2), and (g)(3) of this AD, as applicable. (1) For airplanes having S/Ns 4001 through 4373 inclusive: For the nacelle of the engine primary zone, remove any APD having part number (P/N) 10–1098 and install a new APD having P/N 10–1098–01, in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 84–26–08, Revision B, dated September 24, 2012. (2) For airplanes having S/Ns 4001 through 4373 inclusive: For the nacelle of the landing gear primary zone, remove any APD having P/N 10–1097 or 10–1097–01 and install a new APD having P/N 10–1097–02, in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 84–26–09, Revision A, dated May 12, 2011. (3) For all airplanes: For the propeller engine controller, remove any APD having P/ N 10–1096, 10–1096–01, or 10–1096–02 (serial number is all numeric characters), and install a new APD having P/N 10–1096–02 (serial number is three alpha and four numeric characters), in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 84–26–12, Revision B, dated October 12, 2012. (h) Credit for Previous Actions (1) This paragraph provides credit for actions required by paragraph (g)(1) of this VerDate Mar<15>2010 16:18 Apr 08, 2013 Jkt 229001 AD, if those actions were performed before the effective date of this AD using the service information specified in paragraph (h)(1)(i) or (h)(1)(ii) of this AD, which are not incorporated by reference in this AD. (i) Bombardier Service Bulletin 84–26–08, dated March 11, 2011. (ii) Bombardier Service Bulletin 84–26–08, Revision A, dated May 12, 2011. (2) 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 84–26–09, dated March 11, 2011, which is not incorporated by reference in this AD. (3) 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 the service information specified in paragraph (h)(3)(i) or (h)(3)(ii) of this AD, which are not incorporated by reference in this AD. (i) Bombardier Service Bulletin 84–26–12, dated October 12, 2011. (ii) Bombardier Service Bulletin 84–26–12, Revision A, dated December 13, 2011. (i) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, New York Aircraft Certification Office (ACO), 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. (j) Related Information (1) Refer to MCAI Canadian Airworthiness Directive CF–2012–07R1, effective December 21, 2012; and the service information identified in paragraphs (j)(1)(i), (j)(1)(ii), and (j)(1)(iii) of this AD; for related information. (i) Bombardier Service Bulletin 84–26–08, Revision B, dated September 24, 2012. (ii) Bombardier Service Bulletin 84–26–09, Revision A, dated May 12, 2011. (iii) Bombardier Service Bulletin 84–26–12, Revision B, dated October 12, 2012. (2) For service information identified in this AD, contact Bombardier, Inc., Q-Series PO 00000 Frm 00008 Fmt 4702 Sfmt 4702 21079 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 https://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. Issued in Renton, Washington, on March 28, 2013. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2013–08203 Filed 4–8–13; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2013–0297; Directorate Identifier 2012–NM–205–AD] RIN 2120–AA64 Airworthiness Directives; Bombardier, Inc. Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: SUMMARY: We propose to adopt a new airworthiness directive (AD) for certain Bombardier, Inc. Model DHC–8–102, –103, and –106 airplanes. This proposed AD was prompted by a report of cracking in a lower longeron in a nacelle. This proposed AD would require repetitive inspections for cracking of the lower longerons in the nacelles and replacement with new longerons or repair if necessary. Additionally, this proposed AD specifies an optional terminating action. We are proposing this AD to detect and correct such cracking, which could result in degradation of the structural integrity of the nacelle and possible collapse of the main landing gear (MLG). We must receive comments on this proposed AD by May 24, 2013. 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. • 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. DATES: E:\FR\FM\09APP1.SGM 09APP1 21080 Federal Register / Vol. 78, No. 68 / Tuesday, April 9, 2013 / Proposed Rules • 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 https://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 https:// 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: Jeffrey Zimmer, Aerospace Engineer, Airframe and Mechanical Systems Branch, ANE–171, FAA, New York Aircraft Certification Office, 1600 Stewart Avenue, Suite 410, Westbury, New York 11590; telephone (516) 228– 7306; fax (516) 794–5531. SUPPLEMENTARY INFORMATION: tkelley on DSK3SPTVN1PROD 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–2013–0297; Directorate Identifier 2012–NM–205–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 https:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each VerDate Mar<15>2010 16:18 Apr 08, 2013 Jkt 229001 substantive verbal contact we receive about this proposed AD. Differences Between This AD and the MCAI or Service Information Discussion Although the MCAI and Bombardier Service Bulletin 8–54–39, Revision A, dated August 2, 2012, specify to contact the manufacturer for instructions to repair certain conditions, this proposed AD would require repairing those conditions using a method approved by either the Manager, New York Aircraft Certification Office (ACO), ANE–170, Transport Airplane Directorate, FAA; or TCCA (or its delegated agent). Transport Canada Civil Aviation (TCCA), which is the aviation authority for Canada, has issued Canadian Airworthiness Directive CF–2012–27, dated November 2, 2012 (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: There has been one in-service report where a nacelle lower longeron was found to be cracked during a routine maintenance inspection. The investigation determined that the crack initiated from the right-hand side (RHS) drain hole. Fatigue testing has indicated that both the RHS and left-hand side (LHS) longerons are vulnerable to fatigue cracking. Failure of the nacelle lower longeron would result in a degradation of the structural integrity of the nacelle and could potentially lead to collapse of the main landing gear (MLG). This [Canadian] AD mandates initial and repeat inspections [for cracking] of the RHS and LHS nacelle lower longerons until the terminating action is accomplished. The initial inspection may be either a detailed inspection or a bolt-hole eddy current (BHEC) inspection. The repetitive inspection is a BHEC inspection. The corrective action is replacement of the longeron with a new longeron or repair. The optional terminating action is replacement of the nacelle lower longerons, and cold working of the drain holes. You may obtain further information by examining the MCAI in the AD docket. Relevant Service Information Bombardier, Inc., has issued Service Bulletin 8–54–39, Revision A, dated August 2, 2012. The actions described in this service information are intended to correct the unsafe condition identified in the MCAI. 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. PO 00000 Frm 00009 Fmt 4702 Sfmt 4702 Costs of Compliance Based on the service information, we estimate that this proposed AD would affect about 51 products of U.S. registry. We also estimate that it would take about 21 work-hours per product to comply with the basic requirements of this proposed AD. The average labor rate is $85 per work-hour. Based on these figures, we estimate the cost of the proposed AD on U.S. operators to be $37,485, or $1,785 per product. In addition, we estimate that any necessary follow-on actions would take about 100 work-hours and require parts costing $23,849, for a cost of $32,349 per product. We have no way of determining the number of products that may need these actions. 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 E:\FR\FM\09APP1.SGM 09APP1 Federal Register / Vol. 78, No. 68 / Tuesday, April 9, 2013 / Proposed Rules 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 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new AD: ■ Bombardier, Inc.: Docket No. FAA–2013– 0297; Directorate Identifier 2012–NM– 205–AD. (a) Comments Due Date We must receive comments by May 24, 2013. (b) Affected ADs None. tkelley on DSK3SPTVN1PROD with PROPOSALS (c) Applicability This AD applies to Bombardier, Inc. Model DHC–8–102, –103 airplanes, and airplanes converted to Model DHC–8–106 in accordance with Bombardier Service Bulletin 8–92–07 or Bombardier Service Bulletin 8– 92–08, serial numbers 003 through 287 inclusive, with pre-modification 8/1593 nacelle lower longeron installed, certificated in any category. (d) Subject Air Transport Association (ATA) of America Code 54, Nacelles/pylons. (e) Reason This AD was prompted by a report of cracking in a lower longeron in a nacelle. We are issuing this AD to detect and prevent VerDate Mar<15>2010 16:18 Apr 08, 2013 Jkt 229001 such cracking, which could result in degradation of the structural integrity of the nacelle and possible collapse of the main landing gear (MLG). (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) Initial Inspection At the applicable time specified in paragraph (g)(1), (g)(2), (g)(3) or (g)(4) of this AD: Do a detailed visual inspection or a bolthole eddy current (BHEC) test for cracking of each nacelle lower longeron, in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 8–54–39, Revision A, dated August 2, 2012. (1) For Model DHC–8–102 and –103 airplanes that have accumulated 35,000 total flight cycles or less as of the effective date of this AD: Within 5,000 flight cycles after the effective date of this AD, but not to exceed 36,000 total flight cycles. (2) For Model DHC–8–102 and –103 airplanes that have accumulated more than 35,000 total flight cycles as of the effective date of this AD: Within 1,000 flight cycles after the effective date of this AD. (3) For Model DHC–8–106 airplanes with the Pre-Modification 8/1641 configuration, within 500 flight cycles after the effective date of this AD. (4) For Model DHC–8–106 airplanes with the Post-Modification 8/1641 configuration, within 5,000 flight cycles after the effective date of this AD. (h) Repetitive BHEC Testing After accomplishment of the actions required by paragraph (g) of this AD, at the applicable time specified in paragraph (h)(1) or (h)(2) of this AD: Do repetitive BHEC testing for cracking of each nacelle lower longeron, in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 8–54–39, Revision A, dated August 2, 2012, until the terminating action specified in paragraph (j) of this AD is done. (1) For Model DHC–8–102 and 103 airplanes, at intervals not to exceed 2,500 flight cycles. (2) For Model DHC–8–106 airplanes, at intervals not to exceed 1,854 flight cycles. (i) Replacement or Repair of Crack Longeron If any cracking is found during any inspection required by paragraph (g) or (h) of this AD: Before further flight, replace any cracked nacelle lower longeron with a new longeron, in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 8–54–39, Revision A, dated August 2, 2012; or repair the longeron using a method approved by either the Manager, New York ACO, ANE–170, FAA; or Transport Canada Civil Aviation (TCCA) (or its delegated agent). (j) Optional Terminating Action Accomplishment of the actions specified in paragraphs (j)(1) and (j)(2) of this AD constitutes terminating action for the repetitive BHEC testing specified in PO 00000 Frm 00010 Fmt 4702 Sfmt 4702 21081 paragraph (h) of this AD for that longeron only. (1) Replacement of the nacelle lower longeron, in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 8–54–39, Revision A, dated August 2, 2012. (2) Cold working of the drain holes, in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 8–54–39, Revision A, dated August 2, 2012. (k) Credit for Previous Actions This paragraph provides credit for actions required by paragraph (h) of this AD, if those actions were performed before the effective date of this AD using Bombardier Service Bulletin 8–54–39, dated March 14, 2012, which is not incorporated by reference in this AD. (l) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, New York ACO, 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 manager of the ACO, send it to ATTN: Program Manager, Continuing Operational Safety, FAA, New York ACO, 1600 Stewart Avenue, Suite 410, Westbury, New York 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. (m) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) Canadian Airworthiness Directive CF–2012–27, dated November 2, 2012; and Bombardier Service Bulletin 8–54–39, Revision A, dated August 2, 2012; for related information. (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 https://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. E:\FR\FM\09APP1.SGM 09APP1 21082 Federal Register / Vol. 78, No. 68 / Tuesday, April 9, 2013 / Proposed Rules Issued in Renton, Washington, on March 28, 2013. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2013–08205 Filed 4–8–13; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2013–0315; Directorate Identifier 2013–CE–006–AD] RIN 2120–AA64 Airworthiness Directives; GROB– WERKE Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). tkelley on DSK3SPTVN1PROD with PROPOSALS AGENCY: SUMMARY: We propose to adopt a new airworthiness directive (AD) for GROB– WERKE GMBH & CO KG Model G 115E airplanes. This proposed AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as incorrect cable routing causing electrical shorting behind the left-hand (LH) cockpit instrument panel. We are issuing this proposed AD to require actions to address the unsafe condition on these products. DATES: We must receive comments on this proposed AD by May 24, 2013. 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. • 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 Grob Aircraft AG, Customer Service, Lettenbachstrasse 9, 86874 Tussenhausen-Mattsies, Germany, VerDate Mar<15>2010 16:18 Apr 08, 2013 Jkt 229001 telephone: + 49 (0) 8268–998–105; fax; + 49 (0) 8268–998–200; email: productsupport@grob-aircraft.com; Internet: grob-aircraft.com. 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. 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: Taylor Martin, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329– 4138; fax: (816) 329–4090; email: taylor.martin@faa.gov. Occurrences were reported of finding an electrical shorting of main cable loom behind the left-hand (LH) instrument panel of some Grob G115E aeroplanes. In one case, the main cable loom arcing caused an Electronic Horizontal Situation Indicator failure. During the fleet checks, additional cases of main cable loom routing and consequent rubbing with Omni Bearing Selector behind the cockpit instrument panel were identified, while the cable routing was not in conformity with the approved type design. The investigation results concluded that the instrument panels of affected aeroplanes were removed and subsequently re-installed, in service, during embodiment of various optional modifications. This condition, if not detected and corrected, could lead to smoke in the cockpit and/or functional loss of navigation equipment and instruments. To address this potential unsafe condition, Grob Aircraft AG published Mandatory Service Bulletin (MSB) MSB1078–191/1, providing instructions to inspect and correct the cable routing behind the cockpit instrument panel. For the reason described above, this AD requires accomplishment of a one- time inspection to verify correct cable routing behind the LH cockpit instrument panel and, depending on findings, correction and replacement of damaged parts. You may obtain further information by examining the MCAI in the AD docket. SUPPLEMENTARY INFORMATION: Relevant Service 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–2013–0315; Directorate Identifier 2013–CE–006–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:// 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. GROB–WERKE has issued Service Bulletin No. MSB1078–191/1, dated January 15, 2013. The actions described in this service information are intended to correct the unsafe condition identified in the MCAI. Discussion The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued AD No.: 2013– 0017, dated January 17, 2013 (referred to after this as ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The MCAI states: Costs of Compliance PO 00000 Frm 00011 Fmt 4702 Sfmt 4702 FAA’s Determination and Requirements of the Proposed AD This product has been approved by the aviation authority of another country, and is approved for operation in the United States. Pursuant to our bilateral agreement with this State of Design Authority, they have notified us of the unsafe condition described in the MCAI and service information referenced above. We are proposing this AD because we evaluated all information and determined the unsafe condition exists and is likely to exist or develop on other products of the same type design. We estimate that this proposed AD will affect 0 products of U.S. registry. We also estimate that it would take about 1 work-hour per product to comply with the basic requirements of this proposed AD. The average labor rate is $85 per work-hour. Required parts would cost about $10 per product. E:\FR\FM\09APP1.SGM 09APP1

Agencies

[Federal Register Volume 78, Number 68 (Tuesday, April 9, 2013)]
[Proposed Rules]
[Pages 21079-21082]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-08205]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2013-0297; Directorate Identifier 2012-NM-205-AD]
RIN 2120-AA64


Airworthiness Directives; Bombardier, Inc. Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to adopt a new airworthiness directive (AD) for 
certain Bombardier, Inc. Model DHC-8-102, -103, and -106 airplanes. 
This proposed AD was prompted by a report of cracking in a lower 
longeron in a nacelle. This proposed AD would require repetitive 
inspections for cracking of the lower longerons in the nacelles and 
replacement with new longerons or repair if necessary. Additionally, 
this proposed AD specifies an optional terminating action. We are 
proposing this AD to detect and correct such cracking, which could 
result in degradation of the structural integrity of the nacelle and 
possible collapse of the main landing gear (MLG).

DATES: We must receive comments on this proposed AD by May 24, 2013.

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.
     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.

[[Page 21080]]

     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 https://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 https://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: Jeffrey Zimmer, Aerospace Engineer, 
Airframe and Mechanical Systems Branch, ANE-171, FAA, New York Aircraft 
Certification Office, 1600 Stewart Avenue, Suite 410, Westbury, New 
York 11590; telephone (516) 228-7306; 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-2013-0297; 
Directorate Identifier 2012-NM-205-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 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

    Transport Canada Civil Aviation (TCCA), which is the aviation 
authority for Canada, has issued Canadian Airworthiness Directive CF-
2012-27, dated November 2, 2012 (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:

There has been one in-service report where a nacelle lower longeron 
was found to be cracked during a routine maintenance inspection. The 
investigation determined that the crack initiated from the right-
hand side (RHS) drain hole. Fatigue testing has indicated that both 
the RHS and left-hand side (LHS) longerons are vulnerable to fatigue 
cracking. Failure of the nacelle lower longeron would result in a 
degradation of the structural integrity of the nacelle and could 
potentially lead to collapse of the main landing gear (MLG).

This [Canadian] AD mandates initial and repeat inspections [for 
cracking] of the RHS and LHS nacelle lower longerons until the 
terminating action is accomplished.

The initial inspection may be either a detailed inspection or a bolt-
hole eddy current (BHEC) inspection. The repetitive inspection is a 
BHEC inspection. The corrective action is replacement of the longeron 
with a new longeron or repair. The optional terminating action is 
replacement of the nacelle lower longerons, and cold working of the 
drain holes. You may obtain further information by examining the MCAI 
in the AD docket.

Relevant Service Information

    Bombardier, Inc., has issued Service Bulletin 8-54-39, Revision A, 
dated August 2, 2012. The actions described in this service information 
are intended to correct the unsafe condition identified in the MCAI.

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.

Differences Between This AD and the MCAI or Service Information

    Although the MCAI and Bombardier Service Bulletin 8-54-39, Revision 
A, dated August 2, 2012, specify to contact the manufacturer for 
instructions to repair certain conditions, this proposed AD would 
require repairing those conditions using a method approved by either 
the Manager, New York Aircraft Certification Office (ACO), ANE-170, 
Transport Airplane Directorate, FAA; or TCCA (or its delegated agent).

Costs of Compliance

    Based on the service information, we estimate that this proposed AD 
would affect about 51 products of U.S. registry. We also estimate that 
it would take about 21 work-hours per product to comply with the basic 
requirements of this proposed AD. The average labor rate is $85 per 
work-hour. Based on these figures, we estimate the cost of the proposed 
AD on U.S. operators to be $37,485, or $1,785 per product.
    In addition, we estimate that any necessary follow-on actions would 
take about 100 work-hours and require parts costing $23,849, for a cost 
of $32,349 per product. We have no way of determining the number of 
products that may need these actions.

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

[[Page 21081]]

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-2013-0297; Directorate Identifier 
2012-NM-205-AD.

(a) Comments Due Date

    We must receive comments by May 24, 2013.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Bombardier, Inc. Model DHC-8-102, -103 
airplanes, and airplanes converted to Model DHC-8-106 in accordance 
with Bombardier Service Bulletin 8-92-07 or Bombardier Service 
Bulletin 8-92-08, serial numbers 003 through 287 inclusive, with 
pre-modification 8/1593 nacelle lower longeron installed, 
certificated in any category.

(d) Subject

    Air Transport Association (ATA) of America Code 54, Nacelles/
pylons.

(e) Reason

    This AD was prompted by a report of cracking in a lower longeron 
in a nacelle. We are issuing this AD to detect and prevent such 
cracking, which could result in degradation of the structural 
integrity of the nacelle and possible collapse of the main landing 
gear (MLG).

(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) Initial Inspection

    At the applicable time specified in paragraph (g)(1), (g)(2), 
(g)(3) or (g)(4) of this AD: Do a detailed visual inspection or a 
bolt-hole eddy current (BHEC) test for cracking of each nacelle 
lower longeron, in accordance with the Accomplishment Instructions 
of Bombardier Service Bulletin 8-54-39, Revision A, dated August 2, 
2012.
    (1) For Model DHC-8-102 and -103 airplanes that have accumulated 
35,000 total flight cycles or less as of the effective date of this 
AD: Within 5,000 flight cycles after the effective date of this AD, 
but not to exceed 36,000 total flight cycles.
    (2) For Model DHC-8-102 and -103 airplanes that have accumulated 
more than 35,000 total flight cycles as of the effective date of 
this AD: Within 1,000 flight cycles after the effective date of this 
AD.
    (3) For Model DHC-8-106 airplanes with the Pre-Modification 8/
1641 configuration, within 500 flight cycles after the effective 
date of this AD.
    (4) For Model DHC-8-106 airplanes with the Post-Modification 8/
1641 configuration, within 5,000 flight cycles after the effective 
date of this AD.

(h) Repetitive BHEC Testing

    After accomplishment of the actions required by paragraph (g) of 
this AD, at the applicable time specified in paragraph (h)(1) or 
(h)(2) of this AD: Do repetitive BHEC testing for cracking of each 
nacelle lower longeron, in accordance with the Accomplishment 
Instructions of Bombardier Service Bulletin 8-54-39, Revision A, 
dated August 2, 2012, until the terminating action specified in 
paragraph (j) of this AD is done.
    (1) For Model DHC-8-102 and 103 airplanes, at intervals not to 
exceed 2,500 flight cycles.
    (2) For Model DHC-8-106 airplanes, at intervals not to exceed 
1,854 flight cycles.

(i) Replacement or Repair of Crack Longeron

    If any cracking is found during any inspection required by 
paragraph (g) or (h) of this AD: Before further flight, replace any 
cracked nacelle lower longeron with a new longeron, in accordance 
with the Accomplishment Instructions of Bombardier Service Bulletin 
8-54-39, Revision A, dated August 2, 2012; or repair the longeron 
using a method approved by either the Manager, New York ACO, ANE-
170, FAA; or Transport Canada Civil Aviation (TCCA) (or its 
delegated agent).

(j) Optional Terminating Action

    Accomplishment of the actions specified in paragraphs (j)(1) and 
(j)(2) of this AD constitutes terminating action for the repetitive 
BHEC testing specified in paragraph (h) of this AD for that longeron 
only.
    (1) Replacement of the nacelle lower longeron, in accordance 
with the Accomplishment Instructions of Bombardier Service Bulletin 
8-54-39, Revision A, dated August 2, 2012.
    (2) Cold working of the drain holes, in accordance with the 
Accomplishment Instructions of Bombardier Service Bulletin 8-54-39, 
Revision A, dated August 2, 2012.

(k) Credit for Previous Actions

    This paragraph provides credit for actions required by paragraph 
(h) of this AD, if those actions were performed before the effective 
date of this AD using Bombardier Service Bulletin 8-54-39, dated 
March 14, 2012, which is not incorporated by reference in this AD.

(l) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, New 
York ACO, 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 manager of the ACO, send it 
to ATTN: Program Manager, Continuing Operational Safety, FAA, New 
York ACO, 1600 Stewart Avenue, Suite 410, Westbury, New York 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.

(m) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) Canadian Airworthiness Directive CF-2012-27, dated November 
2, 2012; and Bombardier Service Bulletin 8-54-39, Revision A, dated 
August 2, 2012; for related information.
    (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 
https://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.



[[Page 21082]]


    Issued in Renton, Washington, on March 28, 2013.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2013-08205 Filed 4-8-13; 8:45 am]
BILLING CODE 4910-13-P
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