Airworthiness Directives; SOCATA Airplanes, 51456-51459 [2015-20588]

Download as PDF 51456 Federal Register / Vol. 80, No. 164 / Tuesday, August 25, 2015 / Rules and Regulations (e) Required Actions (1) Within 165 hours time-in-service (TIS), visually inspect the swashplate assembly to determine whether a ferrule is installed on the rotating star. If the ferrule is not visible, use a magnetic retriever positioned in Area (X) as shown in the pictures under paragraph 3.B.2.b., Accomplishment Instructions, of Airbus Helicopters Alert Service Bulletin (ASB) No. EC130 62A010, ASB No. AS350 62.00.34, or ASB No. AS355 62.00.33, all Revision 0, and all dated April 28, 2014, whichever is applicable to your helicopter, to determine whether the ferrule is installed. The magnetic retriever will be magnetized if a ferrule is installed. (2) If a ferrule is not installed, no further action is needed. (3) If a ferrule is installed on the rotating star, before further flight, dye-penetrant inspect the rotating star for a crack in areas ‘‘Z’’ depicted in Figure 1 of Airbus Helicopters ASB No. EC130 62A010, ASB No. AS350 62.00.34, or ASB No. AS355 62.00.33, all Revision 0, and all dated April 28, 2014, as applicable to your model helicopter. (i) If the rotating star has a crack, before further flight, remove from service the rotating star; ferrule; and the screws, washers and nuts used to attach the pitch change rods, compass, and the rotating star deflector. (ii) If the rotating star does not have a crack, within 160 hours TIS, remove from service the rotating star; ferrule; and the screws, washers and nuts used to attach the pitch change rods, compass, and the rotating star deflector. (4) Do not install a rotating star P/N 350A371003–04, 350A371003–05, 350A371003–06, 350A371003–07, or 350A371003–08 with a ferrule. (j) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise. (i) Airbus Helicopters Alert Service Bulletin (ASB) No. EC130 62A010, Revision 0, dated April 28, 2014. (ii) Airbus Helicopters ASB No. AS350 62.00.34, Revision 0, dated April 28, 2014. (iii) Airbus Helicopters ASB No. AS355 62.00.33, Revision 0, dated April 28, 2014. (3) For Airbus Helicopters service information identified in this AD, contact Airbus Helicopters, Inc., 2701 N. Forum Drive, Grand Prairie, TX 75052; telephone (972) 641–0000 or (800) 232–0323; fax (972) 641–3775; or at http:// www.airbushelicopters.com/techpub. (4) You may view this service information at FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N–321, Fort Worth, Texas 76177. For information on the availability of this material at the FAA, call (817) 222–5110. (5) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call (202) 741–6030, or go to: http:// www.archives.gov/federal-register/cfr/ibrlocations.html. (f) Special Flight Permits Special flight permits are prohibited. [FR Doc. 2015–20587 Filed 8–24–15; 8:45 am] BILLING CODE 4910–13–P Lhorne on DSK5TPTVN1PROD with RULES (g) Alternative Methods of Compliance (AMOCs) (1) The Manager, Safety Management Group, FAA, may approve AMOCs for this AD. Send your proposal to: Robert Grant, Aviation Safety Engineer, Safety Management Group, FAA, 10101 Hillwood Pkwy., Fort Worth, Texas 76177; telephone (817) 222– 5110; email asw-ftw-amoc@faa.gov. (2) For operations conducted under a 14 CFR part 119 operating certificate or under 14 CFR part 91, subpart K, we suggest that you notify your principal inspector, or lacking a principal inspector, the manager of the local flight standards district office or certificate holding district office, before operating any aircraft complying with this AD through an AMOC. (h) Additional Information The subject of this AD is addressed in the European Aviation Safety Agency (EASA) AD No. 2014–0132R1, dated June 2, 2014. You may view the EASA AD on the Internet at http://www.regulations.gov in Docket No. FAA–2015–0673. (i) Subject Joint Aircraft Service Component (JASC) Code: 6200, Main Rotor System. VerDate Sep<11>2014 15:04 Aug 24, 2015 Jkt 235001 Issued in Fort Worth, Texas, on August 13, 2015. Lance T. Gant, Acting Directorate Manager, Rotorcraft Directorate, Aircraft Certification Service. DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2015–2047; Directorate Identifier 2015–CE–013–AD; Amendment 39–18243; AD 2015–17–10] RIN 2120–AA64 Airworthiness Directives; SOCATA Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: We are superseding Airworthiness Directive (AD) 2007–04– 13 for certain SOCATA Model TBM 700 airplaness (type certificate previously held by EADS SOCATA). This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of SUMMARY: PO 00000 Frm 00034 Fmt 4700 Sfmt 4700 another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as cracks found on the main landing gear cylinders. We are issuing this AD to require actions to address the unsafe condition on these products. DATES: This AD is effective September 29, 2015. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of September 29, 2015. The Director of the Federal Register approved the incorporation by reference of a certain other publication listed in this AD as of March 23, 2007 (72 FR 7576, February 16, 2007). ADDRESSES: You may examine the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2015– 2047; or in person at the Docket Management Facility, U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. For service information identified in this AD, contact SOCATA, Direction des Services, 65921 Tarbes Cedex 9, France; telephone: 33 (0)5 62.41.73.00; fax: 33 (0)5 62.41.76.54; or SOCATA North America, North Perry Airport, 7501 S Airport Rd., Pembroke Pines, Florida 33023, telephone: (954) 893–1400; fax: (954) 964–4141; Internet: http:// www.socata.com. You may view this 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. It is also available on the Internet at http://www.regulations.gov by searching for Docket No. FAA–2015– 2047. FOR FURTHER INFORMATION CONTACT: Albert J. Mercado, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329– 4119; fax: (816) 329–4090; email: albert.mercado@faa.gov. SUPPLEMENTARY INFORMATION: Discussion We issued a supplemental notice of proposed rulemaking (SNPRM) to make changes to an NPRM (80 FR 8821, February 19, 2015), which would amend 14 CFR part 39 to add an AD that would apply to certain SOCATA Model TBM 700 airplaness (type certificate previously held by EADS SOCATA). That SNPRM was published in the Federal Register on June 11, 2015 (80 FR 33208), and proposed to supersede E:\FR\FM\25AUR1.SGM 25AUR1 Federal Register / Vol. 80, No. 164 / Tuesday, August 25, 2015 / Rules and Regulations AD 2007–04–13, Amendment 39–14945, (72 FR 7576, February 16, 2007) (‘‘AD 2007–04–13’’). Since we issued AD 2007–04–13, it has been determined that the time between repetitive inspections should be extended and an optional terminating action for the repetitive inspections is now available. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued AD No. 2006– 0085R2, dated January 16, 2015 (referred to after this as ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The MCAI states: Lhorne on DSK5TPTVN1PROD with RULES Cracks on several main landing gear (MLG) cylinders have been reported in service. This condition, if not to detected and corrected, could lead to fatigue cracks in the shock strut cylinder of the MLG, which could result in a collapsed MLG during take-off or landing runs, and possibly reduce the structural integrity of the aeroplane. To address this unsafe condition, EASA issued AD 2006–0085 to require repetitive special detailed inspections (SDI) for cracks of the MLG shock strut cylinder and, depending on findings, relevant investigative and corrective actions. After that AD was issued, SOCATA performed an analysis to demonstrate that the inspection interval could be extended, and developed a reinforced MLG less prone to fatigue, which is embodied in production through SOCATA modification (MOD) 70– 0190–32 and can be introduced in service through SOCATA Service Bulletin (SB) 70– 130–32 at Revision 03. Prompted by these developments, EASA issued AD 2006–0085R1 to increase the inspection interval and to introduce the installation of a reinforced MLG on the right hand (RH) side and left hand (LH) side as an optional terminating action for the repetitive SDI required by this AD. Since that AD was issued, it was found that aeroplanes MSN 639 to 683 (inclusive) are not affected by this AD. The applicability has therefore been revised to remove those MSN. The MCAI can be found in the AD docket on the Internet at: http:// www.regulations.gov/ #!documentDetail;D=FAA-2015-20470002. In addition, we have determined that airplanes with MLG with forging body that had not reached 1,750 landings as of March 23, 2007 (the effective date of AD 2007–04–13) were not affected by the AD. This is not the intent and allows airplanes to fly indefinitely with the unsafe condition. This AD includes those airplanes with MLG with forging body either at or under 1,750 landings as of March 23, 2007, and extends the time between the repetitive inspections until a reinforced landing gear is installed, which terminates the repetitive inspections. VerDate Sep<11>2014 15:04 Aug 24, 2015 Jkt 235001 51457 Comments Authority for This Rulemaking We gave the public the opportunity to participate in developing this AD. We received one supportive comment to the NPRM (80 FR 8821, February 19, 2015) and no comments on the SNPRM (80 FR 33208, June 11, 2015) or on the determination of the cost to the public. 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. Conclusion We reviewed the relevant data and determined that air safety and the public interest require adopting the AD as proposed except for minor editorial changes. We have determined that these minor changes: • Are consistent with the intent that was proposed in the SNPRM (80 FR 33208, June 11, 2015) for correcting the unsafe condition; and • Do not add any additional burden upon the public than was already proposed in the SNPRM (80 FR 33208, June 11, 2015). Related Service Information Under 1 CFR Part 51 EADS SOCATA has issued TBM Aircraft Mandatory Service Bulletin SB 70–130, ATA No. 32, dated January 2006, and SOCATA has issued DAHER– SOCATA TBM Aircraft Mandatory Service Bulletin SB 70–130, Revision 3, dated December 2014. The actions described in this service information are intended to correct the unsafe condition identified in the MCAI. The DAHER– SOCATA TBM Aircraft Mandatory Service Bulletin SB 70–130, Revision 3, dated December 2014, incorporates procedures for replacing cracked MLG with a reinforced MLG as a terminating action for the repetitive inspections. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section of this AD. Costs of Compliance We estimate that this AD will affect 431 products of U.S. registry. We also estimate that it will take about 3 workhours per product to comply with the basic requirements of this AD. The average labor rate is $85 per work-hour. Based on these figures, we estimate the cost of this AD on U.S. operators to be $109,905, or $255 per product. In addition, we estimate that any necessary follow-on actions will take about 4 work-hours and require parts costing $6,000, for a cost of $6,340 per product. We have no way of determining the number of products that may need these actions. PO 00000 Frm 00035 Fmt 4700 Sfmt 4700 Regulatory Findings We determined that this AD will not have federalism implications under Executive Order 13132. This AD will 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 AD: (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. Examining the AD Docket You may examine the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2015– 2047; 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 the SNPRM, 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. E:\FR\FM\25AUR1.SGM 25AUR1 51458 Federal Register / Vol. 80, No. 164 / Tuesday, August 25, 2015 / Rules and Regulations List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 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 removing Amendment 39–14945 (72 FR 7576, February 16, 2007), and adding the following new AD: ■ 2015–17–10 SOCATA (type certificate previously held by EADS SOCATA): Amendment 39–18243; Docket No. FAA–2015–2047; Directorate Identifier 2015–CE–013–AD. (a) Effective Date This AD becomes effective September 29, 2015. (b) Affected ADs This AD supersedes AD 2007–04–13, Amendment 39–14945, (72 FR 7576, February 16, 2007) (‘‘AD 2007–04–13’’). (c) Applicability This AD applies to SOCATA Model TBM 700 airplanes, serial numbers 1 through 638 and 687, that: (1) are not equipped with a left-hand main landing gear (MLG) body part number (P/N) D68161 or D68161–1 and a right-hand MLG body P/N D68162 or D68162–1; and (2) are certificated in any category. Lhorne on DSK5TPTVN1PROD with RULES (d) Subject Air Transport Association of America (ATA) Code 32: Landing gear. (e) Reason This AD was prompted 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 cracks found on the main landing gear cylinders. In addition, the FAA determined that airplanes with MLG with forging body that had not reached 1,750 landings as of March 23, 2007 (the effective date of AD 2007–04–13) were not affected by AD 2007–04–13. This is not the intent and allows airplanes to fly indefinitely with the unsafe condition. This AD increases the scope of the affected airplanes by including those airplanes with MLG with forging body either at or under 1,750 landings as of March 23, 2007, increases the time between the repetitive inspections, and incorporates a modification to terminate the required repetitive VerDate Sep<11>2014 15:04 Aug 24, 2015 Jkt 235001 inspections. We are issuing this AD to detect and correct cracks in the shock strut cylinder of the MLG, which could cause the MLG to fail. Failure of the shock strut cylinder of the MLG could result in a collapsed MLG during takeoff or landing and possible reduced structural integrity of the airplane. (f) Actions and Compliance for Airplanes Not Previously Affected by AD 2007–04–13 Unless already done, do the actions in paragraphs (f)(1), (f)(2), and (h) of this AD: (1) For MLG with forging body that were either at or under 1,750 landings as of March 23, 2007 (the effective date of (AD 2007–04– 13): Upon or before accumulating 1,750 landings on the MLG with forging body since new or within the next 100 landings after September 29, 2015 (the effective date of this AD), whichever occurs later, inspect the forging body for cracks. Do the inspection following the Accomplishment Instructions of EADS SOCATA TBM Aircraft Mandatory Service Bulletin SB 70–130, dated January 2006, or DAHER–SOCATA TBM Aircraft Mandatory Service Bulletin SB 70–130, Revision 3, dated December 2014. (2) If no cracks are detected during the inspection required in paragraph (f)(1) of this AD, repetitively thereafter inspect at intervals not to exceed 240 landings until a reinforced landing gear specified in paragraph E. Terminating Solution of the Accomplishment Instructions in DAHER–SOCATA TBM Aircraft Mandatory Service Bulletin SB 70– 130, Revision 3, dated December 2014, is installed. (g) Actions and Compliance for Airplanes Previously Affected by AD 2007–04–13 Unless already done, do the actions in paragraphs (g)(1), (g)(2), and (h) of this AD, including all subparagraphs: (1) As of March 23, 2007 (the effective date retained from AD 2007–04–13), for MLG with forging body totaling more than 1,750 landings but less than 3,501 landings since new: (i) Inspect the forging body for cracks within 100 landings after March 23, 2007 (the effective date retained from AD 2007–04–13), following the Accomplishment Instructions of EADS SOCATA TBM Aircraft Mandatory Service Bulletin SB 70–130, dated January 2006, or DAHER–SOCATA TBM Aircraft Mandatory Service Bulletin SB 70–130, Revision 3, dated December 2014. (ii) If no cracks are detected during the inspection required in paragraph (g)(1)(i) of this AD, repetitively thereafter inspect at intervals not to exceed 240 landings until a reinforced landing gear specified in paragraph E. Terminating Solution of the Accomplishment Instructions in DAHER– SOCATA TBM Aircraft Mandatory Service Bulletin SB 70–130, Revision 3, dated December 2014, is installed. (2) As of March 23, 2007 (the effective date retained from AD 2007–04–13), for MLG with forging body totaling more than 3,500 landings since new: (i) Inspect the forging body for cracks within 25 landings after March 23, 2007 (the effective date retained from AD 2007–04–13), following the Accomplishment Instructions of EADS SOCATA TBM Aircraft Mandatory PO 00000 Frm 00036 Fmt 4700 Sfmt 4700 Service Bulletin SB 70–130, dated January 2006, or DAHER–SOCATA TBM Aircraft Mandatory Service Bulletin SB 70–130, Revision 3, dated December 2014. (ii) If no cracks are detected during the inspection required in paragraph (g)(2)(i) of this AD, repetitively thereafter inspect at intervals not to exceed 240 landings until a reinforced landing gear specified in paragraph E. Terminating Solution of the Accomplishment Instructions in DAHER– SOCATA TBM Aircraft Mandatory Service Bulletin SB 70–130, Revision 3, dated December 2014, is installed. (h) Actions and Compliance for All Affected Airplanes If any cracks are detected during any inspection required in paragraphs (f)(1) through (g)(2) of this AD, including all subparagraphs: (1) Before further flight, remove the affected landing gear leg and confirm the presence of the crack with dye penetrant inspection or fluorescent penetrant inspection. (2) If the crack is confirmed, before further flight, contact SOCATA at the address in paragraph (l)(5) of this AD to coordinate the FAA-approved landing gear repair/ replacement and implement any FAAapproved repair/replacement instructions obtained from SOCATA, or replace the cracked landing gear with a reinforced landing gear specified in paragraph E. Terminating Solution of the Accomplishment Instructions in DAHER–SOCATA TBM Aircraft Mandatory Service Bulletin SB 70– 130, Revision 3, dated December 2014. This replacement terminates the repetitive inspections required by this AD. (i) Calculating Unknown Number of Landings for Compliance The compliance times of this AD are presented in landings instead of hours timein-service (TIS). If the number of landings is unknown, hours TIS may be used by dividing the number of hours TIS by 1.35. (j) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, Standards Office, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Send information to ATTN: Albert J. Mercado, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329–4119; fax: (816) 329–4090; email: albert.mercado@faa.gov. Before using any approved AMOC on any airplane to which the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO. (2) Airworthy Product: For any requirement in this AD to obtain corrective actions from a manufacturer or other source, use these actions if they are FAA-approved. Corrective actions are considered FAA-approved if they are approved by the State of Design Authority (or their delegated agent). You are required to assure the product is airworthy before it is returned to service. E:\FR\FM\25AUR1.SGM 25AUR1 Federal Register / Vol. 80, No. 164 / Tuesday, August 25, 2015 / Rules and Regulations (k) Related Information DEPARTMENT OF TRANSPORTATION Refer to MCAI European Aviation Safety Agency (EASA) AD No. 2006–0085R2, dated January 16, 2015, for related information. You may examine the MCAI on the Internet at http://www.regulations.gov/ #!documentDetail;D=FAA-2015-2047-0002. (l) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise. (3) The following service information was approved for IBR on September 29, 2015. (i) DAHER–SOCATA TBM Aircraft Mandatory Service Bulletin SB 70–130, Revision 3, dated December 2014. (ii) Reserved. (4) The following service information was approved for IBR on March 23, 2007 (72 FR 7576, February 16, 2007). (i) EADS SOCATA TBM Aircraft Mandatory Service Bulletin SB 70–130, dated January 2006. (ii) Reserved. (5) For SOCATA service information identified in this AD, contact SOCATA, Direction des Services, 65921 Tarbes Cedex 9, France; telephone: 33 (0)5 62.41.73.00; fax: 33 (0)5 62.41.76.54; or SOCATA North America, North Perry Airport, 7501 S Airport Rd., Pembroke Pines, Florida 33023, telephone: (954) 893–1400; fax: (954) 964– 4141; Internet: http://www.socata.com. (6) You may view this service information at 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. In addition, you can access this service information on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2015–2047. (7) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: http:// www.archives.gov/federal-register/cfr/ibrlocations.html. Lhorne on DSK5TPTVN1PROD with RULES Issued in Kansas City, Missouri, on August 14, 2015. Earl Lawrence, Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015–20588 Filed 8–24–15; 8:45 am] BILLING CODE 4910–13–P VerDate Sep<11>2014 15:04 Aug 24, 2015 Jkt 235001 Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2014–1050; Directorate Identifier 2014–NM–123–AD; Amendment 39–18241; AD 2015–17–08] RIN 2120–AA64 Airworthiness Directives; Bombardier, Inc. Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model DHC–8–400 series airplanes. This AD was prompted by an in-service report of an uncommanded and unannunciated nose wheel steering during airplane pushback from the gate. This AD requires installing new cable assemblies with a pull-down resistor. We are issuing this AD to prevent an uncommanded nose wheel steering during takeoff or landing in the event of an open circuit in the steering system, and possible consequent runway excursion. SUMMARY: This AD becomes effective September 29, 2015. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of September 29, 2015. ADDRESSES: You may examine the AD docket on the Internet at http:// www.regulations.gov/ #!docketDetail;D=FAA-2014-1050 or in person at the Docket Management Facility, U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC. For service information identified in this AD, contact Bombardier, Inc., QSeries 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 view this 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. It is also available on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2014– 1050. DATES: PO 00000 Frm 00037 Fmt 4700 Sfmt 4700 51459 FOR FURTHER INFORMATION CONTACT: Assata Dessaline, Aerospace Engineer, Avionics and Services Branch, ANE– 172, FAA, New York Aircraft Certification Office (ACO), 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone (516) 228–7301; fax (516) 794–5531. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to certain Bombardier, Inc. Model DHC–8–400 series airplanes. The NPRM published in the Federal Register on January 23, 2015 (80 FR 3504). The Transport Canada Civil Aviation (TCCA), which is the aviation authority for Canada, has issued Canadian Airworthiness Directive CF–2013–38, dated November 28, 2013 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for certain Bombardier, Inc. Model DHC–8–400, –401, and –402 series airplanes. The MCAI states: There has been one in-service report of an un-commanded and un-annunciated nose wheel steering during aeroplane push-back from the gate. The investigation revealed that a design deficiency exists within the steering control unit (SCU) where an open circuit may not be adequately detected and annunciated to the flight crew. A sustained open circuit could result in an un-commanded and unannunciated nose wheel steering input. Un-commanded nose wheel steering during takeoff or landing may lead to a runway excursion. This [Canadian] AD mandates the installation of new cable assemblies, with a pull-down resistor, to ensure that the nose wheel steering system reverts to fail-safe free castor mode in the event of an open circuit in the steering system. You may examine the MCAI in the AD docket on the Internet at http:// www.regulations.gov/ #!documentDetail;D=FAA-2014-10500002. Comments We gave the public the opportunity to participate in developing this AD. The following presents the comment received on the NPRM (80 FR 3504, January 23, 2015) and the FAA’s response to each comment. Request To Remove Certain Service Information Procedures Horizon Air requested that we amend paragraph (g) of the proposed AD (80 FR 3504, January 23, 2015) to exclude Part A, ‘‘Job Set-up,’’ and Part C ‘‘Close Out,’’ sections of the Accomplishment Instructions in Bombardier Service E:\FR\FM\25AUR1.SGM 25AUR1

Agencies

[Federal Register Volume 80, Number 164 (Tuesday, August 25, 2015)]
[Rules and Regulations]
[Pages 51456-51459]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-20588]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-2047; Directorate Identifier 2015-CE-013-AD; 
Amendment 39-18243; AD 2015-17-10]
RIN 2120-AA64


Airworthiness Directives; SOCATA Airplanes

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

ACTION: Final rule.

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SUMMARY: We are superseding Airworthiness Directive (AD) 2007-04-13 for 
certain SOCATA Model TBM 700 airplaness (type certificate previously 
held by EADS SOCATA). This AD results from mandatory continuing 
airworthiness information (MCAI) issued 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 cracks 
found on the main landing gear cylinders. We are issuing this AD to 
require actions to address the unsafe condition on these products.

DATES: This AD is effective September 29, 2015.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of September 
29, 2015.
    The Director of the Federal Register approved the incorporation by 
reference of a certain other publication listed in this AD as of March 
23, 2007 (72 FR 7576, February 16, 2007).

ADDRESSES: You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-
2047; or in person at the Docket Management Facility, U.S. Department 
of Transportation, Docket Operations, M-30, West Building Ground Floor, 
Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590.
    For service information identified in this AD, contact SOCATA, 
Direction des Services, 65921 Tarbes Cedex 9, France; telephone: 33 
(0)5 62.41.73.00; fax: 33 (0)5 62.41.76.54; or SOCATA North America, 
North Perry Airport, 7501 S Airport Rd., Pembroke Pines, Florida 33023, 
telephone: (954) 893-1400; fax: (954) 964-4141; Internet: http://www.socata.com. You may view this 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. It is also available on the Internet at http://www.regulations.gov by searching for Docket No. FAA-2015-2047.

FOR FURTHER INFORMATION CONTACT: Albert J. Mercado, Aerospace Engineer, 
FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, 
Missouri 64106; telephone: (816) 329-4119; fax: (816) 329-4090; email: 
albert.mercado@faa.gov.

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a supplemental notice of proposed rulemaking (SNPRM) to 
make changes to an NPRM (80 FR 8821, February 19, 2015), which would 
amend 14 CFR part 39 to add an AD that would apply to certain SOCATA 
Model TBM 700 airplaness (type certificate previously held by EADS 
SOCATA). That SNPRM was published in the Federal Register on June 11, 
2015 (80 FR 33208), and proposed to supersede

[[Page 51457]]

AD 2007-04-13, Amendment 39-14945, (72 FR 7576, February 16, 2007) 
(``AD 2007-04-13'').
    Since we issued AD 2007-04-13, it has been determined that the time 
between repetitive inspections should be extended and an optional 
terminating action for the repetitive inspections is now available.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Community, has issued AD 
No. 2006-0085R2, dated January 16, 2015 (referred to after this as 
``the MCAI''), to correct an unsafe condition for the specified 
products. The MCAI states:

    Cracks on several main landing gear (MLG) cylinders have been 
reported in service.
    This condition, if not to detected and corrected, could lead to 
fatigue cracks in the shock strut cylinder of the MLG, which could 
result in a collapsed MLG during take-off or landing runs, and 
possibly reduce the structural integrity of the aeroplane.
    To address this unsafe condition, EASA issued AD 2006-0085 to 
require repetitive special detailed inspections (SDI) for cracks of 
the MLG shock strut cylinder and, depending on findings, relevant 
investigative and corrective actions.
    After that AD was issued, SOCATA performed an analysis to 
demonstrate that the inspection interval could be extended, and 
developed a reinforced MLG less prone to fatigue, which is embodied 
in production through SOCATA modification (MOD) 70-0190-32 and can 
be introduced in service through SOCATA Service Bulletin (SB) 70-
130-32 at Revision 03.
    Prompted by these developments, EASA issued AD 2006-0085R1 to 
increase the inspection interval and to introduce the installation 
of a reinforced MLG on the right hand (RH) side and left hand (LH) 
side as an optional terminating action for the repetitive SDI 
required by this AD.
    Since that AD was issued, it was found that aeroplanes MSN 639 
to 683 (inclusive) are not affected by this AD. The applicability 
has therefore been revised to remove those MSN.

The MCAI can be found in the AD docket on the Internet at: http://www.regulations.gov/#!documentDetail;D=FAA-2015-2047-0002.
    In addition, we have determined that airplanes with MLG with 
forging body that had not reached 1,750 landings as of March 23, 2007 
(the effective date of AD 2007-04-13) were not affected by the AD. This 
is not the intent and allows airplanes to fly indefinitely with the 
unsafe condition. This AD includes those airplanes with MLG with 
forging body either at or under 1,750 landings as of March 23, 2007, 
and extends the time between the repetitive inspections until a 
reinforced landing gear is installed, which terminates the repetitive 
inspections.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We received one supportive comment to the NPRM (80 FR 8821, 
February 19, 2015) and no comments on the SNPRM (80 FR 33208, June 11, 
2015) or on the determination of the cost to the public.

Conclusion

    We reviewed the relevant data and determined that air safety and 
the public interest require adopting the AD as proposed except for 
minor editorial changes. We have determined that these minor changes:
     Are consistent with the intent that was proposed in the 
SNPRM (80 FR 33208, June 11, 2015) for correcting the unsafe condition; 
and
     Do not add any additional burden upon the public than was 
already proposed in the SNPRM (80 FR 33208, June 11, 2015).

Related Service Information Under 1 CFR Part 51

    EADS SOCATA has issued TBM Aircraft Mandatory Service Bulletin SB 
70-130, ATA No. 32, dated January 2006, and SOCATA has issued DAHER-
SOCATA TBM Aircraft Mandatory Service Bulletin SB 70-130, Revision 3, 
dated December 2014. The actions described in this service information 
are intended to correct the unsafe condition identified in the MCAI. 
The DAHER-SOCATA TBM Aircraft Mandatory Service Bulletin SB 70-130, 
Revision 3, dated December 2014, incorporates procedures for replacing 
cracked MLG with a reinforced MLG as a terminating action for the 
repetitive inspections. This service information is reasonably 
available because the interested parties have access to it through 
their normal course of business or by the means identified in the 
ADDRESSES section of this AD.

Costs of Compliance

    We estimate that this AD will affect 431 products of U.S. registry. 
We also estimate that it will take about 3 work-hours per product to 
comply with the basic requirements of this AD. The average labor rate 
is $85 per work-hour. Based on these figures, we estimate the cost of 
this AD on U.S. operators to be $109,905, or $255 per product.
    In addition, we estimate that any necessary follow-on actions will 
take about 4 work-hours and require parts costing $6,000, for a cost of 
$6,340 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 AD will not have federalism implications 
under Executive Order 13132. This AD will 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 AD:
    (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.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-
2047; 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 the SNPRM, 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.

[[Page 51458]]

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA amends 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 removing Amendment 39-14945 (72 FR 
7576, February 16, 2007), and adding the following new AD:

2015-17-10 SOCATA (type certificate previously held by EADS SOCATA): 
Amendment 39-18243; Docket No. FAA-2015-2047; Directorate Identifier 
2015-CE-013-AD.

(a) Effective Date

    This AD becomes effective September 29, 2015.

(b) Affected ADs

    This AD supersedes AD 2007-04-13, Amendment 39-14945, (72 FR 
7576, February 16, 2007) (``AD 2007-04-13'').

(c) Applicability

    This AD applies to SOCATA Model TBM 700 airplanes, serial 
numbers 1 through 638 and 687, that:
    (1) are not equipped with a left-hand main landing gear (MLG) 
body part number (P/N) D68161 or D68161-1 and a right-hand MLG body 
P/N D68162 or D68162-1; and
    (2) are certificated in any category.

(d) Subject

    Air Transport Association of America (ATA) Code 32: Landing 
gear.

(e) Reason

    This AD was prompted 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 cracks found on 
the main landing gear cylinders. In addition, the FAA determined 
that airplanes with MLG with forging body that had not reached 1,750 
landings as of March 23, 2007 (the effective date of AD 2007-04-13) 
were not affected by AD 2007-04-13. This is not the intent and 
allows airplanes to fly indefinitely with the unsafe condition. This 
AD increases the scope of the affected airplanes by including those 
airplanes with MLG with forging body either at or under 1,750 
landings as of March 23, 2007, increases the time between the 
repetitive inspections, and incorporates a modification to terminate 
the required repetitive inspections. We are issuing this AD to 
detect and correct cracks in the shock strut cylinder of the MLG, 
which could cause the MLG to fail. Failure of the shock strut 
cylinder of the MLG could result in a collapsed MLG during takeoff 
or landing and possible reduced structural integrity of the 
airplane.

(f) Actions and Compliance for Airplanes Not Previously Affected by AD 
2007-04-13

    Unless already done, do the actions in paragraphs (f)(1), 
(f)(2), and (h) of this AD:
    (1) For MLG with forging body that were either at or under 1,750 
landings as of March 23, 2007 (the effective date of (AD 2007-04-
13): Upon or before accumulating 1,750 landings on the MLG with 
forging body since new or within the next 100 landings after 
September 29, 2015 (the effective date of this AD), whichever occurs 
later, inspect the forging body for cracks. Do the inspection 
following the Accomplishment Instructions of EADS SOCATA TBM 
Aircraft Mandatory Service Bulletin SB 70-130, dated January 2006, 
or DAHER-SOCATA TBM Aircraft Mandatory Service Bulletin SB 70-130, 
Revision 3, dated December 2014.
    (2) If no cracks are detected during the inspection required in 
paragraph (f)(1) of this AD, repetitively thereafter inspect at 
intervals not to exceed 240 landings until a reinforced landing gear 
specified in paragraph E. Terminating Solution of the Accomplishment 
Instructions in DAHER-SOCATA TBM Aircraft Mandatory Service Bulletin 
SB 70-130, Revision 3, dated December 2014, is installed.

(g) Actions and Compliance for Airplanes Previously Affected by AD 
2007-04-13

    Unless already done, do the actions in paragraphs (g)(1), 
(g)(2), and (h) of this AD, including all subparagraphs:
    (1) As of March 23, 2007 (the effective date retained from AD 
2007-04-13), for MLG with forging body totaling more than 1,750 
landings but less than 3,501 landings since new:
    (i) Inspect the forging body for cracks within 100 landings 
after March 23, 2007 (the effective date retained from AD 2007-04-
13), following the Accomplishment Instructions of EADS SOCATA TBM 
Aircraft Mandatory Service Bulletin SB 70-130, dated January 2006, 
or DAHER-SOCATA TBM Aircraft Mandatory Service Bulletin SB 70-130, 
Revision 3, dated December 2014.
    (ii) If no cracks are detected during the inspection required in 
paragraph (g)(1)(i) of this AD, repetitively thereafter inspect at 
intervals not to exceed 240 landings until a reinforced landing gear 
specified in paragraph E. Terminating Solution of the Accomplishment 
Instructions in DAHER-SOCATA TBM Aircraft Mandatory Service Bulletin 
SB 70-130, Revision 3, dated December 2014, is installed.
    (2) As of March 23, 2007 (the effective date retained from AD 
2007-04-13), for MLG with forging body totaling more than 3,500 
landings since new:
    (i) Inspect the forging body for cracks within 25 landings after 
March 23, 2007 (the effective date retained from AD 2007-04-13), 
following the Accomplishment Instructions of EADS SOCATA TBM 
Aircraft Mandatory Service Bulletin SB 70-130, dated January 2006, 
or DAHER-SOCATA TBM Aircraft Mandatory Service Bulletin SB 70-130, 
Revision 3, dated December 2014.
    (ii) If no cracks are detected during the inspection required in 
paragraph (g)(2)(i) of this AD, repetitively thereafter inspect at 
intervals not to exceed 240 landings until a reinforced landing gear 
specified in paragraph E. Terminating Solution of the Accomplishment 
Instructions in DAHER-SOCATA TBM Aircraft Mandatory Service Bulletin 
SB 70-130, Revision 3, dated December 2014, is installed.

(h) Actions and Compliance for All Affected Airplanes

    If any cracks are detected during any inspection required in 
paragraphs (f)(1) through (g)(2) of this AD, including all 
subparagraphs:
    (1) Before further flight, remove the affected landing gear leg 
and confirm the presence of the crack with dye penetrant inspection 
or fluorescent penetrant inspection.
    (2) If the crack is confirmed, before further flight, contact 
SOCATA at the address in paragraph (l)(5) of this AD to coordinate 
the FAA-approved landing gear repair/replacement and implement any 
FAA-approved repair/replacement instructions obtained from SOCATA, 
or replace the cracked landing gear with a reinforced landing gear 
specified in paragraph E. Terminating Solution of the Accomplishment 
Instructions in DAHER-SOCATA TBM Aircraft Mandatory Service Bulletin 
SB 70-130, Revision 3, dated December 2014. This replacement 
terminates the repetitive inspections required by this AD.

(i) Calculating Unknown Number of Landings for Compliance

    The compliance times of this AD are presented in landings 
instead of hours time-in-service (TIS). If the number of landings is 
unknown, hours TIS may be used by dividing the number of hours TIS 
by 1.35.

 (j) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
Standards Office, FAA, has the authority to approve AMOCs for this 
AD, if requested using the procedures found in 14 CFR 39.19. Send 
information to ATTN: Albert J. Mercado, Aerospace Engineer, FAA, 
Small Airplane Directorate, 901 Locust, Room 301, Kansas City, 
Missouri 64106; telephone: (816) 329-4119; fax: (816) 329-4090; 
email: albert.mercado@faa.gov. Before using any approved AMOC on any 
airplane to which the AMOC applies, notify your appropriate 
principal inspector (PI) in the FAA Flight Standards District Office 
(FSDO), or lacking a PI, your local FSDO.
    (2) Airworthy Product: For any requirement in this AD to obtain 
corrective actions from a manufacturer or other source, use these 
actions if they are FAA-approved. Corrective actions are considered 
FAA-approved if they are approved by the State of Design Authority 
(or their delegated agent). You are required to assure the product 
is airworthy before it is returned to service.

[[Page 51459]]

(k) Related Information

    Refer to MCAI European Aviation Safety Agency (EASA) AD No. 
2006-0085R2, dated January 16, 2015, for related information. You 
may examine the MCAI on the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2015-2047-0002.

(l) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless the AD specifies otherwise.
    (3) The following service information was approved for IBR on 
September 29, 2015.
    (i) DAHER-SOCATA TBM Aircraft Mandatory Service Bulletin SB 70-
130, Revision 3, dated December 2014.
    (ii) Reserved.
    (4) The following service information was approved for IBR on 
March 23, 2007 (72 FR 7576, February 16, 2007).
    (i) EADS SOCATA TBM Aircraft Mandatory Service Bulletin SB 70-
130, dated January 2006.
    (ii) Reserved.
    (5) For SOCATA service information identified in this AD, 
contact SOCATA, Direction des Services, 65921 Tarbes Cedex 9, 
France; telephone: 33 (0)5 62.41.73.00; fax: 33 (0)5 62.41.76.54; or 
SOCATA North America, North Perry Airport, 7501 S Airport Rd., 
Pembroke Pines, Florida 33023, telephone: (954) 893-1400; fax: (954) 
964-4141; Internet: http://www.socata.com.
    (6) You may view this service information at 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. In addition, you can access this service information 
on the Internet at http://www.regulations.gov by searching for and 
locating Docket No. FAA-2015-2047.
    (7) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Kansas City, Missouri, on August 14, 2015.
Earl Lawrence,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2015-20588 Filed 8-24-15; 8:45 am]
 BILLING CODE 4910-13-P