81 FR 10540 - Airworthiness Directives; Airbus Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 81, Issue 40 (March 1, 2016)
Federal Aviation Administration
Federal Register Volume 81, Issue 40 (March 1, 2016)
| Page Range | 10540-10544 | |
| FR Document | 2016-04290 |
[Federal Register Volume 81, Number 40 (Tuesday, March 1, 2016)] [Proposed Rules] [Pages 10540-10544] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2016-04290] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2016-3984; Directorate Identifier 2014-NM-119-AD] RIN 2120-AA64 Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). ----------------------------------------------------------------------- SUMMARY: We propose to supersede Airworthiness Directive (AD) 2013-10- 03, for all Airbus Model A330-200, -200 Freighter, and -300 series airplanes; and Model A340-200, -300, -500, and -600 series airplanes. AD 2013-10-03 currently requires one-time inspections for deformation and damage of the bogie beams of the main landing gear (MLG); repetitive inspections for damage and corrosion of the sliding piston sub-assembly on certain airplanes; and related investigative and corrective actions if necessary. Since we issued AD 2013-10-03, we have determined that certain one-time inspections are no longer necessary, certain compliance times may be extended, and an optional terminating action should be provided. This proposed AD would remove Model A340- 500, and -600 series airplanes from the applicability, remove certain one-time inspections of the MLG bogie beams and the sliding piston sub- assembly; revise certain compliance times and provide, for certain airplanes, an optional terminating action for the repetitive actions. We are proposing this AD to detect and correct damage or corrosion under the bogie stop pad of both MLG bogie beams, which could result in a damaged bogie beam and consequent detachment of the beam from the airplane, or collapse of the MLG and departure of the airplane from the runway. DATES: We must receive comments on this proposed AD by April 15, 2016. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods:Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments. Fax: 202-493-2251. Mail: U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590. Hand Delivery: U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this NPRM, contact Airbus SAS, Airworthiness Office--EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone: +33 5 61 93 36 96; fax: +33 5 61 93 45 80; email: [email protected]; Internet http://www.airbus.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. 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-2016- 3984; 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 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: Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone: 425-227-1138; fax: 425-227-1149. 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-2016-3984; Directorate Identifier 2014-NM-119-AD'' at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD based on those comments. We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion On May 13, 2013, we issued AD 2013-10-03, Amendment 39-17456 (78 FR 31386, May 24, 2013). AD 2013-10-03 requires actions intended to address an unsafe condition on all Airbus Model A330-200, -200 Freighter, and -300 series airplanes; and Model A340-200, -300, -500, and -600 series airplanes. (AD 2013-10-03 superseded AD 2010-02-10, Amendment 39-16181 (75 FR 4477, January 28, 2010)). Since we issued AD 2013-10-03, Amendment 39-17456 (78 FR 31386, May 24, 2013), we have determined that certain one-time inspections are no longer necessary, certain compliance times may be extended, and an optional terminating action should be provided. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA AD 2014-0120R1, dated August 31, 2015 (referred to after this as the Mandatory Continuing Airworthiness Information, or ``the MCAI''), to correct an unsafe condition for all Airbus Model A330-200, -200 Freighter, and -300 series airplanes; and Model A340-200, -300, -500, and -600 series airplanes. The MCAI states: During a scheduled maintenance inspection on the Main Landing Gear (MLG), the bogie stop pad was found deformed and cracked. Upon removal of the bogie stop pad for replacement, the bogie beam was also found cracked. The results of a laboratory investigation indicated that an overload event had occurred and no fatigue propagation of the crack was evident. A second bogie beam crack was subsequently found on another aeroplane, located under a bogie stop pad which only had superficial paint damage. This condition, if not detected and corrected, could lead to landing gear bogie detachment from the aeroplane, or landing gear collapse, or a runway excursion, [[Page 10541]] possibly resulting in damage to the aeroplane and injury to the occupants. To address this potential unsafe condition, EASA issued * * * [an earlier AD] to require accomplishment of a one-time detailed inspection under the bogie stop pad of both MLG bogie beams. As a result of the one-time inspection required by that [earlier EASA] AD, applicable to A330, A340-200 and A340-300 aeroplanes, numerous bogie stop pad were found corroded and a few cracked. The one-time inspection was retained in EASA AD 2011-0211 [http://ad.easa.europa.eu/blob/easa_ad_2011_0211_superseded.pdf/AD_2011-0211_1] [which corresponds to FAA AD 2013-10-03, Amendment 39-17456 (78 FR 31386, May 24, 2013)], which superseded * * * [an earlier EASA AD], applicable to all A330 and A340 aeroplanes, which also introduced repetitive inspections for A330, A340-200 and A340- 300 aeroplanes, but not for the A340-500/-600 aeroplanes. Since issuance of EASA AD 2011-0211, further investigation accomplished by Airbus led to the conclusion that the one-time inspection in accordance with Airbus Service Bulletin (SB) A330-32- 3220, or Airbus SB A340-32-4264, or Airbus SB A340-32-5087, as applicable, is no longer necessary and, for those aeroplanes, only the inspections (initial and repetitive) in accordance with Airbus SB A330-32-3248 or Airbus SB A340-32-4286, as applicable, must remain. In addition, Airbus also determined that repetitive inspections of the MLG in accordance with Airbus SB A340-32-5112 are necessary for A340-500/-600 aeroplanes. Consequently, EASA issued * * * [another AD], which partially retained the requirements of EASA AD 2011-0211, which was superseded, and introduced repetitive detailed inspections of the MLG for A340-500 and A340-600 aeroplanes. Since that [EASA] AD was issued, it was determined that repetitive inspections of the MLG are not necessary on the A340-500/ -600 aeroplanes and that the threshold for the inspection of MLG P/N 10-210 series can be delayed. In addition, Airbus developed a mod of the MLG P/N 10-210 series that can be embodied both in production through mod 204421 and in service with Airbus SB A330-32-3268 or SB A340-32-4300, as applicable. This modification constitutes a terminating action for the repetitive inspections for aeroplanes equipped with MLG P/N 10-210 series. For the reasons described above, this [EASA] AD is revised and requires inspection of the MLG (with an amended threshold for MLG P/ N 10-210 series) and introduces an option to terminate the repetitive inspection with a modification of the MLG P/N 10-210 series. The required actions include repetitive detailed inspections for damage and corrosion of the sliding piston sub-assembly, and related investigative and corrective actions if necessary. Related investigative actions include a test for indications of corrosion and damage to the bogie assembly base material, and a magnetic particle inspection for cracks, corrosion, and damage of the bogie beam. Corrective actions include repairing affected parts. The optional terminating action modification of the bogie beam of an MLG having P/N 10-210 consists of installing a nickel under chrome coating, a new bogie beam stop pad, and new stop pad brackets. You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016- 3984. Related Service Information Under 1 CFR Part 51 Airbus has issued Service Bulletin A330-32-3248, Revision 02, dated April 16, 2014. This service information describes procedures for doing a detailed inspection for damage and corrosion of the MLG sliding piston sub-assembly, bogie beam stop pad and the bogie beam under the stop pad; and related investigative and corrective actions. Airbus has also issued Service Bulletin A330-32-3268 and Airbus Service Bulletin A340-32-4300, both dated April 20, 2015. This service information describes procedures for modification of the bogie beam of an MLG having P/N 10-210, which includes installing a nickel under chrome coating, a new bogie beam stop pad, and new stop pad brackets. 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. 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 these same type designs. Explanation of ``RC'' Procedures and Tests in Service Information The FAA worked in conjunction with industry, under the Airworthiness Directive Implementation Aviation Rulemaking Committee (ARC), to enhance the AD system. One enhancement was a new process for annotating which procedures and tests in the service information are required for compliance with an AD. Differentiating these procedures and tests from other tasks in the service information is expected to improve an owner's/operator's understanding of crucial AD requirements and help provide consistent judgment in AD compliance. The procedures and tests identified as Required for Compliance (RC) in any service information have a direct effect on detecting, preventing, resolving, or eliminating an identified unsafe condition. As specified in a Note under the Accomplishment Instructions of the specified service information, procedures and tests that are identified as RC in any service information must be done to comply with the proposed AD. However, procedures and tests that are not identified as RC are recommended. Those procedures and tests that are not identified as RC may be deviated from using accepted methods in accordance with the operator's maintenance or inspection program without obtaining approval of an alternative method of compliance (AMOC), provided the procedures and tests identified as RC can be done and the airplane can be put back in an airworthy condition. Any substitutions or changes to procedures or tests identified as RC will require approval of an AMOC. Costs of Compliance We estimate that this proposed AD affects 89 Model A330-200, -200 Freighter, and -300 series airplanes of U.S. registry. We estimate that it would take about 12 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 this proposed AD on U.S. operators to be $90,780, or $1,020 per product. Currently, there are no affected Model A340-200, or -300, series airplanes on the U.S. Register. However, if an affected airplane is imported and placed on the U.S. Register in the future, it would be subject to the same per-airplane cost specified above for the Model A330-200, -200 Freighter, and -300 series airplanes. In addition, we estimate that any necessary follow-on actions would take about 24 work-hours, and 1 work-hour for reporting, and require parts costing $78, for a cost of $2,203 per product. We have no way of determining the number of aircraft that might need these actions. According to the manufacturer, all of the parts costs of the optional [[Page 10542]] terminating action specified in this proposed AD may be covered under warranty, thereby reducing the cost impact on affected individuals. We do not control warranty coverage for affected individuals. We have received no definitive data that would enable us to provide the work- hour cost estimates for the optional terminating action specified in this proposed AD. Paperwork Reduction Act A federal agency may not conduct or sponsor, and a person is not required to respond to, nor shall a person be subject to penalty for failure to comply with a collection of information subject to the requirements of the Paperwork Reduction Act unless that collection of information displays a current valid OMB control number. The control number for the collection of information required by this AD is 2120- 0056. The paperwork cost associated with this AD has been detailed in the Costs of Compliance section of this document and includes time for reviewing instructions, as well as completing and reviewing the collection of information. Therefore, all reporting associated with this AD is mandatory. Comments concerning the accuracy of this burden and suggestions for reducing the burden should be directed to the FAA at 800 Independence Ave. SW., Washington, DC 20591, ATTN: Information Collection Clearance Officer, AES-200. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA's authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. ``Subtitle VII: Aviation Programs,'' describes in more detail the scope of the Agency's authority. We are issuing this rulemaking under the authority described in ``Subtitle VII, Part A, Subpart III, Section 44701: General requirements.'' Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify this proposed regulation: 1. Is not a ``significant regulatory action'' under Executive Order 12866; 2. Is not a ``significant rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 3. Will not affect intrastate aviation in Alaska; and 4. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. 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 removing Airworthiness Directive (AD) 2013-10-03, Amendment 39-17456 (78 FR 31386, May 24, 2013), and adding the following new AD: Airbus: Docket No. FAA-2016-3984; Directorate Identifier 2014-NM- 119-AD. (a) Comments Due Date We must receive comments by April 15, 2016. (b) Affected ADs This AD replaces AD 2013-10-03, Amendment 39-17456 (78 FR 31386, May 24, 2013). (c) Applicability This AD applies to Airbus airplanes identified in paragraphs (c)(1) and (c)(2) of this AD, certificated in any category; all serial numbers, except those that have embodied Airbus Modification 204421 in production. (1) Model A330-201, -202, -203, -223, -223F, -243, -243F, -301, -302, -303, -321, -322, -323, -341, -342, and -343 airplanes. (2) Model A340-211, -212, -213, -311, -312, -313 airplanes. (d) Subject Air Transport Association (ATA) of America Code 32, Landing gear. (e) Reason This AD was prompted by reports of corroded and cracked bogie beams under the bogie stop pad. We are issuing this AD to detect and correct damage or corrosion under the bogie stop pad of both main landing gear (MLG) bogie beams, which could result in a damaged bogie beam and consequent detachment of the beam from the airplane, or collapse of the MLG and departure of the airplane from the runway. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Repetitive Inspections, Related Investigative Actions, and Corrective Actions For Model A330-200, Model A330-200 Freighter, and Model A330-300 series airplanes; and Model A340-200, and -300 series airplanes; equipped with a MLG having part number (P/N) 201252 series, or P/N 201490 series, or P/N 10-210 series: Do the applicable actions required by paragraph (g)(1) or (g)(2) of this AD. (1) For airplanes equipped, as of the effective date of this AD, with a MLG that has been previously inspected as specified in Airbus Service Bulletin A330-32-3220, Airbus Service Bulletin A330-32-3248, Airbus Service Bulletin A340-32-4264, or Airbus Service Bulletin A340-32-4286, as applicable: At applicable times specified in paragraphs (h)(1) and (h)(2) of this AD, do a detailed inspection for damage (e.g., cracking and fretting) and corrosion of the MLG sliding piston subassembly, bogie beam stop pad, and the bogie beam under the stop pad; and do all applicable related investigative and corrective actions; in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330-32-3248, Revision 02, dated April 16, 2014; or Airbus Service Bulletin A340-32-4286, dated October 5, 2011; as applicable, except as required by paragraph (j) of this AD. Do all applicable related investigative and corrective actions before further flight. Repeat the inspection of the MLG sliding piston sub-assembly, bogie beam stop pad, and the bogie beam under the stop pad, thereafter, at intervals not to exceed 2,500 flight cycles or 24 months, whichever occurs first. (2) For airplanes equipped, as of the effective date of this AD, with a MLG that has not been previously inspected as specified in Airbus Service Bulletin A330-32-3220, Airbus Service Bulletin A330- 32-3248, Airbus Service Bulletin A340-32-4264, or Airbus Service Bulletin, A340-32-4286, as applicable: At the applicable times specified in paragraphs (h)(3) and (h)(4) of this AD, do a detailed inspection for damage (e.g., cracking and fretting) and corrosion of the MLG sliding piston sub-assembly, bogie beam stop pad, and the bogie beam under the stop pad; and do all applicable related investigative and corrective actions; in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330-32-3248, Revision 02, dated April 16, 2014; or Airbus Service Bulletin A340- 32-4286, dated October 5, 2011; as applicable, except [[Page 10543]] as required by paragraph (j) of this AD. Do all applicable related investigative and corrective actions before further flight. Repeat the inspection of the MLG sliding piston sub-assembly, bogie beam stop pad, and the bogie beam under the stop pad, thereafter, at intervals not to exceed 2,500 flight cycles or 24 months, whichever occurs first. (h) Compliance Times for Paragraph (g) of This AD Actions Do the applicable actions required by paragraph (g) of this AD at the applicable time specified in paragraph (h)(1), (h)(2), (h)(3), or (h)(4) of this AD. (1) For airplanes identified in paragraph (g)(1) of this AD having an MLG P/N 201252 series and P/N 201490 series: Before the accumulation of 2,500 total flight cycles or 24 months, whichever occurs first since the later of the times specified in paragraphs (h)(1)(i) and (h)(1)(ii) of this AD. (i) Since first flight after a MLG overhaul. (ii) Since first flight after the most recent accomplishment of an inspection of the MLG as specified in Airbus Service Bulletin A330-32-3220; Airbus Service Bulletin A330-32-3248; Airbus Service Bulletin A340-32-4286; or Airbus Service Bulletin A340-32-4264; as applicable. (2) For airplanes identified in paragraph (g)(1) of this AD having an MLG P/N 10-210 series: Before the accumulation of 126 months since first flight of the MLG on an airplane or since first flight on an airplane after the most recent inspection of the MLG as specified in Airbus Service Bulletin A330-32-3248, Revision 01, dated December 13, 2012; or Airbus Service Bulletin A330-32-3248, Revision 02, dated April 16, 2014; or Airbus Service Bulletin A340- 32-4286, dated October 5, 2011; as applicable. (3) For airplanes identified in paragraph (g)(2) of this AD having an MLG P/N 201252 series and P/N 201490 series: At the later of the times specified in paragraphs (h)(3)(i) and (h)(3)(ii) of this AD. (i) Before the accumulation of 2,500 total flight cycles or 24 months, whichever occurs first since the later of the times specified in paragraphs (h)(3)(i)(A) and (h)(3)(i)(B) of this AD. (A) Since first flight of the MLG on an airplane. (B) Since first flight after a MLG overhaul. (ii) Within 16 months after the effective date of this AD. (4) For airplanes identified in paragraph (g)(2) of this AD having MLG P/N 10-210 series: Before the accumulation of 126 months since first flight of the MLG on an airplane. (i) Optional Overhaul For the purposes of this AD, accomplishment of an MLG overhaul is acceptable instead of an inspection required by paragraph (g) of this AD. The inspections required by paragraph (g) of this AD are not terminated by an MLG overhaul, but are required at the next applicable compliance time required by paragraph (g) of this AD. (j) Service Information Exception If the applicable service information specified in paragraph (g) of this AD specifies to contact Messier-Dowty for instructions, or if any repair required by paragraph (g) of this AD is beyond the maximum repair allowance specified in the applicable service information specified in paragraph (g) of this AD: Before further flight, repair using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA); or Airbus's EASA Design Organization Approval (DOA). (k) Reporting Requirement After accomplishing any of the corrective actions required by paragraph (g) of this AD or any repair required by paragraph (j) of this AD: Report the results of the corrective actions or repair to Airbus, Customer Services Directorate, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex France; Attn: SDC32 Technical Data and Documentation Services; fax: +33 5 61 93 28 06; email: [email protected], at the applicable time specified in paragraph (k)(1) or (k)(2) of this AD. (1) If the corrective action or repair was done on or after the effective date of this AD: Submit the report within 90 days after doing corrective action or repair. (2) If the corrective action or repair was done prior to the effective date of this AD: Submit the report within 90 days after the effective date of this AD. (l) Terminating Action Limitation Accomplishment of corrective actions as required by paragraph (g) of this AD does not constitute terminating action for the repetitive inspections required by this AD. (m) Optional Terminating Action for Certain Airplanes For airplanes with any MLG having P/N 10-210 series: Modification on an airplane of the bogie beam of each MLG having P/N 10-210 series as specified in the Accomplishment Instructions of Airbus Service Bulletin A330-32-3268, dated April 20, 2015; or Airbus Service Bulletin A340-32-4300, dated April 20, 2015; as applicable; constitutes terminating action for the requirements of this AD for that airplane, provided that, following in-service modification, the airplane remains in post-service bulletin configuration. (n) Credit for Previous Actions This paragraph provides credit for the actions required by paragraph (g) of this AD, if those actions were performed before the effective date of this AD using the service information identified in paragraph (n)(1), (n)(2), or (n)(3), (n)(4), or (n)(5) of this AD. (1) Airbus Service Bulletin A330-32-3248, dated October 5, 2011, which is not incorporated by reference in this AD. (2) Airbus Service Bulletin A330-32-3248, Revision 01, including Appendix 01, dated December 13, 2012, which was incorporated by reference in AD 2013-10-03, Amendment 39-17456 (78 FR 31386, May 24, 2013). (3) Airbus Service Bulletin A330-32-3220, dated October 10, 2008, which was incorporated by reference in AD 2010-02-10, Amendment 39-16181 (75 FR 4477, January 28, 2010). (4) Airbus Service Bulletin A330-32-3220, Revision 01, dated October 5, 2011, which was incorporated by reference in AD 2013-10- 03, Amendment 39-17456 (78 FR 31386, May 24, 2013). (5) Airbus Service Bulletin A330-32-3220, Revision 02, dated December 13, 2012, which was incorporated by reference in AD 2013- 10-03, Amendment 39-17456 (78 FR 31386, May 24, 2013). (o) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the International Branch, send it to ATTN: Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone: 425-227-1138; fax: 425-227-1149. Information may be emailed to: [email protected]. (i) 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. (ii) AMOCs approved previously for AD 2013-10-03, Amendment 39- 17456 (78 FR 31386, May 24, 2013), are not approved as AMOCs with this AD. (2) Contacting the Manufacturer: As of the effective date of this AD, for any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA; or Airbus's EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature. (3) Required for Compliance (RC): Except as required by paragraph (j) of this AD: If any service information contains procedures or tests that are identified as RC, those procedures and tests must be done to comply with this AD; any procedures or tests that are not identified as RC are recommended. Those procedures and tests that are not identified as RC may be deviated from using accepted methods in accordance with the operator's maintenance or inspection program without obtaining approval of an AMOC, provided the procedures and tests identified as RC can be done and the airplane can be put back in an airworthy condition. Any substitutions or changes to procedures or tests identified as RC require approval of an AMOC. (4) Reporting Requirements: A federal agency may not conduct or sponsor, and a person is not required to respond to, nor shall a person be subject to a penalty for failure to comply with a collection of information subject to the requirements of [[Page 10544]] the Paperwork Reduction Act unless that collection of information displays a current valid OMB Control Number. The OMB Control Number for this information collection is 2120-0056. Public reporting for this collection of information is estimated to be approximately 5 minutes per response, including the time for reviewing instructions, completing and reviewing the collection of information. All responses to this collection of information are mandatory. Comments concerning the accuracy of this burden and suggestions for reducing the burden should be directed to the FAA at: 800 Independence Ave. SW., Washington, DC 20591, Attn: Information Collection Clearance Officer, AES-200. (p) Special Flight Permits Special flight permits, as described in Section 21.197 and Section 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199), are not allowed if any crack is found during any inspection required by this AD. (q) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA AD 2014-0120R1, dated August 31, 2015, for related information. This MCAI may be found in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-3984. (2) For service information identified in this AD, contact Airbus SAS, Airworthiness Office--EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone: +33 5 61 93 36 96; fax: +33 5 61 93 45 80; email: [email protected]; Internet http://www.airbus.com. You may view this service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221. Issued in Renton, Washington, on February 19, 2016. Dorr M. Anderson, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016-04290 Filed 2-29-16; 8:45 am] BILLING CODE 4910-13-P
![10540 Federal Register / Vol. 81, No. 40 / Tuesday, March 1, 2016 / Proposed Rules
Management, P.O. Box 3707, MC 2H–65, from the airplane, or collapse of the this proposed AD. Send your comments
Seattle, WA 98124–2207; telephone 206– MLG and departure of the airplane from to an address listed under the
544–5000, extension 1; fax 206–766–5680; the runway. ADDRESSES section. Include ‘‘Docket No.
Internet https://www.myboeingfleet.com. You FAA–2016–3984; Directorate Identifier
DATES: We must receive comments on
may view this referenced service information
at the FAA, Transport Airplane Directorate, this proposed AD by April 15, 2016. 2014–NM–119–AD’’ at the beginning of
1601 Lind Avenue SW., Renton, Washington. ADDRESSES: You may send comments, your comments. We specifically invite
For information on the availability of this using the procedures found in 14 CFR comments on the overall regulatory,
material at the FAA, call 425–227–1221. 11.43 and 11.45, by any of the following economic, environmental, and energy
Issued in Renton, Washington, on February methods: aspects of this proposed AD. We will
19, 2016. • Federal eRulemaking Portal: Go to consider all comments received by the
Dorr M. Anderson, http://www.regulations.gov. Follow the closing date and may amend this
instructions for submitting comments. proposed AD based on those comments.
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
• Fax: 202–493–2251. We will post all comments we
• Mail: U.S. Department of receive, without change, to http://
[FR Doc. 2016–04292 Filed 2–29–16; 8:45 am]
Transportation, Docket Operations, M– www.regulations.gov, including any
BILLING CODE 4910–13–P 30, West Building Ground Floor, Room personal information you provide. We
W12–140, 1200 New Jersey Avenue SE., will also post a report summarizing each
Washington, DC 20590. substantive verbal contact we receive
DEPARTMENT OF TRANSPORTATION • Hand Delivery: U.S. Department of about this proposed AD.
Federal Aviation Administration Transportation, Docket Operations, M–
30, West Building Ground Floor, Room Discussion
W12–140, 1200 New Jersey Avenue SE., On May 13, 2013, we issued AD
14 CFR Part 39
Washington, DC, between 9 a.m. and 5 2013–10–03, Amendment 39–17456 (78
[Docket No. FAA–2016–3984; Directorate p.m., Monday through Friday, except FR 31386, May 24, 2013). AD 2013–10–
Identifier 2014–NM–119–AD] Federal holidays. 03 requires actions intended to address
RIN 2120–AA64 For service information identified in an unsafe condition on all Airbus Model
this NPRM, contact Airbus SAS, A330–200, –200 Freighter, and –300
Airworthiness Directives; Airbus Airworthiness Office—EAL, 1 Rond series airplanes; and Model A340–200,
Airplanes Point Maurice Bellonte, 31707 Blagnac –300, –500, and –600 series airplanes.
Cedex, France; telephone: +33 5 61 93 (AD 2013–10–03 superseded AD 2010–
AGENCY: Federal Aviation 36 96; fax: +33 5 61 93 45 80; email: 02–10, Amendment 39–16181 (75 FR
Administration (FAA), DOT. airworthiness.A330-A340@airbus.com; 4477, January 28, 2010)).
ACTION: Notice of proposed rulemaking Internet http://www.airbus.com. You Since we issued AD 2013–10–03,
(NPRM). may view this referenced service Amendment 39–17456 (78 FR 31386,
information at the FAA, Transport May 24, 2013), we have determined that
SUMMARY: We propose to supersede Airplane Directorate, 1601 Lind Avenue certain one-time inspections are no
Airworthiness Directive (AD) 2013–10– SW., Renton, WA. For information on longer necessary, certain compliance
03, for all Airbus Model A330–200, the availability of this material at the times may be extended, and an optional
–200 Freighter, and –300 series FAA, call 425–227–1221. terminating action should be provided.
airplanes; and Model A340–200, –300, The European Aviation Safety Agency
–500, and –600 series airplanes. AD Examining the AD Docket
(EASA), which is the Technical Agent
2013–10–03 currently requires one-time You may examine the AD docket on for the Member States of the European
inspections for deformation and damage the Internet at http:// Union, has issued EASA AD 2014–
of the bogie beams of the main landing www.regulations.gov by searching for 0120R1, dated August 31, 2015 (referred
gear (MLG); repetitive inspections for and locating Docket No. FAA–2016– to after this as the Mandatory
damage and corrosion of the sliding 3984; or in person at the Docket Continuing Airworthiness Information,
piston sub-assembly on certain Management Facility between 9 a.m. or ‘‘the MCAI’’), to correct an unsafe
airplanes; and related investigative and and 5 p.m., Monday through Friday, condition for all Airbus Model A330–
corrective actions if necessary. Since we except Federal holidays. The AD docket 200, –200 Freighter, and –300 series
issued AD 2013–10–03, we have contains this proposed AD, the airplanes; and Model A340–200, –300,
determined that certain one-time regulatory evaluation, any comments –500, and –600 series airplanes. The
inspections are no longer necessary, received, and other information. The MCAI states:
certain compliance times may be street address for the Docket Operations
extended, and an optional terminating office (telephone: 800–647–5527) is in During a scheduled maintenance
action should be provided. This the ADDRESSES section. Comments will inspection on the Main Landing Gear (MLG),
the bogie stop pad was found deformed and
proposed AD would remove Model be available in the AD docket shortly cracked. Upon removal of the bogie stop pad
A340–500, and –600 series airplanes after receipt. for replacement, the bogie beam was also
from the applicability, remove certain FOR FURTHER INFORMATION CONTACT: found cracked.
one-time inspections of the MLG bogie Vladimir Ulyanov, Aerospace Engineer, The results of a laboratory investigation
beams and the sliding piston sub- International Branch, ANM–116, indicated that an overload event had
asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
assembly; revise certain compliance Transport Airplane Directorate, FAA, occurred and no fatigue propagation of the
times and provide, for certain airplanes, 1601 Lind Avenue SW., Renton, WA crack was evident.
an optional terminating action for the 98057–3356; telephone: 425–227–1138; A second bogie beam crack was
repetitive actions. We are proposing this subsequently found on another aeroplane,
fax: 425–227–1149. located under a bogie stop pad which only
AD to detect and correct damage or SUPPLEMENTARY INFORMATION: had superficial paint damage.
corrosion under the bogie stop pad of This condition, if not detected and
both MLG bogie beams, which could Comments Invited
corrected, could lead to landing gear bogie
result in a damaged bogie beam and We invite you to send any written detachment from the aeroplane, or landing
consequent detachment of the beam relevant data, views, or arguments about gear collapse, or a runway excursion,
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![Federal Register / Vol. 81, No. 40 / Tuesday, March 1, 2016 / Proposed Rules 10541
possibly resulting in damage to the aeroplane particle inspection for cracks, corrosion, annotating which procedures and tests
and injury to the occupants. and damage of the bogie beam. in the service information are required
To address this potential unsafe condition, Corrective actions include repairing for compliance with an AD.
EASA issued * * * [an earlier AD] to require Differentiating these procedures and
affected parts.
accomplishment of a one-time detailed
inspection under the bogie stop pad of both
The optional terminating action tests from other tasks in the service
MLG bogie beams. modification of the bogie beam of an information is expected to improve an
As a result of the one-time inspection MLG having P/N 10–210 consists of owner’s/operator’s understanding of
required by that [earlier EASA] AD, installing a nickel under chrome crucial AD requirements and help
applicable to A330, A340–200 and A340–300 coating, a new bogie beam stop pad, and provide consistent judgment in AD
aeroplanes, numerous bogie stop pad were new stop pad brackets. compliance. The procedures and tests
found corroded and a few cracked. You may examine the MCAI in the identified as Required for Compliance
The one-time inspection was retained in AD docket on the Internet at http:// (RC) in any service information have a
EASA AD 2011–0211 [http:// www.regulations.gov by searching for direct effect on detecting, preventing,
ad.easa.europa.eu/blob/easa_ad_2011_0211_
superseded.pdf/AD_2011-0211_1] [which and locating Docket No. FAA–2016– resolving, or eliminating an identified
corresponds to FAA AD 2013–10–03, 3984. unsafe condition.
Amendment 39–17456 (78 FR 31386, May 24, As specified in a Note under the
Related Service Information Under 1 Accomplishment Instructions of the
2013)], which superseded * * * [an earlier
CFR Part 51 specified service information,
EASA AD], applicable to all A330 and A340
aeroplanes, which also introduced repetitive Airbus has issued Service Bulletin procedures and tests that are identified
inspections for A330, A340–200 and A340– A330–32–3248, Revision 02, dated April as RC in any service information must
300 aeroplanes, but not for the A340–500/- 16, 2014. This service information be done to comply with the proposed
600 aeroplanes. describes procedures for doing a AD. However, procedures and tests that
Since issuance of EASA AD 2011–0211,
detailed inspection for damage and are not identified as RC are
further investigation accomplished by Airbus
led to the conclusion that the one-time corrosion of the MLG sliding piston sub- recommended. Those procedures and
inspection in accordance with Airbus Service assembly, bogie beam stop pad and the tests that are not identified as RC may
Bulletin (SB) A330–32–3220, or Airbus SB bogie beam under the stop pad; and be deviated from using accepted
A340–32–4264, or Airbus SB A340–32–5087, related investigative and corrective methods in accordance with the
as applicable, is no longer necessary and, for actions. operator’s maintenance or inspection
those aeroplanes, only the inspections (initial Airbus has also issued Service program without obtaining approval of
and repetitive) in accordance with Airbus SB Bulletin A330–32–3268 and Airbus an alternative method of compliance
A330–32–3248 or Airbus SB A340–32–4286, Service Bulletin A340–32–4300, both
as applicable, must remain.
(AMOC), provided the procedures and
In addition, Airbus also determined that
dated April 20, 2015. This service tests identified as RC can be done and
repetitive inspections of the MLG in information describes procedures for the airplane can be put back in an
accordance with Airbus SB A340–32–5112 modification of the bogie beam of an airworthy condition. Any substitutions
are necessary for A340–500/-600 aeroplanes. MLG having P/N 10–210, which or changes to procedures or tests
Consequently, EASA issued * * * [another includes installing a nickel under identified as RC will require approval of
AD], which partially retained the chrome coating, a new bogie beam stop an AMOC.
requirements of EASA AD 2011–0211, which pad, and new stop pad brackets.
was superseded, and introduced repetitive This service information is reasonably Costs of Compliance
detailed inspections of the MLG for A340– available because the interested parties We estimate that this proposed AD
500 and A340–600 aeroplanes.
Since that [EASA] AD was issued, it was have access to it through their normal affects 89 Model A330–200, –200
determined that repetitive inspections of the course of business or by the means Freighter, and –300 series airplanes of
MLG are not necessary on the A340–500/-600 identified in the ADDRESSES section. U.S. registry.
aeroplanes and that the threshold for the We estimate that it would take about
FAA’s Determination and Requirements 12 work-hours per product to comply
inspection of MLG P/N 10–210 series can be
delayed. In addition, Airbus developed a of This Proposed AD with the basic requirements of this
mod of the MLG P/N 10–210 series that can This product has been approved by proposed AD. The average labor rate is
be embodied both in production through the aviation authority of another $85 per work-hour. Based on these
mod 204421 and in service with Airbus SB country, and is approved for operation figures, we estimate the cost of this
A330–32–3268 or SB A340–32–4300, as
in the United States. Pursuant to our proposed AD on U.S. operators to be
applicable. This modification constitutes a
terminating action for the repetitive bilateral agreement with the State of $90,780, or $1,020 per product.
inspections for aeroplanes equipped with Design Authority, we have been notified Currently, there are no affected Model
MLG P/N 10–210 series. of the unsafe condition described in the A340–200, or –300, series airplanes on
For the reasons described above, this MCAI and service information the U.S. Register. However, if an
[EASA] AD is revised and requires inspection referenced above. We are proposing this affected airplane is imported and placed
of the MLG (with an amended threshold for AD because we evaluated all pertinent on the U.S. Register in the future, it
MLG P/N 10–210 series) and introduces an information and determined an unsafe would be subject to the same per-
option to terminate the repetitive inspection condition exists and is likely to exist or airplane cost specified above for the
with a modification of the MLG P/N 10–210 Model A330–200, –200 Freighter, and
develop on other products of these same
series.
type designs. –300 series airplanes.
asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
The required actions include In addition, we estimate that any
repetitive detailed inspections for Explanation of ‘‘RC’’ Procedures and necessary follow-on actions would take
damage and corrosion of the sliding Tests in Service Information about 24 work-hours, and 1 work-hour
piston sub-assembly, and related The FAA worked in conjunction with for reporting, and require parts costing
investigative and corrective actions if industry, under the Airworthiness $78, for a cost of $2,203 per product. We
necessary. Related investigative actions Directive Implementation Aviation have no way of determining the number
include a test for indications of Rulemaking Committee (ARC), to of aircraft that might need these actions.
corrosion and damage to the bogie enhance the AD system. One According to the manufacturer, all of
assembly base material, and a magnetic enhancement was a new process for the parts costs of the optional
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![10542 Federal Register / Vol. 81, No. 40 / Tuesday, March 1, 2016 / Proposed Rules
terminating action specified in this the relationship between the national (e) Reason
proposed AD may be covered under Government and the States, or on the This AD was prompted by reports of
warranty, thereby reducing the cost distribution of power and corroded and cracked bogie beams under the
impact on affected individuals. We do responsibilities among the various bogie stop pad. We are issuing this AD to
not control warranty coverage for levels of government. detect and correct damage or corrosion under
affected individuals. We have received For the reasons discussed above, I the bogie stop pad of both main landing gear
(MLG) bogie beams, which could result in a
no definitive data that would enable us certify this proposed regulation: damaged bogie beam and consequent
to provide the work-hour cost estimates 1. Is not a ‘‘significant regulatory detachment of the beam from the airplane, or
for the optional terminating action action’’ under Executive Order 12866; collapse of the MLG and departure of the
specified in this proposed AD. 2. Is not a ‘‘significant rule’’ under the airplane from the runway.
Paperwork Reduction Act DOT Regulatory Policies and Procedures (f) Compliance
(44 FR 11034, February 26, 1979);
A federal agency may not conduct or Comply with this AD within the
3. Will not affect intrastate aviation in compliance times specified, unless already
sponsor, and a person is not required to
Alaska; and done.
respond to, nor shall a person be subject
to penalty for failure to comply with a 4. Will not have a significant
economic impact, positive or negative, (g) Repetitive Inspections, Related
collection of information subject to the Investigative Actions, and Corrective
requirements of the Paperwork on a substantial number of small entities Actions
Reduction Act unless that collection of under the criteria of the Regulatory
For Model A330–200, Model A330–200
information displays a current valid Flexibility Act.
Freighter, and Model A330–300 series
OMB control number. The control List of Subjects in 14 CFR Part 39 airplanes; and Model A340–200, and –300
number for the collection of information series airplanes; equipped with a MLG
Air transportation, Aircraft, Aviation having part number (P/N) 201252 series, or
required by this AD is 2120–0056. The
safety, Incorporation by reference, P/N 201490 series, or P/N 10–210 series: Do
paperwork cost associated with this AD
Safety. the applicable actions required by paragraph
has been detailed in the Costs of (g)(1) or (g)(2) of this AD.
Compliance section of this document The Proposed Amendment (1) For airplanes equipped, as of the
and includes time for reviewing Accordingly, under the authority effective date of this AD, with a MLG that has
instructions, as well as completing and delegated to me by the Administrator, been previously inspected as specified in
reviewing the collection of information. the FAA proposes to amend 14 CFR part
Airbus Service Bulletin A330–32–3220,
Therefore, all reporting associated with Airbus Service Bulletin A330–32–3248,
39 as follows: Airbus Service Bulletin A340–32–4264, or
this AD is mandatory. Comments
concerning the accuracy of this burden Airbus Service Bulletin A340–32–4286, as
PART 39—AIRWORTHINESS applicable: At applicable times specified in
and suggestions for reducing the burden DIRECTIVES paragraphs (h)(1) and (h)(2) of this AD, do a
should be directed to the FAA at 800 detailed inspection for damage (e.g., cracking
Independence Ave. SW., Washington, ■ 1. The authority citation for part 39 and fretting) and corrosion of the MLG
DC 20591, ATTN: Information continues to read as follows: sliding piston subassembly, bogie beam stop
Collection Clearance Officer, AES–200. Authority: 49 U.S.C. 106(g), 40113, 44701. pad, and the bogie beam under the stop pad;
and do all applicable related investigative
Authority for This Rulemaking and corrective actions; in accordance with
§ 39.13 [Amended]
Title 49 of the United States Code the Accomplishment Instructions of Airbus
■ 2. The FAA amends § 39.13 by Service Bulletin A330–32–3248, Revision 02,
specifies the FAA’s authority to issue removing Airworthiness Directive (AD)
rules on aviation safety. Subtitle I, dated April 16, 2014; or Airbus Service
2013–10–03, Amendment 39–17456 (78 Bulletin A340–32–4286, dated October 5,
section 106, describes the authority of FR 31386, May 24, 2013), and adding 2011; as applicable, except as required by
the FAA Administrator. ‘‘Subtitle VII: the following new AD: paragraph (j) of this AD. Do all applicable
Aviation Programs,’’ describes in more related investigative and corrective actions
detail the scope of the Agency’s Airbus: Docket No. FAA–2016–3984;
before further flight. Repeat the inspection of
authority. Directorate Identifier 2014–NM–119–AD.
the MLG sliding piston sub-assembly, bogie
We are issuing this rulemaking under (a) Comments Due Date beam stop pad, and the bogie beam under the
the authority described in ‘‘Subtitle VII, We must receive comments by April 15, stop pad, thereafter, at intervals not to exceed
Part A, Subpart III, Section 44701: 2016. 2,500 flight cycles or 24 months, whichever
General requirements.’’ Under that occurs first.
section, Congress charges the FAA with (b) Affected ADs (2) For airplanes equipped, as of the
This AD replaces AD 2013–10–03, effective date of this AD, with a MLG that has
promoting safe flight of civil aircraft in
Amendment 39–17456 (78 FR 31386, May 24, not been previously inspected as specified in
air commerce by prescribing regulations Airbus Service Bulletin A330–32–3220,
for practices, methods, and procedures 2013).
Airbus Service Bulletin A330–32–3248,
the Administrator finds necessary for (c) Applicability Airbus Service Bulletin A340–32–4264, or
safety in air commerce. This regulation This AD applies to Airbus airplanes Airbus Service Bulletin, A340–32–4286, as
is within the scope of that authority identified in paragraphs (c)(1) and (c)(2) of applicable: At the applicable times specified
because it addresses an unsafe condition this AD, certificated in any category; all serial in paragraphs (h)(3) and (h)(4) of this AD, do
that is likely to exist or develop on numbers, except those that have embodied a detailed inspection for damage (e.g.,
asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
products identified in this rulemaking Airbus Modification 204421 in production. cracking and fretting) and corrosion of the
(1) Model A330–201, –202, –203, –223, MLG sliding piston sub-assembly, bogie
action.
–223F, –243, –243F, –301, –302, –303, –321, beam stop pad, and the bogie beam under the
Regulatory Findings –322, –323, –341, –342, and –343 airplanes. stop pad; and do all applicable related
(2) Model A340–211, –212, –213, –311, investigative and corrective actions; in
We determined that this proposed AD accordance with the Accomplishment
–312, –313 airplanes.
would not have federalism implications Instructions of Airbus Service Bulletin A330–
under Executive Order 13132. This (d) Subject 32–3248, Revision 02, dated April 16, 2014;
proposed AD would not have a Air Transport Association (ATA) of or Airbus Service Bulletin A340–32–4286,
substantial direct effect on the States, on America Code 32, Landing gear. dated October 5, 2011; as applicable, except
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![10544 Federal Register / Vol. 81, No. 40 / Tuesday, March 1, 2016 / Proposed Rules
the Paperwork Reduction Act unless that Turbomeca S.A. Arriel 1D and 1D1 781–238–7770; fax: 781–238–7199;
collection of information displays a current turboshaft engines with a pre- email: philip.haberlen@faa.gov.
valid OMB Control Number. The OMB modification (mod) TU357 gas generator SUPPLEMENTARY INFORMATION:
Control Number for this information
collection is 2120–0056. Public reporting for
module (M03), installed. This proposed
AD was prompted by reports of Comments Invited
this collection of information is estimated to
be approximately 5 minutes per response, divergent rubbing between the piston We invite you to send any written
including the time for reviewing instructions, shaft small diameter labyrinth and the relevant data, views, or arguments about
completing and reviewing the collection of rear bearing support. This proposed AD this NPRM. Send your comments to an
information. All responses to this collection would require removing the pre- address listed under the ADDRESSES
of information are mandatory. Comments modification (mod) TU357 gas generator section. Include ‘‘Docket No. FAA–
concerning the accuracy of this burden and 2016–2859; Directorate Identifier 2016–
module (M03) and replacing with a part
suggestions for reducing the burden should
eligible for installation. We are NE–04–AD’’ at the beginning of your
be directed to the FAA at: 800 Independence
Ave. SW., Washington, DC 20591, Attn: proposing this AD to prevent failure of comments. We specifically invite
Information Collection Clearance Officer, the labyrinth seal and engine, in-flight comments on the overall regulatory,
AES–200. shutdown, and loss of control of the economic, environmental, and energy
helicopter. aspects of this NPRM. We will consider
(p) Special Flight Permits
all comments received by the closing
Special flight permits, as described in DATES: We must receive comments on date and may amend this NPRM based
Section 21.197 and Section 21.199 of the this proposed AD by May 2, 2016. on those comments.
Federal Aviation Regulations (14 CFR 21.197
ADDRESSES: You may send comments by We will post all comments we
and 21.199), are not allowed if any crack is
found during any inspection required by this any of the following methods: receive, without change, to http://
AD. • Federal eRulemaking Portal: Go to www.regulations.gov, including any
http://www.regulations.gov. Follow the personal information you provide. We
(q) Related Information
instructions for submitting comments. will also post a report summarizing each
(1) Refer to Mandatory Continuing • Mail: Docket Management Facility, substantive verbal contact with FAA
Airworthiness Information (MCAI) EASA AD
U.S. Department of Transportation, 1200 personnel concerning this NPRM.
2014–0120R1, dated August 31, 2015, for
related information. This MCAI may be New Jersey Avenue SE., West Building Discussion
found in the AD docket on the Internet at Ground Floor, Room W12–140,
http://www.regulations.gov by searching for Washington, DC 20590–0001. The European Aviation Safety Agency
and locating Docket No. FAA–2016–3984. • Hand Delivery: Deliver to Mail (EASA), which is the Technical Agent
(2) For service information identified in address above between 9 a.m. and 5 for the Member States of the European
this AD, contact Airbus SAS, Airworthiness p.m., Monday through Friday, except Community, has issued EASA AD 2016–
Office—EAL, 1 Rond Point Maurice Bellonte, 0009, dated January 13, 2016 (referred to
31707 Blagnac Cedex, France; telephone: +33
Federal holidays.
• Fax: 202–493–2251. hereinafter as ‘‘the MCAI’’), to correct an
5 61 93 36 96; fax: +33 5 61 93 45 80; email:
For service information identified in unsafe condition for the specified
airworthiness.A330-A340@airbus.com;
Internet http://www.airbus.com. You may this NPRM, contact Turbomeca S.A., products. The MCAI states:
view this service information at the FAA, 40220 Tarnos, France; phone: 33 (0)5 59 Some cases of divergent rubbing between
Transport Airplane Directorate, 1601 Lind 74 40 00; fax: 33 (0)5 59 74 45 15. You the piston shaft small diameter labyrinth and
Avenue SW., Renton, WA. For information the rear bearing support have been reported.
may view this service information at the
on the availability of this material at the This condition, if not corrected, could lead
FAA, call 425–227–1221. FAA, Engine & Propeller Directorate, to an uncommanded engine in-flight
1200 District Avenue, Burlington, MA. shutdown.
Issued in Renton, Washington, on February For information on the availability of
19, 2016. You may obtain further information
this material at the FAA, call 781–238–
Dorr M. Anderson,
7125. by examining the MCAI in the AD
Acting Manager, Transport Airplane docket on the Internet at http://
Directorate, Aircraft Certification Service. Examining the AD Docket www.regulations.gov by searching for
[FR Doc. 2016–04290 Filed 2–29–16; 8:45 am] You may examine the AD docket on and locating Docket No. FAA–2016–
BILLING CODE 4910–13–P the Internet at http:// 2859.
www.regulations.gov by searching for Related Service Information
and locating Docket No. FAA–2016–
DEPARTMENT OF TRANSPORTATION Turbomeca S.A. has issued
2859; or in person at the Docket
Mandatory Service Bulletin (MSB) No.
Federal Aviation Administration Operations office between 9 a.m. and 5
292 72 1357, Version B, dated
p.m., Monday through Friday, except
November 12, 2015. The MSB describes
14 CFR Part 39 Federal holidays. The AD docket
procedures for installing a post-
contains this proposed AD, the
[Docket No. FAA–2016–2859; Directorate
modification (mod) TU357 gas generator
mandatory continuing airworthiness
Identifier 2016–NE–04–AD] module (M03). This service information
information (MCAI), the regulatory
is reasonably available because the
RIN 2120–AA64 evaluation, any comments received, and
interested parties have access to it
other information. The address for the
through their normal course of business
asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
Airworthiness Directives; Turbomeca Docket Office (phone: 800–647–5527) is
or by the means identified in the
S.A. Turboshaft Engines in the ADDRESSES section. Comments
ADDRESSES section of this NPRM.
will be available in the AD docket
AGENCY: Federal Aviation FAA’s Determination and Requirements
shortly after receipt.
Administration (FAA), DOT. of This Proposed AD
ACTION: Notice of proposed rulemaking FOR FURTHER INFORMATION CONTACT:
(NPRM). Philip Haberlen, Aerospace Engineer, This product has been approved by
Engine Certification Office, FAA, Engine the aviation authority of France, and is
SUMMARY: We propose to adopt a new & Propeller Directorate, 1200 District approved for operation in the United
airworthiness directive (AD) for all Avenue, Burlington, MA 01803; phone: States. Pursuant to our bilateral
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Document Created: 2018-02-02 14:59:47
Document Modified: 2018-02-02 14:59:47
| Category | Regulatory Information | |
| Collection | Federal Register | |
| sudoc Class | AE 2.7: GS 4.107: AE 2.106: | |
| Publisher | Office of the Federal Register, National Archives and Records Administration | |
| Section | Proposed Rules | |
| Action | Notice of proposed rulemaking (NPRM). | |
| Dates | We must receive comments on this proposed AD by April 15, 2016. | |
| Contact | Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone: 425-227-1138; fax: 425-227-1149. | |
| FR Citation | 81 FR 10540 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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