Airworthiness Directives; Airbus Airplanes, 3510-3513 [2015-00993]

Download as PDF 3510 Federal Register / Vol. 80, No. 15 / Friday, January 23, 2015 / Proposed Rules ACO, to make those findings. For a repair method to be approved, the repair must meet the certification basis of the airplane, and the approval must specifically refer to this AD. (4) AMOCs approved for AD 2004–13–02, Amendment 39–13682 (69 FR 35237, June 24, 2004), are approved as AMOCs for the corresponding provisions of paragraphs (g) and (h) of this AD. (o) Related Information (1) For more information about this AD, contact Bill Ashforth, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: 425–917–6432; fax: 425–917–6590; email: Bill.Ashforth@faa.gov. (2) For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H–65, Seattle, WA 98124–2207; telephone 206– 544–5000, extension 1; fax 206–766–5680; Internet https://www.myboeingfleet.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. Issued in Renton, Washington, on January 14, 2015. John P. Piccola, Jr., Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015–00955 Filed 1–22–15; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2014–1043; Directorate Identifier 2013–NM–079–AD] RIN 2120–AA64 Examining the AD Docket Airworthiness Directives; Airbus Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for all Airbus Model A330–200, A330–200 Freighter, and A330–300 series airplanes; and Model A340–200 and A340–300 series airplanes. This proposed AD was prompted by reports of cracked support strut body ends at a certain frame location of the trimmable horizontal stabilizer (THS). This proposed AD would require repetitive inspections for cracking of the strut ends of the THS support located at a certain frame in the tail cone, and replacement if necessary; and emcdonald on DSK67QTVN1PROD with PROPOSALS SUMMARY: VerDate Sep<11>2014 19:56 Jan 22, 2015 Jkt 235001 reinstallation or installation of reinforcing clamps on certain strut ends. We are proposing this AD to detect and correct cracked support strut body ends of the THS, which could lead to the loss of all four THS support struts and which would make the remaining structure unable to carry limit loads, resulting in the loss of the horizontal tail plane. DATES: We must receive comments on this proposed AD by March 9, 2015. 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 proposed AD, contact Airbus SAS, Airworthiness Office—EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 80; email airworthiness.A330–A340@airbus.com; 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. You may examine the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2014– 1043; 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 PO 00000 Frm 00013 Fmt 4702 Sfmt 4702 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–2014–1043; Directorate Identifier 2013–NM–079–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD based on those comments. We will post all comments we receive, without change, to http:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2014–0068, dated March 18, 2014 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition on all Airbus Model A330–200, A330–200 Freighter, and A330–300 series airplanes; and Model A340–200 and A340–300 series airplanes. The MCAI states: During scheduled maintenance on A330 aeroplanes, several Trimmable Horizontal Stabilizer (THS) support struts at frame (FR) 91 were found cracked at strut body ends. The THS is supported and articulated at FR 91 by four struts to fix the hinges (Y-bolts) and keep the structural integrity in lateral direction. Analysis revealed that cracks can reduce ability of the support struts to carry specified tension loads. This condition, if not detected and corrected, could lead to the loss of all four THS support struts at FR91, which would make the remaining structure unable to carry limit loads, resulting in the loss of Horizontal Tail Plane. A340–500/600 aeroplanes are not affected by this [EASA] AD as different material is used on THS support struts. To address this potentially unsafe condition, EASA issued AD 2013–0076 [http://ad.easa.europa.eu/blob/easa_ad_ 2013_0076_superseded.pdf/AD-2013-0076_1] to require repetitive special detailed inspections [high frequency eddy current (HFEC) inspections for cracking] of all 8 strut ends of the THS support located at FR91 in the tail cone and, depending on findings, replacement of THS support struts. That E:\FR\FM\23JAP1.SGM 23JAP1 Federal Register / Vol. 80, No. 15 / Friday, January 23, 2015 / Proposed Rules [EASA] AD also required, for aeroplanes on which Airbus Modification 203493 had not been embodied in production, or Airbus Service Bulletin (SB) A330–53–3204 or SB A340–53–4199, as applicable, has not been embodied in service, the installation of a clamping device on each support strut end to stop growth of possible cracks (crack stopper function) in order to secure integrity of the struts. Since issuance of EASA AD 2013–0076, it has been discovered that several aeroplanes are fitted with another strut configuration ´ (SARMA Strut) [Societe Anonyme de ´ ´ Recherche Mecanique Appliquee] than the TAC (Technical Airborne Components Industries) strut, which caused the other strut not to be considered. Consequently, Airbus revised Airbus SB A330–53–3206 and SB A340–53–4208, accordingly in order to add a one-time [HFEC] inspection [for cracking] for SARMA struts and in case of finding to replace it with a TAC strut and thereafter to accomplish repetitive inspections and EASA issued AD 2013–0219 [http:// ad.easa.europa.eu/blob/easa_ad_2013_0219_ superseded.pdf/AD-2013-0219_1], which is superseded, and required accomplishment of the instructions as specified in the latest revision of each SB, as applicable. Since issuance of EASA AD 2013–0219, based on the reporting received from operators, it has been determined that repetitive inspections are also to be accomplished for aeroplanes equipped with SARMA strut. Airbus introduced that inspection in the applicable SB at revision 3. For the reasons described above, this [EASA] AD retains the requirements of EASA AD 2013–0219, which is superseded, and requires accomplishment of repetitive [HFEC] inspective inspection [for cracking] for aeroplanes equipped with SARMA strut. This [EASA] AD is considered as an interim action, pending the development of a terminating action. emcdonald on DSK67QTVN1PROD with PROPOSALS 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–2014– 1043. Related Service Information Airbus has issued the following service information: • Airbus Service Bulletin A330–53– 3206, Revision 03, dated February 28, 2014. This service information describes procedures for inspections for cracking of the strut ends of the THS support located in the airplane tail cone for Model A330 airplanes. • Airbus Service Bulletin A340–53– 4208, Revision 03, dated February 28, 2014. This service information describes procedures for inspections for cracking of the strut ends of the THS support located in the airplane tail cone for Model A340 airplanes. The actions described in this service information are intended to correct the unsafe condition identified in the MCAI. VerDate Sep<11>2014 19:56 Jan 22, 2015 Jkt 235001 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. Differences Between This Proposed AD and the MCAI or Service Information Although EASA Airworthiness Directive 2014–0068, dated March 18, 2014, Airbus Service Bulletin A330–53– 3206, Revision 03, dated February 28, 2014, and Airbus Service Bulletin A340–53–4208, Revision 03, dated February 28, 2014, allow further flight after certain cracks are found during compliance with the proposed action, paragraph (j)(2) of this proposed AD would require that any cracked THS support strut be replaced with a new or serviceable TAC strut before further flight. Interim Action We consider this proposed AD interim action. If final action is later identified, we might consider further rulemaking then. Costs of Compliance We estimate that this proposed AD affects 84 airplanes of U.S. registry. We also estimate that it would take about 9 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 $64,260, or $765 per product. We have received no definitive data that would enable us to provide cost estimates for the on-condition replacement specified in this proposed AD. We estimate that any necessary follow-on strut reinforcements would take about 2 work-hours and require parts costing $5,680, for a cost of $5,850 per product. We have no way of determining the number of aircraft that might need this action. According to the manufacturer, some of the costs of 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. As a PO 00000 Frm 00014 Fmt 4702 Sfmt 4702 3511 result, we have included all costs in our cost estimate. 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 1. The authority citation for part 39 continues to read as follows: ■ E:\FR\FM\23JAP1.SGM 23JAP1 3512 Federal Register / Vol. 80, No. 15 / Friday, January 23, 2015 / Proposed Rules Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): ■ Airbus: Docket No. FAA–2014–1043; Directorate Identifier 2013–NM–079–AD. (a) Comments Due Date We must receive comments by March 9, 2015. (b) Affected ADs None. (c) Applicability This AD applies to the airplanes identified in paragraphs (c)(1), (c)(2), and (c)(3) of this AD, certificated in any category, all manufacturer serial numbers. (1) Airbus Model A330–201, –202, –203, –223, –223F, –243, and –243F airplanes. (2) Airbus Model A330–301, –302, –303, –321, –322, –323, –341, –342, and –343 airplanes. (3) Airbus Model A340–211, –212, –213, –311, –312, and –313 airplanes. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Reason This AD was prompted by reports of cracked support strut body ends at a certain frame location of the trimmable horizontal stabilizer (THS). We are issuing this AD to detect and correct cracked support strut body ends of the THS, which could lead to the loss of all four THS support struts and which would make the remaining structure unable to carry limit loads, resulting in the loss of the horizontal tail plane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. emcdonald on DSK67QTVN1PROD with PROPOSALS (g) Definition of Strut Types ´ For the purpose of this AD, a Societe ´ Anonyme de Recherche Mecanique ´ Appliquee (SARMA) strut is a strut on which the diameter of the strut end is lower than 43 millimeters. All other struts are Technical Airborne Components Industries (TAC) struts. (h) Repetitive Inspections of TAC Strut Ends At the applicable time specified in paragraph (i) of this AD, do a high frequency eddy current (HFEC) inspection for cracking of all TAC strut ends of the THS support located at frame (FR) 91 in the tail cone, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330– 53–3206, Revision 03, dated February 28, 2014; or Airbus Service Bulletin A340–53– 4208, Revision 03, dated February 28, 2014; as applicable. Repeat the inspection thereafter at intervals not to exceed 42 months or 20,000 flight hours, whichever occurs first. For airplanes on which Airbus Modification 203493 has been embodied in production, or Airbus Service Bulletin A330– VerDate Sep<11>2014 19:56 Jan 22, 2015 Jkt 235001 53–3204 or Airbus Service Bulletin A340– 53–4199, as applicable, has been embodied in service, remove the clamp from each strut end before accomplishing the inspections required by this paragraph. (i) Compliance Times for Paragraphs (h) and (k) of This AD Do the inspections required by paragraphs (h) and (k) of this AD at the applicable times specified in paragraphs (i)(1), (i)(2), and (i)(3) of this AD. (1) For Model A330 series airplanes having manufacturer serial numbers 012 through 209 inclusive, and Model A340 series airplanes having manufacturer serial numbers 002 through 210 inclusive: Within 6 months after the effective date of this AD. (2) For Model A330 series airplanes having manufacturer serial numbers 211 through 422 inclusive, and Model A340 series airplanes having manufacturer serial numbers 212 through 447 inclusive: Within 24 months after the effective date of this AD. (3) For Model A330 series airplanes having manufacturer serial numbers 423 and subsequent, and Model A340 series airplanes having manufacturer serial numbers 450 through 955 inclusive: Within 36 months after the effective date of this AD or since the first flight of the airplane, whichever occurs later. (j) Corrective Action for TAC Strut Ends and Installation of Reinforcing Clamps (1) If, during any inspection required by paragraph (h) of this AD, no cracks are found: Before further flight, reinstall or install, as applicable, reinforcing clamps on the strut ends, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330–53–3206, Revision 03, dated February 28, 2014; or Airbus Service Bulletin A340–53–4208, Revision 03, dated February 28, 2014. (2) If, during any inspection required by paragraph (h) of this AD, any crack is found: Before further flight, replace any affected strut with a new or serviceable TAC strut and install reinforcing clamps on the strut end, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330– 53–3206, Revision 03, dated February 28, 2014; or Airbus Service Bulletin A340–53– 4208, Revision 03, dated February 28, 2014; as applicable. (k) Repetitive Inspections of SARMA Strut Ends At the applicable time specified in paragraph (i) of this AD, do an HFEC inspection for cracking of all SARMA strut ends of the THS support located at FR 91 in the tail cone, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330–53–3206, Revision 03, dated February 28, 2014; or Airbus Service Bulletin A340–53–4208, Revision 03, dated February 28, 2014; as applicable. Repeat the inspection thereafter at intervals not to exceed 12 months. (l) Corrective Action for SARMA Strut Ends If any crack is found on a strut end during the inspection required by paragraph (k) of this AD: Before further flight, replace any affected SARMA strut with a new or PO 00000 Frm 00015 Fmt 4702 Sfmt 4702 serviceable TAC strut and install reinforcing clamps on the strut end, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330–53–3206, Revision 03, dated February 28, 2014; or Airbus Service Bulletin A340–53–4208, Revision 03, dated February 28, 2014; as applicable. (m) No Terminating Action Replacement of THS struts on an airplane does not constitute terminating action for the repetitive inspections required by this AD. (n) No Reporting Although Airbus Service Bulletin A330– 53–3206, Revision 03, dated February 28, 2014, and Airbus Service Bulletin A340–53– 4208, Revision 03, dated February 28, 2014, specify to submit certain information to the manufacturer, this AD does not include that requirement. (o) Credit for Previous Actions This paragraph provides credit for actions required by paragraphs (g) through (k) of this AD, if those actions were performed before the effective date of this AD using any of the service information identified in paragraphs (n)(1) through (n)(6) of this AD. This service information is not incorporated by reference in this AD. (1) Airbus Service Bulletin A330–53–3206, dated February 7, 2013. (2) Airbus Service Bulletin A330–53–3206, Revision 01, dated June 10, 2013. (3) Airbus Service Bulletin A330–53–3206, Revision 02, dated August 8, 2013. (4) Airbus Service Bulletin A340–53–4208, dated February 7, 2013. (5) Airbus Service Bulletin A340–53–4208, Revision 01, dated June 10, 2013. (6) Airbus Service Bulletin A340–53–4208, Revision 02, dated August 8, 2013. (p) 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: 9-ANM-116AMOC-REQUESTS@faa.gov. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. The AMOC approval letter must specifically reference this AD. (2) Contacting the Manufacturer: 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 E:\FR\FM\23JAP1.SGM 23JAP1 Federal Register / Vol. 80, No. 15 / Friday, January 23, 2015 / Proposed Rules the European Aviation Safety Agency (EASA); or Airbus’s EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature. (q) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2014–0068, dated March 18, 2014, 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– 2014–1043. (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 airworthiness.A330-A340@airbus.com; 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 January 11, 2015. Jeffrey E. Duven, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015–00993 Filed 1–22–15; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2015–0076; Directorate Identifier 2013–NM–246–AD] RIN 2120–AA64 Airworthiness Directives; Airbus Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for all Airbus Model A330–200, A330–200 Freighter, and A330–300 series airplanes; and Airbus Model A340–200, A340–300, A340–500, and A340–600 series airplanes. This proposed AD was prompted by a report that, during a production flight test, the ram air turbine (RAT) did not pressurize the green hydraulic system. For certain airplanes, this proposed AD would require identification of the part number, serial number, and standard of the RAT pump, RAT module, RAT actuator, and RAT lower gearbox assembly; replacement of the balance weight screw, modification of the emcdonald on DSK67QTVN1PROD with PROPOSALS SUMMARY: VerDate Sep<11>2014 19:56 Jan 22, 2015 Jkt 235001 actuator coil spring, modification of the actuator, an inspection of the anti-stall valve for correct installation in the RAT pump housing; and corrective actions if necessary. For certain other airplanes, this proposed AD would require reidentification or replacement of the RAT module. We are proposing this AD to prevent loss of the impeller function and RAT pump pressurization capability, which, if preceded by a total engine flame-out, could result in the loss of control of the airplane. DATES: We must receive comments on this proposed AD by March 9, 2015. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments. • Fax: (202) 493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. • Hand Delivery: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For Airbus service information identified in this proposed AD, contact Airbus SAS, Airworthiness Office— EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 80; email airworthiness.A330A–340@ airbus.com; Internet http:// www.airbus.com. For Hamilton Sundstrand service information identified in this proposed AD, contact Hamilton Sundstrand, Technical Publications, Mail Stop 302–9, 4747 Harrison Avenue, P.O. Box 7002, Rockford, IL 61125–7002; telephone 860–654–3575; fax 860–998–4564; email tech.solutions@hs.utc.com; Internet http://www.hamiltonsundstrand.com. You may view the referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425 227–1221. Examining the AD Docket You may examine the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2015– 0076; 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 PO 00000 Frm 00016 Fmt 4702 Sfmt 4702 3513 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–2015–0076; Directorate Identifier 2013–NM–246–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD based on those comments. We will post all comments we receive, without change, to http:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2013–0274, dated November 15, 2013 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for all Airbus Model A330–200, A330–200 Freighter, and A330–300 series airplanes; and Airbus Model A340–200, A340–300, A340–500, and A340–600 series airplanes. The MCAI states: During a production flight test of an A330– 300 aeroplane, the Ram Air Turbine (RAT) did not pressurize the green hydraulic system. Investigation revealed that the impeller drive (hex) shaft had a reduced length of engagement with the pump drive shaft. This caused the impeller drive shaft to disengage from the pump and disconnect the impeller. It was determined that the disconnection was the result of internal hex dimensions on the pump impeller shaft, which had been changed in a manufacturing drawing. From the investigation analysis, it was possible to identify a list of affected parts. E:\FR\FM\23JAP1.SGM 23JAP1

Agencies

[Federal Register Volume 80, Number 15 (Friday, January 23, 2015)]
[Proposed Rules]
[Pages 3510-3513]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2015-00993]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-1043; Directorate Identifier 2013-NM-079-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to adopt a new airworthiness directive (AD) for all 
Airbus Model A330-200, A330-200 Freighter, and A330-300 series 
airplanes; and Model A340-200 and A340-300 series airplanes. This 
proposed AD was prompted by reports of cracked support strut body ends 
at a certain frame location of the trimmable horizontal stabilizer 
(THS). This proposed AD would require repetitive inspections for 
cracking of the strut ends of the THS support located at a certain 
frame in the tail cone, and replacement if necessary; and 
reinstallation or installation of reinforcing clamps on certain strut 
ends. We are proposing this AD to detect and correct cracked support 
strut body ends of the THS, which could lead to the loss of all four 
THS support struts and which would make the remaining structure unable 
to carry limit loads, resulting in the loss of the horizontal tail 
plane.

DATES: We must receive comments on this proposed AD by March 9, 2015.

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 proposed AD, contact 
Airbus SAS, Airworthiness Office--EAL, 1 Rond Point Maurice Bellonte, 
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 
93 45 80; email airworthiness.A330-A340@airbus.com; 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-2014-
1043; 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-2014-1043; 
Directorate Identifier 2013-NM-079-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD based on those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2014-0068, dated March 18, 2014 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition on all Airbus Model A330-
200, A330-200 Freighter, and A330-300 series airplanes; and Model A340-
200 and A340-300 series airplanes. The MCAI states:

    During scheduled maintenance on A330 aeroplanes, several 
Trimmable Horizontal Stabilizer (THS) support struts at frame (FR) 
91 were found cracked at strut body ends.
    The THS is supported and articulated at FR 91 by four struts to 
fix the hinges (Y-bolts) and keep the structural integrity in 
lateral direction.
    Analysis revealed that cracks can reduce ability of the support 
struts to carry specified tension loads.
    This condition, if not detected and corrected, could lead to the 
loss of all four THS support struts at FR91, which would make the 
remaining structure unable to carry limit loads, resulting in the 
loss of Horizontal Tail Plane.
    A340-500/600 aeroplanes are not affected by this [EASA] AD as 
different material is used on THS support struts.
    To address this potentially unsafe condition, EASA issued AD 
2013-0076 [http://ad.easa.europa.eu/blob/easa_ad_2013_0076_superseded.pdf/AD-2013-0076_1] to require 
repetitive special detailed inspections [high frequency eddy current 
(HFEC) inspections for cracking] of all 8 strut ends of the THS 
support located at FR91 in the tail cone and, depending on findings, 
replacement of THS support struts. That

[[Page 3511]]

[EASA] AD also required, for aeroplanes on which Airbus Modification 
203493 had not been embodied in production, or Airbus Service 
Bulletin (SB) A330-53-3204 or SB A340-53-4199, as applicable, has 
not been embodied in service, the installation of a clamping device 
on each support strut end to stop growth of possible cracks (crack 
stopper function) in order to secure integrity of the struts.
    Since issuance of EASA AD 2013-0076, it has been discovered that 
several aeroplanes are fitted with another strut configuration 
(SARMA Strut) [Societ[eacute] Anonyme de Recherche M[eacute]canique 
Appliqu[eacute]e] than the TAC (Technical Airborne Components 
Industries) strut, which caused the other strut not to be 
considered. Consequently, Airbus revised Airbus SB A330-53-3206 and 
SB A340-53-4208, accordingly in order to add a one-time [HFEC] 
inspection [for cracking] for SARMA struts and in case of finding to 
replace it with a TAC strut and thereafter to accomplish repetitive 
inspections and EASA issued AD 2013-0219 [http://ad.easa.europa.eu/blob/easa_ad_2013_0219_superseded.pdf/AD-2013-0219_1], which is 
superseded, and required accomplishment of the instructions as 
specified in the latest revision of each SB, as applicable.
    Since issuance of EASA AD 2013-0219, based on the reporting 
received from operators, it has been determined that repetitive 
inspections are also to be accomplished for aeroplanes equipped with 
SARMA strut. Airbus introduced that inspection in the applicable SB 
at revision 3.
    For the reasons described above, this [EASA] AD retains the 
requirements of EASA AD 2013-0219, which is superseded, and requires 
accomplishment of repetitive [HFEC] inspective inspection [for 
cracking] for aeroplanes equipped with SARMA strut.
    This [EASA] AD is considered as an interim action, pending the 
development of a terminating action.

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-2014-
1043.

Related Service Information

    Airbus has issued the following service information:
     Airbus Service Bulletin A330-53-3206, Revision 03, dated 
February 28, 2014. This service information describes procedures for 
inspections for cracking of the strut ends of the THS support located 
in the airplane tail cone for Model A330 airplanes.
     Airbus Service Bulletin A340-53-4208, Revision 03, dated 
February 28, 2014. This service information describes procedures for 
inspections for cracking of the strut ends of the THS support located 
in the airplane tail cone for Model A340 airplanes.
    The actions described in this service information are intended to 
correct the unsafe condition identified in the MCAI.

FAA's Determination and Requirements of This Proposed AD

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

Differences Between This Proposed AD and the MCAI or Service 
Information

    Although EASA Airworthiness Directive 2014-0068, dated March 18, 
2014, Airbus Service Bulletin A330-53-3206, Revision 03, dated February 
28, 2014, and Airbus Service Bulletin A340-53-4208, Revision 03, dated 
February 28, 2014, allow further flight after certain cracks are found 
during compliance with the proposed action, paragraph (j)(2) of this 
proposed AD would require that any cracked THS support strut be 
replaced with a new or serviceable TAC strut before further flight.

Interim Action

    We consider this proposed AD interim action. If final action is 
later identified, we might consider further rulemaking then.

Costs of Compliance

    We estimate that this proposed AD affects 84 airplanes of U.S. 
registry.
    We also estimate that it would take about 9 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 $64,260, or $765 
per product.
    We have received no definitive data that would enable us to provide 
cost estimates for the on-condition replacement specified in this 
proposed AD.
    We estimate that any necessary follow-on strut reinforcements would 
take about 2 work-hours and require parts costing $5,680, for a cost of 
$5,850 per product. We have no way of determining the number of 
aircraft that might need this action.
    According to the manufacturer, some of the costs of 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. As a result, we have included all costs in our cost 
estimate.

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:


[[Page 3512]]


    Authority:  49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive (AD):

Airbus: Docket No. FAA-2014-1043; Directorate Identifier 2013-NM-
079-AD.

(a) Comments Due Date

    We must receive comments by March 9, 2015.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to the airplanes identified in paragraphs 
(c)(1), (c)(2), and (c)(3) of this AD, certificated in any category, 
all manufacturer serial numbers.
    (1) Airbus Model A330-201, -202, -203, -223, -223F, -243, and -
243F airplanes.
    (2) Airbus Model A330-301, -302, -303, -321, -322, -323, -341, -
342, and -343 airplanes.
    (3) Airbus Model A340-211, -212, -213, -311, -312, and -313 
airplanes.

(d) Subject

    Air Transport Association (ATA) of America Code 53, Fuselage.

(e) Reason

    This AD was prompted by reports of cracked support strut body 
ends at a certain frame location of the trimmable horizontal 
stabilizer (THS). We are issuing this AD to detect and correct 
cracked support strut body ends of the THS, which could lead to the 
loss of all four THS support struts and which would make the 
remaining structure unable to carry limit loads, resulting in the 
loss of the horizontal tail plane.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Definition of Strut Types

    For the purpose of this AD, a Societ[eacute] Anonyme de 
Recherche M[eacute]canique Appliqu[eacute]e (SARMA) strut is a strut 
on which the diameter of the strut end is lower than 43 millimeters. 
All other struts are Technical Airborne Components Industries (TAC) 
struts.

(h) Repetitive Inspections of TAC Strut Ends

    At the applicable time specified in paragraph (i) of this AD, do 
a high frequency eddy current (HFEC) inspection for cracking of all 
TAC strut ends of the THS support located at frame (FR) 91 in the 
tail cone, in accordance with the Accomplishment Instructions of 
Airbus Service Bulletin A330-53-3206, Revision 03, dated February 
28, 2014; or Airbus Service Bulletin A340-53-4208, Revision 03, 
dated February 28, 2014; as applicable. Repeat the inspection 
thereafter at intervals not to exceed 42 months or 20,000 flight 
hours, whichever occurs first. For airplanes on which Airbus 
Modification 203493 has been embodied in production, or Airbus 
Service Bulletin A330-53-3204 or Airbus Service Bulletin A340-53-
4199, as applicable, has been embodied in service, remove the clamp 
from each strut end before accomplishing the inspections required by 
this paragraph.

(i) Compliance Times for Paragraphs (h) and (k) of This AD

    Do the inspections required by paragraphs (h) and (k) of this AD 
at the applicable times specified in paragraphs (i)(1), (i)(2), and 
(i)(3) of this AD.
    (1) For Model A330 series airplanes having manufacturer serial 
numbers 012 through 209 inclusive, and Model A340 series airplanes 
having manufacturer serial numbers 002 through 210 inclusive: Within 
6 months after the effective date of this AD.
    (2) For Model A330 series airplanes having manufacturer serial 
numbers 211 through 422 inclusive, and Model A340 series airplanes 
having manufacturer serial numbers 212 through 447 inclusive: Within 
24 months after the effective date of this AD.
    (3) For Model A330 series airplanes having manufacturer serial 
numbers 423 and subsequent, and Model A340 series airplanes having 
manufacturer serial numbers 450 through 955 inclusive: Within 36 
months after the effective date of this AD or since the first flight 
of the airplane, whichever occurs later.

(j) Corrective Action for TAC Strut Ends and Installation of 
Reinforcing Clamps

    (1) If, during any inspection required by paragraph (h) of this 
AD, no cracks are found: Before further flight, reinstall or 
install, as applicable, reinforcing clamps on the strut ends, in 
accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A330-53-3206, Revision 03, dated February 28, 2014; or 
Airbus Service Bulletin A340-53-4208, Revision 03, dated February 
28, 2014.
    (2) If, during any inspection required by paragraph (h) of this 
AD, any crack is found: Before further flight, replace any affected 
strut with a new or serviceable TAC strut and install reinforcing 
clamps on the strut end, in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A330-53-3206, Revision 03, 
dated February 28, 2014; or Airbus Service Bulletin A340-53-4208, 
Revision 03, dated February 28, 2014; as applicable.

(k) Repetitive Inspections of SARMA Strut Ends

    At the applicable time specified in paragraph (i) of this AD, do 
an HFEC inspection for cracking of all SARMA strut ends of the THS 
support located at FR 91 in the tail cone, in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A330-53-3206, 
Revision 03, dated February 28, 2014; or Airbus Service Bulletin 
A340-53-4208, Revision 03, dated February 28, 2014; as applicable. 
Repeat the inspection thereafter at intervals not to exceed 12 
months.

(l) Corrective Action for SARMA Strut Ends

    If any crack is found on a strut end during the inspection 
required by paragraph (k) of this AD: Before further flight, replace 
any affected SARMA strut with a new or serviceable TAC strut and 
install reinforcing clamps on the strut end, in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A330-53-3206, 
Revision 03, dated February 28, 2014; or Airbus Service Bulletin 
A340-53-4208, Revision 03, dated February 28, 2014; as applicable.

(m) No Terminating Action

    Replacement of THS struts on an airplane does not constitute 
terminating action for the repetitive inspections required by this 
AD.

(n) No Reporting

    Although Airbus Service Bulletin A330-53-3206, Revision 03, 
dated February 28, 2014, and Airbus Service Bulletin A340-53-4208, 
Revision 03, dated February 28, 2014, specify to submit certain 
information to the manufacturer, this AD does not include that 
requirement.

(o) Credit for Previous Actions

    This paragraph provides credit for actions required by 
paragraphs (g) through (k) of this AD, if those actions were 
performed before the effective date of this AD using any of the 
service information identified in paragraphs (n)(1) through (n)(6) 
of this AD. This service information is not incorporated by 
reference in this AD.
    (1) Airbus Service Bulletin A330-53-3206, dated February 7, 
2013.
    (2) Airbus Service Bulletin A330-53-3206, Revision 01, dated 
June 10, 2013.
    (3) Airbus Service Bulletin A330-53-3206, Revision 02, dated 
August 8, 2013.
    (4) Airbus Service Bulletin A340-53-4208, dated February 7, 
2013.
    (5) Airbus Service Bulletin A340-53-4208, Revision 01, dated 
June 10, 2013.
    (6) Airbus Service Bulletin A340-53-4208, Revision 02, dated 
August 8, 2013.

(p) 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: 9-ANM-116-AMOC-REQUESTS@faa.gov. Before using any 
approved AMOC, notify your appropriate principal inspector, or 
lacking a principal inspector, the manager of the local flight 
standards district office/certificate holding district office. The 
AMOC approval letter must specifically reference this AD.
    (2) Contacting the Manufacturer: 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

[[Page 3513]]

the European Aviation Safety Agency (EASA); or Airbus's EASA Design 
Organization Approval (DOA). If approved by the DOA, the approval 
must include the DOA-authorized signature.

(q) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2014-0068, dated March 18, 2014, 
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-2014-1043.
    (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 airworthiness.A330-A340@airbus.com; 
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 January 11, 2015.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-00993 Filed 1-22-15; 8:45 am]
BILLING CODE 4910-13-P