Airworthiness Directives; Airbus Airplanes, 32503-32507 [2017-14590]

Download as PDF Federal Register / Vol. 82, No. 134 / Friday, July 14, 2017 / Proposed Rules specified compliance time unless it has already been accomplished prior to that time. (e) Compliance You are responsible for performing each action required by this AD within the (1) Before further flight, amend the EC120B Rotorcraft Flight Manual Supplement (RFMS) for the emergency flotation gear Aerazur, by (2) Before each flight over water: (i) Perform a functional check to determine whether flight over water is permitted under the Limitations section in paragraph (f)(1) of this AD. For purposes of this AD, ‘‘flight over water’’ means flight beyond the power-off gliding distance from shore. ‘‘Shore’’ is an area of land adjacent to the water and above the high water mark but does not include land area that is intermittently under water. The actions required by this paragraph may be performed by the owner/operator (pilot) holding at least a private pilot certificate, and must be entered into the aircraft records showing compliance with this AD in accordance with 14 CFR 43.9 (a)(1) through (4) and 14 CFR 91.417(a)(2)(v). The record must be maintained as required by 14 CFR 91.417, 121.380, or 135.439. (ii) If the LACU fails the functional check required by paragraph (f)(2)(i) of this AD, place a placard over the ‘‘float arm’’ pushbutton that reads ‘‘INOP.’’ (3) Within 300 hours time-in-service, replace float arm pushbutton P/N 045004A111A with float arm pushbutton P/N 304–2500–00. Installing float arm pushbutton P/N 304–2500–00 is terminating action for the functional check and placard required by paragraphs (f)(2)(i) and (f)(2)(ii) of this AD. (4) Do not install float arm pushbutton P/N 045004A111A on any helicopter. operating any aircraft complying with this AD through an AMOC. (g) Alternative Methods of Compliance (AMOCs) (1) The Manager, Safety Management Group, FAA, may approve AMOCs for this AD. Send your proposal to: George Schwab, Aviation Safety Engineer, Safety Management Group, Rotorcraft Directorate, FAA, 10101 Hillwood Pkwy, Fort Worth, TX 76177; telephone (817) 222–5110; email 9-ASWFTW-AMOC-Requests@faa.gov. (2) For operations conducted under a 14 CFR part 119 operating certificate or under 14 CFR part 91, subpart K, we suggest that you notify your principal inspector, or lacking a principal inspector, the manager of the local flight standards district office or certificate holding district office before VerDate Sep<11>2014 17:18 Jul 13, 2017 Jkt 241001 (f) Required Actions (1) Airbus Helicopters Emergency Alert Service Bulletin No. 04A007, Revision 1, dated June 30, 2016, and Airbus Helicopters Alert Service Bulletin No. EC120–31A008, dated June 30, 2016, which are not incorporated by reference, contain additional information about the subject of this AD. For service information identified in this AD, contact Airbus Helicopters, 2701 N. Forum Drive, Grand Prairie, TX 75052; telephone (972) 641–0000 or (800) 232–0323; fax (972) 641–3775; or at http:// www.airbushelicopters.com/website/ technical-expert/. You may review a copy of the service information at the FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N–321, Fort Worth, TX 76177. (2) The subject of this AD is addressed in European Aviation Safety Agency (EASA) AD No. 2016–0180, dated September 13, 2016. You may view the EASA AD on the Internet at http://www.regulations.gov in the AD Docket. (i) Subject Joint Aircraft Service Component (JASC) Code: 2560 Emergency Equipment. Issued in Fort Worth, Texas, on June 28, 2017. Scott A. Horn, Acting Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 2017–14373 Filed 7–13–17; 8:45 am] PO 00000 Frm 00011 Fmt 4702 Sfmt 4702 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration (h) Additional Information BILLING CODE 4910–13–P inserting a copy of this AD into the Limitations section of the RFMS or by making pen and ink changes to that section to add the information in figure 1 to paragraph (f)(1) of this AD: 14 CFR Part 39 [Docket No. FAA–2017–0695; Directorate Identifier 2016–NM–173–AD] RIN 2120–AA64 Airworthiness Directives; Airbus Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to supersede Airworthiness Directive (AD) 2009–18– 16, for certain Airbus Model A310–203, –204, –221, –222, –304, –322, –324, and –325 airplanes. AD 2009–18–16 requires an inspection for cracking of certain fastener holes on certain frames, and related investigative and corrective actions if necessary; and modification of certain fastener holes. Since we issued AD 2009–18–16, an evaluation by the design approval holder (DAH) indicated that the compliance times should be reduced. We are proposing this AD to address the unsafe condition on these products. SUMMARY: We must receive comments on this proposed AD by August 28, 2017. 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– DATES: E:\FR\FM\14JYP1.SGM 14JYP1 EP13JY17.002</GPH> mstockstill on DSK30JT082PROD with PROPOSALS (d) Comments Due Date We must receive comments by September 12, 2017. 32503 32504 Federal Register / Vol. 82, No. 134 / Friday, July 14, 2017 / Proposed Rules 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. • Hand Delivery: Deliver to Mail address above 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—EAW, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone: +33 5 61 93 36 96; fax: +33 5 61 93 44 51; email: account.airworth-eas@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–2017– 0695; 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: Dan Rodina, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–2125; fax 425–227–1149. SUPPLEMENTARY INFORMATION: mstockstill on DSK30JT082PROD with PROPOSALS Comments Invited We invite you to send any written relevant data, views, or arguments about this proposal. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA– 2017–0695; Directorate Identifier 2016– NM–173–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 VerDate Sep<11>2014 17:18 Jul 13, 2017 Jkt 241001 substantive verbal contact we receive about this proposed AD. Discussion Fatigue damage can occur locally, in small areas or structural design details, or globally, in widespread areas. Multiple-site damage is widespread damage that occurs in a large structural element such as a single rivet line of a lap splice joining two large skin panels. Widespread damage can also occur in multiple elements such as adjacent frames or stringers. Multiple-site damage and multiple-element damage cracks are typically too small initially to be reliably detected with normal inspection methods. Without intervention, these cracks will grow, and eventually compromise the structural integrity of the airplane. This condition is known as widespread fatigue damage. It is associated with general degradation of large areas of structure with similar structural details and stress levels. As an airplane ages, widespread fatigue damage (WFD) will likely occur, and will certainly occur if the airplane is operated long enough without any intervention. The FAA’s WFD final rule (75 FR 69746, November 15, 2010) became effective on January 14, 2011. The WFD rule requires certain actions to prevent structural failure due to WFD throughout the operational life of certain existing transport category airplanes and all of these airplanes that will be certificated in the future. For existing and future airplanes subject to the WFD rule, the rule requires that DAHs establish a limit of validity (LOV) of the engineering data that support the structural maintenance program. Operators affected by the WFD rule may not fly an airplane beyond its LOV, unless an extended LOV is approved. The WFD rule (75 FR 69746, November 15, 2010) does not require identifying and developing maintenance actions if the DAHs can show that such actions are not necessary to prevent WFD before the airplane reaches the LOV. Many LOVs, however, do depend on accomplishment of future maintenance actions. As stated in the WFD rule, any maintenance actions necessary to reach the LOV will be mandated by airworthiness directives through separate rulemaking actions. In the context of WFD, this action is necessary to enable DAHs to propose LOVs that allow operators the longest operational lives for their airplanes, and still ensure that WFD will not occur. This approach allows for an implementation strategy that provides flexibility to DAHs in determining the timing of service information PO 00000 Frm 00012 Fmt 4702 Sfmt 4702 development (with FAA approval), while providing operators with certainty regarding the LOV applicable to their airplanes. On August 24, 2009, we issued AD 2009–18–16, Amendment 39–16012 (74 FR 46342, September 9, 2009) (‘‘AD 2009–18–16’’), for certain Airbus Model A310–203, –204, –221, –222, –304, –322, –324, and –325 airplanes. AD 2009–18–16 was prompted by an identification of a structural modification that falls within the scope of the work related to the extension of the service life of the affected airplanes and widespread fatigue damage evaluations. AD 2009–18–16 requires inspecting by rotating probe for cracking of fastener holes H1 through H29 on frames (FRs) 43 through 46 inclusive, and inspecting fastener holes H1 through H29 on FRs 43 through 46 inclusive, to determine the edge distance of the fastener hole, and corrective actions if necessary. We issued AD 2009–18–16 to prevent fatigue cracking of the frame foot runouts, which could lead to rupture of the frame foot and cracking in adjacent frames and skin, and which could result in reduced structural integrity of the fuselage. Since we issued AD 2009–18–16, the manufacturer has conducted a new investigation as part of the WFD program and determined that the compliance times must be reduced. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA AD 2016–0197, dated October 5, 2016 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), for all Airbus Model A310– 203, –204, –221, –222, –304, –322, –324, and –325 airplanes. EASA AD 2016– 0197 supersedes EASA AD 2008–0212, dated December 4, 2008. EASA AD 2008–0212 was the MCAI referred to in FAA AD 2009–18–16. The new MCAI states: Within the scope of work related to the extension of the service life of A310 design and widespread fatigue damage evaluations, ´ ´ DGAC [Direction Generale de l’Aviation Civile] France issued AD F–2005–078 (EASA approval 2005–3957) [which corresponds to FAA AD 2006–02–06, Amendment 39–14458 (71 FR 3214, January 20, 2006)] to require a structural modification, as defined in Airbus Service Bulletin (SB) A310–53–2124 (Airbus modification 13023), to increase the service life of junctions of center box upper frame bases to upper fuselage arches. The threshold timescales for accomplishment of the tasks as defined in SB A310–53–2124 were refined and reduced. Consequently, EASA issued AD 2007–0238 to require compliance with Revision 01 of SB E:\FR\FM\14JYP1.SGM 14JYP1 Federal Register / Vol. 82, No. 134 / Friday, July 14, 2017 / Proposed Rules A310–53–2124 at the reduced compliance times, superseding (the requirements of) DGAC France AD F–2005–078. Subsequently, Airbus identified reference material that was erroneously introduced into Airbus SB A310–53–2124 Revision 01. As a result, the SB instructions could not be accomplished properly. Operators that tried to apply SB A310–53–2124 at Revision 01 had to contact Airbus; see also Airbus SBIT [service bulletin information telex] ref. 914.0135/08, dated 03 March 2008. Consequently, [EASA] AD 2007–0238 was revised to exclude reference to Airbus SB A310–53–2124 Revision 01 and to require accomplishment of the task(s) as described in the original SB A310–53–2124 instead, although retaining the reduced compliance times introduced by [EASA] AD 2007–0238 at original issue. EASA AD 2008–0212, superseding [EASA] AD 2007–0238R1, was published to refer to Airbus SB A310 53–2124 Revision 02, the corrected version that was used to meet the requirements of this [EASA] AD. Since [EASA] AD 2008–0212 was issued, new investigations in the frame of the Widespread Fatigue Damage campaign induced thresholds reduction, and Airbus issued SB A310–53–2124 Revision 03. For the reason described above, this [EASA] AD retains the requirements of EASA AD 2008–0212, which is superseded, and requires accomplishment of modification(s) within reduced compliance time, as published in Airbus SB A310–53–2124 Revision 03. mstockstill on DSK30JT082PROD with PROPOSALS Required actions include a high frequency eddy current (HFEC) rotating probe inspection for cracking of certain fastener holes on certain frames, and related investigative and corrective actions if necessary; and modification of certain fastener holes. Related investigative actions include an additional HFEC rotating probe inspection for cracking of fastener holes and a check to determine the edge distance of certain holes. Corrective actions include ream out of cracks and repair. 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–2017– 0695. Related Service Information Under 1 CFR Part 51 Airbus has issued Airbus Service Bulletin A310–53–2124, Revision 03, dated December 22, 2014. The service information describes procedures for a rototest inspection for cracking between FR 43 through FR 46 on the center box, and the cold expansion (modification) of the most fatigue sensitive fastener holes. 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. VerDate Sep<11>2014 17:18 Jul 13, 2017 Jkt 241001 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 NPRM and the MCAI There is a difference between this NPRM and the MCAI regarding how the compliance times are stated for the accomplishment of the inspection and modification specified in paragraph (j) of this proposed AD. The MCAI states that the accomplishment of the inspection and modification specified in Airbus Service Bulletin A310–53–2124 should be accomplished no later than 6 months (estimated by projection of airplane usage) prior to the thresholds specified in the MCAI. Paragraph (j) of this proposed AD specifies that the accomplishment of the inspection and modification should be done ‘‘at the applicable thresholds specified in table 3 to the introductory text of paragraph (j) of this AD.’’ The compliance times specified in table 3 to the introductory text of paragraph (j) of this proposed AD are based upon the average annual utilization of the Airbus airplanes identified in paragraph (c) of this proposed AD. Based on this information, we calculated that within 6 months an Airbus Model A310 series airplane would have accumulated an average of 300 flight cycles and 978 flight hours. Costs of Compliance We estimate that this proposed AD affects 8 airplanes of U.S. registry. We estimate that it would take about 41 work-hours per product to comply with the basic requirements of this proposed AD. The average labor rate is $85 per work-hour. Required parts would cost about $20,180 per product. Based on these figures, we estimate the cost of this proposed AD on U.S. operators to be $189,320, or $23,665 per product. We have received no definitive data that would enable us to provide cost estimates for the on-condition actions (i.e., additional inspection and modification for certain airplanes) specified in this proposed AD. PO 00000 Frm 00013 Fmt 4702 Sfmt 4702 32505 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: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. E:\FR\FM\14JYP1.SGM 14JYP1 32506 § 39.13 Federal Register / Vol. 82, No. 134 / Friday, July 14, 2017 / Proposed Rules [Amended] 2. The FAA amends § 39.13 by removing Airworthiness Directive (AD) 2009–18–16, Amendment 39–16012 (74 FR 46342, September 9, 2009), and adding the following new AD: ■ Airbus: Docket No. FAA–2017–0695; Directorate Identifier 2016–NM–173–AD. (a) Comments Due Date We must receive comments by August 28, 2017. (b) Affected ADs (e) Reason This AD was prompted by an evaluation by the design approval holder indicating that the junctions of center box upper frame bases to the upper fuselage arches are subject to widespread fatigue damage and that the compliance threshold for the modification in AD 2009–18–16 should be reduced. We are issuing this AD to prevent fatigue cracking of the frame foot run-outs, which could lead to rupture of the frame foot and cracking in adjacent frames and skin, and which could result in reduced structural integrity of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. This AD replaces AD 2009–18–16, Amendment 39–16012 (74 FR 46342, September 9, 2009) (‘‘AD 2009–18–16’’). (c) Applicability This AD applies to Airbus Model A310– 203, –204, –221, –222, –304, –322, –324 and –325 airplanes; certificated in any category; all serial numbers. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (g) Inspections and Modification of Fastener Holes Except for airplanes modified before the effective date of this AD using the Accomplishment Instructions of Airbus Service Bulletin A310–53–2124: At the times specified in paragraph (g)(1) of this AD but no later than the times specified in paragraph (g)(2) of this AD, do a high frequency eddy current (HFEC) rotating probe inspection for cracking of fastener holes H1 through H29 on frames 43 through 46, and do all applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A310– 53–2124, Revision 03, dated December 22, 2014, except as required by paragraph (h) of this AD. If no cracking is found and the edge distance of the fastener hole is equal to or greater than the distance specified in the Accomplishment Instructions of Airbus Service Bulletin A310–53–2124, Revision 03, dated December 22, 2014, before further flight, do the modification (cold expansion) of the affected fastener holes, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A310–53–2124, Revision 03, dated December 22, 2014. Do all applicable related investigative and corrective actions before further flight. (1) Inspect at the applicable time specified in table 1 to paragraph (g)(1) of this AD, or within 24 months after the effective date of this AD, whichever occurs later. To establish the average flight time (AFT), take the accumulated flight time (counted from the take-off up to the landing) and divide by the number of accumulated flight cycles. This gives the AFT per flight cycle. TABLE 1 TO PARAGRAPH (G)(1) OF THIS AD—NEW COMPLIANCE TIMES Affected airplanes Compliance time Model A310–203, –204, –221, and –222 airplanes ................................. Model A310–304, –322, –324, and –325 airplanes with an AFT of less than or equal to 3.16 flight hours. Model A310–304, –322, –324, and –325 airplanes with an AFT greater than 3.16 flight hours. (2) Inspect at the later of the times specified in paragraphs (g)(2)(i) and (g)(2)(ii) of this AD. (i) At the applicable time indicated in table 2 to paragraph (g)(2)(i) of this AD. Airbus Model A310–304, –322, –324, and –325 Prior to accumulation of 19,600 flight cycles or since first flight of the airplane, whichever occurs Prior to accumulation of 22,400 flight cycles or since first flight of the airplane, whichever occurs Prior to accumulation of 19,800 flight cycles or since first flight of the airplane, whichever occurs airplanes with an AFT equal to or less than 3.17 flight hours are short range airplanes. Airbus Model A310–304, –322, –324, and –325 airplanes with an AFT exceeding 3.17 flight hours are long range airplanes. For this paragraph, to establish the average flight 39,200 flight hours first. 62,700 flight hours first. 99,200 flight hours first. time, take the accumulated flight time (counted from the take-off up to the landing) and divide by the number of accumulated flight cycles. This provides the AFT per flight cycle. TABLE 2 TO PARAGRAPH (G)(2)(I) OF THIS AD—RETAINED COMPLIANCE TIMES Affected airplanes Inspection/modification compliance time, whichever occurs later Model A310–304, –322, –324 and –325 short range airplanes .............. Prior to accumulation of 26,500 flight cycles or 74,300 flight hours since first flight of the airplane, whichever occurs first Within 3,000 flight cycles after October 14, 2009 (the effective date of AD 2009–18–16), without exceeding 29,200 flight cycles or 81,800 flight hours since first flight, whichever occurs first Prior to accumulation of 23,400 flight cycles or 117,100 flight hours since first flight of the airplane, whichever occurs first Within 3,000 flight cycles after October 14, 2009 (the effective date of AD 2009–18–16), without exceeding 25,800 flight cycles or 129,000 flight hours since first flight, whichever occurs first Prior to accumulation of 23,400 flight cycles or 46,800 flight hours since first flight of the airplane, whichever occurs first Within 3,000 flight cycles after October 14, 2009 (the effective date of AD 2009–18–16), without exceeding 28,800 flight cycles or 57,700 flight hours since first flight, whichever occurs first Model A310–304, –322, –324 and –325 long range airplanes ............... mstockstill on DSK30JT082PROD with PROPOSALS Model A310–203, –204, –221, and A310–222 ........................................ (ii) Within 500 flight cycles or 800 flight hours after October 14, 2009 (the effective date of AD 2009–18–16), whichever occurs first. VerDate Sep<11>2014 17:18 Jul 13, 2017 Jkt 241001 (h) Service Information Exception Where Airbus Service Bulletin A310–53– 2124, Revision 03, dated December 22, 2014, PO 00000 Frm 00014 Fmt 4702 Sfmt 4702 specifies to contact Airbus for appropriate action, and specifies that action as ‘‘RC’’ (Required for Compliance): Before further flight, accomplish corrective actions in E:\FR\FM\14JYP1.SGM 14JYP1 Federal Register / Vol. 82, No. 134 / Friday, July 14, 2017 / Proposed Rules accordance with the procedures specified in paragraph (l)(2) of this AD. (i) Airplanes Modified per Revision 01 of the Service Information For airplanes modified before the effective date of this AD using Airbus Service Bulletin A310–53–2124, Revision 01, dated May 3, 2007: Unless already accomplished, before further flight, do applicable corrective actions 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). (j) Additional Inspection and Modification Except as provided by paragraphs (j)(1) and (j)(2) of this AD, as applicable: At the applicable thresholds specified in table 3 to the introductory text of paragraph (j) of this 32507 AD, contact the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA; or EASA; or Airbus’s EASA DOA for additional inspection and modification instructions. Accomplish those instructions within the compliance times provided by the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA; or EASA; or Airbus’s EASA DOA. TABLE 3 TO THE INTRODUCTORY TEXT OF PARAGRAPH (J) OF THIS AD—ADDITIONAL INSPECTION AND MODIFICATION Thresholds (Flight cycles or flight hours, whichever occurs first after accomplishment of the inspection and modification specified in Airbus Service Bulletin A310–53–2124) Affected airplanes Inspection threshold Modification threshold Model A310–203, –204, –221, and –222 airplanes. Model A310–304, –322, –324, and –325 airplanes. 30,200 flight cycles or 68,122 flight hours ....... 45,500 flight cycles or 102,722 flight hours 37,000 flight cycles or 103,522 flight hours ..... 55,700 flight cycles or 155,722 flight hours (1) For Model A310–203, –204, –221, and –222 airplanes: No additional inspection is required if the inspection and modification specified in Airbus Service Bulletin A310– 53–2124 was done after the accumulation of 29,500 flight cycles and 70,900 flight hours since the first flight of the airplane. (2) For Model A310–304, –322, –324, and –325 airplanes: No additional inspection is required if the inspection and modification specified in Airbus Service Bulletin A310– 53–2124 was done after the accumulation of 22,600 flight cycles and 69,400 flight hours since the first flight of the airplane. 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 provided by paragraph (h) 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. information on the availability of this material at the FAA, call 425–227–1221. mstockstill on DSK30JT082PROD with PROPOSALS (k) 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 Accomplishment Instructions of Airbus Service Bulletin A310–53–2124, dated April 4, 2005; or Airbus Service Bulletin A310–53– 2124, Revision 02, dated May 22, 2008. (l) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the International Branch, send it to the attention of the person identified in paragraph (m)(2) of this AD. Information may be emailed to: 9-ANM-116-AMOCREQUESTS@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. (2) Contacting the Manufacturer: As of the effective date of this AD, for any requirement in this AD to obtain corrective actions from VerDate Sep<11>2014 17:18 Jul 13, 2017 Jkt 241001 (m) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA AD 2016–0197, dated October 5, 2016, 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–2017–0695. (2) For more information about this AD, contact Dan Rodina, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone: 425–227–2125; fax: 425–227– 1149. (3) For service information identified in this AD, contact Airbus SAS, Airworthiness Office—EAW, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone: +33 5 61 93 36 96; fax: +33 5 61 93 44 51; email: account.airworth-eas@ 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 PO 00000 Frm 00015 Fmt 4702 Sfmt 4702 Issued in Renton, Washington, on June 29, 2017. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2017–14590 Filed 7–13–17; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2017–0630; Directorate Identifier 2017–NM–058–AD] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for certain The Boeing Company Model 777–200, –200LR, –300, and –300ER series airplanes. This proposed AD was prompted by reports of corrosion in the aft fuselage. This proposed AD would require a one-time review of the operator’s maintenance procedures, repetitive detailed internal and external inspections for corrosion or cracking, and applicable on-condition actions. This proposed AD would also include an optional terminating action for the inspections. We are proposing this AD to address the unsafe condition on these products. SUMMARY: E:\FR\FM\14JYP1.SGM 14JYP1

Agencies

[Federal Register Volume 82, Number 134 (Friday, July 14, 2017)]
[Proposed Rules]
[Pages 32503-32507]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-14590]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2017-0695; Directorate Identifier 2016-NM-173-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 supersede Airworthiness Directive (AD) 2009-18-
16, for certain Airbus Model A310-203, -204, -221, -222, -304, -322, -
324, and -325 airplanes. AD 2009-18-16 requires an inspection for 
cracking of certain fastener holes on certain frames, and related 
investigative and corrective actions if necessary; and modification of 
certain fastener holes. Since we issued AD 2009-18-16, an evaluation by 
the design approval holder (DAH) indicated that the compliance times 
should be reduced. We are proposing this AD to address the unsafe 
condition on these products.

DATES: We must receive comments on this proposed AD by August 28, 2017.

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-

[[Page 32504]]

30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue 
SE., Washington, DC 20590.
     Hand Delivery: Deliver to Mail address above 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--EAW, 1 Rond Point Maurice Bellonte, 31707 
Blagnac Cedex, France; telephone: +33 5 61 93 36 96; fax: +33 5 61 93 
44 51; email: account.airworth-eas@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-2017-
0695; 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: Dan Rodina, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-2125; 
fax 425-227-1149.

SUPPLEMENTARY INFORMATION: 

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposal. Send your comments to an address listed 
under the ADDRESSES section. Include ``Docket No. FAA-2017-0695; 
Directorate Identifier 2016-NM-173-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

    Fatigue damage can occur locally, in small areas or structural 
design details, or globally, in widespread areas. Multiple-site damage 
is widespread damage that occurs in a large structural element such as 
a single rivet line of a lap splice joining two large skin panels. 
Widespread damage can also occur in multiple elements such as adjacent 
frames or stringers. Multiple-site damage and multiple-element damage 
cracks are typically too small initially to be reliably detected with 
normal inspection methods. Without intervention, these cracks will 
grow, and eventually compromise the structural integrity of the 
airplane. This condition is known as widespread fatigue damage. It is 
associated with general degradation of large areas of structure with 
similar structural details and stress levels. As an airplane ages, 
widespread fatigue damage (WFD) will likely occur, and will certainly 
occur if the airplane is operated long enough without any intervention.
    The FAA's WFD final rule (75 FR 69746, November 15, 2010) became 
effective on January 14, 2011. The WFD rule requires certain actions to 
prevent structural failure due to WFD throughout the operational life 
of certain existing transport category airplanes and all of these 
airplanes that will be certificated in the future. For existing and 
future airplanes subject to the WFD rule, the rule requires that DAHs 
establish a limit of validity (LOV) of the engineering data that 
support the structural maintenance program. Operators affected by the 
WFD rule may not fly an airplane beyond its LOV, unless an extended LOV 
is approved.
    The WFD rule (75 FR 69746, November 15, 2010) does not require 
identifying and developing maintenance actions if the DAHs can show 
that such actions are not necessary to prevent WFD before the airplane 
reaches the LOV. Many LOVs, however, do depend on accomplishment of 
future maintenance actions. As stated in the WFD rule, any maintenance 
actions necessary to reach the LOV will be mandated by airworthiness 
directives through separate rulemaking actions.
    In the context of WFD, this action is necessary to enable DAHs to 
propose LOVs that allow operators the longest operational lives for 
their airplanes, and still ensure that WFD will not occur. This 
approach allows for an implementation strategy that provides 
flexibility to DAHs in determining the timing of service information 
development (with FAA approval), while providing operators with 
certainty regarding the LOV applicable to their airplanes.
    On August 24, 2009, we issued AD 2009-18-16, Amendment 39-16012 (74 
FR 46342, September 9, 2009) (``AD 2009-18-16''), for certain Airbus 
Model A310-203, -204, -221, -222, -304, -322, -324, and -325 airplanes. 
AD 2009-18-16 was prompted by an identification of a structural 
modification that falls within the scope of the work related to the 
extension of the service life of the affected airplanes and widespread 
fatigue damage evaluations. AD 2009-18-16 requires inspecting by 
rotating probe for cracking of fastener holes H1 through H29 on frames 
(FRs) 43 through 46 inclusive, and inspecting fastener holes H1 through 
H29 on FRs 43 through 46 inclusive, to determine the edge distance of 
the fastener hole, and corrective actions if necessary. We issued AD 
2009-18-16 to prevent fatigue cracking of the frame foot run-outs, 
which could lead to rupture of the frame foot and cracking in adjacent 
frames and skin, and which could result in reduced structural integrity 
of the fuselage.
    Since we issued AD 2009-18-16, the manufacturer has conducted a new 
investigation as part of the WFD program and determined that the 
compliance times must be reduced. The European Aviation Safety Agency 
(EASA), which is the Technical Agent for the Member States of the 
European Union, has issued EASA AD 2016-0197, dated October 5, 2016 
(referred to after this as the Mandatory Continuing Airworthiness 
Information, or ``the MCAI''), for all Airbus Model A310-203, -204, -
221, -222, -304, -322, -324, and -325 airplanes. EASA AD 2016-0197 
supersedes EASA AD 2008-0212, dated December 4, 2008. EASA AD 2008-0212 
was the MCAI referred to in FAA AD 2009-18-16. The new MCAI states:

    Within the scope of work related to the extension of the service 
life of A310 design and widespread fatigue damage evaluations, DGAC 
[Direction G[eacute]n[eacute]rale de l'Aviation Civile] France 
issued AD F-2005-078 (EASA approval 2005-3957) [which corresponds to 
FAA AD 2006-02-06, Amendment 39-14458 (71 FR 3214, January 20, 
2006)] to require a structural modification, as defined in Airbus 
Service Bulletin (SB) A310-53-2124 (Airbus modification 13023), to 
increase the service life of junctions of center box upper frame 
bases to upper fuselage arches.
    The threshold timescales for accomplishment of the tasks as 
defined in SB A310-53-2124 were refined and reduced. Consequently, 
EASA issued AD 2007-0238 to require compliance with Revision 01 of 
SB

[[Page 32505]]

A310-53-2124 at the reduced compliance times, superseding (the 
requirements of) DGAC France AD F-2005-078. Subsequently, Airbus 
identified reference material that was erroneously introduced into 
Airbus SB A310-53-2124 Revision 01. As a result, the SB instructions 
could not be accomplished properly. Operators that tried to apply SB 
A310-53-2124 at Revision 01 had to contact Airbus; see also Airbus 
SBIT [service bulletin information telex] ref. 914.0135/08, dated 03 
March 2008.
    Consequently, [EASA] AD 2007-0238 was revised to exclude 
reference to Airbus SB A310-53-2124 Revision 01 and to require 
accomplishment of the task(s) as described in the original SB A310-
53-2124 instead, although retaining the reduced compliance times 
introduced by [EASA] AD 2007-0238 at original issue.
    EASA AD 2008-0212, superseding [EASA] AD 2007-0238R1, was 
published to refer to Airbus SB A310 53-2124 Revision 02, the 
corrected version that was used to meet the requirements of this 
[EASA] AD.
    Since [EASA] AD 2008-0212 was issued, new investigations in the 
frame of the Widespread Fatigue Damage campaign induced thresholds 
reduction, and Airbus issued SB A310-53-2124 Revision 03.
    For the reason described above, this [EASA] AD retains the 
requirements of EASA AD 2008-0212, which is superseded, and requires 
accomplishment of modification(s) within reduced compliance time, as 
published in Airbus SB A310-53-2124 Revision 03.

    Required actions include a high frequency eddy current (HFEC) 
rotating probe inspection for cracking of certain fastener holes on 
certain frames, and related investigative and corrective actions if 
necessary; and modification of certain fastener holes. Related 
investigative actions include an additional HFEC rotating probe 
inspection for cracking of fastener holes and a check to determine the 
edge distance of certain holes. Corrective actions include ream out of 
cracks and repair. 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-2017-0695.

Related Service Information Under 1 CFR Part 51

    Airbus has issued Airbus Service Bulletin A310-53-2124, Revision 
03, dated December 22, 2014. The service information describes 
procedures for a rototest inspection for cracking between FR 43 through 
FR 46 on the center box, and the cold expansion (modification) of the 
most fatigue sensitive fastener holes. 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.

Differences Between This NPRM and the MCAI

    There is a difference between this NPRM and the MCAI regarding how 
the compliance times are stated for the accomplishment of the 
inspection and modification specified in paragraph (j) of this proposed 
AD. The MCAI states that the accomplishment of the inspection and 
modification specified in Airbus Service Bulletin A310-53-2124 should 
be accomplished no later than 6 months (estimated by projection of 
airplane usage) prior to the thresholds specified in the MCAI. 
Paragraph (j) of this proposed AD specifies that the accomplishment of 
the inspection and modification should be done ``at the applicable 
thresholds specified in table 3 to the introductory text of paragraph 
(j) of this AD.'' The compliance times specified in table 3 to the 
introductory text of paragraph (j) of this proposed AD are based upon 
the average annual utilization of the Airbus airplanes identified in 
paragraph (c) of this proposed AD. Based on this information, we 
calculated that within 6 months an Airbus Model A310 series airplane 
would have accumulated an average of 300 flight cycles and 978 flight 
hours.

Costs of Compliance

    We estimate that this proposed AD affects 8 airplanes of U.S. 
registry.
    We estimate that it would take about 41 work-hours per product to 
comply with the basic requirements of this proposed AD. The average 
labor rate is $85 per work-hour. Required parts would cost about 
$20,180 per product. Based on these figures, we estimate the cost of 
this proposed AD on U.S. operators to be $189,320, or $23,665 per 
product.
    We have received no definitive data that would enable us to provide 
cost estimates for the on-condition actions (i.e., additional 
inspection and modification for certain airplanes) specified in this 
proposed AD.

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.

[[Page 32506]]

Sec.  39.13   [Amended]

0
2. The FAA amends Sec.  39.13 by removing Airworthiness Directive (AD) 
2009-18-16, Amendment 39-16012 (74 FR 46342, September 9, 2009), and 
adding the following new AD:

Airbus: Docket No. FAA-2017-0695; Directorate Identifier 2016-NM-
173-AD.

(a) Comments Due Date

    We must receive comments by August 28, 2017.

(b) Affected ADs

    This AD replaces AD 2009-18-16, Amendment 39-16012 (74 FR 46342, 
September 9, 2009) (``AD 2009-18-16'').

(c) Applicability

    This AD applies to Airbus Model A310-203, -204, -221, -222, -
304, -322, -324 and -325 airplanes; certificated in any category; 
all serial numbers.

(d) Subject

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

(e) Reason

    This AD was prompted by an evaluation by the design approval 
holder indicating that the junctions of center box upper frame bases 
to the upper fuselage arches are subject to widespread fatigue 
damage and that the compliance threshold for the modification in AD 
2009-18-16 should be reduced. We are issuing this AD to prevent 
fatigue cracking of the frame foot run-outs, which could lead to 
rupture of the frame foot and cracking in adjacent frames and skin, 
and which could result in reduced structural integrity of the 
airplane.

(f) Compliance

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

(g) Inspections and Modification of Fastener Holes

    Except for airplanes modified before the effective date of this 
AD using the Accomplishment Instructions of Airbus Service Bulletin 
A310-53-2124: At the times specified in paragraph (g)(1) of this AD 
but no later than the times specified in paragraph (g)(2) of this 
AD, do a high frequency eddy current (HFEC) rotating probe 
inspection for cracking of fastener holes H1 through H29 on frames 
43 through 46, and do all applicable related investigative and 
corrective actions, in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A310-53-2124, Revision 03, 
dated December 22, 2014, except as required by paragraph (h) of this 
AD. If no cracking is found and the edge distance of the fastener 
hole is equal to or greater than the distance specified in the 
Accomplishment Instructions of Airbus Service Bulletin A310-53-2124, 
Revision 03, dated December 22, 2014, before further flight, do the 
modification (cold expansion) of the affected fastener holes, in 
accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A310-53-2124, Revision 03, dated December 22, 2014. Do all 
applicable related investigative and corrective actions before 
further flight.
    (1) Inspect at the applicable time specified in table 1 to 
paragraph (g)(1) of this AD, or within 24 months after the effective 
date of this AD, whichever occurs later. To establish the average 
flight time (AFT), take the accumulated flight time (counted from 
the take-off up to the landing) and divide by the number of 
accumulated flight cycles. This gives the AFT per flight cycle.

      Table 1 to Paragraph (g)(1) of This AD--New Compliance Times
------------------------------------------------------------------------
           Affected airplanes                    Compliance time
------------------------------------------------------------------------
Model A310-203, -204, -221, and -222     Prior to accumulation of 19,600
 airplanes.                               flight cycles or 39,200 flight
                                          hours since first flight of
                                          the airplane, whichever occurs
                                          first.
Model A310-304, -322, -324, and -325     Prior to accumulation of 22,400
 airplanes with an AFT of less than or    flight cycles or 62,700 flight
 equal to 3.16 flight hours.              hours since first flight of
                                          the airplane, whichever occurs
                                          first.
Model A310-304, -322, -324, and -325     Prior to accumulation of 19,800
 airplanes with an AFT greater than       flight cycles or 99,200 flight
 3.16 flight hours.                       hours since first flight of
                                          the airplane, whichever occurs
                                          first.
------------------------------------------------------------------------

    (2) Inspect at the later of the times specified in paragraphs 
(g)(2)(i) and (g)(2)(ii) of this AD.
    (i) At the applicable time indicated in table 2 to paragraph 
(g)(2)(i) of this AD. Airbus Model A310-304, -322, -324, and -325 
airplanes with an AFT equal to or less than 3.17 flight hours are 
short range airplanes. Airbus Model A310-304, -322, -324, and -325 
airplanes with an AFT exceeding 3.17 flight hours are long range 
airplanes. For this paragraph, to establish the average flight time, 
take the accumulated flight time (counted from the take-off up to 
the landing) and divide by the number of accumulated flight cycles. 
This provides the AFT per flight cycle.

  Table 2 to Paragraph (g)(2)(i) of This AD--Retained Compliance Times
------------------------------------------------------------------------
                                             Inspection/modification
           Affected airplanes               compliance time, whichever
                                                   occurs later
------------------------------------------------------------------------
Model A310-304, -322, -324 and -325      Prior to accumulation of 26,500
 short range airplanes.                   flight cycles or 74,300 flight
                                          hours since first flight of
                                          the airplane, whichever occurs
                                          first
                                         Within 3,000 flight cycles
                                          after October 14, 2009 (the
                                          effective date of AD 2009-18-
                                          16), without exceeding 29,200
                                          flight cycles or 81,800 flight
                                          hours since first flight,
                                          whichever occurs first
Model A310-304, -322, -324 and -325      Prior to accumulation of 23,400
 long range airplanes.                    flight cycles or 117,100
                                          flight hours since first
                                          flight of the airplane,
                                          whichever occurs first
                                         Within 3,000 flight cycles
                                          after October 14, 2009 (the
                                          effective date of AD 2009-18-
                                          16), without exceeding 25,800
                                          flight cycles or 129,000
                                          flight hours since first
                                          flight, whichever occurs first
Model A310-203, -204, -221, and A310-    Prior to accumulation of 23,400
 222.                                     flight cycles or 46,800 flight
                                          hours since first flight of
                                          the airplane, whichever occurs
                                          first
                                         Within 3,000 flight cycles
                                          after October 14, 2009 (the
                                          effective date of AD 2009-18-
                                          16), without exceeding 28,800
                                          flight cycles or 57,700 flight
                                          hours since first flight,
                                          whichever occurs first
------------------------------------------------------------------------

    (ii) Within 500 flight cycles or 800 flight hours after October 
14, 2009 (the effective date of AD 2009-18-16), whichever occurs 
first.

(h) Service Information Exception

    Where Airbus Service Bulletin A310-53-2124, Revision 03, dated 
December 22, 2014, specifies to contact Airbus for appropriate 
action, and specifies that action as ``RC'' (Required for 
Compliance): Before further flight, accomplish corrective actions in

[[Page 32507]]

accordance with the procedures specified in paragraph (l)(2) of this 
AD.

(i) Airplanes Modified per Revision 01 of the Service Information

    For airplanes modified before the effective date of this AD 
using Airbus Service Bulletin A310-53-2124, Revision 01, dated May 
3, 2007: Unless already accomplished, before further flight, do 
applicable corrective actions 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).

(j) Additional Inspection and Modification

    Except as provided by paragraphs (j)(1) and (j)(2) of this AD, 
as applicable: At the applicable thresholds specified in table 3 to 
the introductory text of paragraph (j) of this AD, contact the 
Manager, International Branch, ANM-116, Transport Airplane 
Directorate, FAA; or EASA; or Airbus's EASA DOA for additional 
inspection and modification instructions. Accomplish those 
instructions within the compliance times provided by the Manager, 
International Branch, ANM-116, Transport Airplane Directorate, FAA; 
or EASA; or Airbus's EASA DOA.

Table 3 to the Introductory Text of Paragraph (j) of This AD--Additional
                       Inspection and Modification
------------------------------------------------------------------------
                                    Thresholds (Flight cycles or flight
                                    hours, whichever occurs first after
                                   accomplishment of the inspection and
                                     modification specified in Airbus
       Affected airplanes             Service Bulletin A310-53-2124)
                                 ---------------------------------------
                                      Inspection         Modification
                                       threshold           threshold
------------------------------------------------------------------------
Model A310-203, -204, -221, and - 30,200 flight       45,500 flight
 222 airplanes.                    cycles or 68,122    cycles or 102,722
                                   flight hours.       flight hours
Model A310-304, -322, -324, and - 37,000 flight       55,700 flight
 325 airplanes.                    cycles or 103,522   cycles or 155,722
                                   flight hours.       flight hours
------------------------------------------------------------------------

    (1) For Model A310-203, -204, -221, and -222 airplanes: No 
additional inspection is required if the inspection and modification 
specified in Airbus Service Bulletin A310-53-2124 was done after the 
accumulation of 29,500 flight cycles and 70,900 flight hours since 
the first flight of the airplane.
    (2) For Model A310-304, -322, -324, and -325 airplanes: No 
additional inspection is required if the inspection and modification 
specified in Airbus Service Bulletin A310-53-2124 was done after the 
accumulation of 22,600 flight cycles and 69,400 flight hours since 
the first flight of the airplane.

(k) 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 Accomplishment Instructions of 
Airbus Service Bulletin A310-53-2124, dated April 4, 2005; or Airbus 
Service Bulletin A310-53-2124, Revision 02, dated May 22, 2008.

(l) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
has the authority to approve AMOCs for this AD, if requested using 
the procedures found in 14 CFR 39.19. In accordance with 14 CFR 
39.19, send your request to your principal inspector or local Flight 
Standards District Office, as appropriate. If sending information 
directly to the International Branch, send it to the attention of 
the person identified in paragraph (m)(2) of this AD. 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.
    (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 provided by 
paragraph (h) 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.

(m) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA AD 2016-0197, dated October 5, 2016, 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-2017-0695.
    (2) For more information about this AD, contact Dan Rodina, 
Aerospace Engineer, International Branch, ANM-116, Transport 
Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-
3356; telephone: 425-227-2125; fax: 425-227-1149.
    (3) For service information identified in this AD, contact 
Airbus SAS, Airworthiness Office--EAW, 1 Rond Point Maurice 
Bellonte, 31707 Blagnac Cedex, France; telephone: +33 5 61 93 36 96; 
fax: +33 5 61 93 44 51; email: account.airworth-eas@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 June 29, 2017.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2017-14590 Filed 7-13-17; 8:45 am]
 BILLING CODE 4910-13-P