82 FR 32503 - Airworthiness Directives; Airbus Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 82, Issue 134 (July 14, 2017)
Federal Aviation Administration
Federal Register Volume 82, Issue 134 (July 14, 2017)
| Page Range | 32503-32507 | |
| FR Document | 2017-14590 |
[Federal Register Volume 82, Number 134 (Friday, July 14, 2017)] [Proposed Rules] [Pages 32503-32507] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2017-14590] ----------------------------------------------------------------------- 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). ----------------------------------------------------------------------- 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: [email protected]; Internet: http://www.airbus.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221. Examining the AD Docket You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-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: [email protected]. 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: [email protected]; Internet: http://www.airbus.com. You may view this service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221. Issued in Renton, Washington, on 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
![32504 Federal Register / Vol. 82, No. 134 / Friday, July 14, 2017 / Proposed Rules
30, West Building Ground Floor, Room substantive verbal contact we receive development (with FAA approval),
W12–140, 1200 New Jersey Avenue SE., about this proposed AD. while providing operators with certainty
Washington, DC 20590. regarding the LOV applicable to their
Discussion
• Hand Delivery: Deliver to Mail airplanes.
address above between 9 a.m. and 5 Fatigue damage can occur locally, in On August 24, 2009, we issued AD
p.m., Monday through Friday, except small areas or structural design details, 2009–18–16, Amendment 39–16012 (74
Federal holidays. or globally, in widespread areas. FR 46342, September 9, 2009) (‘‘AD
For service information identified in Multiple-site damage is widespread 2009–18–16’’), for certain Airbus Model
this NPRM, contact Airbus SAS, damage that occurs in a large structural A310–203, –204, –221, –222, –304,
Airworthiness Office—EAW, 1 Rond element such as a single rivet line of a –322, –324, and –325 airplanes. AD
Point Maurice Bellonte, 31707 Blagnac lap splice joining two large skin panels. 2009–18–16 was prompted by an
Cedex, France; telephone: +33 5 61 93 Widespread damage can also occur in identification of a structural
36 96; fax: +33 5 61 93 44 51; email: multiple elements such as adjacent modification that falls within the scope
account.airworth-eas@airbus.com; frames or stringers. Multiple-site of the work related to the extension of
Internet: http://www.airbus.com. You damage and multiple-element damage the service life of the affected airplanes
may view this referenced service cracks are typically too small initially to and widespread fatigue damage
information at the FAA, Transport be reliably detected with normal evaluations. AD 2009–18–16 requires
Airplane Directorate, 1601 Lind Avenue inspection methods. Without inspecting by rotating probe for cracking
SW., Renton, WA. For information on intervention, these cracks will grow, of fastener holes H1 through H29 on
the availability of this material at the and eventually compromise the frames (FRs) 43 through 46 inclusive,
FAA, call 425–227–1221. structural integrity of the airplane. This and inspecting fastener holes H1
condition is known as widespread through H29 on FRs 43 through 46
Examining the AD Docket fatigue damage. It is associated with inclusive, to determine the edge
You may examine the AD docket on general degradation of large areas of distance of the fastener hole, and
the Internet at http:// structure with similar structural details corrective actions if necessary. We
www.regulations.gov by searching for and stress levels. As an airplane ages, issued AD 2009–18–16 to prevent
and locating Docket No. FAA–2017– widespread fatigue damage (WFD) will fatigue cracking of the frame foot run-
0695; or in person at the Docket likely occur, and will certainly occur if outs, which could lead to rupture of the
Management Facility between 9 a.m. the airplane is operated long enough frame foot and cracking in adjacent
and 5 p.m., Monday through Friday, without any intervention. frames and skin, and which could result
except Federal holidays. The AD docket The FAA’s WFD final rule (75 FR
in reduced structural integrity of the
69746, November 15, 2010) became
contains this proposed AD, the fuselage.
effective on January 14, 2011. The WFD Since we issued AD 2009–18–16, the
regulatory evaluation, any comments
rule requires certain actions to prevent manufacturer has conducted a new
received, and other information. The
structural failure due to WFD investigation as part of the WFD
street address for the Docket Operations
throughout the operational life of program and determined that the
office (telephone: 800–647–5527) is in
certain existing transport category compliance times must be reduced. The
the ADDRESSES section. Comments will
airplanes and all of these airplanes that European Aviation Safety Agency
be available in the AD docket shortly
will be certificated in the future. For
after receipt. (EASA), which is the Technical Agent
existing and future airplanes subject to
FOR FURTHER INFORMATION CONTACT: Dan for the Member States of the European
the WFD rule, the rule requires that
Rodina, Aerospace Engineer, Union, has issued EASA AD 2016–0197,
DAHs establish a limit of validity (LOV)
International Branch, ANM–116, dated October 5, 2016 (referred to after
of the engineering data that support the
Transport Airplane Directorate, FAA, this as the Mandatory Continuing
structural maintenance program.
1601 Lind Avenue SW., Renton, WA Airworthiness Information, or ‘‘the
Operators affected by the WFD rule may
98057–3356; telephone 425–227–2125; MCAI’’), for all Airbus Model A310–
not fly an airplane beyond its LOV,
fax 425–227–1149. 203, –204, –221, –222, –304, –322, –324,
unless an extended LOV is approved.
The WFD rule (75 FR 69746, and –325 airplanes. EASA AD 2016–
SUPPLEMENTARY INFORMATION:
November 15, 2010) does not require 0197 supersedes EASA AD 2008–0212,
Comments Invited dated December 4, 2008. EASA AD
identifying and developing maintenance
We invite you to send any written actions if the DAHs can show that such 2008–0212 was the MCAI referred to in
relevant data, views, or arguments about actions are not necessary to prevent FAA AD 2009–18–16. The new MCAI
this proposal. Send your comments to WFD before the airplane reaches the states:
an address listed under the ADDRESSES LOV. Many LOVs, however, do depend Within the scope of work related to the
section. Include ‘‘Docket No. FAA– on accomplishment of future extension of the service life of A310 design
2017–0695; Directorate Identifier 2016– maintenance actions. As stated in the and widespread fatigue damage evaluations,
DGAC [Direction Générale de l’Aviation
NM–173–AD’’ at the beginning of your WFD rule, any maintenance actions Civile] France issued AD F–2005–078 (EASA
comments. We specifically invite necessary to reach the LOV will be approval 2005–3957) [which corresponds to
comments on the overall regulatory, mandated by airworthiness directives FAA AD 2006–02–06, Amendment 39–14458
economic, environmental, and energy through separate rulemaking actions. (71 FR 3214, January 20, 2006)] to require a
aspects of this proposed AD. We will In the context of WFD, this action is structural modification, as defined in Airbus
mstockstill on DSK30JT082PROD with PROPOSALS
consider all comments received by the necessary to enable DAHs to propose Service Bulletin (SB) A310–53–2124 (Airbus
closing date and may amend this LOVs that allow operators the longest modification 13023), to increase the service
proposed AD based on those comments. operational lives for their airplanes, and life of junctions of center box upper frame
bases to upper fuselage arches.
We will post all comments we still ensure that WFD will not occur. The threshold timescales for
receive, without change, to http:// This approach allows for an accomplishment of the tasks as defined in SB
www.regulations.gov, including any implementation strategy that provides A310–53–2124 were refined and reduced.
personal information you provide. We flexibility to DAHs in determining the Consequently, EASA issued AD 2007–0238
will also post a report summarizing each timing of service information to require compliance with Revision 01 of SB
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![Federal Register / Vol. 82, No. 134 / Friday, July 14, 2017 / Proposed Rules 32505
A310–53–2124 at the reduced compliance FAA’s Determination and Requirements Authority for This Rulemaking
times, superseding (the requirements of) of This Proposed AD
DGAC France AD F–2005–078. Subsequently, Title 49 of the United States Code
Airbus identified reference material that was This product has been approved by specifies the FAA’s authority to issue
erroneously introduced into Airbus SB the aviation authority of another rules on aviation safety. Subtitle I,
A310–53–2124 Revision 01. As a result, the country, and is approved for operation section 106, describes the authority of
SB instructions could not be accomplished in the United States. Pursuant to our the FAA Administrator. ‘‘Subtitle VII:
properly. Operators that tried to apply SB bilateral agreement with the State of Aviation Programs,’’ describes in more
A310–53–2124 at Revision 01 had to contact Design Authority, we have been notified detail the scope of the Agency’s
Airbus; see also Airbus SBIT [service bulletin of the unsafe condition described in the
information telex] ref. 914.0135/08, dated 03 authority.
March 2008.
MCAI and service information We are issuing this rulemaking under
Consequently, [EASA] AD 2007–0238 was referenced above. We are proposing this the authority described in ‘‘Subtitle VII,
revised to exclude reference to Airbus SB AD because we evaluated all pertinent Part A, Subpart III, Section 44701:
A310–53–2124 Revision 01 and to require information and determined an unsafe General requirements.’’ Under that
accomplishment of the task(s) as described in condition exists and is likely to exist or section, Congress charges the FAA with
the original SB A310–53–2124 instead, develop on other products of these same promoting safe flight of civil aircraft in
although retaining the reduced compliance type designs. air commerce by prescribing regulations
times introduced by [EASA] AD 2007–0238
at original issue. Differences Between This NPRM and for practices, methods, and procedures
EASA AD 2008–0212, superseding [EASA] the MCAI the Administrator finds necessary for
AD 2007–0238R1, was published to refer to safety in air commerce. This regulation
There is a difference between this
Airbus SB A310 53–2124 Revision 02, the is within the scope of that authority
corrected version that was used to meet the
NPRM and the MCAI regarding how the
because it addresses an unsafe condition
requirements of this [EASA] AD. compliance times are stated for the
that is likely to exist or develop on
Since [EASA] AD 2008–0212 was issued, accomplishment of the inspection and
products identified in this rulemaking
new investigations in the frame of the modification specified in paragraph (j)
action.
Widespread Fatigue Damage campaign of this proposed AD. The MCAI states
induced thresholds reduction, and Airbus that the accomplishment of the Regulatory Findings
issued SB A310–53–2124 Revision 03. inspection and modification specified in
For the reason described above, this We determined that this proposed AD
Airbus Service Bulletin A310–53–2124
[EASA] AD retains the requirements of EASA would not have federalism implications
should be accomplished no later than 6
AD 2008–0212, which is superseded, and under Executive Order 13132. This
months (estimated by projection of
requires accomplishment of modification(s) proposed AD would not have a
within reduced compliance time, as airplane usage) prior to the thresholds
substantial direct effect on the States, on
published in Airbus SB A310–53–2124 specified in the MCAI. Paragraph (j) of
the relationship between the national
Revision 03. this proposed AD specifies that the
Government and the States, or on the
accomplishment of the inspection and
Required actions include a high distribution of power and
modification should be done ‘‘at the
frequency eddy current (HFEC) rotating responsibilities among the various
applicable thresholds specified in table
probe inspection for cracking of certain 3 to the introductory text of paragraph levels of government.
fastener holes on certain frames, and (j) of this AD.’’ The compliance times For the reasons discussed above, I
related investigative and corrective specified in table 3 to the introductory certify this proposed regulation:
actions if necessary; and modification of text of paragraph (j) of this proposed AD 1. Is not a ‘‘significant regulatory
certain fastener holes. Related are based upon the average annual action’’ under Executive Order 12866;
investigative actions include an utilization of the Airbus airplanes 2. Is not a ‘‘significant rule’’ under the
additional HFEC rotating probe identified in paragraph (c) of this DOT Regulatory Policies and Procedures
inspection for cracking of fastener holes proposed AD. Based on this (44 FR 11034, February 26, 1979);
and a check to determine the edge information, we calculated that within 6 3. Will not affect intrastate aviation in
distance of certain holes. Corrective months an Airbus Model A310 series Alaska; and
actions include ream out of cracks and airplane would have accumulated an 4. Will not have a significant
repair. You may examine the MCAI in average of 300 flight cycles and 978 economic impact, positive or negative,
the AD docket on the Internet at http:// flight hours. on a substantial number of small entities
www.regulations.gov by searching for under the criteria of the Regulatory
and locating Docket No. FAA–2017– Costs of Compliance Flexibility Act.
0695. We estimate that this proposed AD
List of Subjects in 14 CFR Part 39
Related Service Information Under 1 affects 8 airplanes of U.S. registry.
We estimate that it would take about Air transportation, Aircraft, Aviation
CFR Part 51
41 work-hours per product to comply safety, Incorporation by reference,
Airbus has issued Airbus Service with the basic requirements of this Safety.
Bulletin A310–53–2124, Revision 03, proposed AD. The average labor rate is
dated December 22, 2014. The service The Proposed Amendment
$85 per work-hour. Required parts
information describes procedures for a would cost about $20,180 per product. Accordingly, under the authority
rototest inspection for cracking between Based on these figures, we estimate the delegated to me by the Administrator,
FR 43 through FR 46 on the center box, cost of this proposed AD on U.S. the FAA proposes to amend 14 CFR part
mstockstill on DSK30JT082PROD with PROPOSALS
and the cold expansion (modification) operators to be $189,320, or $23,665 per 39 as follows:
of the most fatigue sensitive fastener product.
holes. This service information is We have received no definitive data PART 39—AIRWORTHINESS
reasonably available because the that would enable us to provide cost DIRECTIVES
interested parties have access to it estimates for the on-condition actions
through their normal course of business (i.e., additional inspection and ■ 1. The authority citation for part 39
or by the means identified in the modification for certain airplanes) continues to read as follows:
ADDRESSES section. specified in this proposed AD. Authority: 49 U.S.C. 106(g), 40113, 44701.
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![32506 Federal Register / Vol. 82, No. 134 / Friday, July 14, 2017 / Proposed Rules
§ 39.13 [Amended] (e) Reason cracking of fastener holes H1 through H29 on
This AD was prompted by an evaluation by frames 43 through 46, and do all applicable
■ 2. The FAA amends § 39.13 by related investigative and corrective actions,
the design approval holder indicating that
removing Airworthiness Directive (AD) the junctions of center box upper frame bases in accordance with the Accomplishment
2009–18–16, Amendment 39–16012 (74 to the upper fuselage arches are subject to Instructions of Airbus Service Bulletin A310–
FR 46342, September 9, 2009), and widespread fatigue damage and that the 53–2124, Revision 03, dated December 22,
adding the following new AD: compliance threshold for the modification in 2014, except as required by paragraph (h) of
AD 2009–18–16 should be reduced. We are this AD. If no cracking is found and the edge
Airbus: Docket No. FAA–2017–0695;
issuing this AD to prevent fatigue cracking of distance of the fastener hole is equal to or
Directorate Identifier 2016–NM–173–AD. the frame foot run-outs, which could lead to greater than the distance specified in the
(a) Comments Due Date rupture of the frame foot and cracking in Accomplishment Instructions of Airbus
adjacent frames and skin, and which could Service Bulletin A310–53–2124, Revision 03,
We must receive comments by August 28, result in reduced structural integrity of the dated December 22, 2014, before further
2017. airplane. flight, do the modification (cold expansion)
(b) Affected ADs (f) Compliance of the affected fastener holes, in accordance
with the Accomplishment Instructions of
This AD replaces AD 2009–18–16, Comply with this AD within the
Airbus Service Bulletin A310–53–2124,
Amendment 39–16012 (74 FR 46342, compliance times specified, unless already
Revision 03, dated December 22, 2014. Do all
September 9, 2009) (‘‘AD 2009–18–16’’). done.
applicable related investigative and
(c) Applicability (g) Inspections and Modification of Fastener corrective actions before further flight.
Holes (1) Inspect at the applicable time specified
This AD applies to Airbus Model A310– in table 1 to paragraph (g)(1) of this AD, or
Except for airplanes modified before the
203, –204, –221, –222, –304, –322, –324 and effective date of this AD using the within 24 months after the effective date of
–325 airplanes; certificated in any category; Accomplishment Instructions of Airbus this AD, whichever occurs later. To establish
all serial numbers. Service Bulletin A310–53–2124: At the times the average flight time (AFT), take the
specified in paragraph (g)(1) of this AD but accumulated flight time (counted from the
(d) Subject take-off up to the landing) and divide by the
no later than the times specified in paragraph
Air Transport Association (ATA) of (g)(2) of this AD, do a high frequency eddy number of accumulated flight cycles. This
America Code 53, Fuselage. current (HFEC) rotating probe inspection for 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 ................................. Prior to accumulation of 19,600 flight cycles or 39,200 flight hours
since first flight of the airplane, whichever occurs first.
Model A310–304, –322, –324, and –325 airplanes with an AFT of less Prior to accumulation of 22,400 flight cycles or 62,700 flight hours
than or equal to 3.16 flight hours. since first flight of the airplane, whichever occurs first.
Model A310–304, –322, –324, and –325 airplanes with an AFT greater Prior to accumulation of 19,800 flight cycles or 99,200 flight hours
than 3.16 flight hours. since first flight of the airplane, whichever occurs first.
(2) Inspect at the later of the times airplanes with an AFT equal to or less than time, take the accumulated flight time
specified in paragraphs (g)(2)(i) and (g)(2)(ii) 3.17 flight hours are short range airplanes. (counted from the take-off up to the landing)
of this AD. Airbus Model A310–304, –322, –324, and and divide by the number of accumulated
(i) At the applicable time indicated in table –325 airplanes with an AFT exceeding 3.17 flight cycles. This provides the AFT per flight
2 to paragraph (g)(2)(i) of this AD. Airbus flight hours are long range airplanes. For this cycle.
Model A310–304, –322, –324, and –325 paragraph, to establish the average flight
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
Model A310–304, –322, –324 and –325 long range airplanes ............... 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
Model A310–203, –204, –221, and A310–222 ........................................ 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
mstockstill on DSK30JT082PROD with PROPOSALS
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 (h) Service Information Exception specifies to contact Airbus for appropriate
hours after October 14, 2009 (the effective Where Airbus Service Bulletin A310–53– action, and specifies that action as ‘‘RC’’
date of AD 2009–18–16), whichever occurs (Required for Compliance): Before further
2124, Revision 03, dated December 22, 2014,
first. flight, accomplish corrective actions in
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![Federal Register / Vol. 82, No. 134 / Friday, July 14, 2017 / Proposed Rules 32507
accordance with the procedures specified in Manager, International Branch, ANM–116, AD, contact the Manager, International
paragraph (l)(2) of this AD. Transport Airplane Directorate, FAA; or the Branch, ANM–116, Transport Airplane
European Aviation Safety Agency (EASA); or Directorate, FAA; or EASA; or Airbus’s EASA
(i) Airplanes Modified per Revision 01 of the Airbus’s EASA Design Organization
Service Information DOA for additional inspection and
Approval (DOA). modification instructions. Accomplish those
For airplanes modified before the effective
date of this AD using Airbus Service Bulletin (j) Additional Inspection and Modification instructions within the compliance times
A310–53–2124, Revision 01, dated May 3, Except as provided by paragraphs (j)(1) and provided by the Manager, International
2007: Unless already accomplished, before (j)(2) of this AD, as applicable: At the Branch, ANM–116, Transport Airplane
further flight, do applicable corrective applicable thresholds specified in table 3 to Directorate, FAA; or EASA; or Airbus’s EASA
actions using a method approved by the the introductory text of paragraph (j) of this 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
Affected airplanes modification specified in Airbus Service Bulletin A310–53–2124)
Inspection threshold Modification threshold
Model A310–203, –204, –221, and –222 air- 30,200 flight cycles or 68,122 flight hours ....... 45,500 flight cycles or 102,722 flight hours
planes.
Model A310–304, –322, –324, and –325 air- 37,000 flight cycles or 103,522 flight hours ..... 55,700 flight cycles or 155,722 flight hours
planes.
(1) For Model A310–203, –204, –221, and a manufacturer, the action must be information on the availability of this
–222 airplanes: No additional inspection is accomplished using a method approved by material at the FAA, call 425–227–1221.
required if the inspection and modification the Manager, International Branch, ANM–
Issued in Renton, Washington, on June 29,
specified in Airbus Service Bulletin A310– 116, Transport Airplane Directorate, FAA; or
2017.
53–2124 was done after the accumulation of EASA; or Airbus’s EASA DOA. If approved
29,500 flight cycles and 70,900 flight hours by the DOA, the approval must include the Michael Kaszycki,
since the first flight of the airplane. DOA-authorized signature. Acting Manager, Transport Airplane
(2) For Model A310–304, –322, –324, and (3) Required for Compliance (RC): Except Directorate, Aircraft Certification Service.
–325 airplanes: No additional inspection is as provided by paragraph (h) of this AD: If [FR Doc. 2017–14590 Filed 7–13–17; 8:45 am]
required if the inspection and modification any service information contains procedures BILLING CODE 4910–13–P
specified in Airbus Service Bulletin A310– or tests that are identified as RC, those
53–2124 was done after the accumulation of procedures and tests must be done to comply
22,600 flight cycles and 69,400 flight hours with this AD; any procedures or tests that are
since the first flight of the airplane. not identified as RC are recommended. Those
DEPARTMENT OF TRANSPORTATION
(k) Credit for Previous Actions procedures and tests that are not identified
as RC may be deviated from using accepted
Federal Aviation Administration
This paragraph provides credit for the methods in accordance with the operator’s
actions required by paragraph (g) of this AD, maintenance or inspection program without 14 CFR Part 39
if those actions were performed before the
obtaining approval of an AMOC, provided [Docket No. FAA–2017–0630; Directorate
effective date of this AD using the
the procedures and tests identified as RC can Identifier 2017–NM–058–AD]
Accomplishment Instructions of Airbus
be done and the airplane can be put back in
Service Bulletin A310–53–2124, dated April
an airworthy condition. Any substitutions or RIN 2120–AA64
4, 2005; or Airbus Service Bulletin A310–53–
2124, Revision 02, dated May 22, 2008. changes to procedures or tests identified as
RC require approval of an AMOC. Airworthiness Directives; The Boeing
(l) Other FAA AD Provisions Company Airplanes
(m) Related Information
The following provisions also apply to this
(1) Refer to Mandatory Continuing AGENCY: Federal Aviation
AD:
(1) Alternative Methods of Compliance Airworthiness Information (MCAI) EASA AD Administration (FAA), DOT.
(AMOCs): The Manager, International 2016–0197, dated October 5, 2016, for related ACTION: Notice of proposed rulemaking
Branch, ANM–116, Transport Airplane information. This MCAI may be found in the (NPRM).
Directorate, FAA, has the authority to AD docket on the Internet at http://
approve AMOCs for this AD, if requested www.regulations.gov by searching for and SUMMARY: We propose to adopt a new
using the procedures found in 14 CFR 39.19. locating Docket No. FAA–2017–0695. airworthiness directive (AD) for certain
In accordance with 14 CFR 39.19, send your (2) For more information about this AD,
The Boeing Company Model 777–200,
request to your principal inspector or local contact Dan Rodina, Aerospace Engineer,
International Branch, ANM–116, Transport –200LR, –300, and –300ER series
Flight Standards District Office, as
appropriate. If sending information directly Airplane Directorate, FAA, 1601 Lind airplanes. This proposed AD was
to the International Branch, send it to the Avenue SW., Renton, WA 98057–3356; prompted by reports of corrosion in the
attention of the person identified in telephone: 425–227–2125; fax: 425–227– aft fuselage. This proposed AD would
paragraph (m)(2) of this AD. Information may 1149. require a one-time review of the
be emailed to: 9-ANM-116-AMOC- (3) For service information identified in operator’s maintenance procedures,
mstockstill on DSK30JT082PROD with PROPOSALS
REQUESTS@faa.gov. Before using any this AD, contact Airbus SAS, Airworthiness repetitive detailed internal and external
approved AMOC, notify your appropriate Office—EAW, 1 Rond Point Maurice inspections for corrosion or cracking,
principal inspector, or lacking a principal Bellonte, 31707 Blagnac Cedex, France;
and applicable on-condition actions.
inspector, the manager of the local flight telephone: +33 5 61 93 36 96; fax: +33 5 61
standards district office/certificate holding 93 44 51; email: account.airworth-eas@ This proposed AD would also include
district office. airbus.com; Internet: http://www.airbus.com. an optional terminating action for the
(2) Contacting the Manufacturer: As of the You may view this service information at the inspections. We are proposing this AD
effective date of this AD, for any requirement FAA, Transport Airplane Directorate, 1601 to address the unsafe condition on these
in this AD to obtain corrective actions from Lind Avenue SW., Renton, WA. For products.
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Document Created: 2018-10-24 11:16:13
Document Modified: 2018-10-24 11:16:13
| Category | Regulatory Information | |
| Collection | Federal Register | |
| sudoc Class | AE 2.7: GS 4.107: AE 2.106: | |
| Publisher | Office of the Federal Register, National Archives and Records Administration | |
| Section | Proposed Rules | |
| Action | Notice of proposed rulemaking (NPRM). | |
| Dates | We must receive comments on this proposed AD by August 28, 2017. | |
| 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. | |
| FR Citation | 82 FR 32503 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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