80 FR 25249 - Airworthiness Directives; Airbus Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 80, Issue 85 (May 4, 2015)
Federal Aviation Administration
Federal Register Volume 80, Issue 85 (May 4, 2015)
| Page Range | 25249-25254 | |
| FR Document | 2015-10177 |
[Federal Register Volume 80, Number 85 (Monday, May 4, 2015)] [Proposed Rules] [Pages 25249-25254] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2015-10177] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2015-0937; Directorate Identifier 2014-NM-024-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) 2011-24- 05, for certain Airbus Model A330-201, -202, -203, -223, -243, -301, - 302, -303, -321, -322, -323, -341, -342, and -343 airplanes; and Model A340-200 and -300 series airplanes. AD 2011-24-05 currently requires repetitive inspections for cracking of the hole(s) of the horizontal flange of the keel beam, and repair if necessary. Since we issued AD 2011-24-05, a determination was made that the rototest inspection and applicable corrective actions of a certain fastener hole were inadvertently omitted from the requirements in that AD. This proposed AD would change the inspection compliance times, and, for certain airplanes, would add a one-time ultrasonic inspection for cracking at a certain fastener hole. This proposed AD would also provide optional terminating action for the repetitive inspections. We are proposing this AD to detect and correct cracking of the fastener holes, which could result in rupture of the keel beam, and consequent reduced structural integrity of the airplane. DATES: We must receive comments on this proposed AD by June 18, 2015. ADDRESSES: You may send comments by any of the following methods:Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments. Fax: 202-493-2251. Mail: U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590. Hand Delivery: U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this proposed AD, contact Airbus SAS--Airworthiness Office--EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 80; email [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:// [[Page 25250]] www.regulations.gov by searching for and locating Docket No. FAA-2015- 0937; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone 800-647-5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1138; fax 425-227-1149. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ``Docket No. FAA-2015-0937; Directorate Identifier 2014-NM-024-AD'' at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD based on those comments. We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion On November 7, 2011, we issued AD 2011-24-05, Amendment 39-16869 (76 FR 73496, November 29, 2011), for certain Airbus Model A330-201, - 202, -203, -223, -243, -301, -302, -303, -321, -322, -323, -341, -342, and -343 airplanes; and Model A340-200 and -300 series airplanes. AD 2011-24-05 requires actions intended to address the unsafe condition on the products listed above. Since we issued AD 2011-24-05, Amendment 39-16869 (76 FR 73496, November 29, 2011), the European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2014-0010R1, dated May 5, 2014 (referred to after this as the Mandatory Continuing Airworthiness Information, or ``the MCAI''), to correct an unsafe condition for certain Airbus Model A330-201, -202, -203, -223, -243, -301, -302, - 303, -321, -322, -323, -341, -342, and -343 airplanes; and Model A340- 200 and -300 series airplanes. The MCAI states: During A330 and A340 aeroplanes fatigue tests, cracks were detected on the RH [right-hand] and LH [left-hand] sides between the crossing area of the keel beam fitting and the front spar of the Centre Wing Box (CWB). This condition, if not detected and corrected, could lead to keel beam rupture which would affect the area structural integrity of the area. Prompted by this potential unsafe condition, EASA issued AD 2006-0315 [http://ad.easa.europa.eu/blob/easa_ad_2006_0315.pdf/AD_2006-0315] (later revised to R1) to require repetitive special detailed inspections (SDI) [rotating probe inspection for cracking] on the horizontal flange of the keel beam in the area of first fastener hole aft of Frame (FR) 40 in order to maintain the structural integrity of the aeroplane. After that [EASA] AD was issued, EASA issued AD 2010-0024 [which corresponds to FAA AD 2011-24-05, Amendment 39-16869 (76 FR 73496, November 29, 2011)], retaining the inspection requirements of EASA AD 2006-0315R1 [http://ad.easa.europa.eu/blob/easa_ad_2006_0315R1.pdf/AD_2006-0315R1], which was superseded, extending the applicability to aeroplanes with Airbus Mod 49202 embodied, and reducing the inspection thresholds and intervals. Since that [EASA] AD [2010-0024] was issued, a new fatigue and damage tolerance evaluation has been conducted by Airbus, which concluded that due to the aeroplane utilization, the current inspection threshold and intervals have to be modified. In addition, it was determined that the rototest inspection of fastener hole Nr 6, necessary to ensure that no crack was left unrepaired at the time of fastener hold cold working, was inadvertently not included in Revisions 01 and 02 of both Airbus Service Bulletin (SB) A330-57-3098 and A340-57-4106. Prompted by these findings, EASA issued AD 2014-0010 [http://ad.easa.europa.eu/blob/easa_ad_2014-0010.pdf/AD_2014-0010], retaining the requirements of EASA AD 2010-0024, which was superseded, and redefined the inspection thresholds and intervals [by reducing certain compliance times], and added a one-time ultrasonic inspection of fastener hold Nr 6 in the junction keel beam fitting at FR40 on both LH and RH side[s]. Following issuance of EASA AD 2014-0010, it was identified that there was a need for clarifications [of affected airplanes] * * *. The compliance times vary depending on airplane utilization and configuration. The earliest compliance time for the initial rotating probe inspections is the later of (1) before 10,400 total flight cycles or 67,800 total flight hours, whichever occurs first; and (2) within 24 months or 14,590 flight cycles or 43,790 flight hours, whichever occurs first. The latest compliance time for the initial inspections is the later of (1) before 20,800 total flight cycles or 67,900 total flight hours, whichever occurs first; and (2) within 24 months or 21,180 flight cycles or 63,560 flight hours, whichever occurs first. The compliance times for the repetitive intervals range between 7,800 flight cycles or 50,900 flight hours and 10,700 flight cycles or 35,200 flight hours. The compliance times for the one-time ultrasonic inspection are the latest of (1) 21,000 flight cycles or 60,600 flight hours and within 2,400 flight cycles or 24 months; or the latest of (2) 22,100 flight cycles and 64,400 flight hours, or within 1,300 flight cycles or 24 months. 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-2015- 0937. Related Service Information Under 1 CFR Part 51 Airbus has issued the following service information. Airbus Service Bulletin A330-57-3081, Revision 05, including Appendix 01, dated November 13, 2012. Airbus Service Bulletin A330-57-3090, dated June 15, 2011. Airbus Service Bulletin A330-57-3098, dated August 30, 2007. Airbus Service Bulletin A330-57-3098, Revision 02, June 15, 2011. Airbus Service Bulletin A330-57-3098, Revision 03, including Appendix 01, dated September 24, 2014. Airbus Service Bulletin A330-57-3117, including Appendix 01, dated January 25, 2013. Airbus Service Bulletin A340-57-4089, Revision 05, including Appendix 01, dated November 13, 2012. Airbus Service Bulletin A340-57-4098, Revision 01, dated June 15, 2011. Airbus Service Bulletin A340-57-4106, dated August 30, 2007. Airbus Service Bulletin A340-57-4106, Revision 02, including Appendix 01, dated August 30, 2007. Airbus Service Bulletin A340-57-4106, Revision 03, including Appendix 01, dated September 24, 2012. Airbus Service Bulletin A340-57-4126, including Appendix 01, dated January 25, 2013. This service information describes procedures for inspections for cracking of the hole(s) of the horizontal flange of the keel beam, and contacting the manufacturer for repair instructions. Additionally, this service information describes procedures for a one-time ultrasonic inspection for cracking at fastener hole ``Nr 6,'' and provides [[Page 25251]] optional terminating action for the repetitive inspections. The actions described in this service information are intended to correct the unsafe condition identified in the MCAI. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section of this NPRM. Explanation of Compliance Time The compliance time for the modification specified in this proposed AD for addressing widespread fatigue damage (WFD) was established to ensure that discrepant structure is modified before WFD develops in airplanes. Standard inspection techniques cannot be relied on to detect WFD before it becomes a hazard to flight. We will not grant any extensions of the compliance time to complete any AD-mandated service bulletin related to WFD without extensive new data that would substantiate and clearly warrant such an extension. 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 the same type design. Costs of Compliance We estimate that this proposed AD affects 35 airplanes of U.S. registry. The actions that are required by AD 2011-24-05, Amendment 39-16869 (76 FR 73496, November 29, 2011), and retained in this proposed AD take about 41 work-hours per product, at an average labor rate of $85 per work hour. Required parts cost about $191 per product. Based on these figures, the estimated cost of the actions that are required by AD 2011-24-05 is $3,676 per product. We also estimate that it would take about 23 work-hours per product to comply with the basic requirements of this proposed AD. The average labor rate is $85 per work-hour. Based on these figures, we estimate the cost of this proposed AD on U.S. operators to be $68,425, or $1,955 per product. We have received no definitive data that would enable us to provide a cost estimate for the on-condition actions 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. Sec. 39.13 [Amended] 0 2. The FAA amends Sec. 39.13 by removing Airworthiness Directive (AD) 2011-24-05, Amendment 39-16869 (76 FR 73496, November 29, 2011), and adding the following new AD: Airbus: Docket No. FAA-2015-0937; Directorate Identifier 2014-NM- 024-AD. (a) Comments Due Date We must receive comments by June 18, 2015. (b) Affected ADs This AD replaces AD 2011-24-05, Amendment 39-16869 (76 FR 73496, November 29, 2011). (c) Applicability (1) This AD applies to the airplanes identified in paragraphs (c)(1)(i) and (c)(1)(ii) of this AD, certificated in any category, except as provided by paragraph (c)(2) of this AD. (i) Airbus Model A330-201, -202, -203, -223, -243, -301, -302, - 303, -321, -322, -323, -341, -342, and -343 airplanes, all serial numbers, except those on which Airbus modification 55306 or 55792 has been embodied in production. (ii) Airbus Model A340-211, -212, -213, -311, -312, and -313 airplanes, all serial numbers, except those on which Airbus modification 55306 or 55792 has been embodied in production. (2) This AD does not apply to Airbus Model A340-211, -212, -213, -311, -312, and -313 airplanes on which the repair specified in Airbus Repair Drawing R57115053, R57115051, or R57115047 (installation of titanium doubler on both sides) has been accomplished. AD 2007-12-08, Amendment 39-15086 (72 FR 31171, June 6, 2007), applies to these airplanes. (d) Subject Air Transport Association (ATA) of America Code 57, Wings. (e) Reason This AD was prompted by reports of cracks on the keel beam fitting and the front spar of the center wing box. This AD was also prompted by a determination that the rototest inspection and applicable corrective actions of fastener hole Nr 6 were inadvertently omitted from the requirements in AD 2011-24-05, Amendment 39-16869 (76 FR 73496, November 29, 2011). We are issuing this AD to detect and correct cracking of the fastener holes, which could result in rupture of the keel beam, and consequent reduced structural integrity of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. [[Page 25252]] (g) Retained Non-Destructive Test (NDT) Inspection This paragraph restates the requirements of paragraph (n) of AD 2011-24-05, Amendment 39-16869 (76 FR 73496, November 29, 2011), with new service information and revised credit for certain actions. At the applicable time in paragraph (g)(1) or (g)(2) of this AD, do an NDT inspection of the hole(s) of the horizontal flange of the keel beam located on frame (FR) 40 datum on the right-hand (RH) and/ or left-hand (LH) side of the fuselage, in accordance with the Accomplishment Instructions of the applicable service information specified in paragraph (g)(3), (g)(4), (g)(5), or (g)(6) of this AD. Accomplishing an inspection required by paragraph (j) of this AD terminates the inspections required by this paragraph. (1) For airplanes on which an inspection required by paragraph (h) of AD 2011-24-05, Amendment 39-16869 (76 FR 73496, November 29, 2011), has not been done as of January 3, 2012 (the effective date of AD 2011-24-05): At the applicable time specified in paragraph (g)(1)(i) or (g)(1)(ii) of this AD. (i) For all airplanes except those identified in paragraph (g)(1)(ii) of this AD: Within the ``Mandatory Threshold'' (flight cycles or flight hours) specified in table 1 of paragraph 1.E.(2) of the Accomplishment Instructions of Airbus Service Bulletin A330-57- 3081, including Appendix 01, Revision 04, dated May 31, 2011; or Airbus Service Bulletin A340-57-4089, including Appendix 01, Revision 04, dated May 31, 2011; as applicable; or within 3 months after January 3, 2012 (the effective date AD 2011-24-05, Amendment 39-16869 (76 FR 73496, November 29, 2011)); whichever occurs later. The compliance times for configurations 02 through 06 specified in the ``Mandatory Threshold'' column in table 1 of paragraph 1.E., ``Compliance,'' are total flight cycles and total flight hours. (ii) For Model A330-201, -202, -203, -223, -243, -301, -321, - 322, -323, -341, -342, and -343 airplanes, except those on which Airbus modification 49202 has been embodied in production, or Airbus Service Bulletin A330-57-3090 has been embodied in service, and Model A340-200 and -300 series airplanes, except those on which Airbus modification 49202 has been embodied in production or Airbus Service Bulletin A340-57-4098 has been embodied in service, and except Model A340-211, -212, -213, -311, -312, and -313 airplanes on which the repair specified in Airbus Repair Drawing R57115053, R57115051, or R57115047 has been accomplished: At the earlier of the times specified in paragraphs (g)(1)(ii)(A) and (g)(1)(ii)(B) of this AD. (A) Within the ``Mandatory Threshold'' (flight cycles or flight hours) specified in table 1 of paragraph 1.E.(2) of Airbus Service Bulletin A340-57-4089, including Appendix 01, Revision 02, dated January 24, 2006; or Airbus Service Bulletin A330-57-3081, including Appendix 01, Revision 02, dated January 24, 2006; depending on the configuration of the aircraft model; or within 3 months after September 13, 2007, whichever occurs later. The compliance times for Model A330 post-mod. 41652 and pre-mod. 44360, post-mod. 44360, and pre-mod. 49202 (specified in Airbus Service Bulletin A330-57-3081, including Appendix 01, Revision 02, dated January 24, 2006); and Model A340 post-mod. 41652, post-mod. 43500 and pre-mod. 44360, post-mod. 44360 and pre-mod. 49202, and weight variant 027 (specified in Airbus Service Bulletin A340-57-4089, including Appendix 01, Revision 02, dated January 24, 2006); specified in the ``Mandatory Threshold'' column in table 1 of paragraph 1.E., ``Compliance,'' are total flight cycles and total flight hours. (B) Within the ``Mandatory Threshold'' (flight cycles or flight hours) specified in table 1 of paragraph 1.E.(2) of the Accomplishment Instructions of Airbus Service Bulletin A330-57-3081, including Appendix 01, Revision 04, dated May 31, 2011; or Airbus Service Bulletin A340-57-4089, including Appendix 01, Revision 04, dated May 31, 2011; as applicable; or within 3 months after January 3, 2012 (the effective date of AD 2011-24-05, Amendment 39-16869 (76 FR 73496, November 29, 2011)); whichever occurs later. The compliance times for configurations 02 through 06 specified in the ``Mandatory Threshold'' column in table 1 of paragraph 1.E., ``Compliance,'' are total flight cycles and total flight hours. (2) For airplanes on which an inspection required by paragraph (h) of AD 2011-24-05, Amendment 39-16869 (76 FR 73496, November 29, 2011), has been done as of January 3, 2012 (the effective date of AD 2011-24-05): At the earlier of the times specified in paragraphs (g)(2)(i) and (g)(2)(ii) of this AD. (i) Within the ``Mandatory Intervals'' given in table 1 of paragraph 1.E.(2) of Airbus Service Bulletin A340-57-4089, including Appendix 01, Revision 02, dated January 24, 2006; or Airbus Service Bulletin A330-57-3081, including Appendix 01, Revision 02, dated January 24, 2006; as applicable. (ii) Within the applicable ``Mandatory Interval'' specified in table 1 of Paragraph 1.E.(2). of Airbus Service Bulletin A330-57- 3081, including Appendix 01, Revision 04, dated May 31, 2011,; or Airbus Service Bulletin A340-57-4089, including Appendix 01, Revision 04, dated May 31, 2011; as applicable; or within 3 months after January 3, 2012 (the effective date of AD 2011-24-05, Amendment 39-16869 (76 FR 73496, November 29, 2011)); whichever occurs later. (3) Airbus Service Bulletin A330-57-3081, including Appendix 01, Revision 04, dated May 31, 2011. (4) Airbus Service Bulletin A330-57-3081, including Appendix 01, Revision 05, dated November 13, 2012. (5) Airbus Service Bulletin A340-57-4089, including Appendix 01, Revision 04, dated May 31, 2011. (6) Airbus Service Bulletin A340-57-4089, Revision 05, including Appendix 01, dated November 13, 2012. (h) Retained Repetitive Inspections This paragraph restates the requirements of paragraph (p) of AD 2011-24-05, Amendment 39-16869 (76 FR 73496, November 29, 2011). If no cracking is found during any inspection required by paragraph (g) of this AD, do the actions required by paragraphs (h)(1) and (h)(2) of this AD. (1) Before further flight: Install a new or oversized fastener, as applicable; seal the fastener; and do all other applicable actions; in accordance with the Accomplishment Instructions of the applicable service information specified in paragraph (g)(3), (g)(4), (g)(5), or (g)(6) of this AD. (2) Repeat the inspection required by paragraph (g) of this AD thereafter at intervals not to exceed the ``Mandatory Intervals'' specified in Paragraph 1.E.(2). of Airbus Service Bulletin A330-57- 3081, including Appendix 01, Revision 04, dated May 31, 2011; or Airbus Service Bulletin A340-57-4089, including Appendix 01, Revision 04, dated May 31, 2014; as applicable. (i) Retained Corrective Action and Optional Modification (1) This paragraph restates the requirements of paragraph (o) of AD 2011-24-05, Amendment 39-16869 (76 FR 73496, November 29, 2011), with revised method of compliance language. If any cracking is found during any inspection required by paragraph (g) of this AD, before further flight, repair using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA); or Airbus's EASA Design Organization Approval (DOA). (2) This paragraph restates the requirements of paragraph (r) of AD 2011-24-05, Amendment 39-16869 (76 FR 73496, November 29, 2011), with new service information and revised method of compliance language. Modifying the fastener installation in the junction keel beam fitting at FR 40, as specified in paragraph (i)(2)(i), (i)(2)(ii), (i)(2)(iii), or (i)(2)(iv) of this AD, as applicable, terminates the requirements of paragraphs (g) and (h) of this AD; except, for airplanes on which a crack was detected at hole 5 before oversizing of the keel beam, in accordance with step 3.B.(1)(b)3 of the Accomplishment Instructions of Airbus Service Bulletin A330-57- 3098, dated August 30, 2007; or Airbus Service Bulletin A340-57- 4106, dated August 30, 2007; or in accordance with step 3.C.(2)(c) of the Accomplishment Instructions of Airbus Service Bulletin A330- 57-3098, Revision 03, including Appendix 01, dated September 24, 2012, or Airbus Service Bulletin A340-57-4106, Revision 03, including Appendix 01, dated September 24, 2012; before further flight, repair using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA; or Airbus's EASA DOA. In case of any crack finding during any modification specified in this paragraph: Where the service information specifies to contact Airbus, before further flight, repair using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA; or Airbus's EASA DOA. (i) Modification in accordance with Airbus Service Bulletin A330-57-3098, dated August 30, 2007, before January 3, 2012 (the effective date of AD 2011-24-05, [[Page 25253]] Amendment 39-16869 (76 FR 73496, November 29, 2011)). (ii) Modification in accordance with Airbus Service Bulletin A330-57-3098, Revision 03, including Appendix 01, dated September 24, 2012, before the effective date of this AD. (iii) Modification in accordance with Airbus Service Bulletin A340-57-4106, dated August 30, 2007, before January 3, 2012 (the effective date of AD 2011-24-05, Amendment 39-16869 (76 FR 73496, November 29, 2011)). (iv) Modification in accordance with Airbus Service Bulletin A340-57-4106, Revision 03, including Appendix 01, dated September 24, 2012, before the effective date of this AD. (j) New Repetitive Rotating Probe Inspections At the applicable times specified in paragraphs (j)(1) and (j)(2) of this AD: Do a rotating probe inspection for cracking of the fastener hole(s) of the horizontal flange of the keel beam located on FR 40 datum on the RH and LH side of the fuselage, as applicable to airplane type and depending on airplane configuration and utilization, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330-57-3081, Revision 05, including Appendix 01, dated November 13, 2012; or Airbus Service Bulletin A340-57-4089, Revision 05, including Appendix 01, dated November 13, 2012; as applicable. Repeat the inspection thereafter at intervals not to exceed the ``Mandatory Intervals'' specified in Paragraph 1.E.(2)., of the Accomplishment Timescale of Airbus Service Bulletin A330-57-3081, Revision 05, including Appendix 01, dated November 13, 2012; or Airbus Service Bulletin A340-57-4089, Revision 05, including Appendix 01, dated November 13, 2012; as applicable. Accomplishing an inspection required by this paragraph terminates the inspections required by paragraph (g) of this AD. (1) For airplanes on which the inspection required by paragraph (g) of this AD has not been done as of the effective date of this AD: Do the inspection before exceeding the applicable compliance times specified in the ``mandatory threshold'' column of the tables in paragraph 1.E.(2)., of the Accomplishment Timescale of Airbus Service Bulletin A330-57-3081, Revision 05, including Appendix 01, dated November 13, 2012; or Airbus Service Bulletin A340-57-4089, Revision 05, including Appendix 01, dated November 13, 2012; as applicable; or within 12 months after the effective date of this AD; whichever occurs later. (2) For airplanes on which the inspection required by paragraph (g) of this AD has been done as of the effective date of this AD: Do the inspection within the applicable compliance times specified in the ``mandatory interval'' column of the tables in paragraph 1.E.(2)., of the Accomplishment Timescale of Airbus Service Bulletin A330-57-3081, Revision 05, including Appendix 01, dated November 13, 2012; or Airbus Service Bulletin A340-57-4089, Revision 05, including Appendix 01, dated November 13, 2012; as applicable; or within 12 months after the effective date of this AD; whichever occurs later. (k) Credit for Previous Actions (1) This paragraph provides credit for the initial rotating probe inspection that is part of the inspections required by paragraphs (g) and (j)(1) of this AD, if those actions were performed before the effective date of this AD using the service information specified in paragraph (k)(1)(i) or (k)(1)(ii) of this AD. (i) Airbus Technical Disposition F57D03012810, Issue B, dated August 18, 2003. (ii) Airbus Technical Disposition 582.0651/2002, Issue A, dated October 17, 2002. (2) This paragraph restates the credit for the actions specified in paragraph (k) of AD 2011-24-05, Amendment 39-16869 (76 FR 73496, November 29, 2011), if those actions were performed before January 3, 2012 (the effective date of AD 2011-24-05), using the service information specified in paragraphs (k)(2)(i) through (k)(2)(viii) of this AD. (i) Airbus Service Bulletin A330-57-3081, dated October 30, 2003. (ii) Airbus Service Bulletin A330-57-3081, Revision 01, dated May 18, 2004. (iii) Airbus Service Bulletin A330-57-3081, Revision 02, including Appendix 01, dated January 24, 2006. (iv) Airbus Mandatory Service Bulletin A330-57-3081, Revision 03, dated July 31, 2009. (v) Airbus Service Bulletin A340-57-4089, dated October 30, 2003. (vi) Airbus Service Bulletin A340-57-4089, Revision 01, dated March 2, 2004. (vii) Airbus Service Bulletin A340-57-4089, Revision 02, including Appendix 01, dated January 24, 2006. (viii) Airbus Mandatory Service Bulletin A340-57-4089, Revision 03, dated July 31, 2009. (l) New One-Time Ultrasonic Inspection For airplanes in Configuration 2, as defined in the applicable service information identified in paragraph (l)(3), (l)(4), (l)(5), or (l)(6) of this AD, on which the modification has been done as of the effective date of this AD in accordance with the Accomplishment Instructions of the applicable service information identified in paragraph (l)(3), (l)(4), (l)(5), or (l)(6) of this AD; as applicable to airplane type; and on which fastener hole ``Nr 5'' has been bushed before embodiment of Airbus Service Bulletin A330-57- 3098, or Airbus Service Bulletin A340-57-4106, as applicable; or on which a crack has been found on fastener hole ``Nr 5'' during embodiment of Airbus Service Bulletin A330-57-3098, or Airbus Service Bulletin A340-57-4106, as applicable: At the applicable time specified in paragraph (l)(1) or (l)(2) of this AD, do a one-time ultrasonic inspection for cracking at fastener hole ``Nr 6'' in the junction keel beam fitting at FR 40 LH and RH sides, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330-57-3117, including Appendix 01, dated January 25, 2013; or Airbus Service Bulletin A340-57-4126, including Appendix 01, dated January 25, 2013; as applicable. (1) For Model A330-201, -202, -203, -223, -243, -301, -321, - 322, -323, -341, -342, and -343 airplanes: At the later of the times specified in paragraphs (l)(1)(i) and (l)(1)(ii) of this AD. (i) At the applicable time specified in paragraph 1.E.(2)., of the Accomplishment Timescale of Airbus Service Bulletin A330-57- 3117, including Appendix 01, dated January 25, 2013. (ii) Within 2,400 flight cycles or 24 months after the effective date of this AD, whichever occurs first. (2) For Model A340-211, -212, -213, -311, -312, and -313 airplanes: At the later of the times specified in paragraphs (l)(2)(i) and (l)(2)(ii) of this AD. (i) At the applicable time specified in paragraph 1.E.(2)., of the Accomplishment Timescale of Airbus Service Bulletin A340-57- 4126, including Appendix 01, dated January 25, 2013. (ii) Within 1,300 flight cycles or 24 months after the effective date of this AD, whichever occurs first. (3) Airbus Service Bulletin A330-57-3098, Revision 01, dated July 31, 2009. (4) Airbus Service Bulletin A330-57-3098, Revision 02, dated June 15, 2011. (5) Airbus Service Bulletin A340-57-4106, Revision 01, dated July 31, 2009. (6) Airbus Service Bulletin A340-57-4106, Revision 02, dated June 15, 2011. (m) Corrective Actions (1) If no cracking is found during any inspection required by paragraph (j) of this AD, before further flight: Install new or oversized fastener, as applicable; seal the fastener; and do all other applicable corrective actions; in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330-57-3081, Revision 05, including Appendix 01, dated November 13, 2012; or Airbus Service Bulletin A340-57-4089, Revision 05, including Appendix 01, dated November 13, 2012; as applicable. Thereafter, repeat the inspection required by paragraph (j) of this AD at intervals not to exceed the ``Mandatory Intervals'' specified in Paragraph 1.E.(2)., of the Accomplishment Timescale of Airbus Service Bulletin A330-57-3081, Revision 05, including Appendix 01, dated November 13, 2012; or Airbus Service Bulletin A340-57-4089, Revision 05, including Appendix 01, dated November 13, 2012; as applicable. (2) If any crack is found during any inspection required by paragraph (j) or (l) of this AD; before further flight, repair 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. (n) Airplanes Excluded From Certain Requirements (1) For airplanes on which a rototest was done at fastener hole Nr 6 before cold working of the fastener hole during accomplishment of the actions specified in the applicable service information identified in paragraph (n)(1)(i), (n)(1)(ii), (n)(1)(iii), or (n)(1)(iv) of this AD: The ultrasonic inspection specified in paragraph (l) of this AD is not required. (i) Airbus Service Bulletin A330-57-3098, Revision 01, dated July 31, 2009. (ii) Airbus Service Bulletin A330-57-3098, Revision 02, dated June 15, 2011. [[Page 25254]] (iii) Airbus Service Bulletin A340-57-4106, Revision 01, dated June 31, 2009. (iv) Airbus Service Bulletin A340-57-4106, Revision 02, dated June 15, 2011. (2) For airplanes that have been modified as of the effective date of this AD in accordance with the Accomplishment Instructions of the applicable service information identified in paragraph (n)(1)(i), (n)(1)(ii), (n)(1)(iii), or (n)(1)(iv) of this AD: No action is required by this paragraph, except as otherwise required by paragraph (l) of this AD and, provided that if any crack was found during any modification specified in this paragraph and the service information specified to contact Airbus, repair was done before further flight 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. (o) Optional Terminating Actions (1) Modification of an airplane in accordance with the Accomplishment Instructions of the applicable service information identified in paragraph (o)(1)(i), (o)(1)(ii), (o)(1)(iii), (o)(1)(iv), (o)(1)(v), or (o)(1)(vi) of this AD; as applicable to airplane type and depending on airplane configuration; terminates the requirements of this AD, provided that in case of any crack finding during any modification specified in this paragraph, and the service information specifies to contact Airbus, repair is done before further flight, 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 (i) Airbus Service Bulletin A330-57-3090, dated March 27, 2006. (ii) Airbus Service Bulletin A330-57-3090, Revision 01, dated June 15, 2011. (iii) Airbus Service Bulletin A330-57-3098, Revision 03, including Appendix 01, dated September 24, 2012. (iv) Airbus Service Bulletin A340-57-4098, dated March 27, 2006. (v) Airbus Service Bulletin A340-57-4098, Revision 01, dated June 15, 2011. (vi) Airbus Service Bulletin A340-57-4106, Revision 03, including Appendix 01, dated September 24, 2012. (2) Accomplishment of the ultrasonic inspection required by paragraph (l) of this AD and all applicable corrective actions required by paragraph (m) of this AD terminates the requirements of this AD for those airplanes. (p) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the International Branch, send it to ATTN: Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1138; fax 425-227-1149. Information may be emailed to: [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. The AMOC approval letter must specifically reference this AD. (2) AMOCs approved previously for AD 2011-24-05, Amendment 39- 16869 (76 FR 73496, November 29, 2011), are approved as AMOCs for the corresponding provisions of this AD. (3) 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. (q) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2014-0010R1, dated May 5, 2014, for related information. This MCAI may be found in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-0937. (2) For service information identified in this AD, contact Airbus SAS--Airworthiness Office--EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 80; email [email protected]; Internet http://www.airbus.com. You may view this service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221. Issued in Renton, Washington, on April 13, 2015. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015-10177 Filed 5-1-15; 8:45 am] BILLING CODE 4910-13-P
![Federal Register / Vol. 80, No. 85 / Monday, May 4, 2015 / Proposed Rules 25249
§ 39.13 [Amended] accordance with the procedures specified in Notice of proposed rulemaking
ACTION:
■ 2. The FAA amends § 39.13 by adding paragraph (j) of this AD. (NPRM).
the following new airworthiness (j) Other FAA AD Provisions
directive (AD): SUMMARY: We propose to supersede
The following provisions also apply to this Airworthiness Directive (AD) 2011–24–
Fokker Services B.V.: Docket No. FAA– AD: 05, for certain Airbus Model A330–201,
2015–0933; Directorate Identifier 2014– (1) Alternative Methods of Compliance –202, –203, –223, –243, –301, –302,
NM–098–AD. (AMOCs): The Manager, International
Branch, ANM–116, Transport Airplane
–303, –321, –322, –323, –341, –342, and
(a) Comments Due Date –343 airplanes; and Model A340–200
Directorate, FAA, has the authority to
We must receive comments by June 18, approve AMOCs for this AD, if requested and –300 series airplanes. AD 2011–24–
2015. using the procedures found in 14 CFR 39.19. 05 currently requires repetitive
(b) Affected ADs In accordance with 14 CFR 39.19, send your inspections for cracking of the hole(s) of
request to your principal inspector or local the horizontal flange of the keel beam,
None. Flight Standards District Office, as and repair if necessary. Since we issued
(c) Applicability appropriate. If sending information directly AD 2011–24–05, a determination was
to the International Branch, send it to ATTN: made that the rototest inspection and
This AD applies to Fokker Services B.V. Tom Rodriguez, Aerospace Engineer,
Model F.27 Mark 200, 300, 400, 500, 600, and International Branch; ANM–116, Transport
applicable corrective actions of a certain
700 airplanes, certificated in any category, all
Airplane Directorate, FAA, 1601 Lind fastener hole were inadvertently omitted
serial numbers. from the requirements in that AD. This
Avenue SW., Renton, WA 98057–3356;
(d) Subject telephone 425–227–1137; fax 425–227–1137. proposed AD would change the
Air Transport Association (ATA) of Information may be emailed to: 9-ANM-116- inspection compliance times, and, for
America Code 28, Fuel. AMOC-REQUESTS@faa.gov. Before using certain airplanes, would add a one-time
any approved AMOC, notify your appropriate ultrasonic inspection for cracking at a
(e) Reason principal inspector, or lacking a principal certain fastener hole. This proposed AD
This AD was prompted by a design review, inspector, the manager of the local flight would also provide optional terminating
which revealed that no controlled bonding standards district office/certificate holding
district office. The AMOC approval letter
action for the repetitive inspections. We
provisions are present on a number of critical are proposing this AD to detect and
locations inside the fuel tank or connected to must specifically reference this AD.
(2) Contacting the Manufacturer: For any correct cracking of the fastener holes,
the fuel tank wall; and no anti-spray cover is
installed on the fuel shut-off valve (FSOV) in requirement in this AD to obtain corrective which could result in rupture of the keel
both wings. We are issuing this AD to actions from a manufacturer, the action must beam, and consequent reduced
prevent an ignition source in the fuel tank be accomplished using a method approved structural integrity of the airplane.
vapor space, which could result in a fuel tank by the Manager, International Branch, ANM– DATES: We must receive comments on
explosion and consequent loss of the 116, Transport Airplane Directorate, FAA; or this proposed AD by June 18, 2015.
airplane. the EASA; or Fokker Services B.V.’s EASA
Design Organization Approval (DOA). If ADDRESSES: You may send comments by
(f) Compliance approved by the DOA, the approval must any of the following methods:
Comply with this AD within the include the DOA-authorized signature. • Federal eRulemaking Portal: Go to
compliance times specified, unless already http://www.regulations.gov. Follow the
(k) Related Information
done. instructions for submitting comments.
Refer to Mandatory Continuing • Fax: 202–493–2251.
(g) Installation of Bonding Provisions and Airworthiness Information (MCAI) EASA • Mail: U.S. Department of
Anti-Spray Cover Airworthiness Directive 2014–0099, dated Transportation, Docket Operations, M–
At the next scheduled opening of the fuel April 30, 2014, for related information. This 30, West Building Ground Floor, Room
tanks after the effective date of this AD, but MCAI may be found in the AD docket on the
Internet at http://www.regulations.gov by
W12–140, 1200 New Jersey Avenue SE.,
no later than 84 months after the effective Washington, DC 20590.
date of this AD: Install additional bonding searching for and locating Docket No. FAA–
2015–0933. • Hand Delivery: U.S. Department of
provisions at the applicable locations, and
install an anti-spray cover on the FSOV in
Transportation, Docket Operations, M–
Issued in Renton, Washington, on April 17, 30, West Building Ground Floor, Room
both wings, using a method approved by the 2015.
Manager, International Branch, ANM–116, W12–140, 1200 New Jersey Avenue SE.,
Victor Wicklund, Washington, DC, between 9 a.m. and 5
Transport Airplane Directorate, FAA.
Acting Manager, Transport Airplane p.m., Monday through Friday, except
(h) Revision of Maintenance or Inspection Directorate, Aircraft Certification Service.
Program
Federal holidays.
[FR Doc. 2015–10180 Filed 5–1–15; 8:45 am] For service information identified in
Within 30 days after installing the bonding BILLING CODE 4910–13–P this proposed AD, contact Airbus SAS—
provisions and anti-spray cover specified in
Airworthiness Office—EAL, 1 Rond
paragraph (g) of this AD: Revise the airplane
maintenance or inspection program, as Point Maurice Bellonte, 31707 Blagnac
DEPARTMENT OF TRANSPORTATION Cedex, France; telephone +33 5 61 93 36
applicable, by incorporating fuel
airworthiness limitation items and Critical 96; fax +33 5 61 93 45 80; email
Federal Aviation Administration
Design Configuration Control Limitations airworthiness.A330-A340@airbus.com;
(CDCCLs), using a method approved by the Internet http://www.airbus.com. You
Manager, International Branch, ANM–116, 14 CFR Part 39
may view this referenced service
Transport Airplane Directorate, FAA. [Docket No. FAA–2015–0937; Directorate information at the FAA, Transport
tkelley on DSK3SPTVN1PROD with PROPOSALS
(i) No Alternative Actions, Intervals, and/or Identifier 2014–NM–024–AD] Airplane Directorate, 1601 Lind Avenue
CDCCLs RIN 2120–AA64
SW., Renton, WA. For information on
After accomplishing the revision required the availability of this material at the
by paragraph (h) of this AD, no alternative Airworthiness Directives; Airbus FAA, call 425–227–1221.
actions (e.g., inspections), intervals, or Airplanes Examining the AD Docket
CDCCLs may be used unless the actions,
intervals, or CDCCLs are approved as an AGENCY:Federal Aviation You may examine the AD docket on
alternative method of compliance (AMOC) in Administration (FAA), DOT. the Internet at http://
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![25250 Federal Register / Vol. 80, No. 85 / Monday, May 4, 2015 / Proposed Rules
www.regulations.gov by searching for or ‘‘the MCAI’’), to correct an unsafe cycles or 43,790 flight hours, whichever
and locating Docket No. FAA–2015– condition for certain Airbus Model occurs first. The latest compliance time
0937; or in person at the Docket A330–201, –202, –203, –223, –243, for the initial inspections is the later of
Management Facility between 9 a.m. –301, –302, –303, –321, –322, –323, (1) before 20,800 total flight cycles or
and 5 p.m., Monday through Friday, –341, –342, and –343 airplanes; and 67,900 total flight hours, whichever
except Federal holidays. The AD docket Model A340–200 and –300 series occurs first; and (2) within 24 months or
contains this proposed AD, the airplanes. The MCAI states: 21,180 flight cycles or 63,560 flight
regulatory evaluation, any comments During A330 and A340 aeroplanes fatigue hours, whichever occurs first. The
received, and other information. The tests, cracks were detected on the RH [right- compliance times for the repetitive
street address for the Docket Operations hand] and LH [left-hand] sides between the intervals range between 7,800 flight
office (telephone 800–647–5527) is in crossing area of the keel beam fitting and the cycles or 50,900 flight hours and 10,700
the ADDRESSES section. Comments will front spar of the Centre Wing Box (CWB). flight cycles or 35,200 flight hours. The
be available in the AD docket shortly This condition, if not detected and compliance times for the one-time
corrected, could lead to keel beam rupture ultrasonic inspection are the latest of (1)
after receipt.
which would affect the area structural
FOR FURTHER INFORMATION CONTACT: integrity of the area. 21,000 flight cycles or 60,600 flight
Vladimir Ulyanov, Aerospace Engineer, Prompted by this potential unsafe hours and within 2,400 flight cycles or
International Branch, ANM–116, condition, EASA issued AD 2006–0315 24 months; or the latest of (2) 22,100
Transport Airplane Directorate, FAA, [http://ad.easa.europa.eu/blob/easa_ad_ flight cycles and 64,400 flight hours, or
1601 Lind Avenue SW., Renton, WA 2006_0315.pdf/AD_2006-0315] (later revised within 1,300 flight cycles or 24 months.
98057–3356; telephone 425–227–1138; to R1) to require repetitive special detailed You may examine the MCAI in the
inspections (SDI) [rotating probe inspection AD docket on the Internet at http://
fax 425–227–1149. for cracking] on the horizontal flange of the www.regulations.gov by searching for
SUPPLEMENTARY INFORMATION: keel beam in the area of first fastener hole aft
of Frame (FR) 40 in order to maintain the
and locating Docket No. FAA–2015–
Comments Invited structural integrity of the aeroplane. 0937.
We invite you to send any written After that [EASA] AD was issued, EASA Related Service Information Under 1
relevant data, views, or arguments about issued AD 2010–0024 [which corresponds to CFR Part 51
this proposed AD. Send your comments FAA AD 2011–24–05, Amendment 39–16869
(76 FR 73496, November 29, 2011)], retaining Airbus has issued the following
to an address listed under the the inspection requirements of EASA AD service information.
ADDRESSES section. Include ‘‘Docket No. 2006–0315R1 [http://ad.easa.europa.eu/blob/ • Airbus Service Bulletin A330–57–
FAA–2015–0937; Directorate Identifier easa_ad_2006_0315R1.pdf/AD_2006- 3081, Revision 05, including Appendix
2014–NM–024–AD’’ at the beginning of 0315R1], which was superseded, extending 01, dated November 13, 2012.
your comments. We specifically invite the applicability to aeroplanes with Airbus
• Airbus Service Bulletin A330–57–
comments on the overall regulatory, Mod 49202 embodied, and reducing the
inspection thresholds and intervals. 3090, dated June 15, 2011.
economic, environmental, and energy • Airbus Service Bulletin A330–57–
aspects of this proposed AD. We will Since that [EASA] AD [2010–0024] was
issued, a new fatigue and damage tolerance 3098, dated August 30, 2007.
consider all comments received by the evaluation has been conducted by Airbus, • Airbus Service Bulletin A330–57–
closing date and may amend this which concluded that due to the aeroplane 3098, Revision 02, June 15, 2011.
proposed AD based on those comments. utilization, the current inspection threshold • Airbus Service Bulletin A330–57–
We will post all comments we and intervals have to be modified. 3098, Revision 03, including Appendix
receive, without change, to http:// In addition, it was determined that the 01, dated September 24, 2014.
www.regulations.gov, including any rototest inspection of fastener hole Nr 6, • Airbus Service Bulletin A330–57–
personal information you provide. We necessary to ensure that no crack was left
3117, including Appendix 01, dated
will also post a report summarizing each unrepaired at the time of fastener hold cold
working, was inadvertently not included in January 25, 2013.
substantive verbal contact we receive Revisions 01 and 02 of both Airbus Service • Airbus Service Bulletin A340–57–
about this proposed AD. Bulletin (SB) A330–57–3098 and A340–57– 4089, Revision 05, including Appendix
Discussion 4106. 01, dated November 13, 2012.
Prompted by these findings, EASA issued • Airbus Service Bulletin A340–57–
On November 7, 2011, we issued AD AD 2014–0010 [http://ad.easa.europa.eu/ 4098, Revision 01, dated June 15, 2011.
2011–24–05, Amendment 39–16869 (76 blob/easa_ad_2014-0010.pdf/AD_2014-0010], • Airbus Service Bulletin A340–57–
FR 73496, November 29, 2011), for retaining the requirements of EASA AD 4106, dated August 30, 2007.
certain Airbus Model A330–201, –202, 2010–0024, which was superseded, and • Airbus Service Bulletin A340–57–
–203, –223, –243, –301, –302, –303, redefined the inspection thresholds and
intervals [by reducing certain compliance
4106, Revision 02, including Appendix
–321, –322, –323, –341, –342, and –343 times], and added a one-time ultrasonic 01, dated August 30, 2007.
airplanes; and Model A340–200 and inspection of fastener hold Nr 6 in the • Airbus Service Bulletin A340–57–
–300 series airplanes. AD 2011–24–05 junction keel beam fitting at FR40 on both LH 4106, Revision 03, including Appendix
requires actions intended to address the and RH side[s]. 01, dated September 24, 2012.
unsafe condition on the products listed Following issuance of EASA AD 2014– • Airbus Service Bulletin A340–57–
above. 0010, it was identified that there was a need 4126, including Appendix 01, dated
Since we issued AD 2011–24–05, for clarifications [of affected airplanes] January 25, 2013.
Amendment 39–16869 (76 FR 73496, * * *. This service information describes
tkelley on DSK3SPTVN1PROD with PROPOSALS
November 29, 2011), the European The compliance times vary depending procedures for inspections for cracking
Aviation Safety Agency (EASA), which on airplane utilization and of the hole(s) of the horizontal flange of
is the Technical Agent for the Member configuration. The earliest compliance the keel beam, and contacting the
States of the European Union, has time for the initial rotating probe manufacturer for repair instructions.
issued EASA Airworthiness Directive inspections is the later of (1) before Additionally, this service information
2014–0010R1, dated May 5, 2014 10,400 total flight cycles or 67,800 total describes procedures for a one-time
(referred to after this as the Mandatory flight hours, whichever occurs first; and ultrasonic inspection for cracking at
Continuing Airworthiness Information, (2) within 24 months or 14,590 flight fastener hole ‘‘Nr 6,’’ and provides
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![Federal Register / Vol. 80, No. 85 / Monday, May 4, 2015 / Proposed Rules 25251
optional terminating action for the We have received no definitive data PART 39—AIRWORTHINESS
repetitive inspections. that would enable us to provide a cost DIRECTIVES
The actions described in this service estimate for the on-condition actions
information are intended to correct the specified in this proposed AD. ■ 1. The authority citation for part 39
unsafe condition identified in the continues to read as follows:
Authority for This Rulemaking
MCAI. This service information is Authority: 49 U.S.C. 106(g), 40113, 44701.
reasonably available because the Title 49 of the United States Code
interested parties have access to it § 39.13 [Amended]
specifies the FAA’s authority to issue
through their normal course of business rules on aviation safety. Subtitle I, ■ 2. The FAA amends § 39.13 by
or by the means identified in the section 106, describes the authority of removing Airworthiness Directive (AD)
ADDRESSES section of this NPRM. the FAA Administrator. ‘‘Subtitle VII: 2011–24–05, Amendment 39–16869 (76
Aviation Programs,’’ describes in more FR 73496, November 29, 2011), and
Explanation of Compliance Time adding the following new AD:
detail the scope of the Agency’s
The compliance time for the authority. Airbus: Docket No. FAA–2015–0937;
modification specified in this proposed Directorate Identifier 2014–NM–024–AD.
We are issuing this rulemaking under
AD for addressing widespread fatigue the authority described in ‘‘Subtitle VII, (a) Comments Due Date
damage (WFD) was established to Part A, Subpart III, Section 44701: We must receive comments by June 18,
ensure that discrepant structure is General requirements.’’ Under that 2015.
modified before WFD develops in section, Congress charges the FAA with
airplanes. Standard inspection (b) Affected ADs
promoting safe flight of civil aircraft in
techniques cannot be relied on to detect air commerce by prescribing regulations This AD replaces AD 2011–24–05,
WFD before it becomes a hazard to Amendment 39–16869 (76 FR 73496,
for practices, methods, and procedures November 29, 2011).
flight. We will not grant any extensions the Administrator finds necessary for
of the compliance time to complete any safety in air commerce. This regulation (c) Applicability
AD-mandated service bulletin related to is within the scope of that authority (1) This AD applies to the airplanes
WFD without extensive new data that because it addresses an unsafe condition identified in paragraphs (c)(1)(i) and (c)(1)(ii)
would substantiate and clearly warrant that is likely to exist or develop on of this AD, certificated in any category,
such an extension. products identified in this rulemaking except as provided by paragraph (c)(2) of this
AD.
FAA’s Determination and Requirements action. (i) Airbus Model A330–201, –202, –203,
of This Proposed AD Regulatory Findings –223, –243, –301, –302, –303, –321, –322,
–323, –341, –342, and –343 airplanes, all
This product has been approved by
We determined that this proposed AD serial numbers, except those on which
the aviation authority of another Airbus modification 55306 or 55792 has been
would not have federalism implications
country, and is approved for operation embodied in production.
under Executive Order 13132. This
in the United States. Pursuant to our (ii) Airbus Model A340–211, –212, –213,
proposed AD would not have a
bilateral agreement with the State of –311, –312, and –313 airplanes, all serial
substantial direct effect on the States, on
Design Authority, we have been notified numbers, except those on which Airbus
the relationship between the national modification 55306 or 55792 has been
of the unsafe condition described in the
Government and the States, or on the embodied in production.
MCAI and service information
distribution of power and (2) This AD does not apply to Airbus
referenced above. We are proposing this
responsibilities among the various Model A340–211, –212, –213, –311, –312,
AD because we evaluated all pertinent and –313 airplanes on which the repair
levels of government.
information and determined an unsafe specified in Airbus Repair Drawing
condition exists and is likely to exist or For the reasons discussed above, I
R57115053, R57115051, or R57115047
develop on other products of the same certify this proposed regulation: (installation of titanium doubler on both
type design. 1. Is not a ‘‘significant regulatory sides) has been accomplished. AD 2007–12–
action’’ under Executive Order 12866; 08, Amendment 39–15086 (72 FR 31171,
Costs of Compliance June 6, 2007), applies to these airplanes.
2. Is not a ‘‘significant rule’’ under the
We estimate that this proposed AD DOT Regulatory Policies and Procedures (d) Subject
affects 35 airplanes of U.S. registry. (44 FR 11034, February 26, 1979); Air Transport Association (ATA) of
The actions that are required by AD America Code 57, Wings.
3. Will not affect intrastate aviation in
2011–24–05, Amendment 39–16869 (76
Alaska; and (e) Reason
FR 73496, November 29, 2011), and
retained in this proposed AD take about 4. Will not have a significant This AD was prompted by reports of cracks
41 work-hours per product, at an economic impact, positive or negative, on the keel beam fitting and the front spar
average labor rate of $85 per work hour. on a substantial number of small entities of the center wing box. This AD was also
under the criteria of the Regulatory prompted by a determination that the rototest
Required parts cost about $191 per
Flexibility Act. inspection and applicable corrective actions
product. Based on these figures, the of fastener hole Nr 6 were inadvertently
estimated cost of the actions that are List of Subjects in 14 CFR Part 39 omitted from the requirements in AD 2011–
required by AD 2011–24–05 is $3,676 24–05, Amendment 39–16869 (76 FR 73496,
per product. Air transportation, Aircraft, Aviation November 29, 2011). We are issuing this AD
safety, Incorporation by reference, to detect and correct cracking of the fastener
tkelley on DSK3SPTVN1PROD with PROPOSALS
We also estimate that it would take
about 23 work-hours per product to Safety. holes, which could result in rupture of the
comply with the basic requirements of keel beam, and consequent reduced
The Proposed Amendment structural integrity of the airplane.
this proposed AD. The average labor
rate is $85 per work-hour. Based on Accordingly, under the authority (f) Compliance
these figures, we estimate the cost of delegated to me by the Administrator, Comply with this AD within the
this proposed AD on U.S. operators to the FAA proposes to amend 14 CFR part compliance times specified, unless already
be $68,425, or $1,955 per product. 39 as follows: done.
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![25254 Federal Register / Vol. 80, No. 85 / Monday, May 4, 2015 / Proposed Rules
(iii) Airbus Service Bulletin A340–57– to the International Branch, send it to ATTN: Notice of proposed rulemaking
ACTION:
4106, Revision 01, dated June 31, 2009. Vladimir Ulyanov, Aerospace Engineer, (NPRM).
(iv) Airbus Service Bulletin A340–57– International Branch, ANM–116, Transport
4106, Revision 02, dated June 15, 2011. Airplane Directorate, FAA, 1601 Lind SUMMARY: We propose to adopt a new
(2) For airplanes that have been modified Avenue SW., Renton, WA 98057–3356; airworthiness directive (AD) for all
as of the effective date of this AD in telephone 425–227–1138; fax 425–227–1149. Dassault Aviation Model FAN JET
accordance with the Accomplishment Information may be emailed to: 9-ANM-116-
FALCON, FAN JET FALCON SERIES C,
Instructions of the applicable service AMOC-REQUESTS@faa.gov. Before using
any approved AMOC, notify your appropriate D, E, F, and G airplanes; Model
information identified in paragraph (n)(1)(i),
(n)(1)(ii), (n)(1)(iii), or (n)(1)(iv) of this AD: principal inspector, or lacking a principal MYSTERE–FALCON 200 airplanes; and
No action is required by this paragraph, inspector, the manager of the local flight Model MYSTERE–FALCON 20–C5, 20–
except as otherwise required by paragraph (l) standards district office/certificate holding D5, 20–E5, and 20–F5 airplanes. This
of this AD and, provided that if any crack district office. The AMOC approval letter proposed AD was prompted by reports
was found during any modification specified must specifically reference this AD. of defective fire extinguisher tubes. It
in this paragraph and the service information (2) AMOCs approved previously for AD was determined the defects were caused
specified to contact Airbus, repair was done 2011–24–05, Amendment 39–16869 (76 FR
by corrosion. This proposed AD would
before further flight using a method approved 73496, November 29, 2011), are approved as
AMOCs for the corresponding provisions of require repetitive general visual
by the Manager, International Branch, ANM– inspections of the fire extinguisher
116, Transport Airplane Directorate, FAA; or this AD.
(3) Contacting the Manufacturer: As of the tubes for cracking and corrosion, and
EASA; or Airbus’s EASA DOA. If approved
by the DOA, the approval must include the effective date of this AD, for any requirement replacement of any cracked tube with a
in this AD to obtain corrective actions from serviceable tube, if necessary. We are
DOA-authorized signature.
a manufacturer, the action must be proposing this AD to detect and correct
(o) Optional Terminating Actions accomplished using a method approved by cracking and corrosion in the fire
the Manager, International Branch, ANM–
(1) Modification of an airplane in extinguisher tubes, which could impact
accordance with the Accomplishment 116, Transport Airplane Directorate, FAA; or
EASA; or Airbus’s EASA DOA. If approved the capability to extinguish an engine
Instructions of the applicable service fire, and possibly result in damage to
by the DOA, the approval must include the
information identified in paragraph (o)(1)(i), the airplane and injury to the
DOA-authorized signature.
(o)(1)(ii), (o)(1)(iii), (o)(1)(iv), (o)(1)(v), or passengers.
(o)(1)(vi) of this AD; as applicable to airplane (q) Related Information
type and depending on airplane DATES: We must receive comments on
(1) Refer to Mandatory Continuing
configuration; terminates the requirements of Airworthiness Information (MCAI) EASA this proposed AD by June 18, 2015.
this AD, provided that in case of any crack Airworthiness Directive 2014–0010R1, dated ADDRESSES: You may send comments,
finding during any modification specified in May 5, 2014, for related information. This using the procedures found in 14 CFR
this paragraph, and the service information MCAI may be found in the AD docket on the 11.43 and 11.45, by any of the following
specifies to contact Airbus, repair is done Internet at http://www.regulations.gov by
before further flight, using a method
methods:
approved by the Manager, International
searching for and locating Docket No. FAA– • Federal eRulemaking Portal: Go to
2015–0937. http://www.regulations.gov. Follow the
Branch, ANM–116, Transport Airplane (2) For service information identified in
Directorate, FAA; or EASA; or Airbus’s EASA instructions for submitting comments.
this AD, contact Airbus SAS—Airworthiness
DOA. If approved by the DOA, the approval Office—EAL, 1 Rond Point Maurice Bellonte,
• Fax: 202–493–2251.
must include the DOA-authorized signature 31707 Blagnac Cedex, France; telephone +33
• Mail: U.S. Department of
(i) Airbus Service Bulletin A330–57–3090, 5 61 93 36 96; fax +33 5 61 93 45 80; email Transportation, Docket Operations, M–
dated March 27, 2006. airworthiness.A330-A340@airbus.com; 30, West Building Ground Floor, Room
(ii) Airbus Service Bulletin A330–57–3090, Internet http://www.airbus.com. You may W12–140, 1200 New Jersey Avenue SE.,
Revision 01, dated June 15, 2011. view this service information at the FAA, Washington, DC 20590.
(iii) Airbus Service Bulletin A330–57– Transport Airplane Directorate, 1601 Lind • Hand Delivery: U.S. Department of
3098, Revision 03, including Appendix 01, Avenue SW., Renton, WA. For information Transportation, Docket Operations, M–
dated September 24, 2012. on the availability of this material at the 30, West Building Ground Floor, Room
(iv) Airbus Service Bulletin A340–57– FAA, call 425–227–1221.
4098, dated March 27, 2006.
W12–140, 1200 New Jersey Avenue SE.,
(v) Airbus Service Bulletin A340–57–4098, Issued in Renton, Washington, on April 13, Washington, DC, between 9 a.m. and 5
Revision 01, dated June 15, 2011. 2015. p.m., Monday through Friday, except
(vi) Airbus Service Bulletin A340–57– Michael Kaszycki, Federal holidays.
4106, Revision 03, including Appendix 01, Acting Manager, Transport Airplane
Examining the AD Docket
dated September 24, 2012. Directorate, Aircraft Certification Service.
(2) Accomplishment of the ultrasonic [FR Doc. 2015–10177 Filed 5–1–15; 8:45 am] You may examine the AD docket on
inspection required by paragraph (l) of this
BILLING CODE 4910–13–P
the Internet at http://
AD and all applicable corrective actions www.regulations.gov by searching for
required by paragraph (m) of this AD and locating Docket No. FAA–2015–
terminates the requirements of this AD for 0934; or in person at the Docket
those airplanes. DEPARTMENT OF TRANSPORTATION
Management Facility between 9 a.m.
(p) Other FAA AD Provisions Federal Aviation Administration and 5 p.m., Monday through Friday,
The following provisions also apply to this except Federal holidays. The AD docket
AD: 14 CFR Part 39 contains this proposed AD, the
(1) Alternative Methods of Compliance regulatory evaluation, any comments
[Docket No. FAA–2015–0934; Directorate
(AMOCs): The Manager, International received, and other information. The
tkelley on DSK3SPTVN1PROD with PROPOSALS
Identifier 2014–NM–030–AD]
Branch, ANM–116, Transport Airplane street address for the Docket Operations
Directorate, FAA, has the authority to RIN 2120–AA64 office (telephone 800–647–5527) is in
approve AMOCs for this AD, if requested the ADDRESSES section. Comments will
using the procedures found in 14 CFR 39.19. Airworthiness Directives; Dassault
In accordance with 14 CFR 39.19, send your
be available in the AD docket shortly
Aviation Airplanes after receipt.
request to your principal inspector or local
Flight Standards District Office, as AGENCY:Federal Aviation FOR FURTHER INFORMATION CONTACT: Tom
appropriate. If sending information directly Administration (FAA), DOT. Rodriguez, Aerospace Engineer,
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Document Created: 2018-02-21 10:22:49
Document Modified: 2018-02-21 10:22:49
| 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 June 18, 2015. | |
| Contact | Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1138; fax 425-227-1149. | |
| FR Citation | 80 FR 25249 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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