81 FR 1497 - Airworthiness Directives; Airbus Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 81, Issue 8 (January 13, 2016)
Federal Aviation Administration
Federal Register Volume 81, Issue 8 (January 13, 2016)
| Page Range | 1497-1502 | |
| FR Document | 2015-32256 |
[Federal Register Volume 81, Number 8 (Wednesday, January 13, 2016)] [Rules and Regulations] [Pages 1497-1502] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2015-32256] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2015-0937; Directorate Identifier 2014-NM-024-AD; Amendment 39-18348; AD 2015-25-10] RIN 2120-AA64 Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. ----------------------------------------------------------------------- SUMMARY: We are superseding 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 required repetitive inspections for cracking of the hole(s) of the horizontal flange of the keel beam, and repair if necessary. This new AD requires changing the inspection compliance times, and, for certain airplanes, adding a one- time ultrasonic inspection for cracking at a certain fastener hole. This new AD also provides optional terminating action for the repetitive inspections. This AD was prompted by a determination that the rototest inspection and applicable corrective actions of a certain fastener hole were inadvertently omitted from the requirements in AD 2011-24-05. 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. DATES: This AD becomes effective February 17, 2016. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of February 17, 2016. The Director of the Federal Register approved the incorporation by reference of certain other publications listed in this AD as of January 3, 2012 (76 FR 73496, November 29, 2011). The Director of the Federal Register approved the incorporation by reference of certain other publications listed in this AD as of September 13, 2007 (72 FR 44731, August 9, 2007). ADDRESSES: You may examine the AD docket on the Internet at http://www.regulations.gov/#!docketDetail;D=FAA-2015-0937; or in person at the Docket Management Facility, U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC. For service information identified in this final rule, 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. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015- 0937. 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: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 2011-24-05, Amendment 39-16869 (76 FR 73496, November 29, 2011). AD 2011-24-05 applied to 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 NPRM published in the Federal Register on May 4, 2015 (80 FR 25249). 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 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 hole cold working, was inadvertently not included in [[Page 1498]] 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/#!documentDetail;D=FAA-2015-0937-0002. Comments We gave the public the opportunity to participate in developing this AD. We received no comments on the NPRM (80 FR 25249, May 4, 2015) or on the determination of the cost to the public. Conclusion We reviewed the available data and determined that air safety and the public interest require adopting this AD as proposed, except for minor editorial changes. We have determined that these minor changes:Are consistent with the intent that was proposed in the NPRM (80 FR 25249, May 4, 2015) for correcting the unsafe condition; and Do not add any additional burden upon the public than was already proposed in the NPRM (80 FR 25249, May 4, 2015). Related Service Information Under 1 CFR Part 51 Airbus has issued the following service information. Airbus Service Bulletin A330-57-3081, Revision 05, dated November 13, 2012. Airbus Service Bulletin A330-57-3090, Revision 01, 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, dated September 24, 2012. Airbus Service Bulletin A330-57-3117, dated January 25, 2013. Airbus Service Bulletin A340-57-4089, Revision 05, 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, dated June 15, 2011. Airbus Service Bulletin A340-57-4106, Revision 03, dated September 24, 2012. Airbus Service Bulletin A340-57-4126, 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 optional terminating action for the repetitive inspections. 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. Costs of Compliance We estimate that this AD affects 35 airplanes of U.S. registry. The actions that were required by AD 2011-24-05, Amendment 39-16869 (76 FR 73496, November 29, 2011), and retained in this 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 were required by AD 2011-24-05 is $3,676 per product. We also estimate that it takes about 23 work-hours per product to comply with the basic requirements of this AD. The average labor rate is $85 per work-hour. Based on these figures, we estimate the cost of this 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 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 AD will not have federalism implications under Executive Order 13132. This AD will 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 that this AD: 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. Examining the AD Docket You may examine the AD docket on the Internet at http://www.regulations.gov/#!docketDetail;D=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 AD, the regulatory evaluation, any comments received, and other [[Page 1499]] information. The street address for the Docket Operations office (telephone 800-647-5527) is in the ADDRESSES section. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 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: 2015-25-10 Airbus: Amendment 39-18348. Docket No. FAA-2015-0937; Directorate Identifier 2014-NM-024-AD. (a) Effective Date This AD becomes effective February 17, 2016. (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. (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 Airbus Mandatory Service Bulletin A330-57-3081, including Appendix 01, Revision 04, dated May 31, 2011; or Airbus Mandatory 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 (the effective date of AD 2007-16-02, Amendment 39-15141 (72 FR 44731, August 9, 2007)), whichever occurs later. The compliance times for Model A330 post-mod. 41652 and pre-mod. 44360, post-mod. 44360, and pre-mod. 49202 (as 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 (as 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 Airbus Mandatory Service Bulletin A330-57-3081, including Appendix 01, Revision 04, dated May 31, 2011; or Airbus Mandatory 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 Mandatory Service Bulletin A330-57-3081, including Appendix 01, Revision 04, dated May 31, 2011; or Airbus Mandatory Service Bulletin A340-57-4089, including Appendix 01, Revision 04, dated May 31, 2011; as applicable; or within 3 [[Page 1500]] 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 Mandatory Service Bulletin A330-57-3081, including Appendix 01, Revision 04, dated May 31, 2011. (4) Airbus Service Bulletin A330-57-3081, Revision 05, dated November 13, 2012. (5) Airbus Mandatory Service Bulletin A340-57-4089, including Appendix 01, Revision 04, dated May 31, 2011. (6) Airbus Service Bulletin A340-57-4089, Revision 05, 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 Mandatory Service Bulletin A330-57-3081, including Appendix 01, Revision 04, dated May 31, 2011; or Airbus Mandatory Service Bulletin A340-57-4089, including Appendix 01, Revision 04, dated May 31, 2011; 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, dated September 24, 2012, or Airbus Service Bulletin A340-57-4106, Revision 03, 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, Amendment 39-16869 (76 FR 73496, November 29, 2011)). (ii) Modification in accordance with Airbus Service Bulletin A330-57-3098, Revision 03, 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, 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, dated November 13, 2012; or Airbus Service Bulletin A340-57-4089, Revision 05, 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, dated November 13, 2012; or Airbus Service Bulletin A340-57-4089, Revision 05, 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, dated November 13, 2012; or Airbus Service Bulletin A340-57-4089, Revision 05, 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, dated November 13, 2012; or Airbus Service Bulletin A340-57-4089, Revision 05, 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. This service information was incorporated by reference in AD 2011-24-05, Amendment 39-16869 (76 FR 73496, November 29, 2011). (i) Airbus A330/A340 200-300 Technical Disposition F57D03012810, Issue B, dated August 18, 2003. (ii) Airbus A330/A340 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, which is not incorporated by reference in this AD. (ii) Airbus Service Bulletin A330-57-3081, Revision 01, dated May 18, 2004, which is not incorporated by reference in this AD. (iii) Airbus Service Bulletin A330-57-3081, Revision 02, including Appendix 01, dated January 24, 2006, which was incorporated by reference in AD 2007-12-08, Amendment 39-15086 (72 FR 31171, June 6, 2007). (iv) Airbus Mandatory Service Bulletin A330-57-3081, Revision 03, dated July 31, 2009, which is not incorporated by reference in this AD. (v) Airbus Service Bulletin A340-57-4089, dated October 30, 2003, which is not incorporated by reference in this AD. (vi) Airbus Service Bulletin A340-57-4089, Revision 01, dated March 2, 2004, which is not incorporated by reference in this AD. (vii) Airbus Service Bulletin A340-57-4089, Revision 02, including Appendix 01, dated January 24, 2006, which was incorporated by reference in AD 2007-12-08, Amendment 39-15086 (72 FR 31171, June 6, 2007). (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 [[Page 1501]] 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, dated January 25, 2013; or Airbus Service Bulletin A340-57-4126, 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, 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, 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, excluding Appendix 1, 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, excluding Appendix 1, 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, dated November 13, 2012; or Airbus Service Bulletin A340-57-4089, Revision 05, 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, dated November 13, 2012; or Airbus Service Bulletin A340-57-4089, Revision 05, 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, excluding Appendix 1, Revision 01, dated July 31, 2009. (ii) Airbus Service Bulletin A330-57-3098, Revision 02, dated June 15, 2011. (iii) Airbus Service Bulletin A340-57-4106, excluding Appendix 1, 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, 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, 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 terminate 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-2015-0937-0002. (2) Service information identified in this AD that is not incorporated by reference in this AD is available at the addresses specified in paragraphs (r)(5) and (r)(6) of this AD. (r) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference [[Page 1502]] (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless this AD specifies otherwise. (3) The following service information was approved for IBR on February 17, 2016. (i) Airbus Service Bulletin A330-57-3081, Revision 05, dated November 13, 2012. (ii) Airbus Service Bulletin A330-57-3090, Revision 01, dated June 15, 2011. (iii) Airbus Service Bulletin A330-57-3098, dated August 30, 2007. (iv) Airbus Service Bulletin A330-57-3098, Revision 02, June 15, 2011. (v) Airbus Service Bulletin A330-57-3098, Revision 03, dated September 24, 2012. (vi) Airbus Service Bulletin A330-57-3117, dated January 25, 2013. (vii) Airbus Service Bulletin A340-57-4089, Revision 05, dated November 13, 2012. (viii) Airbus Service Bulletin A340-57-4098, Revision 01, dated June 15, 2011. (ix) Airbus Service Bulletin A340-57-4106, dated August 30, 2007. (x) Airbus Service Bulletin A340-57-4106, Revision 02, dated June 15, 2011. (xi) Airbus Service Bulletin A340-57-4106, Revision 03, dated September 24, 2012. (xii) Airbus Service Bulletin A340-57-4126, dated January 25, 2013. (4) The following service information was approved for IBR on January 3, 2012 (76 FR 73496, November 29, 2011). (i) Airbus Mandatory Service Bulletin A330-57-3081, including Appendix 01, Revision 04, dated May 31, 2011. (ii) Airbus Service Bulletin A330-57-3098, Revision 01, excluding Appendix 1, dated July 31, 2009. (iii) Airbus Mandatory Service Bulletin A340-57-4089, including Appendix 01, Revision 04, dated May 31, 2011. (iv) Airbus Service Bulletin A340-57-4106, excluding Appendix 1, Revision 01, dated July 31, 2009. (5) The following service information was approved for IBR on September 13, 2007 (72 FR 44731, August 9, 2007). (i) Airbus Service Bulletin A330-57-3081, Revision 02, including Appendix 01, dated January 24, 2006. (ii) Airbus Service Bulletin A340-57-4089, Revision 02, including Appendix 01, dated January 24, 2006. (6) 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. (7) 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. (7) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html. Issued in Renton, Washington, on December 9, 2015. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015-32256 Filed 1-12-16; 8:45 am] BILLING CODE 4910-13-P
![Federal Register / Vol. 81, No. 8 / Wednesday, January 13, 2016 / Rules and Regulations 1497
KS 67209; phone: 316–946–4142; fax: 316– flange of the keel beam, and repair if 98057–3356; telephone 425–227–1138;
946–4107; email: paul.devore@faa.gov. necessary. This new AD requires fax 425–227–1149.
(m) Material Incorporated by Reference changing the inspection compliance SUPPLEMENTARY INFORMATION:
(1) The Director of the Federal Register times, and, for certain airplanes, adding
a one-time ultrasonic inspection for Discussion
approved the incorporation by reference
(IBR) of the service information listed in this cracking at a certain fastener hole. This We issued a notice of proposed
paragraph under 5 U.S.C. 552(a) and 1 CFR new AD also provides optional rulemaking (NPRM) to amend 14 CFR
part 51. terminating action for the repetitive part 39 to supersede AD 2011–24–05,
(2) You must use this service information inspections. This AD was prompted by Amendment 39–16869 (76 FR 73496,
as applicable to do the actions required by a determination that the rototest November 29, 2011). AD 2011–24–05
this AD, unless the AD specifies otherwise. inspection and applicable corrective applied to certain Airbus Model A330–
(i) Advanced Aircraft Extinguishers Service
Bulletin TFA10–26–0020, Revision IR, dated
actions of a certain fastener hole were 201, –202, –203, –223, –243, –301, –302,
January 12, 2015. inadvertently omitted from the –303, –321, –322, –323, –341, –342, and
(ii) Reserved. requirements in AD 2011–24–05. We are –343 airplanes; and Model A340–200
(3) For service information identified in issuing this AD to detect and correct and –300 series airplanes. The NPRM
this AD, contact Boeing Commercial cracking of the fastener holes, which published in the Federal Register on
Airplanes, Attention: Data & Services could result in rupture of the keel beam, May 4, 2015 (80 FR 25249).
Management, P. O. Box 3707, MC 2H–65, and consequent reduced structural The European Aviation Safety Agency
Seattle, WA 98124–2207; telephone 206– integrity of the airplane. (EASA), which is the Technical Agent
544–5000, extension 1; fax 206–766–5680;
DATES: This AD becomes effective for the Member States of the European
Internet https://www.myboeingfleet.com.
(4) You may view this service information February 17, 2016. Union, has issued EASA Airworthiness
at FAA, Transport Airplane Directorate, 1601 The Director of the Federal Register Directive 2014–0010R1, dated May 5,
Lind Avenue SW., Renton, WA. For approved the incorporation by reference 2014 (referred to after this as the
information on the availability of this of certain publications listed in this AD Mandatory Continuing Airworthiness
material at the FAA, call 425–227–1221. as of February 17, 2016. Information, or ‘‘the MCAI’’), to correct
(5) You may view this service information The Director of the Federal Register an unsafe condition for certain Airbus
that is incorporated by reference at the approved the incorporation by reference Model A330–201, –202, –203, –223,
National Archives and Records –243, –301, –302, –303, –321, –322,
of certain other publications listed in
Administration (NARA). For information on
the availability of this material at NARA, call this AD as of January 3, 2012 (76 FR –323, –341, –342, and –343 airplanes;
202–741–6030, or go to: http:// 73496, November 29, 2011). and Model A340–200 and –300 series
www.archives.gov/federal-register/cfr/ibr- The Director of the Federal Register airplanes. The MCAI states:
locations.html. approved the incorporation by reference During A330 and A340 aeroplanes fatigue
of certain other publications listed in tests, cracks were detected on the RH [right-
Issued in Renton, Washington, on this AD as of September 13, 2007 (72 FR hand] and LH [left-hand] sides between the
December 28, 2015. 44731, August 9, 2007). crossing area of the keel beam fitting and the
Philip Forde, ADDRESSES: You may examine the AD front spar of the Centre Wing Box (CWB).
Acting Manager, Transport Airplane docket on the Internet at http:// This condition, if not detected and
Directorate, Aircraft Certification Service. www.regulations.gov/ corrected, could lead to keel beam rupture
[FR Doc. 2016–00004 Filed 1–12–16; 8:45 am] which would affect the structural integrity of
#!docketDetail;D=FAA-2015-0937; or in the area.
BILLING CODE 4910–13–P person at the Docket Management Prompted by this potential unsafe
Facility, U.S. Department of condition, EASA issued AD 2006–0315
Transportation, Docket Operations, M– [http://ad.easa.europa.eu/blob/easa_ad_
DEPARTMENT OF TRANSPORTATION 30, West Building Ground Floor, Room 2006_0315.pdf/AD_2006-0315] (later revised
W12–140, 1200 New Jersey Avenue SE., to R1) to require repetitive special detailed
Federal Aviation Administration inspections (SDI) [rotating probe inspection
Washington, DC.
For service information identified in for cracking] on the horizontal flange of the
14 CFR Part 39 this final rule, contact Airbus SAS, keel beam in the area of first fastener hole aft
[Docket No. FAA–2015–0937; Directorate Airworthiness Office—EAL, 1 Rond of Frame (FR) 40 in order to maintain the
Identifier 2014–NM–024–AD; Amendment structural integrity of the aeroplane.
Point Maurice Bellonte, 31707 Blagnac After that [EASA] AD was issued, EASA
39–18348; AD 2015–25–10] Cedex, France; telephone +33 5 61 93 36 issued AD 2010–0024 [which corresponds to
RIN 2120–AA64 96; fax +33 5 61 93 45 80; email FAA AD 2011–24–05, Amendment 39–16869
airworthiness.A330-A340@airbus.com; (76 FR 73496, November 29, 2011)], retaining
Airworthiness Directives; Airbus Internet http://www.airbus.com. You the inspection requirements of EASA AD
Airplanes may view this referenced service 2006–0315R1 [http://ad.easa.europa.eu/blob/
information at the FAA, Transport easa_ad_2006_0315R1.pdf/AD_2006-
AGENCY: Federal Aviation Airplane Directorate, 1601 Lind Avenue 0315R1], which was superseded, extending
Administration (FAA), Department of SW., Renton, WA. For information on the applicability to aeroplanes with Airbus
Transportation (DOT). the availability of this material at the
Mod 49202 embodied, and reducing the
ACTION: Final rule. inspection thresholds and intervals.
FAA, call 425–227–1221. It is also Since that [EASA] AD [2010–0024] was
SUMMARY: We are superseding available on the Internet at http:// issued, a new fatigue and damage tolerance
asabaliauskas on DSK5VPTVN1PROD with RULES
Airworthiness Directive (AD) 2011–24– www.regulations.gov by searching for evaluation has been conducted by Airbus,
05 for certain Airbus Model A330–201, and locating Docket No. FAA–2015– which concluded that due to the aeroplane
–202, –203, –223, –243, –301, –302, 0937. utilization, the current inspection threshold
and intervals have to be modified.
–303, –321, –322, –323, –341, –342, and FOR FURTHER INFORMATION CONTACT:
In addition, it was determined that the
–343 airplanes, and Model A340–200 Vladimir Ulyanov, Aerospace Engineer, rototest inspection of fastener hole Nr 6,
and –300 series airplanes. AD 2011–24– International Branch, ANM–116, necessary to ensure that no crack was left
05 required repetitive inspections for Transport Airplane Directorate, FAA, unrepaired at the time of fastener hole cold
cracking of the hole(s) of the horizontal 1601 Lind Avenue SW., Renton, WA working, was inadvertently not included in
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![1498 Federal Register / Vol. 81, No. 8 / Wednesday, January 13, 2016 / Rules and Regulations
Revisions 01 and 02 of both Airbus Service proposed in the NPRM (80 FR 25249, Based on these figures, we estimate the
Bulletin (SB) A330–57–3098 and A340–57– May 4, 2015). cost of this AD on U.S. operators to be
4106. $68,425, or $1,955 per product.
Prompted by these findings, EASA issued Related Service Information Under 1
We have received no definitive data
AD 2014–0010 [http://ad.easa.europa.eu/ CFR Part 51
blob/easa_ad_2014-0010.pdf/AD_2014-0010], that would enable us to provide a cost
retaining the requirements of EASA AD Airbus has issued the following estimate for the on-condition actions
2010–0024, which was superseded, and service information. specified in this AD.
redefined the inspection thresholds and • Airbus Service Bulletin A330–57–
intervals [by reducing certain compliance 3081, Revision 05, dated November 13, Authority for This Rulemaking
times], and added a one-time ultrasonic 2012. Title 49 of the United States Code
inspection of fastener hold Nr 6 in the • Airbus Service Bulletin A330–57– specifies the FAA’s authority to issue
junction keel beam fitting at FR40 on both LH 3090, Revision 01, dated June 15, 2011. rules on aviation safety. Subtitle I,
and RH side[s]. • Airbus Service Bulletin A330–57–
Following issuance of EASA AD 2014–
section 106, describes the authority of
0010, it was identified that there was a need 3098, dated August 30, 2007. the FAA Administrator. ‘‘Subtitle VII:
for clarifications [of affected airplanes] • Airbus Service Bulletin A330–57– Aviation Programs,’’ describes in more
* * *. 3098, Revision 02, June 15, 2011. detail the scope of the Agency’s
• Airbus Service Bulletin A330–57– authority.
The compliance times vary depending
3098, Revision 03, dated September 24, We are issuing this rulemaking under
on airplane utilization and
2012. the authority described in ‘‘Subtitle VII,
configuration. The earliest compliance
• Airbus Service Bulletin A330–57– Part A, Subpart III, Section 44701:
time for the initial rotating probe
3117, dated January 25, 2013. General requirements.’’ Under that
inspections is the later of (1) before
• Airbus Service Bulletin A340–57– section, Congress charges the FAA with
10,400 total flight cycles or 67,800 total
4089, Revision 05, dated November 13, promoting safe flight of civil aircraft in
flight hours, whichever occurs first; and
2012. air commerce by prescribing regulations
(2) within 24 months or 14,590 flight
• Airbus Service Bulletin A340–57– for practices, methods, and procedures
cycles or 43,790 flight hours, whichever
4098, Revision 01, dated June 15, 2011. the Administrator finds necessary for
occurs first. The latest compliance time • Airbus Service Bulletin A340–57–
for the initial inspections is the later of safety in air commerce. This regulation
4106, dated August 30, 2007. is within the scope of that authority
(1) before 20,800 total flight cycles or • Airbus Service Bulletin A340–57–
67,900 total flight hours, whichever because it addresses an unsafe condition
4106, Revision 02, dated June 15, 2011. that is likely to exist or develop on
occurs first; and (2) within 24 months or • Airbus Service Bulletin A340–57–
21,180 flight cycles or 63,560 flight products identified in this rulemaking
4106, Revision 03, dated September 24, action.
hours, whichever occurs first. The 2012.
compliance times for the repetitive • Airbus Service Bulletin A340–57– Regulatory Findings
intervals range between 7,800 flight 4126, dated January 25, 2013.
cycles or 50,900 flight hours and 10,700 We determined that this AD will not
This service information describes have federalism implications under
flight cycles or 35,200 flight hours. The procedures for inspections for cracking
compliance times for the one-time Executive Order 13132. This AD will
of the hole(s) of the horizontal flange of not have a substantial direct effect on
ultrasonic inspection are the latest of (1) the keel beam, and contacting the
21,000 flight cycles or 60,600 flight the States, on the relationship between
manufacturer for repair instructions. the national government and the States,
hours and within 2,400 flight cycles or
Additionally, this service information or on the distribution of power and
24 months; or the latest of (2) 22,100
describes procedures for a one-time responsibilities among the various
flight cycles and 64,400 flight hours, or
ultrasonic inspection for cracking at levels of government.
within 1,300 flight cycles or 24 months.
You may examine the MCAI in the fastener hole ‘‘Nr 6,’’ and provides For the reasons discussed above, I
AD docket on the Internet at http:// optional terminating action for the certify that this AD:
www.regulations.gov/ repetitive inspections. 1. Is not a ‘‘significant regulatory
#!documentDetail;D=FAA-2015-0937- This service information is reasonably action’’ under Executive Order 12866;
0002. available because the interested parties 2. Is not a ‘‘significant rule’’ under the
have access to it through their normal DOT Regulatory Policies and Procedures
Comments course of business or by the means (44 FR 11034, February 26, 1979);
We gave the public the opportunity to identified in the ADDRESSES section. 3. Will not affect intrastate aviation in
participate in developing this AD. We Alaska; and
Costs of Compliance
received no comments on the NPRM (80 4. Will not have a significant
FR 25249, May 4, 2015) or on the We estimate that this AD affects 35 economic impact, positive or negative,
determination of the cost to the public. airplanes of U.S. registry. on a substantial number of small entities
The actions that were required by AD under the criteria of the Regulatory
Conclusion 2011–24–05, Amendment 39–16869 (76 Flexibility Act.
We reviewed the available data and FR 73496, November 29, 2011), and
retained in this AD take about 41 work- Examining the AD Docket
determined that air safety and the
public interest require adopting this AD hours per product, at an average labor You may examine the AD docket on
as proposed, except for minor editorial rate of $85 per work hour. Required the Internet at http://
asabaliauskas on DSK5VPTVN1PROD with RULES
changes. We have determined that these parts cost about $191 per product. Based www.regulations.gov/
minor changes: on these figures, the estimated cost of #!docketDetail;D=FAA-2015-0937; or in
• Are consistent with the intent that the actions that were required by AD person at the Docket Management
was proposed in the NPRM (80 FR 2011–24–05 is $3,676 per product. Facility between 9 a.m. and 5 p.m.,
25249, May 4, 2015) for correcting the We also estimate that it takes about 23 Monday through Friday, except Federal
unsafe condition; and work-hours per product to comply with holidays. The AD docket contains this
• Do not add any additional burden the basic requirements of this AD. The AD, the regulatory evaluation, any
upon the public than was already average labor rate is $85 per work-hour. comments received, and other
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![Federal Register / Vol. 81, No. 8 / Wednesday, January 13, 2016 / Rules and Regulations 1499
information. The street address for the (e) Reason Bulletin A340–57–4098 has been embodied
Docket Operations office (telephone This AD was prompted by reports of cracks in service, and except Model A340–211,
800–647–5527) is in the ADDRESSES on the keel beam fitting and the front spar –212, –213, –311, –312, and –313 airplanes
of the center wing box. This AD was also on which the repair specified in Airbus
section. Repair Drawing R57115053, R57115051, or
prompted by a determination that the rototest
List of Subjects in 14 CFR Part 39 inspection and applicable corrective actions R57115047 has been accomplished: At the
of fastener hole ‘‘Nr 6’’ were inadvertently earlier of the times specified in paragraphs
Air transportation, Aircraft, Aviation omitted from the requirements in AD 2011– (g)(1)(ii)(A) and (g)(1)(ii)(B) of this AD.
safety, Incorporation by reference, 24–05, Amendment 39–16869 (76 FR 73496, (A) Within the ‘‘Mandatory Threshold’’
Safety. November 29, 2011). We are issuing this AD (flight cycles or flight hours) specified in
to detect and correct cracking of the fastener table 1 of paragraph 1.E.(2) of Airbus Service
Adoption of the Amendment holes, which could result in rupture of the Bulletin A340–57–4089, including Appendix
keel beam, and consequent reduced 01, Revision 02, dated January 24, 2006; or
Accordingly, under the authority Airbus Service Bulletin A330–57–3081,
structural integrity of the airplane.
delegated to me by the Administrator, including Appendix 01, Revision 02, dated
the FAA amends 14 CFR part 39 as (f) Compliance January 24, 2006; depending on the
follows: Comply with this AD within the configuration of the aircraft model; or within
compliance times specified, unless already 3 months after September 13, 2007 (the
PART 39—AIRWORTHINESS done. effective date of AD 2007–16–02,
DIRECTIVES Amendment 39–15141 (72 FR 44731, August
(g) Retained Non-Destructive Test (NDT) 9, 2007)), whichever occurs later. The
Inspection compliance times for Model A330 post-mod.
■ 1. The authority citation for part 39
This paragraph restates the requirements of 41652 and pre-mod. 44360, post-mod. 44360,
continues to read as follows: and pre-mod. 49202 (as specified in Airbus
paragraph (n) of AD 2011–24–05,
Authority: 49 U.S.C. 106(g), 40113, 44701. Amendment 39–16869 (76 FR 73496, Service Bulletin A330–57–3081, including
November 29, 2011), with new service Appendix 01, Revision 02, dated January 24,
§ 39.13 [Amended] information and revised credit for certain 2006); and Model A340 post-mod. 41652,
actions. At the applicable time in paragraph post-mod. 43500 and pre-mod. 44360, post-
■ 2. The FAA amends § 39.13 by (g)(1) or (g)(2) of this AD, do an NDT mod. 44360 and pre-mod. 49202, and weight
removing Airworthiness Directive (AD) inspection of the hole(s) of the horizontal variant 027 (as specified in Airbus Service
2011–24–05, Amendment 39–16869 (76 flange of the keel beam located on frame (FR) Bulletin A340–57–4089, including Appendix
FR 73496, November 29, 2011), and 40 datum on the right-hand (RH) and/or left- 01, Revision 02, dated January 24, 2006);
adding the following new AD: hand (LH) side of the fuselage, in accordance specified in the ‘‘Mandatory Threshold’’
with the Accomplishment Instructions of the column in table 1 of paragraph 1.E.,
2015–25–10 Airbus: Amendment 39–18348.
applicable service information specified in ‘‘Compliance,’’ are total flight cycles and
Docket No. FAA–2015–0937; Directorate
paragraph (g)(3), (g)(4), (g)(5), or (g)(6) of this total flight hours.
Identifier 2014–NM–024–AD.
AD. Accomplishing an inspection required (B) Within the ‘‘Mandatory Threshold’’
(a) Effective Date by paragraph (j) of this AD terminates the (flight cycles or flight hours) specified in
This AD becomes effective February 17, inspections required by this paragraph. table 1 of paragraph 1.E.(2) of Airbus
2016. (1) For airplanes on which an inspection Mandatory Service Bulletin A330–57–3081,
required by paragraph (h) of AD 2011–24–05, including Appendix 01, Revision 04, dated
(b) Affected ADs Amendment 39–16869 (76 FR 73496, May 31, 2011; or Airbus Mandatory Service
This AD replaces AD 2011–24–05, November 29, 2011), has not been done as of Bulletin A340–57–4089, including Appendix
Amendment 39–16869 (76 FR 73496, January 3, 2012 (the effective date of AD 01, Revision 04, dated May 31, 2011; as
November 29, 2011). 2011–24–05): At the applicable time applicable; or within 3 months after January
specified in paragraph (g)(1)(i) or (g)(1)(ii) of 3, 2012 (the effective date of AD 2011–24–05,
(c) Applicability this AD. Amendment 39–16869 (76 FR 73496,
(1) This AD applies to the airplanes (i) For all airplanes except those identified November 29, 2011)); whichever occurs later.
identified in paragraphs (c)(1)(i) and (c)(1)(ii) in paragraph (g)(1)(ii) of this AD: Within the The compliance times for configurations 02
of this AD, certificated in any category, ‘‘Mandatory Threshold’’ (flight cycles or through 06 specified in the ‘‘Mandatory
except as provided by paragraph (c)(2) of this flight hours) specified in table 1 of paragraph Threshold’’ column in table 1 of paragraph
AD. 1.E.(2) of Airbus Mandatory Service Bulletin 1.E., ‘‘Compliance,’’ are total flight cycles and
(i) Airbus Model A330–201, –202, –203, A330–57–3081, including Appendix 01, total flight hours.
–223, –243, –301, –302, –303, –321, –322, Revision 04, dated May 31, 2011; or Airbus (2) For airplanes on which an inspection
–323, –341, –342, and –343 airplanes, all Mandatory Service Bulletin A340–57–4089, required by paragraph (h) of AD 2011–24–05,
serial numbers, except those on which including Appendix 01, Revision 04, dated Amendment 39–16869 (76 FR 73496,
Airbus modification 55306 or 55792 has been May 31, 2011; as applicable; or within 3 November 29, 2011), has been done as of
embodied in production. months after January 3, 2012 (the effective January 3, 2012 (the effective date of AD
(ii) Airbus Model A340–211, –212, –213, date AD 2011–24–05, Amendment 39–16869 2011–24–05): At the earlier of the times
–311, –312, and –313 airplanes, all serial (76 FR 73496, November 29, 2011)); specified in paragraphs (g)(2)(i) and (g)(2)(ii)
numbers, except those on which Airbus whichever occurs later. The compliance of this AD.
modification 55306 or 55792 has been times for configurations 02 through 06 (i) Within the ‘‘Mandatory Intervals’’ given
embodied in production. specified in the ‘‘Mandatory Threshold’’ in table 1 of paragraph 1.E.(2) of Airbus
(2) This AD does not apply to Airbus column in table 1 of paragraph 1.E., Service Bulletin A340–57–4089, including
Model A340–211, –212, –213, –311, –312, ‘‘Compliance,’’ are total flight cycles and Appendix 01, Revision 02, dated January 24,
and –313 airplanes on which the repair total flight hours. 2006; or Airbus Service Bulletin A330–57–
specified in Airbus Repair Drawing (ii) For Model A330–201, –202, –203, –223, 3081, including Appendix 01, Revision 02,
asabaliauskas on DSK5VPTVN1PROD with RULES
R57115053, R57115051, or R57115047 –243, –301, –321, –322, –323, –341, –342, dated January 24, 2006; as applicable.
(installation of titanium doubler on both and –343 airplanes, except those on which (ii) Within the applicable ‘‘Mandatory
sides) has been accomplished. AD 2007–12– Airbus modification 49202 has been Interval’’ specified in table 1 of Paragraph
08, Amendment 39–15086 (72 FR 31171, embodied in production, or Airbus Service 1.E.(2) of Airbus Mandatory Service Bulletin
June 6, 2007), applies to these airplanes. Bulletin A330–57–3090 has been embodied A330–57–3081, including Appendix 01,
in service; and Model A340–200 and –300 Revision 04, dated May 31, 2011; or Airbus
(d) Subject series airplanes, except those on which Mandatory Service Bulletin A340–57–4089,
Air Transport Association (ATA) of Airbus modification 49202 has been including Appendix 01, Revision 04, dated
America Code 57, Wings. embodied in production or Airbus Service May 31, 2011; as applicable; or within 3
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![1502 Federal Register / Vol. 81, No. 8 / Wednesday, January 13, 2016 / Rules and Regulations
(IBR) of the service information listed in this Issued in Renton, Washington, on www.regulations.gov by searching for
paragraph under 5 U.S.C. 552(a) and 1 CFR December 9, 2015. and locating Docket No. FAA–2015–
part 51. Michael Kaszycki, 4213; or in person at the Docket
(2) You must use this service information
Acting Manager, Transport Airplane Management Facility between 9 a.m.
as applicable to do the actions required by
Directorate, Aircraft Certification Service. and 5 p.m., Monday through Friday,
this AD, unless this AD specifies otherwise.
(3) The following service information was [FR Doc. 2015–32256 Filed 1–12–16; 8:45 am] except Federal holidays. The AD docket
approved for IBR on February 17, 2016. BILLING CODE 4910–13–P contains this AD, the regulatory
(i) Airbus Service Bulletin A330–57–3081, evaluation, any comments received, and
Revision 05, dated November 13, 2012. other information. The address for the
(ii) Airbus Service Bulletin A330–57–3090, DEPARTMENT OF TRANSPORTATION Docket Office (telephone: 800–647–
Revision 01, dated June 15, 2011. 5527) is Document Management
(iii) Airbus Service Bulletin A330–57– Federal Aviation Administration Facility, U.S. Department of
3098, dated August 30, 2007.
(iv) Airbus Service Bulletin A330–57– Transportation, Docket Operations, M–
14 CFR Part 39 30, West Building Ground Floor, Room
3098, Revision 02, June 15, 2011.
(v) Airbus Service Bulletin A330–57–3098, [Docket No. FAA–2015–4213; Directorate W12–140, 1200 New Jersey Avenue SE.,
Revision 03, dated September 24, 2012. Identifier 2015–CE–022–AD; Amendment Washington, DC 20590.
(vi) Airbus Service Bulletin A330–57– 39–18359; AD 2016–01–01] FOR FURTHER INFORMATION CONTACT:
3117, dated January 25, 2013. Gregory ‘‘Keith’’ Noles, Aerospace
(vii) Airbus Service Bulletin A340–57– RIN 2120–AA64
4089, Revision 05, dated November 13, 2012. Engineer, FAA, Atlanta Aircraft
(viii) Airbus Service Bulletin A340–57– Airworthiness Directives; Piper Certification Office, 1701 Columbia
4098, Revision 01, dated June 15, 2011. Aircraft, Inc. Airplanes Avenue, College Park, Georgia 30337;
(ix) Airbus Service Bulletin A340–57– telephone: (404) 474–5551; fax: (404)
4106, dated August 30, 2007. AGENCY: Federal Aviation 474–5606; email: gregory.noles@faa.gov.
(x) Airbus Service Bulletin A340–57–4106, Administration (FAA), DOT. SUPPLEMENTARY INFORMATION:
Revision 02, dated June 15, 2011. ACTION: Final rule.
(xi) Airbus Service Bulletin A340–57– Discussion
4106, Revision 03, dated September 24, 2012. SUMMARY: We are adopting a new
(xii) Airbus Service Bulletin A340–57– We issued a notice of proposed
airworthiness directive (AD) for certain rulemaking (NPRM) to amend 14 CFR
4126, dated January 25, 2013. Piper Aircraft, Inc. Model PA–46–500TP
(4) The following service information was part 39 by adding an AD that would
airplanes. This AD was prompted by a apply to certain Piper Aircraft, Inc.
approved for IBR on January 3, 2012 (76 FR
73496, November 29, 2011). report of the wing upper skin joints Model PA–46–500TP airplanes. The
(i) Airbus Mandatory Service Bulletin being manufactured without sealant, NPRM published in the Federal
A330–57–3081, including Appendix 01, which allows water to enter and stay in Register on October 19, 2015 (80 FR
Revision 04, dated May 31, 2011. sealed, bonded stringers. This AD 63151). The NPRM was prompted by a
(ii) Airbus Service Bulletin A330–57–3098, requires inspecting the upper wing report of wing upper skin joints on
Revision 01, excluding Appendix 1, dated surface for sealant; inspecting the wing
July 31, 2009. Piper Aircraft, Inc. Model PA–46–500TP
stringers for water intrusion; inspecting airplanes being manufactured without
(iii) Airbus Mandatory Service Bulletin for deformation and corrosion if
A340–57–4089, including Appendix 01, sealant, which allows water to enter and
evidence of water intrusion exists; and stay in sealed, bonded stringers. The
Revision 04, dated May 31, 2011.
(iv) Airbus Service Bulletin A340–57– taking corrective actions as necessary. NPRM proposed to require inspecting
4106, excluding Appendix 1, Revision 01, We are issuing this AD to correct the the upper wing surface for sealant;
dated July 31, 2009. unsafe condition on these products. inspecting the wing stringers for water
(5) The following service information was DATES: This AD is effective February 17, intrusion; inspecting for deformation
approved for IBR on September 13, 2007 (72 2016. and corrosion if evidence of water
FR 44731, August 9, 2007). The Director of the Federal Register
(i) Airbus Service Bulletin A330–57–3081, intrusion exists; and taking corrective
approved the incorporation by reference actions as necessary. We are issuing this
Revision 02, including Appendix 01, dated
January 24, 2006. of a certain publication listed in this AD AD to correct the unsafe condition on
(ii) Airbus Service Bulletin A340–57–4089, as of February 17, 2016. these products.
Revision 02, including Appendix 01, dated ADDRESSES: For service information
January 24, 2006. Related Service Information Under 1
identified in this AD, contact Piper
(6) For service information identified in CFR Part 51
Aircraft, Inc., Customer Service, 2926
this AD, contact Airbus SAS, Airworthiness Piper Drive, Vero Beach, Florida 32960; We reviewed Piper Aircraft, Inc.
Office—EAL, 1 Rond Point Maurice Bellonte, Service Bulletin No. 1262B, dated April
telephone: (877) 879–0275; fax: none;
31707 Blagnac Cedex, France; telephone +33
email: customer.service@piper.com; 23, 2015. The service bulletin provides
5 61 93 36 96; fax +33 5 61 93 45 80; email
airworthiness.A330-A340@airbus.com; Internet: www.piper.com. You may view instructions for inspecting the upper
Internet http://www.airbus.com. this referenced service information at wing surface for sealant and sealing or
(7) You may view this service information the FAA, Small Airplane Directorate, resealing (if necessary). This service
at the FAA, Transport Airplane Directorate, 901 Locust, Kansas City, Missouri bulletin also provides instructions for
1601 Lind Avenue SW., Renton, WA. For 64106. For information on the inspecting the wing stringers for water
information on the availability of this availability of this material at the FAA, intrusion, and, if water intrusion was
asabaliauskas on DSK5VPTVN1PROD with RULES
material at the FAA, call 425–227–1221. call (816) 329–4148. It is also available found as a result of the inspection,
(7) You may view this service information inspecting for corrosion or deformation.
on the Internet at http://
that is incorporated by reference at the
www.regulations.gov by searching for This service information is reasonably
National Archives and Records
Administration (NARA). For information on locating Docket No. FAA–2015–4213. available because the interested parties
the availability of this material at NARA, call have access to it through their normal
Examining the AD Docket course of business or by the means
202–741–6030, or go to: http://
www.archives.gov/federal-register/cfr/ibr- You may examine the AD docket on identified in the ADDRESSES section of
locations.html. the Internet at http:// this final rule.
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Document Created: 2016-01-13 01:00:51
Document Modified: 2016-01-13 01:00:51
| 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 | Rules and Regulations | |
| Action | Final rule. | |
| Dates | This AD becomes effective February 17, 2016. | |
| Contact | Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1138; fax 425-227-1149. | |
| FR Citation | 81 FR 1497 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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