81 FR 21246 - Airworthiness Directives; Airbus Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 81, Issue 69 (April 11, 2016)
Federal Aviation Administration
Federal Register Volume 81, Issue 69 (April 11, 2016)
| Page Range | 21246-21250 | |
| FR Document | 2016-07574 |
[Federal Register Volume 81, Number 69 (Monday, April 11, 2016)] [Rules and Regulations] [Pages 21246-21250] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2016-07574] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2015-1426; Directorate Identifier 2013-NM-200-AD; Amendment 39-18462; AD 2016-07-17] 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) 97-20-07 for certain Airbus Model A300 B4-600, B4-600R, and F4-600R series airplanes, and Model A300 C4-605R Variant F airplanes (collectively called Model A300-600 series airplanes). AD 97-20-07 required repetitive inspections to detect fatigue cracking in the left and right wings in the area where the top skin attaches to the center spar, and repair or modification of this area if necessary. This new AD reduces the inspection compliance time and repetitive inspection intervals. This AD was prompted by a determination that the inspection compliance time and repetitive inspection interval must be reduced to allow timely detection of fatigue cracking in the left and right wings in the area where the top skin attaches to the center spar. We are issuing this AD to detect and correct this fatigue cracking, which could reduce the residual strength of the top skin of the wings, and consequently [[Page 21247]] affect the structural integrity of the airframe. DATES: This AD becomes effective May 16, 2016. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of May 16, 2016. The Director of the Federal Register approved the incorporation by reference of a certain other publication listed in this AD as of October 30, 1997 (62 FR 50251, September 25, 1997). ADDRESSES: For service information identified in this final rule, contact Airbus SAS, Airworthiness Office--EAW, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email [email protected]; Internet http://www.airbus.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015- 1426. Examining the AD Docket You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015- 1426; 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 information. The street address for the Docket Operations office (telephone 800-647-5527) is in the ADDRESSES section. FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-2125; fax 425-227-1149. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 97-20-07, Amendment 39-10145 (62 FR 50251, September 25, 1997) (``AD 97-20-07''). AD 97-20-07 applied to certain Airbus Model A300 B4-600, B4-600R, and F4-600R series airplanes, and Model A300 C4-605R Variant F airplanes (collectively called Model A300- 600 series airplanes). The NPRM published in the Federal Register on June 5, 2015 (80 FR 32058) (``the NPRM''). The NPRM was prompted by a determination that the inspection compliance time and repetitive inspection interval must be reduced to allow timely detection of fatigue cracking in the left and right wings in the area where the top skin attaches to the center spar. The NPRM proposed to continue to require repetitive inspections to detect fatigue cracking in the left and right wings in the area where the top skin attaches to the center spar, and repair or modification of this area if necessary. The NPRM also proposed to reduce the inspection compliance time and repetitive inspection intervals. We are issuing this AD to detect and correct this fatigue cracking, which could reduce the residual strength of the top skin of the wings, and consequently affect the structural integrity of the airframe. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2013-0221, dated September 19, 2013 (referred to after this as the Mandatory Continuing Airworthiness Information, or ``the MCAI''), to correct an unsafe condition for certain Airbus Model A300 B4-600, B4-600R, and F4-600R series airplanes, and Model A300 C4- 605R Variant F airplanes (collectively called Model A300-600 series airplanes). The MCAI states: During fatigue tests conducted in the early 1990's, cracks were found on the top skin of the wing at the centre spar joint between ribs 1 and 7. Consequently, Airbus developed production mod. 10089 and issued Service Bulletin (SB) A300-57-6041, involving installation of a reinforcing plate on the affected area. Despite this improvement, subsequent cases of cracks were reported by operators. This condition, if not detected and corrected, could adversely affect the structural integrity of the aeroplane. To address this potential unsafe condition, Airbus issued SB A300-57-6044 and DGAC [Direction G[eacute]n[eacute]rale de l'Aviation Civile] France issued * * * [an airworthiness directive] (later revised twice) to require repetitive inspections of the affected area and, depending on findings, accomplishment of applicable corrective action(s). Since [the French] * * * [airworthiness directive] [which corresponds to FAA AD 97-20-07, Amendment 39-10145 (62 FR 50251, September 25, 1997)] was issued, a fleet survey and updated Fatigue and Damage Tolerance Analyses were performed in order to substantiate the second A300-600 Extended Service Goal (ESG2) exercise. The results of these analyses have shown that the inspection thresholds and intervals must be reduced to allow timely detection of these cracks and accomplishment of an applicable corrective action. Prompted by these findings, Airbus issued SB A300-57-6044 Revision 04 [dated August 19, 2011]. For the reasons described above, this [EASA] AD retains the requirements of [the French AD] * * * which is superseded, but requires the repetitive inspections to be accomplished at reduced thresholds and intervals and, depending on findings, corrective actions. 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- 1426. Comments We gave the public the opportunity to participate in developing this AD. We received no comments on the NPRM or on the determination of the cost to the public. Changes Made to This Final Rule Paragraph (m)(2) of the proposed AD inadvertently included the corrective action for the low frequency eddy current (LFEC) inspections for cracking specified in paragraphs (k) and (l) of the proposed AD; however, the corrective action in paragraph (m)(2) of this AD applies only to the new high frequency eddy current (HFEC) inspections required by this AD. We have revised paragraph (m)(2) of this AD to specify the corrective action for the HFEC inspections for cracking specified in paragraphs (i), (j), and (m)(1) of this AD. We have added new paragraph (m)(4) of this AD to specify the corrective actions for the LFEC inspections specified in paragraphs (k) and (l) of this AD. Conclusion We reviewed the available data and determined that air safety and the public interest require adopting this AD with the changes described previously and minor editorial changes. We have determined that these changes:Are consistent with the intent that was proposed in the NPRM for correcting the unsafe condition; and Do not add any additional burden upon the public than was already proposed in the NPRM. Related Service Information Under 1 CFR Part 51 Airbus has issued Service Bulletin A300-57-6044, Revision 04, dated August 19, 2011, including Appendix 01, Revision 04, dated August 19, 2011. The service information describes procedures for inspections to detect fatigue cracking in the left and right wings in the area where the top skin attaches to the center spar, and repair or modification of this area. This service information is reasonably available [[Page 21248]] 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 47 airplanes of U.S. registry. The actions required by AD 97-20-07, and retained in this AD take about 3 work-hours per product, at an average labor rate of $85 per work-hour. Based on these figures, the estimated cost of the actions that were required by AD 97-20-07 is $255 per product. We also estimate that it will take about 5 work-hours per product to comply with the new 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 $19,975, or $425 per product We have received no definitive data that would enable us to provide cost estimates 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. 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) 97-20-07, Amendment 39-10145 (62 FR 50251, September 25, 1997), and adding the following new AD: 2016-07-17 Airbus: Amendment 39-18462. Docket No. FAA-2015-1426; Directorate Identifier 2013-NM-200-AD. (a) Effective Date This AD becomes effective May 16, 2016. (b) Affected ADs This AD replaces AD 97-20-07, Amendment 39-10145 (62 FR 50251, September 25, 1997) (``AD 97-20-07''). (c) Applicability This AD applies to the Airbus airplanes identified in paragraphs (c)(1) through (c)(4) of this AD, certificated in any category, all manufacturer serial numbers except those on which Airbus Modification 10160 has been done in production. (1) Airbus Model A300 B4-601, B4-603, B4-620, and B4-622 airplanes. (2) Airbus Model A300 B4-605R and B4-622R airplanes. (3) Airbus Model A300 F4-605R and F4-622R airplanes. (4) Airbus Model A300 C4-605R Variant F airplanes. (d) Subject Air Transport Association (ATA) of America Code 57, Wings. (e) Reason This AD was prompted by a determination that the inspection compliance time and repetitive inspection interval must be reduced to allow timely detection of fatigue cracking in the left and right wings in the area where the top skin attaches to the center spar. We are issuing this AD to detect and correct this fatigue cracking, which could reduce the residual strength of the top skin of the wings, and consequently affect the structural integrity of the airframe. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Retained Repetitive Inspections and Corrective Actions, With Revised Service Information This paragraph restates the requirements of paragraph (a) of AD 97-20-07, with revised service information. For airplanes on which Airbus Modification 10089 has not been installed: Prior to the accumulation of 18,000 total landings, or within 1,500 landings after October 30, 1997 (the effective date of AD 97-20-07), whichever occurs later, conduct either a detailed visual inspection or a high frequency eddy current (HFEC) inspection to detect fatigue cracking in the left and right wings in the area where the top skin attaches to the center spar between ribs 1 and 7, in accordance with Airbus Service Bulletin A300-57-6044, Revision 2, dated September 6, 1995, including Appendix 1, Revision 1, dated November 25, 1994; or Airbus Service Bulletin A300-57-6044, Revision 04, dated August 19, 2011, including Appendix 01, Revision 04, dated August 19, 2011. As of the effective date of this AD, use only Airbus Service Bulletin A300-57-6044, Revision 04, dated August 19, 2011, including Appendix 01, Revision 04, dated August 19, 2011. Accomplishment of the inspection required by paragraph (i) of this AD terminates the inspection requirements of this paragraph. (1) If no cracking is detected, conduct repetitive inspections thereafter at the following intervals: (i) If the immediately preceding inspection was conducted using detailed visual inspection techniques, conduct the next inspection within 5,000 landings. (ii) If the immediately preceding inspection was conducted using HFEC techniques, conduct the next inspection within 9,500 landings. (2) If any cracking is detected or suspected during any detailed visual inspection required by the introductory text of paragraph (g), paragraph (g)(1), or paragraph (g)(3)(i) of this AD, prior to further flight, confirm this finding and the length of this cracking by conducting an HFEC inspection, in accordance with Airbus Service Bulletin A300-57-6044, Revision 2, dated September 6, 1995, including Appendix 1, Revision 1, dated November 25, 1994; or Airbus Service Bulletin A300-57-6044, Revision 04, dated August 19, 2011, including Appendix 01, Revision 04, dated August 19, 2011. As of the effective date of this AD, use only Airbus Service Bulletin A300-57- 6044, Revision 04, dated August 19, 2011, including Appendix 01, Revision 04, dated August 19, 2011. If no cracking is confirmed during the HFEC inspection, accomplish the repetitive inspection required by paragraph (g)(1)(ii) of this AD at the time specified in that paragraph. [[Page 21249]] (3) If any cracking is detected or confirmed during any HFEC inspection required by the introductory text of paragraph (g), paragraph (g)(1), or paragraph (g)(2) of this AD: (i) If the cracking is 75 millimeters (mm) or less per rib bay, prior to further flight, repair in accordance with Airbus Service Bulletin A300-57-6044, Revision 2, dated September 6, 1995, including Appendix 1, Revision 1, dated November 25, 1994; or Airbus Service Bulletin A300-57-6044, Revision 04, dated August 19, 2011, including Appendix 01, Revision 04, dated August 19, 2011. As of the effective date of this AD, use only Airbus Service Bulletin A300-57- 6044, Revision 04, dated August 19, 2011, including Appendix 01, Revision 04, dated August 19, 2011. Thereafter, conduct repetitive detailed visual inspections of the repaired area at intervals not to exceed 50 landings, in accordance with Airbus Service Bulletin A300- 57-6044, Revision 2, dated September 6, 1995, including Appendix 1, Revision 1, dated November 25, 1994; or Airbus Service Bulletin A300-57-6044, Revision 04, dated August 19, 2011, including Appendix 01, Revision 04, dated August 19, 2011. As of the effective date of this AD, use only Airbus Service Bulletin A300-57-6044, Revision 04, dated August 19, 2011, including Appendix 01, Revision 04, dated August 19, 2011. (ii) If the cracking exceeds 75 mm per rib bay, prior to further flight, install Airbus Modification 10089, in accordance with Airbus Service Bulletin A300-57-6044, Revision 2, dated September 6, 1995, including Appendix 1, Revision 1, dated November 25, 1994; or Airbus Service Bulletin A300-57-6044, Revision 04, dated August 19, 2011, including Appendix 01, Revision 04, dated August 19, 2011. As of the effective date of this AD, use only Airbus Service Bulletin A300-57- 6044, Revision 04, dated August 19, 2011, including Appendix 01, Revision 04, dated August 19, 2011. Thereafter, conduct a low frequency eddy current (LFEC) inspection in accordance with the requirements of paragraph (h) of this AD. Note 1 to paragraph (g) of this AD: Airbus Service Bulletin A300-57-6044, Revision 2, dated September 6, 1995, including Appendix 1, Revision 1, dated November 25, 1994, references Airbus Service Bulletin A300-57-6041, Revision 4, dated November 16, 1995, as an additional source of guidance for installing Airbus Modification 10089. (h) Retained Repetitive Inspections and Corrective Actions for Certain Airplanes, With Revised Service Information and Repair Instructions This paragraph restates the requirements of paragraph (b) of AD 97-20-07, with revised service information and repair instructions. For airplanes on which Airbus Modification 10089 has been installed: Prior to the accumulation of 22,000 total landings after this modification has been installed, or within 1,500 landings after October 30, 1997 (the effective date of AD 97-20-07), whichever occurs later, conduct a LFEC inspection to detect fatigue cracking in the inboard and rear edges of the top skin reinforcing plates, in accordance with Airbus Service Bulletin A300-57-6044, Revision 2, dated September 6, 1995, including Appendix 1, Revision 1, dated November 25, 1994; or Airbus Service Bulletin A300-57-6044, Revision 04, dated August 19, 2011, including Appendix 01, Revision 04, dated August 19, 2011. As of the effective date of this AD, use only Airbus Service Bulletin A300-57-6044, Revision 04, dated August 19, 2011, including Appendix 01, Revision 04, dated August 19, 2011. Accomplishment of the inspection required by paragraph (k) of this AD terminates the inspection requirements of this paragraph. (1) If no cracking is detected, repeat this inspection thereafter at intervals not to exceed 11,000 landings. (2) If any cracking is detected, prior to further flight, repair in accordance with a method approved by the Manager, Standardization Branch, ANM-113, Transport Airplane Directorate, FAA. As of the effective date of this AD, 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). Thereafter, repeat this inspection at intervals not to exceed 11,000 landings. (i) New Requirement of This AD: Initial Inspections For airplanes on which Airbus Modification 10089 has not been installed: At the applicable time specified in paragraphs (i)(1) and (i)(2) of this AD, do either a detailed visual inspection or an HFEC inspection to detect fatigue cracking in the left and right wings in the area where the top skin attaches to the center spar between ribs 1 and 7, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-57-6044, Revision 04, dated August 19, 2011, including Appendix 01, Revision 04, dated August 19, 2011. Accomplishment of the inspection required by this paragraph terminates the inspection requirements of paragraph (g) of this AD. (1) For airplanes whose flight time average is equal to or more than 1.5 hours, at the later of the times specified in paragraphs (i)(1)(i) and (i)(1)(ii) of this AD. (i) Before the accumulation of 14,000 total flight cycles or 30,300 total flight hours, whichever occurs first. (ii) Within 1,500 flight cycles or 3,200 flight hours after the effective date of this AD, whichever occurs first. (2) For airplanes whose flight time average is less than 1.5 hours, at the later of the times specified in paragraphs (i)(2)(i) and (i)(2)(ii) of this AD. (i) Before the accumulation of 15,100 total flight cycles or 22,700 total flight hours, whichever occurs first. (ii) Within 1,600 flight cycles or 2,500 flight hours after the effective date of this AD, whichever occurs first. (j) New Requirement of This AD: Repetitive Inspections Repeat the inspections specified in paragraph (i) of this AD thereafter at the applicable interval specified in paragraphs (j)(1) and (j)(2) of this AD. (1) For airplanes whose flight time average is equal to or more than 1.5 hours, at the applicable interval specified in paragraphs (j)(1)(i) and (j)(1)(ii) of this AD. (i) For a detailed visual inspection, at intervals not to exceed 3,900 flight cycles or 8,400 flight hours, whichever occurs first. (ii) For an HFEC inspection, at intervals not to exceed 7,400 flight cycles or 16,000 flight hours, whichever occurs first. (2) For airplanes whose flight time average is less than 1.5 hours, at the applicable interval specified in paragraphs (j)(2)(i) and (j)(2)(ii) of this AD. (i) For a detailed visual inspection, at intervals not to exceed 4,200 flight cycles or 6,300 flight hours, whichever occurs first. (ii) For an HFEC inspection, at intervals not to exceed 8,000 flight cycles or 11,900 flight hours, whichever occurs first. (k) New Requirement of This AD: Initial Inspection for Certain Airplanes For airplanes on which Airbus Modification 10089 has been installed: At the applicable time specified in paragraphs (k)(1) and (k)(2) of this AD, do an LFEC inspection to detect fatigue cracking in the inboard and rear edges of the top skin reinforcing plates, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-57-6044, Revision 04, dated August 19, 2011, including Appendix 01, Revision 04, dated August 19, 2011. Accomplishment of the inspection required by this paragraph terminates the inspection requirements of paragraph (h) of this AD. (1) For airplanes whose flight time average is equal to or more than 1.5 hours, at the later of the times specified in paragraphs (k)(1)(i) and (k)(1)(ii) of this AD. (i) Before the accumulation of 17,000 total flight cycles or 37,100 total flight hours, whichever occurs first. (ii) Within 1,500 flight cycles or 3,200 flight hours after the effective date of this AD, whichever occurs first. (2) For airplanes whose flight time average is less than 1.5 hours, at the later of the times specified in paragraphs (k)(2)(i) and (k)(2)(ii) of this AD. (i) Before the accumulation of 18,500 total flight cycles or 27,800 total flight hours, whichever occurs first. (ii) Within 1,600 flight cycles or 2,500 flight hours after the effective date of this AD, whichever occurs first. (l) New Requirement of This AD: Repetitive Inspections for Certain Airplanes Repeat the inspection specified in paragraph (k) of this AD thereafter at the applicable interval specified in paragraphs (l)(1) and (l)(2) of this AD. (1) For airplanes whose flight time average is equal to or more than 1.5 hours, at intervals not to exceed 8,500 flight cycles or 18,500 flight hours, whichever occurs first. (2) For airplanes whose flight time average is less than 1.5 hours, at intervals not to exceed 9,200 flight cycles or 13,700 flight hours, whichever occurs first. (m) New Requirement of This AD: Corrective Actions (1) If any cracking is detected or suspected during any detailed inspection required by paragraph (i) or (j) of this AD: Before further flight, confirm this finding and the length of [[Page 21250]] this cracking by conducting an HFEC inspection, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-57- 6044, Revision 04, dated August 19, 2011, including Appendix 01, Revision 04, dated August 19, 2011, except as specified in paragraph (o) of this AD. If no cracking is confirmed during the HFEC inspection, accomplish the applicable repetitive inspections required by paragraphs (j) and (l) of this AD at the applicable time specified in those paragraphs. (2) If any cracking is found during any HFEC inspection required by paragraph (i), (j), or (m)(1) of this AD: Before further flight, do the applicable actions specified in paragraphs (m)(2)(i) and (m)(2)(ii) of this AD. (i) If the cracking is 75 mm or less per each rib bay: Before further flight, repair the cracking, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-57-6044, Revision 04, dated August 19, 2011, including Appendix 01, Revision 04, dated August 19, 2011, except as specified in paragraph (o) of this AD. Do repetitive detailed inspections of the repaired area thereafter at intervals not to exceed 50 flight cycles or 110 flight hours, whichever occurs first, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-57-6044, Revision 04, dated August 19, 2011, including Appendix 01, Revision 04, dated August 19, 2011. Within 250 flight cycles or 550 flight hours, whichever occurs first after doing the temporary repair, do a permanent repair of the repaired area, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-57-6044, Revision 04, dated August 19, 2011, including Appendix 01, Revision 04, dated August 19, 2011. (ii) If the cracking exceeds 75 mm per any rib bay: Before further flight, install Airbus Modification 10089, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-57-6044, Revision 04, dated August 19, 2011, including Appendix 01, Revision 04, dated August 19, 2011. Do an LFEC inspection thereafter at the intervals specified in paragraph (l) of this AD. (3) If any cracking is found during any inspection required by this AD at fastener hole 1A, 1, or 2: Before further flight, repair the cracking, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-57-6044, Revision 04, dated August 19, 2011, including Appendix 01, Revision 04, dated August 19, 2011. (4) If any cracking is found during any LFEC inspection required by paragraph (k) 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. (n) Credit for Previous Actions This paragraph provides credit for actions required by paragraphs (i) through (l) of this AD, if those actions were performed before the effective date of this AD using Airbus Service Bulletin A300-57-6044, Revision 03, dated April 7, 1999, including Appendix 01, Revision 03, dated April 7, 1999, which is not incorporated by reference in this AD. (o) Exception to Service Information Specification Although Airbus Service Bulletin A300-57-6044, Revision 04, dated August 19, 2011, including Appendix 01, Revision 04, dated August 19, 2011, specifies to submit information to Airbus, this AD does not require that submission. (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: Dan Rodina, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057- 3356; telephone 425-227-2125; fax 425-227-1149. 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) 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 2013-0221, dated September 19, 2013, 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-2015-1426. (2) Service information identified in this AD that is not incorporated by reference 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 (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 May 16, 2016 (i) Airbus Service Bulletin A300-57-6044, Revision 04, dated August 19, 2011, including Appendix 01, Revision 04, dated August 19, 2011. (ii) Reserved. (4) The following service information was approved for IBR on October 30, 1997 (62 FR 50251, September 25, 1997). (i) Airbus Service Bulletin A300-57-6044, Revision 2, dated September 6, 1995, including Appendix 1, Revision 1, dated November 25, 1994. Pages 1 through 8 of this document are identified as Revision 2, dated September 6, 1995; pages 9 and 10 are identified as original, dated March 1, 1993. Page 1 of Appendix 1 is identified as Revision 1, dated November 25, 1994; and pages 2 through 6 are identified as original, dated March 1, 1993. (ii) Reserved. (5) For service information identified in this AD, contact Airbus SAS, Airworthiness Office--EAW, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email [email protected]; Internet http://www.airbus.com. (6) 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 March 24, 2016. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016-07574 Filed 4-8-16; 8:45 am] BILLING CODE 4910-13-P
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which Airbus Modification 30975 has been (i)(2), or (i)(3) of this AD. This service telephone +33 5 61 93 36 96; fax +33 5 61
embodied in production. information is not incorporated by reference 93 44 51; email account.airworth-eas@
(1) Airbus Model A319–111, –112, –113, in this AD. airbus.com; Internet http://www.airbus.com.
–114, –115, –131, –132, and –133 airplanes. (1) Airbus Service Bulletin A320–53–1266, (4) You may view this service information
(2) Airbus Model A320–211, –212, –214, dated January 11, 2013. at the FAA, Transport Airplane Directorate,
–231, –232, and –233 airplanes. (2) Airbus Service Bulletin A320–53–1266, 1601 Lind Avenue SW., Renton, WA. For
(3) Airbus Model A321–111, –112, –131, Revision 01, dated June 20, 2013. information on the availability of this
–211, –212, –213, –231, and –232 airplanes. (3) Airbus Service Bulletin A320–53–1266, material at the FAA, call 425–227–1221.
Revision 02, dated August 13, 2014. (5) You may view this service information
(d) Subject
(j) Other FAA AD Provisions that is incorporated by reference at the
Air Transport Association (ATA) of National Archives and Records
America Code 53, Fuselage. The following provisions also apply to this Administration (NARA). For information on
AD: the availability of this material at NARA, call
(e) Reason (1) Alternative Methods of Compliance 202–741–6030, or go to: http://
This AD was prompted by fatigue testing (AMOCs): The Manager, International www.archives.gov/federal-register/cfr/ibr-
that determined that fatigue damage could Branch, ANM–116, Transport Airplane locations.html.
appear on clips, shear webs, and angles at Directorate, FAA, has the authority to
certain rear fuselage sections and certain approve AMOCs for this AD, if requested Issued in Renton, Washington, on March
frames. This AD is intended to complete using the procedures found in 14 CFR 39.19. 25, 2016.
certain mandated programs intended to In accordance with 14 CFR 39.19, send your Michael Kaszycki,
support the airplane reaching its limit of request to your principal inspector or local Acting Manager, Transport Airplane
validity of the engineering data that support Flight Standards District Office, as Directorate, Aircraft Certification Service.
the established structural maintenance appropriate. If sending information directly
[FR Doc. 2016–07375 Filed 4–8–16; 8:45 am]
program. We are issuing this AD to prevent to the International Branch, send it to ATTN:
fatigue damage on the clips, shear webs, and Sanjay Ralhan, Aerospace Engineer, BILLING CODE 4910–13–P
angles, which could affect the structural International Branch, ANM–116, Transport
integrity of the airplane. Airplane Directorate, FAA, 1601 Lind
Avenue SW., Renton, WA 98057–3356; DEPARTMENT OF TRANSPORTATION
(f) Compliance telephone 425–227–1405; fax 425–227–1149.
Comply with this AD within the Information may be emailed to: 9-ANM-116- Federal Aviation Administration
compliance times specified, unless already AMOC-REQUESTS@faa.gov. Before using
done. any approved AMOC, notify your appropriate 14 CFR Part 39
principal inspector, or lacking a principal
(g) Replacement
inspector, the manager of the local flight [Docket No. FAA–2015–1426; Directorate
At the later of the times specified in standards district office/certificate holding Identifier 2013–NM–200–AD; Amendment
paragraphs (g)(1) and (g)(2) of this AD: district office. The AMOC approval letter 39–18462; AD 2016–07–17]
Replace the clips, shear webs, and angles at must specifically reference this AD.
rear fuselage section 19, frame FR72 and (2) Contacting the Manufacturer: For any RIN 2120–AA64
FR74, and do all applicable related requirement in this AD to obtain corrective
investigative actions before further flight, in actions from a manufacturer, the action must Airworthiness Directives; Airbus
accordance with the Accomplishment be accomplished using a method approved
Instructions of Airbus Service Bulletin A320– Airplanes
by the Manager, International Branch, ANM–
53–1266, Revision 03, dated May 7, 2015. If 116, Transport Airplane Directorate, FAA; or AGENCY: Federal Aviation
any crack is found during any related the EASA; or Airbus’s EASA DOA. If
investigative action required by this AD:
Administration (FAA), Department of
approved by the DOA, the approval must
Before further flight, repair using a method Transportation (DOT).
include the DOA-authorized signature.
approved by the Manager, International ACTION: Final rule.
Branch, ANM–116, Transport Airplane (k) Related Information
Directorate, FAA; or the European Aviation (1) Refer to Mandatory Continuing SUMMARY: We are superseding
Safety Agency (EASA); or Airbus’s EASA Airworthiness Information (MCAI) EASA Airworthiness Directive (AD) 97–20–07
Design Organization Approval (DOA). Airworthiness Directive 2014–0177, dated for certain Airbus Model A300 B4–600,
(1) Before exceeding 48,000 flight cycles or July 25, 2014, for related information. This B4–600R, and F4–600R series airplanes,
96,000 flight hours, whichever occurs first MCAI may be found in the AD docket on the and Model A300 C4–605R Variant F
since the airplane’s first flight. Internet at http://www.regulations.gov by
(2) Within 30 days after the effective date airplanes (collectively called Model
searching for and locating Docket No. FAA–
of this AD. 2015–1277. A300–600 series airplanes). AD 97–20–
(2) Service information identified in this 07 required repetitive inspections to
(h) Additional Replacement for Certain detect fatigue cracking in the left and
AD that is not incorporated by reference is
Airplanes
available at the addresses specified in right wings in the area where the top
For airplanes on which the replacement of paragraphs (l)(3) and (l)(4) of this AD. skin attaches to the center spar, and
clips, shear webs, and angles specified in repair or modification of this area if
Airbus Service Bulletin A320–53–1266 is (l) Material Incorporated by Reference
necessary. This new AD reduces the
done before accumulating 30,000 flight (1) The Director of the Federal Register
cycles or 60,000 flight hours, whichever approved the incorporation by reference inspection compliance time and
occurred first since the airplane’s first flight: (IBR) of the service information listed in this repetitive inspection intervals. This AD
Within 30,000 flight cycles or 60,000 flight paragraph under 5 U.S.C. 552(a) and 1 CFR was prompted by a determination that
hours, whichever occurs first after that part 51. the inspection compliance time and
replacement, do the replacement specified in (2) You must use this service information repetitive inspection interval must be
paragraph (g) of this AD. as applicable to do the actions required by reduced to allow timely detection of
jstallworth on DSK7TPTVN1PROD with RULES
this AD, unless this AD specifies otherwise. fatigue cracking in the left and right
(i) Credit for Previous Actions (i) Airbus Service Bulletin A320–53–1266, wings in the area where the top skin
Except as required by paragraph (h) of this Revision 03, dated May 7, 2015.
AD: This paragraph provides credit for the (ii) Reserved. attaches to the center spar. We are
replacement required by paragraph (g) of this (3) For service information identified in issuing this AD to detect and correct
AD, if those actions were performed before this AD, contact Airbus, Airworthiness this fatigue cracking, which could
the effective date of this AD using the service Office—EIAS, 1 Rond Point Maurice reduce the residual strength of the top
information identified in paragraph (i)(1), Bellonte, 31707 Blagnac Cedex, France; skin of the wings, and consequently
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![Federal Register / Vol. 81, No. 69 / Monday, April 11, 2016 / Rules and Regulations 21247
affect the structural integrity of the in the Federal Register on June 5, 2015 corrective action. Prompted by these
airframe. (80 FR 32058) (‘‘the NPRM’’). The findings, Airbus issued SB A300–57–6044
NPRM was prompted by a Revision 04 [dated August 19, 2011].
DATES: This AD becomes effective May For the reasons described above, this
16, 2016. determination that the inspection
[EASA] AD retains the requirements of [the
The Director of the Federal Register compliance time and repetitive French AD] * * * which is superseded, but
approved the incorporation by reference inspection interval must be reduced to requires the repetitive inspections to be
of a certain publication listed in this AD allow timely detection of fatigue accomplished at reduced thresholds and
as of May 16, 2016. cracking in the left and right wings in intervals and, depending on findings,
The Director of the Federal Register the area where the top skin attaches to corrective actions.
approved the incorporation by reference the center spar. The NPRM proposed to You may examine the MCAI in the
of a certain other publication listed in continue to require repetitive AD docket on the Internet at http://
this AD as of October 30, 1997 (62 FR inspections to detect fatigue cracking in www.regulations.gov by searching for
50251, September 25, 1997). the left and right wings in the area and locating Docket No. FAA–2015–
ADDRESSES: For service information where the top skin attaches to the center 1426.
identified in this final rule, contact spar, and repair or modification of this
area if necessary. The NPRM also Comments
Airbus SAS, Airworthiness Office—
EAW, 1 Rond Point Maurice Bellonte, proposed to reduce the inspection We gave the public the opportunity to
31707 Blagnac Cedex, France; telephone compliance time and repetitive participate in developing this AD. We
+33 5 61 93 36 96; fax +33 5 61 93 44 inspection intervals. We are issuing this received no comments on the NPRM or
51; email account.airworth-eas@ AD to detect and correct this fatigue on the determination of the cost to the
airbus.com; Internet http:// cracking, which could reduce the public.
www.airbus.com. You may view this residual strength of the top skin of the
Changes Made to This Final Rule
referenced service information at the wings, and consequently affect the
FAA, Transport Airplane Directorate, structural integrity of the airframe. Paragraph (m)(2) of the proposed AD
1601 Lind Avenue SW., Renton, WA. The European Aviation Safety Agency inadvertently included the corrective
For information on the availability of (EASA), which is the Technical Agent action for the low frequency eddy
this material at the FAA, call 425–227– for the Member States of the European current (LFEC) inspections for cracking
1221. It is also available on the Internet Union, has issued EASA Airworthiness specified in paragraphs (k) and (l) of the
at http://www.regulations.gov by Directive 2013–0221, dated September proposed AD; however, the corrective
searching for and locating Docket No. 19, 2013 (referred to after this as the action in paragraph (m)(2) of this AD
FAA–2015–1426. Mandatory Continuing Airworthiness applies only to the new high frequency
Information, or ‘‘the MCAI’’), to correct eddy current (HFEC) inspections
Examining the AD Docket an unsafe condition for certain Airbus required by this AD. We have revised
You may examine the AD docket on Model A300 B4–600, B4–600R, and F4– paragraph (m)(2) of this AD to specify
the Internet at http:// 600R series airplanes, and Model A300 the corrective action for the HFEC
www.regulations.gov by searching for C4–605R Variant F airplanes inspections for cracking specified in
and locating Docket No. FAA–2015– (collectively called Model A300–600 paragraphs (i), (j), and (m)(1) of this AD.
1426; or in person at the Docket series airplanes). The MCAI states: We have added new paragraph (m)(4) of
Management Facility between 9 a.m. During fatigue tests conducted in the early
this AD to specify the corrective actions
and 5 p.m., Monday through Friday, 1990’s, cracks were found on the top skin of for the LFEC inspections specified in
except Federal holidays. The AD docket the wing at the centre spar joint between ribs paragraphs (k) and (l) of this AD.
contains this AD, the regulatory 1 and 7.
Conclusion
evaluation, any comments received, and Consequently, Airbus developed
other information. The street address for production mod. 10089 and issued Service We reviewed the available data and
Bulletin (SB) A300–57–6041, involving determined that air safety and the
the Docket Operations office (telephone installation of a reinforcing plate on the
800–647–5527) is in the ADDRESSES public interest require adopting this AD
affected area. Despite this improvement, with the changes described previously
section. subsequent cases of cracks were reported by
operators.
and minor editorial changes. We have
FOR FURTHER INFORMATION CONTACT: Dan determined that these changes:
This condition, if not detected and
Rodina, Aerospace Engineer, corrected, could adversely affect the • Are consistent with the intent that
International Branch, ANM–116, structural integrity of the aeroplane. was proposed in the NPRM for
Transport Airplane Directorate, FAA, To address this potential unsafe condition, correcting the unsafe condition; and
1601 Lind Avenue SW., Renton, WA Airbus issued SB A300–57–6044 and DGAC • Do not add any additional burden
98057–3356; telephone 425–227–2125; [Direction Générale de l’Aviation Civile] upon the public than was already
fax 425–227–1149. France issued * * * [an airworthiness proposed in the NPRM.
directive] (later revised twice) to require
SUPPLEMENTARY INFORMATION:
repetitive inspections of the affected area Related Service Information Under 1
Discussion and, depending on findings, accomplishment CFR Part 51
of applicable corrective action(s).
We issued a notice of proposed Since [the French] * * * [airworthiness Airbus has issued Service Bulletin
rulemaking (NPRM) to amend 14 CFR directive] [which corresponds to FAA AD A300–57–6044, Revision 04, dated
part 39 to supersede AD 97–20–07, 97–20–07, Amendment 39–10145 (62 FR August 19, 2011, including Appendix
Amendment 39–10145 (62 FR 50251, 50251, September 25, 1997)] was issued, a 01, Revision 04, dated August 19, 2011.
jstallworth on DSK7TPTVN1PROD with RULES
September 25, 1997) (‘‘AD 97–20–07’’). fleet survey and updated Fatigue and Damage The service information describes
AD 97–20–07 applied to certain Airbus Tolerance Analyses were performed in order procedures for inspections to detect
Model A300 B4–600, B4–600R, and F4– to substantiate the second A300–600 fatigue cracking in the left and right
Extended Service Goal (ESG2) exercise. The
600R series airplanes, and Model A300 results of these analyses have shown that the wings in the area where the top skin
C4–605R Variant F airplanes inspection thresholds and intervals must be attaches to the center spar, and repair or
(collectively called Model A300–600 reduced to allow timely detection of these modification of this area. This service
series airplanes). The NPRM published cracks and accomplishment of an applicable information is reasonably available
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![21248 Federal Register / Vol. 81, No. 69 / Monday, April 11, 2016 / Rules and Regulations
because the interested parties have 2. Is not a ‘‘significant rule’’ under the area where the top skin attaches to the center
access to it through their normal course DOT Regulatory Policies and Procedures spar. We are issuing this AD to detect and
of business or by the means identified (44 FR 11034, February 26, 1979); correct this fatigue cracking, which could
3. Will not affect intrastate aviation in reduce the residual strength of the top skin
in the ADDRESSES section.
of the wings, and consequently affect the
Alaska; and
Costs of Compliance structural integrity of the airframe.
4. Will not have a significant
We estimate that this AD affects 47 economic impact, positive or negative, (f) Compliance
airplanes of U.S. registry. on a substantial number of small entities Comply with this AD within the
The actions required by AD 97–20–07, under the criteria of the Regulatory compliance times specified, unless already
and retained in this AD take about 3 Flexibility Act. done.
work-hours per product, at an average List of Subjects in 14 CFR Part 39 (g) Retained Repetitive Inspections and
labor rate of $85 per work-hour. Based Corrective Actions, With Revised Service
Air transportation, Aircraft, Aviation Information
on these figures, the estimated cost of safety, Incorporation by reference,
the actions that were required by AD Safety. This paragraph restates the requirements of
97–20–07 is $255 per product. paragraph (a) of AD 97–20–07, with revised
Adoption of the Amendment service information. For airplanes on which
We also estimate that it will take
Airbus Modification 10089 has not been
about 5 work-hours per product to Accordingly, under the authority installed: Prior to the accumulation of 18,000
comply with the new basic delegated to me by the Administrator, total landings, or within 1,500 landings after
requirements of this AD. The average the FAA amends 14 CFR part 39 as October 30, 1997 (the effective date of AD
labor rate is $85 per work-hour. Based follows: 97–20–07), whichever occurs later, conduct
on these figures, we estimate the cost of either a detailed visual inspection or a high
this AD on U.S. operators to be $19,975, PART 39—AIRWORTHINESS frequency eddy current (HFEC) inspection to
or $425 per product DIRECTIVES detect fatigue cracking in the left and right
wings in the area where the top skin attaches
We have received no definitive data ■ 1. The authority citation for part 39 to the center spar between ribs 1 and 7, in
that would enable us to provide cost continues to read as follows: accordance with Airbus Service Bulletin
estimates for the on-condition actions A300–57–6044, Revision 2, dated September
specified in this AD. Authority: 49 U.S.C. 106(g), 40113, 44701.
6, 1995, including Appendix 1, Revision 1,
§ 39.13 [Amended] dated November 25, 1994; or Airbus Service
Authority for This Rulemaking Bulletin A300–57–6044, Revision 04, dated
■ 2. The FAA amends § 39.13 by August 19, 2011, including Appendix 01,
Title 49 of the United States Code
removing Airworthiness Directive (AD) Revision 04, dated August 19, 2011. As of the
specifies the FAA’s authority to issue
97–20–07, Amendment 39–10145 (62 effective date of this AD, use only Airbus
rules on aviation safety. Subtitle I,
FR 50251, September 25, 1997), and Service Bulletin A300–57–6044, Revision 04,
section 106, describes the authority of dated August 19, 2011, including Appendix
adding the following new AD:
the FAA Administrator. ‘‘Subtitle VII: 01, Revision 04, dated August 19, 2011.
Aviation Programs,’’ describes in more 2016–07–17 Airbus: Amendment 39–18462. Accomplishment of the inspection required
detail the scope of the Agency’s Docket No. FAA–2015–1426; Directorate by paragraph (i) of this AD terminates the
Identifier 2013–NM–200–AD.
authority. inspection requirements of this paragraph.
We are issuing this rulemaking under (a) Effective Date (1) If no cracking is detected, conduct
repetitive inspections thereafter at the
the authority described in ‘‘Subtitle VII, This AD becomes effective May 16, 2016.
following intervals:
Part A, Subpart III, Section 44701: (b) Affected ADs (i) If the immediately preceding inspection
General requirements.’’ Under that was conducted using detailed visual
This AD replaces AD 97–20–07,
section, Congress charges the FAA with inspection techniques, conduct the next
Amendment 39–10145 (62 FR 50251,
promoting safe flight of civil aircraft in September 25, 1997) (‘‘AD 97–20–07’’). inspection within 5,000 landings.
air commerce by prescribing regulations (ii) If the immediately preceding inspection
for practices, methods, and procedures (c) Applicability was conducted using HFEC techniques,
the Administrator finds necessary for This AD applies to the Airbus airplanes conduct the next inspection within 9,500
safety in air commerce. This regulation identified in paragraphs (c)(1) through (c)(4) landings.
of this AD, certificated in any category, all (2) If any cracking is detected or suspected
is within the scope of that authority
manufacturer serial numbers except those on during any detailed visual inspection
because it addresses an unsafe condition required by the introductory text of
which Airbus Modification 10160 has been
that is likely to exist or develop on paragraph (g), paragraph (g)(1), or paragraph
done in production.
products identified in this rulemaking (1) Airbus Model A300 B4–601, B4–603, (g)(3)(i) of this AD, prior to further flight,
action. B4–620, and B4–622 airplanes. confirm this finding and the length of this
(2) Airbus Model A300 B4–605R and B4– cracking by conducting an HFEC inspection,
Regulatory Findings in accordance with Airbus Service Bulletin
622R airplanes.
We determined that this AD will not (3) Airbus Model A300 F4–605R and F4– A300–57–6044, Revision 2, dated September
have federalism implications under 622R airplanes. 6, 1995, including Appendix 1, Revision 1,
(4) Airbus Model A300 C4–605R Variant F dated November 25, 1994; or Airbus Service
Executive Order 13132. This AD will Bulletin A300–57–6044, Revision 04, dated
not have a substantial direct effect on airplanes.
August 19, 2011, including Appendix 01,
the States, on the relationship between (d) Subject Revision 04, dated August 19, 2011. As of the
the national government and the States, Air Transport Association (ATA) of effective date of this AD, use only Airbus
jstallworth on DSK7TPTVN1PROD with RULES
or on the distribution of power and America Code 57, Wings. Service Bulletin A300–57–6044, Revision 04,
responsibilities among the various dated August 19, 2011, including Appendix
(e) Reason 01, Revision 04, dated August 19, 2011. If no
levels of government.
This AD was prompted by a determination cracking is confirmed during the HFEC
For the reasons discussed above, I
that the inspection compliance time and inspection, accomplish the repetitive
certify that this AD: repetitive inspection interval must be inspection required by paragraph (g)(1)(ii) of
1. Is not a ‘‘significant regulatory reduced to allow timely detection of fatigue this AD at the time specified in that
action’’ under Executive Order 12866; cracking in the left and right wings in the paragraph.
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![21250 Federal Register / Vol. 81, No. 69 / Monday, April 11, 2016 / Rules and Regulations
this cracking by conducting an HFEC (o) Exception to Service Information (ii) Reserved.
inspection, in accordance with the Specification (4) The following service information was
Accomplishment Instructions of Airbus Although Airbus Service Bulletin A300– approved for IBR on October 30, 1997 (62 FR
Service Bulletin A300–57–6044, Revision 04, 57–6044, Revision 04, dated August 19, 2011, 50251, September 25, 1997).
dated August 19, 2011, including Appendix including Appendix 01, Revision 04, dated (i) Airbus Service Bulletin A300–57–6044,
01, Revision 04, dated August 19, 2011, August 19, 2011, specifies to submit Revision 2, dated September 6, 1995,
except as specified in paragraph (o) of this information to Airbus, this AD does not including Appendix 1, Revision 1, dated
AD. If no cracking is confirmed during the require that submission. November 25, 1994. Pages 1 through 8 of this
HFEC inspection, accomplish the applicable document are identified as Revision 2, dated
repetitive inspections required by paragraphs (p) Other FAA AD Provisions September 6, 1995; pages 9 and 10 are
(j) and (l) of this AD at the applicable time The following provisions also apply to this identified as original, dated March 1, 1993.
specified in those paragraphs. AD: Page 1 of Appendix 1 is identified as
(2) If any cracking is found during any (1) Alternative Methods of Compliance Revision 1, dated November 25, 1994; and
HFEC inspection required by paragraph (i), (AMOCs): The Manager, International pages 2 through 6 are identified as original,
(j), or (m)(1) of this AD: Before further flight, Branch, ANM–116, Transport Airplane dated March 1, 1993.
do the applicable actions specified in Directorate, FAA, has the authority to (ii) Reserved.
paragraphs (m)(2)(i) and (m)(2)(ii) of this AD. approve AMOCs for this AD, if requested (5) For service information identified in
(i) If the cracking is 75 mm or less per each using the procedures found in 14 CFR 39.19. this AD, contact Airbus SAS, Airworthiness
rib bay: Before further flight, repair the In accordance with 14 CFR 39.19, send your Office—EAW, 1 Rond Point Maurice
cracking, in accordance with the request to your principal inspector or local Bellonte, 31707 Blagnac Cedex, France;
Accomplishment Instructions of Airbus Flight Standards District Office, as telephone +33 5 61 93 36 96; fax +33 5 61
Service Bulletin A300–57–6044, Revision 04, appropriate. If sending information directly 93 44 51; email account.airworth-
dated August 19, 2011, including Appendix to the International Branch, send it to ATTN: eas@airbus.com; Internet http://
01, Revision 04, dated August 19, 2011, Dan Rodina, Aerospace Engineer, www.airbus.com.
except as specified in paragraph (o) of this International Branch, ANM–116, Transport (6) You may view this service information
AD. Do repetitive detailed inspections of the Airplane Directorate, FAA, 1601 Lind at the FAA, Transport Airplane Directorate,
repaired area thereafter at intervals not to Avenue SW., Renton, WA 98057–3356; 1601 Lind Avenue SW., Renton, WA. For
exceed 50 flight cycles or 110 flight hours, telephone 425–227–2125; fax 425–227–1149. information on the availability of this
whichever occurs first, in accordance with Information may be emailed to: 9-ANM-116- material at the FAA, call 425–227–1221.
the Accomplishment Instructions of Airbus AMOC-REQUESTS@faa.gov. Before using (7) You may view this service information
Service Bulletin A300–57–6044, Revision 04, any approved AMOC, notify your appropriate that is incorporated by reference at the
principal inspector, or lacking a principal National Archives and Records
dated August 19, 2011, including Appendix
inspector, the manager of the local flight Administration (NARA). For information on
01, Revision 04, dated August 19, 2011.
standards district office/certificate holding the availability of this material at NARA, call
Within 250 flight cycles or 550 flight hours,
district office. The AMOC approval letter 202–741–6030, or go to: http://
whichever occurs first after doing the
must specifically reference this AD. www.archives.gov/federal-register/cfr/ibr-
temporary repair, do a permanent repair of
(2) Contacting the Manufacturer: As of the locations.html.
the repaired area, in accordance with the
effective date of this AD, for any requirement
Accomplishment Instructions of Airbus Issued in Renton, Washington, on March
in this AD to obtain corrective actions from
Service Bulletin A300–57–6044, Revision 04, 24, 2016.
a manufacturer, the action must be
dated August 19, 2011, including Appendix Michael Kaszycki,
accomplished using a method approved by
01, Revision 04, dated August 19, 2011. Acting Manager, Transport Airplane
the Manager, International Branch, ANM–
(ii) If the cracking exceeds 75 mm per any 116, Transport Airplane Directorate, FAA; or Directorate, Aircraft Certification Service.
rib bay: Before further flight, install Airbus EASA; or Airbus’s EASA DOA. If approved [FR Doc. 2016–07574 Filed 4–8–16; 8:45 am]
Modification 10089, in accordance with the by the DOA, the approval must include the
Accomplishment Instructions of Airbus BILLING CODE 4910–13–P
DOA-authorized signature.
Service Bulletin A300–57–6044, Revision 04,
dated August 19, 2011, including Appendix (q) Related Information
01, Revision 04, dated August 19, 2011. Do (1) Refer to Mandatory Continuing DEPARTMENT OF TRANSPORTATION
an LFEC inspection thereafter at the intervals Airworthiness Information (MCAI) EASA
specified in paragraph (l) of this AD. Airworthiness Directive 2013–0221, dated Federal Aviation Administration
(3) If any cracking is found during any September 19, 2013, for related information.
inspection required by this AD at fastener This MCAI may be found in the AD docket 14 CFR Part 39
hole 1A, 1, or 2: Before further flight, repair on the Internet at http://www.regulations.gov
the cracking, in accordance with the [Docket No. FAA–2016–5457; Directorate
by searching for and locating Docket No.
Accomplishment Instructions of Airbus Identifier 2016–CE–008–AD; Amendment
FAA–2015–1426.
Service Bulletin A300–57–6044, Revision 04, 39–18469; AD 2016–07–24]
(2) Service information identified in this
dated August 19, 2011, including Appendix AD that is not incorporated by reference is RIN 2120–AA64
01, Revision 04, dated August 19, 2011. available at the addresses specified in
(4) If any cracking is found during any paragraphs (r)(5) and (r)(6) of this AD. Airworthiness Directives; Textron
LFEC inspection required by paragraph (k) or Aviation, Inc. Airplanes
(l) of this AD: Before further flight, repair (r) Material Incorporated by Reference
using a method approved by the Manager, (1) The Director of the Federal Register AGENCY: Federal Aviation
International Branch, ANM–116, Transport approved the incorporation by reference Administration (FAA), DOT.
Airplane Directorate, FAA; or EASA; or (IBR) of the service information listed in this ACTION: Final rule; request for
Airbus’s EASA DOA. paragraph under 5 U.S.C. 552(a) and 1 CFR comments.
part 51.
(n) Credit for Previous Actions (2) You must use this service information SUMMARY: We are adopting a new
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This paragraph provides credit for actions as applicable to do the actions required by airworthiness directive (AD) for all
required by paragraphs (i) through (l) of this this AD, unless this AD specifies otherwise.
AD, if those actions were performed before
Textron Aviation, Inc. Models 310
(3) The following service information was
the effective date of this AD using Airbus approved for IBR on May 16, 2016 through 310R, E310H, E310J, T310P
Service Bulletin A300–57–6044, Revision 03, (i) Airbus Service Bulletin A300–57–6044, through T310R, 310J–1, 320 through
dated April 7, 1999, including Appendix 01, Revision 04, dated August 19, 2011, 320F, 320–1, 335, 340, 340A, 401
Revision 03, dated April 7, 1999, which is including Appendix 01, Revision 04, dated through 401B, 402 through 402C, 411,
not incorporated by reference in this AD. August 19, 2011. 411A, 414, 414A, and 421 through 421C
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Document Created: 2016-04-09 00:11:50
Document Modified: 2016-04-09 00:11:50
| 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 May 16, 2016. | |
| Contact | Dan Rodina, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-2125; fax 425-227-1149. | |
| FR Citation | 81 FR 21246 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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