Airworthiness Directives; Airbus Airplanes, 71596-71602 [2016-23261]

Download as PDF 71596 Federal Register / Vol. 81, No. 201 / Tuesday, October 18, 2016 / Rules and Regulations with this AD; any procedures or tests that are not identified as RC are recommended. Those procedures and tests that are not identified as RC may be deviated from using accepted methods in accordance with the operator’s maintenance or inspection program without obtaining approval of an AMOC, provided the procedures and tests identified as RC can be done and the airplane can be put back in an airworthy condition. Any substitutions or changes to procedures or tests identified as RC require approval of an AMOC. (l) Credit for Previous Actions This paragraph provides credit for actions required by paragraphs (g) and (h) of this AD, if those actions were performed before the effective date of this AD using the applicable service information specified in paragraphs (l)(1), (l)(2), (l)(3), and (l)(4) of this AD. This service information is not incorporated by reference in this AD. (1) Airbus Service Bulletin A330–28–3127, dated July 14, 2015. (2) Airbus Service Bulletin A330–28–3127, Revision 01, dated September 24, 2015. (3) Airbus Service Bulletin A340–28–4138, dated July 14, 2015. (4) Airbus Service Bulletin A340–28–5060, dated July 14, 2015. Lhorne on DSK30JT082PROD with RULES required by paragraph (k)(1) or (k)(2) of this AD, as applicable. (1) For an airplane that does not have an affected fuel pump installed: After the identification of the fuel pump part numbers required by paragraph (g) of this AD, no person may install an affected fuel pump on the airplane. (2) For an airplane that has an affected fuel pump installed: After modification of the airplane as required by paragraph (h) of this AD, no person may install an affected fuel pump on the airplane. (n) Related Information (m) 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: 9ANM-116-AMOC-REQUESTS@faa.gov. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/ certificate holding district office. The AMOC approval letter must specifically reference this AD. (2) Contacting the Manufacturer: 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 the European Aviation Safety Agency (EASA); or Airbus’s EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature. (3) Required for Compliance (RC): Except as provide by paragraph (j) of this AD, if any service information contains procedures or tests that are identified as RC, those procedures and tests must be done to comply VerDate Sep<11>2014 12:31 Oct 17, 2016 Jkt 241001 (1) Refer to Continuing Airworthiness Information (MCAI) EASA AD 2015–0194, dated September 22, 2015, for related information. You may examine the MCAI on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA– 2016–6418. (o) 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. (i) Airbus Service Bulletin A330–28–3127, Revision 02, dated April 14, 2016. (ii) Airbus Service Bulletin A340–28–4138, Revision 01, dated September 24, 2015. (iii) Airbus Service Bulletin A340–28– 5060, Revision 01, dated September 24, 2015. (3) 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: airworthiness.A330–A340@airbus.com; Internet: http://www.airbus.com. You may view this service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. (4) 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. (5) 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/ibrlocations.html. Issued in Renton, Washington, on September 26, 2016. Dionne Palermo, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016–23647 Filed 10–17–16; 8:45 am] BILLING CODE 4910–13–P PO 00000 Frm 00018 Fmt 4700 Sfmt 4700 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2015–8470; Directorate Identifier 2013–NM–199–AD; Amendment 39–18674; AD 2016–20–08] RIN 2120–AA64 Airworthiness Directives; Airbus Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: We are superseding Airworthiness Directive (AD) 95–21–09 for all Airbus Model A300 series airplanes, and 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 95–21–09 required repetitive inspections for cracking of the No. 2 flap beams, and replacement of the flap beams, if necessary; and provided optional modifications for extending certain inspection thresholds, and an optional terminating modification for certain inspections. This new AD requires reduced compliance times for inspections and also reduces the number of airplanes affected. This AD was prompted by a determination that the compliance times must be reduced. We are issuing this AD to detect and correct cracking of the No. 2 flap beams, which could result in rupture of the flap beams and reduced structural integrity of the airplane. DATES: This AD is effective November 22, 2016. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of November 22, 2016. The Director of the Federal Register approved the incorporation by reference of certain other publications listed in this AD as of November 17, 1995 (60 FR 53847, October 18, 1995). 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 account.airworth-eas@ airbus.com; Internet http:// www.airbus.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of SUMMARY: E:\FR\FM\18OCR1.SGM 18OCR1 Federal Register / Vol. 81, No. 201 / Tuesday, October 18, 2016 / Rules and Regulations 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–2015–8470. 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– 8470; 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 address for the Docket Office (telephone 800–647–5527) is 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 20590. 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 Lhorne on DSK30JT082PROD with RULES We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 95–21–09, Amendment 39–9395 (60 FR 53847, October 18, 1995) (‘‘AD 95–21–09’’). AD 95–21–09 applied to all Airbus Model A300 and A300–600 series airplanes. The NPRM published in the Federal Register on January 20, 2016 (81 FR 3045) (‘‘the NPRM’’). The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA AD 2013– 0234R2, dated October 7, 2013 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for certain Airbus Model A300 and A300–600 series airplanes. The MCAI states: Fatigue and ‘‘fail safe’’ tests developed on a test specimen confirmed that cracks may appear and propagate from the bolt holes of the base member and the side members of flap beam No. 2. The development of such cracks, if not detected, could result in a rupture of flap beams No. 2, which could adversely affect the structural integrity of the airframe. To address this potential unsafe condition, Airbus issued Service Bulletin (SB) A300– 57–0116 and SB A300–57–6005 and DGAC ´ ´ [Direction Generale de l’Aviation Civile] VerDate Sep<11>2014 12:31 Oct 17, 2016 Jkt 241001 France issued AD 1986–187–076(B), later revised, to require a repetitive inspection programme [and corrective action] for A300 and A300–600 aeroplanes. [French AD 86– 187–076(B)R3, dated March 2, 1994, corresponds to FAA AD 95–21–09, which superseded FAA AD 85–07–04, Amendment 39–5027 (50 FR 13013, April 2, 1985).] For A300 aeroplanes, and in the frame of the Extended Service Goal (ESG) exercise, it was shown that design changes (Airbus Mod. 4740/Airbus SB A300–57–0128 or Airbus Mod. 5815/Airbus SB A300–57–0141) were not sufficient to enable full ESG life without inspections. For A300–600 aeroplanes, since DGAC France AD 1986–187–076(B) was issued, a fleet survey and updated Fatigue and Damage Tolerance analyses have been performed in order to substantiate the second A300–600 ESG2 exercise. Airbus SB A300–57–6005 has been revised accordingly to decrease the inspection thresholds and intervals. For the reasons described above, this [EASA] AD retains the requirements of DGAC France AD 1986–187–076(B)R4, which is superseded, and requires those inspections to be accomplished at reduced thresholds and intervals. This [EASA] AD has been revised to correct typographical errors in some compliance times defined in Appendix 1, Tables 1 and 2. The MCAI also reduces the number of airplanes identified in the applicability by exempting certain Model A300–600 airplanes on which certain Airbus modifications have been embodied. 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– 8470. Comments We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the NPRM and the FAA’s response to each comment. Request To Remove Certain Exceptions in the Proposed Applicability United Parcel Service (UPS) requested that the applicability exceptions in paragraphs (c)(3) and (c)(4) of the proposed AD be revised to remove Airbus Modifications 11133 and 12699 as exceptions. UPS stated that the exceptions provided in paragraphs (c)(3) and (c)(4) of the proposed AD are inconsistent with the effectivity specified in the service information referenced in the NPRM. UPS pointed out that the effectivity of Airbus Service Bulletin A300–57–6005, Revision 06, dated November 14, 2013, applies to airplanes with manufacturer serial number (MSN) 775 and subsequent, with MSN 775 as the production cut-in for Airbus Modification 11133. UPS asserted that this service bulletin’s PO 00000 Frm 00019 Fmt 4700 Sfmt 4700 71597 effectivity also does not list all postmodification 11133 and 12699 airplanes. UPS stated that the determining factor for the service information effectivity is whether an airplane is approved for the extended service goal (ESG–2) operational life or not. UPS also pointed out that the effectivity of Airbus Service Bulletin A300–57–6005, Revision 06, dated November 14, 2013, does not include Model A300 F4–622 airplanes that are in a UPS configuration (Airbus Modifications 11133, 12047, 12048, 12050, but not 12699), which would mean UPS would need to request an alternative method of compliance (AMOC) or other means to show compliance for those airplanes. We acknowledge the concern UPS identified regarding the clarity of the AD applicability. Therefore, we have revised the applicability to match the related MCAI, which should address UPS’s concern. We do not intend for this AD to affect UPS’s specified A300 F4–622R configuration (Airbus Modifications 11133, 12047, 12048, 12050, but not 12699). We have revised paragraph (c)(4) of this AD accordingly. However, we do not agree to delete references to both Airbus Modifications 11133 and 12699 from the applicability of this AD since there are airplanes with these modifications in the worldwide fleet that might be imported and placed on the U.S. Register. Therefore, we have not removed references to Airbus Modifications 11133 and 12699 from paragraphs (c)(3) and (c)(4) of this AD. Request To Remove Typographical Error UPS requested that paragraph (l)(2) of the proposed AD be revised to remove a typographical error that resulted in listing Model A300 F4–622R airplanes twice. We agree that there was a typographical error, as described by UPS. We have removed the redundant reference in this AD. Additional Change to This AD We added new paragraph (m) to this AD to specify clearly the required calculation method for establishing the average flight times (AFT) for the compliance times for certain inspections required by this AD. We also redesignated subsequent paragraphs. Conclusion We reviewed the available data, including the comments received, and determined that air safety and the public interest require adopting this AD with the changes described previously E:\FR\FM\18OCR1.SGM 18OCR1 71598 Federal Register / Vol. 81, No. 201 / Tuesday, October 18, 2016 / Rules and Regulations 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. 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. Related Service Information Under 1 CFR Part 51 Airbus has issued Service Bulletins A300–57–0116, Revision 07, dated September 19, 2011, including Appendixes A and B; and A300–57– 6005, Revision 06, dated November 14, 2013. This service information describes procedures for ultrasonic inspections of the No. 2 flap beam base and side members. These documents are distinct since they apply to different airplane models. 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. Regulatory Findings Lhorne on DSK30JT082PROD with RULES Costs of Compliance We estimate that this AD affects 49 airplanes of U.S. registry. The actions required by AD 95–21–09 and retained in this AD, take about 6 work-hours per product, at an average labor rate of $85 per work-hour. Required parts cost about $0 per product. Based on these figures, the estimated cost of the actions that were required by AD 95–21–09 is $510 per product, per inspection cycle. We also estimate that it takes about 6 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 $24,990 per inspection cycle, or $510 per product, per inspection cycle. 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 VerDate Sep<11>2014 12:31 Oct 17, 2016 Jkt 241001 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 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by removing Airworthiness Directive (AD) 95–21–09, Amendment 39–9395 (60 FR 53847, October 18, 1995), and adding the following new AD: ■ 2016–20–08 Airbus: Amendment 39–18674; Docket No. FAA–2015–8470; Directorate Identifier 2013–NM–199–AD. (a) Effective Date This AD is effective November 22, 2016. (b) Affected ADs This AD replaces AD 95–21–09, Amendment 39–9395 (60 FR 53847, October 18, 1995) (‘‘AD 95–21–09’’). PO 00000 Frm 00020 Fmt 4700 Sfmt 4700 (c) Applicability This AD applies to the Airbus airplanes identified in paragraphs (c)(1) through (c)(5) of this AD, certificated in any category. (1) Airbus Model A300 B2–1A, B2–1C, B2K–3C, B2–203, B4–2C, B4–103, and B4– 203 airplanes, all manufacturer serial numbers (MSNs). (2) Airbus Model A300 B4–601, B4–603, B4–620, B4–622, B4–605R, and B4–622R airplanes, all MSNs. (3) Airbus Model A300 F4–605R, all MSNs, except those airplanes on which both Airbus Modifications 11133 and 12699 have been embodied. (4) Airbus Model A300 F4–622R airplanes, all MSNs, except those airplanes on which the modifications identified in paragraph (c)(4)(i) or (c)(4)(ii) of this AD have been embodied. (i) All Airbus Modifications 11133, 12047, 12048, and 12050 have been embodied. (ii) Both Airbus Modifications 11133 and 12699 have been embodied. (5) Airbus Model A300 C4–605R Variant F airplanes, all MSNs. (d) Subject Air Transport Association (ATA) of America Code 57, Wings. (e) Reason This AD was prompted by a determination that the compliance times must be reduced. We are issuing this AD to detect and correct cracking of the No. 2 flap beams, which could result in rupture of the flap beams and reduced structural integrity of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Retained Inspection and Corrective Actions for Model A300 Series Airplanes, With Note 3 of AD 95–21–09 Incorporated and Additional Terminating Provisions This paragraph restates the requirements of paragraph (a) of AD 95–21–09, with Note 3 of AD 95–21–09 incorporated and additional terminating provisions. For Model A300 series airplanes: Prior to the accumulation of 15,000 total landings, or within the next 120 days after May 9, 1985 (the effective date of AD 85–07–04, Amendment 39–5027 (50 FR 13013, April 2, 1985) (‘‘AD 85–07–04’’)), whichever occurs later, inspect for cracking of the base steel member and light alloy side members of the No. 2 flap beams, left hand and right hand, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300–57–116, Revision 6, dated July 16, 1993. Accomplishing the requirements of paragraph (h) or (l) of this AD terminates the requirements of this paragraph. Measurement of crack length is performed by measurement of the probe displacement (perpendicular to symmetry plane of beam) between defect indication appearance and its complete disappearance. The bolt hole indication should not be interpreted as an indication of a defect. These two indications appear very close together because the defects originate from the bolt holes. E:\FR\FM\18OCR1.SGM 18OCR1 Federal Register / Vol. 81, No. 201 / Tuesday, October 18, 2016 / Rules and Regulations (1) If no cracking is detected: Except as provided by paragraph (i) of this AD, repeat the inspection at intervals not to exceed 1,700 landings until the requirements of paragraph (h) or (l) of this AD are accomplished. (2) If any crack is detected that is less than or equal to 4 millimeters (mm): Repeat the inspection at intervals not to exceed 250 landings, until the requirements of paragraph (h) or (l) of this AD are accomplished. (3) If any crack is detected that exceeds 4 mm: Prior to further flight, replace the flap beam in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300–57–116, Revision 6, dated July 16, 1993, and prior to the accumulation of 15,000 flight cycles on the replaced flap beam, perform the ultrasonic inspection as required by paragraph (h) or (l) of this AD. Lhorne on DSK30JT082PROD with RULES (h) Retained Ultrasonic Inspection and Corrective Action for Model A300 Series Airplanes, With Additional Terminating Provisions This paragraph restates the requirements of paragraph (b) of AD 95–21–09, with additional terminating provisions. For Model A300 series airplanes: Prior to the accumulation of 15,000 total landings, or within the next 1,000 landings after November 17, 1995 (the effective date of AD 95–21–09), whichever occurs later, perform an ultrasonic inspection to detect cracking of the No. 2 flap beams, in accordance with Airbus Service Bulletin A300–57–116, Revision 6, dated July 16, 1993. Accomplishment of this inspection terminates the inspections required by paragraph (g) of this AD. Accomplishment of the requirements of paragraph (l) of this AD terminates the requirements of this paragraph. (1) If no cracking is detected: Except as provided by paragraph (i) of this AD, repeat the ultrasonic inspections thereafter at intervals not to exceed 1,700 landings. (2) If any crack is detected beyond the bolt hole, and that crack is less than or equal to 4 mm in length: Repeat the ultrasonic inspections thereafter at intervals not to exceed 250 landings. (3) If any crack is detected beyond the bolt hole and that crack is greater than 4 mm in length: Prior to further flight, replace the flap beam in accordance with Airbus Service Bulletin A300–57–116, Revision 6, dated July 16, 1993; and prior to the accumulation of 15,000 flight cycles on the replaced flap beam, perform the ultrasonic inspection as required by this paragraph. (i) Retained Modification of the No. 2 Track Beam for Model A300 Series Airplanes, With Changes to Compliance Extension This paragraph restates the provisions of paragraph (c) of AD 95–21–09, with changes to compliance extension. For Model A300 series airplanes: After accomplishing the initial inspection required by paragraph (h) of this AD, accomplishment of either paragraph (i)(1) or (i)(2) of this AD before the effective date of this AD extends the fatigue life of the No. 2 flap track beam as specified in those paragraphs, provided that no VerDate Sep<11>2014 12:31 Oct 17, 2016 Jkt 241001 cracking is detected during any inspection required by paragraph (g) or (h) of this AD. (1) Removal of any damage and the installation of larger diameter bolts on the No. 2 flap track beam (Modification No. 4740), in accordance with Airbus Service Bulletin A300–57–128, Revision 3, dated January 26, 1990, extends the interval for the first repetitive inspection required by paragraph (h) of this AD from 1,700 landings to 12,000 landings, provided that Modification No. 4740 is accomplished prior to the accumulation of 16,700 total landings on the flap beams. Following accomplishment of the first repetitive inspection, subsequent repetitive inspections shall be performed at intervals not to exceed 1,700 landings. (2) Cold working of the bolt holes and the installation of larger diameter bolts on the No. 2 flap track beam (Modification No. 5815), in accordance with Airbus Service Bulletin A300–57–141, Revision 7, dated July 16, 1993, extends the interval for the first repetitive inspection required by paragraph (h) of this AD from 1,700 landings to the interval specified in paragraph (i)(2)(i) or (i)(2)(ii) of this AD. (i) If interference fit bolts that are 15⁄32-inch in diameter are fitted, the interval for the first repetitive inspection required by paragraph (h) of this AD is extended to 22,000 landings, provided that Modification No. 5815 is accomplished prior to the accumulation of 16,700 total landings on the flap beam. Following accomplishment of the first repetitive inspection required by paragraph (h) of this AD, subsequent repetitive inspections shall be performed at intervals not to exceed 1,700 landings. (ii) If interference fit bolts that are 7⁄16- or 3⁄8-inch in diameter are fitted, the interval for the first repetitive inspection required by paragraph (h) of this AD is extended to 33,000 landings, provided that Modification No. 5815 is accomplished prior to the accumulation of 16,700 total landings on the flap beam. Following accomplishment of the first repetitive inspection required by paragraph (h) of this AD, subsequent repetitive inspections shall be performed at intervals not to exceed 1,700 landings. (j) Retained Ultrasonic Inspection and Corrective Actions for Model A300–600 Series Airplanes, With Terminating Provisions This paragraph restates the requirements of paragraph (d) of AD 95–21–09, with terminating provisions. For Model A300–600 series airplanes: Prior to the accumulation of 15,000 total landings, or within the next 1,000 landings after November 17, 1995 (the effective date of AD 95–21–09), whichever occurs later, perform an ultrasonic inspection to detect cracking of the No. 2 flap track beams, in accordance with Airbus Service Bulletin A300–57–6005, Revision 2, dated December 16, 1993. Accomplishing the actions required by paragraph (l) of this AD terminates the requirements of this paragraph. (1) If no cracking is detected, repeat the ultrasonic inspections thereafter at intervals not to exceed 1,700 landings. (2) If any crack is detected beyond the bolt hole and that crack is less than or equal to PO 00000 Frm 00021 Fmt 4700 Sfmt 4700 71599 4 mm in length: Repeat the ultrasonic inspections thereafter at intervals not to exceed 250 landings. (3) If any crack is detected beyond the bolt hole and that crack is greater than 4 mm in length: Prior to further flight, replace the flap beam in accordance with Airbus Service Bulletin A300–57–6005, Revision 2, dated December 16, 1993, and prior to the accumulation of 15,000 landings on the replaced flap beam, perform the ultrasonic inspection required by paragraph (j) of this AD. (k) Retained Optional Action With Note 5 of AD 95–21–09 Incorporated and Changes To Terminating Action This paragraph restates the provisions of paragraph (e) of AD 95–21–09, with Note 5 of AD 95–21–09 incorporated and changes to terminating action. For Model A300–600 series airplanes: Installation of oversized transition fit bolts in cold-worked holes, in accordance with Airbus Service Bulletin A300–57–6006, Revision 4, dated July 25, 1994 (Modification No. 5815), constitutes terminating action for the repetitive inspection requirements of paragraph (j) of this AD, provided that no cracking is detected during any inspection required by paragraph (j) of this AD, and provided that the installation is accomplished prior to the accumulation of 15,000 total landings and before the effective date of this AD. If any bolt requires oversizing above 7⁄16-inch diameter during accomplishment of this installation, prior to further flight, repair using a method approved by the Manager, Standardization Branch, ANM–113, FAA, Transport Airplane Directorate; or by the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA. As of the effective date of this AD, any new repair approval must be done using a method approved by the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA. If Airbus Service Bulletin A300–57–6005, Revision 2, dated December 16, 1993, was accomplished concurrently with Airbus Service Bulletin A300–57–6006, Revision 3, dated December 16, 1993 (Modification No. 5815), the ultrasonic inspection for cracking required by paragraph (j) of this AD need not be performed since the eddy current inspection detailed for Modification No. 5815 is more comprehensive. (l) New Requirement of This AD: Initial and Repetitive Ultrasonic Inspections At the applicable time specified in paragraph (l)(1) or (l)(2) of this AD and, thereafter at intervals not to exceed those defined in table 3 to paragraph (l) of this AD, as applicable, accomplish an ultrasonic inspection for cracking of the steel base member and the aluminum side members’ flap beam on the left-hand (LH) and righthand (RH) sides, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300–57–0116, Revision 07, dated September 19, 2011, including Appendixes A and B; or Airbus Service Bulletin A300–57–6005, Revision 06, dated November 14, 2013; as applicable. For the purposes of this AD, average flight time E:\FR\FM\18OCR1.SGM 18OCR1 71600 Federal Register / Vol. 81, No. 201 / Tuesday, October 18, 2016 / Rules and Regulations (AFT) must be established as specified in paragraph (m) of this AD. Doing the actions required by this paragraph terminates the requirements of paragraphs (g) through (k) of this AD. (1) For Model A300 B2–1A, B2–1C, B2K– 3C, B2–203, B4–2C, B4–103, and B4–203 airplanes (referred to as Model A300 series airplanes): Within the applicable compliance time defined in table 1 to paragraph (l) of this AD. (2) For Model A300 B4–601, B4–603, B4– 620, B4–622, B4–605R, B4–622R, F4–605R, F4–622R airplanes, and Model A300 C4– 605R Variant F airplanes (referred to as Model A300–600 series airplanes): At the later of the times specified in paragraphs (l)(2)(i) and (l)(2)(ii) of this AD. (i) Within the compliance time defined in table 2 to paragraph (l) of this AD. (ii) Within 300 flight cycles or 640 flight hours after the effective date of this AD, whichever occurs first. TABLE 1 TO PARAGRAPH (l) OF THIS AD—INSPECTION COMPLIANCE TIMES FOR MODEL A300 SERIES AIRPLANES Airplane configuration Compliance times for airplanes with an AFT of less than 1.5 Compliance times for airplanes with an AFT of more than or equal to 1.5 Model A300 B2–1A, B2–1C, B2K–3C, B2–203 airplanes on which Airbus Modifications 4740 and 5815 have not been embodied. Model A300 B4–103 airplanes on which Airbus Modifications 4740 and 5815 have not been embodied. Model A300 B4–2C, and B4–203 airplanes on which Airbus Modifications 4740 and 5815 have not been embodied. Model A300 B2–1A, B2–1C, B2K–3C, B2–203 airplanes on which Airbus Modification 4740 has been embodied. Model A300 B4–103 airplanes on which Airbus Modification 4740 has been embodied. Within 15,000 flight cycles or 16,900 flight hours since first flight of the airplane, whichever occurs first. Within 15,000 flight cycles or 20,500 flight hours since first flight of the airplane, whichever occurs first. Within 16,200 flight cycles or 22,200 flight hours since first flight of the airplane, whichever occurs first. Within 12,000 flight cycles or 13,500 flight hours since embodiment of Airbus Modification 4740, whichever occurs first. Within 12,000 flight cycles or 16,400 flight hours since embodiment of Airbus Modification 4740, whichever occurs first. Within 12,900 flight cycles or 17,700 flight hours since embodiment of Airbus Modification 4740, whichever occurs first. Within 33,000 flight cycles or 37,200 flight hours since embodiment of Airbus Modification 5815, whichever occurs first. Within 15,000 flight cycles or 16,900 flight hours since first flight of the airplane, whichever occurs first. Within 15,000 flight cycles or 20,500 flight hours since first flight of the airplane, whichever occurs first. Within 15,000 flight cycles or 34,000 flight hours since first flight of the airplane, whichever occurs first. Within 12,000 flight cycles or 13,500 flight hours since embodiment of Airbus Modification 4740, whichever occurs first. Within 12,000 flight cycles or 16,400 flight hours since embodiment of Airbus Modification 4740, whichever occurs first. Within 12,000 flight cycles or 27,200 flight hours since embodiment of Airbus Modification 4740, whichever occurs first. Within 33,000 flight cycles or 37,200 flight hours since embodiment of Airbus Modification 5815, whichever occurs first. Within 33,000 flight cycles or 45,200 flight hours since embodiment of Airbus Modification 5815, whichever occurs first. Within 35,600 flight cycles or 48,800 flight hours since embodiment of Airbus Modification 5815, whichever occurs first. Within 33,000 flight cycles or 45,200 flight hours since embodiment of Airbus Modification 5815, whichever occurs first. Within 33,000 flight cycles or 74,900 flight hours since embodiment of Airbus Modification 5815, whichever occurs first. Within 22,000 flight cycles or 24,800 flight hours since embodiment of Airbus Modification 5815, whichever occurs first. Within 22,000 flight cycles or 24,800 flight hours since embodiment of Airbus Modification 5815, whichever occurs first. Within 22,000 flight cycles or 30,100 flight hours since embodiment of Airbus Modification 5815, whichever occurs first. Within 22,000 flight cycles or 30,100 flight hours since embodiment of Airbus Modification 5815, whichever occurs first. Within 23,700 flight cycles or 32,500 flight hours since embodiment of Airbus Modification 5815, whichever occurs first. Within 22,000 flight cycles or 49,900 flight hours since embodiment of Airbus Modification 5815, whichever occurs first. Model A300 B4–2C, and B4–203 airplanes on which Airbus Modification 4740 has been embodied. Model A300 B2–1A, B2–1C, B2K–3C, B2–203 airplanes on which Airbus Modification 5815 has been embodied and no bolt larger than 7⁄16-inch diameter is fitted. Model A300 B4–103 airplanes on which Airbus Modification 5815 has been embodied and no bolt larger than 7⁄16-inch diameter is fitted. Model A300 B4–2C, and B4–203 airplanes on which Airbus Modification 5815 has been embodied and no bolt larger than 7⁄16-inch diameter is fitted. Model A300 B2–1A, B2–1C, B2K–3C, B2–203 airplanes on which Airbus Modification 5815 has been embodied and at least one bolt with a 15⁄32-inch diameter is fitted. Model A300 B4–103 airplanes on which Airbus Modification 5815 has been embodied and at least one bolt with a 15⁄32-inch diameter is fitted. Model A300 B4–2C, and B4–203, airplanes on which Airbus Modification 5815 has been embodied and at least one bolt with a 15⁄32-inch diameter is fitted. TABLE 2 TO PARAGRAPH (1) OF THIS AD—COMPLIANCE TIMES FOR MODEL A300–600 SERIES AIRPLANES Lhorne on DSK30JT082PROD with RULES Airplane configuration Compliance times for airplanes with an AFT of less than 1.5 Compliance times for airplanes with an AFT of more than or equal to 1.5 Model A300–600 series airplanes on which Airbus Modification 5815 and Airbus Modification 11133 have not been embodied. Model A300–600 series airplanes on which Airbus Modification 5815 has been embodied and no bolt larger than 7⁄16-inch diameter is fitted. Model A300–600 series airplanes on which Airbus Modification 5815 has been embodied and at least one bolt 15⁄32-inch diameter is fitted. Within 16,200 flight cycles or 24,300 flight hours since first flight of the airplane, whichever occurs first. Within 35,600 flight cycles or 53,400 flight hours since embodiment of Airbus Modification 5815, whichever occurs first. Within 15,000 flight cycles or 32,400 flight hours since first flight of the airplane, whichever occurs first. Within 33,000 flight cycles or 71,200 flight hours since embodiment of Airbus Modification 5815, whichever occurs first. Within 23,700 flight cycles or 35,600 flight hours since embodiment of Airbus Modification 5815, whichever occurs first. Within 22,000 flight cycles or 47,500 flight hours since embodiment of Airbus Modification 5815, whichever occurs first. VerDate Sep<11>2014 12:31 Oct 17, 2016 Jkt 241001 PO 00000 Frm 00022 Fmt 4700 Sfmt 4700 E:\FR\FM\18OCR1.SGM 18OCR1 Federal Register / Vol. 81, No. 201 / Tuesday, October 18, 2016 / Rules and Regulations 71601 TABLE 2 TO PARAGRAPH (1) OF THIS AD—COMPLIANCE TIMES FOR MODEL A300–600 SERIES AIRPLANES—Continued Airplane configuration Compliance times for airplanes with an AFT of less than 1.5 Compliance times for airplanes with an AFT of more than or equal to 1.5 Model A300–600 series airplanes on which Airbus Modification 11133 has been embodied. Within 35,600 flight cycles or 53,400 flight hours since first flight, whichever occurs first. Within 33,000 flight cycles or 71,200 flight hours since first flight, whichever occurs first. TABLE 3 TO PARAGRAPH (1) OF THIS AD—REPETITIVE INSPECTION INTERVALS Repetitive interval (not to exceed) for airplanes with an AFT of less than 1.5 Airplane models A300 B2–1A, B2–1C, B2K–3C, B2–203 ............ A300 B4–103 airplanes ...................................... A300 B4–2C, and B4–203 ................................. A300–600 series airplanes ................................. (m) Calculating the AFT For the purpose of this AD, the AFT must be established as specified in paragraphs (m)(1), (m)(2), and (m)(3) of this AD. (1) For the initial inspection, the average flight time is the total accumulated flight hours, counted from take-off to touch-down, divided by the total accumulated flight cycles at the effective date of this AD. (2) For the first repeated inspection interval, the average flight time is the total accumulated flight hours divided by the total accumulated flight cycles at the time of the inspection threshold. (3) For all inspection intervals onward, the average flight time is the flight hours divided by the flight cycles accumulated between the last two inspections. Lhorne on DSK30JT082PROD with RULES (n) New Requirement of This AD: Corrective Action If any crack is found during any inspection required by paragraph (l) of this AD: Before further flight, replace the flap beam 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). Replacement of the flap beam does not constitute terminating action for the inspections required by paragraph (l) of this AD. (o) Credit for Previous Actions (1) This paragraph provides credit for inspections required by paragraph (g) of this AD, if those inspections were performed before November 17, 1995 (the effective date of AD 95–21–09) using Airbus Service Bulletin A300–57–116, Revision 1, dated August 27, 1983; Revision 2, dated April 24, 1984; Revision 3, dated July 20, 1984; Revision 4, dated August 13, 1986; or Revision 5, dated July 10, 1989; as applicable. (2) This paragraph provides credit for actions required by paragraph (l) of this AD, if those actions were performed before the effective date of this AD using the applicable VerDate Sep<11>2014 12:31 Oct 17, 2016 Jkt 241001 1,500 flight whichever 1,500 flight whichever 1,600 flight whichever 1,600 flight whichever cycles or occurs first. cycles or occurs first. cycles or occurs first. cycles or occurs first. 1,600 flight hours, 2,000 flight hours, 2,200 flight hours, 2,400 flight hours, service information identified in paragraphs (o)(2)(i) through (o)(2)(x) of this AD. (i) Airbus Service Bulletin A300–57–6005, Revision 2, dated December 16, 1993, which was previously incorporated by reference on November 17, 1995 (60 FR 53847, October 18, 1995). (ii) Airbus Service Bulletin A300–57–6005, Revision 03, dated November 25, 1997. (iii) Airbus Service Bulletin A300–57– 6005, Revision 04, dated October 25, 1999. (iv) Airbus Service Bulletin A300–57– 6005, Revision 05, dated April 25, 2013. (v) Airbus Service Bulletin A300–57–116, Revision 1, dated August 27, 1983. (vi) Airbus Service Bulletin A300–57–116, Revision 2, dated April 24, 1984. (vii) Airbus Service Bulletin A300–57–116, Revision 3, dated July 20, 1984. (viii) Airbus Service Bulletin A300–57– 116, Revision 4, dated August 13, 1986. (ix) Airbus Service Bulletin A300–57–116, Revision 5, dated July 10, 1989. (x) Airbus Service Bulletin A300–57–116, Revision 6, dated July 16, 1993, which was previously incorporated by reference on November 17, 1995 (60 FR 53847, October 18, 1995). (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: 9-ANM-116AMOC-REQUESTS@faa.gov. PO 00000 Frm 00023 Fmt 4700 Sfmt 4700 Repetitive interval (not to exceed) for airplanes with an AFT equal to or more than 1.5 1,500 flight whichever 1,500 flight whichever 1,500 flight whichever 1,500 flight whichever cycles or occurs first. cycles or occurs first. cycles or occurs first. cycles or occurs first. 1,600 flight hours, 2,000 flight hours, 3,400 flight hours, 3,200 flight hours, (i) 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. (ii) AMOCs approved previously for AD 95–21–09, are approved as AMOCs for the corresponding provisions of paragraphs (g) through (j) of 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. (3) Required for Compliance (RC): Except as required by paragraph (n) of this AD: If any service information contains procedures or tests that are identified as RC, those procedures and tests must be done to comply with this AD; any procedures or tests that are not identified as RC are recommended. Those procedures and tests that are not identified as RC may be deviated from using accepted methods in accordance with the operator’s maintenance or inspection program without obtaining approval of an AMOC, provided the procedures and tests identified as RC can be done and the airplane can be put back in an airworthy condition. Any substitutions or changes to procedures or tests identified as RC require approval of an AMOC. (q) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA AD 2013–0234R2, dated October 7, 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–2015–8470. (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. E:\FR\FM\18OCR1.SGM 18OCR1 71602 Federal Register / Vol. 81, No. 201 / Tuesday, October 18, 2016 / Rules and Regulations Lhorne on DSK30JT082PROD with RULES (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 November 22, 2016. (i) Airbus Service Bulletin A300–57–0116, Revision 07, dated September 19, 2011, including Appendixes A and B. Only the first page of Appendixes A and B of this document are identified as appendixes. (ii) Airbus Service Bulletin A300–57–6005, Revision 06, dated November 14, 2013. (4) The following service information was approved for IBR on November 17, 1995 (60 FR 53847, October 18, 1995). (i) Airbus Service Bulletin A300–57–116, Revision 6, dated July 16, 1993, which contains the following effective pages: Pages 1 through 11 of this document are identified as Revision 6, dated July 16, 1993. (ii) Airbus Service Bulletin A300–57–128, Revision 3, dated January 26, 1990, which contains the following effective pages: Page 1 is identified as Revision 3, dated January 26, 1990; pages 2 through 5 are identified as Revision 1, dated February 7, 1986; and pages 6 through 14 are identified as the original issue, dated August 27, 1983. (iii) Airbus Service Bulletin A300–57–141, Revision 7, dated July 16, 1993, which contains the following effective pages: Pages 1 through 24 of this document are identified as Revision 7, dated July 16, 1993. (iv) Airbus Service Bulletin A300–57– 6005, Revision 2, dated December 16, 1993, which contains the following effective pages: Pages 1 through 4 are identified as Revision 2, dated December 16, 1993; pages 5 through 7 and 9 are identified as Revision 1, dated February 26, 1993; and page 8 is identified as the original issue, dated August 13, 1986. (v) Airbus Service Bulletin A300–57–6006, Revision 4, dated July 25, 1994, which contains the following effective pages: Pages 1, 2, 5, and 7 are identified as Revision 4, dated July 25, 1994; and pages 3, 4, 6, and 8 through 20 are identified as Revision 3, dated December 16, 1993. (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 account.airworth-eas@ airbus.com; 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/ibrlocations.html. VerDate Sep<11>2014 12:31 Oct 17, 2016 Jkt 241001 Issued in Renton, Washington, on September 19, 2016. Dionne Palermo, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016–23261 Filed 10–17–16; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2015–8132; Directorate Identifier 2015–NM–127–AD; Amendment 39–18663; AD 2016–19–14] RIN 2120–AA64 Airworthiness Directives; Airbus Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for certain Airbus Model A318 and A319 series airplanes; Model A320–211, –212, –214, –231, –232, and –233 airplanes; and Model A321 series airplanes. This AD was prompted by a report of cracks found during maintenance inspections on certain lugs of the 10VU rack side fittings in the cockpit. This AD requires repetitive inspections for cracking of the lugs on the 10VU rack side fittings, and repair of any cracking. We are issuing this AD to prevent reading difficulties of flight-critical information displayed to the flightcrew during a critical phase of flight, such as an approach or takeoff, which could result in loss of airplane control at an altitude insufficient for recovery. SUMMARY: www.regulations.gov by searching for and locating Docket No. FAA–2015– 8132. 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– 8132; 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 Office (telephone 800–647– 5527) is 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 20590. FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–1405; fax 425–227–1149. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to certain Airbus Model A318, A319, A320, and A321 series airplanes. The NPRM published in the Federal Register on December 31, 2015 (80 FR 81792) (‘‘the NPRM’’). The NPRM was prompted by a report of cracks found during maintenance inspections on certain lugs of the 10VU rack side fittings in the cockpit. The NPRM proposed to require repetitive inspections for cracking of the lugs on the 10VU rack side fittings, and repair DATES: This AD is effective November of any cracking. We are issuing this AD 22, 2016. to prevent reading difficulties of flightThe Director of the Federal Register critical information displayed to the approved the incorporation by reference flightcrew during a critical phase of of a certain publication listed in this AD flight, such as an approach or takeoff, as of November 22, 2016. which could result in loss of airplane ADDRESSES: For service information control at an altitude insufficient for identified in this final rule, contact recovery. Airbus, Airworthiness Office—EIAS, 1 The European Aviation Safety Agency Rond Point Maurice Bellonte, 31707 (EASA), which is the Technical Agent Blagnac Cedex, France; telephone +33 5 for the Member States of the European 61 93 36 96; fax +33 5 61 93 44 51; email Union, has issued EASA Airworthiness account.airworth-eas@airbus.com; Directive 2015–0170, dated August 18, Internet http://www.airbus.com. You 2015 (referred to after this as the may view this referenced service Mandatory Continuing Airworthiness information at the FAA, Transport Information, or ‘‘the MCAI’’), to correct Airplane Directorate, 1601 Lind Avenue an unsafe condition for certain Airbus SW., Renton, WA. For information on Model A318 and A319 series airplanes; the availability of this material at the Model A320–211, –212, –214, –231, FAA, call 425–227–1221. It is also –232, and –233 airplanes; and Model available on the Internet at http:// A321 series airplanes. The MCAI states: PO 00000 Frm 00024 Fmt 4700 Sfmt 4700 E:\FR\FM\18OCR1.SGM 18OCR1

Agencies

[Federal Register Volume 81, Number 201 (Tuesday, October 18, 2016)]
[Rules and Regulations]
[Pages 71596-71602]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-23261]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-8470; Directorate Identifier 2013-NM-199-AD; 
Amendment 39-18674; AD 2016-20-08]
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) 95-21-09 for 
all Airbus Model A300 series airplanes, and 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 95-
21-09 required repetitive inspections for cracking of the No. 2 flap 
beams, and replacement of the flap beams, if necessary; and provided 
optional modifications for extending certain inspection thresholds, and 
an optional terminating modification for certain inspections. This new 
AD requires reduced compliance times for inspections and also reduces 
the number of airplanes affected. This AD was prompted by a 
determination that the compliance times must be reduced. We are issuing 
this AD to detect and correct cracking of the No. 2 flap beams, which 
could result in rupture of the flap beams and reduced structural 
integrity of the airplane.

DATES: This AD is effective November 22, 2016.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of November 22, 
2016.
    The Director of the Federal Register approved the incorporation by 
reference of certain other publications listed in this AD as of 
November 17, 1995 (60 FR 53847, October 18, 1995).

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 account.airworth-eas@airbus.com; Internet 
http://www.airbus.com. You may view this referenced service information 
at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., 
Renton, WA. For information on the availability of

[[Page 71597]]

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-2015-8470.

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-
8470; 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 address for the Docket Office (telephone 800-
647-5527) is 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 20590.

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 95-21-09, Amendment 39-9395 (60 FR 53847, 
October 18, 1995) (``AD 95-21-09''). AD 95-21-09 applied to all Airbus 
Model A300 and A300-600 series airplanes. The NPRM published in the 
Federal Register on January 20, 2016 (81 FR 3045) (``the NPRM'').
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA AD 
2013-0234R2, dated October 7, 2013 (referred to after this as the 
Mandatory Continuing Airworthiness Information, or ``the MCAI''), to 
correct an unsafe condition for certain Airbus Model A300 and A300-600 
series airplanes. The MCAI states:

    Fatigue and ``fail safe'' tests developed on a test specimen 
confirmed that cracks may appear and propagate from the bolt holes 
of the base member and the side members of flap beam No. 2.
    The development of such cracks, if not detected, could result in 
a rupture of flap beams No. 2, which could adversely affect the 
structural integrity of the airframe.
    To address this potential unsafe condition, Airbus issued 
Service Bulletin (SB) A300-57-0116 and SB A300-57-6005 and DGAC 
[Direction G[eacute]n[eacute]rale de l'Aviation Civile] France 
issued AD 1986-187-076(B), later revised, to require a repetitive 
inspection programme [and corrective action] for A300 and A300-600 
aeroplanes. [French AD 86-187-076(B)R3, dated March 2, 1994, 
corresponds to FAA AD 95-21-09, which superseded FAA AD 85-07-04, 
Amendment 39-5027 (50 FR 13013, April 2, 1985).]
    For A300 aeroplanes, and in the frame of the Extended Service 
Goal (ESG) exercise, it was shown that design changes (Airbus Mod. 
4740/Airbus SB A300-57-0128 or Airbus Mod. 5815/Airbus SB A300-57-
0141) were not sufficient to enable full ESG life without 
inspections.
    For A300-600 aeroplanes, since DGAC France AD 1986-187-076(B) 
was issued, a fleet survey and updated Fatigue and Damage Tolerance 
analyses have been performed in order to substantiate the second 
A300-600 ESG2 exercise. Airbus SB A300-57-6005 has been revised 
accordingly to decrease the inspection thresholds and intervals.
    For the reasons described above, this [EASA] AD retains the 
requirements of DGAC France AD 1986-187-076(B)R4, which is 
superseded, and requires those inspections to be accomplished at 
reduced thresholds and intervals.
    This [EASA] AD has been revised to correct typographical errors 
in some compliance times defined in Appendix 1, Tables 1 and 2.

    The MCAI also reduces the number of airplanes identified in the 
applicability by exempting certain Model A300-600 airplanes on which 
certain Airbus modifications have been embodied. 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-2015-8470.

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following presents the comments received on the NPRM and 
the FAA's response to each comment.

Request To Remove Certain Exceptions in the Proposed Applicability

    United Parcel Service (UPS) requested that the applicability 
exceptions in paragraphs (c)(3) and (c)(4) of the proposed AD be 
revised to remove Airbus Modifications 11133 and 12699 as exceptions. 
UPS stated that the exceptions provided in paragraphs (c)(3) and (c)(4) 
of the proposed AD are inconsistent with the effectivity specified in 
the service information referenced in the NPRM. UPS pointed out that 
the effectivity of Airbus Service Bulletin A300-57-6005, Revision 06, 
dated November 14, 2013, applies to airplanes with manufacturer serial 
number (MSN) 775 and subsequent, with MSN 775 as the production cut-in 
for Airbus Modification 11133. UPS asserted that this service 
bulletin's effectivity also does not list all post-modification 11133 
and 12699 airplanes. UPS stated that the determining factor for the 
service information effectivity is whether an airplane is approved for 
the extended service goal (ESG-2) operational life or not. UPS also 
pointed out that the effectivity of Airbus Service Bulletin A300-57-
6005, Revision 06, dated November 14, 2013, does not include Model A300 
F4-622 airplanes that are in a UPS configuration (Airbus Modifications 
11133, 12047, 12048, 12050, but not 12699), which would mean UPS would 
need to request an alternative method of compliance (AMOC) or other 
means to show compliance for those airplanes.
    We acknowledge the concern UPS identified regarding the clarity of 
the AD applicability. Therefore, we have revised the applicability to 
match the related MCAI, which should address UPS's concern. We do not 
intend for this AD to affect UPS's specified A300 F4-622R configuration 
(Airbus Modifications 11133, 12047, 12048, 12050, but not 12699). We 
have revised paragraph (c)(4) of this AD accordingly. However, we do 
not agree to delete references to both Airbus Modifications 11133 and 
12699 from the applicability of this AD since there are airplanes with 
these modifications in the worldwide fleet that might be imported and 
placed on the U.S. Register. Therefore, we have not removed references 
to Airbus Modifications 11133 and 12699 from paragraphs (c)(3) and 
(c)(4) of this AD.

Request To Remove Typographical Error

    UPS requested that paragraph (l)(2) of the proposed AD be revised 
to remove a typographical error that resulted in listing Model A300 F4-
622R airplanes twice.
    We agree that there was a typographical error, as described by UPS. 
We have removed the redundant reference in this AD.

Additional Change to This AD

    We added new paragraph (m) to this AD to specify clearly the 
required calculation method for establishing the average flight times 
(AFT) for the compliance times for certain inspections required by this 
AD. We also redesignated subsequent paragraphs.

Conclusion

    We reviewed the available data, including the comments received, 
and determined that air safety and the public interest require adopting 
this AD with the changes described previously

[[Page 71598]]

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 Bulletins A300-57-0116, Revision 07, 
dated September 19, 2011, including Appendixes A and B; and A300-57-
6005, Revision 06, dated November 14, 2013. This service information 
describes procedures for ultrasonic inspections of the No. 2 flap beam 
base and side members. These documents are distinct since they apply to 
different airplane models. 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 49 airplanes of U.S. registry.
    The actions required by AD 95-21-09 and retained in this AD, take 
about 6 work-hours per product, at an average labor rate of $85 per 
work-hour. Required parts cost about $0 per product. Based on these 
figures, the estimated cost of the actions that were required by AD 95-
21-09 is $510 per product, per inspection cycle.
    We also estimate that it takes about 6 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 $24,990 per inspection cycle, or $510 
per product, per inspection cycle.
    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) 
95-21-09, Amendment 39-9395 (60 FR 53847, October 18, 1995), and adding 
the following new AD:

2016-20-08 Airbus: Amendment 39-18674; Docket No. FAA-2015-8470; 
Directorate Identifier 2013-NM-199-AD.

(a) Effective Date

    This AD is effective November 22, 2016.

(b) Affected ADs

    This AD replaces AD 95-21-09, Amendment 39-9395 (60 FR 53847, 
October 18, 1995) (``AD 95-21-09'').

(c) Applicability

    This AD applies to the Airbus airplanes identified in paragraphs 
(c)(1) through (c)(5) of this AD, certificated in any category.
    (1) Airbus Model A300 B2-1A, B2-1C, B2K-3C, B2-203, B4-2C, B4-
103, and B4-203 airplanes, all manufacturer serial numbers (MSNs).
    (2) Airbus Model A300 B4-601, B4-603, B4-620, B4-622, B4-605R, 
and B4-622R airplanes, all MSNs.
    (3) Airbus Model A300 F4-605R, all MSNs, except those airplanes 
on which both Airbus Modifications 11133 and 12699 have been 
embodied.
    (4) Airbus Model A300 F4-622R airplanes, all MSNs, except those 
airplanes on which the modifications identified in paragraph 
(c)(4)(i) or (c)(4)(ii) of this AD have been embodied.
    (i) All Airbus Modifications 11133, 12047, 12048, and 12050 have 
been embodied.
    (ii) Both Airbus Modifications 11133 and 12699 have been 
embodied.
    (5) Airbus Model A300 C4-605R Variant F airplanes, all MSNs.

(d) Subject

    Air Transport Association (ATA) of America Code 57, Wings.

(e) Reason

    This AD was prompted by a determination that the compliance 
times must be reduced. We are issuing this AD to detect and correct 
cracking of the No. 2 flap beams, which could result in rupture of 
the flap beams and reduced structural integrity of the airplane.

(f) Compliance

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

(g) Retained Inspection and Corrective Actions for Model A300 Series 
Airplanes, With Note 3 of AD 95-21-09 Incorporated and Additional 
Terminating Provisions

    This paragraph restates the requirements of paragraph (a) of AD 
95-21-09, with Note 3 of AD 95-21-09 incorporated and additional 
terminating provisions. For Model A300 series airplanes: Prior to 
the accumulation of 15,000 total landings, or within the next 120 
days after May 9, 1985 (the effective date of AD 85-07-04, Amendment 
39-5027 (50 FR 13013, April 2, 1985) (``AD 85-07-04'')), whichever 
occurs later, inspect for cracking of the base steel member and 
light alloy side members of the No. 2 flap beams, left hand and 
right hand, in accordance with the Accomplishment Instructions of 
Airbus Service Bulletin A300-57-116, Revision 6, dated July 16, 
1993. Accomplishing the requirements of paragraph (h) or (l) of this 
AD terminates the requirements of this paragraph. Measurement of 
crack length is performed by measurement of the probe displacement 
(perpendicular to symmetry plane of beam) between defect indication 
appearance and its complete disappearance. The bolt hole indication 
should not be interpreted as an indication of a defect. These two 
indications appear very close together because the defects originate 
from the bolt holes.

[[Page 71599]]

    (1) If no cracking is detected: Except as provided by paragraph 
(i) of this AD, repeat the inspection at intervals not to exceed 
1,700 landings until the requirements of paragraph (h) or (l) of 
this AD are accomplished.
    (2) If any crack is detected that is less than or equal to 4 
millimeters (mm): Repeat the inspection at intervals not to exceed 
250 landings, until the requirements of paragraph (h) or (l) of this 
AD are accomplished.
    (3) If any crack is detected that exceeds 4 mm: Prior to further 
flight, replace the flap beam in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A300-57-116, Revision 6, 
dated July 16, 1993, and prior to the accumulation of 15,000 flight 
cycles on the replaced flap beam, perform the ultrasonic inspection 
as required by paragraph (h) or (l) of this AD.

(h) Retained Ultrasonic Inspection and Corrective Action for Model A300 
Series Airplanes, With Additional Terminating Provisions

    This paragraph restates the requirements of paragraph (b) of AD 
95-21-09, with additional terminating provisions. For Model A300 
series airplanes: Prior to the accumulation of 15,000 total 
landings, or within the next 1,000 landings after November 17, 1995 
(the effective date of AD 95-21-09), whichever occurs later, perform 
an ultrasonic inspection to detect cracking of the No. 2 flap beams, 
in accordance with Airbus Service Bulletin A300-57-116, Revision 6, 
dated July 16, 1993. Accomplishment of this inspection terminates 
the inspections required by paragraph (g) of this AD. Accomplishment 
of the requirements of paragraph (l) of this AD terminates the 
requirements of this paragraph.
    (1) If no cracking is detected: Except as provided by paragraph 
(i) of this AD, repeat the ultrasonic inspections thereafter at 
intervals not to exceed 1,700 landings.
    (2) If any crack is detected beyond the bolt hole, and that 
crack is less than or equal to 4 mm in length: Repeat the ultrasonic 
inspections thereafter at intervals not to exceed 250 landings.
    (3) If any crack is detected beyond the bolt hole and that crack 
is greater than 4 mm in length: Prior to further flight, replace the 
flap beam in accordance with Airbus Service Bulletin A300-57-116, 
Revision 6, dated July 16, 1993; and prior to the accumulation of 
15,000 flight cycles on the replaced flap beam, perform the 
ultrasonic inspection as required by this paragraph.

(i) Retained Modification of the No. 2 Track Beam for Model A300 Series 
Airplanes, With Changes to Compliance Extension

    This paragraph restates the provisions of paragraph (c) of AD 
95-21-09, with changes to compliance extension. For Model A300 
series airplanes: After accomplishing the initial inspection 
required by paragraph (h) of this AD, accomplishment of either 
paragraph (i)(1) or (i)(2) of this AD before the effective date of 
this AD extends the fatigue life of the No. 2 flap track beam as 
specified in those paragraphs, provided that no cracking is detected 
during any inspection required by paragraph (g) or (h) of this AD.
    (1) Removal of any damage and the installation of larger 
diameter bolts on the No. 2 flap track beam (Modification No. 4740), 
in accordance with Airbus Service Bulletin A300-57-128, Revision 3, 
dated January 26, 1990, extends the interval for the first 
repetitive inspection required by paragraph (h) of this AD from 
1,700 landings to 12,000 landings, provided that Modification No. 
4740 is accomplished prior to the accumulation of 16,700 total 
landings on the flap beams. Following accomplishment of the first 
repetitive inspection, subsequent repetitive inspections shall be 
performed at intervals not to exceed 1,700 landings.
    (2) Cold working of the bolt holes and the installation of 
larger diameter bolts on the No. 2 flap track beam (Modification No. 
5815), in accordance with Airbus Service Bulletin A300-57-141, 
Revision 7, dated July 16, 1993, extends the interval for the first 
repetitive inspection required by paragraph (h) of this AD from 
1,700 landings to the interval specified in paragraph (i)(2)(i) or 
(i)(2)(ii) of this AD.
    (i) If interference fit bolts that are \15/32\-inch in diameter 
are fitted, the interval for the first repetitive inspection 
required by paragraph (h) of this AD is extended to 22,000 landings, 
provided that Modification No. 5815 is accomplished prior to the 
accumulation of 16,700 total landings on the flap beam. Following 
accomplishment of the first repetitive inspection required by 
paragraph (h) of this AD, subsequent repetitive inspections shall be 
performed at intervals not to exceed 1,700 landings.
    (ii) If interference fit bolts that are \7/16\- or \3/8\-inch in 
diameter are fitted, the interval for the first repetitive 
inspection required by paragraph (h) of this AD is extended to 
33,000 landings, provided that Modification No. 5815 is accomplished 
prior to the accumulation of 16,700 total landings on the flap beam. 
Following accomplishment of the first repetitive inspection required 
by paragraph (h) of this AD, subsequent repetitive inspections shall 
be performed at intervals not to exceed 1,700 landings.

(j) Retained Ultrasonic Inspection and Corrective Actions for Model 
A300-600 Series Airplanes, With Terminating Provisions

    This paragraph restates the requirements of paragraph (d) of AD 
95-21-09, with terminating provisions. For Model A300-600 series 
airplanes: Prior to the accumulation of 15,000 total landings, or 
within the next 1,000 landings after November 17, 1995 (the 
effective date of AD 95-21-09), whichever occurs later, perform an 
ultrasonic inspection to detect cracking of the No. 2 flap track 
beams, in accordance with Airbus Service Bulletin A300-57-6005, 
Revision 2, dated December 16, 1993. Accomplishing the actions 
required by paragraph (l) of this AD terminates the requirements of 
this paragraph.
    (1) If no cracking is detected, repeat the ultrasonic 
inspections thereafter at intervals not to exceed 1,700 landings.
    (2) If any crack is detected beyond the bolt hole and that crack 
is less than or equal to 4 mm in length: Repeat the ultrasonic 
inspections thereafter at intervals not to exceed 250 landings.
    (3) If any crack is detected beyond the bolt hole and that crack 
is greater than 4 mm in length: Prior to further flight, replace the 
flap beam in accordance with Airbus Service Bulletin A300-57-6005, 
Revision 2, dated December 16, 1993, and prior to the accumulation 
of 15,000 landings on the replaced flap beam, perform the ultrasonic 
inspection required by paragraph (j) of this AD.

(k) Retained Optional Action With Note 5 of AD 95-21-09 Incorporated 
and Changes To Terminating Action

    This paragraph restates the provisions of paragraph (e) of AD 
95-21-09, with Note 5 of AD 95-21-09 incorporated and changes to 
terminating action. For Model A300-600 series airplanes: 
Installation of oversized transition fit bolts in cold-worked holes, 
in accordance with Airbus Service Bulletin A300-57-6006, Revision 4, 
dated July 25, 1994 (Modification No. 5815), constitutes terminating 
action for the repetitive inspection requirements of paragraph (j) 
of this AD, provided that no cracking is detected during any 
inspection required by paragraph (j) of this AD, and provided that 
the installation is accomplished prior to the accumulation of 15,000 
total landings and before the effective date of this AD. If any bolt 
requires oversizing above \7/16\-inch diameter during accomplishment 
of this installation, prior to further flight, repair using a method 
approved by the Manager, Standardization Branch, ANM-113, FAA, 
Transport Airplane Directorate; or by the Manager, International 
Branch, ANM-116, Transport Airplane Directorate, FAA. As of the 
effective date of this AD, any new repair approval must be done 
using a method approved by the Manager, International Branch, ANM-
116, Transport Airplane Directorate, FAA. If Airbus Service Bulletin 
A300-57-6005, Revision 2, dated December 16, 1993, was accomplished 
concurrently with Airbus Service Bulletin A300-57-6006, Revision 3, 
dated December 16, 1993 (Modification No. 5815), the ultrasonic 
inspection for cracking required by paragraph (j) of this AD need 
not be performed since the eddy current inspection detailed for 
Modification No. 5815 is more comprehensive.

(l) New Requirement of This AD: Initial and Repetitive Ultrasonic 
Inspections

    At the applicable time specified in paragraph (l)(1) or (l)(2) 
of this AD and, thereafter at intervals not to exceed those defined 
in table 3 to paragraph (l) of this AD, as applicable, accomplish an 
ultrasonic inspection for cracking of the steel base member and the 
aluminum side members' flap beam on the left-hand (LH) and right-
hand (RH) sides, in accordance with the Accomplishment Instructions 
of Airbus Service Bulletin A300-57-0116, Revision 07, dated 
September 19, 2011, including Appendixes A and B; or Airbus Service 
Bulletin A300-57-6005, Revision 06, dated November 14, 2013; as 
applicable. For the purposes of this AD, average flight time

[[Page 71600]]

(AFT) must be established as specified in paragraph (m) of this AD. 
Doing the actions required by this paragraph terminates the 
requirements of paragraphs (g) through (k) of this AD.
    (1) For Model A300 B2-1A, B2-1C, B2K-3C, B2-203, B4-2C, B4-103, 
and B4-203 airplanes (referred to as Model A300 series airplanes): 
Within the applicable compliance time defined in table 1 to 
paragraph (l) of this AD.
    (2) For Model A300 B4-601, B4-603, B4-620, B4-622, B4-605R, B4-
622R, F4-605R, F4-622R airplanes, and Model A300 C4-605R Variant F 
airplanes (referred to as Model A300-600 series airplanes): At the 
later of the times specified in paragraphs (l)(2)(i) and (l)(2)(ii) 
of this AD.
    (i) Within the compliance time defined in table 2 to paragraph 
(l) of this AD.
    (ii) Within 300 flight cycles or 640 flight hours after the 
effective date of this AD, whichever occurs first.

  Table 1 to Paragraph (l) of This AD--Inspection Compliance Times for
                       Model A300 Series Airplanes
------------------------------------------------------------------------
                                                    Compliance times for
                              Compliance times for    airplanes with an
   Airplane configuration       airplanes with an    AFT of more than or
                              AFT of less than 1.5      equal to 1.5
------------------------------------------------------------------------
Model A300 B2-1A, B2-1C, B2K- Within 15,000 flight  Within 15,000 flight
 3C, B2-203 airplanes on       cycles or 16,900      cycles or 16,900
 which Airbus Modifications    flight hours since    flight hours since
 4740 and 5815 have not been   first flight of the   first flight of the
 embodied.                     airplane, whichever   airplane, whichever
                               occurs first.         occurs first.
Model A300 B4-103 airplanes   Within 15,000 flight  Within 15,000 flight
 on which Airbus               cycles or 20,500      cycles or 20,500
 Modifications 4740 and 5815   flight hours since    flight hours since
 have not been embodied.       first flight of the   first flight of the
                               airplane, whichever   airplane, whichever
                               occurs first.         occurs first.
Model A300 B4-2C, and B4-203  Within 16,200 flight  Within 15,000 flight
 airplanes on which Airbus     cycles or 22,200      cycles or 34,000
 Modifications 4740 and 5815   flight hours since    flight hours since
 have not been embodied.       first flight of the   first flight of the
                               airplane, whichever   airplane, whichever
                               occurs first.         occurs first.
Model A300 B2-1A, B2-1C, B2K- Within 12,000 flight  Within 12,000 flight
 3C, B2-203 airplanes on       cycles or 13,500      cycles or 13,500
 which Airbus Modification     flight hours since    flight hours since
 4740 has been embodied.       embodiment of         embodiment of
                               Airbus Modification   Airbus Modification
                               4740, whichever       4740, whichever
                               occurs first.         occurs first.
Model A300 B4-103 airplanes   Within 12,000 flight  Within 12,000 flight
 on which Airbus               cycles or 16,400      cycles or 16,400
 Modification 4740 has been    flight hours since    flight hours since
 embodied.                     embodiment of         embodiment of
                               Airbus Modification   Airbus Modification
                               4740, whichever       4740, whichever
                               occurs first.         occurs first.
Model A300 B4-2C, and B4-203  Within 12,900 flight  Within 12,000 flight
 airplanes on which Airbus     cycles or 17,700      cycles or 27,200
 Modification 4740 has been    flight hours since    flight hours since
 embodied.                     embodiment of         embodiment of
                               Airbus Modification   Airbus Modification
                               4740, whichever       4740, whichever
                               occurs first.         occurs first.
Model A300 B2-1A, B2-1C, B2K- Within 33,000 flight  Within 33,000 flight
 3C, B2-203 airplanes on       cycles or 37,200      cycles or 37,200
 which Airbus Modification     flight hours since    flight hours since
 5815 has been embodied and    embodiment of         embodiment of
 no bolt larger than \7/16\-   Airbus Modification   Airbus Modification
 inch diameter is fitted.      5815, whichever       5815, whichever
                               occurs first.         occurs first.
Model A300 B4-103 airplanes   Within 33,000 flight  Within 33,000 flight
 on which Airbus               cycles or 45,200      cycles or 45,200
 Modification 5815 has been    flight hours since    flight hours since
 embodied and no bolt larger   embodiment of         embodiment of
 than \7/16\-inch diameter     Airbus Modification   Airbus Modification
 is fitted.                    5815, whichever       5815, whichever
                               occurs first.         occurs first.
Model A300 B4-2C, and B4-203  Within 35,600 flight  Within 33,000 flight
 airplanes on which Airbus     cycles or 48,800      cycles or 74,900
 Modification 5815 has been    flight hours since    flight hours since
 embodied and no bolt larger   embodiment of         embodiment of
 than \7/16\-inch diameter     Airbus Modification   Airbus Modification
 is fitted.                    5815, whichever       5815, whichever
                               occurs first.         occurs first.
Model A300 B2-1A, B2-1C, B2K- Within 22,000 flight  Within 22,000 flight
 3C, B2-203 airplanes on       cycles or 24,800      cycles or 24,800
 which Airbus Modification     flight hours since    flight hours since
 5815 has been embodied and    embodiment of         embodiment of
 at least one bolt with a      Airbus Modification   Airbus Modification
 \15/32\-inch diameter is      5815, whichever       5815, whichever
 fitted.                       occurs first.         occurs first.
Model A300 B4-103 airplanes   Within 22,000 flight  Within 22,000 flight
 on which Airbus               cycles or 30,100      cycles or 30,100
 Modification 5815 has been    flight hours since    flight hours since
 embodied and at least one     embodiment of         embodiment of
 bolt with a \15/32\-inch      Airbus Modification   Airbus Modification
 diameter is fitted.           5815, whichever       5815, whichever
                               occurs first.         occurs first.
Model A300 B4-2C, and B4-     Within 23,700 flight  Within 22,000 flight
 203, airplanes on which       cycles or 32,500      cycles or 49,900
 Airbus Modification 5815      flight hours since    flight hours since
 has been embodied and at      embodiment of         embodiment of
 least one bolt with a \15/    Airbus Modification   Airbus Modification
 32\-inch diameter is fitted.  5815, whichever       5815, whichever
                               occurs first.         occurs first.
------------------------------------------------------------------------


Table 2 to Paragraph (1) of This AD--Compliance Times for Model A300-600
                            Series Airplanes
------------------------------------------------------------------------
                                                    Compliance times for
                              Compliance times for    airplanes with an
   Airplane configuration       airplanes with an    AFT of more than or
                              AFT of less than 1.5      equal to 1.5
------------------------------------------------------------------------
Model A300-600 series         Within 16,200 flight  Within 15,000 flight
 airplanes on which Airbus     cycles or 24,300      cycles or 32,400
 Modification 5815 and         flight hours since    flight hours since
 Airbus Modification 11133     first flight of the   first flight of the
 have not been embodied.       airplane, whichever   airplane, whichever
                               occurs first.         occurs first.
Model A300-600 series         Within 35,600 flight  Within 33,000 flight
 airplanes on which Airbus     cycles or 53,400      cycles or 71,200
 Modification 5815 has been    flight hours since    flight hours since
 embodied and no bolt larger   embodiment of         embodiment of
 than \7/16\-inch diameter     Airbus Modification   Airbus Modification
 is fitted.                    5815, whichever       5815, whichever
                               occurs first.         occurs first.
Model A300-600 series         Within 23,700 flight  Within 22,000 flight
 airplanes on which Airbus     cycles or 35,600      cycles or 47,500
 Modification 5815 has been    flight hours since    flight hours since
 embodied and at least one     embodiment of         embodiment of
 bolt \15/32\-inch diameter    Airbus Modification   Airbus Modification
 is fitted.                    5815, whichever       5815, whichever
                               occurs first.         occurs first.

[[Page 71601]]

 
Model A300-600 series         Within 35,600 flight  Within 33,000 flight
 airplanes on which Airbus     cycles or 53,400      cycles or 71,200
 Modification 11133 has been   flight hours since    flight hours since
 embodied.                     first flight,         first flight,
                               whichever occurs      whichever occurs
                               first.                first.
------------------------------------------------------------------------


  Table 3 to Paragraph (1) of This AD--Repetitive Inspection Intervals
------------------------------------------------------------------------
                                                     Repetitive interval
                               Repetitive interval   (not to exceed) for
       Airplane models         (not to exceed) for    airplanes with an
                                airplanes with an   AFT equal to or more
                              AFT of less than 1.5        than 1.5
------------------------------------------------------------------------
A300 B2-1A, B2-1C, B2K-3C,    1,500 flight cycles   1,500 flight cycles
 B2-203.                       or 1,600 flight       or 1,600 flight
                               hours, whichever      hours, whichever
                               occurs first.         occurs first.
A300 B4-103 airplanes.......  1,500 flight cycles   1,500 flight cycles
                               or 2,000 flight       or 2,000 flight
                               hours, whichever      hours, whichever
                               occurs first.         occurs first.
A300 B4-2C, and B4-203......  1,600 flight cycles   1,500 flight cycles
                               or 2,200 flight       or 3,400 flight
                               hours, whichever      hours, whichever
                               occurs first.         occurs first.
A300-600 series airplanes...  1,600 flight cycles   1,500 flight cycles
                               or 2,400 flight       or 3,200 flight
                               hours, whichever      hours, whichever
                               occurs first.         occurs first.
------------------------------------------------------------------------

(m) Calculating the AFT

    For the purpose of this AD, the AFT must be established as 
specified in paragraphs (m)(1), (m)(2), and (m)(3) of this AD.
    (1) For the initial inspection, the average flight time is the 
total accumulated flight hours, counted from take-off to touch-down, 
divided by the total accumulated flight cycles at the effective date 
of this AD.
    (2) For the first repeated inspection interval, the average 
flight time is the total accumulated flight hours divided by the 
total accumulated flight cycles at the time of the inspection 
threshold.
    (3) For all inspection intervals onward, the average flight time 
is the flight hours divided by the flight cycles accumulated between 
the last two inspections.

(n) New Requirement of This AD: Corrective Action

    If any crack is found during any inspection required by 
paragraph (l) of this AD: Before further flight, replace the flap 
beam 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). Replacement of the flap beam does not constitute 
terminating action for the inspections required by paragraph (l) of 
this AD.

(o) Credit for Previous Actions

    (1) This paragraph provides credit for inspections required by 
paragraph (g) of this AD, if those inspections were performed before 
November 17, 1995 (the effective date of AD 95-21-09) using Airbus 
Service Bulletin A300-57-116, Revision 1, dated August 27, 1983; 
Revision 2, dated April 24, 1984; Revision 3, dated July 20, 1984; 
Revision 4, dated August 13, 1986; or Revision 5, dated July 10, 
1989; as applicable.
    (2) This paragraph provides credit for actions required by 
paragraph (l) of this AD, if those actions were performed before the 
effective date of this AD using the applicable service information 
identified in paragraphs (o)(2)(i) through (o)(2)(x) of this AD.
    (i) Airbus Service Bulletin A300-57-6005, Revision 2, dated 
December 16, 1993, which was previously incorporated by reference on 
November 17, 1995 (60 FR 53847, October 18, 1995).
    (ii) Airbus Service Bulletin A300-57-6005, Revision 03, dated 
November 25, 1997.
    (iii) Airbus Service Bulletin A300-57-6005, Revision 04, dated 
October 25, 1999.
    (iv) Airbus Service Bulletin A300-57-6005, Revision 05, dated 
April 25, 2013.
    (v) Airbus Service Bulletin A300-57-116, Revision 1, dated 
August 27, 1983.
    (vi) Airbus Service Bulletin A300-57-116, Revision 2, dated 
April 24, 1984.
    (vii) Airbus Service Bulletin A300-57-116, Revision 3, dated 
July 20, 1984.
    (viii) Airbus Service Bulletin A300-57-116, Revision 4, dated 
August 13, 1986.
    (ix) Airbus Service Bulletin A300-57-116, Revision 5, dated July 
10, 1989.
    (x) Airbus Service Bulletin A300-57-116, Revision 6, dated July 
16, 1993, which was previously incorporated by reference on November 
17, 1995 (60 FR 53847, October 18, 1995).

(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: 9-ANM-116-AMOC-REQUESTS@faa.gov.
    (i) 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.
    (ii) AMOCs approved previously for AD 95-21-09, are approved as 
AMOCs for the corresponding provisions of paragraphs (g) through (j) 
of 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.
    (3) Required for Compliance (RC): Except as required by 
paragraph (n) of this AD: If any service information contains 
procedures or tests that are identified as RC, those procedures and 
tests must be done to comply with this AD; any procedures or tests 
that are not identified as RC are recommended. Those procedures and 
tests that are not identified as RC may be deviated from using 
accepted methods in accordance with the operator's maintenance or 
inspection program without obtaining approval of an AMOC, provided 
the procedures and tests identified as RC can be done and the 
airplane can be put back in an airworthy condition. Any 
substitutions or changes to procedures or tests identified as RC 
require approval of an AMOC.

(q) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA AD 2013-0234R2, dated October 7, 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-2015-8470.
    (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.

[[Page 71602]]

(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 
November 22, 2016.
    (i) Airbus Service Bulletin A300-57-0116, Revision 07, dated 
September 19, 2011, including Appendixes A and B. Only the first 
page of Appendixes A and B of this document are identified as 
appendixes.
    (ii) Airbus Service Bulletin A300-57-6005, Revision 06, dated 
November 14, 2013.
    (4) The following service information was approved for IBR on 
November 17, 1995 (60 FR 53847, October 18, 1995).
    (i) Airbus Service Bulletin A300-57-116, Revision 6, dated July 
16, 1993, which contains the following effective pages: Pages 1 
through 11 of this document are identified as Revision 6, dated July 
16, 1993.
    (ii) Airbus Service Bulletin A300-57-128, Revision 3, dated 
January 26, 1990, which contains the following effective pages: Page 
1 is identified as Revision 3, dated January 26, 1990; pages 2 
through 5 are identified as Revision 1, dated February 7, 1986; and 
pages 6 through 14 are identified as the original issue, dated 
August 27, 1983.
    (iii) Airbus Service Bulletin A300-57-141, Revision 7, dated 
July 16, 1993, which contains the following effective pages: Pages 1 
through 24 of this document are identified as Revision 7, dated July 
16, 1993.
    (iv) Airbus Service Bulletin A300-57-6005, Revision 2, dated 
December 16, 1993, which contains the following effective pages: 
Pages 1 through 4 are identified as Revision 2, dated December 16, 
1993; pages 5 through 7 and 9 are identified as Revision 1, dated 
February 26, 1993; and page 8 is identified as the original issue, 
dated August 13, 1986.
    (v) Airbus Service Bulletin A300-57-6006, Revision 4, dated July 
25, 1994, which contains the following effective pages: Pages 1, 2, 
5, and 7 are identified as Revision 4, dated July 25, 1994; and 
pages 3, 4, 6, and 8 through 20 are identified as Revision 3, dated 
December 16, 1993.
    (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 account.airworth-eas@airbus.com; 
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 September 19, 2016.
Dionne Palermo,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-23261 Filed 10-17-16; 8:45 am]
BILLING CODE 4910-13-P