Airworthiness Directives; Airbus Airplanes, 61990-61993 [2016-21283]

Download as PDF 61990 Federal Register / Vol. 81, No. 174 / Thursday, September 8, 2016 / Rules and Regulations 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 manager of the ACO, send it to the attention of the person identified in paragraph (l) of this AD. (2) 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. Lhorne on DSK30JT082PROD with RULES (l) Related Information For more information about this AD, contact Gideon Jose, Aerospace Engineer, Systems and Equipment Branch, ACE–119A, FAA, Atlanta Aircraft Certification Office (ACO), 1701 Columbia Avenue, College Park, Georgia 30337; phone: 404–474–5569; fax: 404–474–5606; email: Gideon.Jose@faa.gov. (m) 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 the AD specifies otherwise. (i) Gulfstream G300 Maintenance Manual Temporary Revision (TR) 32–2, dated April 29, 2016. (ii) Gulfstream G300 Maintenance Manual TR 5–3, dated April 29, 2016. (iii) Gulfstream G350 Maintenance Manual TR 32–1, dated April 22, 2016. (iv) Gulfstream G350 Maintenance Manual TR 5–2, dated April 22, 2016. (v) Gulfstream G400 Maintenance Manual TR 32–2, dated April 29, 2016. (vi) Gulfstream G400 Maintenance Manual TR 5–3, dated April 29, 2016. (vii) Gulfstream G450 Maintenance Manual TR 32–1, dated April 22, 2016. (viii) Gulfstream G450 Maintenance Manual TR 5–2, dated April 22, 2016. (ix) Gulfstream G500 Maintenance Manual TR 32–1, dated May 20, 2016. (x) Gulfstream G500 Maintenance Manual TR 5–3, dated May 20, 2016. (xi) Gulfstream G550 Maintenance Manual TR 32–1, dated May 20, 2016. (xii) Gulfstream G550 Maintenance Manual TR 5–3, dated May 20, 2016. (xiii) Gulfstream II Maintenance Manual TR 32–1, dated April 15, 2016. (xiv) Gulfstream II Maintenance Manual TR 5–3, dated April 15, 2016. (xv) Gulfstream IIB Maintenance Manual TR 32–3, dated April 15, 2016. (xvi) Gulfstream IIB Maintenance Manual TR 5–3, dated April 15, 2016. (xvii) Gulfstream III Maintenance Manual TR 32–1, dated April 15, 2016. (xviii) Gulfstream III Maintenance Manual TR 5–2, dated April 15, 2016. (xix) Gulfstream IV Maintenance Manual TR 32–2, dated April 29, 2016. (xx) Gulfstream IV Maintenance Manual TR 5–7, dated April 29, 2016. (xxi) Gulfstream V Maintenance Manual TR 32–2, dated May 20, 2016. (xxii) Gulfstream V Maintenance Manual TR 5–3, dated May 20, 2016. VerDate Sep<11>2014 15:15 Sep 07, 2016 Jkt 238001 (3) For Gulfstream service information identified in this AD, contact Gulfstream Aerospace Corporation, Technical Publications Dept., P.O. Box 2206, Savannah, GA 31402–2206; telephone 800–810–4853; fax 912–965–3520; email pubs@ gulfstream.com; Internet https:// www.gulfstream.com/product_support/ technical_pubs/pubs/index.htm. (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: https:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued in Renton, Washington, on August 24, 2016. John P. Piccola, Jr., Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016–21155 Filed 9–7–16; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2016–6671; Directorate Identifier 2015–NM–164–AD; Amendment 39–18643; AD 2016–18–12] 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 A300 B4–203 and A300 B4–2C airplanes. This AD was prompted by cracks found on pylon side panels (upper section) at rib 8. This AD requires a detailed inspection for crack indications of the pylon side panels; a high frequency eddy current (HFEC) inspection to confirm any crack indications; and repair of any cracking, or modification of the pylon side panels, and repetitive inspections and repair if necessary. We are issuing this AD to detect and correct cracking of the pylon side panels. Such cracking could result in pylon structural failure and in-flight loss of an engine. DATES: This AD is effective October 13, 2016. The Director of the Federal Register approved the incorporation by reference SUMMARY: PO 00000 Frm 00010 Fmt 4700 Sfmt 4700 of a certain publication listed in this AD as of October 13, 2016. 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 https:// www.airbus.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227– 1221. It is also available on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA–2016–6671. Examining the AD Docket You may examine the AD docket on the Internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2016– 6671; 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: 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 by adding an AD that would apply to certain Airbus Model A300 B4– 203 and A300 B4–2C airplanes. The NPRM published in the Federal Register on May 23, 2016 (81 FR 32256) (‘‘the NPRM’’). The NPRM was prompted by cracks found on pylon side panels (upper section) at rib 8. The NPRM proposed to require a detailed inspection for crack indications of the pylon side panels; an HFEC inspection to confirm any crack indications; and repair of any cracking, or modification of the pylon side panels, and repetitive inspections and repair if necessary. We are issuing this AD to detect and correct E:\FR\FM\08SER1.SGM 08SER1 Federal Register / Vol. 81, No. 174 / Thursday, September 8, 2016 / Rules and Regulations cracking of the pylon side panels. Such cracking could result in pylon structural failure and in-flight loss of an engine. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2015–0201, dated October 7, 2015 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for certain Airbus Model A300 B4–203 and A300 B4–2C airplanes. The MCAI states: Cracks were found on pylon side panels (upper section) at rib 8 on Airbus A300, A310 and A300–600 aeroplanes equipped with General Electric engines. Investigation of these findings indicated that this problem was likely to also affect aeroplanes of this type design with other engine installations. This condition, if not detected and corrected, could lead to reduced strength of the pylon primary structure, possibly resulting in pylon structural failure and inflight loss of an engine. Prompted by these findings, EASA issued AD 2008–0181 [which corresponded to FAA AD 2010–06–04, Amendment 39–16228 (75 FR 11428, March 11, 2010; corrected May 4, 2010 (75 FR 23572))] to require repetitive detailed visual inspections and, depending on aeroplane configuration and/or findings, the accomplishment of applicable corrective action(s). Since that [EASA] AD 2008–0181 was issued, a fleet survey and updated Fatigue and Damage Tolerance analyses have been performed in order to substantiate the second A300–600 Extended Service Goal (ESG2) exercise. The results of these analyses have shown that the risk for these aeroplanes is higher than initially determined and consequently, the threshold and interval were reduced to allow timely detection of these cracks and the accomplishment of applicable corrective action(s). Consequently, EASA AD 2013–0136 was published to supersede EASA AD 2008–0181 and to require the inspections to be accomplished within reduced thresholds and intervals. Afterwards, [EASA] AD 2013–0136 was mistakenly revised [EASA AD 2013– 0136R1 corresponds to FAA AD 2015–26–06, Amendment 39–18354 (81 FR 1870 January 14, 2016)] to reduce the Applicability, because it was considered at the time that aeroplanes on which Airbus mod 03599 was embodied, were not concerned by the requirements of EASA AD 2013–0136. Since EASA AD 2013–0136R1 was issued, a more thorough analysis determined that post-mod 03599 aeroplanes could be affected by this unsafe condition after all. [During] further deeper review, a list of nineteen A300 aeroplanes was identified as missing in the [EASA] AD 2013–0136R1 applicability (aeroplanes post-mod 03599). For the reasons described above this AD retains the requirements of EASA AD 2013– 0136R1 and mandates these requirements for the 19 missing A300 aeroplanes MSNs [manufacturer serial numbers]. You may examine the MCAI in the AD docket on the Internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2016– 6671. Comments We gave the public the opportunity to participate in developing this AD. We received no comments on the NPRM or on the determination of the cost to the public. Conclusion We reviewed the relevant data and determined that air safety and the 61991 public interest require adopting this AD as proposed, except for minor editorial changes. We have determined that these minor changes: • Are consistent with the intent that was proposed in the NPRM for correcting the unsafe condition; and • Do not add any additional burden upon the public than was already proposed in the NPRM. Related Service Information Under 1 CFR Part 51 Airbus has issued Service Bulletin A300–54–0075, Revision 04, dated May 26, 2015. The service information describes procedures for an inspection for crack indications of the pylons, a HFEC inspection to confirm cracking, modification of the pylon side panels, and repair if necessary. Airbus has also issued Service Bulletin A300–54–0081, dated August 11, 1993. This service information describes installation of a doubler on the left pylon 1 and right pylon 2, on pylon side panels (upper section) at Rib 8. 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 4 airplanes of U.S. registry. We estimate the following costs to comply with this AD: ESTIMATED COSTS Action Labor cost Cost per product Inspection of the pylon side panels 30 work-hours × $85 per hour = $2,550 per inspection cycle. $2,550 per inspection cycle .......... We estimate the following costs to do any necessary repairs that would be required based on the results of the inspection. We have no way of Cost on U.S. operators $10,200 per inspection cycle. determining the number of airplanes that might need this repair. ON-CONDITION COSTS Action Labor cost Parts cost Crack repair ................................... 56 work-hours × $85 per hour = $4,760 per repair. $3,910 per repair .......................... Lhorne on DSK30JT082PROD with RULES 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 VerDate Sep<11>2014 15:15 Sep 07, 2016 Jkt 238001 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 PO 00000 Frm 00011 Fmt 4700 Sfmt 4700 Cost per product $8,670 per repair. 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 E:\FR\FM\08SER1.SGM 08SER1 61992 Federal Register / Vol. 81, No. 174 / Thursday, September 8, 2016 / Rules and Regulations 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 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 adding the following new airworthiness directive (AD): ■ 2016–18–12 Airbus: Amendment 39–18643; Docket No. FAA–2016–6671; Directorate Identifier 2015–NM–164–AD. (a) Effective Date This AD is effective October 13, 2016. Lhorne on DSK30JT082PROD with RULES (b) Affected ADs None. (c) Applicability This AD applies to Airbus Model A300 B4– 203 and A300 B4–2C airplanes, certificated in any category, manufacturer serial numbers 210, 212, 218, 220, 227, 234, 235, 236, 239, 247, 255, 256, 259, 261, 274, 277, 292, 299, and 302. (d) Subject Air Transport Association (ATA) of America Code 54, Nacelles/Pylons. VerDate Sep<11>2014 16:39 Sep 07, 2016 Jkt 238001 (e) Reason This AD was prompted by cracks found on pylon side panels (upper section) at rib 8. We are issuing this AD to detect and correct cracking of the pylon side panels. Such cracking could result in pylon structural failure and in-flight loss of an engine. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Detailed Inspection of Pylons and Corrections At the applicable time specified in Airbus Service Bulletin A300–54–0075, Revision 04, dated May 26, 2015: Do a detailed inspection for crack indications of the pylons 1 and 2 side panels (upper section) at rib 8, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300– 54–0075, Revision 04, dated May 26, 2015. (h) Crack Confirmation If any crack indication is found during the inspection required by paragraph (g) of this AD: Before further flight, do a high frequency eddy current (HFEC) inspection to confirm the crack, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300–54–0075, Revision 04, dated May 26, 2015. (i) Follow-on Actions for No Crack/ Indication If the inspection required by paragraph (g) of this AD reveals no crack indication, or if the HFEC inspection specified by paragraph (h) of this AD confirms no crack: Do the actions specified in either paragraph (i)(1) or (i)(2) of this AD. (1) Repeat the inspection required by paragraph (g) of this AD at the applicable time specified in Airbus Service Bulletin A300–54–0075, Revision 04, dated May 26, 2015. (2) At the applicable time specified in Airbus Service Bulletin A300–54–0081, dated August 11, 1993: Modify the pylons, in accordance with Airbus Service Bulletin A300–54–0081, dated August 11, 1993. Thereafter, repeat the HFEC inspection specified in paragraph (h) of this AD at the applicable interval specified in Airbus Service Bulletin A300–54–0075, Revision 04, dated May 26, 2015, and repair any crack before further flight using a method approved by the Manager, International Branch, ANM– 116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA); or Airbus’s EASA Design Organization Approval (DOA). (j) Follow-on Actions for Crack Findings If any crack is confirmed during the inspection required by paragraph (h) of this AD, repair before further flight using a method approved by the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA; or EASA; or Airbus’s EASA DOA. (k) Credit for Previous Actions This paragraph provides credit for actions required by paragraphs (g), (h), (i), and (j) of this AD, if those actions were performed PO 00000 Frm 00012 Fmt 4700 Sfmt 4700 before the effective date of this AD using the service information specified in paragraphs (k)(1) through (k)(4) of this AD. (1) Airbus Service Bulletin A300–54–0075, dated August 11, 1993, which was incorporated by referenced in AD 2010–06– 04, Amendment 39–16228 (75 FR 11428, March 11, 2010); corrected May 4, 2010 (75 FR 23572). (2) Airbus Service Bulletin A300–54–0075, Revision 01, dated November 9, 2007. (3) Airbus Service Bulletin A300–54–0075, Revision 02, dated June 26, 2008. (4) Airbus Service Bulletin A300–54–0075, Revision 03, dated March 27, 2013. (l) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM–116, 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. 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 EASA; or Airbus’s EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature. (m) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2015–0201, dated October 7, 2015, for related information. This MCAI may be found in the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA– 2016–6671. (2) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraph (n)(3) of this AD. (n) 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 A300–54–0075, Revision 04, dated May 26, 2015. E:\FR\FM\08SER1.SGM 08SER1 Federal Register / Vol. 81, No. 174 / Thursday, September 8, 2016 / Rules and Regulations (ii) Airbus Service Bulletin A300–54–0081, dated August 11, 1993. (3) For service information identified in this AD, contact Airbus SAS, Airworthiness Office—EAW, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email account.airworth-eas@ airbus.com; Internet https://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: https:// www.archives.gov/federal-register/cfr/ibrlocations.html. DATES: Issued in Renton, Washington, on August 25, 2016. John P. Piccola, Jr., Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. Examining the AD Docket [FR Doc. 2016–21283 Filed 9–7–16; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2015–5814; Directorate Identifier 2014–NM–247–AD; Amendment 39–18639; AD 2016–18–09] 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, A319, and A320 series airplanes. This AD was prompted by reports of chafing damage on the fuselage skin at the bottom of certain frames, underneath the fairing structure. This AD requires repetitive detailed inspections for damage on the fuselage skin at certain frames, and applicable related investigative and corrective actions. We are issuing this AD to detect and correct damage to the fuselage skin, which could lead to crack initiation and propagation, possibly resulting in reduced structural integrity of the fuselage. Lhorne on DSK30JT082PROD with RULES SUMMARY: VerDate Sep<11>2014 15:15 Sep 07, 2016 Jkt 238001 This AD is effective October 13, 2016. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of October 13, 2016. ADDRESSES: For service information identified in this final rule, contact Airbus, Airworthiness Office—EIAS, 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 https://www.airbus.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. It is also available on the Internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2015– 5814. You may examine the AD docket on the Internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2015– 5814; 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, and A320 series airplanes. The NPRM published in the Federal Register on November 27, 2015 (80 FR 74045) (‘‘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 2014–0259, dated December 5, 2014 (referred to after this as the Mandatory Continuing PO 00000 Frm 00013 Fmt 4700 Sfmt 4700 61993 Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for certain Airbus Model A318, A319, and A320 series airplanes. The MCAI states: An operator reported finding chafing damage on the fuselage skin at the bottom of frame (FR) 34 junction between stringer (STR) 43 left hand (LH) side and right hand (RH) side on several aeroplanes, underneath the fairing structure. After investigation, a contact between the fairing nut plate and the fuselage was identified, causing damage to the fuselage. This condition, if not detected and corrected, could lead to crack initiation and propagation, possibly resulting in reduced structural integrity of the fuselage. For the reason described above, this [EASA] AD requires repetitive detailed inspections (DET) of the fuselage [for chafing] at FR 34 and provides an optional terminating action [modification of the belly fairing] to the repetitive inspections required by this [EASA] AD. Related investigative actions include a special detailed inspection of external fuselage skin panel for any cracking, and measurement of crack length and remaining thickness. Corrective actions include repair or modification of the fuselage skin panel. You may examine the MCAI in the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA–2015–5814. 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 Use Latest Service Information Airbus requested that we revise paragraph (i) of the NPRM to add Airbus Service Bulletin A320–53–1281, Revision 02, including Appendix 01, dated October 9, 2015. United Airlines also requested that we revise paragraph (i) of the NPRM to add Airbus Service Bulletin A320–53–1281, Revision 02, including Appendix 01, dated October 9, 2015, and provide credit for Airbus Service Bulletin A320– 53–1281, Revision 01, dated December 1, 2014. United Airlines explained that Airbus Service Bulletin A320–53–1281, Revision 02, including Appendix 01, dated October 9, 2015, includes numerous configuration additions. For the reasons stated by the commenter, we agree to revise this AD to include Airbus Service Bulletin A320–53–1281, Revision 02, including Appendix 01, dated October 9, 2015. Airbus Service Bulletin A320–53–1281, Revision 02, including Appendix 01, E:\FR\FM\08SER1.SGM 08SER1

Agencies

[Federal Register Volume 81, Number 174 (Thursday, September 8, 2016)]
[Rules and Regulations]
[Pages 61990-61993]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-21283]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-6671; Directorate Identifier 2015-NM-164-AD; 
Amendment 39-18643; AD 2016-18-12]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: We are adopting a new airworthiness directive (AD) for certain 
Airbus Model A300 B4-203 and A300 B4-2C airplanes. This AD was prompted 
by cracks found on pylon side panels (upper section) at rib 8. This AD 
requires a detailed inspection for crack indications of the pylon side 
panels; a high frequency eddy current (HFEC) inspection to confirm any 
crack indications; and repair of any cracking, or modification of the 
pylon side panels, and repetitive inspections and repair if necessary. 
We are issuing this AD to detect and correct cracking of the pylon side 
panels. Such cracking could result in pylon structural failure and in-
flight loss of an engine.

DATES: This AD is effective October 13, 2016.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of October 13, 
2016.

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 
https://www.airbus.com. You may view this referenced service information 
at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., 
Renton, WA. For information on the availability of this material at the 
FAA, call 425-227-1221. It is also available on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2016-
6671.

Examining the AD Docket

    You may examine the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2016-
6671; 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: 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 by adding an AD that would apply to certain Airbus Model A300 
B4-203 and A300 B4-2C airplanes. The NPRM published in the Federal 
Register on May 23, 2016 (81 FR 32256) (``the NPRM''). The NPRM was 
prompted by cracks found on pylon side panels (upper section) at rib 8. 
The NPRM proposed to require a detailed inspection for crack 
indications of the pylon side panels; an HFEC inspection to confirm any 
crack indications; and repair of any cracking, or modification of the 
pylon side panels, and repetitive inspections and repair if necessary. 
We are issuing this AD to detect and correct

[[Page 61991]]

cracking of the pylon side panels. Such cracking could result in pylon 
structural failure and in-flight loss of an engine.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2015-0201, dated October 7, 2015 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for certain Airbus Model 
A300 B4-203 and A300 B4-2C airplanes. The MCAI states:

    Cracks were found on pylon side panels (upper section) at rib 8 
on Airbus A300, A310 and A300-600 aeroplanes equipped with General 
Electric engines. Investigation of these findings indicated that 
this problem was likely to also affect aeroplanes of this type 
design with other engine installations.
    This condition, if not detected and corrected, could lead to 
reduced strength of the pylon primary structure, possibly resulting 
in pylon structural failure and in-flight loss of an engine.
    Prompted by these findings, EASA issued AD 2008-0181 [which 
corresponded to FAA AD 2010-06-04, Amendment 39-16228 (75 FR 11428, 
March 11, 2010; corrected May 4, 2010 (75 FR 23572))] to require 
repetitive detailed visual inspections and, depending on aeroplane 
configuration and/or findings, the accomplishment of applicable 
corrective action(s).
    Since that [EASA] AD 2008-0181 was issued, a fleet survey and 
updated Fatigue and Damage Tolerance analyses have been performed in 
order to substantiate the second A300-600 Extended Service Goal 
(ESG2) exercise. The results of these analyses have shown that the 
risk for these aeroplanes is higher than initially determined and 
consequently, the threshold and interval were reduced to allow 
timely detection of these cracks and the accomplishment of 
applicable corrective action(s).
    Consequently, EASA AD 2013-0136 was published to supersede EASA 
AD 2008-0181 and to require the inspections to be accomplished 
within reduced thresholds and intervals. Afterwards, [EASA] AD 2013-
0136 was mistakenly revised [EASA AD 2013-0136R1 corresponds to FAA 
AD 2015-26-06, Amendment 39-18354 (81 FR 1870 January 14, 2016)] to 
reduce the Applicability, because it was considered at the time that 
aeroplanes on which Airbus mod 03599 was embodied, were not 
concerned by the requirements of EASA AD 2013-0136.
    Since EASA AD 2013-0136R1 was issued, a more thorough analysis 
determined that post-mod 03599 aeroplanes could be affected by this 
unsafe condition after all.
    [During] further deeper review, a list of nineteen A300 
aeroplanes was identified as missing in the [EASA] AD 2013-0136R1 
applicability (aeroplanes post-mod 03599).
    For the reasons described above this AD retains the requirements 
of EASA AD 2013-0136R1 and mandates these requirements for the 19 
missing A300 aeroplanes MSNs [manufacturer serial numbers].

    You may examine the MCAI in the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2016-
6671.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We received no comments on the NPRM or on the determination of 
the cost to the public.

Conclusion

    We reviewed the relevant data and determined that air safety and 
the public interest require adopting this AD as proposed, except for 
minor editorial changes. We have determined that these minor changes:
     Are consistent with the intent that was proposed in the 
NPRM for correcting the unsafe condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM.

Related Service Information Under 1 CFR Part 51

    Airbus has issued Service Bulletin A300-54-0075, Revision 04, dated 
May 26, 2015. The service information describes procedures for an 
inspection for crack indications of the pylons, a HFEC inspection to 
confirm cracking, modification of the pylon side panels, and repair if 
necessary.
    Airbus has also issued Service Bulletin A300-54-0081, dated August 
11, 1993. This service information describes installation of a doubler 
on the left pylon 1 and right pylon 2, on pylon side panels (upper 
section) at Rib 8.
    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 4 airplanes of U.S. registry.
    We estimate the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                Action                        Labor cost            Cost per product      Cost on U.S. operators
----------------------------------------------------------------------------------------------------------------
Inspection of the pylon side panels..  30 work-hours x $85 per  $2,550 per inspection    $10,200 per inspection
                                        hour = $2,550 per        cycle.                   cycle.
                                        inspection cycle.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary repairs that 
would be required based on the results of the inspection. We have no 
way of determining the number of airplanes that might need this repair.

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                Action                        Labor cost               Parts cost            Cost per product
----------------------------------------------------------------------------------------------------------------
Crack repair.........................  56 work-hours x $85 per  $3,910 per repair......  $8,670 per repair.
                                        hour = $4,760 per
                                        repair.
----------------------------------------------------------------------------------------------------------------

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

[[Page 61992]]

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 adding the following new airworthiness 
directive (AD):

2016-18-12 Airbus: Amendment 39-18643; Docket No. FAA-2016-6671; 
Directorate Identifier 2015-NM-164-AD.

(a) Effective Date

    This AD is effective October 13, 2016.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Airbus Model A300 B4-203 and A300 B4-2C 
airplanes, certificated in any category, manufacturer serial numbers 
210, 212, 218, 220, 227, 234, 235, 236, 239, 247, 255, 256, 259, 
261, 274, 277, 292, 299, and 302.

(d) Subject

    Air Transport Association (ATA) of America Code 54, Nacelles/
Pylons.

(e) Reason

    This AD was prompted by cracks found on pylon side panels (upper 
section) at rib 8. We are issuing this AD to detect and correct 
cracking of the pylon side panels. Such cracking could result in 
pylon structural failure and in-flight loss of an engine.

(f) Compliance

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

(g) Detailed Inspection of Pylons and Corrections

    At the applicable time specified in Airbus Service Bulletin 
A300-54-0075, Revision 04, dated May 26, 2015: Do a detailed 
inspection for crack indications of the pylons 1 and 2 side panels 
(upper section) at rib 8, in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A300-54-0075, Revision 04, 
dated May 26, 2015.

(h) Crack Confirmation

    If any crack indication is found during the inspection required 
by paragraph (g) of this AD: Before further flight, do a high 
frequency eddy current (HFEC) inspection to confirm the crack, in 
accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A300-54-0075, Revision 04, dated May 26, 2015.

(i) Follow-on Actions for No Crack/Indication

    If the inspection required by paragraph (g) of this AD reveals 
no crack indication, or if the HFEC inspection specified by 
paragraph (h) of this AD confirms no crack: Do the actions specified 
in either paragraph (i)(1) or (i)(2) of this AD.
    (1) Repeat the inspection required by paragraph (g) of this AD 
at the applicable time specified in Airbus Service Bulletin A300-54-
0075, Revision 04, dated May 26, 2015.
    (2) At the applicable time specified in Airbus Service Bulletin 
A300-54-0081, dated August 11, 1993: Modify the pylons, in 
accordance with Airbus Service Bulletin A300-54-0081, dated August 
11, 1993. Thereafter, repeat the HFEC inspection specified in 
paragraph (h) of this AD at the applicable interval specified in 
Airbus Service Bulletin A300-54-0075, Revision 04, dated May 26, 
2015, and repair any crack before further flight using a method 
approved by the Manager, International Branch, ANM-116, Transport 
Airplane Directorate, FAA; or the European Aviation Safety Agency 
(EASA); or Airbus's EASA Design Organization Approval (DOA).

(j) Follow-on Actions for Crack Findings

    If any crack is confirmed during the inspection required by 
paragraph (h) of this AD, repair before further flight using a 
method approved by the Manager, International Branch, ANM-116, 
Transport Airplane Directorate, FAA; or EASA; or Airbus's EASA DOA.

(k) Credit for Previous Actions

    This paragraph provides credit for actions required by 
paragraphs (g), (h), (i), and (j) of this AD, if those actions were 
performed before the effective date of this AD using the service 
information specified in paragraphs (k)(1) through (k)(4) of this 
AD.
    (1) Airbus Service Bulletin A300-54-0075, dated August 11, 1993, 
which was incorporated by referenced in AD 2010-06-04, Amendment 39-
16228 (75 FR 11428, March 11, 2010); corrected May 4, 2010 (75 FR 
23572).
    (2) Airbus Service Bulletin A300-54-0075, Revision 01, dated 
November 9, 2007.
    (3) Airbus Service Bulletin A300-54-0075, Revision 02, dated 
June 26, 2008.
    (4) Airbus Service Bulletin A300-54-0075, Revision 03, dated 
March 27, 2013.

(l) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Branch, ANM-116, 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. 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 EASA; 
or Airbus's EASA DOA. If approved by the DOA, the approval must 
include the DOA-authorized signature.

(m) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2015-0201, dated October 7, 
2015, for related information. This MCAI may be found in the AD 
docket on the Internet at https://www.regulations.gov by searching 
for and locating Docket No. FAA-2016-6671.
    (2) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraph (n)(3) of this AD.

(n) 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 A300-54-0075, Revision 04, dated May 
26, 2015.

[[Page 61993]]

    (ii) Airbus Service Bulletin A300-54-0081, dated August 11, 
1993.
    (3) For service information identified in this AD, contact 
Airbus SAS, Airworthiness Office--EAW, 1 Rond Point Maurice 
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; 
fax +33 5 61 93 44 51; email account.airworth-eas@airbus.com; 
Internet https://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: https://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on August 25, 2016.
John P. Piccola, Jr.,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-21283 Filed 9-7-16; 8:45 am]
BILLING CODE 4910-13-P