Airworthiness Directives; Airbus Airplanes, 11134-11137 [2017-03021]

Download as PDF 11134 Federal Register / Vol. 82, No. 33 / Tuesday, February 21, 2017 / Rules and Regulations 2017–02–12 The Boeing Company: Amendment 39–18791; Docket No. FAA–2016–6426; Directorate Identifier 2016–NM–023–AD. Compliance): Before further flight, repair using a method approved in accordance with the procedures specified in paragraph (j) of this AD. (a) Effective Date This AD is effective March 28, 2017. (i) Parts Installation Limitation As of the effective date of this AD: A horizontal stabilizer may be installed on any airplane, provided all applicable actions required by the introductory text of paragraph (g) and paragraphs (g)(1) and (g)(2) of this AD are done within the compliance times specified in the introductory text of paragraph (g) of this AD, and in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737–55A1092, dated August 7, 2015, except as required by paragraph (h) of this AD. (b) Affected ADs None. (c) Applicability (1) This AD applies to all The Boeing Company Model 737–300, –400, and –500 series airplanes, certificated in any category. (2) Installation of Supplemental Type Certificate (STC) ST01219SE (https:// rgl.faa.gov/Regulatory_and_Guidance_ Library/rgstc.nsf/0/ ebd1cec7b301293e86257cb30045557a/$FILE/ ST01219SE.pdf) does not affect the ability to accomplish the actions required by this AD. Therefore, for airplanes on which STC ST01219SE is installed, a ‘‘change in product’’ alternative method of compliance (AMOC) approval request is not necessary to comply with the requirements of 14 CFR 39.17. (d) Subject Air Transport Association (ATA) of America Code 55, Stabilizers. (e) Unsafe Condition This AD was prompted by reports of intergranular cracks on the front spar chord lugs of the outboard horizontal stabilizer. We are issuing this AD to detect and correct cracking of the front spar chord lugs of the horizontal stabilizer. Such cracking could cause stabilizer instability, adversely affect controllability of the airplane, and adversely affect the structural integrity of the airplane. rmajette on DSK2TPTVN1PROD with RULES (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Repetitive Inspections and Repairs Within 27 months after the effective date of this AD: Do the actions required by paragraphs (g)(1) and (g)(2) of this AD, and do all applicable repairs, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737–55A1092, dated August 7, 2015, except as required by paragraph (h) of this AD. Do all applicable repairs before further flight. Repeat the inspections specified in paragraphs (g)(1) and (g)(2) of this AD thereafter at the applicable intervals specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 737–55A1092, dated August 7, 2015. (1) Do a detailed inspection for corrosion and an ultrasonic inspection for cracking of the front spar chord lugs of the left and right horizontal stabilizers. (2) Do a detailed inspection for corrosion of the lug bores of the front spar chord of the left and right horizontal stabilizers. (h) Service Information Exception Where Boeing Alert Service Bulletin 737– 55A1092, dated August 7, 2015, specifies to contact Boeing for appropriate action, and specifies that action as ‘‘RC’’ (Required for VerDate Sep<11>2014 14:42 Feb 17, 2017 Jkt 241001 (j) Alternative Methods of Compliance (AMOCs) (1) The Manager, Los Angeles Aircraft Certification Office (ACO), 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 manager of the ACO, send it to the attention of the person identified in paragraph (k) of this AD. Information may be emailed to: 9-ANM-LAACO-ACO-AMOCRequests@faa.gov. (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. (3) An AMOC that provides an acceptable level of safety may be used for any repair, modification, or alteration required by this AD if it is approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) that has been authorized by the Manager, Los Angeles ACO, to make those findings. To be approved, the repair method, modification deviation, or alteration deviation must meet the certification basis of the airplane, and the approval must specifically refer to this AD. (4) Except as required by paragraph (h) of this AD: For service information that contains steps that are labeled as RC, the provisions of paragraphs (j)(4)(i) and (j)(4)(ii) of this AD apply. (i) The steps labeled as RC, including substeps under an RC step and any figures identified in an RC step, must be done to comply with the AD. If a step or substep is labeled ‘‘RC Exempt,’’ then the RC requirement is removed from that step or substep. An AMOC is required for any deviations to RC steps, including substeps and identified figures. (ii) Steps not labeled 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 RC steps, including substeps and identified figures, can still be done as specified, and the airplane can be put back in an airworthy condition. (k) Related Information For more information about this AD, contact Payman Soltani, Aerospace Engineer, PO 00000 Frm 00004 Fmt 4700 Sfmt 4700 Airframe Branch, ANM–120L, FAA, Los Angeles ACO, 3960 Paramount Boulevard, Lakewood, CA 90712–4137; phone: 562–627– 5313; fax: 562–627–5210; email: Payman.Soltani@faa.gov. (l) 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) Boeing Alert Service Bulletin 737– 55A1092, dated August 7, 2015. (ii) Reserved. (3) For Boeing service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H–65, Seattle, WA 98124–2207; telephone: 206–544–5000, extension 1; fax: 206–766– 5680; Internet: https:// www.myboeingfleet.com. (4) You may view this service information at 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 January 17, 2017. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2017–01825 Filed 2–17–17; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2016–9066; Directorate Identifier 2014–NM–113–AD; Amendment 39–18800; AD 2017–04–05] 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) 2011–10– 17 for all Airbus Model A300 and A310 series airplanes, and Model A300 B4– 600, B4–600R, and F4–600R series airplanes, and Model C4–605R Variant F SUMMARY: E:\FR\FM\21FER1.SGM 21FER1 Federal Register / Vol. 82, No. 33 / Tuesday, February 21, 2017 / Rules and Regulations airplanes (collectively called A300–600 series airplanes). AD 2011–10–17 required revising the maintenance program by incorporating certain airworthiness limitation items (ALIs). This AD requires revising the maintenance or inspection program, as applicable, to incorporate new or revised structural inspection requirements. This AD also removes Model A310 and A300–600 series airplanes from the applicability. This AD was prompted by a revision of certain ALI documents, which specify more restrictive instructions and/or airworthiness limitations. We are issuing this AD to address the unsafe condition on these products. 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: FOR FURTHER INFORMATION CONTACT: Examining the AD Docket Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 2011–10–17, Amendment 39–16698 (76 FR 27875, May 13, 2011) (‘‘AD 2011–10–17’’). AD 2011–10–17 applied to all Airbus Model A300 and A310 series airplanes, and Model A300 B4–600, B4–600R, and F4– 600R series airplanes, and Model A300 C4–605R Variant F airplanes (collectively called Model A300–600 series airplanes). The NPRM published in the Federal Register on September 12, 2016 (81 FR 62679). The NPRM was prompted by a revision of certain ALI documents, which specify more restrictive instructions and/or airworthiness limitations. The NPRM proposed to require revising the maintenance or inspection program, as applicable, to incorporate new or revised structural inspection requirements. The NPRM also proposed to remove Model A310 and A300–600 series airplanes from the applicability. We are issuing this AD to detect and correct fatigue cracking, damage, and corrosion in certain structure; such fatigue cracking, damage, and corrosion could result in reduced structural integrity of the airplane. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued Airworthiness Directive 2015–0115, dated June 23, 2015 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’) to correct an unsafe condition. The MCAI states: You may examine the AD docket on the Internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2016– 9066; 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. The airworthiness limitations applicable to the Damage Tolerant Airworthiness Limitation Items (DT ALIs) are currently listed in the Airbus Airworthiness Limitations Sections [ALS] Part 2. Airbus recently revised the A300 ALS Part 2 and this Revision 02 was approved by EASA. Airbus A300 ALS Part 2 Revision 02 introduces more restrictive maintenance requirements and airworthiness limitations, which have been identified as mandatory actions for continued airworthiness. EASA issued AD 2014–0124 to require compliance with the maintenance requirements and associated airworthiness limitations defined in Airbus A300 ALS Part 2 Revision 01. For the reasons described above, this [EASA] AD retains the requirements of EASA AD 2014–0124 for A300 aeroplanes and This AD is effective March 28, 2017. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of March 28, 2017. The Director of the Federal Register approved the incorporation by reference of a certain other publication listed in this AD as of June 17, 2011 (76 FR 27875, May 13, 2011). DATES: 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–2016–9066. rmajette on DSK2TPTVN1PROD with RULES ADDRESSES: VerDate Sep<11>2014 14:42 Feb 17, 2017 Jkt 241001 PO 00000 Frm 00005 Fmt 4700 Sfmt 4700 11135 requires implementation of new or more restrictive maintenance instructions and/or airworthiness limitations as specified in Airbus A300 ALS Part 2 Revision 02. The requirements for A310 and A300–600 aeroplanes remain unchanged and are covered by EASA AD 2014–0124R1 [FAA AD 2013–13–13, Amendment 39–17501 (79 FR 48957, August 19, 2014), contains the corresponding requirements for the Model A300–600 and A310 series airplanes]. The unsafe condition is fatigue cracking, damage, or corrosion in certain structure (principal structural elements), which could result in reduced structural integrity of the airplane. 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– 9066. Comments We gave the public the opportunity to participate in developing this AD. The following presents the comment received on the NPRM and the FAA’s response to the comment. Request To Revise MCAI Reference Airbus requested that we reference the correct MCAI in paragraph (k) of the proposed AD, which is EASA Airworthiness Directive 2015–0115, dated June 23, 2015. We agree with the commenter’s request. We have confirmed that EASA Airworthiness Directive 2015–0115, dated June 23, 2015, is the MCAI that should be referenced in this AD. We have revised this AD accordingly. Conclusion We reviewed the available data, including the comment received, and determined that air safety and the public interest require adopting this AD with the change described previously and minor editorial changes. We have determined that these changes: • Are consistent with the intent that was proposed in the NPRM for correcting the unsafe condition; and • Do not add any additional burden upon the public than was already proposed in the NPRM. Related Service Information Under 1 CFR Part 51 Airbus has issued Airbus A300 Airworthiness Limitations Section, Part 2—Damage-Tolerant Airworthiness Limitation Items (DT ALIs), Revision 02, dated October 3, 2014. This service information describes airworthiness limitations applicable to the DT ALIs. This service information is reasonably available because the interested parties have access to it through their normal E:\FR\FM\21FER1.SGM 21FER1 11136 Federal Register / Vol. 82, No. 33 / Tuesday, February 21, 2017 / Rules and Regulations course of business or by the means identified in the ADDRESSES section. under the criteria of the Regulatory Flexibility Act. Costs of Compliance List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. We estimate that this AD affects 11 airplanes of U.S. registry. The actions required by AD 2011–10– 17 and retained in this AD take about 1 work-hour per product, at an average labor rate of $85 per work-hour. Based on these figures, the estimated cost of the actions that were required by AD 2011–10–17 is $85 per product. We also estimate that it would take about 1 work-hour 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 $935, or $85 per product. 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. rmajette on DSK2TPTVN1PROD with RULES 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 14:42 Feb 17, 2017 Jkt 241001 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 Authority for This Rulemaking VerDate Sep<11>2014 Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: [Amended] 2. The FAA amends § 39.13 by removing Airworthiness Directive (AD) 2011–10–17, Amendment 39–16698 (76 FR 27875, May 13, 2011), and adding the following new AD: ■ 2017–04–05 Airbus: Amendment 39–18800; Docket No. FAA–2016–9066; Directorate Identifier 2014–NM–113–AD. (a) Effective Date This AD is effective March 28, 2017. (b) Affected ADs This AD replaces AD 2011–10–17, Amendment 39–16698 (76 FR 27875, May 13, 2011) (‘‘AD 2011–10–17’’). (c) Applicability This AD applies to all Airbus Model A300 B2–1A, B2–1C, B4–2C, B2K–3C, B4–103, B2– 203, and B4–203 airplanes, certificated in any category. (d) Subject Air Transport Association (ATA) of America Codes 52, Doors; 53, Fuselage; 54, Nacelles/pylons; 55, Stabilizers; and 57, Wings. (e) Reason This AD was prompted by a revision of certain airworthiness limitations item (ALI) documents, which specify more restrictive instructions and/or airworthiness limitations. We are issuing this AD to detect and correct fatigue cracking, damage, and corrosion in certain structure; such fatigue cracking, damage, and corrosion could result in reduced structural integrity of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Retained Revision of the Maintenance Program, With Changes This paragraph restates the requirements of paragraph (s) of AD 2011–10–17, with changes. Within 3 months after June 17, 2011 (the effective date of AD 2011–10–17): Revise the maintenance program to incorporate the PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 structural inspections and inspection intervals defined in the Airbus A300 ALI Document AI/SE–M2/95A.1308/07, Issue 4, dated June 2008. Thereafter, except as required by paragraph (h) of this AD and except as provided by paragraph (j)(1) of this AD, no alternative structural inspections or inspection intervals may be approved. The initial ALI tasks must be done at the times specified in Airbus A300 ALI Document AI/ SE–M2/95A.1308/07, Issue 4, dated June 2008. (h) New Requirement of This AD: Maintenance or Inspection Program Revision Within 3 months the effective date of this AD: Revise the maintenance program or inspection program, as applicable, to incorporate the structural inspections and inspection intervals defined in Airbus A300 Airworthiness Limitations Section (ALS), Part 2—Damage-Tolerant Airworthiness Limitation Items, Revision 02, dated October 3, 2014. The initial compliance times for the ALI tasks identified in Airbus A300 ALS, Part 2—Damage-Tolerant Airworthiness Limitation Items, Revision 02, dated October 3, 2014, are at the applicable times specified in Airbus A300 ALS, Part 2—DamageTolerant Airworthiness Limitation Items, Revision 02, dated October 3, 2014, or within 3 months after the effective date of this AD, whichever occurs later. Accomplishing the applicable initial ALI tasks constitutes terminating action for the requirements of paragraphs (g) of this AD for that airplane only. (i) No Alternative Actions or Intervals After the maintenance or inspection program has been revised as required by paragraph (h) of this AD, no alternative actions (e.g., inspections) or intervals may be used unless the actions or intervals are approved as an alternative method of compliance (AMOC) in accordance with the procedures specified in paragraph (j)(1) of this AD. (j) 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. (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. The AMOC E:\FR\FM\21FER1.SGM 21FER1 Federal Register / Vol. 82, No. 33 / Tuesday, February 21, 2017 / Rules and Regulations approval letter must specifically reference this AD. (ii) AMOCs approved previously for AD 2011–10–17 are approved as AMOCs for the corresponding provisions 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 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. (k) Related Information Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2015–0115, dated June 23, 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– 2016–9066. rmajette on DSK2TPTVN1PROD with RULES (l) 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 March 28, 2017. (i) Airbus A300 Airworthiness Limitations Section, Part 2—Damage-Tolerant Airworthiness Limitation Items, Revision 02, dated October 3, 2014. (ii) Reserved. (4) The following service information was approved for IBR on June 17, 2011 (76 FR 27875, May 13, 2011). (i) Airbus A300 Airworthiness Limitations Inspections Document AI/SE–M2/95A.1308/ 07, Issue 4, dated June 2008. (ii) Reserved. (5) For service information identified in this AD, contact Airbus SAS, Airworthiness Office– EAW, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email account.airworth-eas@airbus.com; Internet https://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: https:// www.archives.gov/federal-register/cfr/ibrlocations.html. VerDate Sep<11>2014 14:42 Feb 17, 2017 Jkt 241001 Issued in Renton, Washington, on January 24, 2017. Dionne Palermo, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2017–03021 Filed 2–17–17; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2016–9111; Directorate Identifier 2016–NM–132–AD; Amendment 39–18802; AD 2017–04–07] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 757 airplanes. This AD was prompted by reports of single and multiple uncommanded spoiler panel extensions during flight when there was a hydraulic system failure. This AD requires replacing certain spoiler power control units (PCUs) with new or changed PCUs. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective March 28, 2017. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of March 28, 2017. ADDRESSES: For service information identified in this final rule, contact Boeing Commercial Airplanes, Attention: Contractual & Data Services (C&DS), 2600 Westminster Blvd., MC 110–SK57, Seal Beach, CA 90740–5600; telephone 562–797–1717; Internet https://www.myboeingfleet.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– 9111. SUMMARY: Examining the AD Docket You may examine the AD docket on the Internet at https:// PO 00000 Frm 00007 Fmt 4700 Sfmt 4700 11137 www.regulations.gov by searching for and locating Docket No. FAA–2016– 9111; 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 (phone: 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: Myra Kuck, Aerospace Engineer, Cabin Safety/Mechanical & Environmental Systems Branch, ANM–150L, FAA, Los Angeles Aircraft Certification Office (ACO), 3960 Paramount Boulevard, Lakewood, CA 90712–4137; phone: 562–627–5316; fax: 562–627–5210; email: myra.j.kuck@faa.gov. 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 The Boeing Company Model 757 airplanes. The NPRM published in the Federal Register on September 22, 2016 (81 FR 65307) (‘‘the NPRM’’). The NPRM was prompted by reports of single and multiple uncommanded spoiler panel extensions during flight. The condition known as ‘‘spoiler panel float’’ occurred when there was a hydraulic system pressure loss. When the flaps were extended beyond 20 degrees the spoiler panel float became severe enough to adversely impact airplane control. The NPRM proposed to require replacing certain spoiler PCUs with new or changed PCUs. We are issuing this AD to prevent an uncommanded extension of multiple spoiler panels on one wing, in the event of a hydraulic system failure, which could result in the loss of control of the airplane. 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. Support for the NPRM United Airlines expressed support for the NPRM. Request To Revise Applicability MOOG Commercial Aircraft Group (MOOG) requested that we revise the applicability to include Boeing Model E:\FR\FM\21FER1.SGM 21FER1

Agencies

[Federal Register Volume 82, Number 33 (Tuesday, February 21, 2017)]
[Rules and Regulations]
[Pages 11134-11137]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-03021]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-9066; Directorate Identifier 2014-NM-113-AD; 
Amendment 39-18800; AD 2017-04-05]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

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

ACTION: Final rule.

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

SUMMARY: We are superseding Airworthiness Directive (AD) 2011-10-17 for 
all Airbus Model A300 and A310 series airplanes, and Model A300 B4-600, 
B4-600R, and F4-600R series airplanes, and Model C4-605R Variant F

[[Page 11135]]

airplanes (collectively called A300-600 series airplanes). AD 2011-10-
17 required revising the maintenance program by incorporating certain 
airworthiness limitation items (ALIs). This AD requires revising the 
maintenance or inspection program, as applicable, to incorporate new or 
revised structural inspection requirements. This AD also removes Model 
A310 and A300-600 series airplanes from the applicability. This AD was 
prompted by a revision of certain ALI documents, which specify more 
restrictive instructions and/or airworthiness limitations. We are 
issuing this AD to address the unsafe condition on these products.

DATES: This AD is effective March 28, 2017.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of March 28, 
2017.
    The Director of the Federal Register approved the incorporation by 
reference of a certain other publication listed in this AD as of June 
17, 2011 (76 FR 27875, May 13, 2011).

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-
9066.

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-
9066; 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 2011-10-17, Amendment 39-16698 (76 FR 27875, 
May 13, 2011) (``AD 2011-10-17''). AD 2011-10-17 applied to all Airbus 
Model A300 and A310 series airplanes, and Model A300 B4-600, B4-600R, 
and F4-600R series airplanes, and Model A300 C4-605R Variant F 
airplanes (collectively called Model A300-600 series airplanes). The 
NPRM published in the Federal Register on September 12, 2016 (81 FR 
62679). The NPRM was prompted by a revision of certain ALI documents, 
which specify more restrictive instructions and/or airworthiness 
limitations. The NPRM proposed to require revising the maintenance or 
inspection program, as applicable, to incorporate new or revised 
structural inspection requirements. The NPRM also proposed to remove 
Model A310 and A300-600 series airplanes from the applicability. We are 
issuing this AD to detect and correct fatigue cracking, damage, and 
corrosion in certain structure; such fatigue cracking, damage, and 
corrosion could result in reduced structural integrity of the airplane.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued 
Airworthiness Directive 2015-0115, dated June 23, 2015 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI'') to correct an unsafe condition. The MCAI states:

    The airworthiness limitations applicable to the Damage Tolerant 
Airworthiness Limitation Items (DT ALIs) are currently listed in the 
Airbus Airworthiness Limitations Sections [ALS] Part 2.
    Airbus recently revised the A300 ALS Part 2 and this Revision 02 
was approved by EASA. Airbus A300 ALS Part 2 Revision 02 introduces 
more restrictive maintenance requirements and airworthiness 
limitations, which have been identified as mandatory actions for 
continued airworthiness.
    EASA issued AD 2014-0124 to require compliance with the 
maintenance requirements and associated airworthiness limitations 
defined in Airbus A300 ALS Part 2 Revision 01.
    For the reasons described above, this [EASA] AD retains the 
requirements of EASA AD 2014-0124 for A300 aeroplanes and requires 
implementation of new or more restrictive maintenance instructions 
and/or airworthiness limitations as specified in Airbus A300 ALS 
Part 2 Revision 02.
    The requirements for A310 and A300-600 aeroplanes remain 
unchanged and are covered by EASA AD 2014-0124R1 [FAA AD 2013-13-13, 
Amendment 39-17501 (79 FR 48957, August 19, 2014), contains the 
corresponding requirements for the Model A300-600 and A310 series 
airplanes].

    The unsafe condition is fatigue cracking, damage, or corrosion in 
certain structure (principal structural elements), which could result 
in reduced structural integrity of the airplane. 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-2016-9066.

Comments

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

Request To Revise MCAI Reference

    Airbus requested that we reference the correct MCAI in paragraph 
(k) of the proposed AD, which is EASA Airworthiness Directive 2015-
0115, dated June 23, 2015.
    We agree with the commenter's request. We have confirmed that EASA 
Airworthiness Directive 2015-0115, dated June 23, 2015, is the MCAI 
that should be referenced in this AD. We have revised this AD 
accordingly.

Conclusion

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

Related Service Information Under 1 CFR Part 51

    Airbus has issued Airbus A300 Airworthiness Limitations Section, 
Part 2--Damage-Tolerant Airworthiness Limitation Items (DT ALIs), 
Revision 02, dated October 3, 2014. This service information describes 
airworthiness limitations applicable to the DT ALIs.
    This service information is reasonably available because the 
interested parties have access to it through their normal

[[Page 11136]]

course of business or by the means identified in the ADDRESSES section.

Costs of Compliance

    We estimate that this AD affects 11 airplanes of U.S. registry.
    The actions required by AD 2011-10-17 and retained in this AD take 
about 1 work-hour per product, at an average labor rate of $85 per 
work-hour. Based on these figures, the estimated cost of the actions 
that were required by AD 2011-10-17 is $85 per product.
    We also estimate that it would take about 1 work-hour 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 $935, or $85 per product.

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) 
2011-10-17, Amendment 39-16698 (76 FR 27875, May 13, 2011), and adding 
the following new AD:

2017-04-05 Airbus: Amendment 39-18800; Docket No. FAA-2016-9066; 
Directorate Identifier 2014-NM-113-AD.

(a) Effective Date

    This AD is effective March 28, 2017.

(b) Affected ADs

    This AD replaces AD 2011-10-17, Amendment 39-16698 (76 FR 27875, 
May 13, 2011) (``AD 2011-10-17'').

(c) Applicability

    This AD applies to all Airbus Model A300 B2-1A, B2-1C, B4-2C, 
B2K-3C, B4-103, B2-203, and B4-203 airplanes, certificated in any 
category.

(d) Subject

    Air Transport Association (ATA) of America Codes 52, Doors; 53, 
Fuselage; 54, Nacelles/pylons; 55, Stabilizers; and 57, Wings.

(e) Reason

    This AD was prompted by a revision of certain airworthiness 
limitations item (ALI) documents, which specify more restrictive 
instructions and/or airworthiness limitations. We are issuing this 
AD to detect and correct fatigue cracking, damage, and corrosion in 
certain structure; such fatigue cracking, damage, and corrosion 
could result in reduced structural integrity of the airplane.

(f) Compliance

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

(g) Retained Revision of the Maintenance Program, With Changes

    This paragraph restates the requirements of paragraph (s) of AD 
2011-10-17, with changes. Within 3 months after June 17, 2011 (the 
effective date of AD 2011-10-17): Revise the maintenance program to 
incorporate the structural inspections and inspection intervals 
defined in the Airbus A300 ALI Document AI/SE-M2/95A.1308/07, Issue 
4, dated June 2008. Thereafter, except as required by paragraph (h) 
of this AD and except as provided by paragraph (j)(1) of this AD, no 
alternative structural inspections or inspection intervals may be 
approved. The initial ALI tasks must be done at the times specified 
in Airbus A300 ALI Document AI/SE-M2/95A.1308/07, Issue 4, dated 
June 2008.

(h) New Requirement of This AD: Maintenance or Inspection Program 
Revision

    Within 3 months the effective date of this AD: Revise the 
maintenance program or inspection program, as applicable, to 
incorporate the structural inspections and inspection intervals 
defined in Airbus A300 Airworthiness Limitations Section (ALS), Part 
2--Damage-Tolerant Airworthiness Limitation Items, Revision 02, 
dated October 3, 2014. The initial compliance times for the ALI 
tasks identified in Airbus A300 ALS, Part 2--Damage-Tolerant 
Airworthiness Limitation Items, Revision 02, dated October 3, 2014, 
are at the applicable times specified in Airbus A300 ALS, Part 2--
Damage-Tolerant Airworthiness Limitation Items, Revision 02, dated 
October 3, 2014, or within 3 months after the effective date of this 
AD, whichever occurs later. Accomplishing the applicable initial ALI 
tasks constitutes terminating action for the requirements of 
paragraphs (g) of this AD for that airplane only.

(i) No Alternative Actions or Intervals

    After the maintenance or inspection program has been revised as 
required by paragraph (h) of this AD, no alternative actions (e.g., 
inspections) or intervals may be used unless the actions or 
intervals are approved as an alternative method of compliance (AMOC) 
in accordance with the procedures specified in paragraph (j)(1) of 
this AD.

(j) 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. The AMOC

[[Page 11137]]

approval letter must specifically reference this AD.
    (ii) AMOCs approved previously for AD 2011-10-17 are approved as 
AMOCs for the corresponding provisions 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 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.

(k) Related Information

    Refer to Mandatory Continuing Airworthiness Information (MCAI) 
EASA Airworthiness Directive 2015-0115, dated June 23, 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-2016-9066.

(l) 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 
March 28, 2017.
    (i) Airbus A300 Airworthiness Limitations Section, Part 2--
Damage-Tolerant Airworthiness Limitation Items, Revision 02, dated 
October 3, 2014.
    (ii) Reserved.
    (4) The following service information was approved for IBR on 
June 17, 2011 (76 FR 27875, May 13, 2011).
    (i) Airbus A300 Airworthiness Limitations Inspections Document 
AI/SE-M2/95A.1308/07, Issue 4, dated June 2008.
    (ii) Reserved.
    (5) For service information identified in this AD, contact 
Airbus SAS, Airworthiness Office- EAW, 1 Rond Point Maurice 
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; 
fax +33 5 61 93 44 51; email account.airworth-eas@airbus.com; 
Internet https://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: https://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on January 24, 2017.
Dionne Palermo,
Acting Manager,
    Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2017-03021 Filed 2-17-17; 8:45 am]
 BILLING CODE 4910-13-P
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