Airworthiness Directives; Airbus Airplanes, 52832-52835 [2017-24501]

Download as PDF 52832 Federal Register / Vol. 82, No. 219 / Wednesday, November 15, 2017 / Rules and Regulations (d) Subject Joint Aircraft System Component (JASC) Code 7531, Compressor bleed governor. Burlington, MA 01803; phone: 781–238– 7754; fax: 781–238–7199; email: john.frost@ faa.gov. (e) Unsafe Condition This AD was prompted by an engine fire that occurred as a result of malfunctions related to the operability bleed valve (OBV). We are issuing this AD to prevent failure of the OBV. The unsafe condition, if not corrected, could result in failure of the OBV, engine fire, and damage to the airplane. (k) 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) General Electric Company (GE) Service Bulletin CF34–8C–AL S/B 75–0019 Revision 01, dated October 24, 2017. (ii) Reserved. (3) For GE service information identified in this AD, contact General Electric Company, GE-Aviation, Room 285, 1 Neumann Way, Cincinnati, OH 45215, phone: 513–552–3272; fax: 513–552–3329; email: geae.aoc@ge.com. (4) You may view this service information at FAA, FAA, Engine & Propeller Standards Branch, 1200 District Avenue, Burlington, MA. For information on the availability of this material at the FAA, call 781–238–7125. (5) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: http:// www.archives.gov/federal-register/cfr/ibrlocations.html. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Required Actions (1) Inspect the bleed air manifold link rod assemblies and the OBV supply, return, and drain fuel fittings within 500 flight hours after the effective date of this AD. (2) Use the Accomplishment Instructions, paragraph 3.B., in GE Service Bulletin (SB) CF34–8C–AL S/B 75–0019 Revision 01, dated October 24, 2017, to do the inspection. Replace parts that fail this inspection according to the following criteria: (i) Replace any OBV that fails the inspection with a part eligible for installation before further flight. (ii) Replace any additional hardware that fails inspection within 50 flight cycles. The engine can be returned to service each day for up to the 50 flight cycles if the OBV rosan rings and fittings are examined each day for fuel leaks and looseness based on the criteria in Table 1 of GE SB CF34–8C–AL S/B 75– 0019 Revision 01, dated October 24, 2017. (3) The reporting instructions in paragraphs 3.B.(3), 3.B.(5)(e), 3.B.(6)(e), and 3.B.(8) of GE SB CF34–8C–AL S/B 75–0019 Revision 01, dated October 24, 2017, are not required by this AD. sradovich on DSK3GMQ082PROD with RULES (h) Credit for Previous Actions You may take credit for the actions that are required by paragraph (g) of this AD if you performed these actions before the effective date of this AD using GE CF34–8C SB 75– 0019 R00, dated August 4, 2017. (i) Alternative Methods of Compliance (AMOCs) (1) The Manager, ECO Branch, 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 certification office, send it to the attention of the person identified in paragraph (j) of this AD. You may email your request to: ANE-AD-AMOC@ 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. (j) Related Information For more information about this AD, contact John Frost, Aerospace Engineer, ECO Branch, FAA, 1200 District Avenue, VerDate Sep<11>2014 15:48 Nov 14, 2017 Jkt 244001 Issued in Burlington, Massachusetts, on November 9, 2017. Robert J. Ganley, Manager, Engine and Propeller Standards Branch, Aircraft Certification Service. [FR Doc. 2017–24700 Filed 11–14–17; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2017–0710; Product Identifier 2017–NM–019–AD; Amendment 39–19098; AD 2017–23–04] 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 B4–600R series airplanes; Model A300 B4–603, B4–620, and B4–622 airplanes; Model A300 C4– 605R Variant F airplanes; and Model A300 F4–605R airplanes. This AD was prompted by a determination that the top stringer joints at rib 18 are an area of uniform stress distribution, which SUMMARY: PO 00000 Frm 00010 Fmt 4700 Sfmt 4700 indicates that cracks may develop in adjacent stringers at the same time. This AD requires an inspection of the upper wing skin and top stringer joints, and modification of the stringer joint couplings if necessary. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective December 20, 2017. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of December 20, 2017. ADDRESSES: For service information identified in this final rule, contact Airbus SAS, Airworthiness Office— EAW, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email account.airworth-eas@ airbus.com; Internet http:// www.airbus.com. You may view this referenced service information at the FAA, Transport Standards Branch, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA–2017– 0710. Examining the AD Docket You may examine the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2017– 0710; 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 Section, Transport Standards Branch, 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– 600R series airplanes; Model A300 B4– 603, B4–620, and B4–622 airplanes; E:\FR\FM\15NOR1.SGM 15NOR1 Federal Register / Vol. 82, No. 219 / Wednesday, November 15, 2017 / Rules and Regulations Model A300 C4–605R Variant F airplanes; and Model A300 F4–605R airplanes. The NPRM published in the Federal Register on July 27, 2017 (82 FR 34885) (‘‘the NPRM’’). The NPRM was prompted by a determination that the top stringer joints at rib 18 are an area of uniform stress distribution, which indicates that cracks may develop in adjacent stringers at the same time. The NPRM proposed to require an inspection of the upper wing skin and top stringer joints, and modification of the stringer joint couplings if necessary. We are issuing this AD to detect and correct damage (including cracking) at the stringer joints, which could reduce the structural integrity of the wing. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA AD 2017–0023, dated February 10, 2017 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for certain Airbus Model A300 B4–600R series airplanes; Model A300 B4–603, B4–620, and B4–622 airplanes; Model A300 C4–605R Variant F airplanes; and Model A300 F4–605R airplanes. The MCAI states: Prompted by the conclusion of the WFD analysis, Airbus issued Service Bulletin (SB) A300–57–6118 to provide modification instructions. The modification will both relife via oversizing and inspect via nondestructive test a defined number of stringer joint fastener holes at Rib 18. This modification will delay the onset of cracking at the stringer joint, providing it is completed at the specified time and will delay the requirement for subsequent inspection. For the reasons described above, this [EASA] AD requires a detailed visual inspection (DVI) [for damage, including cracking] of the upper wing skin and the top stringer joints at Rib 18, [and corrective action if necessary] and modification of the stringer joint couplings at Rib 18, on both wings [as applicable]. In response to the FAA Part 26 rule change concerning Widespread Fatigue Damage (WFD), all wing structural items of the A300– 600 design deemed potentially susceptible to WFD were assessed. The top stringer joints at Rib 18 were highlighted as an area of uniform stress distribution, indicating that cracks may develop in adjacent stringers at the same time which is known as Multi Element Damage (MED). Each affected stringer joint consists of three main load transferring parts: An overlapping flange, two straps attached through the stringer web and a strap on the top flange. All the components of the joint are attached with fasteners. The fastener holes were the subject of a MED WFD analysis, which showed that cracking could occur from a number of the holes in the joint on stringers 11, 12, 13, 14, 15, 16, 17, and 18. This condition, if not detected and corrected, could reduce the structural integrity of the wing. 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. The modification includes a related investigative action, i.e., a special detailed (roto-probe) inspection for damage, including cracking, of the fastener holes in the upper wing skin, and corrective action if necessary. Corrective actions include repairing any damage. You may examine the MCAI in the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2017– 0710. Comments Request To Update the Costs of Compliance FedEx supported the intent of the NPRM, but requested that we update the parts cost in the Costs of Compliance section of the proposed AD to reflect the cost of two parts kits. FedEx noted that the proposed AD listed the parts cost for only one kit. FedEx pointed out that operators may need to modify both wings and could therefore need two parts kits per airplane. We agree with the commenter’s request. We have revised the Costs of Compliance section of this final rule to 52833 reflect two parts kits, each costing $4,770. Request To Fix a Typographical Error Airbus requested that we correct a reference to ‘‘Airbus Model A300 C4– 605 Variant F’’ airplanes in paragraph (g)(2) of the proposed AD. The correct model name is ‘‘A300 C4–605R Variant F’’ airplanes. We agree with the commenter’s request. We have corrected the typographical error in this AD. Conclusion We reviewed the relevant data, considered the comments received, and determined that air safety and the public interest require adopting this AD with the changes described previously and minor editorial changes. We have determined that these 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. We also determined that these changes will not increase the economic burden on any operator or increase the scope of this AD. Related Service Information Under 1 CFR Part 51 Airbus has issued Service Bulletin A300–57–6118, Revision 01, dated January 31, 2017. This service information describes procedures for an inspection of the upper wing skin and top stringer joints at rib 18, and modification of the stringer joint couplings. 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 65 airplanes of U.S. registry. We estimate the following costs to comply with this AD: ESTIMATED COSTS Labor cost Parts cost Cost per product Inspection and modification ................. sradovich on DSK3GMQ082PROD with RULES Action 37 work-hours × $85 per hour = $3,145. Up to $9,540 ......... Up to $12,685 ....... We have received no definitive data that will allow us to provide cost estimates for certain on-condition actions specified in this AD. VerDate Sep<11>2014 15:48 Nov 14, 2017 Jkt 244001 Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, PO 00000 Frm 00011 Fmt 4700 Sfmt 4700 Cost on U.S. operators Up to $824,525. section 106, describes the authority of the FAA Administrator. ‘‘Subtitle VII: Aviation Programs,’’ describes in more detail the scope of the Agency’s authority. E:\FR\FM\15NOR1.SGM 15NOR1 52834 Federal Register / Vol. 82, No. 219 / Wednesday, November 15, 2017 / Rules and Regulations 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. This AD is issued in accordance with authority delegated by the Executive Director, Aircraft Certification Service, as authorized by FAA Order 8000.51C. In accordance with that order, issuance of ADs is normally a function of the Compliance and Airworthiness Division, but during this transition period, the Executive Director has delegated the authority to issue ADs applicable to transport category airplanes to the Director of the System Oversight Division. 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. sradovich on DSK3GMQ082PROD with RULES 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: ■ VerDate Sep<11>2014 15:48 Nov 14, 2017 Jkt 244001 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): ■ 2017–23–04 Airbus: Amendment 39–19098; Docket No. FAA–2017–0710; Product Identifier 2017–NM–019–AD. (a) Effective Date This AD is effective December 20, 2017. (b) Affected ADs None. (c) Applicability This AD applies to Airbus Model A300 B4– 605R, B4–622R, B4–603, C4–605R Variant F, B4–620, B4–622, and F4–605R airplanes, certificated in any category, all serial numbers except Model A300 F4–605R airplanes that have embodied Airbus modification 12699 in production. (d) Subject Air Transport Association (ATA) of America Code 57, Wings. (e) Reason This AD was prompted by a determination that the top stringer joints at rib 18 are an area of uniform stress distribution, which indicates that cracks may develop in adjacent stringers at the same time. We are issuing this AD to detect and correct damage (including cracking) at the stringer joints, which could reduce the structural integrity of the wing. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Definitions For the purposes of this AD, the definitions in paragraphs (g)(1) through (g)(5) of this AD apply. (1) Group 1 airplanes are defined as Airbus Model A300 B4–603, B4–605R, B4–620, B4– 622, and B4–622R airplanes. (2) Group 2 airplanes are defined as Airbus Model A300 C4–605R Variant F and F4–605R (if in pre-modification 12699 configuration) airplanes. (3) Short range (SR) is defined as airplanes with an average flight time of less than 1.5 flight hours per flight cycle. (4) Long range (LR) is defined as airplanes with an average flight time equal to or higher than 1.5 flight hours per flight cycle. (5) For determining the ‘‘short range’’ and ‘‘long range’’ airplanes, the average flight time is the total accumulated flight hours, counted from take-off to touch-down, divided by the total accumulated flight cycles at the effective date of this AD. (h) Inspection and Modification Not before exceeding the applicable lower thresholds as specified in table 1 to paragraph (h) of this AD, and within the compliance times specified in paragraphs (h)(1), (h)(2), (h)(3), and (h)(4) of this AD, as applicable: Accomplish a detailed visual inspection for damage (including cracking) of PO 00000 Frm 00012 Fmt 4700 Sfmt 4700 the upper wing skin and top stringer joints at rib 18 on both wings, do all applicable corrective actions, and do the applicable modification, including related investigative and corrective actions, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300–57–6118, Revision 01, dated January 31, 2017, except as required by paragraph (i) of this AD. Do all applicable modifications, related investigative actions, and corrective actions before further flight. (1) For Group 1, LR airplanes: Inspect at the time specified in paragraph (h)(1)(i) or (h)(1)(ii) of this AD, whichever occurs later. (i) Before exceeding 32,500 flight cycles or 70,300 flight hours, whichever occurs first since first flight of the airplane. (ii) Within 700 flight cycles, 1,500 flight hours, or 12 months, whichever occurs first after the effective date of this AD. (2) For Group 1, SR airplanes: Inspect at the time specified in paragraphs (h)(2)(i) or (h)(2)(ii) of this AD, whichever occurs later. (i) Before exceeding 35,100 flight cycles or 52,600 flight hours, whichever occurs first since the first flight of the airplane. (ii) Within 700 flight cycles or 1,000 flight hours, or 12 months, whichever occurs first after the effective date of this AD. (3) For Group 2, LR airplanes: Inspect before exceeding 35,000 flight cycles or 75,700 flight hours, whichever occurs first since the first flight of the airplane. (4) For Group 2, SR airplanes: Inspect before exceeding 37,800 flight cycles or 56,700 flight hours, whichever occurs first since the first flight of the airplane. TABLE 1 TO PARAGRAPH (h) OF THIS AD—COMPLIANCE TIME LOWER THRESHOLDS Compliance time flight cycles (FC) or flight hours (FH), whichever occurs first since first flight of the airplane Applicable airplanes Group 1, LR Group 1, SR Group 2, LR Group 2, SR Not before exceeding 66,700 FH. Not before exceeding 43,000 FH. Not before exceeding 61,700 FH. Not before exceeding 51,600 FH. 30,900 FC or 28,700 FC or 28,600 FC or 34,400 FC or (i) Service Information Exception Where Airbus Service Bulletin A300–57– 6118, Revision 01, dated January 31, 2017, specifies to contact Airbus for appropriate action, and specifies that action as ‘‘RC’’ (Required for Compliance): Before further flight, accomplish corrective actions in accordance with the procedures specified in paragraph (k)(2) of this AD. (j) Credit for Previous Actions This paragraph provides credit for actions required by paragraph (h) of this AD, if those actions were performed before the effective date of this AD using Airbus Service Bulletin A300–57–6118, dated June 30, 2015. (k) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International E:\FR\FM\15NOR1.SGM 15NOR1 Federal Register / Vol. 82, No. 219 / Wednesday, November 15, 2017 / Rules and Regulations (ii) Reserved. (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 http://www.airbus.com. (4) You may view this service information at the FAA, Transport Standards Branch, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. (5) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: http:// www.archives.gov/federal-register/cfr/ibrlocations.html. (l) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA AD 2017–0023, dated February 10, 2017, for related information. This MCAI may be found in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA–2017–0710. (2) For more information about this AD, contact Dan Rodina, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425– 227–2125; fax 425–227–1149. (3) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (m)(3) and (m)(4) of this AD. sradovich on DSK3GMQ082PROD with RULES Section, Transport Standards Branch, 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 Section, send it to the attention of the person identified in paragraph (l)(2) of this AD. Information may be emailed to: 9-ANM-116-AMOCREQUESTS@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. (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 Section, Transport Standards Branch, 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 DOAauthorized signature. (3) Required for Compliance (RC): Except as required by paragraph (i) of this AD, if any service information contains procedures or tests that are identified as RC, those procedures and tests must be done to comply with this AD; any procedures or tests that are not identified as RC are recommended. Those procedures and tests that are not identified as RC may be deviated from using accepted methods in accordance with the operator’s maintenance or inspection program without obtaining approval of an AMOC, provided the procedures and tests identified as RC can be done and the airplane can be put back in an airworthy condition. Any substitutions or changes to procedures or tests identified as RC require approval of an AMOC. AGENCY: (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 this AD specifies otherwise. (i) Airbus Service Bulletin A300–57–6118, Revision 01, dated January 31, 2017. VerDate Sep<11>2014 15:48 Nov 14, 2017 Jkt 244001 Issued in Renton, Washington, on November 3, 2017. Jeffrey E. Duven, Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2017–24501 Filed 11–14–17; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2017–0715; Product Identifier 2017–NM–073–AD; Amendment 39–19096; AD 2017–23–02] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule. We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737–200, –200C, –300, –400, and –500 series airplanes. This AD was prompted by an evaluation by the design approval holder (DAH) indicating that the fuselage crown skin panels are subject to widespread fatigue damage (WFD). This AD requires repetitive inspections, replacement, and applicable oncondition actions for certain fuselage crown skin panels. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective December 20, 2017. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of December 20, 2017. ADDRESSES: For service information identified in this final rule, contact SUMMARY: PO 00000 Frm 00013 Fmt 4700 Sfmt 4700 52835 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 Standards Branch, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. It is also available on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2017– 0715. Examining the AD Docket You may examine the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2017– 0715; 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 final rule, 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: Jennifer Tsakoumakis, Aerospace Engineer, Airframe Section, FAA, Los Angeles ACO Branch, 3960 Paramount Boulevard, Lakewood, CA 90712–4137; phone: 562–627–5264; fax: 562–627– 5210; email: Jennifer.Tsakoumakis@ 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 737–200, –200C, –300, –400, and –500 series airplanes. The NPRM published in the Federal Register on August 10, 2017 (82 FR 37366). The NPRM was prompted by an evaluation by the DAH indicating that the fuselage crown skin panels are subject to WFD. The NPRM proposed to require repetitive inspections, replacement, and applicable on-condition actions for certain fuselage crown skin panels. We are issuing this AD to detect and correct cracking in the fuselage crown skin panels. Multiple adjacent cracks in the fuselage crown skin could link up and lead to decompression or loss of structural integrity of the airplane. E:\FR\FM\15NOR1.SGM 15NOR1

Agencies

[Federal Register Volume 82, Number 219 (Wednesday, November 15, 2017)]
[Rules and Regulations]
[Pages 52832-52835]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-24501]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2017-0710; Product Identifier 2017-NM-019-AD; Amendment 
39-19098; AD 2017-23-04]
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 B4-600R series airplanes; Model A300 B4-603, B4-620, 
and B4-622 airplanes; Model A300 C4-605R Variant F airplanes; and Model 
A300 F4-605R airplanes. This AD was prompted by a determination that 
the top stringer joints at rib 18 are an area of uniform stress 
distribution, which indicates that cracks may develop in adjacent 
stringers at the same time. This AD requires an inspection of the upper 
wing skin and top stringer joints, and modification of the stringer 
joint couplings if necessary. We are issuing this AD to address the 
unsafe condition on these products.

DATES: This AD is effective December 20, 2017.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of December 20, 
2017.

ADDRESSES: For service information identified in this final rule, 
contact Airbus SAS, Airworthiness Office--EAW, 1 Rond Point Maurice 
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax 
+33 5 61 93 44 51; email account.airworth-eas@airbus.com; Internet 
http://www.airbus.com. You may view this referenced service information 
at the FAA, Transport Standards Branch, 1601 Lind Avenue SW., Renton, 
WA. For information on the availability of this material at the FAA, 
call 425-227-1221. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2017-
0710.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2017-
0710; 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 Section, Transport Standards Branch, 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 
B4-600R series airplanes; Model A300 B4-603, B4-620, and B4-622 
airplanes;

[[Page 52833]]

Model A300 C4-605R Variant F airplanes; and Model A300 F4-605R 
airplanes. The NPRM published in the Federal Register on July 27, 2017 
(82 FR 34885) (``the NPRM''). The NPRM was prompted by a determination 
that the top stringer joints at rib 18 are an area of uniform stress 
distribution, which indicates that cracks may develop in adjacent 
stringers at the same time. The NPRM proposed to require an inspection 
of the upper wing skin and top stringer joints, and modification of the 
stringer joint couplings if necessary. We are issuing this AD to detect 
and correct damage (including cracking) at the stringer joints, which 
could reduce the structural integrity of the wing.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA AD 
2017-0023, dated February 10, 2017 (referred to after this as the 
Mandatory Continuing Airworthiness Information, or ``the MCAI''), to 
correct an unsafe condition for certain Airbus Model A300 B4-600R 
series airplanes; Model A300 B4-603, B4-620, and B4-622 airplanes; 
Model A300 C4-605R Variant F airplanes; and Model A300 F4-605R 
airplanes. The MCAI states:

    In response to the FAA Part 26 rule change concerning Widespread 
Fatigue Damage (WFD), all wing structural items of the A300-600 
design deemed potentially susceptible to WFD were assessed. The top 
stringer joints at Rib 18 were highlighted as an area of uniform 
stress distribution, indicating that cracks may develop in adjacent 
stringers at the same time which is known as Multi Element Damage 
(MED). Each affected stringer joint consists of three main load 
transferring parts: An overlapping flange, two straps attached 
through the stringer web and a strap on the top flange. All the 
components of the joint are attached with fasteners. The fastener 
holes were the subject of a MED WFD analysis, which showed that 
cracking could occur from a number of the holes in the joint on 
stringers 11, 12, 13, 14, 15, 16, 17, and 18.
    This condition, if not detected and corrected, could reduce the 
structural integrity of the wing.
    Prompted by the conclusion of the WFD analysis, Airbus issued 
Service Bulletin (SB) A300-57-6118 to provide modification 
instructions. The modification will both re-life via oversizing and 
inspect via non-destructive test a defined number of stringer joint 
fastener holes at Rib 18. This modification will delay the onset of 
cracking at the stringer joint, providing it is completed at the 
specified time and will delay the requirement for subsequent 
inspection.
    For the reasons described above, this [EASA] AD requires a 
detailed visual inspection (DVI) [for damage, including cracking] of 
the upper wing skin and the top stringer joints at Rib 18, [and 
corrective action if necessary] and modification of the stringer 
joint couplings at Rib 18, on both wings [as applicable].

    The modification includes a related investigative action, i.e., a 
special detailed (roto-probe) inspection for damage, including 
cracking, of the fastener holes in the upper wing skin, and corrective 
action if necessary. Corrective actions include repairing any damage.
    You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2017-
0710.

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 Update the Costs of Compliance

    FedEx supported the intent of the NPRM, but requested that we 
update the parts cost in the Costs of Compliance section of the 
proposed AD to reflect the cost of two parts kits. FedEx noted that the 
proposed AD listed the parts cost for only one kit. FedEx pointed out 
that operators may need to modify both wings and could therefore need 
two parts kits per airplane.
    We agree with the commenter's request. We have revised the Costs of 
Compliance section of this final rule to reflect two parts kits, each 
costing $4,770.

Request To Fix a Typographical Error

    Airbus requested that we correct a reference to ``Airbus Model A300 
C4-605 Variant F'' airplanes in paragraph (g)(2) of the proposed AD. 
The correct model name is ``A300 C4-605R Variant F'' airplanes.
    We agree with the commenter's request. We have corrected the 
typographical error in this AD.

Conclusion

    We reviewed the relevant data, considered the comments received, 
and determined that air safety and the public interest require adopting 
this AD with the changes described previously and minor editorial 
changes. We have determined that these 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.
    We also determined that these changes will not increase the 
economic burden on any operator or increase the scope of this AD.

Related Service Information Under 1 CFR Part 51

    Airbus has issued Service Bulletin A300-57-6118, Revision 01, dated 
January 31, 2017. This service information describes procedures for an 
inspection of the upper wing skin and top stringer joints at rib 18, 
and modification of the stringer joint couplings. 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 65 airplanes of U.S. registry.
    We estimate the following costs to comply with this AD:

                                                                     Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
              Action                        Labor cost                   Parts cost                 Cost per product           Cost on U.S. operators
--------------------------------------------------------------------------------------------------------------------------------------------------------
Inspection and modification.......  37 work-hours x $85 per     Up to $9,540................  Up to $12,685...............  Up to $824,525.
                                     hour = $3,145.
--------------------------------------------------------------------------------------------------------------------------------------------------------

    We have received no definitive data that will allow us to provide 
cost estimates for certain on-condition actions specified in this AD.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. ``Subtitle VII: Aviation 
Programs,'' describes in more detail the scope of the Agency's 
authority.

[[Page 52834]]

    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.
    This AD is issued in accordance with authority delegated by the 
Executive Director, Aircraft Certification Service, as authorized by 
FAA Order 8000.51C. In accordance with that order, issuance of ADs is 
normally a function of the Compliance and Airworthiness Division, but 
during this transition period, the Executive Director has delegated the 
authority to issue ADs applicable to transport category airplanes to 
the Director of the System Oversight Division.

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):

2017-23-04 Airbus: Amendment 39-19098; Docket No. FAA-2017-0710; 
Product Identifier 2017-NM-019-AD.

(a) Effective Date

    This AD is effective December 20, 2017.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Airbus Model A300 B4-605R, B4-622R, B4-603, 
C4-605R Variant F, B4-620, B4-622, and F4-605R airplanes, 
certificated in any category, all serial numbers except Model A300 
F4-605R airplanes that have embodied Airbus modification 12699 in 
production.

(d) Subject

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

(e) Reason

    This AD was prompted by a determination that the top stringer 
joints at rib 18 are an area of uniform stress distribution, which 
indicates that cracks may develop in adjacent stringers at the same 
time. We are issuing this AD to detect and correct damage (including 
cracking) at the stringer joints, which could reduce the structural 
integrity of the wing.

(f) Compliance

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

(g) Definitions

    For the purposes of this AD, the definitions in paragraphs 
(g)(1) through (g)(5) of this AD apply.
    (1) Group 1 airplanes are defined as Airbus Model A300 B4-603, 
B4-605R, B4-620, B4-622, and B4-622R airplanes.
    (2) Group 2 airplanes are defined as Airbus Model A300 C4-605R 
Variant F and F4-605R (if in pre-modification 12699 configuration) 
airplanes.
    (3) Short range (SR) is defined as airplanes with an average 
flight time of less than 1.5 flight hours per flight cycle.
    (4) Long range (LR) is defined as airplanes with an average 
flight time equal to or higher than 1.5 flight hours per flight 
cycle.
    (5) For determining the ``short range'' and ``long range'' 
airplanes, the average flight time is the total accumulated flight 
hours, counted from take-off to touch-down, divided by the total 
accumulated flight cycles at the effective date of this AD.

(h) Inspection and Modification

    Not before exceeding the applicable lower thresholds as 
specified in table 1 to paragraph (h) of this AD, and within the 
compliance times specified in paragraphs (h)(1), (h)(2), (h)(3), and 
(h)(4) of this AD, as applicable: Accomplish a detailed visual 
inspection for damage (including cracking) of the upper wing skin 
and top stringer joints at rib 18 on both wings, do all applicable 
corrective actions, and do the applicable modification, including 
related investigative and corrective actions, in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A300-57-6118, 
Revision 01, dated January 31, 2017, except as required by paragraph 
(i) of this AD. Do all applicable modifications, related 
investigative actions, and corrective actions before further flight.
    (1) For Group 1, LR airplanes: Inspect at the time specified in 
paragraph (h)(1)(i) or (h)(1)(ii) of this AD, whichever occurs 
later.
    (i) Before exceeding 32,500 flight cycles or 70,300 flight 
hours, whichever occurs first since first flight of the airplane.
    (ii) Within 700 flight cycles, 1,500 flight hours, or 12 months, 
whichever occurs first after the effective date of this AD.
    (2) For Group 1, SR airplanes: Inspect at the time specified in 
paragraphs (h)(2)(i) or (h)(2)(ii) of this AD, whichever occurs 
later.
    (i) Before exceeding 35,100 flight cycles or 52,600 flight 
hours, whichever occurs first since the first flight of the 
airplane.
    (ii) Within 700 flight cycles or 1,000 flight hours, or 12 
months, whichever occurs first after the effective date of this AD.
    (3) For Group 2, LR airplanes: Inspect before exceeding 35,000 
flight cycles or 75,700 flight hours, whichever occurs first since 
the first flight of the airplane.
    (4) For Group 2, SR airplanes: Inspect before exceeding 37,800 
flight cycles or 56,700 flight hours, whichever occurs first since 
the first flight of the airplane.

  Table 1 to Paragraph (h) of This AD--Compliance Time Lower Thresholds
------------------------------------------------------------------------
                                     Compliance time flight cycles  (FC)
                                      or flight hours (FH),  whichever
       Applicable  airplanes         occurs first since  first flight of
                                                the airplane
------------------------------------------------------------------------
Group 1, LR.......................  Not before exceeding 30,900 FC or
                                     66,700 FH.
Group 1, SR.......................  Not before exceeding 28,700 FC or
                                     43,000 FH.
Group 2, LR.......................  Not before exceeding 28,600 FC or
                                     61,700 FH.
Group 2, SR.......................  Not before exceeding 34,400 FC or
                                     51,600 FH.
------------------------------------------------------------------------

(i) Service Information Exception

    Where Airbus Service Bulletin A300-57-6118, Revision 01, dated 
January 31, 2017, specifies to contact Airbus for appropriate 
action, and specifies that action as ``RC'' (Required for 
Compliance): Before further flight, accomplish corrective actions in 
accordance with the procedures specified in paragraph (k)(2) of this 
AD.

(j) Credit for Previous Actions

    This paragraph provides credit for actions required by paragraph 
(h) of this AD, if those actions were performed before the effective 
date of this AD using Airbus Service Bulletin A300-57-6118, dated 
June 30, 2015.

(k) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International

[[Page 52835]]

Section, Transport Standards Branch, 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 Section, send it to the attention of the person 
identified in paragraph (l)(2) of this AD. 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.
    (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 
Section, Transport Standards Branch, FAA; or the European Aviation 
Safety Agency (EASA); or Airbus's EASA Design Organization Approval 
(DOA). If approved by the DOA, the approval must include the DOA-
authorized signature.
    (3) Required for Compliance (RC): Except as required by 
paragraph (i) of this AD, if any service information contains 
procedures or tests that are identified as RC, those procedures and 
tests must be done to comply with this AD; any procedures or tests 
that are not identified as RC are recommended. Those procedures and 
tests that are not identified as RC may be deviated from using 
accepted methods in accordance with the operator's maintenance or 
inspection program without obtaining approval of an AMOC, provided 
the procedures and tests identified as RC can be done and the 
airplane can be put back in an airworthy condition. Any 
substitutions or changes to procedures or tests identified as RC 
require approval of an AMOC.

(l) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA AD 2017-0023, dated February 10, 2017, for related 
information. This MCAI may be found in the AD docket on the Internet 
at http://www.regulations.gov by searching for and locating Docket 
No. FAA-2017-0710.
    (2) For more information about this AD, contact Dan Rodina, 
Aerospace Engineer, International Section, Transport Standards 
Branch, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 
425-227-2125; fax 425-227-1149.
    (3) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (m)(3) and (m)(4) of this AD.

(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 this AD specifies otherwise.
    (i) Airbus Service Bulletin A300-57-6118, Revision 01, dated 
January 31, 2017.
    (ii) Reserved.
    (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 http://www.airbus.com.
    (4) You may view this service information at the FAA, Transport 
Standards Branch, 1601 Lind Avenue SW., Renton, WA. For information 
on the availability of this material at the FAA, call 425-227-1221.
    (5) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on November 3, 2017.
Jeffrey E. Duven,
Director, System Oversight Division, Aircraft Certification Service.
[FR Doc. 2017-24501 Filed 11-14-17; 8:45 am]
BILLING CODE 4910-13-P