Airworthiness Directives; Airbus SAS Airplanes, 5592-5595 [2019-02925]

Download as PDF 5592 Federal Register / Vol. 84, No. 36 / Friday, February 22, 2019 / Rules and Regulations (required for compliance) in, and in accordance with, the Accomplishment Instructions of BASB 737–57A1327, R2. (h) Exceptions to Service Information Specifications (1) For purposes of determining compliance with the requirements of this AD: Where BASB 737–57A1327, R2 uses the phrase ‘‘the original issue date of this service bulletin,’’ this AD requires using September 22, 2017 (the effective date of AD 2017–16– 05). (2) For purposes of determining compliance with the requirements of this AD: Where BASB 737–57A1327, R2 uses the phrase ‘‘the Revision 2 date of this service bulletin,’’ this AD requires using ‘‘the effective date of this AD.’’ (i) Parts Installation Limitation As of the effective date of this AD, no person may install a Krueger flap or Krueger flap bullnose on any airplane identified in paragraph (c)(1)(i), (c)(1)(ii), or (c)(1)(iii) of this AD, unless the actions required by paragraph (g) of this AD have been accomplished on the Krueger flap bullnose after installation but prior to further flight. These actions are required only for the Krueger flap(s) or Krueger flap bullnose(s) being installed. (j) Credit for Previous Actions (1) This paragraph provides credit for the actions specified in paragraph (g) of this AD, if those actions were performed before September 22, 2017 (the effective date of AD 2017–16–05), using Boeing Alert Service Bulletin 737–57A1327, dated May 20, 2016. (2) This paragraph provides credit for the actions specified in paragraph (g) of this AD, if those actions were performed before the effective date of this AD, using Boeing Alert Service Bulletin 737–57A1327, Revision 1, dated September 28, 2016. (k) Alternative Methods of Compliance (AMOCs) (1) The Manager, Seattle ACO 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 (l)(1) of this AD. Information may be emailed to: 9ANM-Seattle-ACO-AMOC-Requests@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, Seattle ACO Branch, FAA, to make those findings. To be approved, the repair method, modification deviation, or alteration deviation must meet VerDate Sep<11>2014 15:50 Feb 21, 2019 Jkt 247001 the certification basis of the airplane, and the approval must specifically refer to this AD. (4) AMOCs approved previously for AD 2017–16–05 are approved as AMOCs for the corresponding provisions of BASB 737– 57A1327, R2 that are required by paragraph (g) of this AD. (5) For service information that contains steps that are labeled as RC, the provisions of paragraphs (k)(5)(i) and (k)(5)(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) Operators may deviate from steps not labeled as RC by 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. (1) For more information about this AD, contact Alan Pohl, Aerospace Engineer, Airframe Section, FAA, Seattle ACO Branch, 2200 South 216th St., Des Moines, WA 98198; phone and fax: 206–231–3527; email: alan.pohl@faa.gov. (2) 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 the AD specifies otherwise. (i) Boeing Alert Service Bulletin 737– 57A1327, Revision 2, dated July 25, 2017. (ii) [Reserved] (3) For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Contractual & Data Services (C&DS), 2600 Westminster Blvd., MC 110–SK57, Seal Beach, CA 90740–5600; phone: 562–797–1717; internet: https:// www.myboeingfleet.com. (4) You may view this service information at the FAA, Transport Standards Branch, 2200 South 216th St., Des Moines, WA. For information on the availability of this material at the FAA, call 206–231–3195. (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. Frm 00010 Fmt 4700 [FR Doc. 2019–02930 Filed 2–21–19; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2018–0906; Product Identifier 2018–NM–122–AD; Amendment 39–19561; AD 2019–03–09] RIN 2120–AA64 Airworthiness Directives; Airbus SAS Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for all Airbus SAS Model A310–304, –322, –324, and –325 airplanes. This AD was prompted by an evaluation by the design approval holder (DAH) indicating that certain wing skin stringer joints are subject to widespread fatigue damage (WFD). This AD requires a rototest inspection of the fastener holes in the affected areas and repair if necessary, and modifying the fastener holes. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective March 29, 2019. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of March 29, 2019. ADDRESSES: For service information identified in this final rule, contact Airbus SAS, Airworthiness Office— EAW, Rond-Point Emile Dewoitine No: 2, 31700 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email account.airwortheas@airbus.com; internet https:// www.airbus.com. You may view this service information at the FAA, Transport Standards Branch, 2200 South 216th St., Des Moines, WA. For information on the availability of this material at the FAA, call 206–231–3195. It is also available on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA–2018– 0906. SUMMARY: (l) Related Information PO 00000 Issued in Des Moines, Washington, on February 7, 2019. Michael Kaszycki, Acting Director, System Oversight Division, Aircraft Certification Service. Sfmt 4700 Examining the AD Docket You may examine the AD docket on the internet at https:// E:\FR\FM\22FER1.SGM 22FER1 Federal Register / Vol. 84, No. 36 / Friday, February 22, 2019 / Rules and Regulations www.regulations.gov by searching for and locating Docket No. FAA–2018– 0906; or in person at Docket Operations 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 Docket Operations (phone: 800–647–5527) is U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE, Washington, DC 20590. Dan Rodina, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone and fax 206–231–3225. FOR FURTHER INFORMATION CONTACT: 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 all Airbus SAS Model A310– 304, –322, –324, and –325 airplanes. The NPRM published in the Federal Register on November 5, 2018 (83 FR 55294). The NPRM was prompted by an evaluation by the DAH indicating that certain wing skin stringer joints are subject to WFD. The NPRM proposed to require a rototest inspection of the fastener holes in the affected areas and repair if necessary, and modifying the fastener holes. We are issuing this AD to address any cracking of the top wing skin stringer joints at rib 19, which could result in reduced 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 2018–0174, dated August 14, 2018 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for all Airbus SAS Model A310–304, –322, –324, and –325 airplanes. The MCAI states: In response to US 14 CFR part 26 concerning Widespread Fatigue Damage (WFD), Airbus assessed all wing structural items of the Airbus A310 design deemed potentially susceptible to WFD. The top [wing] skin stringer joints at rib 19 at level of the first fastener row 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. This condition, if not corrected, could reduce the structural integrity of the wing. Prompted by the conclusion of WFD analysis, Airbus issued the SB [Service Bulletin A310–57–2108, dated November 9, 2017] to provide modification instructions. The accomplishment of this modification at the specified time will extend the life of the fastener holes in the affected area in order to reach the Limit of Validity. For the reasons described above, this [EASA] AD requires a one-time inspection of the [fastener] holes in the affected area, accomplishment of applicable corrective action(s) [contacting the manufacturer], depending on findings, and modification. 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–2018– 0906. 5593 Comments We gave the public the opportunity to participate in developing this final rule. We received no comments on the NPRM or on the determination of the cost to the public. Conclusion We reviewed the relevant data and determined that air safety and the public interest require adopting this final rule as proposed, except for minor editorial changes. We have determined that these minor changes: • Are consistent with the intent that was proposed in the NPRM for addressing the unsafe condition; and • Do not add any additional burden upon the public than was already proposed in the NPRM. Related Service Information Under 1 CFR Part 51 Airbus has issued Service Bulletin A310–57–2108, dated November 9, 2017. This service information describes procedures for accomplishing a rototest inspection of the fastener holes in the affected areas and repair if necessary, and modifying the fastener holes. 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 14 airplanes of U.S. registry. We estimate the following costs to comply with this AD: ESTIMATED COSTS FOR REQUIRED ACTIONS Labor cost Parts cost Cost per product Cost on U.S. operators 43 work-hours × $85 per hour = $3,655 ..................................................................................... $0 $3,655 $51,170 We have received no definitive data that would enable us to provide cost estimates for the on-condition actions specified in this AD. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. Subtitle VII: Aviation Programs, describes in more detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III, Section 44701: VerDate Sep<11>2014 15:50 Feb 21, 2019 Jkt 247001 ‘‘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 PO 00000 Frm 00011 Fmt 4700 Sfmt 4700 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 and associated appliances to the Director of the System Oversight Division. Regulatory Findings 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 E:\FR\FM\22FER1.SGM 22FER1 5594 Federal Register / Vol. 84, No. 36 / Friday, February 22, 2019 / Rules and Regulations List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 (f) Compliance [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): ■ 2019–03–09 Airbus SAS: Amendment 39– 19561; Docket No. FAA–2018–0906; Product Identifier 2018–NM–122–AD. (a) Effective Date This AD is effective March 29, 2019. (b) Affected ADs None. (c) Applicability This AD applies to all Airbus SAS Model A310–304, –322, –324, and –325 airplanes, certificated in any category. (d) Subject Air Transport Association (ATA) of America Code 57, Wings. (e) Reason This AD was prompted by an evaluation by the design approval holder (DAH) indicating (i) Corrective Actions (k) Other FAA AD Provisions If, during the inspection required by paragraph (h) of this AD, any discrepancy (i.e., cracking or discrepant hole diameter) or existing repair is detected, before further flight, obtain corrective actions approved by the Manager, International Section, Transport Standards Branch, FAA; or the European Aviation Safety Agency (EASA); or Airbus SAS’s EASA Design Organization Approval (DOA); and accomplish the corrective actions within the compliance time specified therein. If approved by the DOA, the approval must include the DOA-authorized signature. The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International 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 (j) Modification If, during the inspection required by paragraph (h) of this AD, no existing repair or discrepancy is detected, before further flight, modify the fastener holes in accordance with the Accomplishment Instructions of Airbus Service Bulletin A310– 57–2108, dated November 9, 2017. VerDate Sep<11>2014 15:50 Feb 21, 2019 Jkt 247001 PO 00000 Frm 00012 Fmt 4700 that top wing skin stringer joints at rib 19 are subject to widespread fatigue damage (WFD). We are issuing this AD to address any cracking of the top wing skin stringer joints at rib 19, which could result in reduced structural integrity of the wing. Sfmt 4700 Comply with this AD within the compliance times specified, unless already done. (g) Definitions (1) The affected areas are defined as the top wing skin stringers, 9 to 15, at the stringer joints, outboard of rib 19, on both wings. (2) The average flight time (AFT) is defined as flight hours (FH) divided by flight cycles (FC) accumulated by an individual airplane since the airplane’s first flight, specified in hours and hundredths of an hour. Refer to the Airbus A310 Maintenance Review Board Report Section D2 for guidance on determining the AFT. (h) Inspection Within the applicable compliance times specified in figure 1 to paragraph (h) of this AD, accomplish a rototest inspection of the fastener holes in the affected areas in accordance with the Accomplishment Instructions of Airbus Service Bulletin A310– 57–2108, dated November 9, 2017. actions from a manufacturer, the action must be accomplished using a method approved by the Manager, International Section, Transport Standards Branch, FAA; or the EASA; or Airbus SAS’s EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature. (3) Required for Compliance (RC): 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. E:\FR\FM\22FER1.SGM 22FER1 ER22FE19.015</GPH> 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. Federal Register / Vol. 84, No. 36 / Friday, February 22, 2019 / Rules and Regulations (l) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA AD 2018–0174, dated August 14, 2018, 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–2018–0906. (2) For more information about this AD, contact Dan Rodina, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone and fax 206– 231–3225. (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 Issued in Des Moines, Washington, on February 7, 2019. Michael Kaszycki, Acting Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2019–02925 Filed 2–21–19; 8:45 am] BILLING CODE 4910–13–P VerDate Sep<11>2014 15:50 Feb 21, 2019 Jkt 247001 DEPARTMENT OF TRANSPORTATION Examining the AD Docket Federal Aviation Administration You may examine the AD docket on the internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2018– 0907; or in person at Docket Operations 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 Docket Operations (phone: 800–647–5527) is 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, 2200 South 216th St., Des Moines, WA 98198; telephone and fax 206–231–3225. SUPPLEMENTARY INFORMATION: 14 CFR Part 39 [Docket No. FAA–2018–0907; Product Identifier 2018–NM–118–AD; Amendment 39–19562; AD 2019–03–10] RIN 2120–AA64 Airworthiness Directives; Airbus SAS Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: We are superseding Airworthiness Directive (AD) 2017–07– 05, which applied to all Airbus SAS Model A300 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). AD 2017–07–05 required repetitive detailed visual inspections of the main landing gear (MLG) leg components and replacement of the MLG leg if cracked components are found. This AD retains the requirements of AD 2017–07–05 and removes the credit for doing an MLG overhaul in lieu of the initial inspection of the MLG leg components. This AD was prompted by further investigation after AD 2017–07– 05 was issued, which revealed that overhaul of the MLG does not alleviate the need for inspecting the MLG hinge arm/barrel pin for cracking. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective March 29, 2019. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of March 29, 2019. ADDRESSES: For service information identified in this final rule, contact Airbus SAS, Airworthiness Office— EAW, Rond-Point Emile Dewoitine No: 2, 31700 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email account.airwortheas@airbus.com; internet https:// www.airbus.com. You may view this referenced service information at the FAA, Transport Standards Branch, 2200 South 216th St., Des Moines, WA. For information on the availability of this material at the FAA, call 206–231–3195. It is also available on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA–2018– 0907. SUMMARY: (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 A310–57–2108, dated November 9, 2017. (ii) [Reserved] (3) For service information identified in this AD, contact Airbus SAS, Airworthiness Office—EAW, Rond-Point Emile Dewoitine No: 2, 31700 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. (4) You may view this service information at the FAA, Transport Standards Branch, 2200 South 216th St., Des Moines, WA. For information on the availability of this material at the FAA, call 206–231–3195. (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. 5595 PO 00000 Frm 00013 Fmt 4700 Sfmt 4700 Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 2017–07–05, Amendment 39–18843 (82 FR 16101, April 3, 2017) (‘‘AD 2017–07–05’’). AD 2017–07–05 applied to all Airbus SAS Model A300 series airplanes; and Model A300–600 series airplanes. The NPRM published in the Federal Register on November 6, 2018 (83 FR 55498). The NPRM was prompted by further investigation after AD 2017–07–05 was issued, which revealed that overhaul of the MLG does not alleviate the need for inspecting the MLG hinge arm/barrel pin for cracking. The NPRM proposed to retain the requirements of AD 2017–07– 05 and remove the credit for doing an MLG overhaul in lieu of the initial inspection of the MLG leg components. We are issuing this AD to address cracking of certain components in the MLG leg, which could result in an MLG collapse, and consequent damage to the airplane and injury to the airplane occupants. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA AD 2018–0170, dated August 6, 2018 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for all Airbus SAS Model A300 series airplanes; and Model A300–600 series airplanes. The MCAI states: Two cases were reported of finding a cracked MLG hinge arm/barrel pin, one was discovered in service during a maintenance E:\FR\FM\22FER1.SGM 22FER1

Agencies

[Federal Register Volume 84, Number 36 (Friday, February 22, 2019)]
[Rules and Regulations]
[Pages 5592-5595]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2019-02925]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2018-0906; Product Identifier 2018-NM-122-AD; Amendment 
39-19561; AD 2019-03-09]
RIN 2120-AA64


Airworthiness Directives; Airbus SAS Airplanes

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

ACTION: Final rule.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for all 
Airbus SAS Model A310-304, -322, -324, and -325 airplanes. This AD was 
prompted by an evaluation by the design approval holder (DAH) 
indicating that certain wing skin stringer joints are subject to 
widespread fatigue damage (WFD). This AD requires a rototest inspection 
of the fastener holes in the affected areas and repair if necessary, 
and modifying the fastener holes. We are issuing this AD to address the 
unsafe condition on these products.

DATES: This AD is effective March 29, 2019.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of March 29, 
2019.

ADDRESSES: For service information identified in this final rule, 
contact Airbus SAS, Airworthiness Office--EAW, Rond-Point Emile 
Dewoitine No: 2, 31700 Blagnac Cedex, France; telephone +33 5 61 93 36 
96; fax +33 5 61 93 44 51; email account.airworth-eas@airbus.com; 
internet https://www.airbus.com. You may view this service information 
at the FAA, Transport Standards Branch, 2200 South 216th St., Des 
Moines, WA. For information on the availability of this material at the 
FAA, call 206-231-3195. It is also available on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2018-
0906.

Examining the AD Docket

    You may examine the AD docket on the internet at https://

[[Page 5593]]

www.regulations.gov by searching for and locating Docket No. FAA-2018-
0906; or in person at Docket Operations 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 Docket Operations (phone: 800-647-
5527) is 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, 2200 South 
216th St., Des Moines, WA 98198; telephone and fax 206-231-3225.

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 all Airbus SAS Model A310-
304, -322, -324, and -325 airplanes. The NPRM published in the Federal 
Register on November 5, 2018 (83 FR 55294). The NPRM was prompted by an 
evaluation by the DAH indicating that certain wing skin stringer joints 
are subject to WFD. The NPRM proposed to require a rototest inspection 
of the fastener holes in the affected areas and repair if necessary, 
and modifying the fastener holes.
    We are issuing this AD to address any cracking of the top wing skin 
stringer joints at rib 19, which could result in reduced 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 
2018-0174, dated August 14, 2018 (referred to after this as the 
Mandatory Continuing Airworthiness Information, or ``the MCAI''), to 
correct an unsafe condition for all Airbus SAS Model A310-304, -322, -
324, and -325 airplanes. The MCAI states:

    In response to US 14 CFR part 26 concerning Widespread Fatigue 
Damage (WFD), Airbus assessed all wing structural items of the 
Airbus A310 design deemed potentially susceptible to WFD. The top 
[wing] skin stringer joints at rib 19 at level of the first fastener 
row 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.
    This condition, if not corrected, could reduce the structural 
integrity of the wing.
    Prompted by the conclusion of WFD analysis, Airbus issued the SB 
[Service Bulletin A310-57-2108, dated November 9, 2017] to provide 
modification instructions. The accomplishment of this modification 
at the specified time will extend the life of the fastener holes in 
the affected area in order to reach the Limit of Validity.
    For the reasons described above, this [EASA] AD requires a one-
time inspection of the [fastener] holes in the affected area, 
accomplishment of applicable corrective action(s) [contacting the 
manufacturer], depending on findings, and modification.

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-2018-
0906.

Comments

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

Conclusion

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

Related Service Information Under 1 CFR Part 51

    Airbus has issued Service Bulletin A310-57-2108, dated November 9, 
2017. This service information describes procedures for accomplishing a 
rototest inspection of the fastener holes in the affected areas and 
repair if necessary, and modifying the fastener holes.
    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 14 airplanes of U.S. registry. We 
estimate the following costs to comply with this AD:

                                      Estimated Costs for Required Actions
----------------------------------------------------------------------------------------------------------------
                                                                                    Cost per       Cost on U.S.
                          Labor cost                              Parts cost        product         operators
----------------------------------------------------------------------------------------------------------------
43 work-hours x $85 per hour = $3,655........................              $0           $3,655          $51,170
----------------------------------------------------------------------------------------------------------------

    We have received no definitive data that would enable us to provide 
cost estimates for the on-condition actions specified in this AD.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. Subtitle VII: Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
Subtitle VII, Part A, Subpart III, Section 44701: ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.
    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 and 
associated appliances to the Director of the System Oversight Division.

Regulatory Findings

    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

[[Page 5594]]

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):

2019-03-09 Airbus SAS: Amendment 39-19561; Docket No. FAA-2018-0906; 
Product Identifier 2018-NM-122-AD.

(a) Effective Date

    This AD is effective March 29, 2019.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to all Airbus SAS Model A310-304, -322, -324, 
and -325 airplanes, certificated in any category.

(d) Subject

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

(e) Reason

    This AD was prompted by an evaluation by the design approval 
holder (DAH) indicating that top wing skin stringer joints at rib 19 
are subject to widespread fatigue damage (WFD). We are issuing this 
AD to address any cracking of the top wing skin stringer joints at 
rib 19, which could result in reduced structural integrity of the 
wing.

(f) Compliance

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

(g) Definitions

    (1) The affected areas are defined as the top wing skin 
stringers, 9 to 15, at the stringer joints, outboard of rib 19, on 
both wings.
    (2) The average flight time (AFT) is defined as flight hours 
(FH) divided by flight cycles (FC) accumulated by an individual 
airplane since the airplane's first flight, specified in hours and 
hundredths of an hour. Refer to the Airbus A310 Maintenance Review 
Board Report Section D2 for guidance on determining the AFT.

(h) Inspection

    Within the applicable compliance times specified in figure 1 to 
paragraph (h) of this AD, accomplish a rototest inspection of the 
fastener holes in the affected areas in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A310-57-2108, 
dated November 9, 2017.
[GRAPHIC] [TIFF OMITTED] TR22FE19.015

(i) Corrective Actions

    If, during the inspection required by paragraph (h) of this AD, 
any discrepancy (i.e., cracking or discrepant hole diameter) or 
existing repair is detected, before further flight, obtain 
corrective actions approved by the Manager, International Section, 
Transport Standards Branch, FAA; or the European Aviation Safety 
Agency (EASA); or Airbus SAS's EASA Design Organization Approval 
(DOA); and accomplish the corrective actions within the compliance 
time specified therein. If approved by the DOA, the approval must 
include the DOA-authorized signature.

(j) Modification

    If, during the inspection required by paragraph (h) of this AD, 
no existing repair or discrepancy is detected, before further 
flight, modify the fastener holes in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A310-57-2108, 
dated November 9, 2017.

(k) Other FAA AD Provisions

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

[[Page 5595]]

(l) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA AD 2018-0174, dated August 14, 2018, 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-2018-0906.
    (2) For more information about this AD, contact Dan Rodina, 
Aerospace Engineer, International Section, Transport Standards 
Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone 
and fax 206-231-3225.
    (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 A310-57-2108, dated November 9, 
2017.
    (ii) [Reserved]
    (3) For service information identified in this AD, contact 
Airbus SAS, Airworthiness Office--EAW, Rond-Point Emile Dewoitine 
No: 2, 31700 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.
    (4) You may view this service information at the FAA, Transport 
Standards Branch, 2200 South 216th St., Des Moines, WA. For 
information on the availability of this material at the FAA, call 
206-231-3195.
    (5) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, call 202-741-6030, or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Des Moines, Washington, on February 7, 2019.
Michael Kaszycki,
Acting Director, System Oversight Division, Aircraft Certification 
Service.
[FR Doc. 2019-02925 Filed 2-21-19; 8:45 am]
 BILLING CODE 4910-13-P
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