Airworthiness Directives; Airbus Airplanes, 91060-91062 [2016-29676]

Download as PDF 91060 Federal Register / Vol. 81, No. 242 / Friday, December 16, 2016 / Proposed Rules of this AD: Incorporate ModSum 4–903234 to modify installed Jetway Compatible Handrail Stowage Bracket, in accordance with PART A3 of the Accomplishment Instructions of Bombardier Service Bulletin 84–52–79, Revision C, dated February 2, 2016. Incorporating ModSum 4–903234 terminates the actions required by paragraph (g) of this AD. (i) Credit for Previous Actions This paragraph provides credit for actions required by paragraph (g) of this AD, if those actions were performed before the effective date of this AD using the service information identified in paragraph (i)(1), (i)(2), or (i)(3) of this AD. (1) Bombardier Service Bulletin 84–52–79, dated May 1, 2014. (2) Bombardier Service Bulletin 84–52–79, Revision A, dated November 18, 2014. (3) Bombardier Service Bulletin 84–52–79, Revision B, dated April 8, 2015. asabaliauskas on DSK3SPTVN1PROD with PROPOSALS (j) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, New York Aircraft Certification Office (ACO), ANE–170, 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 ACO, send it to ATTN: Program Manager, Continuing Operational Safety, FAA, New York ACO, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516–228–7300; fax 516–794–5531. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/ certificate holding district office. The AMOC approval letter must specifically reference this AD. (2) Contacting the Manufacturer: For any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, New York ACO, ANE–170, FAA; or Transport Canada Civil Aviation (TCCA); or Bombardier, Inc.’s TCCA Design Approval Organization (DAO). If approved by the DAO, the approval must include the DAO-authorized signature. (k) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) Canadian Airworthiness Directive CF–2015–02, dated January 27, 2015, for related information. This MCAI may be found in the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA–2016–9438. (2) For service information identified in this NPRM, contact Bombardier, Inc., QSeries Technical Help Desk, 123 Garratt Boulevard, Toronto, Ontario M3K 1Y5, Canada; telephone 416–375–4000; fax 416– 375–4539; email thd.qseries@ aero.bombardier.com; Internet https:// www.bombardier.com. You may view this referenced service information at the FAA, VerDate Sep<11>2014 18:25 Dec 15, 2016 Jkt 241001 Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. Issued in Renton, Washington, on December 2, 2016. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016–29671 Filed 12–15–16; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2016–9498; Directorate Identifier 2016–NM–105–AD] RIN 2120–AA64 Airworthiness Directives; Airbus Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for all Airbus Model A321 series airplanes. This proposed AD was prompted by a determination from fatigue testing on the Model A321 airframe that cracks could develop in the cabin floor beam junction at certain fuselage frame locations. This proposed AD would require repetitive inspections for cracking in the cabin floor beam junction at certain fuselage frame locations, and repair if necessary. We are proposing this AD to address the unsafe condition on these products. DATES: We must receive comments on this proposed AD by January 30, 2017. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods: • Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. • Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this NPRM, contact Airbus, Airworthiness Office—EIAS, 1 Rond Point Maurice Bellonte, 31707 Blagnac SUMMARY: PO 00000 Frm 00012 Fmt 4702 Sfmt 4702 Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email account.airworth-eas@airbus.com; Internet https://www.airbus.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. Examining the AD Docket You may examine the AD docket on the Internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2016– 9498; 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 proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone 800–647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–1405; fax 425–227–1149. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2016–9498; Directorate Identifier 2016–NM–105–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD based on those comments. We will post all comments we receive, without change, to https:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2016–0105, dated June 6, 2016 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe E:\FR\FM\16DEP1.SGM 16DEP1 Federal Register / Vol. 81, No. 242 / Friday, December 16, 2016 / Proposed Rules condition on all Airbus Model A321 series airplanes. The MCAI states: Following the results of a new full scale fatigue test campaign on the A321 airframe in the context of the A321 extended service goal, it was identified that cracks could develop in the cabin floor beam junctions at fuselage frame (FR) 35.1 and FR 35.2, on both left hand (LH) and right hand (RH) sides, also on aeroplanes operated in the context of design service goal. This condition, if not detected and corrected, could reduce the structural integrity of the fuselage. Prompted by these findings, Airbus developed an inspection programme, published in Service Bulletin (SB) A320–53– 1317, SB A320–53–1318, SB A320–53–1319, and SB A320–53–1320, each containing instructions for a different location. For the reasons described above, this [EASA] AD requires repetitive detailed inspections (DET) of the affected cabin floor beam junctions and [for cracking], depending on findings, accomplishment of a repair. This [EASA] AD is considered an interim action, pending development of a permanent solution. * * * * * You may examine the MCAI in the AD docket on the Internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2016– 9498. Related Service Information Under 1 CFR Part 51 Airbus has issued the following service information, which describes procedures for inspections for cracking on the frame to cabin floor beam junction at certain fuselage frame locations, and repairs. • Airbus Service Bulletin A320–53– 1317, dated December 15, 2015 (FR 35.1 on the right-hand side). • Airbus Service Bulletin A320–53– 1318, dated October 9, 2015 (FR 35.1 on the left-hand side). • Airbus Service Bulletin A320–53– 1319, dated October 9, 2015 (FR 35.2 on the right-hand side). • Airbus Service Bulletin A320–53– 1320, dated October 9, 2015 (FR 35.2 on the left-hand side). This service information is reasonably available because the interested parties 91061 have access to it through their normal course of business or by the means identified in the ADDRESSES section. FAA’s Determination and Requirements of This Proposed AD This product has been approved by the aviation authority of another country, and is approved for operation in the United States. Pursuant to our bilateral agreement with the State of Design Authority, we have been notified of the unsafe condition described in the MCAI and service information referenced above. We are proposing this AD because we evaluated all pertinent information and determined an unsafe condition exists and is likely to exist or develop on other products of the same type design. Costs of Compliance We estimate that this proposed AD affects 175 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: ESTIMATED COSTS Action Labor cost Inspection ............... 6 work-hours × $85 per hour = $510 per inspection cycle. asabaliauskas on DSK3SPTVN1PROD with PROPOSALS We have received no definitive data that would enable us to provide cost estimates for the on-condition actions specified in this proposed AD. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. ‘‘Subtitle VII: Aviation Programs,’’ describes in more detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in ‘‘Subtitle VII, Part A, Subpart III, Section 44701: General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We determined that this proposed AD would not have federalism implications VerDate Sep<11>2014 18:25 Dec 15, 2016 Jkt 241001 Parts cost Cost per product $0 $510 per inspection cycle ........... under Executive Order 13132. This proposed AD would 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 this proposed regulation: 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. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PO 00000 Frm 00013 Fmt 4702 Cost on U.S. operators Sfmt 4702 $89,250 per inspection cycle. PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): ■ Airbus: Docket No. FAA–2016–9498; Directorate Identifier 2016–NM–105–AD. (a) Comments Due Date We must receive comments by January 30, 2017. (b) Affected ADs None. (c) Applicability This AD applies to Airbus Model A321– 111, –112, –131, –211, –212, –213, –231, and –232 airplanes, certificated in any category, all manufacturer serial numbers. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Reason This AD was prompted by a determination from fatigue testing on the Model A321 airframe that cracks could develop in the E:\FR\FM\16DEP1.SGM 16DEP1 91062 Federal Register / Vol. 81, No. 242 / Friday, December 16, 2016 / Proposed Rules cabin floor beam junction at certain fuselage frame locations. We are issuing this AD to detect and correct cracking in the cabin floor beam junction at certain fuselage frame locations, which could result in reduced structural integrity of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Repetitive Inspections Before exceeding 36,900 total flight cycles since first flight of the airplane, or within 2,100 flight cycles after the effective date of this AD, whichever occurs later: Do a detailed inspection for cracking of the frame to cabin floor beam junction on the aft and forward sides at frame (FR) 35.1 and FR 35.2 on the left-hand and right-hand sides, in accordance with the Accomplishment Instructions of the Airbus service information specified in paragraphs (g)(1), (g)(2), (g)(3), and (g)(4) of this AD. Repeat the inspection of the frame to cabin floor beam junction on the aft and forward sides at FR 35.1 and FR 35.2 on the left-hand and right-hand sides thereafter at intervals not to exceed 15,300 flight cycles. (1) Airbus Service Bulletin A320–53–1317, dated December 15, 2015 (FR 35.1 right-hand side). (2) Airbus Service Bulletin A320–53–1318, dated October 9, 2015 (FR 35.1 left-hand side). (3) Airbus Service Bulletin A320–53–1319, dated October 9, 2015 (FR 35.2 right-hand side). (4) Airbus Service Bulletin A320–53–1320, dated October 9, 2015 (FR 35.2 left-hand side). asabaliauskas on DSK3SPTVN1PROD with PROPOSALS (h) Repair If any crack is found during any inspection required by paragraph (g) of this AD: Before further flight, repair using a method approved by the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA); or Airbus’s EASA Design Organization Approval (DOA). Although the service information specified in paragraph (g) of this AD specifies to contact Airbus for repair instructions, and specifies that action as ‘‘RC’’ (Required for Compliance), this AD requires repair as specified in this paragraph. Repair of an airplane as required by this paragraph does not constitute terminating action for the repetitive actions required by paragraph (g) of this AD, unless specified otherwise in the instructions provided by the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA; or EASA; or Airbus’s EASA DOA. (i) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your VerDate Sep<11>2014 18:25 Dec 15, 2016 Jkt 241001 request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the International Branch, send it to ATTN: Sanjay Ralhan, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–1405; fax 425–227–1149. Information may be emailed to: 9-ANM-116AMOC-REQUESTS@faa.gov. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. (2) Contacting the Manufacturer: For any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, International Branch, ANM– 116, Transport Airplane Directorate, FAA; or EASA; or Airbus’s EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature. (3) Required for Compliance (RC): Except as required by paragraph (h) 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. (j) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2016–0105, dated June 6, 2016, for related information. This MCAI may be found in the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA– 2016–9498. (2) For service information identified in this AD, contact Airbus, Airworthiness Office—EIAS, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email account.airworth-eas@ airbus.com; Internet https://www.airbus.com. You may view this service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. Issued in Renton, Washington, on December 2, 2016. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016–29676 Filed 12–15–16; 8:45 am] BILLING CODE 4910–13–P PO 00000 Frm 00014 Fmt 4702 Sfmt 4702 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2015–8428; Directorate Identifier 2014–NM–032–AD] RIN 2120–AA64 Airworthiness Directives; Airbus Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Supplemental notice of proposed rulemaking (SNPRM); reopening of comment period. AGENCY: We are revising an earlier proposal to supersede Airworthiness Directive (AD) 2011–17–09 for all Airbus Model A330–200, –200 Freighter, and –300 series airplanes; and AD 2012–25–12 for all Airbus Model A330–200 and –300 series airplanes. The notice of proposed rulemaking (NPRM) proposed to require revising the maintenance or inspection program, as applicable, to incorporate new or revised airworthiness limitation requirements. The NPRM was prompted by revisions to certain airworthiness limitations items (ALI) documents, which specify more restrictive instructions and/or airworthiness limitations. This action revises the NPRM by proposing to require revising the maintenance or inspection program, as applicable, to incorporate more restrictive, instructions and/or airworthiness limitations that the manufacturer has recently issued. We are proposing this AD to address the unsafe condition on these products. DATES: We must receive comments on this SNPRM by January 30, 2017. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods: • Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. • Hand Delivery: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For Airbus service information identified in this SNPRM, contact SUMMARY: E:\FR\FM\16DEP1.SGM 16DEP1

Agencies

[Federal Register Volume 81, Number 242 (Friday, December 16, 2016)]
[Proposed Rules]
[Pages 91060-91062]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-29676]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-9498; Directorate Identifier 2016-NM-105-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to adopt a new airworthiness directive (AD) for all 
Airbus Model A321 series airplanes. This proposed AD was prompted by a 
determination from fatigue testing on the Model A321 airframe that 
cracks could develop in the cabin floor beam junction at certain 
fuselage frame locations. This proposed AD would require repetitive 
inspections for cracking in the cabin floor beam junction at certain 
fuselage frame locations, and repair if necessary. We are proposing 
this AD to address the unsafe condition on these products.

DATES: We must receive comments on this proposed AD by January 30, 
2017.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590.
     Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this NPRM, contact Airbus, 
Airworthiness Office--EIAS, 1 Rond Point Maurice Bellonte, 31707 
Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 
51; email account.airworth-eas@airbus.com; Internet https://www.airbus.com. You may view this referenced service information at the 
FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. 
For information on the availability of this material at the FAA, call 
425-227-1221.

Examining the AD Docket

    You may examine the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2016-
9498; 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 proposed AD, the regulatory evaluation, any comments 
received, and other information. The street address for the Docket 
Operations office (telephone 800-647-5527) is in the ADDRESSES section. 
Comments will be available in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1405; 
fax 425-227-1149.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2016-9498; 
Directorate Identifier 2016-NM-105-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD based on those comments.
    We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2016-0105, dated June 6, 2016 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe

[[Page 91061]]

condition on all Airbus Model A321 series airplanes. The MCAI states:

    Following the results of a new full scale fatigue test campaign 
on the A321 airframe in the context of the A321 extended service 
goal, it was identified that cracks could develop in the cabin floor 
beam junctions at fuselage frame (FR) 35.1 and FR 35.2, on both left 
hand (LH) and right hand (RH) sides, also on aeroplanes operated in 
the context of design service goal.
    This condition, if not detected and corrected, could reduce the 
structural integrity of the fuselage.
    Prompted by these findings, Airbus developed an inspection 
programme, published in Service Bulletin (SB) A320-53-1317, SB A320-
53-1318, SB A320-53-1319, and SB A320-53-1320, each containing 
instructions for a different location.
    For the reasons described above, this [EASA] AD requires 
repetitive detailed inspections (DET) of the affected cabin floor 
beam junctions and [for cracking], depending on findings, 
accomplishment of a repair.
    This [EASA] AD is considered an interim action, pending 
development of a permanent solution.
* * * * *

    You may examine the MCAI in the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2016-
9498.

Related Service Information Under 1 CFR Part 51

    Airbus has issued the following service information, which 
describes procedures for inspections for cracking on the frame to cabin 
floor beam junction at certain fuselage frame locations, and repairs.
     Airbus Service Bulletin A320-53-1317, dated December 15, 
2015 (FR 35.1 on the right-hand side).
     Airbus Service Bulletin A320-53-1318, dated October 9, 
2015 (FR 35.1 on the left-hand side).
     Airbus Service Bulletin A320-53-1319, dated October 9, 
2015 (FR 35.2 on the right-hand side).
     Airbus Service Bulletin A320-53-1320, dated October 9, 
2015 (FR 35.2 on the left-hand side).
    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.

FAA's Determination and Requirements of This Proposed AD

    This product has been approved by the aviation authority of another 
country, and is approved for operation in the United States. Pursuant 
to our bilateral agreement with the State of Design Authority, we have 
been notified of the unsafe condition described in the MCAI and service 
information referenced above. We are proposing this AD because we 
evaluated all pertinent information and determined an unsafe condition 
exists and is likely to exist or develop on other products of the same 
type design.

Costs of Compliance

    We estimate that this proposed AD affects 175 airplanes of U.S. 
registry.
    We estimate the following costs to comply with this proposed AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                 Cost on U.S.
              Action                    Labor cost        Parts cost      Cost per product        operators
----------------------------------------------------------------------------------------------------------------
Inspection.......................  6 work-hours x $85               $0  $510 per inspection  $89,250 per
                                    per hour = $510                      cycle.               inspection cycle.
                                    per inspection
                                    cycle.
----------------------------------------------------------------------------------------------------------------

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

Authority for This Rulemaking

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

Regulatory Findings

    We determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would 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 this proposed 
regulation:
    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.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 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):

Airbus: Docket No. FAA-2016-9498; Directorate Identifier 2016-NM-
105-AD.

(a) Comments Due Date

    We must receive comments by January 30, 2017.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Airbus Model A321-111, -112, -131, -211, -
212, -213, -231, and -232 airplanes, certificated in any category, 
all manufacturer serial numbers.

(d) Subject

    Air Transport Association (ATA) of America Code 53, Fuselage.

(e) Reason

    This AD was prompted by a determination from fatigue testing on 
the Model A321 airframe that cracks could develop in the

[[Page 91062]]

cabin floor beam junction at certain fuselage frame locations. We 
are issuing this AD to detect and correct cracking in the cabin 
floor beam junction at certain fuselage frame locations, which could 
result in reduced structural integrity of the airplane.

(f) Compliance

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

(g) Repetitive Inspections

    Before exceeding 36,900 total flight cycles since first flight 
of the airplane, or within 2,100 flight cycles after the effective 
date of this AD, whichever occurs later: Do a detailed inspection 
for cracking of the frame to cabin floor beam junction on the aft 
and forward sides at frame (FR) 35.1 and FR 35.2 on the left-hand 
and right-hand sides, in accordance with the Accomplishment 
Instructions of the Airbus service information specified in 
paragraphs (g)(1), (g)(2), (g)(3), and (g)(4) of this AD. Repeat the 
inspection of the frame to cabin floor beam junction on the aft and 
forward sides at FR 35.1 and FR 35.2 on the left-hand and right-hand 
sides thereafter at intervals not to exceed 15,300 flight cycles.
    (1) Airbus Service Bulletin A320-53-1317, dated December 15, 
2015 (FR 35.1 right-hand side).
    (2) Airbus Service Bulletin A320-53-1318, dated October 9, 2015 
(FR 35.1 left-hand side).
    (3) Airbus Service Bulletin A320-53-1319, dated October 9, 2015 
(FR 35.2 right-hand side).
    (4) Airbus Service Bulletin A320-53-1320, dated October 9, 2015 
(FR 35.2 left-hand side).

(h) Repair

    If any crack is found during any inspection required by 
paragraph (g) of this AD: Before further flight, repair using a 
method approved by the Manager, International Branch, ANM-116, 
Transport Airplane Directorate, FAA; or the European Aviation Safety 
Agency (EASA); or Airbus's EASA Design Organization Approval (DOA). 
Although the service information specified in paragraph (g) of this 
AD specifies to contact Airbus for repair instructions, and 
specifies that action as ``RC'' (Required for Compliance), this AD 
requires repair as specified in this paragraph. Repair of an 
airplane as required by this paragraph does not constitute 
terminating action for the repetitive actions required by paragraph 
(g) of this AD, unless specified otherwise in the instructions 
provided by the Manager, International Branch, ANM-116, Transport 
Airplane Directorate, FAA; or EASA; or Airbus's EASA DOA.

(i) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
has the authority to approve AMOCs for this AD, if requested using 
the procedures found in 14 CFR 39.19. In accordance with 14 CFR 
39.19, send your request to your principal inspector or local Flight 
Standards District Office, as appropriate. If sending information 
directly to the International Branch, send it to ATTN: Sanjay 
Ralhan, Aerospace Engineer, International Branch, ANM-116, Transport 
Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-
3356; telephone 425-227-1405; fax 425-227-1149. 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 
Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA; or 
Airbus's EASA DOA. If approved by the DOA, the approval must include 
the DOA-authorized signature.
    (3) Required for Compliance (RC): Except as required by 
paragraph (h) 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.

(j) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2016-0105, dated June 6, 2016, 
for related information. This MCAI may be found in the AD docket on 
the Internet at https://www.regulations.gov by searching for and 
locating Docket No. FAA-2016-9498.
    (2) For service information identified in this AD, contact 
Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice Bellonte, 
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 
61 93 44 51; email account.airworth-eas@airbus.com; Internet https://www.airbus.com. You may view this service information at the FAA, 
Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. 
For information on the availability of this material at the FAA, 
call 425-227-1221.

    Issued in Renton, Washington, on December 2, 2016.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-29676 Filed 12-15-16; 8:45 am]
 BILLING CODE 4910-13-P