
[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]


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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).

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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 http://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 http://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 http://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 http://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 http://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 http://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 http://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


