[Federal Register Volume 82, Number 33 (Tuesday, February 21, 2017)]
[Proposed Rules]
[Pages 11162-11164]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-03031]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-9571; Directorate Identifier 2016-NM-139-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 
full scale fatigue test campaign on these airplanes in the context of 
the extended service goal. This proposed AD would require inspections 
of the affected 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 April 7, 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 [email protected]; 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-
9571; 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-2016-9571; 
Directorate Identifier 2016-NM-139-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 2016-0146, dated July 20, 2016 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for 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 on the fastener 
holes of frame (FR) 35.1, FR 35.2, and FR 35.3 between stringers 
(STR) 29 and STR 32 and at the FR 35.2 to Slidebox junction (Triform 
fitting), both left hand (LH) and right hand (RH) sides.
    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) A320-53-1308, SB A320-53-1309, SB A320-53-1310, SB 
A320-53-1311, SB A320-53-1312 and SB A320-53-1313, each containing 
instructions for a different location. For the reasons described 
above, this [EASA] AD requires repetitive special detailed 
(rototest) inspections (SDI) of the affected frame locations and, 
depending on findings, accomplishment of a repair.
    This [EASA] AD is considered an interim action, pending the 
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-
9571.

[[Page 11163]]

Related Service Information Under 1 CFR Part 51

    We reviewed the following Airbus service information. This service 
information describes procedures for repetitive rototest inspections 
for cracking of the affected frame locations, and contacting Airbus for 
repair instructions. These service bulletins are distinct because they 
apply to different frame locations.
     Airbus Service Bulletin A320-53-1308, dated November 4, 
2015.
     Airbus Service Bulletin A320-53-1309, dated November 4, 
2015.
     Airbus Service Bulletin A320-53-1310, dated November 4, 
2015.
     Airbus Service Bulletin A320-53-1311, dated November 4, 
2015.
     Airbus Service Bulletin A320-53-1312, dated November 4, 
2015.
     Airbus Service Bulletin A320-53-1313, dated November 4, 
2015.
    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 176 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.....................  54 work-hours x $85     $1,070 per         $5,660 per         $996,160 per
                                  per hour = $4,590 per   inspection cycle.  inspection cycle.  inspection
                                  inspection cycle.                                             cycle.
----------------------------------------------------------------------------------------------------------------

    We have no way to estimate the costs to do any necessary repairs 
that would be required based on the results of the proposed inspection. 
We have no way of determining the number of airplanes that might need 
these repairs.

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-2016-9571; Directorate Identifier 2016-NM-
139-AD.

(a) Comments Due Date

    We must receive comments by April 7, 2017.

(b) Affected ADs

    None.

(c) Applicability

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

(d) Subject

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

(e) Reason

    This AD was prompted by a full scale fatigue test campaign on 
Airbus Model A321 series airplanes in the context of the extended 
service goal. It was determined that cracks could develop on the 
fastener holes of certain frames on the left-hand (LH) and right-
hand (RH) sides of the affected airplanes. We are issuing this AD to 
detect and correct cracking of the fastener holes at certain frame 
locations, which could result in reduced structural integrity of the 
fuselage.

(f) Compliance

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

(g) Repetitive Inspections of the Frames, Stringers, and Slidebox 
Junctions

    At the applicable time specified in table 1 to paragraph (g) of 
this AD, do a rototest inspection for cracking at frame (FR) 35.1, 
FR 35.2, and FR 35.3 on the LH and RH sides, in accordance with the 
Accomplishment Instructions of the Airbus service information 
specified in paragraphs (g)(1), (g)(2), (g)(3), (g)(4), (g)(5), and 
(g)(6) of this AD. Repeat the inspection thereafter at intervals not 
to exceed 5,300 flight cycles.

[[Page 11164]]

    (1) Airbus Service Bulletin A320-53-1308, dated November 4, 2015 
(FR 35.1 LH side).
    (2) Airbus Service Bulletin A320-53-1309, dated November 4, 2015 
(FR 35.1 RH side).
    (3) Airbus Service Bulletin A320-53-1310, dated November 4, 2015 
(FR 35.2 LH side).
    (4) Airbus Service Bulletin A320-53-1311, dated November 4, 2015 
(FR 35.2 RH side).
    (5) Airbus Service Bulletin A320-53-1312, dated November 4, 2015 
(FR 35.3 LH side).
    (6) Airbus Service Bulletin A320-53-1313, dated November 4, 2015 
(FR 35.3 RH side).

        Table 1 to Paragraph (g) of This AD--Inspection Threshold
------------------------------------------------------------------------
 Airplane accumulated total flight
  cycles at the effective date of              Compliance time
              this AD
------------------------------------------------------------------------
For airplanes with 18,300 total     Before exceeding 18,300 total flight
 flight cycles or less.              cycles, or within 5,300 flight
                                     cycles after the effective date of
                                     this AD, whichever occurs later.
For airplanes with more than        Before exceeding 23,600 total flight
 18,300 total flight cycles.         cycles, or within 2,100 flight
                                     cycles after the effective date of
                                     this AD, whichever occurs later.
------------------------------------------------------------------------

(h) Corrective Action

    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 inspections required by 
paragraph (g) of this AD for that airplane, unless specified 
otherwise in the repair instructions approved 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: [email protected]. 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 the 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 2016-0146, dated July 20, 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-2016-9571.
    (2) For service information identified in this AD, contact 
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 [email protected]; 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 January 11, 2017.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2017-03031 Filed 2-17-17; 8:45 am]
 BILLING CODE 4910-13-P