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[Federal Register Volume 77, Number 89 (Tuesday, May 8, 2012)]
[Proposed Rules]
[Pages 26996-26998]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2012-11023]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2012-0427; Directorate Identifier 2011-NM-202-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 
certain Airbus Model A320-214 and-232 airplanes. This proposed AD was 
prompted by reports that medium-head fasteners were installed in lieu 
of shear-head fasteners on a certain upper panel which manufacturer 
fatigue and damage tolerance analyses demonstrated could have an affect 
on panel fatigue life. This proposed AD would require repetitive 
inspections for cracking of certain fasteners, and repairs if 
necessary. We are proposing this AD to detect and correct cracking 
which could result in the loss of structural integrity of the airplane.

DATES: We must receive comments on this proposed AD by June 22, 2012.

ADDRESSES: You may send comments 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: 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 service information identified in this proposed AD, contact 
Airbus SAS-EAW (Airworthiness Office), 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 review copies of the referenced service 
information at the FAA, Transport Airplane Directorate, 1601 Lind 
Avenue SW., Renton, Washington. 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; or in person at the Docket Operations office 
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, Washington 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-2012-0427; 
Directorate Identifier 2011-NM-202-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 Community, has issued EASA 
Airworthiness Directive 2011-0176, dated September 13, 2011 (referred 
to after this as ``the MCAI''), to correct an unsafe condition for the 
specified products. The MCAI states:

    A problem was reported during the installation of upper panels 
on Frame 35 in Airbus A320 final assembly line. Investigations 
revealed that medium head fasteners, Part Number (P/N) EN6114V3, 
were installed in lieu of shear head fasteners, P/N ASNA2657V3 and 
ASNA2043V3, which were previously used. Installation of these medium 
head fasteners leads to a deeper

[[Page 26997]]

countersink in the panel. Fatigue and damage tolerance analyses were 
performed, the results of which demonstrated that this installation 
could have a fatigue impact on two rows of fasteners between 
stringers (STGR) 5 and 6, and indicated the need for a specific 
inspection in this area.
    This condition, if not detected and corrected, could impair the 
structural integrity of the affected aeroplanes.
    For the reasons described above, this [EASA] AD requires 
repetitive special detailed [high frequency eddy current] 
inspections [for cracking] of the affected fasteners and, depending 
on findings, the accomplishment of associated corrective actions 
[repair].

You may obtain further information by examining the MCAI in the AD 
docket.

Relevant Service Information

    Airbus has issued Service Bulletin A320-53-1244, including Appendix 
1, dated March 17, 2011. The actions described in this service 
information are intended to correct the unsafe condition identified in 
the MCAI.

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

    Based on the service information, we estimate that this proposed AD 
would affect about 44 products of U.S. registry. We also estimate that 
it would take about 3 work-hours per product to comply with the basic 
requirements of this proposed AD. The average labor rate is $85 per 
work-hour. Based on these figures, we estimate the cost of the proposed 
AD on U.S. operators to be $11,220, or $255 per product.
    We have received no definitive data that would enable us to provide 
cost estimates for the on-condition actions specified in this proposed 
AD. We have no way of determining the number of products that may need 
these actions.

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.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this proposed AD and placed it in the AD docket.

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

    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]

    2. The FAA amends Sec.  39.13 by adding the following new AD:

Airbus: Docket No. FAA-2012-0427; Directorate Identifier 2011-NM-
202-AD.

(a) Comments Due Date

    We must receive comments by June 22, 2012.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Airbus Model A320-214 and -232 airplanes; 
certificated in any category; manufacturer serial numbers 3456, 
3503, 3516, 3529, 3591, 3597, 3611, 3631, 3696, 3698, 3714, 3719, 
3775, 3777, 3780, 3782, 3786, 3797, 3805, 3812, 3870, 3907, 3909, 
3913, 3922, 3929, 3946, 3953, 3975, 3979, 3991, 4010, 4012, 4014, 
4027, 4034, 4043, 4046, 4064, 4065, 4084, 4093, 4094, and 4097.

(d) Subject

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

(e) Reason

    This AD was prompted by reports that medium-head fasteners were 
installed in lieu of shear-head fasteners on a certain upper panel 
which manufacturer fatigue and damage tolerance analyses 
demonstrated could have an effect on panel fatigue life. We are 
issuing this AD to detect and correct cracking which could result in 
the loss of structural integrity of the airplane.

(f) Compliance

    You are responsible for having the actions required by this AD 
performed within the compliance times specified, unless the actions 
have already been done.

(g) Repetitive Inspection

    At the later of the times in paragraphs (g)(1) and (g)(2) of 
this AD: Do a high frequency eddy current inspection for cracking of 
the 2 rows of 6 fasteners at frame 35 between stringers 5 and 6 on 
the left and right sides, in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A320-53-1244, excluding 
Appendix 1, dated March 17, 2011. Repeat the inspection thereafter 
at intervals not to exceed 28,100 flight cycles or 56,300 flight 
hours, whichever occurs first.
    (1) Before the accumulation of 35,900 total flight cycles or 
88,100 total flight hours, whichever occurs first.
    (2) Within 30 days after the effective date of this AD.

(h) Corrective Action

    If any crack is detected during any inspection required by 
paragraph (g) of this AD: Before further flight, repair the crack 
using a method approved by either the Manager, International Branch, 
ANM-116, Transport Airplane Directorate, FAA; or the European 
Aviation Safety Agency (EASA) or its delegated agent.

(i) Other FAA AD Provisions

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

[[Page 26998]]

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, Washington 
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. The AMOC approval letter must specifically reference this 
AD.
    (2) Airworthy Product: For any requirement in this AD to obtain 
corrective actions from a manufacturer or other source, use these 
actions if they are FAA-approved. Corrective actions are considered 
FAA-approved if they are approved by the State of Design Authority 
(or their delegated agent). You are required to assure the product 
is airworthy before it is returned to service.

(j) Related Information

    Refer to MCAI EASA Airworthiness Directive 2011-0176, dated 
September 13, 2011; and Airbus Service Bulletin A320-53-1244, 
excluding Appendix 1, dated March 17, 2011; for related information.

    Issued in Renton, Washington, on April 29, 2012.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2012-11023 Filed 5-7-12; 8:45 am]
BILLING CODE 4910-13-P
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