Document ID: FAA-2013-0096-0001
Agency: faa
Document Type: Proposed Rule
Title: Airworthiness Directives: Airbus Airplanes
Posted Date: 2013-03-04T05:00Z

[Federal Register Volume 78, Number 42 (Monday, March 4, 2013)]
[Proposed Rules]
[Pages 14029-14031]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-04903]

=======================================================================
-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2013-0096; Directorate Identifier 2012-NM-143-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 
certain Airbus Model A318-112, A319-111, A319-112, A319-115, A319-132, 
and A319-133 airplanes. This proposed AD was prompted by a report that 
a fastener, which connects the cargo door keel beam foot to the 
circumferential butt-strap and the section 13-14 lower shell panel, was 
not installed on airplanes during production. This proposed AD would 
require inspecting forward fuselage frame 24, stringer 39, right hand, 
to determine if the fastener is missing; measuring the hole dimensions 
of the five holes surrounding the missing fastener if necessary; and 
related investigative and corrective actions if necessary. We are 
proposing this AD to detect and correct the missing fastener, which 
could result in reduced structural integrity of the airplane.

DATES: We must receive comments on this proposed AD by April 18, 2013.

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, Airworthiness Office--EAS, 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, 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; 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-2013-0096; 
Directorate Identifier 2012-NM-143-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 2012-0132, dated July 19, 2012 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for the specified 
products. The MCAI states:

    During a ground inspection of an A319 aeroplane in production, 
it was discovered that one fastener was missing at stringer (STGR) 
39 on the right-hand (RH) side of FR [forward fuselage frame] 24 
(Section 13-14 side). The hole of the missing fastener was not 
drilled. The missing fastener, a 4.8 mm [millimeter] diameter 
titanium bolt, Part Number (P/N) EN 6114 V3-7, should connect the 
cargo door keel beam foot to the circumferential butt-strap and the 
section 13-14 lower shell panel. Further investigations have 
revealed that the affected fastener has not been installed on a 
limited number of aeroplanes in production, due to incorrect 
production instructions.
    This condition, if not corrected, could impair the structural 
integrity of the affected aeroplanes.
* * * * *
The required actions include doing a detailed inspection to determine 
if the fastener is missing, measuring the hole dimensions of the five 
holes surrounding the missing fastener if necessary, and related 
investigative and corrective actions if necessary. The related 
investigative actions include a rototest inspection of the five holes 
for cracking. The corrective actions include repairing any holes with 
diameter values that exceed the specified dimensions, repairing any 
cracking found, and installing new fasteners. You may obtain further 
information by examining the MCAI in the AD docket.

Relevant Service Information

    Airbus has issued Service Bulletin A320-53-1242, including Appendix 
01, dated May 22, 2012. The actions described in this service 
information are intended to correct the unsafe condition identified in 
the MCAI.

[[Page 14030]]

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.

Differences Between This Proposed AD and the MCAI or Service 
Information

    Although EASA Airworthiness Directive 2012-0132, dated July 19, 
2012, specifies to contact the manufacturer for instructions to repair 
certain conditions, this proposed AD would require repairing those 
conditions using a method approved by either the Manager, International 
Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA (or its 
delegated agent).

Costs of Compliance

    Based on the service information, we estimate that this proposed AD 
would affect about 3 products of U.S. registry. We also estimate that 
it would take about 26 work-hours per product to comply with the basic 
requirements of this proposed AD. The average labor rate is $85 per 
work-hour. Required parts would cost $1,904 per product. Where the 
service information lists required parts costs that are covered under 
warranty, we have assumed that there will be no charge for these parts. 
As we do not control warranty coverage for affected parties, some 
parties may incur costs higher than estimated here. Based on these 
figures, we estimate the cost of the proposed AD on U.S. operators to 
be up to $12,342, or $4,114 per product.

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

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 AD:

Airbus: Docket No. FAA-2013-0096; Directorate Identifier 2012-NM-
143-AD.

(a) Comments Due Date

    We must receive comments by April 18, 2013.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Airbus Model A318-112, A319-111, A319-112, 
A319-115, A319-132, and A319-133 airplanes; certificated in any 
category; manufacturer serial numbers 3983, 3985, 3998, 4000, 4004, 
4007, 4018, 4020, 4029, 4036, 4038 through 4040 inclusive, 4048, 
4052, 4056, 4069, 4071, 4076, 4080, 4087, 4089, 4121, 4125, 4127, 
4129, 4132, 4141, 4151, 4163, 4164, 4166, 4169, 4171, 4182, 4192, 
4200, 4204, 4211, 4215, 4222, 4227, 4228, 4254, 4256, 4258, 4259, 
4262, 4268, 4275, 4282, 4285, 4287, 4301, 4313, 4319, 4327, 4332, 
and 4336.

(d) Subject

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

(e) Reason

    This AD was prompted by a report that a fastener, which connects 
the cargo door keel beam foot to the circumferential butt-strap and 
the section 13-14 lower shell panel, was not installed on airplanes 
during production. We are issuing this AD to detect and correct the 
missing fastener, which could result in reduced 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) Inspections

    At the applicable time specified in table 1 to paragraphs (g) 
and (h) of this AD: Do a detailed inspection at forward fuselage 
frame 24, stringer 39, right hand, to determine if the fastener is 
missing, in accordance with the Accomplishment Instructions of 
Airbus Service Bulletin A320-53-1242, excluding Appendix 01, dated 
May 22, 2012.

      Table 1 to Paragraphs (g) and (h) of This AD--Compliance Time
------------------------------------------------------------------------
        Airplane configuration--                Compliance time--
------------------------------------------------------------------------
Model A319 airplanes, except             Before the accumulation of
 manufacturer serial numbers 4151,        5,000 total flight cycles
 4228, and 4319; and Model A318           since first flight of the
 airplanes, pre-mod 39195, and on which   airplane, or within 4,300
 the actions specified in Airbus          flight cycles after the
 Service Bulletin A320[dash]00-1219       effective date of this AD,
 have not been embodied in service.       whichever occurs later.

[[Page 14031]]

 
Model A318 airplanes, post-mod 39195;    Before the accumulation of
 and Model A318 airplanes on which the    3,000 total flight cycles
 actions specified in Airbus Service      since first flight of the
 Bulletin A320-00-1219 have been          airplane, or within 90 days
 embodied in service.                     after the effective date of
                                          this AD, whichever occurs
                                          later.
Model A319 airplanes, manufacturer       Before the accumulation of
 serial numbers 4151, 4228, and 4319      2,500 total flight cycles
 (post-mod 28238, 28162, and 28342).      since first flight of the
                                          airplane, or within 90 days
                                          after the effective date of
                                          this AD, whichever occurs
                                          later.
------------------------------------------------------------------------

(h) Measurements and Corrective Actions

    If, during any inspection required by paragraph (g) of this AD, 
the fastener is determined to be missing, within the applicable 
compliance time specified in table 1 to paragraphs (g) and (h) of 
this AD: Measure the hole dimensions of the five holes surrounding 
the missing fastener, and do all applicable related investigative 
and corrective actions, in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A320-53-1242, excluding 
Appendix 01, dated May 22, 2012, except where the service bulletin 
specifies to contact Airbus, before further flight, repair using a 
method approved by either the Manager, International Branch, ANM-
116, Transport Airplane Directorate, FAA; or EASA (or its delegated 
agent). Do all applicable related investigative and corrective 
actions before further flight.

(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, 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

    (1) Refer to Mandatory Continuing Airworthiness Information EASA 
Airworthiness Directive 2012-0132, dated July 19, 2012; and Airbus 
Service Bulletin A320-53-1242, excluding Appendix 01, dated May 22, 
2012; for related information.
    (2) For service information identified in this AD, contact 
Airbus, Airworthiness Office--EAS, 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, WA. For information on the availability of this 
material at the FAA, call 425-227-1221.

    Issued in Renton, Washington, on February 25, 2013.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2013-04903 Filed 3-1-13; 8:45 am]
BILLING CODE 4910-13-P