Airworthiness Directives; Airbus Airplanes, 71996-71998 [2013-28170]

Agencies

• Federal Aviation Administration
• DEPARTMENT OF TRANSPORTATION

[Federal Register Volume 78, Number 231 (Monday, December 2, 2013)]
[Rules and Regulations]
[Pages 71996-71998]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-28170]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2013-0096; Directorate Identifier 2012-NM-143-AD; 
Amendment 39-17566; AD 2013-17-02]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

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SUMMARY: We are adopting a new airworthiness directive (AD) for certain 
Airbus Model A318-112, A319-111, A319-112, A319-115, A319-132, and 
A319-133 airplanes. 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. This AD requires 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 doing related 
investigative and corrective actions if necessary. We are issuing this 
AD to detect and correct the missing fastener, which could result in 
reduced structural integrity of the airplane.

DATES: This AD becomes effective January 6, 2014.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of January 6, 
2014.

ADDRESSES: You may examine the AD docket on the Internet at https://www.regulations.gov or in person at the U.S. Department of 
Transportation, Docket Operations, M-30, West Building Ground Floor, 
Room W12-140, 1200 New Jersey Avenue SE., Washington, DC.

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: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 by adding an AD that would apply to the specified products. The 
NPRM was published in the Federal Register on March 4, 2013 (78 FR 
14029). The NPRM proposed to correct an unsafe condition for the 
specified products.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Community, has issued 
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 doing 
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 on the Internet at 
https://www.regulations.gov/#!documentDetail;D=FAA-2013-0096-0002.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We have considered the comments received.

Request To Refer to Revised EASA AD

    Airbus requested that paragraph (j) of the NPRM (78 FR 14029, March 
4, 2013) be revised to refer to revised EASA AD 2012-0132R1, dated 
March 1, 2013 (https://ad.easa.europa.eu/blob/easa_ad_2012_0132_R1.pdf).
    We do not agree with the commenter's request. EASA AD 2012-0132R1, 
dated March 1, 2013, was revised to clarify the configurations of the 
Airbus Model A318 and A319 airplanes included in table 1 of EASA AD 
2012-0132R1, dated March 1, 2013. The clarifying text that EASA 
included in EASA AD 2012-0132R1, dated March 1, 2013, was designated in 
the NPRM (78 FR 14029, March 4, 2013) as ``Table 1 to Paragraphs (g) 
and (h) of this AD.''
    We have re-designated the material in table 1 to paragraphs (g) and 
(h) of the NPRM (78 FR 14029, March 4, 2013) as paragraphs (g)(1), 
(g)(2), and (g)(3) in this final rule. This change does not affect the 
intent of this AD. In addition, we revised references to ``Table 1 to 
Paragraphs (g) and (h) of this AD'' that appeared in paragraphs (g) and 
(h) of the NPRM to instead refer to paragraphs (g)(1), (g)(2), and 
(g)(3) of this AD. No change was made to this final rule with respect 
to the commenter's request to revise paragraph (j) of this final rule.

Request To Allow Credit for Actions Previously Accomplished Using 
Previous Revisions of the Service Information

    Airbus requested that table 1 to paragraphs (g) and (h) of the NPRM 
(78 FR 14029, March 4, 2013) be revised to provide credit for actions 
that are accomplished before the effective date of this AD using Airbus 
Service Bulletin A320-00-1219 dated November 9, 2010; Revision 01, 
dated December 8, 2010; Revision 02, dated September 6, 2011; or 
Revision 03, dated March 28, 2012.
    We do not agree with the commenter's request. As stated previously, 
the material in table 1 to paragraphs (g) and (h) of the NPRM (78 FR 
14029, March 4, 2013) has been re-designated as paragraphs (g)(1), 
(g)(2), and (g)(3) of this final rule. Those paragraphs do not mandate 
accomplishing any actions using Airbus Service Bulletin A320-00-

[[Page 71997]]

1219. That service information is only referenced to provide guidance 
to operators regarding certain configurations of Model A318 and A319 
airplanes. No change was made to this final rule with regard to the 
commenter's request.

Request To Revise Airbus Contact Information

    Airbus requested that we revise the contact information for the 
Airbus office of airworthiness from EAS to EIAS.
    We agree with the request and have included the revised contact 
information in paragraph (k)(3) of this final rule.

Conclusion

    We reviewed the available data, including the comments received, 
and determined that air safety and the public interest require adopting 
this AD with the changes described previously and minor editorial 
changes. We have determined that these changes:
     Are consistent with the intent that was proposed in the 
NPRM (78 FR 14029, March 4, 2013) for correcting the unsafe condition; 
and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM (78 FR 14029, March 4, 2013).

Costs of Compliance

    We estimate that this AD affects about 3 products of U.S. registry. 
We also estimate that it takes about 26 work hours per product to 
comply with the basic requirements of this AD. The average labor rate 
is $85 per work hour. Required parts 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 this 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 AD will not have federalism implications 
under Executive Order 13132. This AD will 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 that this AD:
    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 AD and placed it in the AD docket.

Examining the AD Docket

    You may examine the AD docket on the Internet at https://www.regulations.gov/#!docketDetail;D=FAA-2013-0096; 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 AD, the 
MCAI, 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.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA amends 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:

2013-17-02 Airbus: Amendment 39-17566. Docket No. FAA-2013-0096; 
Directorate Identifier 2012-NM-143-AD.

(a) Effective Date

    This airworthiness directive (AD) becomes effective January 6, 
2014.

(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 paragraph (g)(1), (g)(2), or 
(g)(3) 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, dated May 22, 2012.
    (1) For Model A319 airplanes, except manufacturer serial numbers 
4151, 4228, and 4319; and Model A318 airplanes, pre-modification 
39195, and on which the actions specified in Airbus Service Bulletin 
A320-00-1219 have not been embodied in service: Inspect before the 
accumulation of 5,000 total flight cycles since first flight of the 
airplane, or within 4,300 flight cycles after the effective date of 
this AD, whichever occurs later.
    (2) For Model A318 airplanes, post-modification 39195; and Model 
A318 airplanes on which the actions specified in Airbus Service 
Bulletin A320-00-1219 have been embodied in service: Inspect before 
the

[[Page 71998]]

accumulation of 3,000 total flight cycles since first flight of the 
airplane, or within 90 days after the effective date of this AD, 
whichever occurs later.
    (3) For Model A319 airplanes, manufacturer serial numbers 4151, 
4228, and 4319 (post-modification 28238, 28162, and 28342): Inspect 
before the accumulation of 2,500 total flight cycles 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 paragraph (g)(1), (g)(2), or (g)(3) 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, 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 the European Aviation Safety Agency (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, 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 Mandatory Continuing Airworthiness Information EASA 
Airworthiness Directive 2012-0132, dated July 19, 2012, for related 
information, which can be found in the AD docket on the Internet at 
https://www.regulations.gov/#!documentDetail;D=FAA-2013-0096-0002.

(k) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless this AD specifies otherwise.
    (i) Airbus Service Bulletin A320-53-1242, dated May 22, 2012.
    (ii) Reserved.
    (3) 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.
    (4) 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.
    (5) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, call 202-741-6030, or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on August 9, 2013.
Jeffrey E. Duven,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2013-28170 Filed 11-29-13; 8:45 am]
BILLING CODE 4910-13-P