[Federal Register Volume 72, Number 177 (Thursday, September 13, 2007)]
[Proposed Rules]
[Pages 52309-52311]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: E7-18046]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-29170; Directorate Identifier 2007-NM-075-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A319 and A320 Series 
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 the 
products listed above. This proposed AD results from mandatory 
continuing airworthiness information (MCAI) originated by an aviation 
authority of another country to identify and correct an unsafe 
condition on an aviation product. The MCAI describes the unsafe 
condition as:

    Some taperlocks used in the wing-to-fuselage junction at rib 1 
were found to be non-compliant with the applicable specification, 
resulting in a loss of pre-tension in the fasteners. In such 
conditions, the structural integrity of the aircraft could be 
affected.

The proposed AD would require actions that are intended to address the 
unsafe condition described in the MCAI.

DATES: We must receive comments on this proposed AD by October 15, 
2007.

ADDRESSES: You may send comments by any of the following methods:
     DOT Docket Web Site: Go to http://dms.dot.gov and follow 
the instructions for sending your comments electronically.
     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: Room W12-140 on the ground floor of the 
West Building, 1200 New Jersey Avenue SE., Washington, DC, between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
     Federal eRulemaking Portal: http://www.regulations.gov. 
Follow the instructions for submitting comments.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://dms.dot.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: Tim Dulin, Aerospace Engineer, 
International Branch, ANM-116, FAA, Transport Airplane Directorate, 
1601 Lind Avenue SW., Renton, Washington 98057-3356; telephone (425) 
227-2141; 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-2007-
29170; Directorate Identifier 2007-NM-075-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://dms.dot.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 2007-0067R1, dated June 7, 2007 (referred to 
after this

[[Page 52310]]

as ``the MCAI''), to correct an unsafe condition for the specified 
products. The MCAI states:

    Some taperlocks used in the wing-to-fuselage junction at rib 1 
were found to be non-compliant with the applicable specification, 
resulting in a loss of pre-tension in the fasteners. In such 
conditions, the structural integrity of the aircraft could be 
affected.
    This Airworthiness Directive mandates a repetitive internal 
inspection of the lower stiffeners, and a repetitive external 
inspection of the lower panels in center and outer wing box at level 
of rib 1 junction.

The corrective action includes contacting Airbus for repair 
instructions and repair if any crack is found. You may obtain further 
information by examining the MCAI in the AD docket.

Relevant Service Information

    Airbus has issued Service Bulletins A320-57-1129 and A320-57-1130, 
both Revision 01, both dated July 28, 2006. The actions described in 
this service information are intended to correct the unsafe condition 
identified in the MCAI.
    Depending on airplane configuration, the compliance times specified 
in Service Bulletin A320-57-1129 range from between 37,500 and 42,000 
flight cycles and 96,100 and 107,300 flight hours, whichever occurs 
first, from AD effective date; the repetitive intervals range from 
between 6,100 and 6,500 flight cycles and 15,700 and 16,800 flight 
hours, whichever occurs first; the grace period is 6,100 flight cycles 
or 15,600 flight hours, whichever occurs first.
    Depending on airplane configuration, the compliance times specified 
in Service Bulletin A320-57-1130 range from between 23,600 and 45,000 
flight cycles and 60,400 and 101,000 flight hours, whichever occurs 
first, from AD effective date; the repetitive intervals range from 
between 6,100 and 10,000 flight cycles and 15,600 and 22,500 flight 
hours, whichever occurs first; the grace period is 6,100 flight cycles 
or 15,600 flight hours, whichever occurs first.

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 AD and the MCAI or Service Information

    We have reviewed the MCAI and related service information and, in 
general, agree with their substance. But we might have found it 
necessary to use different words from those in the MCAI to ensure the 
AD is clear for U.S. operators and is enforceable. In making these 
changes, we do not intend to differ substantively from the information 
provided in the MCAI and related service information.
    We might also have proposed different actions in this AD from those 
in the MCAI in order to follow FAA policies. Any such differences are 
highlighted in a Note within the proposed AD.

Costs of Compliance

    Based on the service information, we estimate that this proposed AD 
would affect about 583 products of U.S. registry. We also estimate that 
it would take about between 16 and 77 work-hours per product to comply 
with the basic requirements of this proposed AD. The average labor rate 
is $80 per work-hour. Based on these figures, we estimate the cost of 
the proposed AD on U.S. operators to be between $746,240 and 
$3,591,280, or between $1,280 and $6,160 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); and
    3. 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, 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-2007-29170; Directorate Identifier 2007-NM-
075-AD.

Comments Due Date

    (a) We must receive comments by October 15, 2007.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Airbus Model A319 and A320 series 
airplanes, certificated in any category, all certified models, all 
serial numbers (MSN); except airplanes identified in paragraphs 
(c)(1) and (c)(2) of this AD. Model A320 series airplanes MSN 2164 
through MSN 2688 that have partially received Airbus Modification 
33421 in production are affected by the requirements of this AD.
    (1) Model A319 series airplanes that have received Airbus 
Modifications 28238, 28162, and 28342 in production, or Airbus 
Modification 33421 in production.
    (2) Model A320 series airplanes that have received Airbus 
Modification 33421 fully embodied in production.

[[Page 52311]]

Subject

    (d) Air Transport Association (ATA) of America Code 57: Wings.

Reason

    (e) The mandatory continuing airworthiness information (MCAI) 
states:

    Some taperlocks used in the wing-to-fuselage junction at rib 1 
were found to be non-compliant with the applicable specification, 
resulting in a loss of pre-tension in the fasteners. In such 
conditions, the structural integrity of the aircraft could be 
affected.
    This Airworthiness Directive mandates a repetitive internal 
inspection of the lower stiffeners, and a repetitive external 
inspection of the lower panels in center and outer wing box at level 
of rib 1 junction.

The corrective action includes contacting Airbus for repair 
instructions and repair if any crack is found.

Actions and Compliance

    (f) Unless already done, do the following actions.
    (1) For A320-200 aircraft: Before the defined threshold or 
within the defined grace period after the effective date of this AD, 
whichever occurs later, as listed in paragraph 1.E., ``Compliance,'' 
of Airbus Service Bulletin A320-57-1129, Revision 01, dated July 28, 
2006, and following the instructions given in the service bulletin, 
perform an internal ultrasonic inspection of the lower stiffeners in 
the center and outer wing box at the level of the rib 1 junction to 
detect cracks, and if any crack is found, before further flight 
contact Airbus for repair instructions and repair. Repeat this 
inspection at the intervals defined in paragraph 1.E., 
``Compliance,'' of the service bulletin.
    (2) For all aircraft: Before the defined threshold or within the 
defined grace period after the effective date of this AD, whichever 
occurs later, as listed in paragraph 1.E., ``Compliance,'' of Airbus 
Service Bulletin A320-57-1130, Revision 01, dated July 28, 2006, and 
following the instructions given in the service bulletin, perform an 
external ultrasonic inspection of the lower stiffeners in the center 
and outer wing box at the level of the rib 1 junction to detect 
cracks, and if any crack is found, before further flight contact 
Airbus for repair instructions and repair. Repeat this inspection at 
the intervals defined in paragraph 1.E., ``Compliance,'' of the 
service bulletin. Aircraft that have already accomplished Airbus 
Service Bulletin A320-57-1130, dated September 10, 2004, are 
compliant with this paragraph.
    (3) Modification of the aircraft in accordance with the 
instructions contained in Airbus Service Bulletins A320-57-1131, 
A320-57-1137, or A320-57-1140, all dated November 21, 2006; 
terminates the repetitive inspection requirements of this AD.

FAA AD Differences

    Note: This AD differs from the MCAI and/or service information 
as follows:
    Although the MCAI or service information does not specify a 
compliance time for corrective action (repair of cracks), paragraphs 
(f)(1) and (f)(2) of this AD require that the corrective action be 
done before further flight.
    Although the MCAI and/or service information specify a 
compliance time for accomplishing the inspections after the 
effective date on the MCAI, this AD requires compliance within the 
specified compliance time after the effective date of this AD.

Other FAA AD Provisions

    (g) 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. Send information to ATTN: Tim Dulin, Aerospace Engineer, 
International Branch, ANM-116, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone 
(425) 227-2141; fax (425) 227-1149. Before using any approved AMOC 
on any airplane to which the AMOC applies, notify your appropriate 
principal inspector (PI) in the FAA Flight Standards District Office 
(FSDO), or lacking a PI, your local FSDO.
    (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.
    (3) Reporting Requirements: For any reporting requirement in 
this AD, under the provisions of the Paperwork Reduction Act, the 
Office of Management and Budget (OMB) has approved the information 
collection requirements and has assigned OMB Control Number 2120-
0056.

Related Information

    (h) Refer to MCAI EASA Airworthiness Directive 2007-0067R1, 
dated June 7, 2007; and Airbus Service Bulletins A320-57-1129 and 
A320-57-1130, both Revision 01, both dated July 28, 2006; for 
related information.

    Issued in Renton, Washington, on September 4, 2007.
Stephen P. Boyd,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E7-18046 Filed 9-12-07; 8:45 am]
BILLING CODE 4910-13-P