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CFR Citation: 14 CFR Part 39

Docket ID: [Docket No. FAA-2007-29170; Directorate Identifier 2007-NM-075-AD]

RIN ID: RIN 2120-AA64

NOTICE: PROPOSED RULES

ACTION: Airworthiness directives:

DOCUMENT ACTION: Notice of proposed rulemaking (NPRM).

SUBJECT CATEGORY: Airworthiness Directives; Airbus Model A319 and A320 Series Airplanes

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

DOCUMENT 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 wingtofuselage junction at rib 1 were found to be noncompliant with the applicable specification, resulting in a loss of pretension 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.

SUMMARY: Airbus,

SUPPLEMENTAL INFORMATION

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. FAA2007 29170; Directorate Identifier 2007NM075AD'' 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 20070067R1, dated June 7, 2007 (referred to after this
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as ``the MCAI''), to correct an unsafe condition for the specified products. The MCAI states:

Some taperlocks used in the wingtofuselage junction at rib 1 were found to be noncompliant with the applicable specification, resulting in a loss of pretension 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 A320571129 and A320571130, 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 A320571129 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 A320571130 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 workhours per product to comply with the basic requirements of this proposed AD. The average labor rate is $80 per workhour. 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 39AIRWORTHINESS 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. FAA200729170; Directorate Identifier 2007NM 075AD.
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.
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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 wingtofuselage junction at rib 1 were found to be noncompliant with the applicable specification, resulting in a loss of pretension 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 A320200 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 A320571129, 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 A320571130, 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 A320571130, dated September 10, 2004, are compliant with this paragraph.
(3) Modification of the aircraft in accordance with the instructions contained in Airbus Service Bulletins A320571131, A320571137, or A320571140, 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, ANM116, 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, ANM116, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 980573356; telephone (425) 2272141; fax (425) 2271149. 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 FAAapproved. Corrective actions are considered FAAapproved 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 20070067R1, dated June 7, 2007; and Airbus Service Bulletins A320571129 and A320571130, 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. E718046 Filed 91207; 8:45 am]
BILLING CODE 491013P

FOR FURTHER INFORMATION CONTACT Tim Dulin, Aerospace Engineer, International Branch, ANM116, FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington 980573356; telephone (425) 2272141; fax (425) 2271149.