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CFR Citation: 14 CFR Part 39

Docket ID: [Docket No. FAA-2007-0390; Directorate Identifier 2007-NM-260-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 A318, A319, A320, and A321 Airplanes

DATES: We must receive comments on this proposed AD by February 8, 2008.

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:

Several cases of cracks on the main landing gear (MLG) door hinge fitting and MLG door actuator fitting on the keel beam were reported.

Such failure could lead to the loss [of] the MLG door and could cause damage to the aircraft and/or hazard to persons or property on the ground.
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. FAA20070390; Directorate Identifier 2007NM260AD'' 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 20070161, dated June 11, 2007 (referred to after this as ``the MCAI''), to correct an unsafe condition for the specified products. The MCAI states:

Several cases of cracks on the main landing gear (MLG) door hinge fitting and MLG door actuator fitting on the keel beam were reported.

Such failure could lead to the loss [of] the MLG door and could cause damage to the aircraft and/or hazard to persons or property on the ground.

This Airworthiness Directive (AD) mandates a onetime detailed visual inspection (DVI) and special detailed inspection (SDI) of the MLG door hinge fitting and actuator fitting.
The inspections are for cracking, damage, correct installation, and correct adjustment. The corrective actions include correcting incorrect adjustments and installations, and contacting Airbus for instructions to repair damage and cracking. You may obtain further information by examining the MCAI in the AD docket.

Relevant Service Information

Airbus has issued Service Bulletins A320531195, Revision 02, dated April 5, 2007, and A320531196, Revision 01, dated November 29, 2006. 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.
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 [[Page 1557]]

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 641 products of U.S. registry. We also estimate that it would take about 28 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 $1,435,840, or $2,240 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. FAA20070390; Directorate Identifier 2007NM 260AD.
Comments Due Date
(a) We must receive comments by February 8, 2008.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Airbus Model A318, A319, A320, and A321 series airplanes, all certified models, certificated in any category, all serial numbers up to manufacturer's serial number (MSN) 2850 inclusive, except MSNs 0115, 0184, 0782, 1151, 1190, 2650, 2675, 2706, 2801, and 2837.
Subject
(d) Air Transport Association (ATA) of America Code 53: Fuselage.
Reason
(e) The mandatory continuing airworthiness information (MCAI) states:

Several cases of cracks on the main landing gear (MLG) door hinge fitting and MLG door actuator fitting on the keel beam were reported.

Such failure could lead to the loss [of] the MLG door and could cause damage to the aircraft and/or hazard to persons or property on the ground.

This Airworthiness Directive (AD) mandates a onetime detailed visual inspection (DVI) and special detailed inspection (SDI) of the MLG door hinge fitting and actuator fitting.

The inspections are for cracking, damage, correct installation, and correct adjustment. The corrective actions include correcting incorrect adjustments and installations, and contacting Airbus for instructions to repair damage and cracking.
Actions and Compliance
(f) Unless already done, do the following actions.
(1) At the latest of the times specified in paragraphs (f)(1)(i), (f)(1)(ii), and (f)(1)(iii) of this AD, perform detailed visual, high frequency eddy current (HFEC), and ultrasonic inspections (for cracking, damage, correct installation, and correct adjustment, as applicable) of the left hand (LH) and right hand (RH) MLG door actuator fitting on the keel beam, and do all applicable corrective actions before further flight. Where the service bulletin specifies the applicable corrective action is contacting Airbus, contact Airbus for repair instructions and repair before further flight. Do all actions required by this paragraph in accordance with the Accomplishment Instructions of Airbus Service Bulletin A32053 1195, Revision 02, dated April 5, 2007.
(i) Within 6,000 flight cycles since first flight.
(ii) Within 1,500 flight cycles after the effective date of this AD.
(iii) Within 6,000 flight cycles from the latest MLG door actuator fitting replacement.
(2) At the later of the times specified in paragraphs (f)(2)(i) and (f)(2)(ii) of this AD, perform detailed visual and HFEC inspections (for cracking, damage, correct installation, and correct adjustment, as applicable) of the LH and RH MLG door hinge fitting on the keel beam, and do all applicable corrective actions before further flight. Where the service bulletin specifies the applicable corrective action is contacting Airbus, contact Airbus for repair instructions and repair before further flight. Do all actions required by this paragraph in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320531196, Revision 01, dated November 29, 2006.
(i) Within 4,500 flight cycles since first flight.
(ii) Within 1,500 flight cycles after the effective date of this AD.
(3) Actions done before the effective date of this AD in accordance with the applicable service bulletins listed in paragraphs (f)(3)(i), (f)(3)(ii), and (f)(3)(iii) of this AD are acceptable for compliance with the corresponding actions required by this AD.
(i) Airbus Service Bulletin A320531195, dated June 23, 2006. (ii) Airbus Service Bulletin A320531195, Revision 01, dated November 29, 2006.
(iii) Airbus Service Bulletin A320531196, dated June 23, 2006. FAA AD Differences

Note: This AD differs from the MCAI and/or service information as follows: No differences.
Other FAA AD Provisions
(g) The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, Transport Airplane Directorate, 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,
[[Page 1558]]
Transport Airplane Directorate, FAA, 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 European Aviation Safety Agency (EASA) Airworthiness Directive 20070161, dated June 11, 2007, Airbus Service Bulletin A320531195, Revision 02, dated April 5, 2007, and Airbus Service Bulletin A320531196, Revision 01, dated November 29, 2006, for related information.

Issued in Renton, Washington, on December 19, 2007. Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. E8164 Filed 1808; 8:45 am]
BILLING CODE 491013P

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