Browse: Departments   Dates   Agencies  

CFR Citation: 14 CFR Part 39

Docket ID: [Docket No. FAA-2008-0667; Directorate Identifier 2008-NM-009-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 A330-200, A330-300, and A340-300 Series Airplanes

DATES: We must receive comments on this proposed AD by July 24, 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:

During fatigue tests (EF3) on the A340600, damages were found in longitudinal doubler
[[Page 35604]]
at VTP (vertical tail plane) attachment cutout between Frame (FR) 80 and FR86. This damage occurred between 58341 and 72891 simulated flight cycles (FC).

Due to the higher Design Service Goal and different design (e.g. doubler thickness) [of the] A330200/300 and A340300 aircraft series, the damage assessment concluded [there was] potential impact on [the airplanes specified in the] applicability.
* * * * *
The unsafe condition is crack propagation in the VTP attachment cutout, which could reduce airplane structural integrity in the tail section. The proposed AD would require actions that are intended to address the unsafe condition described in the MCAI.

SUMMARY: Airbus Model A330-200, A330-300, and A340 300 Series Airplanes,

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. FAA20080667; Directorate Identifier 2008NM009AD'' 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 20070284, dated November 12, 2007 (referred to after this as ``the MCAI''), to correct an unsafe condition for the specified products. The MCAI states:

During fatigue tests (EF3) on the A340600, damages were found in longitudinal doubler at VTP (vertical tail plane) attachment cutout between Frame (FR) 80 and FR86. This damage occurred between 58341 and 72891 simulated Flight Cycles (FC).

Due to the higher Design Service Goal and different design (e.g. doubler thickness) [of the] A330200/300 and A340300 aircraft series, the damage assessment concluded [there was] potential impact on [the airplanes specified in the] applicability.
[T]o allow early detection of cracks, which could [prevent] possible crack propagation and consequently maintain the structural integrity of the upper shell structure between FR80 and FR86, this Airworthiness Directive (AD) mandates an inspection program [for cracking] of this area using a high frequency eddy current (HFEC) method, and a modification to improve the upper shell structure. The unsafe condition is crack propagation in the VTP attachment cutout, which could reduce airplane structural integrity in the tail section. Corrective actions include doing eddy current inspections for cracking of certain fastener rows, and contacting Airbus for repair instructions and repairing. You may obtain further information by examining the MCAI in the AD docket.

Relevant Service Information

Airbus has issued the service bulletins specified in the following table. The compliance times in paragraph 1.E.(2) of the service bulletins range from 14,200 total flight cycles through 27,900 total flight cycles (for the initial inspection); from 1,700 flight cycles or 11,900 flight hours, whichever occurs first, through 4,600 flight cycles or 14,000 flight hours, whichever occurs first (for the repetitive inspection intervals); and from 10,700 total flight cycles through 14,200 total flight cycles (for the modification); depending upon airplane model and weight variant. The actions described in this service information are intended to correct the unsafe condition identified in the MCAI.
Airbus Service Information
Service Bulletin Date A330533159.............................. September 19, 2007. A330533160.............................. July 9, 2007.
A330533168.............................. September 19, 2007. A340534165.............................. September 19, 2007. A340534172.............................. July 10, 2007.
A340534174.............................. September 19, 2007. 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 26 products of U.S. registry. We also estimate that it would take about 202 workhours per product to comply with the basic requirements of this proposed AD. The average labor rate is $80 per workhour. Required
[[Page 35605]]
parts would cost about $19,020 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 costs. 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 $914,680, or $35,180 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. FAA20080667; Directorate Identifier 2008NM 009AD.
Comments Due Date
(a) We must receive comments by July 24, 2008.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Airbus Model A330200, A330300, and A340300 series airplanes; certificated in any category; all certified models, all serial numbers; on which Airbus modification 44205 has been embodied in production, except those on which Airbus modification 52974 or 53223 has been embodied in production. Subject
(d) Air Transport Association (ATA) of America Code 53: Fuselage.
Reason
(e) The mandatory continuing airworthiness information (MCAI) states:

During fatigue tests (EF3) on the A340600, damages were found in longitudinal doubler at VTP (vertical tail plane) attachment cutout between Frame (FR) 80 and FR86. This damage occurred between 58341 and 72891 simulated Flight Cycles (FC).

Due to the higher Design Service Goal and different design (e.g. doubler thickness) [of the] A330200/300 and A340300 aircraft series, the damage assessment concluded [there was] potential impact on [the airplanes specified in the] applicability.
[T]o allow early detection of cracks, which could [prevent] possible crack propagation and consequently maintain the structural integrity of the upper shell structure between FR80 and FR86, this Airworthiness Directive (AD) mandates an inspection program [for cracking] of this area using a high frequency eddy current (HFEC) method, and a modification to improve the upper shell structure. The unsafe condition is crack propagation in the VTP attachment cutout, which could reduce airplane structural integrity in the tail section. Corrective actions include doing eddy current inspections for cracking of certain fastener rows, and contacting Airbus for repair instructions and repairing.
Actions and Compliance
(f) Unless already done, do the following actions.
(1) For Airbus Model A330300 and A340300 series airplanes, except Model A340300 weight variant (WV) 027 airplanes: At the applicable compliance time specified in paragraph (f)(2) of this AD, perform a HFEC inspection of the upper shell structure between FR80 and FR86, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330533168 or A340534174, both dated September 19, 2007, as applicable.
(i) If no crack is detected, repeat the inspection thereafter within the intervals specified in paragraph 1.E.(2) of Airbus Service Bulletin A330573168 or A340534174, as applicable.
(ii) If any crack is detected during any inspection required by this AD: Before next flight, contact Airbus for repair instructions and do applicable repairs.
(iii) Doing the modification of the upper shell structure in accordance with Airbus Service Bulletin A330533159 or Airbus Service Bulletin A340534165, both dated September 19, 2007, as applicable, ends the inspections required by paragraph (f)(1) of this AD.
(2) Do the actions required by paragraph (f)(1) of this AD at the later of the compliance times specified in paragraph (f)(2)(i) and (f)(2)(ii) of this AD.
(i) Within the compliance times specified in paragraph 1.E.(2) of Airbus Service Bulletin A330533168 or A340534174, both dated September 19, 2007, as applicable.
(ii) Within 3 months after the effective date of this AD. (3) At the applicable time specified in paragraphs (f)(3)(i), (f)(3)(ii), and (f)(3)(iii) of this AD or within 3 months after the effective date of this AD, whichever occurs later, modify the upper shell structure between FR80 and FR86 (including doing eddy current inspections for cracking of certain fastener rows and applicable corrective actions) in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A330533160, dated July 9, 2007, or Airbus Service Bulletin A340534172, dated July 10, 2007, as applicable. Do all applicable corrective actions before further flight.
(i) For Model A330200 airplanes, WV 020 through WV 027: Prior to the accumulation of 13,500 total flight cycles.
(ii) For Model A330200 airplanes, WV 050 through WV 055: Prior to the accumulation of 10,700 total flight cycles or 59,300 total flight hours, whichever occurs first.
(iii) For Model A340300 airplanes, WV 027: Prior to the accumulation of 14,200 total flight cycles.

FAA AD Differences

Note: This AD differs from the MCAI and/or service information as follows: Although the MCAI allows further flight after cracks are found during compliance with the required action, this AD requires that you repair the crack(s) before further flight.
[[Page 35606]]
Other FAA AD Provisions
(g) The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM116, Transport Airplane Directorate, 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: Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 980573356; telephone (425) 2271138; 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 20070284, dated November 12, 2007, and the service bulletins specified in Table 1 of this AD, for related information.
Table 1.Service Information
Airbus Service Bulletin Date A330533159.............................. September 19, 2007. A330533160.............................. July 9, 2007.
A330533168.............................. September 19, 2007. A340534165.............................. September 19, 2007. A340534172.............................. July 10, 2007.
A340534174.............................. September 19, 2007.

Issued in Renton, Washington, on June 9, 2008.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. E814192 Filed 62308; 8:45 am]
BILLING CODE 491013P

FOR FURTHER INFORMATION CONTACT Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 980573356; telephone (425) 2271138; fax (425) 2271149.