[Federal Register Volume 62, Number 227 (Tuesday, November 25, 1997)]
[Proposed Rules]
[Pages 62723-62725]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 97-30858]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97-NM-178-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A300 and A300-600 Series 
Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: This document proposes the adoption of a new airworthiness 
directive (AD) that is applicable to certain Airbus Model A300 and 
A300-600 series airplanes. This proposal would require inspections to 
detect cracks in Gear Rib 5 of the main landing gear (MLG) attachment 
fittings at the lower flange, and repair, if necessary. This proposal 
is prompted by issuance of mandatory continuing airworthiness 
information by a foreign civil airworthiness authority. The actions 
specified by the proposed AD are intended to detect and correct fatigue 
cracking of the MLG attachment fittings, which could result in reduced 
structural integrity of the airplane.

DATES: Comments must be received by December 26, 1997.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-103, 
Attention: Rules Docket No. 97-NM-178-AD, 1601 Lind Avenue, SW., 
Renton, Washington 98055-4056. Comments may be inspected at this 
location between 9:00 a.m. and 3:00 p.m., Monday through Friday, except 
Federal holidays.
    The service information referenced in the proposed rule may be 
obtained from Airbus Industrie, 1 Rond Point Maurice Bellonte, 31707 
Blagnac Cedex, France. This information may be examined at the FAA, 
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, 
Washington.

FOR FURTHER INFORMATION CONTACT: International Branch, ANM-116, FAA, 
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, 
Washington 98055-4056; telephone (425) 227-2110; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION:

Comments Invited

    Interested persons are invited to participate in the making of the 
proposed rule by submitting such written data, views, or arguments as 
they may desire. Communications shall identify the Rules Docket number 
and be submitted in triplicate to the address specified above. All 
communications received on or before the closing date for comments, 
specified above, will be considered before taking action on the 
proposed rule. The proposals contained in this notice may be changed in 
light of the comments received.
    Comments are specifically invited on the overall regulatory, 
economic, environmental, and energy aspects of the proposed rule. All 
comments submitted will be available, both before and after the closing 
date for comments, in the Rules Docket for examination by interested 
persons. A report summarizing each FAA-public contact concerned with 
the substance of this proposal will be filed in the Rules Docket.
    Commenters wishing the FAA to acknowledge receipt of their comments 
submitted in response to this notice must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 97-NM-178-AD.'' The postcard will be date stamped and 
returned to the commenter.

Availability of NPRMs

    Any person may obtain a copy of this NPRM by submitting a request 
to the FAA, Transport Airplane Directorate, ANM-103, Attention: Rules 
Docket No. 97-NM-178-AD, 1601 Lind Avenue, SW., Renton, Washington 
98055-4056.

Discussion

    The Direction Generale de l'Aviation Civile (DGAC), which is the 
airworthiness authority for France,

[[Page 62724]]

notified the FAA that an unsafe condition may exist on certain Airbus 
Model A300 and A300-600 series airplanes. The DGAC advises that, on two 
in-service airplanes, fatigue cracking has been detected on Gear Rib 5 
of the main landing gear attachment fitting at the lower flange. Such 
fatigue cracking, if not detected and corrected in a timely manner, 
could result in reduced structural integrity of the airplane.

Explanation of Relevant Service Information

    Airbus has issued Service Bulletins A300-57A6087 (for Model A300-
600 series airplanes) and A300-57A0234 (for Model A300 series 
airplanes), both dated August 5, 1997. These service bulletins describe 
procedures for detailed visual and high frequency eddy current 
inspections to detect cracks in Gear Rib 5 of the main landing gear 
attachment fittings at the lower flange. The DGAC classified these 
service bulletins as mandatory and issued French airworthiness 
directive (CN) 97-274-230(B), dated September 24, 1997, in order to 
assure the continued airworthiness of these airplanes in France.

FAA's Conclusions

    These airplane models are manufactured in France and are type 
certificated for operation in the United States under the provisions of 
section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and 
the applicable bilateral airworthiness agreement. Pursuant to this 
bilateral airworthiness agreement, the DGAC has kept the FAA informed 
of the situation described above. The FAA has examined the findings of 
the DGAC, reviewed all available information, and determined that AD 
action is necessary for products of this type design that are 
certificated for operation in the United States.

Explanation of Requirements of Proposed Rule

    Since an unsafe condition has been identified that is likely to 
exist or develop on other airplanes of the same type design registered 
in the United States, the proposed AD would require accomplishment of 
the actions specified in the service bulletins described previously, 
except as discussed below.

Differences Between the Proposed AD and the Related Service 
Bulletins

    The service bulletins described previously specify that appropriate 
corrective action may be obtained by contacting the manufacturer, 
Airbus, directly. However, this proposed AD would requires that any 
such repair be accomplished in accordance with a method approved by the 
FAA.

Cost Impact

    The FAA estimates that 67 airplanes of U.S. registry would be 
affected by this proposed AD, that it would take approximately 6 work 
hours per airplane to accomplish the proposed actions, and that the 
average labor rate is $60 per work hour. Based on these figures, the 
cost impact of the proposed AD on U.S. operators is estimated to be 
$24,120, or $360 per airplane.
    The cost impact figure discussed above is based on assumptions that 
no operator has yet accomplished any of the proposed requirements of 
this AD action, and that no operator would accomplish those actions in 
the future if this AD were not adopted.

Regulatory Impact

    The regulations proposed herein would not have substantial direct 
effects 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. Therefore, in 
accordance with Executive Order 12612, it is determined that this 
proposal would not have sufficient federalism implications to warrant 
the preparation of a Federalism Assessment.
    For the reasons discussed above, I certify that 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) if promulgated, 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. A copy of the draft 
regulatory evaluation prepared for this action is contained in the 
Rules Docket. A copy of it may be obtained by contacting the Rules 
Docket at the location provided under the caption ADDRESSES.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

The Proposed Amendment

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration proposes to amend 
part 39 of the Federal Aviation Regulations (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. Section 39.13 is amended by adding the following new 
airworthiness directive:

Airbus Industrie: Docket 97-NM-178-AD.

    Applicability: Model A300-600 series airplanes, as listed in 
Airbus Service Bulletin A300-57A6087, dated August 5, 1997; and 
Model A300 series airplanes, as listed in Airbus Service Bulletin 
A300-57A0234, dated August 5, 1997; certificated in any category.

    Note 1: This AD applies to each airplane identified in the 
preceding applicability provision, regardless of whether it has been 
otherwise modified, altered, or repaired in the area subject to the 
requirements of this AD. For airplanes that have been modified, 
altered, or repaired so that the performance of the requirements of 
this AD is affected, the owner/operator must request approval for an 
alternative method of compliance in accordance with paragraph (d) of 
this AD. The request should include an assessment of the effect of 
the modification, alteration, or repair on the unsafe condition 
addressed by this AD; and, if the unsafe condition has not been 
eliminated, the request should include specific proposed actions to 
address it.

    Compliance: Required as indicated, unless accomplished 
previously.
    To detect and correct cracks in Gear Rib 5 of the main landing 
gear attachment fittings at the lower flange, which could result in 
reduced structural integrity of the airplane, accomplish the 
following:
    (a) For Model A300 series airplanes that have accumulated more 
than 27,000 flight cycles as of the effective date of this AD: 
Except as provided by paragraph (b) of this AD, within 40 flight 
cycles after the effective date of this AD, perform a detailed 
visual inspection to detect cracks in Gear Rib 5 of the main landing 
gear attachment fittings at the lower flange, in accordance with 
Airbus Service Bulletin A300-57A0234, dated August 5, 1997. 
Thereafter, repeat the inspection at intervals not to exceed 40 
flight cycles, until the actions required by paragraph (b) are 
accomplished.
    (b) For all airplanes: Perform a detailed visual and a high 
frequency eddy current inspection to detect cracks in Gear Rib 5 of 
the main landing gear attachment fittings at the lower flange, in 
accordance with Airbus Service Bulletin A300-57A6087 (for Model 
A300-600 series airplanes) or A300-57A0234 (for Model A300 series 
airplanes), both dated August 5, 1997; as applicable; at the time 
specified in paragraph (b)(1) or (b)(2) of this AD, as applicable. 
Accomplishment of the inspection required by this paragraph 
terminates the inspections required by paragraph (a) of this AD.
    (1) For airplanes that have accumulated 20,000 or more total 
flight cycles as of the effective date of this AD: Inspect within 
500

[[Page 62725]]

flight cycles after the effective date of this AD.
    (2) For airplanes that have accumulated less than 20,000 total 
flight cycles as of the effective date of this AD: Inspect prior to 
the accumulation of 18,000 total flight cycles, or within 1,500 
flight cycles after the effective date of this AD, whichever occurs 
later.
    (c) If any crack is detected during any inspection required by 
this AD, prior to further flight, repair in accordance with a method 
approved by the Manager, International Branch, ANM-116, FAA, 
Transport Airplane Directorate.
    (d) An alternative method of compliance or adjustment of the 
compliance time that provides an acceptable level of safety may be 
used if approved by the Manager, International Branch, ANM-116. 
Operators shall submit their requests through an appropriate FAA 
Principal Maintenance Inspector, who may add comments and then send 
it to the Manager, International Branch, ANM-116.

    Note 2: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the International Branch, ANM-116.

    (e) Special flight permits may be issued in accordance with 
Secs. 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 
21.197 and 21.199) to operate the airplane to a location where the 
requirements of this AD can be accomplished.

    Note 3: The subject of this AD is addressed in French 
airworthiness directive (CN) 97-274-230(B), dated September 24, 
1997.

    Issued in Renton, Washington, on November 18, 1997.
Stewart R. Miller,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 97-30858 Filed 11-24-97; 8:45 am]
BILLING CODE 4910-13-U