[Federal Register Volume 60, Number 84 (Tuesday, May 2, 1995)]
[Proposed Rules]
[Pages 21470-21471]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 95-10710]



 ========================================================================
 Proposed Rules
                                                 Federal Register
 ________________________________________________________________________
 
 This section of the FEDERAL REGISTER contains notices to the public of 
 the proposed issuance of rules and regulations. The purpose of these 
 notices is to give interested persons an opportunity to participate in 
 the rule making prior to the adoption of the final rules.
 
 ========================================================================
 

  Federal Register / Vol. 60, No. 84 / Tuesday, May 2, 1995 / Proposed 
Rules  
[[Page 21470]]

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 95-NM-03-AD]


Airworthiness Directives; Airbus Model 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 all Airbus Model A300-600 series 
airplanes. This proposal would require repetitive inspections to detect 
cracks in the bottom skin of the wing in the area of the cutout for the 
pylon rear attachment fitting, and repair, if necessary. This proposal 
is prompted by a report indicating that, during full-scale fatigue 
testing, a crack was found in the bottom skin of the wing at the cutout 
for the aft pylon attachment fitting due to fatigue-related stress. The 
actions specified by the proposed AD are intended to prevent such 
fatigue-related cracking, which could result in reduced structural 
integrity of the wing.

DATES: Comments must be received by June 12, 1995.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-103, 
Attention: Rules Docket No. 95-NM-03-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: Stephen Slotte, Aerospace Engineer, 
Standardization Branch, ANM-113, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (206) 
227-2797; fax (206) 227-1320.

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 95-NM-03-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. 95-NM-03-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, recently notified the FAA that an 
unsafe condition may exist on all Airbus Model A300-600 series 
airplanes. The DGAC advises that, during full scale fatigue testing, a 
crack was found in the bottom skin of the wing at the cut out for the 
aft pylon attachment fitting after the airplane accumulated 
approximately 58,650 total simulated flights. Investigation revealed 
that such cracking was caused by fatigue-related stress. Such fatigue-
related cracking, if not detected and corrected in a timely manner, 
could result in reduced structural integrity of the wing.
    Airbus has issued Service Bulletin A300-57-6028, Revision 3, dated 
September 13, 1994, which describes procedures for repetitive detailed 
visual inspections to detect cracks in the bottom skin of the wing in 
the area of the cut out for the pylon rear attachment fitting, and 
repair, if necessary. The DGAC classified this service bulletin as 
mandatory and issued French airworthiness directive 94-069-158(B), 
dated March 30, 1994, in order to assure the continued airworthiness of 
these airplanes in France.
    This airplane model is manufactured in France and is type 
certificated for operation in the United States under the provisions of 
Sec. 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.
    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 repetitive detailed 
visual inspections to detect cracks in the wing bottom skin of the wing 
in the area of the cut out for the pylon rear attachment fitting, and 
repair, if necessary. The inspection actions would be required to be 
accomplished in accordance with the service bulletin described 
previously. Any necessary repair of the wing bottom skin would be 
required to be accomplished in accordance with a method approved by the 
FAA.
    As a result of recent communications with the Air Transport 
Association [[Page 21471]] (ATA) of America, the FAA has learned that, 
in general, some operators may misunderstand the legal effect of AD's 
on airplanes that are identified in the applicability provision of the 
AD, but that have been altered or repaired in the area addressed by the 
AD. The FAA points out that all airplanes identified in the 
applicability provision of an AD are legally subject to the AD. If an 
airplane has been altered or repaired in the affected area in such a 
way as to affect compliance with the AD, the owner or operator is 
required to obtain FAA approval for an alternative method of compliance 
with the AD, in accordance with the paragraph of each AD that provides 
for such approvals. A note has been included in this notice to clarify 
this long standing requirement.
    The FAA estimates that 35 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 
total cost impact of the proposed AD on U.S. operators is estimated to 
be $12,600, or $360 per airplane.
    The total 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.
    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. App. 1354(a), 1421 and 1423; 49 U.S.C. 
106(g); and 14 CFR 11.89.


Sec. 39.13  [Amended]

    2. Section 39.13 is amended by adding the following new 
airworthiness directive:

Airbus Industrie: Docket 95-NM-03-AD. -

    Applicability: All Model A300-600 series airplanes, certificated 
in any category.

    Note 1: This AD applies to each airplane identified in the 
preceding applicability provision, regardless of whether it has been 
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 use the authority 
provided in paragraph (b) to request approval from the FAA. This 
approval may address either no action, if the current configuration 
eliminates the unsafe condition; or different actions necessary to 
address the unsafe condition described in this AD. Such a request 
should include an assessment of the effect of the changed 
configuration on the unsafe condition addressed by this AD. In no 
case does the presence of any modification, alteration, or repair 
remove any airplane from the applicability of this AD.

    Compliance: Required as indicated, unless accomplished 
previously.
    To prevent reduced structural integrity of the wing, accomplish 
the following:
    (a) Prior to the accumulation of 24,000 total flight cycles 
since date of manufacture of the airplane, or within 750 flight 
cycles after the effective date of the AD, whichever occurs later, 
perform a detailed visual inspection to detect cracks in the bottom 
skin of the wing in the area of the cut out for the pylon rear 
attachment fitting, in accordance with Airbus Service Bulletin A300-
57-6028, Revision 3, dated September 13, 1994. Repeat the inspection 
thereafter at intervals not to exceed 9,000 flight cycles. If any 
crack is detected, prior to further flight, repair the wing bottom 
skin in accordance with a method approved by the Manager, 
Standardization Branch, ANM-113, FAA, Transport Airplane 
Directorate.
    (b) 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, Standardization Branch, ANM-13. 
Operators shall submit their requests through an appropriate FAA 
Principal Maintenance Inspector, who may add comments and then send 
it to the Manager, Standardization Branch, ANM-113.

    Note 2: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Standardization Branch, ANM-113.

    (c) 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.

    Issued in Renton, Washington, on April 26, 1995.
James V. Devany,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 95-10710 Filed 5-1-95; 8:45 am]
BILLING CODE 4910-13-U