Airworthiness Directives; Airbus Model A300-600 Series Airplanes

[Federal Register Volume 60, Number 178 (Thursday, September 14, 1995)]
[Rules and Regulations]
[Pages 47677-47678]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 95-21946]



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Federal Register / Vol. 60, No. 178 / Thursday, September 14, 1995 / 
Rules and Regulations


[[Page 47677]]


DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 95-NM-03-AD; Amendment 39-9355; AD 95-18-08]


Airworthiness Directives; Airbus Model A300-600 Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: This amendment adopts a new airworthiness directive (AD), 
applicable to all Airbus Model A300-600 series airplanes, that requires 
repetitive 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. This amendment 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 cut out for the aft pylon attachment 
fitting due to fatigue-related stress. The actions specified by this AD 
are intended to prevent such fatigue-related cracking, which could 
result in reduced structural integrity of the wing.

DATES: Effective October 16, 1995.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of October 16, 1995.

ADDRESSES: The service information referenced in this AD may be 
obtained from Airbus Industrie, 1 Rond Point Maurice Bellonte, 31707 
Blagnac Cedex, France. This information may be examined at the Federal 
Aviation Administration (FAA), Transport Airplane Directorate, Rules 
Docket, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of 
the Federal Register, 800 North Capitol Street NW., suite 700, 
Washington, DC.

FOR FURTHER INFORMATION CONTACT: Charles Huber, Aerospace Engineer, 
Standardization Branch, ANM-113, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (206) 
227-2589; fax (206) 227-1149.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) to include an airworthiness 
directive (AD) that is applicable to all Airbus Model A300-600 series 
airplanes was published in the Federal Register on May 2, 1995 (60 FR 
21470). That action proposed to require 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.
    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the two comments received.
    Both commenters support the proposed rule.
    After careful review of the available data, including the comments 
noted above, the FAA has determined that air safety and the public 
interest require the adoption of the rule as proposed.
    The FAA estimates that 35 airplanes of U.S. registry will be 
affected by this AD, that it will take approximately 6 work hours per 
airplane to accomplish the required actions, and that the average labor 
rate is $60 per work hour. Based on these figures, the total cost 
impact of the 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 
requirements of this AD action, and that no operator would accomplish 
those actions in the future if this AD were not adopted. -
    The regulations adopted herein will 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 final 
rule does not have sufficient federalism implications to warrant the 
preparation of a Federalism Assessment.
    For the reasons discussed above, I certify that this action (1) is 
not a ``significant regulatory action'' under Executive Order 12866; 
(2) is not a ``significant rule'' under 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. A final evaluation has been prepared for this action 
and it is contained in the Rules Docket. A copy of it may be obtained 
from the Rules Docket at the location provided under the caption 
ADDRESSES.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration amends 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 USC 106(g), 40101, 40113, 44701.


Sec. 39.13  [Amended]

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

95-18-08  Airbus Industrie: Amendment 39-9355. 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) of this AD 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 

[[Page 47678]]
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-113, 
FAA, Transport Airplane Directorate. 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.
    (d) The inspection shall be done in accordance with Airbus 
Service Bulletin A300-57-6028, Revision 3, dated September 13, 1994, 
which contains the specified effective pages:

------------------------------------------------------------------------
                                          Revision                      
                                            level                       
                Page No.                  shown on   Date shown on page 
                                            page-                       
------------------------------------------------------------------------
-1-6-...................................        3-  Sept. 13, 1994. -   
7-9-....................................        2-  Feb. 22, 1994.      
------------------------------------------------------------------------

This incorporation by reference was approved by the Director of the 
Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 
51. Copies may be obtained from Airbus Industrie, 1 Rond Point 
Maurice Bellonte, 31707 Blagnac Cedex, France. Copies may be 
inspected at the FAA, Transport Airplane Directorate, 1601 Lind 
Avenue, SW., Renton, Washington; or at the Office of the Federal 
Register, 800 North Capitol Street NW., suite 700, Washington, DC.
    -(e) This amendment becomes effective on October 16, 1995.

    Issued in Renton, Washington, on August 29, 1995.

Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.

[FR Doc. 95-21946 Filed 9-13-95; 8:45 am]

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