[Federal Register Volume 63, Number 21 (Monday, February 2, 1998)]
[Rules and Regulations]
[Pages 5224-5225]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-2285]



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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97-NM-178-AD; Amendment 39-10298; AD 98-03-06]
RIN 2120-AA64


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

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment adopts a new airworthiness directive (AD), 
applicable to certain Airbus Model A300 and A300-600 series airplanes, 
that requires 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 amendment is prompted by issuance of mandatory 
continuing airworthiness information by a foreign civil airworthiness 
authority. The actions specified by this 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: Effective March 9, 1998.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of March 9, 1998.

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: Norman B. Martenson, Manager, 
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: 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 certain Airbus Model A300 and 
A300-600 series airplanes was published in the Federal Register on 
November 25, 1997 (62 FR 62723). That action proposed to 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.

Comments

    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.

Conclusion

    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.

Cost Impact

    The FAA estimates that 67 Model A300 and A300-600 series 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 cost impact of the 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 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 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 U.S.C. 106(g), 40113, 44701.


Sec. 39.13  [Amended]

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

98-03-06  Airbus Industrie: Amendment 39-10298. 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 
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

[[Page 5225]]

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 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 
sections 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.
    (f) The actions shall be done in accordance with Airbus Service 
Bulletin A300-57A6087, dated August 5, 1997; or Airbus Service 
Bulletin A300-57A0234, dated August 5, 1997; as applicable. 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.

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

    (g) This amendment becomes effective on March 9, 1998.

    Issued in Renton, Washington, on January 23, 1998.
Stewart R. Miller,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 98-2285 Filed 1-30-98; 8:45 am]
BILLING CODE 4910-13-U