AD 2002-04-02

[Federal Register Volume 67, Number 35 (Thursday, February 21, 2002)]
[Rules and Regulations]
[Pages 7947-7949]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 02-3849]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-NM-390-AD; Amendment 39-12659; AD 2002-04-02]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A300 F4-605R 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 F4-605R airplanes, that 
requires installation of external doublers at frames 29 and 33. The 
actions specified by this AD are intended to prevent fatigue cracking 
of certain circumferential joints, which could result in reduced 
structural integrity of the fuselage in the vicinity of the upper deck 
cargo door.

DATES: Effective March 28, 2002.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of March 28, 2002.

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: Tim Backman, Aerospace Engineer, 
International Branch, ANM-116, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
227-2797; fax (425) 227-1149.

[[Page 7948]]


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 F4-605R 
airplanes was published in the Federal Register on April 30, 2001 (66 
FR 21292). That action proposed to require installation of external 
doublers at frames 29 and 33.

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the comment received.

Request To Expand Applicability of AD

    The commenter, the manufacturer, says that French airworthiness 
directive 2000-456-323(B), issued by the Direction Generale de 
l'Aviation Civile (DGAC), applies to both Airbus Model A300 F4-605R 
production freighters and Model A300 series airplanes that have been 
converted to freighter configurations by supplemental type certificates 
(STCs) approved by the DGAC. However, the notice of proposed rulemaking 
(NPRM) issued by the FAA does not apply to airplanes that have been 
converted to freighter configurations. The commenter requests that the 
applicability of the AD be expanded to include Airbus Model A300 series 
airplanes which have been converted to freighter configurations by 
STC's approved by the FAA.
    The FAA does not concur. The service bulletins cited by the DGAC in 
the French airworthiness directive apply only to production freighters 
and not to airplanes converted to freighter configurations in 
accordance with STCs. To address these converted airplanes, the FAA 
plans to work with the holders of STCs for those airplanes to evaluate 
the upper fuselage circumferential joints for fatigue. Depending upon 
the results, the FAA may issue further rulemaking addressing those 
airplanes.

Conclusion

    After careful review of the available data, including the comment 
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 32 Model A300 F4-605R airplanes of U.S. 
registry will be affected by this AD, that it will take approximately 
85 work hours per airplane to accomplish the required actions, and that 
the average labor rate is $60 per work hour. Required parts will cost 
approximately $1,820 per airplane. Based on these figures, the cost 
impact of the AD on U.S. operators is estimated to be $221,440 or 
$6,920 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. The cost impact figures discussed 
in AD rulemaking actions represent only the time necessary to perform 
the specific actions actually required by the AD. These figures 
typically do not include incidental costs, such as the time required to 
gain access and close up, planning time, or time necessitated by other 
administrative actions.

Regulatory Impact

    The regulations adopted herein will 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. Therefore, it 
is determined that this final rule does not have federalism 
implications under Executive Order 13132.
    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:

2002-04-02  Airbus Industrie: Amendment 39-12659. Docket 2000-NM-
390-AD.

    Applicability: Model A300 F4-605R airplanes, certificated in any 
category, except those on which Airbus production Modification 12081 
or the modification specified by Airbus Service Bulletin A300-53-
6119, Revision 01, dated September 25, 2000, has been installed.

    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 (b) 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 prevent fatigue cracking of certain circumferential joints, 
which could result in reduced structural integrity of the fuselage 
in the vicinity of the upper deck cargo door, accomplish the 
following:

Installation of Doublers

    (a) Before the airplane accumulates 10,000 total flight cycles, 
or within 6 months after the effective date of this AD, whichever 
occurs later: Install external doublers at frames 29 and 33, in 
accordance with Airbus Service Bulletin A300-53-6119, Revision 01, 
dated September 25, 2000.

Alternative Methods of Compliance

    (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, International Branch, ANM-116, 
Transport Airplane Directorate, FAA. 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.

Special Flight Permits

    (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.

Incorporation by Reference

    (d) The installation shall be done in accordance with Airbus 
Service Bulletin

[[Page 7949]]

A300-53-6119, Revision 01, dated September 25, 2000. 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 2000-456-323(B), dated November 15, 2000.

Effective Date

    (e) This amendment becomes effective on March 28, 2002.

    Issued in Renton, Washington, on February 11, 2002.
Vi L. Lipski,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 02-3849 Filed 2-20-02; 8:45 am]
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