Airworthiness Directives; Airbus Model A300 B2 Series Airplanes and Model A300 B4-2C, B4-103, and B4-203 Series Airplanes

[Federal Register Volume 66, Number 248 (Thursday, December 27, 2001)]
[Rules and Regulations]
[Pages 66733-66734]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 01-31428]



[[Page 66733]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-NM-247-AD; Amendment 39-12572; AD 2001-26-08]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A300 B2 Series Airplanes 
and Model A300 B4-2C, B4-103, and B4-203 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 all Airbus Model A300 B2 series airplanes and Model A300 
B4-2C, B4-103, and B4-203 series airplanes, that requires identifying 
the types and areas of repairs on the airplane between frame 10 and 
frame 80, and performing follow-on actions for certain repairs. These 
actions are necessary to detect and correct fatigue cracking of certain 
repairs of the fuselage between frame 10 and frame 80, which could 
result in reduced structural integrity of the airplane. These actions 
are intended to address the identified unsafe condition.

DATES: Effective January 31, 2002.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of January 31, 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: Dan Rodina, Aerospace Engineer, 
International Branch, ANM-116, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
227-2125; 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 all Airbus Model A300 B2 and B4 
series airplanes was published in the Federal Register on August 28, 
2001 (66 FR 45192). That action proposed to require identifying the 
types and areas of repairs on the airplane between frame 10 and frame 
80, and performing follow-on actions for certain repairs.

Comments

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

Revise Applicability Statement of Proposed AD

    One commenter requests that the FAA revise the applicability 
statement of the proposed AD to exclude Model A300 B4-600 series 
airplanes. The commenter states that this is an appropriate change 
because French airworthiness directive 2000-261-312(B), dated June 28, 
2000 (which is the French airworthiness directive corresponding to the 
proposed AD), and Airbus Service Bulletin A300-53-0313, Revision 01, 
dated April 27, 1999 (which the proposed AD refers to as the 
appropriate source of service information for certain actions therein), 
do not apply to Model A300 B4-600 series airplanes.
    We concur with the commenter's request. We do not intend this AD to 
apply to Model A300 B4-600 series airplanes. However, based on the 
commenter's request, we recognize that the identification of the 
affected airplanes models in the proposed rule could potentially 
confuse some owner/operators. Therefore, we have revised the 
applicability statement of this AD, as well as the title and summary 
sections in the preamble of this AD, to clarify that this AD applies to 
all Airbus Model A300 B2 series airplanes and Model A300 B4-2C, B4-103, 
and B4-203 series airplanes.

Request To Provide for Modified Airplanes

    One commenter, a supplemental type certificate (STC) holder, 
requests that we provide a different follow-on action for airplanes 
that have been converted from passenger airplanes to freighters 
according to a specific STC. The commenter explains that such 
conversion results in increased loads on certain fuselage skin panels 
on the airplane. The commenter states that, if an operator of a 
converted airplane identifies an existing repair that is subject to 
this AD on one of the fuselage skin panels affected by the conversion, 
the operator should contact the STC holder for assistance in evaluating 
the repair.
    We do not concur that any change is necessary in this regard, 
though we do concur that the operator should contact the STC holder for 
assistance in evaluating the repair. Note 1 of this AD specifies that, 
if an airplane has been modified in such a way that the AD requirements 
have been affected, the owner/operator must request approval of an 
alternative method of compliance in accordance with paragraph (d) of 
this AD. This provision would apply to airplanes modified per the 
commenter's STC.

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 with the change described 
previously. The FAA has determined that this change will neither 
increase the economic burden on any operator nor increase the scope of 
the AD.

Cost Impact

    The FAA estimates that 13 airplanes of U.S. registry will be 
affected by this AD, that it will take approximately 2 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 
this AD on U.S. operators is estimated to be $1,560, or $120 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)

[[Page 66734]]

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:

2001-26-08  Airbus: Amendment 39-12572. Docket 2000-NM-247-AD.

    Applicability: All Model A300 B2 series airplanes and Model A300 
B4-2C, B4-103, and B4-203 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 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 fatigue cracking of certain repairs of the 
fuselage between frame 10 and frame 80, which could result in 
reduced structural integrity of the airplane, accomplish the 
following:

Identification of Repairs

    (a) Before 10,000 total landings, or before 2,500 landings after 
the effective date of this AD, whichever occurs later: Identify the 
types and areas of repairs on the airplane between frame 10 and 
frame 80, as specified in Airbus Service Bulletin A300-53-0313, 
Revision 01, dated April 27, 1999. Do the actions per the 
Accomplishment Instructions of the service bulletin. If none of the 
repairs specified in the service bulletin are found, no additional 
action is needed under this AD.

Follow-On Actions

    (b) If, during the inspection, any repair is found that meets 
the criteria specified in Airbus Service Bulletin A300-53-0313, 
Revision 01, dated April 27, 1999: Do either an eddy current or 
ultrasonic inspection, depending on the type of repair found, to 
detect cracking of the applicable area identified in Flow Chart 1, 
Figure 1, Sheet 1, of the service bulletin. Do the inspection at the 
time and in the manner specified in the service bulletin. Based on 
the results of the inspection, take the actions shown in the 
following table:

                       Table 1.--Follow-On Actions
------------------------------------------------------------------------
   If the following is found:           Then--        Per this schedule:
------------------------------------------------------------------------
(1) No cracking.................  Repeat the          At least every
                                   inspection.         2,500 landings.
(2) Any cracking................  Replace the repair  Before further
                                   per a method        flight.
                                   approved by
                                   either the
                                   Manager,
                                   International
                                   Branch, ANM-116,
                                   FAA, Transport
                                   Airplane
                                   Directorate, or
                                   the Direction
                                   Generale de
                                   l'Aviation Civile
                                   (DGAC) (or its
                                   delegated agent).
------------------------------------------------------------------------

Terminating Action

    (c) Replacement of a repair that is specified in Airbus Service 
Bulletin A300-53-0313, Revision 01, dated April 27, 1999, per a 
method approved by either the Manager, International Branch, ANM-
116, or the DGAC (or its delegated agent), terminates the 
requirements of this AD.

Alternative Methods of Compliance

    (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.

Special Flight Permits

    (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.

Incorporation by Reference

    (f) Except as provided in Table 1 and paragraph (c) of this AD, 
the actions shall be done in accordance with Airbus Service Bulletin 
A300-53-0313, Revision 01, dated April 27, 1999. 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 2000-261-312(B), dated June 28, 2000.

Effective Date

    (g) This amendment becomes effective on January 31, 2002.

    Issued in Renton, Washington, on December 14, 2001.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 01-31428 Filed 12-26-01; 8:45 am]
BILLING CODE 4910-13-P

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