[Federal Register Volume 62, Number 125 (Monday, June 30, 1997)]
[Rules and Regulations]
[Pages 35072-35073]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 97-16854]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 96-NM-182-AD; Amendment 39-10059; AD 97-14-02]
RIN 2120-AA64
Airworthiness Directives; Airbus Industrie Model 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 Industrie Model A300-600 series airplanes,
that requires repetitive eddy current inspections to detect cracks of
the outer skin of the fuselage at certain frames, and repair or
reinforcement of the structure at the frames, if necessary. This
amendment also requires eventual reinforcement of the structure at
certain frames, which, when accomplished, terminates the repetitive
inspections. This amendment is prompted by a report indicating that
fatigue cracks were found in the area of certain frames. The actions
specified by this AD are intended to prevent such fatigue cracking,
which could reduce the structural integrity of the airframe and result
in rapid decompression of the airplane.
DATES: Effective August 4, 1997.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of August 4, 1997.
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,
Standardization Branch, ANM-113, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425)
227-2797; 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 Industrie Model
A300-600 series airplanes was published in the Federal Register on
March 26, 1997 (62 FR 14361). That action proposed to require
repetitive eddy current inspections to detect cracks of the outer skin
of the fuselage at frames 28A and 30A above stringer 30; and repair or
reinforcement of the structure of the frames, if necessary.
Additionally, that action proposed to require eventual reinforcement of
the structure at frames 28 and 29, and frames 30 and 31, between
stringers 29 and 30, which, when accomplished, terminates the
repetitive inspections.
Interested persons have been afforded an opportunity to participate
in the making of this amendment. Due consideration has been given to
the single comment received.
The commenter supports the proposed rule.
The FAA has revised paragraph (a)(2) of this AD by adding the
phrase ``prior to further flight'' to clarify the compliance time for
the repair or reinforcement of any cracking found. This phrase was
omitted inadvertently from the proposed rule.
The FAA also has removed NOTE 1 of the proposal, which excluded
certain airplanes from the applicability of this AD. The FAA considers
it unnecessary to include this information in the final rule.
Conclusion
After careful review of the available data, including the changes
noted above, the FAA has determined that air safety and the public
interest require the adoption of the rule with the changes previously
described. The FAA has determined that these changes will neither
increase the economic burden on any operator nor increase the scope of
the AD.
Cost Impact
The FAA estimates that 34 Airbus Industrie Model A300-600 series
airplanes of U.S. registry will be affected by this AD.
The eddy current inspection that is required by this AD will take
approximately 1 work hour per airplane to accomplish, at an average
labor rate of $60 per work hour. Based on these figures, the cost
impact of the required inspection on U.S. operators is estimated to be
$2,040, or $60 per airplane, per inspection cycle.
The reinforcement that is required by this AD will take
approximately 93 work hours per airplane to accomplish, at an average
labor rate of $60 per work hour. Required parts will cost approximately
$7,200 per airplane. Based on these figures, the cost impact of the
required modification on U.S. operators is estimated to be $434,520, or
$12,780 per airplane.
The cost impact figures discussed above are 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
[[Page 35073]]
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:
97-14-02 Airbus Industrie: Amendment 39-10059. Docket 96-NM-182-AD.
Applicability: Model A300-600 series airplanes on which Airbus
Modification 8683 was not accomplished during production, or on
which Airbus Modification 8684 has not been installed; certificated
in any category.
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 (c) 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 the fuselage outer skin at frames
28A and 30A, which could reduce the structural integrity of the
airframe and result in rapid decompression of the airplane,
accomplish the following:
(a) Prior to the accumulation of 14,100 total flight cycles, or
within 12 months after the effective date of the AD, whichever
occurs later, conduct an eddy current inspection to detect cracking
of the fuselage outer skin at frames 28A and 30A above stringer 30,
in accordance with Airbus Service Bulletin A300-53-6045, dated March
21, 1995, as revised by Change Notice No. O.A., dated June 1, 1995.
(1) If no cracking is found, repeat the inspection thereafter at
intervals not to exceed 4,500 flight cycles.
(2) If any cracking is found that is within the limits specified
in the service bulletin, prior to further flight, repair in
accordance with paragraph 2.D. of the Accomplishment Instructions of
Airbus Service Bulletin A300-53-6045, dated March 21, 1995, as
revised by Change Notice No. O.A., dated June 1, 1995; or reinforce
the structure at frames 28 and 29, and at frames 30 and 31, between
stringers 29 and 30, in accordance with Airbus Service Bulletin
A300-53-6037, dated March 21, 1995.
(i) If the repair is accomplished: After the repair, repeat the
eddy current inspection thereafter at intervals not to exceed 4,500
flight cycles.
(ii) If the reinforcement is accomplished: Such reinforcement
constitutes terminating action for the repetitive inspections
required by this AD.
(3) If any cracking is found that is outside the limits
specified in the service bulletin, prior to further flight,
reinforce the structure at frames 28 and 29, and at frames 30 and
31, between stringers 29 and 30, in accordance with Airbus Service
Bulletin A300-53-6037, dated March 21, 1995. Such reinforcement
constitutes terminating action for the repetitive inspections
required by this AD.
(b) Within 5 years after the effective date of this AD,
reinforce the structure at frames 28 and 29, and at frames 30 and
31, between stringers 29 and 30, in accordance with Airbus Service
Bulletin A300-53-6037, dated March 21, 1995. Such reinforcement
constitutes terminating action for the repetitive inspections
required by this AD.
(c) 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.
(d) 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.
(e) The actions shall be done in accordance with Airbus Service
Bulletin A300-53-6045, dated March 21, 1995, as revised by Change
Notice No. O.A., dated June 1, 1995; and Airbus Service Bulletin
A300-53-6037, dated March 21, 1995. 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.
(f) This amendment becomes effective on August 4, 1997.
Issued in Renton, Washington, on June 23, 1997.
S.R. Miller,
Acting Manager,
Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. 97-16854 Filed 6-27-97; 8:45 am]
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