[Federal Register Volume 63, Number 237 (Thursday, December 10, 1998)]
[Rules and Regulations]
[Pages 68167-68169]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-32623]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 97-NM-153-AD; Amendment 39-10933; AD 98-25-07]
RIN 2120-AA64
Airworthiness Directives; Airbus 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 Model A300-600 series airplanes, that
requires repetitive inspections to detect cracks in the angle fitting
at frame 40 of the center wing box, and corrective actions, if
necessary; and eventual modification of that angle fitting, which
terminates the repetitive inspections. 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 prevent cracks in the center wing box angle fitting, which
could result in the failure of the center wing box at frame 40, and
consequent reduced structural integrity of the airplane.
DATES: Effective January 14, 1999.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of January 14, 1999.
[[Page 68168]]
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 A300-600
series airplanes was published as a supplemental notice of proposed
rulemaking (NPRM) in the Federal Register on October 14, 1998 (63 FR
55063). That action proposed to require repetitive inspections to
detect cracks in the angle fitting at frame 40 of the center wing box,
and corrective actions, if necessary; and eventual modification of that
angle fitting, which would terminate the repetitive inspections.
Comments
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.
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 54 Model A300-600 series airplanes of U.S.
registry will be affected by this AD.
It will take approximately 36 work hours per airplane to accomplish
the required inspection, at an average labor rate of $60 per work hour.
Based on these figures, the cost impact of the inspection required by
this AD on U.S. operators is estimated to be $116,640, or $2,160 per
airplane, per inspection cycle.
It will take approximately 754 work hours per airplane to
accomplish the required modification, at an average labor rate of $60
per work hour. Required parts will cost approximately $11,605 per
airplane. Based on these figures, the cost impact of the modification
required by this AD on U.S. operators is estimated to be $3,069,630, or
$56,845 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 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:
98-25-07 Airbus: Amendment 39-10933. Docket 97-NM-153-AD.
Applicability: Model A300-600 series airplanes on which Airbus
Modification 10453 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 (e) 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 cracks in the center wing box angle fitting, which
could result in the failure of the center wing box at frame 40, and
consequent reduced structural integrity of the airplane, accomplish
the following:
(a) Prior to the accumulation of the threshold specified in
Table 1 of this AD, as applicable, or within 1,500 flight cycles
after the effective date of this AD, whichever occurs later: Perform
a detailed visual, eddy current, or liquid penetrant inspection to
detect cracking in the angle fitting of frame 40 (both left and
right), with the nut removed, in accordance with Airbus Service
Bulletin A300-57-6052, Revision 1, dated July 22, 1996. Thereafter,
repeat the inspections at the interval specified in Table 1 of this
AD, as applicable, until the actions required by paragraph (c) of
this AD have been accomplished.
[[Page 68169]]
Table 1
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Eddy current/
Visual liquid
Threshold inspection penetrant
Average flight time (AFT): flight hours/flight cycles (flight interval inspection
cycles) (flight interval
cycles) (flight
cycles)
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2.10-2.49....................................................... 5,900 4,700 5,300
2.50-2.99....................................................... 5,600 4,400 4,900
3.00-3.49....................................................... 5,200 4,100 4,600
3.50-3.99....................................................... 4,800 3,800 4,200
4.00-4.49....................................................... 4,400 3,500 3,900
4.50-4.99....................................................... 4,000 3,200 3,500
5.00-5.49....................................................... 3,600 2,800 3,200
5.50-5.99....................................................... 3,200 2,500 2,800
6.00-6.50....................................................... 2,800 2,200 2,500
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(b) Except as provided by paragraph (d) of this AD, if any crack
is found during an inspection required by paragraph (a) of this AD,
prior to further flight, accomplish follow-on corrective actions in
accordance with the procedures specified in Airbus Service Bulletin
A300-57-6052, Revision 1, dated July 22, 1996.
(c) Within 4 years after the effective date of this AD, modify
the angle fitting at frame 40 (both left and right) in accordance
with Airbus Service Bulletin A300-57-6053, Revision 1, dated October
31, 1995. Accomplishment of the modification constitutes terminating
action for the repetitive inspections required by paragraph (a) of
this AD.
(d) If any crack is found during an inspection required by
paragraph (a) of this AD, and the applicable service bulletin
specifies to contact the manufacturer for an appropriate action:
Prior to further flight, repair in accordance with a method approved
by the Manager, International Branch, ANM-116, FAA, Transport
Airplane Directorate.
(e) 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.
(f) 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.
(g) Except as provided by paragraph (d) of this AD, the actions
shall be done in accordance with Airbus Service Bulletin A300-57-
6052, Revision 1, dated July 22, 1996; and Airbus Service Bulletin
A300-57-6053, Revision 1, dated October 31, 1995, which contains the
following list of effective pages:
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Revision level shown
Page No. on page Date shown on page
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1, 7-9, 11-15, 19-24, 35, 36, 41, 42, 45-47.... 1 October 31, 1995.
2-6, 10, 16-18, 25-34, 37-40, 43, 44........... Original February 21, 1995.
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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) 95-111-181(B) R1, dated October 23,
1996.
(h) This amendment becomes effective on January 14, 1999.
Issued in Renton, Washington, on December 2, 1998.
John W. McGraw,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 98-32623 Filed 12-9-98; 8:45 am]
BILLING CODE 4910-13-P
