[Federal Register Volume 63, Number 185 (Thursday, September 24, 1998)]
[Rules and Regulations]
[Pages 50981-50983]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-25354]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 98-NM-82-AD; Amendment 39-10793; AD 98-20-27]
RIN 2120-AA64
Airworthiness Directives; Airbus Industrie Model A300-600 Series
Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
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[[Page 50982]]
SUMMARY: This amendment adopts a new airworthiness directive (AD),
applicable to all Airbus Model A300-600 series airplanes, that requires
repetitive inspections to detect fatigue cracking of the wing top skin
at the front spar joint; and a follow-on eddy current inspection 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 wing top skin at the
front spar joint, which could result in reduced structural integrity of
the airplane.
DATES: Effective October 29, 1998.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of October 29, 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 all Airbus Model A300-600 series
airplanes was published in the Federal Register on May 12, 1998 (63 FR
26109). That action proposed to require repetitive inspections to
detect fatigue cracking of the wing top skin at the front spar joint;
and a follow-on eddy current inspection and repair, if necessary.
Interested persons have been afforded an opportunity to participate
in the making of this amendment. Due consideration has been given to
the comments received.
One commenter expresses no objection to the proposed rule.
Request To Allow Flight With Known Cracks
One commenter recommends that the proposed AD be revised to allow
continued operation of an unrepaired airplane following detection of
cracks, utilizing the allowable damage limits and temporary repairs
described in Airbus Service Bulletin A300-57-6045. The commenter
expresses confidence that allowing continued flight within the
allowable crack limits and with the temporary repairs specified in the
service bulletin will provide the necessary level of safety. The
commenter further states that the manufacturer has not identified a
permanent repair for the area, nor has a preventive modification been
identified that would allow termination of the inspections required by
this proposed AD. Additionally, the commenter notes that the area where
the cracks may occur would require an extensive internal repair that
has not been developed at this time. If such cracking occurs, an
airplane could be grounded for a long time period while a repair is
developed, analyzed, and approved.
The FAA does not concur. It is the FAA's policy to require repair
of known cracks prior to further flight (except in certain cases of
unusual need). This policy is based on the fact that such damaged
airplanes do not conform to the FAA certificated type design, and
therefore, are not airworthy until a properly approved repair is
incorporated. Although the referenced service bulletin specifies
temporary repairs for certain crack findings, it does not provide such
repairs for cracking outside certain limits. For those cases, the
service bulletin specifies that, depending upon crack length, operators
should either contact the manufacturer for appropriate repairs or
accomplish repetitive visual inspections at specified intervals.
Therefore, the FAA has determined that, due to the safety implications
and consequences associated with cracking of the wing top skin at the
front spar joint, any subject area that is found to be cracked must be
addressed, prior to further flight, in accordance with a method
approved by the FAA.
Later Revision of Service Bulletin
One commenter has provided a copy of Airbus Service Bulletin A300-
57-6045, Revision 02, dated April 21, 1998, including Appendix 1,
Revision 02, dated April 21, 1998, but makes no specific request in
regard to this revision. Airbus Service Bulletin A300-57-6045, Revision
1, dated August 3, 1994, including Appendix 1, Revision 1, dated August
3, 1994, was cited in the proposed AD as the appropriate source of
service information for accomplishment of the actions required by this
AD. The FAA has reviewed Revision 02 of the service bulletin and has
determined that it contains no substantive differences from Revision 1.
Therefore, the final rule has been revised to add Revision 02 as an
appropriate source of service information.
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 previously
described. 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 54 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 inspection, and that the average
labor rate is $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 $6,480, or $120 per airplane, per inspection cycle.
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.
[[Page 50983]]
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:
98-20-27 Airbus Industrie: Amendment 39-10793. Docket 98-NM-82-AD.
Applicability: All Model A300-600 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 (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 detect and correct fatigue cracking of the wing top skin at
the front spar joint, which could result in reduced structural
integrity of the airplane, accomplish the following:
(a) Prior to the accumulation of 22,000 total flight cycles, or
within 2,000 flight cycles after the effective date of this AD,
whichever occurs later, perform a detailed visual inspection to
detect fatigue cracking of the wing top skin at the front spar
joint, in accordance with Airbus Service Bulletin A300-57-6045,
Revision 1, dated August 3, 1994, including Appendix 1, Revision 1,
dated August 3, 1994; or Airbus Service Bulletin A300-57-6045,
Revision 02, dated April 21, 1998, including Appendix 1, Revision
02, dated April 21, 1998. Repeat the detailed visual inspection
thereafter at intervals not to exceed 8,000 flight cycles.
(b) If any cracking is suspected or detected during any
inspection required by paragraph (a) of this AD, prior to further
flight, perform an eddy current inspection to confirm the findings
of the visual inspection, in accordance with Airbus Service Bulletin
A300-57-6045, Revision 1, dated August 3, 1994, including Appendix
1, Revision 1, dated August 3, 1994; or Airbus Service Bulletin
A300-57-6045, Revision 02, dated April 21, 1998, including Appendix
1, Revision 02, dated April 21, 1998. If any cracking is detected
during any eddy current inspection, prior to further flight, repair
in accordance with a method approved by the Manager, International
Branch, ANM-116, FAA, Transport Airplane Directorate, or the
Direction Generale de l'Aviation Civile or (its delegated agent).
(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, 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.
(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 A300-57-6045, Revision 1, dated August 3, 1994, including
Appendix 1, Revision 1, dated August 3, 1994; or Airbus Service
Bulletin A300-57-6045, Revision 02, dated April 21, 1998, including
Appendix 1, Revision 02, dated April 21, 1998. Revision 1 of Airbus
Service Bulletin A300-57-6045 contains the following list of
effective pages:
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Revision level
Page No. shown on page Date shown on page
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1-10.......................... 1................ August 3, 1994.
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Appendix 1
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1-2........................... 1................ August 3, 1994.
3-6........................... Original......... March 18, 1993.
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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 97-374-238(B), dated December 3, 1997.
(f) This amendment becomes effective on October 29, 1998.
Issued in Renton, Washington, on September 16, 1998.
S.R. Miller,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 98-25354 Filed 9-23-98; 8:45 am]
BILLING CODE 4910-13-U
