[Federal Register Volume 63, Number 31 (Tuesday, February 17, 1998)]
[Rules and Regulations]
[Pages 7642-7643]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-3260]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 97-NM-240-AD; Amendment 39-10323; AD 98-04-10]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A300 and 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 all Airbus Model A300 and A300-600 series airplanes, that
requires repetitive inspections for cracking of the lugs of hinge
brackets of inner airbrakes (spoilers) No. 1 and No. 2, and corrective
action, if necessary. This amendment is prompted by the issuance of
mandatory continuing airworthiness information by a foreign civil
airworthiness authority. The actions specified by this AD are intended
to prevent detachment of the spoilers and consequent reduced
controllability of the airplane.
DATES: Effective March 24, 1998.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of March 24, 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 and A300-600
series airplanes was published in the Federal Register on November 6,
1997 (62 FR 60047). That action proposed to require repetitive
inspections for cracking of the lugs of hinge brackets of inner
airbrakes (spoilers) No. 1 and No. 2, and corrective action, if
necessary.
Comments
Interested persons have been afforded an opportunity to participate
in the making of this amendment. No comments were submitted in response
to the proposal or the FAA's determination of the cost to the public.
Clarification of Referenced Repair Drawings
The FAA has revised paragraph (b) of this final rule to clarify the
referenced repair drawings by adding the company name, the applicable
revision level, and the date of the drawings.
Conclusion
After careful review of the available data, including the
clarification 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 102 Model A300 and A300-600 series airplanes
of U.S. registry will be affected by this AD, that it will take
approximately 4 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 the AD on U.S. operators is estimated
to be $24,480, or $240 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.
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
[[Page 7643]]
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:
98-04-10 Airbus Industrie: Amendment 39-10323. Docket 97-NM-240-AD.
Applicability: All Model A300 and A300-600 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 (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 cracking of the lugs of hinge brackets of
inner airbrakes (spoilers) No. 1 and No. 2 of both wings, which
could result in detachment of the spoilers and consequent reduced
controllability of the airplane, accomplish the following:
(a) Perform a high frequency eddy current (HFEC) inspection for
cracking of the lugs of the center hinge brackets of spoilers No. 1
and No. 2, in accordance with Airbus Service Bulletin A300-57-0229
(for Model A300 series airplanes) or A300-57-6074 (for Model A300-
600 series airplanes), both dated October 16, 1996, as applicable.
Accomplish the inspection at the time specified in paragraph (a)(1),
(a)(2), or (a)(3), as applicable, of this AD. If any discrepancy is
found, prior to further flight, perform the follow-on actions
specified in the Accomplishment Instructions of the applicable
service bulletin. Repeat the HFEC inspection thereafter at intervals
not to exceed 8,200 flight cycles.
(1) For airplanes that have accumulated less than 23,200 total
flight cycles as of the effective date of this AD: Inspect prior to
the accumulation of 16,000 total flight cycles, or within 1,000
flight cycles after the effective date of this AD, whichever occurs
later.
(2) For airplanes that have accumulated 23,200 total flight
cycles or more, but less than 36,500 total flight cycles as of the
effective date of this AD: Inspect within 500 flight cycles after
the effective date of this AD.
(3) For airplanes that have accumulated 36,500 total flight
cycles or more as of the effective date of this AD: Inspect within
50 flight cycles after the effective date of this AD.
(b) Airbus Service Bulletins A300-57-6074 and A300-57-0229, both
dated October 16, 1996, specify that the actions required by
paragraph (a) of this AD may be accomplished in accordance with a
method ``left to the operator's discretion.'' [Operators may use a
discretionary method only if that method has been approved as an
alternative method of compliance in accordance with paragraph (c) of
this AD.] Therefore, this AD requires that the replacement of a
bracket as required by paragraph (a) be accomplished in accordance
with the procedures specified in British Aerospace Repair Drawings
(for Airbus Model A300 and A300-600 series airplanes) R572-40205,
Revision F, dated August 12, 1997 (for a center hinge bracket), and/
or R572-40208, Revision B, dated August 12, 1997 (for an inner or
outer hinge bracket), as applicable.
(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, 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, 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 inspections shall be done in accordance with Airbus
Service Bulletin A300-57-0229, dated October 16, 1996, or Airbus
Service Bulletin A300-57-6074, dated October 16, 1996; as
applicable. The replacement shall be done in accordance with the
following British Aerospace Repair, as applicable, which contain the
specified list of effective pages:
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Repair drawings referenced and Revision level
date Sheet No. shown on sheet Date shown on sheet
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572-40205, Revision F, August 12, 1, 8, 13-15............... F August 12, 1997.
1997.
2-7, 9-12................ A March 6, 1996.
572-40208, Revision B, August 12, 1, 6, 8-10................ B August 12, 1997.
1997.
2-5, 7.................... A February 21, 1996.
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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 97-080-211(B)R1, dated May 21, 1997.
(f) This amendment becomes effective on March 24, 1998.
Issued in Renton, Washington, on February 4, 1998.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 98-3260 Filed 2-13-98; 8:45 am]
BILLING CODE 4910-13-U
