[Federal Register Volume 62, Number 215 (Thursday, November 6, 1997)]
[Proposed Rules]
[Pages 60047-60049]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 97-29342]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 97-NM-240-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A300 and A300-600 Series
Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: This document proposes the adoption of a new airworthiness
directive (AD) that is applicable to all Airbus Model A300 and A300-600
series airplanes. This proposal would 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. This
proposal is prompted by the issuance of mandatory continuing
airworthiness information by a foreign civil airworthiness authority.
The actions specified by the proposed AD are intended to prevent
detachment of the spoilers and consequent reduced controllability of
the airplane.
DATES: Comments must be received by December 8, 1997.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-103,
Attention: Rules Docket No. 97-NM-240-AD, 1601 Lind Avenue, SW.,
Renton, Washington 98055-4056. Comments may be inspected at this
location between 9:00 a.m. and 3:00 p.m., Monday through Friday, except
Federal holidays.
The service information referenced in the proposed rule may be
obtained from Airbus Industrie, 1 Rond Point Maurice Bellonte, 31707
Blagnac Cedex, France. This information may be examined at the FAA,
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton,
Washington.
[[Page 60048]]
FOR FURTHER INFORMATION CONTACT: Charles D. Huber, Aerospace Engineer,
Standardization Branch, ANM-113, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425)
227-2589; fax (425) 227-1149.
SUPPLEMENTARY INFORMATION:
Comments Invited
Interested persons are invited to participate in the making of the
proposed rule by submitting such written data, views, or arguments as
they may desire. Communications shall identify the Rules Docket number
and be submitted in triplicate to the address specified above. All
communications received on or before the closing date for comments,
specified above, will be considered before taking action on the
proposed rule. The proposals contained in this notice may be changed in
light of the comments received.
Comments are specifically invited on the overall regulatory,
economic, environmental, and energy aspects of the proposed rule. All
comments submitted will be available, both before and after the closing
date for comments, in the Rules Docket for examination by interested
persons. A report summarizing each FAA-public contact concerned with
the substance of this proposal will be filed in the Rules Docket.
Commenters wishing the FAA to acknowledge receipt of their comments
submitted in response to this notice must submit a self-addressed,
stamped postcard on which the following statement is made: ``Comments
to Docket Number 97-NM-240-AD.'' The postcard will be date stamped and
returned to the commenter.
Availability of NPRMs
Any person may obtain a copy of this NPRM by submitting a request
to the FAA, Transport Airplane Directorate, ANM-103, Attention: Rules
Docket No. 97-NM-240-AD, 1601 Lind Avenue, SW., Renton, Washington
98055-4056.
Discussion
The Direction Generale de l'Aviation Civile (DGAC), which is the
airworthiness authority for France, notified the FAA that an unsafe
condition may exist on all Airbus Model A300 and A300-600 series
airplanes. The DGAC advises that it received four reports indicating
that, during routine maintenance, fatigue cracking was detected in lugs
of the center hinge bracket of an inner airbrake (spoiler) No. 1.
Fatigue cracking and failure of center hinge brackets due to increased
loading could result in propagation of cracks of the inner and outer
hinge brackets. Such fatigue cracking, if not detected and corrected in
a timely manner, could result in detachment of the spoilers and
consequent reduced controllability of the airplane.
Explanation of Relevant Service Information
Airbus has issued Service Bulletins A300-57-0229 (for Model A300
series airplanes) and A300-57-6074 (for Model A300-600 series
airplanes), both dated October 16, 1996. These service bulletins
describe procedures for repetitive high frequency eddy current (HFEC)
inspections for cracking of the lugs of hinge brackets of spoilers No.
1 and No. 2 of both wings; and replacement, with a serviceable bracket,
of any bracket having a cracked lug. The DGAC classified these service
bulletins as mandatory and issued French airworthiness directive 97-
080-211(B)R1, dated May 21, 1997, in order to assure the continued
airworthiness of these airplanes in France.
FAA's Conclusions
These airplane models are manufactured in France and are type
certificated for operation in the United States under the provisions of
section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and
the applicable bilateral airworthiness agreement. Pursuant to this
bilateral airworthiness agreement, the DGAC has kept the FAA informed
of the situation described above. The FAA has examined the findings of
the DGAC, reviewed all available information, and determined that AD
action is necessary for products of this type design that are
certificated for operation in the United States.
Explanation of Requirements of Proposed Rule
Since an unsafe condition has been identified that is likely to
exist or develop on other airplanes of the same type design registered
in the United States, the proposed AD would require accomplishment of
the actions specified in the service bulletins described previously,
except as described below.
Differences Between the Proposed AD and the Service Bulletins
Airbus Service Bulletins A300-57-6074 and A300-57-0229, both dated
October 16, 1996, specify that the corrective actions required by this
proposed AD may be accomplished in accordance with a method ``left to
the operator's discretion.'' However, operators would use a
discretionary method only if that method has been approved by the FAA.
Therefore, this AD requires that the actions be accomplished in
accordance with the procedures specified in Repair Drawing R57240205
(for a center hinge bracket) and/or R57240208 (for an inner or outer
hinge bracket), as applicable.
Cost Impact
The FAA estimates that 102 Airbus Model A300 and A300-600 series
airplanes of U.S. registry would be affected by this proposed AD, that
it would take approximately 4 work hours per airplane to accomplish the
proposed actions, and that the average labor rate is $60 per work hour.
Based on these figures, the cost impact of the proposed 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 proposed 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 proposed herein would 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
proposal would not have sufficient federalism implications to warrant
the preparation of a Federalism Assessment.
For the reasons discussed above, I certify that this proposed
regulation (1) is not a ``significant regulatory action'' under
Executive Order 12866; (2) is not a ``significant rule'' under the DOT
Regulatory Policies and Procedures (44 FR 11034, February 26, 1979);
and (3) if promulgated, 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 copy of the draft
regulatory evaluation prepared for this action is contained in the
Rules Docket. A copy of it may be obtained by contacting the Rules
Docket at the location provided under the caption ADDRESSES.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
The Proposed Amendment
Accordingly, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration proposes to amend
part
[[Page 60049]]
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:
Airbus Industrie: 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
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 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 Repair Drawing R57240205 (for a
center hinge bracket) and/or R57240208 (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, 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.
Note 3: The subject of this AD is addressed in French
airworthiness directive 97-080-211(B)R1, dated May 21, 1997.
Issued in Renton, Washington, on October 30, 1997.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 97-29342 Filed 11-5-97; 8:45 am]
BILLING CODE 4910-13-U
