[Federal Register Volume 65, Number 1 (Monday, January 3, 2000)]
[Proposed Rules]
[Pages 91-93]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-34032]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 99-NM-304-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A300 Series Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: This document proposes the adoption of a new airworthiness
directive (AD) that is applicable to certain Airbus Model A300 series
airplanes. This proposal would require a one-time detailed visual
inspection to detect corrosion on the outer surface of the fuselage
skin panel; application of corrosion preventive protection; and
corrective action, if necessary. This proposal is prompted by issuance
of mandatory continuing airworthiness information by a foreign civil
airworthiness authority. The actions specified by the proposed AD are
intended to detect and correct corrosion of the fuselage skin panel,
which could result in cracking and consequent reduced structural
integrity of the airplane.
DATES: Comments must be received by February 2, 2000.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-114,
Attention: Rules Docket No. 99-NM-304-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.
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:
[[Page 92]]
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 99-NM-304-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-114, Attention: Rules
Docket No. 99-NM-304-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 certain Airbus Model A300 series airplanes. The
DGAC advises that several cases of corrosion have been reported on the
outer surface of the fuselage skin panel between fuselage frames 39 and
40, and between stringers 27 and 33. Cracking on the fuselage skin
panels and associated stiffeners has also been detected, resulting from
the adverse effects of stress corrosion. Such corrosion and cracking,
if not corrected, could result in reduced structural integrity of the
airplane.
Explanation of Relevant Service Information
Airbus has issued Service Bulletin A300-53-0328, dated March 5,
1999, which describes procedures for inspection for corrosion;
application of corrosion preventive protection to delay the occurrence
of corrosion; and repair if correction is detected. The service
bulletin describes several repair methods, including rework of corroded
areas, repair of panels still within permitted limits, or replacement
of panels outside permitted limits, depending on the severity of the
corrosion. Accomplishment of the actions specified in the service
bulletin is intended to adequately address the identified unsafe
condition. The DGAC classified this service bulletin as mandatory and
issued French airworthiness directive 1999-209-281(B), dated May 19,
1999, in order to ensure the continued airworthiness of these airplanes
in France.
FAA's Conclusions
This airplane model is manufactured in France and is type
certificated for operation in the United States under the provisions of
Sec. 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 bulletin described previously,
except as described below.
Differences Between Proposed Rule and Service Bulletin
Operators should note that, although the service bulletin specifies
that the manufacturer may be contacted for disposition of certain
repair conditions, this proposal would require replacement of the skin
panel to be accomplished in accordance with the service bulletin.
Cost Impact
The FAA estimates that 3 airplanes of U.S. registry would be
affected by this proposed AD, that it would take approximately 4 or 22
work hours per airplane, depending on the airplane configuration, to
accomplish the proposed inspection, 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 between $240 or $1,320
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 a substantial direct
effect 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, it
is determined that this proposal would not have federalism implications
under Executive Order 13132.
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 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 99-NM-304-AD.
[[Page 93]]
Applicability: Model A300 series airplanes, certificated in any
category; except those on which Airbus Modification 04201 has been
accomplished.
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 corrosion of the fuselage skin panel,
which could result in cracking and consequent reduced structural
integrity of the airplane, accomplish the following:
Inspection
(a) Perform a one-time detailed visual inspection of the outer
surface of the fuselage skin panel between fuselage frames FR39 and
FR40, and between stringers 27 and 33, for corrosion; in accordance
with Airbus Service Bulletin A300-53-0328, dated March 5, 1999.
Perform the inspection at the applicable time specified in paragraph
(a)(1), (a)(2), or (a)(3) of this AD. If any corrosion is found,
prior to further flight, repair (i.e., rework corroded areas, or
repair or replace panels, as applicable) in accordance with the
service bulletin, except as provided by paragraph (b) of this AD.
Temporary repairs must be replaced with permanent repairs prior to
accumulation of the life limits specified in the service bulletin.
(1) For airplanes for which the date of manufacture was less
than 15 years before the effective date of this AD: Inspect within
18 months after the effective date of this AD.
(2) For airplanes for which the date of manufacture was at least
15 but less than 20 years before the effective date of this AD:
Inspect within 12 months after the effective date of this AD.
(3) For airplanes for which the date of manufacture was 20 or
more years before the effective date of this AD: Inspect within 6
months after the effective date of this AD.
Note 2: For the purposes of this AD, a detailed visual
inspection is defined as: ``An intensive visual examination of a
specific structural area, system, installation, or assembly to
detect damage, failure, or irregularity. Available lighting is
normally supplemented with a direct source of good lighting at
intensity deemed appropriate by the inspector. Inspection aids such
as mirror, magnifying lenses, etc., may be used. Surface cleaning
and elaborate access procedures may be required.''
(b) Where Airbus Service Bulletin A300-53-0328, dated March 5,
1999, specifies that Airbus may be contacted for a repair, prior to
further flight, replace the skin panel with a new or serviceable
skin panel in accordance with the service bulletin.
Alternative Methods of Compliance
(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 3: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the International Branch, ANM-116.
Special Flight Permits
(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 4: The subject of this AD is addressed in French
airworthiness directive 1999-209-281(B), dated May 19, 1999.
Issued in Renton, Washington, on December 27, 1999.
D.L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 99-34032 Filed 12-30-99; 8:45 am]
BILLING CODE 4910-13-P
