[Federal Register Volume 61, Number 61 (Thursday, March 28, 1996)]
[Proposed Rules]
[Pages 13789-13791]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 96-7548]
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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39
[Docket No. 95-NM-208-AD]
Airworthiness Directives; Airbus Model A320-111, -211, and -231
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 certain Airbus Model A320-111, -
211, and -231 series airplanes. This proposal would require repetitive
high frequency eddy current inspections to detect cracks around the
fasteners of the lower forward corners of the sliding window frames,
and repair, if necessary. This proposal would also require installation
of a modification for each affected fastener hole, which would
terminate the repetitive inspections. This proposal is prompted by the
results of full-scale fatigue tests which indicated that fatigue
cracking occurred on the lower forward corner of the sliding window
frames at frame 4. The actions specified by the proposed AD are
intended to prevent such fatigue cracking, which could result in rapid
depressurization of the airplane.
DATES: Comments must be received by May 6, 1996.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-103,
Attention: Rules Docket No. 95-NM-208-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: Tim Backman, Aerospace Engineer,
Standardization Branch, ANM-113, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (206)
227-2797; fax (206) 227-1149.
SUPPLEMENTARY INFORMATION:
Comments Invited
Interested persons are invited to participate in the making of the
[[Page 13790]]
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 95-NM-208-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. 95-NM-208-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, recently notified the FAA that an
unsafe condition may exist on certain Airbus Model A320-111, -211, and
-231 series airplanes. The DGAC advises that, during full-scale fatigue
tests on a Model A320 series airplane test article, fatigue cracking
was found on the lower forward corner of the sliding window frames at
frame 4. Fatigue cracking on the lower forward corner of the sliding
window frames at frame 4, if not detected and corrected in a timely
manner, could result in rapid depressurization of the airplane.
Airbus has issued Service Bulletin A320-53-1082, Revision 1, dated
November 9, 1994, which describes procedures for a high frequency eddy
current inspection to detect cracks around the five fasteners of the
lower forward corners of the sliding window frames at frame 4. For
cases where no cracks are detected during inspection, the service
bulletin describes procedures for either conducting repetitive
inspections, or installing Modification 23685P3199. The service
bulletin also permits further flight with cracking around the five
fasteners.
Airbus has also issued Service Bulletin A320-53-1044, dated
February 8, 1994, which describes procedures for installation of
Modification 23685P3199. The modification entails cold working each of
the five fastener holes on each side and installing a tension bolt.
Accomplishment of the modification on each of the 5 fasteners on each
side would eliminate the need for the repetitive inspections.
The DGAC classified these service bulletins as mandatory and issued
French airworthiness directive 94-166-056(B), dated July 20, 1994, in
order to assure the continued airworthiness of these airplanes in
France.
This airplane model is manufactured in France and is 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.
Since an unsafe condition has been identified that is likely to
exist or develop on other airplanes of the same type design, the
proposed AD would require high frequency eddy current inspection(s) to
detect cracks around the 5 fasteners of the lower forward corners of
the sliding window frames at frame 4. For cases where no cracks are
detected during inspection, the proposed AD would require installation
of Modification 23685P3199, which would constitute terminating action
for the repetitive inspection requirements. The actions would be
required to be accomplished in accordance with the procedures of the
service bulletins described previously.
Operators should note that, unlike the procedures described in the
referenced service bulletin, this proposed AD would not permit further
flight with cracking detected around any of the 5 fasteners of the
lower forward corner of the sliding window frame at frame 4. The FAA
has determined that, due to the safety implications and consequences
associated with such cracking, all cracks that are found must be
repaired prior to further flight. The repair would be required to be
accomplished in accordance with a method approved by the FAA.
The FAA estimates that 21 airplanes of U.S. registry would be
affected by this proposed AD, that it would take approximately 5 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
$6,300, or $300 per airplane, per inspection cycle.
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.
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 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:
[[Page 13791]]
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 95-NM-208-AD.
Applicability: Model A320-111, -211, and -231 series airplanes;
manufacturer's serial numbers 002 through 008 inclusive, 010 through
014 inclusive, 016 through 078 inclusive, and 080 through 098
inclusive; 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 are 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 prevent fatigue cracking on the lower forward corner of the
sliding window frames at frame 4, which could result in rapid
depressurization of the airplane, accomplish the following:
(a) Prior to the accumulation of 15,000 total landings, or 3
months after the effective date of this AD, whichever occurs first,
perform a high frequency eddy current inspection to detect cracks
around the 5 fasteners of the lower forward corners of the sliding
window frames at frame 4, in accordance with the procedures of
Airbus Service Bulletin A320-53-1082, Revision 1, dated November 9,
1994.
(1) If no cracks are detected, repeat the inspection thereafter
at intervals not to exceed 15,000 landings.
(2) If any crack is detected, prior to further flight, repair it
in accordance with a method approved by the Manager, Standardization
Branch, ANM-113, FAA, Transport Airplane Directorate.
(b) Prior to the accumulation of 30,000 total landings, or 5
years after the effective date of this AD, whichever occurs later,
accomplish Airbus Modification 23685P3199 for each fastener hole, in
accordance with Airbus Service Bulletin A320-53-1044, dated February
8, 1994. Accomplishment of the modification constitutes terminating
action for the repetitive inspection requirements of paragraph (a)
of this AD.
(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.
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.
Issued in Renton, Washington, on March 22, 1996.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 96-7548 Filed 3-27-96; 8:45 am]
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