[Federal Register Volume 63, Number 75 (Monday, April 20, 1998)]
[Proposed Rules]
[Pages 19421-19423]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-9757]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 97-NM-250-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A320 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 series
airplanes. This proposal would require repetitive rotating probe
inspections of fastener holes and/or the adjacent tooling hole of a
former junction of the aft fuselage, and corrective action, if
necessary. This AD also provides for optional terminating action for
the repetitive inspections. 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 prevent reduced structural integrity of the aft fuselage
caused by fatigue cracking of the former junction at frame 68.
DATES: Comments must be received by May 20, 1998.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-114,
Attention: Rules Docket No. 97-NM-250-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:
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-250-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. 97-NM-250-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 A320 series airplanes. The
DGAC advises that it has received a report indicating that, during
fatigue tests on a Model A320 test article, at 85,734 simulated
flights, four cracks developed in the fastener holes of the former
junction at frame 68. Such fatigue cracking, if not detected and
corrected in a timely manner, could result in reduced structural
integrity of the aft fuselage of the airplane.
Explanation of Relevant Service Information
Airbus has issued Service Bulletin A320-53-1089, dated November 22,
1995, which describes procedures for performing a rotating probe
inspection of the fastener holes and/or the adjacent tooling hole of
the former junction at frame 68, as applicable (depending upon the
configuration of the airplane), and follow-on repetitive inspections,
if necessary.
Airbus also has issued Service Bulletin A320-53-1090, dated
November 22, 1995, which describes procedures for cold working the
fastener holes and/or adjacent tooling hole (Modifications 21780 and
21781), which would eliminate the need for the repetitive inspections
specified in Airbus Service Bulletin A320-53-1089.
The DGAC classified Airbus Service Bulletin A320-53-1089 as
mandatory and issued French airworthiness directive 96-298-093(B)R1,
dated January 29, 1997, in order to assure the continued airworthiness
of these airplanes in France. (The DGAC approved Airbus Service
Bulletin A320-53-1090.)
FAA's Conclusions
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
[[Page 19422]]
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 Airbus Service Bulletin A320-53-1089,
described previously; except that the repair of any crack would be
required to be accomplished in accordance with a method approved by the
FAA. This proposed AD also would provide for optional terminating
action for the repetitive inspections required by this proposed AD.
Operators should note that, in consonance with the findings of the
DGAC, the FAA has determined that the repetitive inspections proposed
by this AD can be allowed to continue in lieu of accomplishment of a
terminating action. In making this determination, the FAA considers
that, in this case, long-term continued operational safety will be
adequately assured by accomplishing the repetitive inspections to
detect cracking before it represents a hazard to the airplane.
Cost Impact
The FAA estimates that 10 Airbus Model A320 series airplanes of
U.S. registry would be affected by this proposed AD.
Should an operator be required to accomplish the proposed
inspection of the fastener holes and the adjacent tooling hole, it
would take approximately 8 work hours per airplane to accomplish this
proposed inspection, at an average labor rate of $60 per work hour.
Based on these figures, the cost impact of this inspection proposed by
this AD on U.S. operators is estimated to be $480 per airplane, per
inspection cycle.
Should an operator be required to accomplish the proposed
inspection of only the tooling hole, it would take approximately 3 work
hours per airplane to accomplish this proposed inspection, at an
average labor rate of $60 per work hour. Based on these figures, the
cost impact of this inspection proposed by this AD on U.S. operators is
estimated to be $180 per airplane, per inspection cycle.
The cost impact figures discussed above are 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.
Should an operator elect to accomplish the optional terminating
action specified in this proposed AD, it would take approximately 9
work hours to cold work the fastener holes and tooling hole, or 3 work
hours to cold work (only) the tooling hole. The average labor rate is
$60 per work hour. Based on these figures, the cost impact of the
optional terminating action would be $540 per airplane for cold working
the fastener hole and tooling holes, or $180 per airplane for cold
working (only) the tooling hole.
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 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-250-AD.
Applicability: Model A320 series airplanes, as listed in Airbus
Service Bulletins A320-53-1089 and A320-53-1090, both dated November
22, 1995; on which Airbus Modifications 21780 and 21781 (reference
Airbus Service Bulletin A320-53-1090) have not been installed;
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 (b) 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 former junction at
frame 68, which could result in reduced structural integrity of the
aft fuselage, accomplish the following:
(a) Prior to the accumulation of 20,000 total flight cycles, or
within 500 flight cycles after the effective date of this AD,
whichever occurs later, perform a rotating probe inspection for
fatigue cracking of the fastener holes and/or the adjacent tooling
hole, as applicable, of the right- and left-hand former junctions at
frame 68, in accordance with Airbus Service Bulletin A320-53-1089,
dated November 22, 1995.
(1) If no crack is detected, accomplish either paragraph
(a)(1)(i) or (a)(1)(ii) of this AD.
(i) Repeat the inspection thereafter at intervals not to exceed
20,000 flight cycles. Or
(ii) Prior to further flight following the accomplishment of the
inspection required by paragraph (a) of this AD, cold work the
fastener holes and/or the adjacent tooling hole of the right- and
left-hand former junctions at frame 68, as applicable, in accordance
with Airbus Service Bulletin A320-53-1090, dated November 22, 1995.
Accomplishment of this cold working constitutes terminating action
for the repetitive inspections required by this AD.
(2) If any crack is detected, prior to further flight, repair it
in accordance with a method approved by the Manager, International
Branch, ANM-116, FAA, Transport Airplane Directorate.
[[Page 19423]]
(b) 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.
(c) 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 96-298-093(B)R1, dated January 29, 1997.
Issued in Renton, Washington, on April 7, 1998.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 98-9757 Filed 4-17-98; 8:45 am]
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