[Federal Register Volume 63, Number 91 (Tuesday, May 12, 1998)]
[Proposed Rules]
[Pages 26102-26104]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-12518]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 97-NM-156-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 inspections to detect
cracking in the inner flange of door frame 66, and corrective actions,
if necessary. This proposal also would provide for an 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 correct such fatigue cracking, which
could result in reduced structural integrity of the airplane.
DATES: Comments must be received by June 11, 1998.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-114,
Attention: Rules Docket No. 97-NM-156-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, 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-156-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
[[Page 26103]]
FAA, Transport Airplane Directorate, ANM-114, Attention: Rules Docket
No. 97-NM-156-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, during fatigue testing on a Model A320 test article,
between 60,500 and 85,700 flight cycles, three cracks developed on the
inner flange of door frame 66 at stringer 18 and stringer 20. The
cracks were located around the edges of the gusset plate attachment
holes of the inner flange of door frame 66, which, during routine
visual inspection, would be hidden by the gusset plates. Such fatigue
cracking, if not corrected, could result in reduced structural
integrity of the airplane.
Explanation of Relevant Service Information
Airbus has issued Service Bulletin A320-53-1071, dated November 7,
1995, as revised by Change Notice 0A, dated July 5, 1996. This service
bulletin describes procedures for repetitive rotating probe eddy
current inspections to detect cracking around the edges of the gusset
plate attachment holes of the inner flange of door frame 66, left and
right, at stringer positions P18, P20, P22, P18', P20', and P22'. The
DGAC classified this service bulletin as mandatory and issued French
airworthiness directive 96-234-087(B), dated October 23, 1996, in order
to assure the continued airworthiness of these airplanes in France.
Accomplishment of the actions specified in the service bulletin is
intended to adequately address the identified unsafe condition.
Airbus also has issued Service Bulletin A320-53-1072, dated
November 7, 1995, as revised by Change Notice 0A, dated July 5, 1996.
This service bulletin describes procedures for modification of the
gusset plate attachment holes. The modification involves cold working
the attachment holes of the inner flange of door frame 66, left and
right, at stringer positions P18, P20, P22, P18', P20', and P22..
Accomplishment of the modification would eliminate the need for the
repetitive inspections. The DGAC has approved this service bulletin.
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 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 Service Bulletin A320-53-1071 described
previously, except as described in the following section. This proposed
AD also would provide for optional terminating action for the
repetitive inspections.
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.
Differences Between the Proposed AD and the Foreign Service
Information
The proposed AD would differ from the previously described Airbus
service bulletins and French airworthiness directive, which specify
that Airbus be contacted for a repair solution for cracking detected
during an inspection. In the proposed AD, however, repair of any crack
would be required to be accomplished in accordance with a method
approved by the FAA.
Also, operators should note that, unlike the procedures described
in Airbus Service Bulletin A320-53-1071, this proposed AD would not
permit further flight if cracks are detected around the edges of the
gusset plate attachment holes of the inner flange of door frame 66. The
FAA has determined that, because of the safety implications and
consequences associated with such cracking, any subject attachment hole
that is found to have cracking must be repaired or modified prior to
further flight.
Cost Impact
The FAA estimates that 132 airplanes of U.S. registry would be
affected by this proposed AD.
It would take approximately 8 work hours per airplane to accomplish
the proposed inspection, at an average labor rate of $60 per work hour.
Based on these figures, the cost impact of the inspection proposed by
this AD on U.S. operators is estimated to be $63,360, or $480 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.
Should an operator elect to accomplish the proposed modification,
it would take approximately 5 work hours per airplane to accomplish the
actions, at an average labor rate of $60 per work hour. Based on these
figures, the cost impact of the modification proposed by this AD on
U.S. operators is estimated to be $300 per airplane.
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
[[Page 26104]]
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-156-AD.
Applicability: Model A320 series airplanes on which Airbus
Modification 21778 (reference Airbus Service Bulletin A320-53-1072,
dated November 7, 1995, as revised by Change Notice 0A, dated July
5, 1996) has not been accomplished, 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 correct fatigue cracking in the inner flange of door frame
66, left and right, which could result in reduced structural
integrity of the airplane, accomplish the following:
(a) Prior to the accumulation of 20,000 total flight cycles, or
within 1 year after the effective date of this AD, whichever occurs
later: Perform a rotating probe eddy current inspection to detect
cracking around the edges of the gusset plate attachment holes of
the inner flange of door frame 66, left and right, at stringer
positions P18, P20, P22, P18', P20', and P22', in accordance with
Airbus Service Bulletin A320-53-1071, dated November 7, 1995, as
revised by Change Notice 0A, dated July 5, 1996. If any crack is
detected, prior to further flight, repair in accordance with a
method approved by the Manager, International Branch, ANM-116, FAA,
Transport Airplane Directorate. Repeat the inspection thereafter at
intervals not to exceed 20,000 flight cycles.
(b) Modification of the gusset plate attachment holes of the
inner flange of door frame 66, left and right (Airbus Modification
21778), in accordance with Airbus Service Bulletin A320-53-1072,
dated November 7, 1995, as revised by Change Notice 0A, dated July
5, 1996, constitutes terminating action for the repetitive
inspection requirements 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, 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.
(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 96-234-087(B), dated October 23, 1996.
Issued in Renton, Washington, on May 5, 1998.
John J. Hickey,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 98-12518 Filed 5-11-98; 8:45 am]
BILLING CODE 4910-13-U
