[Federal Register Volume 63, Number 71 (Tuesday, April 14, 1998)]
[Proposed Rules]
[Pages 18156-18158]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-9759]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 97-NM-194-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A320 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 A320 series
airplanes. This proposal would require repetitive inspections to detect
fatigue cracking on the connecting angle between frame 56 and the
right-hand frame support at stringer 38; and replacement of the
connecting angle, if necessary. This proposal also provides 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 detect and correct fatigue
cracking on the connecting angle, which could result in reduced
structural integrity of the airplane.
DATES: Comments must be received by May 14, 1998.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
[[Page 18157]]
Administration (FAA), Transport Airplane Directorate, ANM-114,
Attention: Rules Docket No. 97-NM-194-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-194-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-194-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 full-scale testing on a Model A320 test
article, fatigue cracks were found at 60,500 simulated flights on the
connecting angle between frame 56 and the right-hand frame support at
stringer 38. This condition, if not corrected, could result in reduced
structural integrity of the airplane.
Explanation of Relevant Service Information
Airbus has issued Service Bulletin A320-53-1084, Revision 1, dated
November 28, 1995, which describes procedures for repetitive visual
inspections to detect fatigue cracking on the connecting angle between
frame 56 and the right-hand frame support at stringer 38. In addition,
Airbus has issued Service Bulletin A320-53-1011, dated December 9,
1994, which describes procedures for replacement of the connecting
angle with a new part, which would eliminate the need for the
repetitive inspections described in Airbus Service Bulletin A320-53-
1084. Accomplishment of the actions specified in the service bulletins
is intended to adequately address the identified unsafe condition.
The DGAC classified Airbus Service Bulletin A320-53-1084, Revision
1, as mandatory and issued French airworthiness directive 96-237-
090(B), dated October 23, 1996, and Erratum to French airworthiness
directive 96-237-090(B), dated February 26, 1997, in order to assure
the continued airworthiness of these airplanes in France. The DGAC has
also approved Airbus Service Bulletin A320-53-1011.
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 bulletins described previously,
except as discussed below. 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 fatigue cracking before it represents a hazard to the airplane.
Differences Between Proposed Rule and Service Bulletins
Operators should note that, unlike the procedures described in
Airbus Service Bulletin A320-53-1084, Revision 1, dated November 28,
1995, this proposed AD would not permit further flight if cracks are
detected on the connecting angle between frame 56 and the right-hand
frame support at stringer 38. The FAA has determined that, because of
the safety implications and consequences associated with such cracking,
any subject connecting angle that is found to be cracked must be
replaced with a new part prior to further flight.
Cost Impact
The FAA estimates that 5 airplanes of U.S. registry would be
affected by this proposed AD. It would take approximately 1 work hour
per airplane to accomplish the inspection proposed by this AD, at an
average labor rate of $60 per work hour. Based on this figure, the cost
impact of the inspection proposed by this AD on U.S. operators is
estimated to be $300, or $60 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.
Should an operator elect to perform the optional terminating
replacement proposed by this AD, it would take approximately 3 work
hours per airplane to accomplish the modification,
[[Page 18158]]
at an average labor rate of $60 per work hour. Required parts would
cost $136 or $153 per airplane, depending on the service kit purchased.
Based on these figures, the cost impact of the optional terminating
modification proposed by this AD on U.S. operators is estimated to be
as low as $1,580, or $316 per airplane and as high as $1,665, or $333
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 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-194-AD.
Applicability: Model A320 series airplanes, on which Airbus
Modification 20941 (reference Airbus Service Bulletin A320-53-1011,
dated December 9, 1994) 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 detect and correct fatigue cracking on the connecting angle
between frame 56 and the right-hand frame support at stringer 38,
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 1,000 flight cycles after the effective date of this AD,
whichever occurs later, perform a visual inspection for fatigue
cracking on the connecting angle between frame 56 and the right-hand
frame support at stringer 38, in accordance with Airbus Service
Bulletin A320-53-1084, Revision 1, dated November 28, 1995.
(1) If no cracking is detected, accomplish either paragraph
(a)(1)(i) or (a)(1)(ii) of this AD.
(i) Prior to further flight, replace the connecting angle
between frame 56 and the right-hand frame support at stringer 38
with a new part, in accordance with Airbus Service Bulletin A320-53-
1011, dated December 9, 1994; or
(ii) Repeat the visual inspection thereafter at intervals not to
exceed 12,000 flight cycles.
(2) If any cracking is detected, prior to further flight,
replace the connecting angle between frame 56 and the right-hand
frame support at stringer 38 with a new part, in accordance with
Airbus Service Bulletin A320-53-1011, dated December 9, 1994.
(b) Accomplishment of the replacement of the connecting angle
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, 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 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 96-237-090(B), dated October 23, 1996, and
Erratum to French airworthiness directive 96-237-090(B), dated
February 26, 1997.
Issued in Renton, Washington, on April 7, 1998.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 98-9759 Filed 4-13-98; 8:45 am]
BILLING CODE 4910-13-U
