[Federal Register: November 17, 2003 (Volume 68, Number 221)]
[Proposed Rules]
[Page 64830-64832]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr17no03-16]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2001-NM-107-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A320-111, -211, -212, 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, -212, and -231 series airplanes. This proposal would require
repetitive inspections for fatigue cracking around the fasteners
attaching the pressure panel to the flexible bracket at frame 36,
adjacent to the longitudinal beams on the left and right sides of the
airplane; and repair as necessary. This proposal would also provide an
optional terminating action for the repetitive inspections. This action
is necessary to detect and correct fatigue cracking around the
fasteners attaching the pressure panel to the flexible bracket at the
frame 36 adjacent to the longitudinal beams, which could result in
reduced structural integrity and possible rapid decompression of the
airplane. This action is intended to address the identified unsafe
condition.
DATES: Comments must be received by December 17, 2003.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-114,
Attention: Rules Docket No. 2001-NM-107-AD, 1601 Lind Avenue, SW.,
Renton, Washington 98055-4056. Comments may be inspected at this
location between 9 a.m. and 3 p.m., Monday through Friday, except
Federal holidays. Comments may be submitted via fax to (425) 227-1232.
Comments may also be sent via the Internet using the following address: 9-anm-nprmcomment@faa.gov. Comments sent via fax or the Internet must
contain ``Docket No. 2001-NM-107-AD'' in the subject line and need not
be submitted in triplicate. Comments sent via the Internet as attached
electronic files must be formatted in Microsoft Word 97 or 2000 or
ASCII text.
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 Dulin, Aerospace Engineer,
International Branch, ANM-116, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425)
227-2141; 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 action may be changed in
light of the comments received.
Submit comments using the following format:
[sbull] Organize comments issue-by-issue. For example, discuss a
request to change the compliance time and a request to change the
service bulletin reference as two separate issues.
[sbull] For each issue, state what specific change to the proposed
AD is being requested.
[sbull] Include justification (e.g., reasons or data) for each
request.
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 action must submit a self-addressed,
stamped postcard on which the following statement is made: ``Comments
to Docket Number 2001-NM-107-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. 2001-NM-107-AD, 1601 Lind Avenue, SW., Renton, Washington
98055-4056.
Discussion
The Direction G[eacute]n[eacute]rale 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 A320-111, -211, -
212, and -231 series airplanes. The DGAC advises that during fatigue
tests, cracking was detected around the fasteners attaching the
pressure panel to the flexible bracket at frame 36, adjacent to the
longitudinal beams on the left and right sides of the airplane.
Investigation revealed that the damage was caused by high loads in this
area. Such cracking, if not corrected, could result in reduced
structural integrity and possible rapid decompression of the airplane.
Explanation of Relevant Service Information
Airbus has issued Service Bulletin A320-53-1030, Revision 01, dated
May 21, 2002. This service bulletin describes procedures for repetitive
inspections for fatigue cracking around the fasteners attaching the
pressure panel to the flexible bracket at frame 36, adjacent to the
longitudinal beams on the left and right sides of the airplane; and
repair if necessary. This service bulletin permits flight with cracks
of specific lengths.
Airbus Service Bulletin A320-53-1030, Revision 01, includes
procedures for the following actions:
[sbull] Repetitive rotating probe inspections on airplanes with a
center fuel tank, or repetitive detailed inspections on airplanes
without a center fuel tank, for cracking of the fastener holes that
attach the pressure panel to the flexible bracket at frame 36, adjacent
to the longitudinal beams.
[sbull] For certain airplanes on which cracking of specific lengths
is found, installation of the applicable repair/modification kit
(including modification of the pressure panel and longitudinal beams by
removing material, inspection of bolt holes for cracking, repair of
cracked areas, cold expansion of the bolt holes, and installation of a
doubler).
Airbus Service Bulletin A320-53-1029, Revision 01, includes
procedures for modifying the pressure panels located at frame 36
(including drilling
[[Page 64831]]
and reaming fastener holes to the oversize start diameter, performing
rotating probe inspections to detect cracking around fasteners holes,
repairing cracked areas, and cold expanding the fastener holes).
Accomplishment of this service bulletin on airplanes on which no
cracking is detected eliminates the need for the repetitive inspections
specified in Airbus Service Bulletin A320-53-1030, Revision 01.
Installation of any repair/modification kit in accordance with the
Accomplishment Instructions of either service bulletin eliminates the
need for the repetitive inspections of the repaired/modified area
specified in Airbus Service Bulletin A300-53-1030, Revision 01.
Accomplishment of the actions specified in Airbus Service Bulletin
A300-53-1030, Revision 01, is intended to adequately address the
identified unsafe condition. The DGAC classified this service bulletin
as mandatory and issued French airworthiness directive 2000-531-155(B),
dated December 27, 2000, 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
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 AD
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 A300-53-1030, Revision
01, described previously, except as discussed below. This proposed AD
also would provide for optional terminating action for the repetitive
inspections.
Consistent with the findings of the DGAC, the proposed AD would
allow repetitive inspections to continue in lieu of the terminating
action, provided no cracking is found during any inspection. In making
this determination, we considered that long-term continued operational
safety in this case will be adequately ensured by repetitive
inspections to detect cracking before it represents a hazard to the
airplane.
Differences Between the Service Information and the Proposed AD
Although the service bulletins specify that operators may contact
the manufacturer for disposition of certain repair conditions, this
proposal would require operators to repair those conditions per a
method approved by either the FAA or the DGAC (or its delegated agent).
In light of the type of repair that would be required to address the
unsafe condition, and consistent with existing bilateral airworthiness
agreements, we have determined that, for this proposed AD, a repair
approved by either the FAA or the DGAC would be acceptable for
compliance with this proposed AD.
No Flight With Cracks
Unlike Airbus Service Bulletin A300-53-1030, Revision 01, this
proposed AD would not permit further flight if any cracking is
detected, regardless of crack length, around the fasteners that attach
the pressure panel to the flexible bracket at frame 36, adjacent to the
longitudinal beams on the left and right sides of the airplane. We have
determined that, because of the safety implications and consequences
associated with such cracking, any cracking must be repaired before
further flight.
Cost Impact
The FAA estimates that 24 airplanes of U.S. registry would be
affected by this proposed AD.
For airplanes without a center fuel tank, it would take
approximately 1 work hour per airplane to accomplish the proposed
detailed inspection, at an average labor rate of $65 per work hour.
Based on these figures, the cost impact of the proposed detailed
inspection is estimated to be $65 per airplane, per inspection cycle.
For airplanes with a center fuel tank, it would take approximately
2 work hours per airplane to accomplish the proposed rotating probe
inspection at an average labor rate of $65 per work hour. Based on
these figures, the cost impact of the proposed inspection is estimated
to $130 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. The cost impact figures
discussed in AD rulemaking actions represent only the time necessary to
perform the specific actions actually required by the AD. These figures
typically do not include incidental costs, such as the time required to
gain access and close up, planning time, or time necessitated by other
administrative actions.
Should an operator elect to perform the optional terminating
action, it would take approximately 12 work hours per airplane to
accomplish the proposed cold work modification, at an average labor
rate of $65 per work hour. The cost of required parts is $650. Based on
these figures, the cost impact of the optional terminating action is
estimated to be $1,430 per airplane.
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.
[[Page 64832]]
Sec. 39.13 [Amended]
2. Section 39.13 is amended by adding the following new
airworthiness directive:
Airbus: Docket 2001-NM-107-AD.
Applicability: Model A320-111, -211, -212, and -231 series
airplanes having manufacturer serial numbers 0002 through 0107
inclusive; certificated in any category; except those airplanes on
which Airbus Modification 21202/K1432 has been incorporated in
production, or Airbus Service Bulletin A320-53-1029, Revision 01,
dated April 29, 2002, has been incorporated in service.
Compliance: Required as indicated, unless accomplished
previously.
To detect and correct fatigue cracking around the fasteners
connecting the pressure panel to the flexible bracket at frame 36,
adjacent to the longitudinal beams on the left and right sides of
the airplane, which could result in reduced structural integrity and
possible rapid decompression of the airplane, accomplish the
following:
Inspection and Follow-On Actions
(a) Prior to the accumulation of 30,000 total flight cycles, do
a rotating probe inspection on airplanes with a center fuel tank, or
a detailed inspection on airplanes without a center fuel tank, to
detect cracking around the fasteners that attach the pressure panel
to the flexible bracket at frame 36, adjacent to the longitudinal
beams on the left and right sides of the airplane, in accordance
with the Accomplishment Instructions of Airbus Service Bulletin
A320-53-1030, Revision 01, dated May 21, 2002.
Note 1: For the purposes of this AD, a detailed 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) If no cracks are detected by the inspection required by
paragraph (a) of this AD, repeat the applicable inspection
thereafter at intervals not to exceed 6,000 flight cycles for
airplanes without a center fuel tank, and at intervals not to exceed
18,000 flight cycles for airplanes with a center fuel tank.
Corrective Actions
(c) If any cracking is detected during any inspection required
by paragraph (a) of this AD, before further flight, repair the
affected structure by accomplishing all applicable actions in
accordance with paragraphs 3.B. through 3.E. of the Accomplishment
Instructions of Airbus Service Bulletin A320-53-1030, Revision 01,
dated May 21, 2002. Repeat the applicable inspection thereafter at
intervals not to exceed 6,000 flight cycles for airplanes without a
center fuel tank, and at intervals not to exceed 18,000 flight
cycles for airplanes with a center fuel tank. For any area where
cracking is repaired, the repair constitutes terminating action for
the repetitive inspection of that area.
Note 2: Airbus Service Bulletin A320-53-1030 references Airbus
Service Bulletin A320-53-1029, Revision 01, dated April 29, 2002, as
an additional source of service information for certain repairs.
(d) If any service bulletin specifies to contact the
manufacturer for appropriate action: Before further flight, repair
in accordance with a method approved by the Manager, International
Branch, ANM-116, FAA, Transport Airplane Directorate or the
Direction Gale de l'Aviation Civile (or its delegated agent).
Optional Terminating Action
(e) Modification of the structure around the fasteners that
attach the pressure panel to the flexible bracket at frame 36,
adjacent to the longitudinal beams on the left and right sides of
the airplane, by accomplishing all applicable actions in accordance
with paragraphs 3.A. through 3.E of the Accomplishment Instructions
of Airbus Service Bulletin A320-53-1029, Revision 01, dated April
29, 2002, constitutes terminating action for this AD.
Credit for Actions Done per Previous Issue of Service Bulletins
(f) Accomplishment of the required actions before the effective
date of this AD in accordance with Airbus Service Bulletin A320-53-
1030, dated January 5, 2000; or Airbus Service Bulletin A320-53-
1029, dated January 5, 2000; is considered acceptable for compliance
with the applicable requirements of paragraphs (a), (b), and (c) of
this AD.
Alternative Methods of Compliance
(g) In accordance with 14 CFR 39.19, the Manager, International
Branch, ANM-116, FAA, is authorized to approve alternative methods
of compliance for this AD.
Note 3: The subject of this AD is addressed in French
airworthiness directive 2000-531-155(B), dated December 27, 2000.
Issued in Renton, Washington, on November 10, 2003.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 03-28606 Filed 11-14-03; 8:45 am]
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