[Federal Register Volume 68, Number 221 (Monday, November 17, 2003)]
[Proposed Rules]
[Pages 64830-64832]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 03-28606]


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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: 
[email protected]. 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]
BILLING CODE 4910-13-P