[Federal Register Volume 69, Number 26 (Monday, February 9, 2004)]
[Rules and Regulations]
[Pages 5907-5909]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 04-2466]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-NM-107-AD; Amendment 39-13451; AD 2004-03-07]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A320-111, -211, -212, and 
-231 Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment adopts a new airworthiness directive (AD), 
applicable to certain Airbus Model A320-111, -211, -212, and -231 
series airplanes. This AD requires 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 AD 
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: Effective March 15, 2004.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of March 15, 2004.

ADDRESSES: The service information referenced in this AD may be 
obtained from Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac 
Cedex, France. This information may be examined at the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, Rules Docket, 
1601 Lind Avenue, SW., Renton, Washington; or at the Office of the 
Federal Register, 800 North Capitol Street, NW., suite 700, Washington, 
DC.

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: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) to include an airworthiness 
directive (AD)

[[Page 5908]]

that is applicable to certain Airbus Model A320-111, -211, -212, and -
231 series airplanes was published in the Federal Register on November 
17, 2003 (68 FR 64830). That action proposed to 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. That action also provided an optional terminating 
action for the repetitive inspections.

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. No comments were submitted in response 
to the proposal or the FAA's determination of the cost to the public.

Conclusion

    After careful review of the available data, the FAA has determined 
that air safety and the public interest require the adoption of the 
rule as proposed.

Cost Impact

    The FAA estimates that 24 airplanes of U.S. registry will be 
affected by this AD.
    For airplanes without a center fuel tank, it will take 
approximately 1 work hour per airplane to accomplish the detailed 
inspection, at an average labor rate of $65 per work hour. Based on 
these figures, the cost impact of the detailed inspection is estimated 
to be $65 per airplane, per inspection cycle.
    For airplanes with a center fuel tank, it will take approximately 2 
work hours per airplane to accomplish the rotating probe inspection at 
an average labor rate of $65 per work hour. Based on these figures, the 
cost impact of the 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 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 will take approximately 12 work hours per airplane to 
accomplish the 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 adopted herein will 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 final rule does not have federalism 
implications under Executive Order 13132.
    For the reasons discussed above, I certify that this action (1) is 
not a ``significant regulatory action'' under Executive Order 12866; 
(2) is not a ``significant rule'' under DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979); and (3) 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 final evaluation has been prepared for this action 
and it is contained in the Rules Docket. A copy of it may be obtained 
from the Rules Docket at the location provided under the caption 
ADDRESSES.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

0
Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration amends part 39 of 
the Federal Aviation Regulations (14 CFR part 39) as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
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]

0
2. Section 39.13 is amended by adding the following new airworthiness 
directive:

2004-03-07 Airbus: Amendment 39-13451. 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 crack is 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 crack 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 G[eacute]n[eacute]rale de l'Aviation Civile (or its 
delegated agent).

[[Page 5909]]

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, is authorized to approve alternative methods of 
compliance for this AD.

Incorporation by Reference

    (h) Unless otherwise specified in this AD, the actions must be 
done in accordance with Airbus Service Bulletin A320-53-1030, 
Revision 01, excluding Appendix 01, dated May 21, 2002. This 
incorporation by reference was approved by the Director of the 
Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 
51. Copies may be obtained from Airbus, 1 Rond Point Maurice 
Bellonte, 31707 Blagnac Cedex, France. Copies may be inspected at 
the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., 
Renton, Washington; or at the Office of the Federal Register, 800 
North Capitol Street, NW., suite 700, Washington, DC.

    Note 3: The subject of this AD is addressed in French 
airworthiness directive 2000-531-155(B), dated December 27, 2000.

Effective Date

    (i) This amendment becomes effective on March 15, 2004.

    Issued in Renton, Washington, on January 29, 2004.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 04-2466 Filed 2-6-04; 8:45 am]
BILLING CODE 4910-13-P