[Federal Register: February 9, 2004 (Volume 69, Number 26)]
[Rules and Regulations]
[Page 5907-5909]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr09fe04-2]
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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]
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