[Federal Register: October 13, 2004 (Volume 69, Number 197)]
[Rules and Regulations]
[Page 60809-60811]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr13oc04-8]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2002-NM-211-AD; Amendment 39-13819; AD 2004-20-14]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A300 B4 Series Airplanes
and Model A300 B4-600, A300 B4-600R, and A300 F4-600R (Collectively
Called A300-600) Series Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
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SUMMARY: This amendment supersedes an existing airworthiness directive
(AD), applicable to all Airbus Model A300 B4 series airplanes and all
Airbus Model A300-600 series airplanes. That AD currently requires a
one-time high frequency eddy current inspection to detect cracking of
the splice fitting at fuselage frame (FR) 47 between stringers 24 and
25; and corrective actions if necessary. This amendment requires new
repetitive inspections of an expanded area and adds airplanes to the
applicability in the existing AD. The actions specified by this AD are
intended to detect and correct cracking of the splice fitting at
fuselage FR 47, which could result in reduced structural integrity of
the airplane. This action is intended to address the identified unsafe
condition.
DATES: Effective November 17, 2004.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of November 17, 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 National Archives
and Records Administration (NARA). For information on the availability
of this material at NARA, call (202) 741-6030, or go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html
.
FOR FURTHER INFORMATION CONTACT: Tim Backman, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, 1601
Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 227-
2797; fax (425) 227-1149.
SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal
Aviation Regulations (14 CFR part 39) by superseding AD 2001-03-14,
amendment 39-12118 (66 FR 10957, February 21, 2001), was published as a
supplemental notice of proposed rulemaking (NPRM) in the Federal
Register on August 4, 2004 (69 FR 47035). The proposal is applicable to
all Airbus Model A300 series airplanes and all Airbus Model A300-600
series airplanes. The action proposed to require new repetitive high
frequency eddy current inspections to detect cracking of an expanded
area, and corrective actions, if necessary; and to add airplanes to the
applicability in the existing AD.
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.
Clarification of Service Information Requirements for Paragraph (b) of
This AD
In our response to comments in the Preamble of the supplemental
NPRM, we stated our intent to revise paragraphs (a), (b), and (c) of
the supplemental NPRM to refer to Revision 02 of the referenced Airbus
service bulletins as the appropriate sources of service information for
accomplishment of the required actions. (Revision 01 of those service
bulletins was referenced in the original NPRM for accomplishment of the
required actions.) However, while we revised paragraphs (a) and (c) of
the supplemental NPRM, we inadvertently omitted the revision to
paragraph (b). Therefore, we have revised paragraph (b) of this final
rule to reference Revision 02 of Airbus Service Bulletin A300-53-6123
as the appropriate source of service information for the required
actions in that paragraph.
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 with the change
[[Page 60810]]
described previously. The FAA has determined that this change will
neither increase the economic burden on any operator nor increase the
scope of the AD.
Cost Impact
There are approximately 92 airplanes of U.S. registry that will be
affected by this AD.
The inspection of an expanded area that is required in this AD will
take approximately 29 work hours per airplane to accomplish, at an
average labor rate of $65 per work hour. Based on these figures, the
cost impact of the required inspection on U.S. operators is estimated
to be $173,420, or $1,885 per airplane, per inspection cycle.
The cost impact figure discussed above is 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.
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 removing amendment 39-12118 (66 FR
10957, February 21, 2001), and by adding a new airworthiness directive
(AD), amendment 39-13819, to read as follows:
2004-20-14 Airbus: Amendment 39-13819. Docket 2002-NM-211-AD.
Supersedes AD 2001-03-14, Amendment 39-12118.
Applicability: All Model A300 B4-600, B4-600R, and F4-600R
(collectively called A300-600) series airplanes; and all Model A300
B4 series airplanes; certificated in any category.
Compliance: Required as indicated, unless accomplished
previously.
To detect and correct cracking of the splice fitting at fuselage
frame (FR) 47, which could result in reduced structural integrity of
the airplane, accomplish the following:
Repetitive Inspections
(a) For airplanes defined in Airbus Service Bulletin A300-53-
0350, Revision 02, dated November 12, 2002: Do a high frequency eddy
current (HFEC) inspection to detect cracking of the splice fitting
at fuselage FR 47 between stringers 24 and 26 (left- and right-hand
sides), at the applicable times specified in paragraph (a)(1) or
(a)(2) of this AD. Repeat the inspection thereafter at the earlier
of the flight-cycle/flight-hour intervals specified in the
applicable column in Table 2 of Figure 1 and Sheet 1 of the
Accomplishment Instructions of the service bulletin. Do the
inspections in accordance with the service bulletin, excluding
Appendix 01.
(1) For airplanes that have accumulated 20,000 or more total
flight cycles as of the effective date of this AD: Do the initial
inspection at the later of the times specified in paragraphs
(a)(1)(i) and (a)(1)(ii) of this AD:
(i) At the earlier of the flight-cycle/flight-hour intervals
after the effective date of this AD, as specified in the applicable
column in Table 1 of Figure 1 and Sheet 1 of the Accomplishment
Instructions of the service bulletin.
(ii) Within 750 flight cycles or 1,500 flight hours after the
effective date of this AD, whichever is first.
(2) For airplanes that have accumulated fewer than 20,000 total
flight cycles as of the effective date of this AD: Do the initial
inspection at the later of the times specified in paragraphs
(a)(2)(i) and (a)(2)(ii) of this AD.
(i) At the earlier of the flight-cycle/flight-hour intervals
after the effective date of this AD, as specified in the applicable
column in Table 1 of Figure 1 and Sheet 1 of the Accomplishment
Instructions of the service bulletin.
(ii) Within 1,800 flight cycles or 3,000 flight hours after the
effective date of this AD, whichever is first.
(b) For airplanes defined in Airbus Service Bulletin A300-53-
6123, Revision 02, dated November 12, 2002: Do the HFEC inspection
required by paragraph (a) of this AD at the applicable times
specified in paragraph (b)(1) or (b)(2) of this AD. Repeat the
inspection thereafter at the earlier of the flight-cycle/flight-hour
intervals specified in the applicable column in Table 2 of Figure 1
and Sheet 1 of the Accomplishment Instructions of the service
bulletin. Do the inspections in accordance with the service
bulletin, excluding Appendix 01.
(1) For airplanes that have accumulated 10,000 or more total
flight cycles as of the effective date of this AD: Do the initial
inspection within 750 flight cycles or 1,900 flight hours after the
effective date of this AD, whichever is first.
(2) For airplanes that have accumulated fewer than 10,000 total
flight cycles as of the effective date of this AD: Do the initial
inspection at the later of the times specified in paragraphs
(b)(2)(i) and (b)(2)(ii) of this AD.
(i) At the earlier of the flight-cycle/flight-hour intervals
after the effective date of this AD, as specified in the applicable
column in Table 1 of Figure 1 and Sheet 1 of the Accomplishment
Instructions of the service bulletin.
(ii) Within 1,500 flight cycles or 3,800 flight hours after the
effective date of this AD, whichever is first.
Repair
(c) Repair any cracking found during any inspection required by
this AD before further flight, in accordance with Airbus Service
Bulletin A300-53-0350 or A300-53-6123, both Revision 02, both
excluding Appendix 01, both dated November 12, 2002; as applicable.
Where the service bulletins specify to contact Airbus in case of
certain crack findings, this AD requires that a repair be
accomplished before further flight in accordance with a method
approved by either the Manager, International Branch, ANM-116, FAA,
Transport Airplane Directorate; or the Direction
G[eacute]n[eacute]rale de l'Aviation Civile (DGAC) (or its delegated
agent).
Credit for Previous Issues of Airbus Service Bulletin
(d) Accomplishment of the actions before the effective date of
this AD in accordance with Airbus Service Bulletin A300-53-0350 or
A300-53-6123, Revision 01, dated December 18, 2001; is considered
acceptable for compliance with the corresponding actions specified
in this AD.
Alternative Methods of Compliance
(e) In accordance with 14 CFR 39.19, the Manager, International
Branch, ANM-116, is authorized to approve alternative methods of
compliance for this AD.
[[Page 60811]]
Incorporation by Reference
(f) Unless otherwise specified in this AD, the actions shall be
done in accordance with Airbus Service Bulletin A300-53-0350,
Revision 02, excluding Appendix 01, dated November 12, 2002; and
Airbus Service Bulletin A300-53-6123, Revision 02, excluding
Appendix 01, dated November 12, 2002; as applicable. 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 National Archives and Records
Administration (NARA). For information on the availability of this
material at NARA, call (202) 741-6030, or go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html
.
Note 1: The subject of this AD is addressed in French
airworthiness directive 2002-184(B), dated April 3, 2002.
Effective Date
(g) This amendment becomes effective on November 17, 2004.
Issued in Renton, Washington, on September 30, 2004.
Kevin M. Mullin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 04-22564 Filed 10-12-04; 8:45 am]
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