[Federal Register: September 12, 2006 (Volume 71, Number 176)]
[Rules and Regulations]
[Page 53559-53562]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr12se06-7]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2006-25047; Directorate Identifier 2006-NM-028-AD;
Amendment 39-14759; AD 2006-19-02]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A300 B4-600, B4-600R, and
F4-600R Series Airplanes, and Model A300 C4-605R Variant F Airplanes
(Collectively Called A300-600 Series Airplanes)
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
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SUMMARY: The FAA is superseding an existing airworthiness directive
(AD), which applies to certain Airbus Model A300-600 series airplanes.
That AD currently requires repetitive eddy current inspections to
detect cracks of the outer skin of the fuselage at certain frames, and
repair or reinforcement of the structure at the frames, if necessary.
That AD also requires eventual reinforcement of the structure at
certain frames, which, when accomplished, terminates the repetitive
inspections. This new AD requires, for airplanes that were previously
reinforced but not repaired in accordance with the existing AD, a one-
time inspection for cracking of the fuselage outer skin at frames 28A
and 30A above stringer 30, and repair if necessary. This AD results
from a report that the previously required actions were not sufficient
to correct cracking before the structural reinforcement was installed.
We are issuing this AD to prevent such fatigue cracking, which could
result in reduced structural integrity, and consequent rapid
decompression of the airplane.
DATES: This AD becomes effective October 17, 2006.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in the AD as of October 17,
2006.
On August 4, 1997 (62 FR 35072, June 30, 1997), the Director of the
Federal Register approved the incorporation by reference of Airbus
Service Bulletin A300-53-6045, dated March 21, 1995, as revised by
Change Notice No. O.A., dated June 1, 1995; and Airbus Service Bulletin
A300-53-6037, dated March 21, 1995.
ADDRESSES: You may examine the AD docket on the Internet at http://dms.dot.gov
or in person at the Docket Management Facility, U.S.
Department of Transportation, 400 Seventh Street, SW., Nassif Building,
Room PL-401, Washington, DC.
Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex,
France, for service information identified in this AD.
FOR FURTHER INFORMATION CONTACT: Tom Stafford, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425)
227-1622; fax (425) 227-1149.
SUPPLEMENTARY INFORMATION:
Examining the Docket
You may examine the airworthiness directive (AD) docket on the
Internet at http://dms.dot.gov or in person at the Docket Management
Facility office between 9 a.m. and 5 p.m., Monday through Friday,
except Federal holidays. The Docket Management Facility office
(telephone (800) 647-5227) is located on the plaza level of the Nassif
Building at the street address stated in the ADDRESSES section.
Discussion
The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 to include an AD that supersedes AD 97-14-02, amendment 39-
10059 (62 FR 35072, June 30, 1997). The existing AD applies to certain
Airbus Model A300-600 series airplanes. That NPRM was published in the
Federal Register on June 15, 2006 (71 FR 34563). That NPRM proposed to
continue to require repetitive eddy current inspections to detect
cracks of the outer skin of the fuselage at certain frames, and repair
or reinforcement of the structure at the frames, if necessary. That
NPRM also proposed to continue to require eventual reinforcement of the
structure at certain frames, which, when accomplished, terminates the
repetitive inspections. That NPRM also proposed
[[Page 53560]]
to require, for airplanes that were previously reinforced but not
repaired in accordance with the existing AD, a one-time inspection for
cracking of the fuselage outer skin at frames 28A and 30A above
stringer 30, and repair if necessary.
Comments
We provided the public the opportunity to participate in the
development of this AD. No comments have been received on the NPRM or
on the determination of the cost to the public.
Conclusion
We have carefully reviewed the available data and determined that
air safety and the public interest require adopting the AD as proposed.
Costs of Compliance
This AD will affect about 53 airplanes of U.S. registry. The
following table provides the estimated costs for U.S. operators to
comply with this AD. The average labor rate is $80 per work hour.
Estimated Costs
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Work
Action hours Parts Cost per airplane Fleet cost
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Inspection (required by AD 97-14- 1 None $80, per inspection cycle..................... $4,240, per inspection cycle.
02).
Reinforcement (required by AD 97- 93 $7,200 $14,640....................................... $775,920.
14-02).
Inspection (new required action).. 1 None $80........................................... $4,240.
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Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. Subtitle VII, Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
subtitle VII, part A, subpart III, section 44701, ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We have determined that this AD will not have federalism
implications under Executive Order 13132. This AD 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.
For the reasons discussed above, I certify that this AD:
(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.
We prepared a regulatory evaluation of the estimated costs to
comply with this AD and placed it in the AD docket. See the ADDRESSES
section for a location to examine the regulatory evaluation.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
0
Accordingly, under the authority delegated to me by the Administrator,
the FAA amends 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. The Federal Aviation Administration (FAA) amends Sec. 39.13 by
removing amendment 39-10059 (62 FR 35072, June 30, 1997) and by adding
the following new airworthiness directive (AD):
2006-19-02 Airbus: Amendment 39-14759. Docket No. FAA-2006-25047;
Directorate Identifier 2006-NM-028-AD.
Effective Date
(a) This AD becomes effective October 17, 2006.
Affected ADs
(b) This AD supersedes AD 97-14-02.
Applicability
(c) This AD applies to Airbus Model A300 B4-601, B4-603, B4-620,
B4-622, B4-605R, B4-622R, F4-605R, F4-622R, and C4-605R Variant F
airplanes, certificated in any category, except those on which
Airbus Modification 8683 has been done.
Unsafe Condition
(d) This AD results from a report that the previously required
actions were not sufficient to correct cracking before the
structural reinforcement was installed. We are issuing this AD to
prevent fatigue cracking of the outer skin of the fuselage at
certain frames, which could result in reduced structural integrity,
and consequent rapid decompression of the airplane.
Compliance
(e) You are responsible for having the actions required by this
AD performed within the compliance times specified, unless the
actions have already been done.
Restatement of the Requirements of AD 97-14-02
(f) Prior to the accumulation of 14,100 total flight cycles, or
within 12 months after August 4, 1997 (the effective date of AD 97-
14-02), whichever occurs later, conduct an eddy current inspection
to detect cracking of the fuselage outer skin at frames 28A and 30A
above stringer 30, in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A300-53-6045, dated March
21, 1995, as revised by Change Notice No. O.A., dated June 1, 1995;
or Airbus Service Bulletin A300-53-6045, Revision 03, dated October
28, 2004. After the effective date of this AD, only Revision 03 may
be used. After the effective date of this AD, the initial eddy
current inspection and all applicable repairs required by this
paragraph must be done before doing the reinforcement specified in
paragraph (g) of this AD.
(1) If no cracking is found, repeat the eddy current inspection
thereafter at intervals not to exceed 4,500 flight cycles.
(2) If any cracking is found that is within the limits specified
in the service bulletin: Prior to further flight do the actions in
paragraph (f)(2)(i) or (f)(2)(ii) of this AD. After the effective
date of this AD, only Airbus Service Bulletin A300-53-6045, Revision
03, dated October 28, 2004, may be used for the repair specified in
paragraph (f)(2)(i) of this AD; and the reinforcement option
specified in paragraph (f)(2)(ii) of this AD is not allowed in
accordance with this paragraph.
[[Page 53561]]
(i) Repair in accordance with paragraph 2.D. of the
Accomplishment Instructions of Airbus Service Bulletin A300-53-6045,
dated March 21, 1995, as revised by Change Notice No. O.A., dated
June 1, 1995; or paragraph 3.C. of the Accomplishment Instructions
of Airbus Service Bulletin A300-53-6045, Revision 03, dated October
28, 2004. After the repair, repeat the eddy current inspection
thereafter at intervals not to exceed 4,500 flight cycles.
(ii) Reinforce the structure at frames 28 and 29, and at frames
30 and 31, between stringers 29 and 30, in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A300-53-6037,
dated March 21, 1995; or Airbus Service Bulletin A300-53-6037,
Revision 02, dated October 28, 2004. Such reinforcement constitutes
terminating action for the repetitive inspections required by this
AD.
(3) If any cracking is found that is outside the limits
specified in the service bulletin: Prior to further flight,
reinforce the structure at frames 28 and 29, and at frames 30 and
31, between stringers 29 and 30, in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A300-53-6037,
dated March 21, 1995; or Airbus Service Bulletin A300-53-6037,
Revision 02, dated October 28, 2004. After the effective date of
this AD, only Revision 02 may be used. Such reinforcement
constitutes terminating action for the repetitive inspections
required by this AD.
(g) Within 5 years after August 4, 1997: Reinforce the structure
at frames 28 and 29, and at frames 30 and 31, between stringers 29
and 30, in accordance with the Accomplishment Instructions of Airbus
Service Bulletin A300-53-6037, dated March 21, 1995; or Airbus
Service Bulletin A300-53-6037, Revision 02, dated October 28, 2004.
After the effective date of this AD, only Revision 02 may be used.
Such reinforcement constitutes terminating action for the repetitive
inspections required by this AD. After the effective date of this
AD, the initial eddy current inspection and all applicable repairs
required by paragraph (f) of this AD must be done before doing the
reinforcement.
New Requirements of This AD
Inspection and Corrective Action
(h) For airplanes that meet the conditions of both paragraphs
(h)(1) and (h)(2) of this AD: Within 2,400 flight cycles or 18
months after the effective date of this AD, whichever occurs first,
conduct an eddy current inspection to detect cracking of the
fuselage outer skin at frames 28A and 30A above stringer 30, in
accordance with the Accomplishment Instructions of Airbus Service
Bulletin A300-53-6045, Revision 03, dated October 28, 2004. If no
cracking is found: No further action is required by this paragraph.
If any cracking is found: Before further flight, repair the cracking
using a method approved by either the Manager, International Branch,
ANM-116, Transport Airplane Directorate, FAA; or the Direction
G[eacute]n[eacute]rale de l'Aviation Civile (DGAC) (or its delegated
agent).
(1) Airplanes that were reinforced before the effective date of
this AD in accordance with any service bulletin specified in Table 1
of this AD.
Table 1.--Reinforcement Service Bulletins
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Airbus service bulletin Revision level Date
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A300-53-6037.............................. Original................... March 21, 1995.
1.......................... February 3, 1999.
02......................... October 28, 2004.
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(2) Airplanes that were not inspected and repaired in accordance
with any service bulletin specified in Table 2 of this AD.
Table 2.--Inspection and Repair Service Bulletins
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Airbus service bulletin Revision level Date
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A300-53-6045.............................. Original................... March 21, 1995.
01......................... August 25, 1997.
02......................... May 2, 1999.
03......................... October 28, 2004.
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Alternative Methods of Compliance (AMOCs)
(i)(1) The Manager, International Branch, ANM-116, Transport
Airplane Directorate, FAA, has the authority to approve AMOCs for
this AD, if requested in accordance with the procedures found in 14
CFR 39.19.
(2) Before using any AMOC approved in accordance with Sec.
39.19 on any airplane to which the AMOC applies, notify the
appropriate principal inspector in the FAA Flight Standards
Certificate Holding District Office.
Related Information
(j) French airworthiness directive F-2005-002, dated January 5,
2005, also addresses the subject of this AD.
Material Incorporated by Reference
(k) You must use the service information identified in Table 3
of this AD to perform the actions that are required by this AD,
unless the AD specifies otherwise.
Table 3.--Material Incorporated by Reference
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Airbus service bulletin Revision level Date
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A300-53-6037.............................. Original................... March 21, 1995.
A300-53-6037.............................. 02......................... October 28, 2004.
A300-53-6045.............................. 03......................... October 28, 2004.
A300-53-6045, as revised by Change Notice Original................... March 21, 1995.
No. O.A., dated June 1, 1995.
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[[Page 53562]]
(1) The Director of the Federal Register approved the
incorporation by reference of Airbus Service Bulletin A300-53-6037,
Revision 02, dated October 28, 2004; and Airbus Service Bulletin
A300-53-6045, Revision 03, dated October 28, 2004; in accordance
with 5 U.S.C. 552(a) and 1 CFR part 51.
(2) On August 4, 1997 (62 FR 35072, June 30, 1997), the Director
of the Federal Register approved the incorporation by reference of
Airbus Service Bulletin A300-53-6045, dated March 21, 1995, as
revised by Change Notice No. O.A., dated June 1, 1995; and Airbus
Service Bulletin A300-53-6037, dated March 21, 1995.
(3) Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac
Cedex, France, for a copy of this service information. You may
review copies at the Docket Management Facility, U.S. Department of
Transportation, 400 Seventh Street, SW., Room PL-401, Nassif
Building, Washington, DC; on the Internet at http://dms.dot.gov; or
at the National Archives and Records Administration (NARA). For
information on the availability of this material at the NARA, call
(202) 741-6030, or go to http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html
.
Issued in Renton, Washington, on September 1, 2006.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E6-14942 Filed 9-11-06; 8:45 am]
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