Airworthiness Directives; Airbus Model A330-301, -321, -322, -341, and -342 Airplanes; and Model A340-200 and A340-300 Series Airplanes, 57493-57497 [05-19045]
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57493
Federal Register / Vol. 70, No. 190 / Monday, October 3, 2005 / Rules and Regulations
Testing the Firex Electrical Circuits
(f) Within 18 months after the
accumulation of 15,000 total flight hours, or
within 18 months after September 24, 2003
(the effective date of AD 2003–17–07),
whichever occurs later: Test the capability of
the electrical circuits of the Firex fire
extinguishers for the engine and the APU, as
applicable, per the applicable alert service
bulletin (ASB) listed in Table 1 of this AD.
(1) For any airplane equipped with an
APU: If any electrical circuit of the Firex fire
extinguishers for the APU does not pass the
testing, before further flight, accomplish the
troubleshooting procedures specified in the
applicable ASB. Dispatch with an inoperative
APU is permitted for the amount of time
specified in the Minimum Equipment List.
Dispatch after that time is not permitted until
the circuits are repaired per the Boeing
Standard Wiring Practices Manual (SWPM)
D6–82481.
(2) For all airplanes: If any electrical circuit
of the Firex fire extinguishers for the engine
does not pass the testing, before further
flight, accomplish the troubleshooting
procedures specified in the applicable ASB,
and repair per SWPM D6–82481. Dispatch is
not permitted until the circuits have been
repaired.
Actions Accomplished Per Previous Issue of
Service Bulletins
(g) Tests and troubleshooting procedures
accomplished before the effective date of this
AD per McDonnell Douglas Alert Service
Bulletin DC9–26A029, dated July 27, 2000; or
MD11–26A039, dated July 31, 2000; are
considered acceptable for compliance with
the corresponding action specified in
paragraph (f) of this AD.
Alternative Methods of Compliance
(h) An alternative method of compliance or
adjustment of the compliance time that
provides an acceptable level of safety may be
used if approved by the Manager, Los
Angeles Aircraft Certification Office (ACO),
FAA. Operators shall submit their requests
through an appropriate FAA Principal
Maintenance Inspector, who may add
comments and then send it to the Manager,
Los Angeles ACO.
Note 2: Information concerning the
existence of approved alternative methods of
compliance with this AD, if any, may be
obtained from the Los Angeles ACO.
Special Flight Permits
(i) Special flight permits may be issued in
accordance with sections 21.197 and 21.199
of the Federal Aviation Regulations (14 CFR
21.197 and 21.199) to operate the airplane to
a location where the requirements of this AD
can be accomplished.
Material Incorporated by Reference
(j) You must use the service bulletins listed
in Table 2 of this AD to perform the actions
that are required by this AD, unless the AD
specifies otherwise.
TABLE 2.—APPLICABLE SERVICE BULLETINS
Service bulletin
Revision level
Boeing Alert Service Bulletin DC8–26A042, including Appendix A ..................................................
McDonnell Douglas Alert Service Bulletin DC9–26A029 ..................................................................
McDonnell Douglas Alert Service Bulletin DC10–26A050 ................................................................
McDonnell Douglas Alert Service Bulletin MD11–26A039 ...............................................................
McDonnell Douglas Alert Service Bulletin MD90–26A005 ...............................................................
Original ..................
Revision 01 ............
Original ..................
Revision 01 ............
Original ..................
(1) On September 24, 2003 (68 FR 50058,
August 20, 2003), the Director of the Federal
Register approved the incorporation by
reference of Boeing and McDonnell Douglas
service bulletins listed in Table 2.
(2) Contact Boeing Commercial Airplanes,
Long Beach Division, 3855 Lakewood
Boulevard, Long Beach, California 90846,
Attention: Data and Service Management,
Dept. C1–L5A (D800–0024), 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 https://
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 https://www.archives.gov/
federal_register/code_of_federal_regulations/
ibr_locations.html.
ribs 1 and 2 having initiated at the build
slot. We are issuing this AD to detect
and correct fatigue cracking in the
vertical web of the wing rear spar,
which could result in reduced structural
integrity of the wing.
DATES: Effective October 18, 2005.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in the AD
as of October 18, 2005.
We must receive comments on this
AD by December 2, 2005.
ADDRESSES: Use one of the following
addresses to submit comments on this
AD.
• DOT Docket web site: Go to
https://dms.dot.gov and follow the
instructions for sending your comments
electronically.
• Government-wide rulemaking web
site: Go to https://www.regulations.gov
and follow the instructions for sending
your comments electronically.
• Mail: Docket Management Facility;
U.S. Department of Transportation, 400
Seventh Street SW., Nassif Building,
Room PL–401, Washington, DC 20590.
• Fax: (202) 493–2251.
• Hand Delivery: Room PL–401 on
the plaza level of the Nassif Building,
400 Seventh Street SW., Washington,
DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
Contact Airbus, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France,
Issued in Renton, Washington, on
September 20, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 05–19438 Filed 9–30–05; 8:45 am]
BILLING CODE 4910–13–P
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14:53 Sep 30, 2005
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2005–22485; Directorate
Identifier 2001–NM–337–AD; Amendment
39–14293; AD 2005–19–28]
RIN 2120–AA64
Airworthiness Directives; Airbus Model
A330–301, –321, –322, –341, and –342
Airplanes; and Model A340–200 and
A340–300 Series Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for
comments.
AGENCY:
SUMMARY: The FAA is adopting a new
airworthiness directive (AD) for certain
Airbus Model A330–301, –321, –322,
–341, and –342 airplanes; and Model
A340–200 and A340–300 series
airplanes. This AD requires repetitive
inspections for cracks in the aft face of
the rear spar at the area adjacent to the
bolt holes and the end of the build slot,
and repair if necessary. The AD also
provides an optional terminating action
for the repetitive inspections. This AD
results from a report that, during fatigue
tests of the wing, cracks were found in
the vertical web of the rear spar between
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Date
January 31, 2002.
May 8, 2001.
July 31, 2000.
November 21, 2002.
July 31, 2000.
57494
Federal Register / Vol. 70, No. 190 / Monday, October 3, 2005 / Rules and Regulations
for service information identified in this
AD.
You may examine the contents of the
AD docket on the Internet at https://
dms.dot.gov, or in person at the Docket
Management Facility, U.S. Department
of Transportation, 400 Seventh Street
SW., Room PL–401, Washington, DC.
This docket number is FAA–2005–
22485; the directorate identifier for this
docket is 2001–NM–337–AD.
FOR FURTHER INFORMATION CONTACT: Tim
Backman, Aerospace Engineer, ANM–
116, International Branch, FAA,
Transport Airplane Directorate, 1601
Lind Avenue, SW., Renton, Washington
98055–4056; telephone (425) 227–2797;
fax (425) 227–1149.
SUPPLEMENTARY INFORMATION:
Comments Invited
Although this is a final rule that was
not preceded by notice and an
opportunity for public comment, we
invite you to submit any relevant
written data, views, or arguments
regarding this AD. Include ‘‘Docket No.
FAA–2005–22485; Directorate Identifier
2001–NM–337–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of the AD. We will consider all
comments received by the closing date
and may amend the AD in light of those
comments.
We will post all comments we
receive, without change, to https://
dms.dot.gov, including any personal
information you provide. We will also
post a report summarizing each
substantive verbal contact with FAA
personnel concerning this AD. Using the
search function of that web site, anyone
can find and read the comments in any
of our dockets, including the name of
the individual who sent the comment
(or signed the comment on behalf of an
association, business, labor union, etc.).
You may review the DOT’s complete
Privacy Act Statement in the Federal
Register published on April 11, 2000
(65 FR 19477–78), or you may visit
https://dms.dot.gov.
Examining the Docket
You may examine the AD docket on
the Internet at https://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 DOT
street address stated in the ADDRESSES
section. Comments will be available in
the AD docket shortly after the Docket
Management System receives them.
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Service Bulletin A340–57–4065, dated
August 29, 2001 (for Model A340–200
The Direction Generale de l’Aviation
and A340–300 series airplanes). These
Civile (DGAC), which is the
service bulletins describe procedures for
airworthiness authority for France,
notified us that an unsafe condition may changing the profile of the end radius of
the build slot to reduce the stress
exist on certain Airbus Model A330–
concentration in the area, which
301, –321, –322, –341, and –342
reduces the probability of fatigue
airplanes; and Model A340–200 and
cracking. The re-profiling involves first
A340–300 series airplanes. The DGAC
doing an HFEC inspection for cracks of
advises that, during fatigue tests of the
the aft face of the rear spar at the area
wing, cracks were found in the vertical
adjacent to the bolt holes. If cracks are
web of the rear spar between ribs 1 and
found that will be removed by the re2. These fatigue cracks propagated from
profiling cut-out, the service bulletins
the build slot to the nearest adjacent
specify that the re-profiling can proceed.
bolt hole. This condition, if not
If any crack is found that is outside the
corrected, could result in reduced
re-profiling cut-out, the service bulletins
structural integrity of the wing.
specify contacting Airbus for repair
instructions before further flight. Doing
Relevant Service Information
this re-profiling eliminates the need for
Airbus has issued Service Bulletin
the repetitive inspection requirements
A330–57–3059, Revision 01, dated
of Airbus Service Bulletins A330–57–
September 13, 2001 (for Model A330–
3059 and A340–57–4066.
301, –321, –322, –341, and –342
Accomplishing the actions specified
airplanes); and Service Bulletin A340–
in the service information is intended to
57–4066, Revision 01, dated September
adequately address the unsafe
13, 2001 (for Model A340–200 and
condition. The DGAC mandated the
A340–300 series airplanes). The service service information and issued French
bulletins describe procedures for doing
airworthiness directives 2001–268(B)
repetitive high-frequency eddy current
R1, dated July 25, 2001, and 2001–
(HFEC) inspections for cracks in the aft
269(B), dated June 27, 2001, to ensure
face of the rear spar at the area adjacent
the continued airworthiness of these
to the bolt holes and the end of the build airplanes in France.
slot. If no cracks are found, the service
bulletins give intervals for repeating the FAA’s Determination and Requirements
of This AD
HFEC inspection until the terminating
action, described below, is
These airplane models are
accomplished. If any crack is found the
manufactured in France and are type
service bulletins give the following
certificated for operation in the United
procedures for repair, depending on the States under the provisions of section
extent of the crack.
21.29 of the Federal Aviation
• For any crack that has not reached
Regulations (14 CFR 21.29) and the
the fastener holes ‘‘B,’’ and is still
applicable bilateral airworthiness
within a specified modification cut-out
agreement. Pursuant to this bilateral
area, the service bulletins state that the
airworthiness agreement, the DGAC has
airplane may continue operation at
kept the FAA informed of the situation
various reduced inspection intervals,
described above. We have examined the
depending on the length of the crack,
DGAC’s findings, evaluated all pertinent
until the terminating action is
information, and determined that we
accomplished.
need to issue an AD for products of this
• For any crack that extends to
type design that are certificated for
fastener holes ‘‘B,’’ but not beyond, the
operation in the United States.
service bulletin gives procedures for
Therefore, we are issuing this AD to
doing a temporary repair and then doing detect and correct fatigue cracking in
the terminating action, described below, the vertical web of the wing rear spar,
at a specified interval following the
which could result in reduced structural
temporary repair. The temporary repair
integrity of the wing. This AD requires
includes the related investigative action accomplishing the actions specified in
of a leak test after the access panels are
the service information described
installed at the work area.
previously.
• If any crack is found that extends
Differences Between the AD and the
beyond the specified modification cutFrench Airworthiness Directives
out area, the service bulletin specifies
The applicability of the French
that operators should contact Airbus for
airworthiness directives excludes
repair instructions.
airplanes on which Airbus Service
Airbus has also issued Service
Bulletins A330–57–3058 or A340–57–
Bulletin A330–57–3058, dated August
4065 was accomplished in service, as
29, 2001 (for Model A330–301, –321,
applicable. However, we have not
–322, –341, and –342 airplanes); and
Discussion
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Federal Register / Vol. 70, No. 190 / Monday, October 3, 2005 / Rules and Regulations
excluded those airplanes in the
applicability of this AD; rather, this AD
includes a requirement to accomplish
the actions specified in the applicable
service bulletin. This requirement
would ensure that the actions specified
in the service bulletin and required by
this AD are accomplished on all affected
airplanes. Operators must continue to
operate the airplane in the configuration
required by this AD unless an
alternative method of compliance is
approved.
Unlike the procedures described in
the service bulletins that are mandated
by the French airworthiness directives,
this AD would not permit further flight
if any crack is detected. For cracks that
have not reached fastener holes ‘‘B’’ or
that extend to fastener holes ‘‘B,’’ but
not beyond, this AD requires doing the
temporary repair in accordance with the
service bulletin. In addition, unlike the
procedures described in the service
57495
for this AD, a repair we or the DGAC
approve would be acceptable for
compliance with this AD.
These differences have been
coordinated with the DGAC.
bulletins, this AD would not permit
further flight if any crack has extended
beyond the fastener holes ‘‘B,’’ and is
still within a specified modification cutout area. We have determined that,
because of the safety implications and
consequences associated with that
cracking, any crack of this size must be
permanently repaired (by using the reprofiling procedure) before further
flight.
The service bulletins that are
mandated by the French airworthiness
directives specify that you may contact
the manufacturer for instructions on
how to repair certain conditions, but
this AD would require you to repair
those conditions using a method that we
or the DGAC (or its delegated agent)
approve. 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,
Costs of Compliance
None of the airplanes affected by this
action are on the U.S. Register. All
airplanes affected by this AD are
currently operated by non-U.S.
operators under foreign registry;
therefore, they are not directly affected
by this AD action. However, we
consider this AD necessary to ensure
that the unsafe condition is addressed if
any affected airplane is imported and
placed on the U.S. Register in the future.
The following table provides the
estimated costs to comply with this AD
for any affected airplane that might be
imported and placed on the U.S.
Register in the future.
ESTIMATED COSTS
Action
HFEC Inspection, per inspection cycle ....................
Re-profiling (Optional Terminating Action) ...............
FAA’s Determination of the Effective
Date
No airplane affected by this AD is
currently on the U.S. Register.
Therefore, providing notice and
opportunity for public comment is
unnecessary before this AD is issued,
and this AD may be made effective in
less than 30 days after it is published in
the Federal Register.
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.
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Average labor
rate per hour
Work hours
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2
70
$65
$65
Parts cost
Cost per airplane
None ...........
None ...........
$130, per inspection cycle.
$4,550.
Regulatory Findings
Adoption of the Amendment
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 the 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. 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.
I
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
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Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
I
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The Federal Aviation
Administration (FAA) amends § 39.13
by adding the following new
airworthiness directive (AD):
I
2005–19–28 Airbus: Amendment 39–14293.
Docket No. FAA–2005–22485;
Directorate Identifier 2001–NM–337–AD.
Effective Date
(a) This AD becomes effective October 18,
2005.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Airbus Model A330–
301, –321, –322, –341, and –342 airplanes;
and Model A340–211, –212, –213, –311,
–312, and –313 airplanes; certificated in any
category; except airplanes on which Airbus
Modification 41300 or 42547 has been
accomplished, as applicable.
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Federal Register / Vol. 70, No. 190 / Monday, October 3, 2005 / Rules and Regulations
Unsafe Condition
(d) This AD results from a report that,
during fatigue tests of the wing, cracks were
found in the vertical web of the rear spar
between ribs 1 and 2 having initiated at the
build slot. The FAA is issuing this AD to
detect and correct fatigue cracking in the
vertical web of the wing rear spar, which
could result in reduced structural integrity of
the wing.
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.
Bulletin A340–57–4066, Revision 01, dated
September 13, 2001.
Service Bulletin Reference
(f) Unless otherwise specified in this AD,
the term ‘‘service bulletin,’’ as used in this
AD, means the Accomplishment Instructions
of the following service bulletins, as
applicable:
(1) For Model A330–301, –321, –322, –341,
and –342 airplanes: Airbus Service Bulletin
A330–57–3059, Revision 01, dated
September 13, 2001; and
(2) For Model A340–211, –212, –213, –311,
–312, and –313 airplanes: Airbus Service
Repetitive Inspections
(g) At the applicable threshold in Table 1
of this AD, do a high frequency eddy current
inspection for cracks in the aft face of the rear
spar at the area adjacent to the bolt holes and
the end of the build slot; and repeat the
inspection thereafter at the applicable
repetitive interval in Table 1 of this AD, until
the repair required by paragraph (k) of this
AD is accomplished. Do all inspections in
accordance with the applicable service
bulletin.
TABLE 1.—INSPECTION THRESHOLDS AND INTERVALS
Threshold
Repetitive interval
The later of—
The earlier of—
Model—
A330–301, –321, –322, –341, and –342 airplanes.
A340–211, –212, –213, –311, –312, and –313
airplanes.
Repair
(h) If any crack is found during any
inspection required by paragraph (g) of this
AD, and the crack has not reached the
fastener holes ‘‘B’’ or extends to fastener
holes ‘‘B,’’ but not beyond, before further
flight: Do the temporary repair in accordance
with the applicable service bulletin and
repeat the inspection thereafter at the
applicable interval in paragraph (g) of this
AD until the permanent repair required by
paragraph (k) of this AD is accomplished.
(i) If any crack is found during any
inspection required by paragraph (g) of this
AD, and the crack has extended beyond
fastener holes ‘‘B,’’: Before further flight, do
the permanent repair in paragraph (k) of this
AD.
(j) Where the service bulletin specifies that
operators may contact the manufacturer for
instructions on how to repair cracks that
extend beyond the modification cut-out area:
Before further flight, repair according to a
method approved by either the Manager,
International Branch, ANM–116, FAA,
Transport Airplane Directorate; or the
´ ´
Direction Generale de l’Aviation Civile
(DGAC) (or its delegated agent).
Optional Terminating Action—Permanent
Repair (Re-Profiling)
(k) Doing the permanent repair in
accordance with the applicable service
bulletin in paragraph (k)(1) or (k)(2) of this
AD terminates the repetitive inspection
requirements of this AD. Where the service
bulletins in paragraph (k)(1) and (k)(2) of this
AD specify that operators may contact the
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• Before the accumulation of 10,300 total
flight cycles or 32,000 total flight hours,
whichever occurs earlier; or
• Within 6 months after the effective date of
this AD.
• Before the accumulation of 9,800 total flight
cycles or total 48,200 flight hours, whichever occurs earlier; or
• Within 6 months after the effective date of
this AD.
• 8,300 flight cycles; and
• 25,800 flight hours.
• 8,200 flight cycles; and
• 40,100 flight hours.
manufacturer for instructions on how to
repair certain conditions: Before further
flight, repair according to a method approved
by either the Manager, International Branch,
ANM–116, FAA, Transport Airplane
Directorate; or the DGAC (or its delegated
agent).
(1) For Model A330–301, –321, –322, –341,
and –342 airplanes: Airbus Service Bulletin
A330–57–3058, dated August 29, 2001.
(2) For Model A340–211, –212, –213, –311,
–312, and –313 airplanes: Airbus Service
Bulletin A340–57–4065, dated August 29,
2001.
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 § 39.19 on any airplane to
which the AMOC applies, notify the
appropriate principal inspector in the FAA
Flight Standards Certificate Holding District
Office.
Actions Done in Accordance With Previous
Issues of Service Bulletins
Material Incorporated by Reference
(o) You must use the Airbus service
bulletins identified in Table 3 of this AD to
perform the actions that are required by this
AD, as applicable, unless the AD specifies
otherwise. The Director of the Federal
Register approved the incorporation by
reference of these documents in accordance
with 5 U.S.C. 552(a) and 1 CFR part 51.
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
https://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 https://www.archives.gov/
federal_register/code_of_federal_regulations/
ibr_locations.html.
(l) Actions done before the effective date of
this AD in accordance with the service
bulletins identified in Table 2 of this AD, are
acceptable for compliance with the
corresponding action required by this AD.
TABLE 2.—PREVIOUS ISSUES OF
SERVICE BULLETINS
Airbus Service Bulletins
Date
A330–57–3059 .................
A340–57–4066 .................
March 16, 2001.
March 16, 2001.
Alternative Methods of Compliance
(AMOCs)
(m)(1) The Manager, International Branch,
ANM–116, Transport Airplane Directorate,
FAA, has the authority to approve AMOCs
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Related Information
(n) French airworthiness directives 2001–
268(B) R1, dated July 25, 2001, and 2001–
269(B), dated June 27, 2001, also address the
subject of this AD.
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Federal Register / Vol. 70, No. 190 / Monday, October 3, 2005 / Rules and Regulations
TABLE 3.—MATERIAL INCORPORATED BY REFERENCE
Airbus Service Bulletins
A330–57–3058
A330–57–3059
A340–57–4065
A340–57–4066
..................................................................................................................................
..................................................................................................................................
..................................................................................................................................
..................................................................................................................................
Issued in Renton, Washington, on
September 15, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 05–19045 Filed 9–30–05; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 71
[Docket No. FAA–2005–22006; Airspace
Docket No. 05–ACE–30]
Modification of Class E Airspace;
Sheldon Municipal Airport, IA
Federal Aviation
Administration (FAA), DOT.
ACTION: Direct final rule; request for
comments.
AGENCY:
SUMMARY: This action modifies the size
of the Class E5 airspace area beginning
at 700 feet above the surface at Sheldon,
IA to contain Instrument Flight Rule
(IFR) operations in controlled airspace.
The radius of the airspace area is
expanded from within a 6.4-mile radius
to within a 6.9-mile radius of the
airport. This action brings the Class E5
airspace area into compliance with FAA
directives.
DATES: This direct final rule is effective
on 0901 UTC, December 22, 2005.
Comments for inclusion in the Rules
Docket must be received on or before
October 28, 2005.
ADDRESSES: Send comments on this
proposal to the Docket Management
System, U.S. Department of
Transportation, Room Plaza 401, 400
Seventh Street, SW., Washington, DC
20590–0001. You must identify the
docket number FAA–2005–22006/
Airspace Docket No. 05–ACE–30, at the
beginning of your comments. You may
also submit comments on the Internet at
https://dms.dot.gov. You may review the
public docket containing the proposal,
any comments received, and any final
disposition in person in the Dockets
Office between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal
holidays. The Docket Office (telephone
1–800–647–5527) is on the plaza level
VerDate Aug<31>2005
Revision level
14:53 Sep 30, 2005
Jkt 208001
of the Department of Transportation
NASSIF Building at the above address.
FOR FURTHER INFORMATION CONTACT:
Brenda Mumper, Air Traffic Division,
Airspace Branch, ACE–520A, DOT
Regional Headquarters Building, Federal
Aviation Administration, 901 Locust,
Kansas City, MO 64106; telephone:
(816) 329–2524.
SUPPLEMENTARY INFORMATION: This
amendment to 14 CFR 71 modifies the
Class E airspace beginning at 700 feet
above the surface at Sheldon Municipal
Airport, IA to contain Instrument Flight
Rule (IFR) operations in controlled
airspace. The area will be depicted on
appropriate aeronautical charts. Class E
airspace areas are published in
Paragraph 6005 of FAA Order 7400.9N,
Airspace Designations and Reporting
Points, dated September 1, 2005, and
effective September 16, 2005, which is
incorporated by reference in 14 CFR
71.1. The Class E airspace designations
listed in this document will be
published subsequently in the Order.
The Direct Final Rule Procedure
The FAA anticipates that this
regulation will not result in adverse or
negative comment and, therefore, is
issuing it as a direct final rule. Previous
actions of this nature have not been
controversial and have not resulted in
adverse comments or objections. Unless
a written adverse or negative comment,
or a written notice of intent to submit
an adverse or negative comment is
received within the comment period,
the regulation will become effective on
the date specified above. After the close
of the comment period, the FAA will
publish a document in the Federal
Register indicating that no adverse or
negative comments were received and
confirming the date on which the final
rule will become effective. If the FAA
does receive, within the comment
period, an adverse or negative comment,
or written notice of intent to submit
such a comment, a document
withdrawing the direct final rule will be
published in the Federal Register, and
a notice of proposed rulemaking may be
published with a new comment period.
Comments Invited
Interested parties are invited to
participate in this rulemaking by
PO 00000
Frm 00015
Fmt 4700
Sfmt 4700
Original ..................
01 ...........................
Original ..................
01 ...........................
Date
August 29, 2001.
September 13, 2001.
August 29, 2001.
September 13, 2001.
submitting such written data, views, or
arguments, as they may desire.
Comments that provide the factual basis
supporting the views and suggestions
presented are particularly helpful in
developing reasoned regulatory
decisions on the proposal. Comments
are specifically invited on the overall
regulatory, aeronautical, economic,
environmental, and energy-related
aspects of the proposal.
Communications should identify both
docket numbers and be submitted in
triplicate to the address listed above.
Commenters wishing the FAA to
acknowledge receipt of their comments
on this notice must submit with those
comments a self-addressed, stamped
postcard on which the following
statement is made: ‘‘Comments to
Docket No. FAA–2005–22006/Airspace
Docket No. 05–ACE–30.’’ The postcard
will be date/time stamped and returned
to the commenter.
Agency Findings
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.
The FAA has determined that this
regulation only involves an established
body of technical regulations for which
frequent and routine amendments are
necessary to keep them operationally
current. Therefore, this regulation—(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)
does not warrant preparation of a
Regulatory Evaluation as the anticipated
impact is so minimal. Since this is a
routine matter that will only affect air
traffic procedures and air navigation, it
is certified that this rule, when
promulgated, will not have a significant
economic impact on a substantial
number of small entities under the
criteria of the Regulatory Flexibility Act.
This rulemaking is promulgated
under the authority described in
E:\FR\FM\03OCR1.SGM
03OCR1
]]>Agencies
[Federal Register Volume 70, Number 190 (Monday, October 3, 2005)]
[Rules and Regulations]
[Pages 57493-57497]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-19045]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2005-22485; Directorate Identifier 2001-NM-337-AD;
Amendment 39-14293; AD 2005-19-28]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A330-301, -321, -322, -
341, and -342 Airplanes; and Model A340-200 and A340-300 Series
Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for comments.
-----------------------------------------------------------------------
SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
certain Airbus Model A330-301, -321, -322, -341, and -342 airplanes;
and Model A340-200 and A340-300 series airplanes. This AD requires
repetitive inspections for cracks in the aft face of the rear spar at
the area adjacent to the bolt holes and the end of the build slot, and
repair if necessary. The AD also provides an optional terminating
action for the repetitive inspections. This AD results from a report
that, during fatigue tests of the wing, cracks were found in the
vertical web of the rear spar between ribs 1 and 2 having initiated at
the build slot. We are issuing this AD to detect and correct fatigue
cracking in the vertical web of the wing rear spar, which could result
in reduced structural integrity of the wing.
DATES: Effective October 18, 2005.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in the AD as of October 18,
2005.
We must receive comments on this AD by December 2, 2005.
ADDRESSES: Use one of the following addresses to submit comments on
this AD.
DOT Docket web site: Go to https://dms.dot.gov and follow
the instructions for sending your comments electronically.
Government-wide rulemaking web site: Go to https://
www.regulations.gov and follow the instructions for sending your
comments electronically.
Mail: Docket Management Facility; U.S. Department of
Transportation, 400 Seventh Street SW., Nassif Building, Room PL-401,
Washington, DC 20590.
Fax: (202) 493-2251.
Hand Delivery: Room PL-401 on the plaza level of the
Nassif Building, 400 Seventh Street SW., Washington, DC, between 9 a.m.
and 5 p.m., Monday through Friday, except Federal holidays.
Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex,
France,
[[Page 57494]]
for service information identified in this AD.
You may examine the contents of the AD docket on the Internet at
https://dms.dot.gov, or in person at the Docket Management Facility,
U.S. Department of Transportation, 400 Seventh Street SW., Room PL-401,
Washington, DC. This docket number is FAA-2005-22485; the directorate
identifier for this docket is 2001-NM-337-AD.
FOR FURTHER INFORMATION CONTACT: Tim Backman, Aerospace Engineer, ANM-
116, International Branch, FAA, Transport Airplane Directorate, 1601
Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 227-
2797; fax (425) 227-1149.
SUPPLEMENTARY INFORMATION:
Comments Invited
Although this is a final rule that was not preceded by notice and
an opportunity for public comment, we invite you to submit any relevant
written data, views, or arguments regarding this AD. Include ``Docket
No. FAA-2005-22485; Directorate Identifier 2001-NM-337-AD'' at the
beginning of your comments. We specifically invite comments on the
overall regulatory, economic, environmental, and energy aspects of the
AD. We will consider all comments received by the closing date and may
amend the AD in light of those comments.
We will post all comments we receive, without change, to https://
dms.dot.gov, including any personal information you provide. We will
also post a report summarizing each substantive verbal contact with FAA
personnel concerning this AD. Using the search function of that web
site, anyone can find and read the comments in any of our dockets,
including the name of the individual who sent the comment (or signed
the comment on behalf of an association, business, labor union, etc.).
You may review the DOT's complete Privacy Act Statement in the Federal
Register published on April 11, 2000 (65 FR 19477-78), or you may visit
https://dms.dot.gov.
Examining the Docket
You may examine the AD docket on the Internet at https://
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 DOT
street address stated in the ADDRESSES section. Comments will be
available in the AD docket shortly after the Docket Management System
receives them.
Discussion
The Direction Generale de l'Aviation Civile (DGAC), which is the
airworthiness authority for France, notified us that an unsafe
condition may exist on certain Airbus Model A330-301, -321, -322, -341,
and -342 airplanes; and Model A340-200 and A340-300 series airplanes.
The DGAC advises that, during fatigue tests of the wing, cracks were
found in the vertical web of the rear spar between ribs 1 and 2. These
fatigue cracks propagated from the build slot to the nearest adjacent
bolt hole. This condition, if not corrected, could result in reduced
structural integrity of the wing.
Relevant Service Information
Airbus has issued Service Bulletin A330-57-3059, Revision 01, dated
September 13, 2001 (for Model A330-301, -321, -322, -341, and -342
airplanes); and Service Bulletin A340-57-4066, Revision 01, dated
September 13, 2001 (for Model A340-200 and A340-300 series airplanes).
The service bulletins describe procedures for doing repetitive high-
frequency eddy current (HFEC) inspections for cracks in the aft face of
the rear spar at the area adjacent to the bolt holes and the end of the
build slot. If no cracks are found, the service bulletins give
intervals for repeating the HFEC inspection until the terminating
action, described below, is accomplished. If any crack is found the
service bulletins give the following procedures for repair, depending
on the extent of the crack.
For any crack that has not reached the fastener holes
``B,'' and is still within a specified modification cut-out area, the
service bulletins state that the airplane may continue operation at
various reduced inspection intervals, depending on the length of the
crack, until the terminating action is accomplished.
For any crack that extends to fastener holes ``B,'' but
not beyond, the service bulletin gives procedures for doing a temporary
repair and then doing the terminating action, described below, at a
specified interval following the temporary repair. The temporary repair
includes the related investigative action of a leak test after the
access panels are installed at the work area.
If any crack is found that extends beyond the specified
modification cut-out area, the service bulletin specifies that
operators should contact Airbus for repair instructions.
Airbus has also issued Service Bulletin A330-57-3058, dated August
29, 2001 (for Model A330-301, -321, -322, -341, and -342 airplanes);
and Service Bulletin A340-57-4065, dated August 29, 2001 (for Model
A340-200 and A340-300 series airplanes). These service bulletins
describe procedures for changing the profile of the end radius of the
build slot to reduce the stress concentration in the area, which
reduces the probability of fatigue cracking. The re-profiling involves
first doing an HFEC inspection for cracks of the aft face of the rear
spar at the area adjacent to the bolt holes. If cracks are found that
will be removed by the re-profiling cut-out, the service bulletins
specify that the re-profiling can proceed. If any crack is found that
is outside the re-profiling cut-out, the service bulletins specify
contacting Airbus for repair instructions before further flight. Doing
this re-profiling eliminates the need for the repetitive inspection
requirements of Airbus Service Bulletins A330-57-3059 and A340-57-4066.
Accomplishing the actions specified in the service information is
intended to adequately address the unsafe condition. The DGAC mandated
the service information and issued French airworthiness directives
2001-268(B) R1, dated July 25, 2001, and 2001-269(B), dated June 27,
2001, to ensure the continued airworthiness of these airplanes in
France.
FAA's Determination and Requirements of This AD
These airplane models are manufactured in France and are 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. We have examined the DGAC's findings,
evaluated all pertinent information, and determined that we need to
issue an AD for products of this type design that are certificated for
operation in the United States.
Therefore, we are issuing this AD to detect and correct fatigue
cracking in the vertical web of the wing rear spar, which could result
in reduced structural integrity of the wing. This AD requires
accomplishing the actions specified in the service information
described previously.
Differences Between the AD and the French Airworthiness Directives
The applicability of the French airworthiness directives excludes
airplanes on which Airbus Service Bulletins A330-57-3058 or A340-57-
4065 was accomplished in service, as applicable. However, we have not
[[Page 57495]]
excluded those airplanes in the applicability of this AD; rather, this
AD includes a requirement to accomplish the actions specified in the
applicable service bulletin. This requirement would ensure that the
actions specified in the service bulletin and required by this AD are
accomplished on all affected airplanes. Operators must continue to
operate the airplane in the configuration required by this AD unless an
alternative method of compliance is approved.
Unlike the procedures described in the service bulletins that are
mandated by the French airworthiness directives, this AD would not
permit further flight if any crack is detected. For cracks that have
not reached fastener holes ``B'' or that extend to fastener holes
``B,'' but not beyond, this AD requires doing the temporary repair in
accordance with the service bulletin. In addition, unlike the
procedures described in the service bulletins, this AD would not permit
further flight if any crack has extended beyond the fastener holes
``B,'' and is still within a specified modification cut-out area. We
have determined that, because of the safety implications and
consequences associated with that cracking, any crack of this size must
be permanently repaired (by using the re-profiling procedure) before
further flight.
The service bulletins that are mandated by the French airworthiness
directives specify that you may contact the manufacturer for
instructions on how to repair certain conditions, but this AD would
require you to repair those conditions using a method that we or the
DGAC (or its delegated agent) approve. 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 AD, a repair we or the DGAC approve would be acceptable
for compliance with this AD.
These differences have been coordinated with the DGAC.
Costs of Compliance
None of the airplanes affected by this action are on the U.S.
Register. All airplanes affected by this AD are currently operated by
non-U.S. operators under foreign registry; therefore, they are not
directly affected by this AD action. However, we consider this AD
necessary to ensure that the unsafe condition is addressed if any
affected airplane is imported and placed on the U.S. Register in the
future.
The following table provides the estimated costs to comply with
this AD for any affected airplane that might be imported and placed on
the U.S. Register in the future.
Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
Average labor
Action Work hours rate per hour Parts cost Cost per airplane
--------------------------------------------------------------------------------------------------------------------------------------------------------
HFEC Inspection, per inspection cycle 2 $65 None..................... $130, per inspection cycle.
Re-profiling (Optional Terminating 70 $65 None..................... $4,550.
Action).
--------------------------------------------------------------------------------------------------------------------------------------------------------
FAA's Determination of the Effective Date
No airplane affected by this AD is currently on the U.S. Register.
Therefore, providing notice and opportunity for public comment is
unnecessary before this AD is issued, and this AD may be made effective
in less than 30 days after it is published in the Federal Register.
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 the 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. 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
adding the following new airworthiness directive (AD):
2005-19-28 Airbus: Amendment 39-14293. Docket No. FAA-2005-22485;
Directorate Identifier 2001-NM-337-AD.
Effective Date
(a) This AD becomes effective October 18, 2005.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Airbus Model A330-301, -321, -322, -341,
and -342 airplanes; and Model A340-211, -212, -213, -311, -312, and
-313 airplanes; certificated in any category; except airplanes on
which Airbus Modification 41300 or 42547 has been accomplished, as
applicable.
[[Page 57496]]
Unsafe Condition
(d) This AD results from a report that, during fatigue tests of
the wing, cracks were found in the vertical web of the rear spar
between ribs 1 and 2 having initiated at the build slot. The FAA is
issuing this AD to detect and correct fatigue cracking in the
vertical web of the wing rear spar, which could result in reduced
structural integrity of the wing.
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.
Service Bulletin Reference
(f) Unless otherwise specified in this AD, the term ``service
bulletin,'' as used in this AD, means the Accomplishment
Instructions of the following service bulletins, as applicable:
(1) For Model A330-301, -321, -322, -341, and -342 airplanes:
Airbus Service Bulletin A330-57-3059, Revision 01, dated September
13, 2001; and
(2) For Model A340-211, -212, -213, -311, -312, and -313
airplanes: Airbus Service Bulletin A340-57-4066, Revision 01, dated
September 13, 2001.
Repetitive Inspections
(g) At the applicable threshold in Table 1 of this AD, do a high
frequency eddy current inspection for cracks in the aft face of the
rear spar at the area adjacent to the bolt holes and the end of the
build slot; and repeat the inspection thereafter at the applicable
repetitive interval in Table 1 of this AD, until the repair required
by paragraph (k) of this AD is accomplished. Do all inspections in
accordance with the applicable service bulletin.
Table 1.--Inspection Thresholds and Intervals
----------------------------------------------------------------------------------------------------------------
Threshold Repetitive interval
Model-- ------------------------------------------------------------------------------
The later of-- The earlier of--
----------------------------------------------------------------------------------------------------------------
A330-301, -321, -322, -341, and - Before the accumulation of 8,300 flight cycles; and
342 airplanes. 10,300 total flight cycles or 32,000 25,800 flight hours.
total flight hours, whichever occurs
earlier; or
Within 6 months after the
effective date of this AD.
A340-211, -212, -213, -311, -312, Before the accumulation of 8,200 flight cycles; and
and -313 airplanes. 9,800 total flight cycles or total 40,100 flight hours.
48,200 flight hours, whichever occurs
earlier; or
Within 6 months after the
effective date of this AD.
----------------------------------------------------------------------------------------------------------------
Repair
(h) If any crack is found during any inspection required by
paragraph (g) of this AD, and the crack has not reached the fastener
holes ``B'' or extends to fastener holes ``B,'' but not beyond,
before further flight: Do the temporary repair in accordance with
the applicable service bulletin and repeat the inspection thereafter
at the applicable interval in paragraph (g) of this AD until the
permanent repair required by paragraph (k) of this AD is
accomplished.
(i) If any crack is found during any inspection required by
paragraph (g) of this AD, and the crack has extended beyond fastener
holes ``B,'': Before further flight, do the permanent repair in
paragraph (k) of this AD.
(j) Where the service bulletin specifies that operators may
contact the manufacturer for instructions on how to repair cracks
that extend beyond the modification cut-out area: Before further
flight, repair according to a method approved by either the Manager,
International Branch, ANM-116, FAA, Transport Airplane Directorate;
or the Direction Generale de l'Aviation Civile (DGAC) (or its
delegated agent).
Optional Terminating Action--Permanent Repair (Re-Profiling)
(k) Doing the permanent repair in accordance with the applicable
service bulletin in paragraph (k)(1) or (k)(2) of this AD terminates
the repetitive inspection requirements of this AD. Where the service
bulletins in paragraph (k)(1) and (k)(2) of this AD specify that
operators may contact the manufacturer for instructions on how to
repair certain conditions: Before further flight, repair according
to a method approved by either the Manager, International Branch,
ANM-116, FAA, Transport Airplane Directorate; or the DGAC (or its
delegated agent).
(1) For Model A330-301, -321, -322, -341, and -342 airplanes:
Airbus Service Bulletin A330-57-3058, dated August 29, 2001.
(2) For Model A340-211, -212, -213, -311, -312, and -313
airplanes: Airbus Service Bulletin A340-57-4065, dated August 29,
2001.
Actions Done in Accordance With Previous Issues of Service Bulletins
(l) Actions done before the effective date of this AD in
accordance with the service bulletins identified in Table 2 of this
AD, are acceptable for compliance with the corresponding action
required by this AD.
Table 2.--Previous Issues of Service Bulletins
------------------------------------------------------------------------
Airbus Service Bulletins Date
------------------------------------------------------------------------
A330-57-3059........................... March 16, 2001.
A340-57-4066........................... March 16, 2001.
------------------------------------------------------------------------
Alternative Methods of Compliance (AMOCs)
(m)(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
(n) French airworthiness directives 2001-268(B) R1, dated July
25, 2001, and 2001-269(B), dated June 27, 2001, also address the
subject of this AD.
Material Incorporated by Reference
(o) You must use the Airbus service bulletins identified in
Table 3 of this AD to perform the actions that are required by this
AD, as applicable, unless the AD specifies otherwise. The Director
of the Federal Register approved the incorporation by reference of
these documents in accordance with 5 U.S.C. 552(a) and 1 CFR part
51. 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 https://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 https://www.archives.gov/federal_register/
code_of_federal_regulations/ibr_locations.html.
[[Page 57497]]
Table 3.--Material Incorporated by Reference
----------------------------------------------------------------------------------------------------------------
Airbus Service Bulletins Revision level Date
----------------------------------------------------------------------------------------------------------------
A330-57-3058.......................... Original......................... August 29, 2001.
A330-57-3059.......................... 01............................... September 13, 2001.
A340-57-4065.......................... Original......................... August 29, 2001.
A340-57-4066.......................... 01............................... September 13, 2001.
----------------------------------------------------------------------------------------------------------------
Issued in Renton, Washington, on September 15, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 05-19045 Filed 9-30-05; 8:45 am]
BILLING CODE 4910-13-P
