Airworthiness Directives; Airbus Model A330-200 and -300, and A340-200 and -300 Series Airplanes, 40387-40389 [06-6180]
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Federal Register / Vol. 71, No. 136 / Monday, July 17, 2006 / Rules and Regulations
40387
Compliance
(e) To address this problem, you must do
the following:
Actions
Compliance
Procedures
(1) Inspect, visually and using fluorescent dye
penetrant, the support structures for the inboard and center aileron hinge fittings on
both wings for cracks.
(2) If you do not find cracks during the inspection required in paragraph (e)(1) of this AD,
reinforce the support structures for the inboard and center aileron hinge fittings on
both wings that are crack free.
(3) If you find cracks during the inspection required in paragraph (e)(1) of this AD, replace
and reinforce the cracked support structure.
Within the next 150 hours time-in-service or
12 months after August 21, 2006 (the effective date of this AD), whichever occurs first.
Before further flight after the inspection required in paragraph (e)(1) of this AD. After
doing the reinforcement, no further action is
required.
Follow Twin Commander Aircraft LLC Alert
Service Bulletin 236A and Alert Service Bulletin 238, both dated December 21, 2004,
as applicable.
Follow Twin Commander Aircraft LLC Alert
Service Bulletin 236A and Alert Service Bulletin 238, both dated December 21, 2004,
as applicable.
Before further flight after the inspection required in paragraph (e)(1) of this AD. After
doing the replacement and reinforcement,
no further action is required.
Follow Twin Commander Aircraft LLC Alert
Service Bulletin 236A and Alert Service Bulletin 238, both dated December 21, 2004,
as applicable.
Alternative Methods of Compliance
(AMOCs)
DEPARTMENT OF TRANSPORTATION
(f) The Manager, Seattle Aircraft
Certification Office (ACO), FAA, ATTN:
Vince Massey, Aerospace Engineer, Seattle,
ACO, 1601 Lind Avenue SW., Renton, WA
98057; telephone: (425) 917–6475; facsimile:
(425) 917–6590, has the authority to approve
AMOCs for this AD, if requested using the
procedures found in 14 CFR 39.19.
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2006–24522; Directorate
Identifier 2006–NM–002–AD; Amendment
39–14680; AD 2006–14–09]
RIN 2120–AA64
Material Incorporated by Reference
rmajette on PROD1PC67 with RULES
(g) You must do the actions required by
this AD following Twin Commander Aircraft
LLC Alert Service Bulletin 236A and Twin
Commander Aircraft LLC Alert Service
Bulletin 238, both dated December 21, 2004.
The Director of the Federal Register approved
the incorporation by reference of these
service bulletins in accordance with 5 U.S.C.
552(a) and 1 CFR part 51. To get a copy of
this service information, contact Twin
Commander Aircraft LLC, 19010 59th Drive
NE., Arlington, WA 98223, telephone: (360)
435–9797; facsimile: (360) 435–1112. To
review copies of this service information, go
to the National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, go
to: https://www.archives.gov/federal_register/
code_of_federal_regulations/
ibr_locations.html or call (202) 741–6030. To
view the AD docket, go to the Docket
Management Facility; US Department of
Transportation, 400 Seventh Street, SW.,
Nassif Building, Room PL–401, Washington,
DC 20590–001 or on the Internet at https://
dms.dot.gov. The docket number is FAA–
2006–23785; Directorate Identifier 2006–CE–
10–AD.
Issued in Kansas City, Missouri, on July 7,
2006.
Kim Smith,
Manager, Small Airplane Directorate, Aircraft
Certification Service.
[FR Doc. 06–6225 Filed 7–14–06; 8:45 am]
BILLING CODE 4910–13–M
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15:22 Jul 14, 2006
Jkt 208001
Airworthiness Directives; Airbus Model
A330–200 and –300, and A340–200 and
–300 Series Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
SUMMARY: The FAA is adopting a new
airworthiness directive (AD) for certain
Airbus Model A330–200 and –300, and
A340–200 and –300 series airplanes.
This AD requires modifying certain
rotary actuator assemblies for the
leading edge slat. This AD results from
a leak found at the seal of the torque
limiter output shaft of the Type A rotary
actuator of leading edge slat No. 1. We
are issuing this AD to prevent a decrease
in the torque limiter function, which
could result in degradation and damage
to the attachment bolts of the leading
edge slat, loss of the slat, and
consequent reduced control of the
airplane.
This AD becomes effective
August 21, 2006.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in the AD
as of August 21, 2006.
ADDRESSES: You may examine 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,
DATES:
PO 00000
Frm 00003
Fmt 4700
Sfmt 4700
SW., Nassif Building, Room PL–401,
Washington, DC.
Contact Airbus, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France,
for the service information identified in
this AD.
Tim
Backman, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton,
Washington 98055–4056; telephone
(425) 227–2797; fax (425) 227–1149.
FOR FURTHER INFORMATION CONTACT:
SUPPLEMENTARY INFORMATION:
Examining the Docket
You may examine the airworthiness
directive (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 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 would
apply to certain Airbus Model A330–
200 and –300, and A340–200 and –300
series airplanes. That NPRM was
published in the Federal Register on
April 21, 2006 (71 FR 20599). That
NPRM proposed to require modifying
certain rotary actuator assemblies for the
leading edge slat.
Comments
We provided the public the
opportunity to participate in the
development of this AD. We have
considered the single comment
received.
E:\FR\FM\17JYR1.SGM
17JYR1
40388
Federal Register / Vol. 71, No. 136 / Monday, July 17, 2006 / Rules and Regulations
Request To Revise the Applicability
Airbus requests that Model A330–302
and –303 airplanes be included in the
applicability of paragraph (c) of the
NPRM. Airbus states that those
airplanes are in the process of being
type certificated in the U.S.
We agree. We have determined that
Model A330–302 and –303 airplanes are
subject to the identified unsafe
condition of this AD. Therefore, we
have revised the applicability of
paragraph (c) of this AD to include those
airplanes to ensure that the identified
unsafe condition is addressed if any of
those affected airplanes are imported
and placed on the U.S. Register in the
future.
Conclusion
We have carefully reviewed the
available data, including the comment
received, and determined that air safety
and the public interest require adopting
the AD with the change described
previously. This change will neither
increase the economic burden on any
operator nor increase the scope of the
AD.
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Costs of Compliance
This AD affects about 9 airplanes of
U.S. registry. The modification
(including operational test) takes about
4 work hours per airplane, at an average
labor rate of $80 per work hour.
Required parts are free of charge. Based
on these figures, the estimated cost of
the AD for U.S. operators is $2,880, or
$320 per airplane.
Currently, there are no affected Model
A330–302 and –303 airplanes on the
U.S. Register. However, if an affected
airplane is imported and placed on the
U.S. Register in the future, it would be
subject to the same per-airplane cost
specified above.
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
VerDate Aug<31>2005
15:22 Jul 14, 2006
Jkt 208001
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
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
I
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
2006–14–09 Airbus: Amendment 39–14680.
Docket No. FAA–2006–24522;
Directorate Identifier 2006–NM–002–AD.
Effective Date
(a) This AD becomes effective August 21,
2006.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Airbus Model A330–
201, 202, –203, –223, and –243; A330–301,
–302, –303, –321, –322, –323, –341, –342,
PO 00000
Frm 00004
Fmt 4700
Sfmt 4700
and –343; A340–211, –212, and –213; and
A340–311, –312, and –313 airplanes,
certificated in any category; except airplanes
on which Airbus Modification 50138 was
done during production.
Unsafe Condition
(d) This AD results from a leak found at the
seal of the torque limiter output shaft of the
Type A rotary actuator of leading edge slat
No. 1. We are issuing this AD to prevent a
decrease in the torque limiter function,
which could result in degradation and
damage to the attachment bolts of the leading
edge slat, loss of the slat, and consequent
reduced control 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.
Modification
(f) Within 38 months after the effective
date of this AD: Modify any Type A rotary
actuator assembly for the leading edge slat
having part number (P/N) 954A0000–01 or
954A0000–02, or P/N 954B0000–01, as
applicable, by doing all the applicable
actions in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A330–27–3100, Revision 01,
dated May 23, 2005; or A340–27–4106,
Revision 01, dated May 23, 2005; as
applicable.
(g) Modification of any Type A rotary
actuator assembly for the leading edge slat
having P/N 954B0000–01, in accordance with
Airbus Service Bulletin A330–27–3105 or
A340–27–4110, both Revision 02, both dated
October 10, 2005; as applicable; is acceptable
for compliance with the corresponding
modification specified in paragraph (f) of this
AD.
Note 1: Airbus Service Bulletins A330–27–
3100 and A340–27–4106 refer to Goodrich
Actuation Systems Service Bulletin 954–27–
M954–07, Revision 2, dated August 9, 2004;
and Airbus Service Bulletins A330–27–3105
and A340–27–4110 refer to Goodrich
Actuation Systems Service Bulletin 954–27–
M954–06, Revision 2, dated May 20, 2004; as
additional sources of service information for
modifying the rotary actuator assembly for
the leading edge slat.
Parts Installation
(h) As of the effective date of this AD, no
Type A rotary actuator assembly for the
leading edge slat having P/N 954A0000–01,
–02, or 954B0000–01 may be installed unless
the part has been modified in accordance
with the actions required by paragraph (f) or
(g) of this AD, as applicable.
Actions Accomplished Previously
(i) Modifications done before the effective
date of this AD in accordance with Airbus
Service Bulletins A330–27–3100, dated
October 30, 2002; A330–27–3105, dated
October 30, 2002, or Revision 01, dated
March 27, 2003; A340–27–4106, dated
October 30, 2002; or A340–27–4110, dated
October 30, 2002, or Revision 01, dated
March 27, 2003; as applicable; are acceptable
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17JYR1
Federal Register / Vol. 71, No. 136 / Monday, July 17, 2006 / Rules and Regulations
for compliance with the corresponding
requirements of paragraphs (f) and (g) of this
AD, as applicable.
Alternative Methods of Compliance
(AMOCs)
Related Information
(k) French airworthiness directives F–
2005–067 and F–2005–068, both dated April
27, 2005, also address the subject of this AD.
Material Incorporated by Reference
(l) You must use the applicable Airbus
service bulletin identified in Table 1 of this
AD to perform the actions that are required
by this AD, 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.
TABLE 1.—MATERIAL INCORPORATED
BY REFERENCE
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A330–27–3100
A330–27–3105
A340–27–4106
A340–27–4110
Revision
level
..
..
..
..
01
02
01
02
Date
May 23, 2005.
Oct. 10, 2005.
May 23, 2005.
Oct. 10, 2005.
Issued in Renton, Washington, on July 6,
2006.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 06–6180 Filed 7–14–06; 8:45 am]
BILLING CODE 4910–13–P
VerDate Aug<31>2005
15:22 Jul 14, 2006
Federal Aviation Administration
14 CFR Part 39
(j)(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 § 39.19 on any airplane to
which the AMOC applies, notify the
appropriate principal inspector in the FAA
Flight Standards Certificate Holding District
Office.
Airbus Service
Bulletin
DEPARTMENT OF TRANSPORTATION
Jkt 208001
[Docket No. FAA–2006–23644; Directorate
Identifier 2006–CE–03–AD; Amendment 39–
14679; AD 2006–14–08]
RIN 2120–AA64
Airworthiness Directives; Mitsubishi
Heavy Industries MU–2B Series
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
SUMMARY: The FAA adopts a new
airworthiness directive (AD) for some
Mitsubishi Heavy Industries (MHI) MU–
2B series airplanes. This AD requires
you to verify that the current flight idle
blade angles are set at 12 degrees. If not
already set at that angle, set the flight
idle blade angles to 12 degrees. This AD
results from a recent safety evaluation
that used a data-driven approach to
analyze the design, operation, and
maintenance of the MU–2B series
airplanes in order to determine their
safety and define what steps, if any, are
necessary for their safe operation. Part
of that evaluation was the identification
of unsafe conditions that exist or could
develop on the affected type design
airplanes. We are issuing this AD to
prevent incorrect flight idle blade angle
settings. This unsafe condition, if not
corrected, could lead to an asymmetric
thrust situation in certain flight
conditions, which could result in
airplane controllability problems.
DATES: This AD becomes effective on
August 21, 2006.
As of August 21, 2006, the Director of
the Federal Register approved the
incorporation by reference of certain
publications listed in the regulation.
ADDRESSES: To get the service
information identified in this AD,
contact Mitsubishi Heavy Industries
America, Inc., 4951 Airport Parkway,
Suite 800, Addison, Texas 75001;
telephone: 972–934–5480; facsimile:
972–934–5488.
To view the AD docket, go to the
Docket Management Facility; U.S.
Department of Transportation, 400
Seventh Street, SW., Nassif Building,
Room PL–401, Washington, DC 20590–
001 or on the Internet at https://
dms.dot.gov. The docket number is
FAA–2006–23644; Directorate Identifier
2006–CE–03–AD.
FOR FURTHER INFORMATION CONTACT: Rao
Edupuganti, Aerospace Engineer, Fort
Worth ACO, ASW–150, Rotorcraft
PO 00000
Frm 00005
Fmt 4700
Sfmt 4700
40389
Directorate, FAA, 2601 Meacham
Boulevard, Fort Worth, Texas 76137–
4298; telephone: 817–222–5284;
facsimile: 817–222–5960.
SUPPLEMENTARY INFORMATION:
Discussion
On February 3, 2006, we issued a
proposal to amend part 39 of the Federal
Aviation Regulations (14 CFR part 39) to
include an AD that would apply to some
MHI MU–2B series airplanes. This
proposal was published in the Federal
Register as a notice of proposed
rulemaking (NPRM) on February 9, 2006
(71 FR 6685). The NPRM proposed to
require you to check the flight idle blade
angle setting and set to 12 degrees if not
already.
Comments
We provided the public the
opportunity to participate in developing
this AD. The following presents the
comment received on the proposal and
FAA’s response to the comment:
Comment Issue: Need for Issuance of
This AD After 25 Years Since the
Issuance of the Service Bulletin
Mitsubishi Heavy Industries America,
Inc. questions the need for an AD 25
years after the service bulletin has been
issued. In 1980, MHI (Mitsubishi
Aircraft International, Inc. at the time of
issuance) issued Service Bulletin No.
SB016/61–001, dated March 18, 1980, to
change the flight blade angles from 16
degrees to 12 degrees. The type
certificate data sheet for the affected
airplanes was also revised to
incorporate this change, which included
Note 3 to indicate a small group of
airplanes that may not have
incorporated Service Bulletin No.
SB016/61–001. No Japanese AD was
issued because no airplanes on the
Japanese type certificate were affected
by this change. The Japanese airplanes
had already incorporated the intent of
the service bulletin.
At the time the service bulletin was
issued, the FAA evaluated the available
information and found that there were
no reports of problems or incidents of
flight idle blade angle settings with
airplanes of U.S. registry. Therefore, we
did not issue an airworthiness directive
at that time.
Based on information received from
the safety evaluation done in 2005 for
the MU–2B series airplanes, we
identified flight idle blade angles set at
16 degrees instead of 12 degrees as a
potential problem.
After analyzing this issue using our
risk-based methodology and the
information received from the safety
evaluation, we identified that an unsafe
E:\FR\FM\17JYR1.SGM
17JYR1
]]>Agencies
[Federal Register Volume 71, Number 136 (Monday, July 17, 2006)]
[Rules and Regulations]
[Pages 40387-40389]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 06-6180]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2006-24522; Directorate Identifier 2006-NM-002-AD;
Amendment 39-14680; AD 2006-14-09]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A330-200 and -300, and
A340-200 and -300 Series Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
certain Airbus Model A330-200 and -300, and A340-200 and -300 series
airplanes. This AD requires modifying certain rotary actuator
assemblies for the leading edge slat. This AD results from a leak found
at the seal of the torque limiter output shaft of the Type A rotary
actuator of leading edge slat No. 1. We are issuing this AD to prevent
a decrease in the torque limiter function, which could result in
degradation and damage to the attachment bolts of the leading edge
slat, loss of the slat, and consequent reduced control of the airplane.
DATES: This AD becomes effective August 21, 2006.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in the AD as of August 21,
2006.
ADDRESSES: You may examine 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., Nassif Building,
Room PL-401, Washington, DC.
Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex,
France, for the service information identified in this AD.
FOR FURTHER INFORMATION CONTACT: Tim Backman, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425)
227-2797; fax (425) 227-1149.
SUPPLEMENTARY INFORMATION:
Examining the Docket
You may examine the airworthiness directive (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 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 would apply to certain Airbus Model
A330-200 and -300, and A340-200 and -300 series airplanes. That NPRM
was published in the Federal Register on April 21, 2006 (71 FR 20599).
That NPRM proposed to require modifying certain rotary actuator
assemblies for the leading edge slat.
Comments
We provided the public the opportunity to participate in the
development of this AD. We have considered the single comment received.
[[Page 40388]]
Request To Revise the Applicability
Airbus requests that Model A330-302 and -303 airplanes be included
in the applicability of paragraph (c) of the NPRM. Airbus states that
those airplanes are in the process of being type certificated in the
U.S.
We agree. We have determined that Model A330-302 and -303 airplanes
are subject to the identified unsafe condition of this AD. Therefore,
we have revised the applicability of paragraph (c) of this AD to
include those airplanes to ensure that the identified unsafe condition
is addressed if any of those affected airplanes are imported and placed
on the U.S. Register in the future.
Conclusion
We have carefully reviewed the available data, including the
comment received, and determined that air safety and the public
interest require adopting the AD with the change described previously.
This change will neither increase the economic burden on any operator
nor increase the scope of the AD.
Costs of Compliance
This AD affects about 9 airplanes of U.S. registry. The
modification (including operational test) takes about 4 work hours per
airplane, at an average labor rate of $80 per work hour. Required parts
are free of charge. Based on these figures, the estimated cost of the
AD for U.S. operators is $2,880, or $320 per airplane.
Currently, there are no affected Model A330-302 and -303 airplanes
on the U.S. Register. However, if an affected airplane is imported and
placed on the U.S. Register in the future, it would be subject to the
same per-airplane cost specified above.
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
adding the following new airworthiness directive (AD):
2006-14-09 Airbus: Amendment 39-14680. Docket No. FAA-2006-24522;
Directorate Identifier 2006-NM-002-AD.
Effective Date
(a) This AD becomes effective August 21, 2006.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Airbus Model A330-201, 202, -203, -223,
and -243; A330-301, -302, -303, -321, -322, -323, -341, -342, and -
343; A340-211, -212, and -213; and A340-311, -312, and -313
airplanes, certificated in any category; except airplanes on which
Airbus Modification 50138 was done during production.
Unsafe Condition
(d) This AD results from a leak found at the seal of the torque
limiter output shaft of the Type A rotary actuator of leading edge
slat No. 1. We are issuing this AD to prevent a decrease in the
torque limiter function, which could result in degradation and
damage to the attachment bolts of the leading edge slat, loss of the
slat, and consequent reduced control 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.
Modification
(f) Within 38 months after the effective date of this AD: Modify
any Type A rotary actuator assembly for the leading edge slat having
part number (P/N) 954A0000-01 or 954A0000-02, or P/N 954B0000-01, as
applicable, by doing all the applicable actions in accordance with
the Accomplishment Instructions of Airbus Service Bulletin A330-27-
3100, Revision 01, dated May 23, 2005; or A340-27-4106, Revision 01,
dated May 23, 2005; as applicable.
(g) Modification of any Type A rotary actuator assembly for the
leading edge slat having P/N 954B0000-01, in accordance with Airbus
Service Bulletin A330-27-3105 or A340-27-4110, both Revision 02,
both dated October 10, 2005; as applicable; is acceptable for
compliance with the corresponding modification specified in
paragraph (f) of this AD.
Note 1: Airbus Service Bulletins A330-27-3100 and A340-27-4106
refer to Goodrich Actuation Systems Service Bulletin 954-27-M954-07,
Revision 2, dated August 9, 2004; and Airbus Service Bulletins A330-
27-3105 and A340-27-4110 refer to Goodrich Actuation Systems Service
Bulletin 954-27-M954-06, Revision 2, dated May 20, 2004; as
additional sources of service information for modifying the rotary
actuator assembly for the leading edge slat.
Parts Installation
(h) As of the effective date of this AD, no Type A rotary
actuator assembly for the leading edge slat having P/N 954A0000-01,
-02, or 954B0000-01 may be installed unless the part has been
modified in accordance with the actions required by paragraph (f) or
(g) of this AD, as applicable.
Actions Accomplished Previously
(i) Modifications done before the effective date of this AD in
accordance with Airbus Service Bulletins A330-27-3100, dated October
30, 2002; A330-27-3105, dated October 30, 2002, or Revision 01,
dated March 27, 2003; A340-27-4106, dated October 30, 2002; or A340-
27-4110, dated October 30, 2002, or Revision 01, dated March 27,
2003; as applicable; are acceptable
[[Page 40389]]
for compliance with the corresponding requirements of paragraphs (f)
and (g) of this AD, as applicable.
Alternative Methods of Compliance (AMOCs)
(j)(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
(k) French airworthiness directives F-2005-067 and F-2005-068,
both dated April 27, 2005, also address the subject of this AD.
Material Incorporated by Reference
(l) You must use the applicable Airbus service bulletin
identified in Table 1 of this AD to perform the actions that are
required by this AD, 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.
Table 1.--Material Incorporated by Reference
------------------------------------------------------------------------
Revision
Airbus Service Bulletin level Date
------------------------------------------------------------------------
A330-27-3100....................... 01 May 23, 2005.
A330-27-3105....................... 02 Oct. 10, 2005.
A340-27-4106....................... 01 May 23, 2005.
A340-27-4110....................... 02 Oct. 10, 2005.
------------------------------------------------------------------------
Issued in Renton, Washington, on July 6, 2006.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 06-6180 Filed 7-14-06; 8:45 am]
BILLING CODE 4910-13-P
