Airworthiness Directives; Airbus Model A310-200 and -300 Series Airplanes, 28254-28256 [06-4503]
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28254
Federal Register / Vol. 71, No. 94 / Tuesday, May 16, 2006 / Rules and Regulations
Alternative Methods of Compliance
(AMOCs)
(1)(l) 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 14 CFR 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
(m) French airworthiness directive F–
2004–028 R2, dated October 26, 2005, also
addresses the subject of this AD.
Material Incorporated by Reference
(n) You must use Airbus Service Bulletin
A330–54–3021, Revision 01, including
Appendix 01, dated June 16, 2004, to perform
the actions that are required by this AD,
unless the AD specifies otherwise. If you do
the optional terminating action, you must use
Airbus Service Bulletin A330–54–3022,
dated May 25, 2005, to perform that action.
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.
Issued in Renton, Washington, on May 8,
2006.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 06–4504 Filed 5–15–06; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2006–24104; Directorate
Identifier 2005–NM–231–AD; Amendment
39–14595; AD 2006–10–11]
cprice-sewell on PROD1PC66 with RULES
RIN 2120–AA64
Airworthiness Directives; Airbus Model
A310–200 and –300 Series Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
VerDate Aug<31>2005
15:11 May 15, 2006
Jkt 208001
SUMMARY: The FAA is adopting a new
airworthiness directive (AD) for certain
Airbus Model A310–200 and –300 series
airplanes. This AD requires repetitive
inspections for cracking of the flap
transmission shafts, and replacing the
transmission shafts if necessary. This
AD also provides an optional
terminating action for the repetitive
inspections. This AD results from
reports of longitudinal cracks due to
stress corrosion in the transmission
shafts between the power control unit
(PCU) and the torque limiters of the flap
transmission system. We are issuing this
AD to detect and correct cracking of the
flap transmission shaft, which could
compromise shaft structural integrity
and lead to a disabled flap transmission
shaft and reduced controllability of the
airplane.
DATES: This AD becomes effective June
20, 2006.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in the AD
as of June 20, 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 service information identified in this
AD.
FOR FURTHER INFORMATION CONTACT:
Thomas Stafford, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton,
Washington 98055–4056; 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
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 A310–
200 and –300 series airplanes. That
NPRM was published in the Federal
Register on March 9, 2006 (71 FR
PO 00000
Frm 00026
Fmt 4700
Sfmt 4700
12152). That NPRM proposed to require
repetitive inspections for cracking of the
flap transmission shafts, and replacing
the transmission shafts if necessary. The
NPRM also proposed to provide an
optional terminating action for the
repetitive inspections.
Comments
We provided the public the
opportunity to participate in the
development of this AD. We received no
comments on the NPRM or on the
determination of the cost to the public.
Change to NPRM
We inadvertently deleted reference to
the reporting requirement stated in the
´ ´
Direction Generale de l’Aviation Civile
(DGAC) Airworthiness Directive and the
Airbus service bulletin. This AD does
not require reporting the results of the
inspection to Airbus, which is a
difference among the DGAC
Airworthiness Directive, the service
bulletin, and this AD. We have added
our non-requirement as paragraph (j) of
this AD and reidentified subsequent
paragraphs accordingly.
Conclusion
We have carefully reviewed the
available data and determined that air
safety and the public interest require
adopting the AD with the change
described previously. We have
determined that this change will neither
increase the economic burden on any
operator nor increase the scope of the
AD.
Costs of Compliance
This AD will affect about 59 airplanes
of U.S. registry. The required
inspections will take about 1 work hour
per airplane, at an average labor rate of
$65 per work hour. Based on these
figures, the estimated cost of the AD for
U.S. operators is $3,835, or $65 per
airplane, per inspection cycle.
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
E:\FR\FM\16MYR1.SGM
16MYR1
Federal Register / Vol. 71, No. 94 / Tuesday, May 16, 2006 / Rules and Regulations
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.
Applicability
(c) This AD applies to Airbus Model A310–
203, –204, –221, –222, –304, –322, –324, and
–325 airplanes, certificated in any category;
except for airplanes on which Airbus
Modification 12247 has been embodied in
production.
Regulatory Findings
Unsafe Condition
(d) This AD results from reports of
longitudinal cracks due to stress corrosion in
the transmission shafts between the power
control unit (PCU) and the torque limiters of
the flap transmission system. We are issuing
this AD to detect and correct cracking of the
flap transmission shaft, which could
compromise shaft structural integrity and
lead to a disabled flap transmission shaft and
reduced controllability of the airplane.
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):
cprice-sewell on PROD1PC66 with RULES
I
2006–10–11 Airbus: Amendment 39–14595.
FAA–2006–24104; Directorate Identifier
2005–NM–231–AD.
Effective Date
(a) This AD becomes effective June 20,
2006.
Affected ADs
(b) None.
VerDate Aug<31>2005
15:11 May 15, 2006
Jkt 208001
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.
Inspection and Corrective Action
(f) At the earlier of the compliance times
specified in paragraph (f)(1) or (f)(2) of this
AD: Perform a detailed inspection for stress
corrosion cracking of the flight transmission
shafts located between the PCU and the
torque limiters in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A310–27–2092, Revision 02,
dated April 11, 2005. Thereafter, repeat the
inspections as required by paragraph (g) of
this AD. Before further flight, replace any
cracked transmission shaft discovered during
any inspection required by this AD with a
new or reconditioned shaft, in accordance
with the Accomplishment Instructions of
Airbus Service Bulletin A310–27–2095,
dated March 29, 2000.
(1) Within 2,000 flight hours after the last
flap asymmetry protection test performed in
accordance with Airbus A310 Maintenance
Planning Document (MPD) Task 275600–01–
1.
(2) Within 8,000 flight cycles after the last
flap asymmetry protection test performed in
accordance with Airbus A310 MPD Task
275600–02–1 or 800 flight cycles after the
effective date of this AD, whichever comes
later.
Note 1: Airbus Service Bulletin A310–27–
2092, Revision 02, dated April 11, 2005,
refers to Lucas Liebherr Service Bulletin
551A–27–624, Revision 1, dated August 18,
2000, as an additional source of service
information for accomplishing the
inspections.
Note 2: Airbus Service Bulletin A310–27–
2092, Revision 02, refers to Airbus Service
Bulletin A310–27–2095, dated March 29,
2000, as a source of service information for
replacing the flap transmission shafts.
Note 3: Airbus Service Bulletin A310–27–
2095 refers to Lucas Liebherr Service Bulletin
551A–27-M551–05, dated January 12, 2000,
as an additional source of service information
for replacing the flap transmission shafts.
Repetitive Inspections
(g) Repeat the inspection required by
paragraph (f) of this AD at the applicable
PO 00000
Frm 00027
Fmt 4700
Sfmt 4700
28255
times specified in paragraphs (g)(1), (g)(2),
and (g)(3) of this AD.
(1) Before further flight after any
occurrence of jamming of the flap
transmission system.
(2) At intervals not to exceed 2,000 flight
hours after each flap asymmetry protection
test performed in accordance with Airbus
A310 MPD Task 275600–01–1.
(3) At intervals not to exceed 8,000 flight
cycles after each flap asymmetry protection
test performed in accordance with Airbus
A310 MPD Task 275600–02–1.
Optional Terminating Action
(h) Replacing any flap transmission shaft
with a new or reconditioned transmission
shaft in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A310–27–2095, dated March
29, 2000, ends the inspections required for
that transmission shaft only.
Actions Performed Using Previously Issued
Service Information
(i) Actions performed in accordance with
Airbus Service Bulletin A310–27–2092,
dated April 9, 1999; or Revision 01, dated
December 11, 2001, are considered
acceptable for compliance with the
corresponding requirements of this AD.
No Reporting
(j) Although Airbus Service Bulletin A310–
27–2092, Revision 02, dated April 11, 2005,
specifies to submit certain information to the
manufacturer, this AD does not include that
requirement.
Alternative Methods of Compliance
(AMOCs)
(k)(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.
Related Information
(l) French airworthiness directive F–2005–
174, dated October 26, 2005, also addresses
the subject of this AD.
Material Incorporated by Reference
(m) You must use Airbus Service Bulletin
A310–27–2092, Revision 02, dated April 11,
2005; and Airbus Service Bulletin A310–27–
2095, dated March 29, 2000; as applicable, 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 copies 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
E:\FR\FM\16MYR1.SGM
16MYR1
28256
Federal Register / Vol. 71, No. 94 / Tuesday, May 16, 2006 / Rules and Regulations
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.
Issued in Renton, Washington, on May 8,
2006.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 06–4503 Filed 5–15–06; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2006–24120; Directorate
Identifier 2006–NM–021–AD; Amendment
39–14593; AD 2006–10–09]
RIN 2120–AA64
Airworthiness Directives; Empresa
Brasileira de Aeronautica S.A.
(EMBRAER) Model EMB–120, –120ER,
–120FC, –120QC, and –120RT
Airplanes in Operation
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
cprice-sewell on PROD1PC66 with RULES
AGENCY:
SUMMARY: The FAA is adopting a new
airworthiness directive (AD) for all
Empresa Brasileira de Aeronautica S.A.
(EMBRAER) Model EMB–120, –120ER,
–120FC, –120QC, and –120RT airplanes
in operation. This AD requires replacing
the protective tubes and conduits of the
wiring harnesses of the refueling vent
and pilot valves with non-conductive
hoses; modifying the harness wiring and
supports; and rerouting the harnesses to
prevent interference with adjacent
strobe light connectors; as applicable.
This AD results from a fuel system
review conducted by the manufacturer.
We are issuing this AD to prevent a
potential source of ignition near a fuel
tank, which, in combination with
flammable fuel vapors, could result in a
fuel tank explosion.
DATES: This AD becomes effective June
20, 2006.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in the AD
as of June 20, 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.
VerDate Aug<31>2005
15:11 May 15, 2006
Jkt 208001
Contact Empresa Brasileira de
Aeronautica S.A. (EMBRAER), P.O. Box
343—CEP 12.225, Sao Jose dos
Campos—SP, Brazil, for service
information identified in this AD.
FOR FURTHER INFORMATION CONTACT: Dan
Rodina, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton,
Washington 98055–4056; telephone
(425) 227–2125; 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 all Empresa Brasileira de
Aeronautica S.A. (EMBRAER) EMB–
120( ) airplane models in operation.
That NPRM was published in the
Federal Register on March 14, 2006 (71
FR 13058). That NPRM proposed to
require replacing the protective tubes
and conduits of the wiring harnesses of
the refueling vent and pilot valves with
non-conductive hoses; modifying the
harness wiring and supports; and
rerouting the harnesses to prevent
interference with adjacent strobe light
connectors; as applicable.
Comments
We provided the public the
opportunity to participate in the
development of this AD. We received no
comments on the NPRM or on the
determination of the cost to the public.
Explanation of Change to Applicability
We have revised the applicability of
the existing AD to identify model
designations as published in the most
recent type certificate data sheet for the
affected models.
Conclusion
We have carefully reviewed the
available data and determined that air
safety and the public interest require
adopting the AD with the change
described previously. We have
determined that this change will neither
increase the economic burden on any
PO 00000
Frm 00028
Fmt 4700
Sfmt 4700
operator nor increase the scope of the
AD.
Costs of Compliance
This AD will affect about 180
airplanes of U.S. registry. The required
actions will take between 4 and 24 work
hours per airplane, at an average labor
rate of $65 per work hour. Required
parts will cost between $555 and $6,179
per airplane. Based on these figures,
which depend upon airplane
configuration, the estimated cost of this
AD for U.S. operators is between
$146,700 and $1,393,020, or between
$815 and $7,739 per airplane.
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.
E:\FR\FM\16MYR1.SGM
16MYR1
]]>Agencies
[Federal Register Volume 71, Number 94 (Tuesday, May 16, 2006)]
[Rules and Regulations]
[Pages 28254-28256]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 06-4503]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2006-24104; Directorate Identifier 2005-NM-231-AD;
Amendment 39-14595; AD 2006-10-11]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A310-200 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 A310-200 and -300 series airplanes. This AD
requires repetitive inspections for cracking of the flap transmission
shafts, and replacing the transmission shafts if necessary. This AD
also provides an optional terminating action for the repetitive
inspections. This AD results from reports of longitudinal cracks due to
stress corrosion in the transmission shafts between the power control
unit (PCU) and the torque limiters of the flap transmission system. We
are issuing this AD to detect and correct cracking of the flap
transmission shaft, which could compromise shaft structural integrity
and lead to a disabled flap transmission shaft and reduced
controllability of the airplane.
DATES: This AD becomes effective June 20, 2006.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in the AD as of June 20, 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 service information identified in this AD.
FOR FURTHER INFORMATION CONTACT: Thomas Stafford, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; 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 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
A310-200 and -300 series airplanes. That NPRM was published in the
Federal Register on March 9, 2006 (71 FR 12152). That NPRM proposed to
require repetitive inspections for cracking of the flap transmission
shafts, and replacing the transmission shafts if necessary. The NPRM
also proposed to provide an optional terminating action for the
repetitive inspections.
Comments
We provided the public the opportunity to participate in the
development of this AD. We received no comments on the NPRM or on the
determination of the cost to the public.
Change to NPRM
We inadvertently deleted reference to the reporting requirement
stated in the Direction G[eacute]n[eacute]rale de l'Aviation Civile
(DGAC) Airworthiness Directive and the Airbus service bulletin. This AD
does not require reporting the results of the inspection to Airbus,
which is a difference among the DGAC Airworthiness Directive, the
service bulletin, and this AD. We have added our non-requirement as
paragraph (j) of this AD and reidentified subsequent paragraphs
accordingly.
Conclusion
We have carefully reviewed the available data and determined that
air safety and the public interest require adopting the AD with the
change described previously. We have determined that this change will
neither increase the economic burden on any operator nor increase the
scope of the AD.
Costs of Compliance
This AD will affect about 59 airplanes of U.S. registry. The
required inspections will take about 1 work hour per airplane, at an
average labor rate of $65 per work hour. Based on these figures, the
estimated cost of the AD for U.S. operators is $3,835, or $65 per
airplane, per inspection cycle.
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
[[Page 28255]]
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):
2006-10-11 Airbus: Amendment 39-14595. FAA-2006-24104; Directorate
Identifier 2005-NM-231-AD.
Effective Date
(a) This AD becomes effective June 20, 2006.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Airbus Model A310-203, -204, -221, -222,
-304, -322, -324, and -325 airplanes, certificated in any category;
except for airplanes on which Airbus Modification 12247 has been
embodied in production.
Unsafe Condition
(d) This AD results from reports of longitudinal cracks due to
stress corrosion in the transmission shafts between the power
control unit (PCU) and the torque limiters of the flap transmission
system. We are issuing this AD to detect and correct cracking of the
flap transmission shaft, which could compromise shaft structural
integrity and lead to a disabled flap transmission shaft and reduced
controllability 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.
Inspection and Corrective Action
(f) At the earlier of the compliance times specified in
paragraph (f)(1) or (f)(2) of this AD: Perform a detailed inspection
for stress corrosion cracking of the flight transmission shafts
located between the PCU and the torque limiters in accordance with
the Accomplishment Instructions of Airbus Service Bulletin A310-27-
2092, Revision 02, dated April 11, 2005. Thereafter, repeat the
inspections as required by paragraph (g) of this AD. Before further
flight, replace any cracked transmission shaft discovered during any
inspection required by this AD with a new or reconditioned shaft, in
accordance with the Accomplishment Instructions of Airbus Service
Bulletin A310-27-2095, dated March 29, 2000.
(1) Within 2,000 flight hours after the last flap asymmetry
protection test performed in accordance with Airbus A310 Maintenance
Planning Document (MPD) Task 275600-01-1.
(2) Within 8,000 flight cycles after the last flap asymmetry
protection test performed in accordance with Airbus A310 MPD Task
275600-02-1 or 800 flight cycles after the effective date of this
AD, whichever comes later.
Note 1: Airbus Service Bulletin A310-27-2092, Revision 02, dated
April 11, 2005, refers to Lucas Liebherr Service Bulletin 551A-27-
624, Revision 1, dated August 18, 2000, as an additional source of
service information for accomplishing the inspections.
Note 2: Airbus Service Bulletin A310-27-2092, Revision 02,
refers to Airbus Service Bulletin A310-27-2095, dated March 29,
2000, as a source of service information for replacing the flap
transmission shafts.
Note 3: Airbus Service Bulletin A310-27-2095 refers to Lucas
Liebherr Service Bulletin 551A-27-M551-05, dated January 12, 2000,
as an additional source of service information for replacing the
flap transmission shafts.
Repetitive Inspections
(g) Repeat the inspection required by paragraph (f) of this AD
at the applicable times specified in paragraphs (g)(1), (g)(2), and
(g)(3) of this AD.
(1) Before further flight after any occurrence of jamming of the
flap transmission system.
(2) At intervals not to exceed 2,000 flight hours after each
flap asymmetry protection test performed in accordance with Airbus
A310 MPD Task 275600-01-1.
(3) At intervals not to exceed 8,000 flight cycles after each
flap asymmetry protection test performed in accordance with Airbus
A310 MPD Task 275600-02-1.
Optional Terminating Action
(h) Replacing any flap transmission shaft with a new or
reconditioned transmission shaft in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A310-27-2095,
dated March 29, 2000, ends the inspections required for that
transmission shaft only.
Actions Performed Using Previously Issued Service Information
(i) Actions performed in accordance with Airbus Service Bulletin
A310-27-2092, dated April 9, 1999; or Revision 01, dated December
11, 2001, are considered acceptable for compliance with the
corresponding requirements of this AD.
No Reporting
(j) Although Airbus Service Bulletin A310-27-2092, Revision 02,
dated April 11, 2005, specifies to submit certain information to the
manufacturer, this AD does not include that requirement.
Alternative Methods of Compliance (AMOCs)
(k)(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
(l) French airworthiness directive F-2005-174, dated October 26,
2005, also addresses the subject of this AD.
Material Incorporated by Reference
(m) You must use Airbus Service Bulletin A310-27-2092, Revision
02, dated April 11, 2005; and Airbus Service Bulletin A310-27-2095,
dated March 29, 2000; as applicable, 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 copies 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
[[Page 28256]]
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.
Issued in Renton, Washington, on May 8, 2006.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 06-4503 Filed 5-15-06; 8:45 am]
BILLING CODE 4910-13-P
