Airworthiness Directives; Airbus Model A319-131, -132, and -133; A320-232 and -233; and A321-131, -231, and -232 Airplanes, 16025-16027 [06-2961]
Download as PDF
<![CDATA[
Federal Register / Vol. 71, No. 61 / Thursday, March 30, 2006 / Rules and Regulations
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Service Bulletin 8–52–60, dated August 28,
2002.
ACTION:
16025
Final rule.
DEPARTMENT OF TRANSPORTATION
SUMMARY: The FAA is adopting a new
airworthiness directive (AD) for certain
Airbus Model A319–131, –132, and
–133; A320–232 and –233; and A321–
131, –231, and –232 airplanes. This AD
requires inspecting for cracks or failure
of the primary load path components of
the engine forward mount, and
corrective action if necessary. This AD
also requires removing, re-installing,
and re-torquing the attachment bolts for
the secondary load path. This AD
results from a report that, during
modification of certain engine forward
mount assemblies of the left and right
engines done at an engine shop visit, an
incorrect torque was applied to the
attachment bolts. We are issuing this AD
to prevent structural failure of the
secondary load path of the forward
engine mount, which, if combined with
failure of the primary load path, could
result in separation of the engine from
the airplane.
DATES: This AD becomes effective May
4, 2006.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in the AD
as of May 4, 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: Tim
Dulin, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton,
Washington 98055–4056; telephone
(425) 227–2141; fax (425) 227–1149.
SUPPLEMENTARY INFORMATION:
Replace Pressure Control Valve
(f) Within 30 months after the effective
date of this AD, replace the pressure control
valve of the Type 1 emergency door by
incorporating ModSum 8Q101159 in
accordance with the Accomplishment
Instructions of Bombardier Service Bulletin
8–52–60, Revision A, dated April 28, 2003.
Federal Aviation Administration
Examining the Docket
Replacement According to Previous Issue of
Service Bulletin
(g) Replacing the pressure control valve of
the Type 1 emergency door is also acceptable
for compliance with the requirements of
paragraph (f) of this AD if done before the
effective date of this AD in accordance the
Accomplishment Instructions of Bombardier
Airworthiness Directives; Airbus Model
A319–131, –132, and –133; A320–232
and –233; and A321–131, –231, and
–232 Airplanes
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
2006–07–02 Bombardier, Inc. (Formerly de
Havilland, Inc.): Amendment 39–14529.
Docket No. FAA–2005–20628;
Directorate Identifier 2004–NM–51–AD.
Effective Date
(a) This AD becomes effective May 4, 2006.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Bombardier Model
DHC–8–301, –311, and –315 airplanes,
certificated in any category, serial numbers
100 through 593 inclusive.
Unsafe Condition
(d) This AD results from reports that the
pressure control valve of the Type 1
emergency door is susceptible to freezing. We
are issuing this AD to ensure that the
pressure control valve does not freeze and
prevent the door seal from deflating, which
could result in the inability to open the door
in an emergency.
cprice-sewell on PROD1PC66 with RULES
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.
VerDate Aug<31>2005
15:18 Mar 29, 2006
Jkt 208001
Alternative Methods of Compliance
(AMOCs)
(h)(1) The Manager, New York Aircraft
Certification Office, 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
(i) Canadian airworthiness directive CF–
2003–04, dated February 3, 2003, also
addresses the subject of this AD.
Material Incorporated by Reference
(j) You must use Bombardier Service
Bulletin 8–52–60, Revision A, dated April 28,
2003, 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 this document in accordance
with 5 U.S.C. 552(a) and 1 CFR part 51.
Contact Bombardier, Inc., Bombardier
Regional Aircraft Division, 123 Garratt
Boulevard, Downsview, Ontario M3K 1Y5,
Canada, 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 March
17, 2006.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 06–2960 Filed 3–29–06; 8:45 am]
BILLING CODE 4910–13–U
14 CFR Part 39
[Docket No. FAA–2005–23142; Directorate
Identifier 2005–NM–154–AD; Amendment
39–14532; AD 2006–07–05]
RIN 2120–AA64
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
AGENCY:
PO 00000
Frm 00011
Fmt 4700
Sfmt 4700
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
E:\FR\FM\30MRR1.SGM
30MRR1
16026
Federal Register / Vol. 71, No. 61 / Thursday, March 30, 2006 / Rules and Regulations
part 39 to include an AD that would
apply to certain Airbus Model A319–
131, –132, and –133; A320–232 and
–233; and A321–131 and –231
airplanes. That NPRM was published in
the Federal Register on December 1,
2005 (70 FR 72088). That NPRM
proposed to require inspecting for
cracks or failure of the primary load
path components of the engine forward
mount, and corrective action if
necessary. That NPRM also proposed to
require removing, re-installing, and retorquing the attachment bolts for the
secondary load path.
Comments
We provided the public the
opportunity to participate in the
development of this AD. We have
considered the comment received from
one commenter.
cprice-sewell on PROD1PC66 with RULES
Clarification of Applicability
The commenter states that Airbus
Model A321–232 airplanes are not
identified in the applicability of the AD.
The commenter notes that there have
been nine of these airplanes delivered
that are not U.S.-registered.
We infer that the commenter wants us
to include Airbus Model A321–232
airplanes in the applicability of the AD.
We agree with the commenter. The
proposed AD is applicable to Airbus
Model A319–131, –132, and –133;
A320–232 and –233; and A321–131 and
–231 airplanes. Model A321–232
airplanes have been approved, but are
not yet identified in the type certificate
data sheet (TCDS). Considering this
approval, we have changed the
applicability throughout the AD
accordingly. Additionally, no Model
A321–232 airplane is currently on the
U.S. Register so no additional work is
required for U.S. operators.
Clarification of Applicability in
Paragraph (f) of the NPRM
We note that paragraph (f) of the
NPRM contains an error in referencing
the airplane models on which the
detailed inspection must be done. Our
intent was to specify all of the airplane
models identified in Airbus All
Operators Telex A320–71A1036,
Revision 1, dated June 28, 2005, as
referenced in the applicability section;
however, we inadvertently excluded
Model A320–232 and –233 airplanes in
paragraph (f). We have verified that the
inspection has been accomplished on all
affected models. Therefore, no
additional work is required for U.S.
operators. Adding these models to
paragraph (f) will ensure that any
affected airplane that is imported into
the U.S. after the effective date of this
VerDate Aug<31>2005
15:18 Mar 29, 2006
Jkt 208001
AD is inspected, as required by this AD.
We have added a new paragraph (f)(3)
to the AD to include these models.
Conclusion
We have carefully reviewed the
available data, including the comment
that has been received, and determined
that air safety and the public interest
require adopting the AD with the
changes described previously. These
changes will neither increase the
economic burden on any operator nor
increase the scope of the AD.
Costs of Compliance
This AD affects about 131 airplanes of
U.S. registry.
The inspection takes about 2 work
hours per airplane (1 work hour per
engine), at an average labor rate of $65
per work hour. Based on these figures,
the estimated cost of the inspection for
U.S. operators is $17,030, or $130 per
airplane.
The removal, re-installation, and retorquing takes about 8 work hours per
airplane (4 work hours per engine), at an
average labor rate of $65 per work hour.
Based on these figures, the estimated
cost of the adjustments for U.S.
operators is $68,120, or $520 per
airplane.
If any Model A321–232 airplane is
imported and placed on the U.S.
Register in the future, it will take about
2 work hours per airplane for the
inspection and 8 work hours per
airplane for the removal, re-installation,
and re-torquing, at an average labor rate
of $65 per work hour. Based on these
figures, the estimated cost of the AD
will be $750 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.
PO 00000
Frm 00012
Fmt 4700
Sfmt 4700
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
2006–07–05 Airbus: Amendment 39–14532.
Docket No. FAA–2005–23142;
Directorate Identifier 2005–NM–154–AD.
Effective Date
(a) This AD becomes effective May 4, 2006.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Airbus Model A319–
131, –132, and –133 airplanes; Model A320–
232 and –233 airplanes; and Model A321–
131, –231, and –232 airplanes; certificated in
any category; as identified in Airbus All
Operators Telex (AOT) A320–71A1036,
Revision 1, dated June 28, 2005.
E:\FR\FM\30MRR1.SGM
30MRR1
Federal Register / Vol. 71, No. 61 / Thursday, March 30, 2006 / Rules and Regulations
Unsafe Condition
(d) This AD results from a report that,
during modification of certain engine
forward mount assemblies of the left and
right engines done at an engine shop visit, an
incorrect torque was applied to the
attachment bolts. We are issuing this AD to
prevent structural failure of the secondary
load path of the forward engine mount,
which, if combined with failure of the
primary load path, could result in separation
of the engine from 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.
Note 1: For the purposes of this AD, a
detailed inspection is: ‘‘An intensive
examination of a specific item, installation,
or assembly to detect damage, failure, or
irregularity. Available lighting is normally
supplemented with a direct source of good
lighting at an intensity deemed appropriate.
Inspection aids such as mirror, magnifying
lenses, etc., may be necessary. Surface
cleaning and elaborate procedures may be
required.’’
cprice-sewell on PROD1PC66 with RULES
Inspection and Corrective Action
(f) Perform a detailed inspection for cracks
or failure of the primary load path
components of the engine forward mount by
doing all the applicable actions in
accordance with the procedures in Airbus
AOT A320–71A1036, Revision 1, dated June
28, 2005. Perform the actions at the time
specified in paragraph (f)(1), (f)(2), or (f)(3) of
this AD, as applicable. Do any corrective
action before further flight in accordance
with the procedures in the AOT.
(1) For Model A321–131, –231, and –232
airplanes: Do the inspection within 5 days
after the effective date of this AD.
(2) For Model A319–131, –132, and –133
airplanes: Do the inspection within 10 days
after the effective date of this AD.
(3) For Model A320–232 and –233
airplanes: Do the inspection within 10 days
after the effective date of this AD.
(g) For all airplanes: At the applicable time
specified in paragraph (g)(1) or (g)(2) of this
AD, remove, re-install, and re-torque each of
the attachment bolts of the engine forward
mount assembly in accordance with the
procedures in Airbus AOT A320–71A1036,
Revision 1, dated June 28, 2005.
(1) If the inspection specified in paragraph
(f) of this AD was accomplished after the
effective date of this AD: Do the actions
within 2,250 flight cycles after accomplishing
the inspection.
(2) If the inspection specified in paragraph
(f) of this AD was accomplished before the
effective date of this AD: Do the actions
within 2,250 flight cycles after the effective
date of this AD.
No Reporting Required
DEPARTMENT OF TRANSPORTATION
(i) Although Airbus AOT A320–71A1036,
Revision 1, dated June 28, 2005, recommends
that inspection results be reported to the
manufacturer, this AD does not include that
requirement.
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 § 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 emergency airworthiness
directive UF–2005–117, dated June 29, 2005,
also addresses the subject of this AD.
Material Incorporated by Reference
(l) You must use Airbus All Operators
Telex A320–71A1036, Revision 1, dated June
28, 2005, to perform the actions that are
required by this AD, unless the AD specifies
otherwise. (Only page 1 of the all operators
telex contains the document number,
revision number, and date of the document;
no other page of the document contains this
information.) The Director of the Federal
Register approved the incorporation by
reference of this document 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 March
17, 2006.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 06–2961 Filed 3–29–06; 8:45 am]
BILLING CODE 4910–13–P
Actions Accomplished Previously
(h) Inspections, adjustments or repairs
done before the effective date of this AD in
accordance with the procedures in Airbus
AOT A320–71A1036, dated June 27, 2005,
are acceptable for compliance with the
corresponding actions required by this AD.
VerDate Aug<31>2005
15:18 Mar 29, 2006
Jkt 208001
PO 00000
Frm 00013
Fmt 4700
16027
Sfmt 4700
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2005–23023; Directorate
Identifier 2005–CE–49–AD; Amendment 39–
14533; AD 2006–07–06]
RIN 2120–AA64
Airworthiness Directives; Cirrus
Design Corporation Models SR20 and
SR22 Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
SUMMARY: The FAA adopts a new
airworthiness directive (AD) for certain
Cirrus Design Corporation (CDC) Models
SR20 and SR22 airplanes. This AD
requires you to inspect the fuel line and
wire bundles for any chafing damage;
replace any damaged fuel line and
repair any damaged wires or sheathing
of the wire harness if any chafing
damage is found; and install (to prevent
any chafing damage to the fuel line and
wire bundles) the forward loop clamp,
fuel line shield, aft loop clamp, and
anti-chafe tubing. This AD results from
reports of fuel line leaks resulting from
wire chafing on the fuel lines. We are
issuing this AD to detect, correct, and
prevent damage to the fuel line and wire
bundles, which could result in fuel
leaks. This failure could lead to unsafe
fuel vapor within the cockpit and
possible fire.
DATES: This AD becomes effective on
May 11, 2006.
As of May 11, 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 Cirrus Design Corporation, 4515
Taylor Circle, Duluth, Minnesota 55811;
telephone: (218) 727–2737, or on the
Internet at https://www.cirrusdesign.com.
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–2005–23023; Directorate Identifier
2005–CE–49–AD.
FOR FURTHER INFORMATION CONTACT:
Wess Rouse, Aerospace Engineer, ACE–
117C, Chicago Aircraft Certification
Office, 2300 East Devon Avenue, Room
107, Des Plaines, Illinois 60018;
telephone: (847) 294–8113; facsimile:
(847) 294–7834.
E:\FR\FM\30MRR1.SGM
30MRR1
]]>Agencies
[Federal Register Volume 71, Number 61 (Thursday, March 30, 2006)]
[Rules and Regulations]
[Pages 16025-16027]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 06-2961]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2005-23142; Directorate Identifier 2005-NM-154-AD;
Amendment 39-14532; AD 2006-07-05]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A319-131, -132, and -133;
A320-232 and -233; and A321-131, -231, and -232 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 A319-131, -132, and -133; A320-232 and -233; and
A321-131, -231, and -232 airplanes. This AD requires inspecting for
cracks or failure of the primary load path components of the engine
forward mount, and corrective action if necessary. This AD also
requires removing, re-installing, and re-torquing the attachment bolts
for the secondary load path. This AD results from a report that, during
modification of certain engine forward mount assemblies of the left and
right engines done at an engine shop visit, an incorrect torque was
applied to the attachment bolts. We are issuing this AD to prevent
structural failure of the secondary load path of the forward engine
mount, which, if combined with failure of the primary load path, could
result in separation of the engine from the airplane.
DATES: This AD becomes effective May 4, 2006.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in the AD as of May 4, 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: Tim Dulin, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425)
227-2141; 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
[[Page 16026]]
part 39 to include an AD that would apply to certain Airbus Model A319-
131, -132, and -133; A320-232 and -233; and A321-131 and -231
airplanes. That NPRM was published in the Federal Register on December
1, 2005 (70 FR 72088). That NPRM proposed to require inspecting for
cracks or failure of the primary load path components of the engine
forward mount, and corrective action if necessary. That NPRM also
proposed to require removing, re-installing, and re-torquing the
attachment bolts for the secondary load path.
Comments
We provided the public the opportunity to participate in the
development of this AD. We have considered the comment received from
one commenter.
Clarification of Applicability
The commenter states that Airbus Model A321-232 airplanes are not
identified in the applicability of the AD. The commenter notes that
there have been nine of these airplanes delivered that are not U.S.-
registered.
We infer that the commenter wants us to include Airbus Model A321-
232 airplanes in the applicability of the AD. We agree with the
commenter. The proposed AD is applicable to Airbus Model A319-131, -
132, and -133; A320-232 and -233; and A321-131 and -231 airplanes.
Model A321-232 airplanes have been approved, but are not yet identified
in the type certificate data sheet (TCDS). Considering this approval,
we have changed the applicability throughout the AD accordingly.
Additionally, no Model A321-232 airplane is currently on the U.S.
Register so no additional work is required for U.S. operators.
Clarification of Applicability in Paragraph (f) of the NPRM
We note that paragraph (f) of the NPRM contains an error in
referencing the airplane models on which the detailed inspection must
be done. Our intent was to specify all of the airplane models
identified in Airbus All Operators Telex A320-71A1036, Revision 1,
dated June 28, 2005, as referenced in the applicability section;
however, we inadvertently excluded Model A320-232 and -233 airplanes in
paragraph (f). We have verified that the inspection has been
accomplished on all affected models. Therefore, no additional work is
required for U.S. operators. Adding these models to paragraph (f) will
ensure that any affected airplane that is imported into the U.S. after
the effective date of this AD is inspected, as required by this AD. We
have added a new paragraph (f)(3) to the AD to include these models.
Conclusion
We have carefully reviewed the available data, including the
comment that has been received, and determined that air safety and the
public interest require adopting the AD with the changes described
previously. These changes will neither increase the economic burden on
any operator nor increase the scope of the AD.
Costs of Compliance
This AD affects about 131 airplanes of U.S. registry.
The inspection takes about 2 work hours per airplane (1 work hour
per engine), at an average labor rate of $65 per work hour. Based on
these figures, the estimated cost of the inspection for U.S. operators
is $17,030, or $130 per airplane.
The removal, re-installation, and re-torquing takes about 8 work
hours per airplane (4 work hours per engine), at an average labor rate
of $65 per work hour. Based on these figures, the estimated cost of the
adjustments for U.S. operators is $68,120, or $520 per airplane.
If any Model A321-232 airplane is imported and placed on the U.S.
Register in the future, it will take about 2 work hours per airplane
for the inspection and 8 work hours per airplane for the removal, re-
installation, and re-torquing, at an average labor rate of $65 per work
hour. Based on these figures, the estimated cost of the AD will be $750
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.
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):
2006-07-05 Airbus: Amendment 39-14532. Docket No. FAA-2005-23142;
Directorate Identifier 2005-NM-154-AD.
Effective Date
(a) This AD becomes effective May 4, 2006.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Airbus Model A319-131, -132, and -133
airplanes; Model A320-232 and -233 airplanes; and Model A321-131, -
231, and -232 airplanes; certificated in any category; as identified
in Airbus All Operators Telex (AOT) A320-71A1036, Revision 1, dated
June 28, 2005.
[[Page 16027]]
Unsafe Condition
(d) This AD results from a report that, during modification of
certain engine forward mount assemblies of the left and right
engines done at an engine shop visit, an incorrect torque was
applied to the attachment bolts. We are issuing this AD to prevent
structural failure of the secondary load path of the forward engine
mount, which, if combined with failure of the primary load path,
could result in separation of the engine from 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.
Note 1: For the purposes of this AD, a detailed inspection is:
``An intensive examination of a specific item, installation, or
assembly to detect damage, failure, or irregularity. Available
lighting is normally supplemented with a direct source of good
lighting at an intensity deemed appropriate. Inspection aids such as
mirror, magnifying lenses, etc., may be necessary. Surface cleaning
and elaborate procedures may be required.''
Inspection and Corrective Action
(f) Perform a detailed inspection for cracks or failure of the
primary load path components of the engine forward mount by doing
all the applicable actions in accordance with the procedures in
Airbus AOT A320-71A1036, Revision 1, dated June 28, 2005. Perform
the actions at the time specified in paragraph (f)(1), (f)(2), or
(f)(3) of this AD, as applicable. Do any corrective action before
further flight in accordance with the procedures in the AOT.
(1) For Model A321-131, -231, and -232 airplanes: Do the
inspection within 5 days after the effective date of this AD.
(2) For Model A319-131, -132, and -133 airplanes: Do the
inspection within 10 days after the effective date of this AD.
(3) For Model A320-232 and -233 airplanes: Do the inspection
within 10 days after the effective date of this AD.
(g) For all airplanes: At the applicable time specified in
paragraph (g)(1) or (g)(2) of this AD, remove, re-install, and re-
torque each of the attachment bolts of the engine forward mount
assembly in accordance with the procedures in Airbus AOT A320-
71A1036, Revision 1, dated June 28, 2005.
(1) If the inspection specified in paragraph (f) of this AD was
accomplished after the effective date of this AD: Do the actions
within 2,250 flight cycles after accomplishing the inspection.
(2) If the inspection specified in paragraph (f) of this AD was
accomplished before the effective date of this AD: Do the actions
within 2,250 flight cycles after the effective date of this AD.
Actions Accomplished Previously
(h) Inspections, adjustments or repairs done before the
effective date of this AD in accordance with the procedures in
Airbus AOT A320-71A1036, dated June 27, 2005, are acceptable for
compliance with the corresponding actions required by this AD.
No Reporting Required
(i) Although Airbus AOT A320-71A1036, Revision 1, dated June 28,
2005, recommends that inspection results be reported to the
manufacturer, this AD does not include that requirement.
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 emergency airworthiness directive UF-2005-117, dated
June 29, 2005, also addresses the subject of this AD.
Material Incorporated by Reference
(l) You must use Airbus All Operators Telex A320-71A1036,
Revision 1, dated June 28, 2005, to perform the actions that are
required by this AD, unless the AD specifies otherwise. (Only page 1
of the all operators telex contains the document number, revision
number, and date of the document; no other page of the document
contains this information.) The Director of the Federal Register
approved the incorporation by reference of this document 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 March 17, 2006.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 06-2961 Filed 3-29-06; 8:45 am]
BILLING CODE 4910-13-P
