Airworthiness Directives; Airbus Model A318, A319, A320, and A321 Airplanes, 52421-52423 [E6-14623]
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Federal Register / Vol. 71, No. 172 / Wednesday, September 6, 2006 / Rules and Regulations
chapters of the AMM. The applicable
revision level of the referenced chapters is
that in effect on February 7, 2001. Doing the
revision specified in paragraph (g) of this AD
replaces Chapters 27, 32, 53, and 54 listed in
Section 05–10–11 and Chapters 52, 53, 54,
55, and 57 listed in Section 05–10–17 that are
in effect on February 7, 2001, with Chapters
27, 32, 53, and 54 listed in Section 05–10–
11, ‘‘Mandatory Life Limitations (Airframe)’’;
and Chapters 52, 53, 54, 55, and 57 listed in
Section 05–10–17, ‘‘Structurally Significant
Items (SSIs)’’; both dated July 15, 2004; of the
British Aerospace ATP AMM.
Airworthiness Limitations Specified in AD
2005–19–03
(g) Within 30 days after September 28,
2005 (the effective date of AD 2005–19–03),
revise the ALS of the Instructions for
Continued Airworthiness according to a
method approved by the Manager,
International Branch, ANM–116, Transport
Airplane Directorate, FAA. One approved
method is by incorporating the tasks for
Chapters 27, 32, 53, and 54 listed in Section
05–10–11, ‘‘Mandatory Life Limitations
(Airframe)’’; and the tasks for Chapters 52,
53, 54, 55, and 57 listed in Section 05–10–
17, ‘‘Structurally Significant Items (SSIs)’’;
both dated July 15, 2004; of the British
Aerospace ATP AMM; into the ALS. These
chapters replace the corresponding chapters
in Section 05–00–00, dated August 15, 1997,
of the British Aerospace ATP AMM as
specified in paragraph (f) of this AD. Doing
the revision specified in paragraph (h) of this
AD replaces certain Chapter 52 and 53 tasks
listed in Section 05–10–17, ‘‘Structurally
Significant Items (SSIs)’’, dated July 15, 2004,
of the British Aerospace ATP AMM, with the
corresponding Chapter 52 and 53 tasks listed
BAE Systems (Operations) Limited Service
Bulletin ATP–51–002, dated December 20,
2005.
New Requirements of This AD
jlentini on PROD1PC65 with RULES
New and Revised Airworthiness Limitations
(h) Within 30 days after the effective date
of this AD, revise the ALS of the Instructions
for Continued Airworthiness by
incorporating the new and revised tasks for
Chapters 52 and 53 as specified in BAE
Systems (Operations) Limited Service
Bulletin ATP–51–002, dated December 20,
2005, into the ALS. The revised Chapter 52
and 53 tasks replace the corresponding
Chapter 52 and 53 tasks in Section 05–10–
17, ‘‘Structurally Significant Items (SSIs)’’,
dated July 15, 2004, of the British Aerospace
ATP AMM, as specified in paragraph (g) of
this AD.
(i) Except as provided by paragraph (k) of
this AD: After the actions specified in
paragraphs (f), (g), and (h) of this AD have
been accomplished, no alternative
inspections or inspection intervals may be
approved for the structural elements
specified in the documents listed in
paragraphs (f), (g), and (h) of this AD.
No Reporting Required
(j) Although BAE Systems (Operations)
Limited Service Bulletin ATP–51–002, dated
December 20, 2005, specifies to submit
certain information to the manufacturer, this
AD does not include that requirement.
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16:42 Sep 05, 2006
Jkt 205001
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) British airworthiness directive G–2004–
0020, dated August 25, 2004, and European
Aviation Safety Agency (EASA)
airworthiness directive 2006–0090, dated
April 20, 2006, also address the subject of
this AD.
Material Incorporated by Reference
(m) You must use BAE Systems
(Operations) Limited Service Bulletin ATP–
51–002, dated December 20, 2005, 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 British Aerospace Regional
Aircraft American Support, 13850 Mclearen
Road, Herndon, Virginia 20171, 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 August
23, 2006.
Kalene C. Yanamura,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. E6–14631 Filed 9–5–06; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2006–24199; Directorate
Identifier 2006–NM–025–AD; Amendment
39–14744; AD 2006–18–06]
RIN 2120–AA64
Airworthiness Directives; Airbus Model
A318, A319, A320, and A321 Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
PO 00000
Frm 00019
Fmt 4700
Sfmt 4700
52421
SUMMARY: The FAA is adopting a new
airworthiness directive (AD) for certain
Airbus Model A318, A319, A320, and
A321 airplanes. This AD requires
revising the Limitations section of the
airplane flight manual (AFM);
performing a one-time hardness test of
certain ribs of the left- and right-hand
engine pylons, as applicable, which
would terminate the AFM limitations;
and performing related corrective
actions if necessary. This AD results
from a report that certain stainless steel
ribs installed in the engine pylon may
not have been heat-treated during
manufacture, which could result in
significantly reduced structural integrity
of the pylon. We are issuing this AD to
detect and correct reduced structural
integrity of the engine pylon, which
could lead to separation of the engine
from the airplane.
DATES: This AD becomes effective
October 11, 2006.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in the AD
as of October 11, 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 98057–3356; 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
part 39 to include an AD that would
apply to certain Airbus Model A318,
A319, A320, and A321 airplanes. That
NPRM was published in the Federal
E:\FR\FM\06SER1.SGM
06SER1
52422
Federal Register / Vol. 71, No. 172 / Wednesday, September 6, 2006 / Rules and Regulations
Register on March 27, 2006 (71 FR
15065). That NPRM proposed to require
revising the Limitations section of the
airplane flight manual (AFM);
performing a one-time hardness test of
certain ribs of the left- and right-hand
engine pylons, as applicable, which
would terminate the AFM limitations;
and performing related corrective
actions if necessary.
Comments
We provided the public the
opportunity to participate in the
development of this AD. We have
considered the comment received.
Request To Revise Hardness Test
Requirement
The Air Transport Association (ATA),
on behalf of its member, Northwest
Airlines (NWA), requests that we review
the requirement for the hardness test
specified in the NPRM. NWA states that
the NPRM proposes a hardness test
before further flight in the case of a hard
or overweight landing and further states
that French airworthiness directive F–
2006–011 R1, dated January 18, 2006,
which also addresses the subject of this
AD, did not have such a requirement.
NWA asserts that a requirement to
visually inspect the airplane and pylons
for deformation after a hard landing
already exists. NWA believes that, as a
hardness test requires special tooling
and expertise that would not likely be
available at most locations where a hard
landing might occur, the hardness test is
not appropriate and a visual inspection
in accordance with maintenance
procedures should be accomplished
instead.
We agree with NWA that a hardness
test after a hard or overweight landing
is not necessary. Therefore, we have
revised paragraph (g) of the AD to
remove the requirement for a hardness
test after a hard or overweight landing.
jlentini on PROD1PC65 with RULES
Clarification of Corrective Actions
To prevent possible confusion, we
have revised paragraph (h) of the AD to
clarify that the specified corrective
actions apply to discrepant ribs
discovered during the hardness test
required by paragraph (g) of the AD.
Supersedure of French Airworthiness
Directive
The European Aviation Safety Agency
(EASA) has issued airworthiness
directive 2006–0136, dated May 22,
2006. The EASA airworthiness directive
supersedes French airworthiness
directive F–2006–011 R1, dated January
18, 2006, which was referenced in the
NPRM as the applicable parallel
airworthiness directive. The EASA
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16:42 Sep 05, 2006
Jkt 205001
airworthiness directive contains no new
or revised material that affects the
technical content of this AD; however,
we have revised paragraph (k) of this
AD for clarity and traceability of
information that applies to this AD.
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 changes described
previously. We have determined that
these changes will neither increase the
economic burden on any operator nor
increase the scope of the AD.
Costs of Compliance
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;
Frm 00020
Fmt 4700
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
This AD will affect about 112
airplanes of U.S. registry. The required
hardness test 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 $7,280, or $65
per airplane.
PO 00000
(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.
Sfmt 4700
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
2006–18–06 Airbus: Amendment 39–
14744. Docket No. FAA–2006–24199;
Directorate Identifier 2006–NM–025–AD.
Effective Date
(a) This AD becomes effective October 11,
2006.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Airbus Model A318,
A319, A320, and A321 airplanes, certificated
in any category; having a manufacturer serial
number as identified in Airbus All Operators
Telex (AOT) A320–54A1015, dated
December 14, 2005 (referred to after this
paragraph as ‘‘the AOT’’).
Unsafe Condition
(d) This AD results from a report that
certain stainless steel ribs installed in the
engine pylon may not have been heat-treated
during manufacture, which could result in
significantly reduced structural integrity of
the pylon. We are issuing this AD to detect
and correct reduced structural integrity of the
engine pylon, which could lead to 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.
E:\FR\FM\06SER1.SGM
06SER1
Federal Register / Vol. 71, No. 172 / Wednesday, September 6, 2006 / Rules and Regulations
Revise Limitations
(f) Within 10 days after the effective date
of this AD, revise the Limitations section of
the Airbus A318/319/320/321 Airplane
Flight Manual (AFM) to include the
following statement. This may be done by
inserting a copy of this AD into the AFM.
‘‘In case of flight in severe turbulence,
strictly adhere to reduced speeds as defined
in Aircraft Flight Manual 4.03.00 P 03.’’
Note 1: When a statement identical to that
specified in paragraph (f) of this AD has been
included in the general revisions of the AFM,
and the general revisions have been inserted
into the AFM, the copy of this AD may be
removed from the Limitations section of the
AFM unless it has already been removed as
specified in paragraph (g) or (h) of this AD.
Hardness Test
(g) Within the compliance time specified in
paragraph (g)(1) or (g)(2) of this AD, as
applicable: Perform a one-time hardness test
to determine the hardness of ribs 8 and 9 of
the left- and right-hand engine pylons, in
accordance with the instructions of the AOT.
If no discrepant rib is found installed on the
airplane, the statement specified in
paragraph (f) of this AD may be removed
from the Limitations section of the AFM.
(1) For airplanes equipped with CFM
engines: Within 6 months after the effective
date of this AD.
(2) For airplanes equipped with IAE
engines: Within 9 months after the effective
date of this AD.
Note 2: The AOT refers to Airbus Repair
Instruction 546 12081, Issue B, dated January
3, 2006, as an additional source of service
information for accomplishing the actions
specified by the AOT.
Corrective Actions
(h) For any discrepant rib found during the
hardness test specified by paragraph (g) of
this AD: Within the compliance time
specified in paragraph (h)(1) or (h)(2) of this
AD, as applicable, perform applicable
corrective actions in accordance with the
instructions of the AOT. When corrective
actions have been applied to all discrepant
ribs found on the airplane, the statement
specified in paragraph (f) of this AD may be
removed from the Limitations section of the
AFM for that airplane.
(1) For airplanes equipped with CFM
engines: Within 14 days after accomplishing
the hardness test required by paragraph (g) of
this AD.
(2) For airplanes equipped with IAE
engines: Within 28 days after accomplishing
the hardness test required by paragraph (g) of
this AD.
jlentini on PROD1PC65 with RULES
No Reporting Requirement
(i) Although the AOT referenced in this AD
specifies to submit certain information 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
VerDate Aug<31>2005
16:42 Sep 05, 2006
Jkt 205001
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) European Aviation Safety Agency
airworthiness directive 2006–0136, dated
May 22, 2006, also addresses the subject of
this AD.
Material Incorporated by Reference
(l) You must use Airbus All Operators
Telex A320–54A1015, dated December 14,
2005, 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 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 August
23, 2006.
Kalene C. Yanamura,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. E6–14623 Filed 9–5–06; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2006–24667; Directorate
Identifier 2006–NM–009–AD; Amendment
39–14746; AD 2006–18–08]
RIN 2120–AA64
Airworthiness Directives; Goodyear
Aviation Tires, Part Number 217K22–1,
Installed on Various Transport
Category Airplanes, Including But Not
Limited to Bombardier Model BD–700–
1A10 and BD–700–1A11 Airplanes; and
Gulfstream Model G–1159, G–1159A,
G–1159B, G–IV, GIV–X, GV, and GV–SP
Series Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
PO 00000
Frm 00021
Fmt 4700
Sfmt 4700
52423
SUMMARY: The FAA is adopting a new
airworthiness directive (AD) for certain
aviation tires installed on various
transport category airplanes. This AD
requires a one-time inspection of the
nosewheel tires to determine if they are
within a designated serial number
range, and replacement if necessary.
This AD results from reports of tread
separations and tread-area bulges on the
nosewheel tires. We are issuing this AD
to prevent tread separation from a
nosewheel tire during takeoff or
landing, which could result in
compromised nosewheel steering or
ingestion of separated tread by an
engine, and consequent reduced
controllability of the airplane on the
runway or in the air.
DATES: This AD becomes effective
October 11, 2006.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in the AD
as of October 11, 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 Goodyear Tire and Rubber
Company, 1144 E. Market Street, Akron,
OH 44316–0001, for service information
identified in this AD.
FOR FURTHER INFORMATION CONTACT: Nick
Miller, Aerospace Engineer, Systems
and Flight Test Branch, ACE–117C,
Chicago Aircraft Certification Office,
FAA, 2300 East Devon Avenue, Room
107, Des Plaines, IL 60018; telephone
(847) 294–7518; fax (847) 294–7834.
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 aviation tires installed
on various transport category airplanes.
That NPRM was published in the
Federal Register on May 3, 2006 (71 FR
25987). That NPRM proposed to require
a one-time inspection of the nosewheel
E:\FR\FM\06SER1.SGM
06SER1
]]>Agencies
[Federal Register Volume 71, Number 172 (Wednesday, September 6, 2006)]
[Rules and Regulations]
[Pages 52421-52423]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E6-14623]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2006-24199; Directorate Identifier 2006-NM-025-AD;
Amendment 39-14744; AD 2006-18-06]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A318, A319, A320, and A321
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 A318, A319, A320, and A321 airplanes. This AD
requires revising the Limitations section of the airplane flight manual
(AFM); performing a one-time hardness test of certain ribs of the left-
and right-hand engine pylons, as applicable, which would terminate the
AFM limitations; and performing related corrective actions if
necessary. This AD results from a report that certain stainless steel
ribs installed in the engine pylon may not have been heat-treated
during manufacture, which could result in significantly reduced
structural integrity of the pylon. We are issuing this AD to detect and
correct reduced structural integrity of the engine pylon, which could
lead to separation of the engine from the airplane.
DATES: This AD becomes effective October 11, 2006.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in the AD as of October 11,
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 98057-3356; 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 part 39 to include an AD that would apply to certain Airbus Model
A318, A319, A320, and A321 airplanes. That NPRM was published in the
Federal
[[Page 52422]]
Register on March 27, 2006 (71 FR 15065). That NPRM proposed to require
revising the Limitations section of the airplane flight manual (AFM);
performing a one-time hardness test of certain ribs of the left- and
right-hand engine pylons, as applicable, which would terminate the AFM
limitations; and performing related corrective actions if necessary.
Comments
We provided the public the opportunity to participate in the
development of this AD. We have considered the comment received.
Request To Revise Hardness Test Requirement
The Air Transport Association (ATA), on behalf of its member,
Northwest Airlines (NWA), requests that we review the requirement for
the hardness test specified in the NPRM. NWA states that the NPRM
proposes a hardness test before further flight in the case of a hard or
overweight landing and further states that French airworthiness
directive F-2006-011 R1, dated January 18, 2006, which also addresses
the subject of this AD, did not have such a requirement. NWA asserts
that a requirement to visually inspect the airplane and pylons for
deformation after a hard landing already exists. NWA believes that, as
a hardness test requires special tooling and expertise that would not
likely be available at most locations where a hard landing might occur,
the hardness test is not appropriate and a visual inspection in
accordance with maintenance procedures should be accomplished instead.
We agree with NWA that a hardness test after a hard or overweight
landing is not necessary. Therefore, we have revised paragraph (g) of
the AD to remove the requirement for a hardness test after a hard or
overweight landing.
Clarification of Corrective Actions
To prevent possible confusion, we have revised paragraph (h) of the
AD to clarify that the specified corrective actions apply to discrepant
ribs discovered during the hardness test required by paragraph (g) of
the AD.
Supersedure of French Airworthiness Directive
The European Aviation Safety Agency (EASA) has issued airworthiness
directive 2006-0136, dated May 22, 2006. The EASA airworthiness
directive supersedes French airworthiness directive F-2006-011 R1,
dated January 18, 2006, which was referenced in the NPRM as the
applicable parallel airworthiness directive. The EASA airworthiness
directive contains no new or revised material that affects the
technical content of this AD; however, we have revised paragraph (k) of
this AD for clarity and traceability of information that applies to
this AD.
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 changes described previously.
We have determined that these changes will neither increase the
economic burden on any operator nor increase the scope of the AD.
Costs of Compliance
This AD will affect about 112 airplanes of U.S. registry. The
required hardness test 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 $7,280, or $65 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):
2006-18-06 Airbus: Amendment 39-14744. Docket No. FAA-2006-24199;
Directorate Identifier 2006-NM-025-AD.
Effective Date
(a) This AD becomes effective October 11, 2006.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Airbus Model A318, A319, A320, and A321
airplanes, certificated in any category; having a manufacturer
serial number as identified in Airbus All Operators Telex (AOT)
A320-54A1015, dated December 14, 2005 (referred to after this
paragraph as ``the AOT'').
Unsafe Condition
(d) This AD results from a report that certain stainless steel
ribs installed in the engine pylon may not have been heat-treated
during manufacture, which could result in significantly reduced
structural integrity of the pylon. We are issuing this AD to detect
and correct reduced structural integrity of the engine pylon, which
could lead to 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.
[[Page 52423]]
Revise Limitations
(f) Within 10 days after the effective date of this AD, revise
the Limitations section of the Airbus A318/319/320/321 Airplane
Flight Manual (AFM) to include the following statement. This may be
done by inserting a copy of this AD into the AFM.
``In case of flight in severe turbulence, strictly adhere to
reduced speeds as defined in Aircraft Flight Manual 4.03.00 P 03.''
Note 1: When a statement identical to that specified in
paragraph (f) of this AD has been included in the general revisions
of the AFM, and the general revisions have been inserted into the
AFM, the copy of this AD may be removed from the Limitations section
of the AFM unless it has already been removed as specified in
paragraph (g) or (h) of this AD.
Hardness Test
(g) Within the compliance time specified in paragraph (g)(1) or
(g)(2) of this AD, as applicable: Perform a one-time hardness test
to determine the hardness of ribs 8 and 9 of the left- and right-
hand engine pylons, in accordance with the instructions of the AOT.
If no discrepant rib is found installed on the airplane, the
statement specified in paragraph (f) of this AD may be removed from
the Limitations section of the AFM.
(1) For airplanes equipped with CFM engines: Within 6 months
after the effective date of this AD.
(2) For airplanes equipped with IAE engines: Within 9 months
after the effective date of this AD.
Note 2: The AOT refers to Airbus Repair Instruction 546 12081,
Issue B, dated January 3, 2006, as an additional source of service
information for accomplishing the actions specified by the AOT.
Corrective Actions
(h) For any discrepant rib found during the hardness test
specified by paragraph (g) of this AD: Within the compliance time
specified in paragraph (h)(1) or (h)(2) of this AD, as applicable,
perform applicable corrective actions in accordance with the
instructions of the AOT. When corrective actions have been applied
to all discrepant ribs found on the airplane, the statement
specified in paragraph (f) of this AD may be removed from the
Limitations section of the AFM for that airplane.
(1) For airplanes equipped with CFM engines: Within 14 days
after accomplishing the hardness test required by paragraph (g) of
this AD.
(2) For airplanes equipped with IAE engines: Within 28 days
after accomplishing the hardness test required by paragraph (g) of
this AD.
No Reporting Requirement
(i) Although the AOT referenced in this AD specifies to submit
certain information 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) European Aviation Safety Agency airworthiness directive
2006-0136, dated May 22, 2006, also addresses the subject of this
AD.
Material Incorporated by Reference
(l) You must use Airbus All Operators Telex A320-54A1015, dated
December 14, 2005, 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 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 August 23, 2006.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E6-14623 Filed 9-5-06; 8:45 am]
BILLING CODE 4910-13-P
