Airworthiness Directives; Airbus Airplanes, 12989-12991 [2012-4498]
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12989
Rules and Regulations
Federal Register
Vol. 77, No. 43
Monday, March 5, 2012
This section of the FEDERAL REGISTER
contains regulatory documents having general
applicability and legal effect, most of which
are keyed to and codified in the Code of
Federal Regulations, which is published under
50 titles pursuant to 44 U.S.C. 1510.
The Code of Federal Regulations is sold by
the Superintendent of Documents. Prices of
new books are listed in the first FEDERAL
REGISTER issue of each week.
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2011–0997; Directorate
Identifier 2011–NM–043–AD; Amendment
39–16963; AD 2012–04–07]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for certain
Airbus Model A330–200 series
airplanes; Model A330–300 series
airplanes; Model A340–200 series
airplanes; and Model A340–300 series
airplanes. This AD was prompted by a
report that three failures of the
retraction bracket occurred during
fatigue testing before the calculated life
limit of the main landing gear (MLG).
This AD requires repetitive replacement
of the affected retraction bracket of the
MLG. We are issuing this AD to prevent
failure of the retraction bracket, which
could result in a MLG extension with no
damping, and consequent structural
damage of the MLG.
DATES: This AD becomes effective April
9, 2012.
ADDRESSES: You may examine the AD
docket on the Internet at https://
www.regulations.gov or in person at the
U.S. Department of Transportation,
Docket Operations, M–30, West
Building Ground Floor, Room W12–140,
1200 New Jersey Avenue SE.,
Washington, DC.
FOR FURTHER INFORMATION CONTACT:
Vladimir Ulyanov, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
tkelley on DSK3SPTVN1PROD with RULES
SUMMARY:
VerDate Mar<15>2010
16:55 Mar 02, 2012
Jkt 226001
1601 Lind Avenue SW., Renton,
Washington 98057–3356; telephone
(425) 227–1138; fax (425) 227–1149.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would
apply to the specified products. That
NPRM was published in the Federal
Register on October 5, 2011 (76 FR
61645). That NPRM proposed to correct
an unsafe condition for the specified
products. The MCAI states:
During fatigue testing of the MLG [main
landing gear], three failures of the retraction
bracket occurred before the calculated life
limitation. Further analysis has confirmed
that those failures were due to fatigue
initiated by fretting between the bush and lug
bore.
The failure of the retraction bracket, if not
detected, could lead to a MLG extension with
no damping resulting in MLG structural
damage.
Airbus carried out an investigation,
demonstrating that the life limit of retraction
brackets must be reduced to 19,800 Landings
(LDG), which is below the life limit stated in
the following A330 and A340 Airbus ALS
Part 4 revisions:
—Airbus A330 ALS Part 4 revision 02
approved by EASA on 16 December 2009.
—Airbus A340 ALS Part 4 revision 01
approved by EASA on 15 December 2009.
In order to maintain the structural integrity
of the aeroplane, this [EASA] AD requires the
replacement of these MLG retraction brackets
before the accumulation of 19,800 total LDG.
You may obtain further information by
examining the MCAI in the AD docket.
Comments
We gave the public the opportunity to
participate in developing this AD. We
received no comments on the NPRM (76
FR 61645, October 5, 2011) or on the
determination of the cost to the public.
Explanation of Change Made to This
AD
We have re-designated Notes 1 and 2
of the NPRM (76 FR 61645, October 5,
2011) as paragraph (h) in this final rule,
and re-identified subsequent paragraphs
accordingly.
Conclusion
We reviewed the relevant data, and
determined that air safety and the
public interest require adopting the AD
with the change described previously—
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Frm 00001
Fmt 4700
Sfmt 4700
and minor editorial changes. We have
determined that these minor changes:
• Are consistent with the intent that
was proposed in the NPRM (76 FR
61645, October 5, 2011) for correcting
the unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the NPRM (76 FR 61645,
October 5, 2011).
We also determined that these
changes will not increase the economic
burden on any operator or increase the
scope of the AD.
Costs of Compliance
We estimate that this AD will affect
29 products of U.S. registry. We also
estimate that it will take about 25 workhours per product to comply with the
basic requirements of this AD. The
average labor rate is $85 per work-hour.
Required parts will cost about $200,000
per product. Based on these figures, we
estimate the cost of this AD to the U.S.
operators to be $5,861,625, or $202,125
per product.
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 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.
E:\FR\FM\05MRR1.SGM
05MRR1
12990
Federal Register / Vol. 77, No. 43 / Monday, March 5, 2012 / Rules and Regulations
For the reasons discussed above, I
certify this proposed regulation:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in
Alaska; and
4. 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.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov; or in person at the
Docket Operations office between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains the NPRM (76 FR 61645,
October 5, 2011), the regulatory
evaluation, any comments received, and
other information. The street address for
the Docket Operations office (telephone
(800) 647–5527) is in the ADDRESSES
section. Comments will be available in
the AD docket shortly after receipt.
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:
PART 39—AIRWORTHINESS
DIRECTIVES
–311, –312, and –313 airplanes; certificated
in any category, all manufacturer serial
numbers; except airplanes on which Airbus
modification 54500 has been embodied in
production; and except airplanes on which
Airbus Service Bulletin A330–32–3212 or
Airbus Service Bulletin A340–32–4256 has
been embodied in service; as applicable to
airplane model.
be found in Task 32–11–11–000–804–A,
Removal of the MLG Retraction Bracket
Assembly, and Task 32–11–11–400–804–A,
Installation of the MLG Retraction Bracket
Assembly, of Subsection 32–11–11 of
Chapter 32 of the Airbus A330 or A340
Aircraft Maintenance Manual, as applicable.
(d) Subject
Air Transport Association (ATA) of
America Code 32: Landing Gear.
(1) For purposes of this AD, ‘‘total
landings’’ is defined as the accumulated
landings since the initial entry of the MLG
retraction bracket into service on any
airplane.
(2) For purposes of this AD, the initial
entry into service for the transferable systems
components/items is defined as the date at
which the component/item accomplishes the
first flight for which it will undertake its
intended function.
(e) Reason
This AD was prompted by a report that
three failures of the retraction bracket
occurred during fatigue testing before the
calculated life limit of the main landing gear
(MLG). We are issuing this AD to prevent
failure of the retraction bracket, which could
result in a MLG extension with no damping,
and consequent structural damage of the
MLG.
(f) Compliance
You are responsible for having the actions
required by this AD performed within the
compliance times specified, unless the
actions have already been done.
(g) Replacement
Before the accumulation of 19,800 total
landings on the retraction brackets of the
MLG or within 900 flight hours after the
effective date of this AD, whichever occurs
later: Replace the affected retraction bracket
of the MLG specified in table 1 of this AD
with a serviceable part, in accordance with
a method approved by the Manager,
International Branch, ANM–116, FAA, or
European Aviation Safety Agency (EASA) (or
its delegated agent). Thereafter, before the
accumulation of 19,800 total landings on any
retraction bracket of the MLG identified in
table 1 of this AD, replace the retraction
bracket with a serviceable part, in accordance
with a method approved by the Manager,
International Branch, ANM–116, FAA, or
EASA (or its delegated
TABLE 1—RETRACTION BRACKET OF
THE MLG
1. The authority citation for part 39
continues to read as follows:
■
Nomenclature
Part No.
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
Retraction Bracket of the
MLG ..................................
[Amended]
2. The FAA amends § 39.13 by adding
the following new AD:
■
2012–04–07 Airbus: Amendment 39–16963.
Docket No. FAA–2011–0997; Directorate
Identifier 2011–NM–043–AD.
tkelley on DSK3SPTVN1PROD with RULES
(a) Effective Date
This airworthiness directive (AD) becomes
effective April 9, 2012.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Airbus Model A330–
201, –202, –203, –223, –243, –301, –302,
–303, –321, –322, –323, –341, –342, and –343
airplanes; and Model A340–211, –212, –213,
VerDate Mar<15>2010
16:55 Mar 02, 2012
Jkt 226001
201478303
201478304
201478305
201478306
201478307
201478308
201428380
201428381
201428382
201428383
201428384
201428385
201428378
201428379
201428351
201428352
Note 1 to paragraph (g) of this AD:
Additional guidance for the replacement can
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Fmt 4700
Sfmt 4700
(h) Definitions
(i) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Branch, ANM–116, FAA, has the authority to
approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19.
In accordance with 14 CFR 39.19, send your
request to your principal inspector or local
Flight Standards District Office, as
appropriate. If sending information directly
to the International Branch, send it to ATTN:
Vladimir Ulyanov, Aerospace Engineer,
International Branch, ANM–116, Transport
Airplane Directorate, FAA, 1601 Lind
Avenue SW., Renton, Washington 98057–
3356; telephone (425) 227–1138; fax (425)
227–1149. Information may be emailed to: 9ANM-116-AMOC-REQUESTS@faa.gov.
Before using any approved AMOC, notify
your appropriate principal inspector, or
lacking a principal inspector, the manager of
the local flight standards district office/
certificate holding district office. The AMOC
approval letter must specifically reference
this AD.
(2) Airworthy Product: For any requirement
in this AD to obtain corrective actions from
a manufacturer or other source, use these
actions if they are FAA-approved. Corrective
actions are considered FAA-approved if they
are approved by the State of Design Authority
(or their delegated agent). You are required
to assure the product is airworthy before it
is returned to service.
(j) Related Information
(1) Refer to MCAI Airworthiness Directive
EASA AD 2010–0205, dated October 8, 2010,
for related information.
(2) For Airbus service information
identified in this AD contact Airbus SAS—
Airworthiness Office—EAL, 1 Rond Point
Maurice Bellonte, 31707 Blagnac Cedex,
France; telephone +33 5 61 93 36 96; fax +33
5 61 93 45 80; email airworthiness.A330–
A340@airbus.com; Internet https://
www.airbus.com.
(k) Material Incorporated by Reference
None.
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Federal Register / Vol. 77, No. 43 / Monday, March 5, 2012 / Rules and Regulations
Issued in Renton, Washington, on February
14, 2012.
Kalene C. Yanamura,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2012–4498 Filed 3–2–12; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2011–1420; Directorate
Identifier 2011–CE–035–AD; Amendment
39–16905; AD 2011–27–04]
RIN 2120–AA64
Airworthiness Directives; Hawker
Beechcraft Corporation Airplanes
Equipped With a Certain Supplemental
Type Certificate (STC)
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule; correction.
AGENCY:
The FAA is correcting an
airworthiness directive (AD) that
published in the Federal Register. That
AD applies to all Hawker Beechcraft
Corporation Models 95–C55, D55, E55,
58, and 58A airplanes equipped with a
certain STC. The description of the
affected STCs in the first sentence of the
SUPPLEMENTARY INFORMATION, Discussion
section, is incorrect. This document
corrects that error. In all other respects,
the original document remains the
same.
SUMMARY:
This final rule is effective March
5, 2012. The effective date for AD 2011–
27–04 (76 FR 81790, December 29,
2011) remains December 29, 2011.
ADDRESSES: You may examine the AD
docket on the Internet at https://
www.regulations.gov; or in person at the
Docket Management Facility between 9
a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The AD
docket contains this AD, the regulatory
evaluation, any comments received, and
other information. The address for the
Docket Office (phone: 800–647–5527) is
Document Management Facility, U.S.
Department of Transportation, Docket
Operations, M–30, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue SE., Washington,
DC 20590.
FOR FURTHER INFORMATION CONTACT: Eric
B. Potter, Aerospace Engineer, Atlanta
Aircraft Certification Office, FAA, 1701
Columbia Avenue, College Park, Georgia
30337; phone: (404) 474–5583; fax: (404)
474–5606; email: eric.potter@faa.gov.
tkelley on DSK3SPTVN1PROD with RULES
DATES:
VerDate Mar<15>2010
16:55 Mar 02, 2012
Jkt 226001
SUPPLEMENTARY INFORMATION:
Airworthiness Directive 2011–27–04,
amendment 39–16905 (76 FR 81790,
December 29, 2011), currently requires
assuring the airspeed indicator(s) and/or
airspeed limitations placard(s) have the
correct minimum control speed (VMC)
markings for all Hawker Beechcraft
Corporation Models 95–C55, D55, E55,
58, and 58A airplanes equipped with a
certain STC.
As published, the description of the
affected STCs in the first sentence of the
SUPPLEMENTARY INFORMATION, Discussion
section, is incorrect.
No other part of the preamble or
regulatory information has been
changed; therefore, only the changed
portion of the preamble to the final rule
is being published in the Federal
Register.
The effective date of this AD remains
December 29, 2011.
Correction of Non-Regulatory Text
In the Federal Register of December
29, 2011, AD 2011–27–04; Amendment
39–16905 is corrected as follows:
On page 81790, in the third column,
on line 2 under the heading
SUPPLEMENTARY INFORMATION,
Discussion, correct ‘‘, we found that
STC SA1762SO (installation of vortex
generators) and STC SA4016NM
(Foxstar Baron modification of winglets
and different engines and propellers)
were installed.’’ to read ‘‘, we found that
STC SA1762SO (Foxstar Baron
modification of winglets and different
engines and propellers) and STC
SA4016NM (installation of vortex
generators) were installed.’’
Issued in Kansas City, Missouri, on
February 23, 2012.
John Colomy,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2012–5290 Filed 3–2–12; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2011–0588; Directorate
Identifier 2010–SW–074–AD; Amendment
39–16717; AD 2011–12–10]
RIN 2120–AA64
Airworthiness Directives; Robinson
Helicopter Company Helicopters
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule; correction.
AGENCY:
PO 00000
Frm 00003
Fmt 4700
Sfmt 4700
12991
The FAA is correcting an
airworthiness directive (AD) that was
published in the Federal Register. That
AD applies to Robinson Helicopter
Company (Robinson) Model R22, R22
Alpha, R22 Beta, R22 Mariner, R44, and
R44 II helicopters. The paragraph
reference in paragraph (b) of the
Compliance section is incorrect.
Paragraph (b) references paragraph (d),
when it should reference paragraph (c).
This document corrects that error.
Additionally, the word ‘‘inspection’’ has
been added in paragraph (b) for
clarification. In all other respects, the
original document remains the same.
DATES: The effective date of this final
rule is March 5, 2012. The effective date
for AD 2011–12–10 remains July 5,
2011.
Examining the AD Docket: You may
examine the AD docket on the Internet
at https://www.regulations.gov; or in
person at the Docket Operations Office
between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
The AD docket contains this AD, any
incorporated-by-reference service
information, the economic evaluation,
any comments received, and other
information. The street address for the
Docket Operations Office (phone: 800–
647–5527) is U.S. Department of
Transportation, Docket Operations
Office, M–30, West Building Ground
Floor, Room W12–140, 1200 New Jersey
Avenue SE., Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: Eric
D. Schrieber, Aerospace Engineer, Los
Angeles Aircraft Certification Office,
Transport Airplane Directorate, FAA,
3960 Paramount Blvd., Lakewood, CA
90712; telephone (562) 627–5348; email
eric.schrieber@faa.gov (regarding Model
R22 helicopters); or Fred Guerin,
Aerospace Engineer, Los Angeles
Aircraft Certification Office, Transport
Airplane Directorate, FAA, 3960
Paramount Blvd., Lakewood, CA 90712;
telephone (562) 627–5232; email
fred.guerin@faa.gov (regarding Model
R44 helicopters).
SUPPLEMENTARY INFORMATION:
Airworthiness Directive 2011–12–10,
Amendment 39–16717 (76 FR 35330,
June 17, 2011), currently includes the
following paragraph (b) in the
compliance section:
‘‘(b) If you find any bare metal in the
area of the skin-to-spar bond line, before
further flight, inspect the blade by
following the requirements of paragraph
(d) of this AD.’’
As published, the reference to
paragraph (d) is incorrect. The correct
reference is to paragraph (c). Paragraph
(c) contains the inspection
requirements, and the incorrect
SUMMARY:
E:\FR\FM\05MRR1.SGM
05MRR1
Agencies
[Federal Register Volume 77, Number 43 (Monday, March 5, 2012)]
[Rules and Regulations]
[Pages 12989-12991]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2012-4498]
========================================================================
Rules and Regulations
Federal Register
________________________________________________________________________
This section of the FEDERAL REGISTER contains regulatory documents
having general applicability and legal effect, most of which are keyed
to and codified in the Code of Federal Regulations, which is published
under 50 titles pursuant to 44 U.S.C. 1510.
The Code of Federal Regulations is sold by the Superintendent of Documents.
Prices of new books are listed in the first FEDERAL REGISTER issue of each
week.
========================================================================
Federal Register / Vol. 77, No. 43 / Monday, March 5, 2012 / Rules
and Regulations
[[Page 12989]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2011-0997; Directorate Identifier 2011-NM-043-AD;
Amendment 39-16963; AD 2012-04-07]
RIN 2120-AA64
Airworthiness Directives; Airbus Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for certain
Airbus Model A330-200 series airplanes; Model A330-300 series
airplanes; Model A340-200 series airplanes; and Model A340-300 series
airplanes. This AD was prompted by a report that three failures of the
retraction bracket occurred during fatigue testing before the
calculated life limit of the main landing gear (MLG). This AD requires
repetitive replacement of the affected retraction bracket of the MLG.
We are issuing this AD to prevent failure of the retraction bracket,
which could result in a MLG extension with no damping, and consequent
structural damage of the MLG.
DATES: This AD becomes effective April 9, 2012.
ADDRESSES: You may examine the AD docket on the Internet at https://www.regulations.gov or in person at the U.S. Department of
Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue SE., Washington, DC.
FOR FURTHER INFORMATION CONTACT: Vladimir Ulyanov, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, Washington 98057-3356; telephone (425)
227-1138; fax (425) 227-1149.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would apply to the specified products.
That NPRM was published in the Federal Register on October 5, 2011 (76
FR 61645). That NPRM proposed to correct an unsafe condition for the
specified products. The MCAI states:
During fatigue testing of the MLG [main landing gear], three
failures of the retraction bracket occurred before the calculated
life limitation. Further analysis has confirmed that those failures
were due to fatigue initiated by fretting between the bush and lug
bore.
The failure of the retraction bracket, if not detected, could
lead to a MLG extension with no damping resulting in MLG structural
damage.
Airbus carried out an investigation, demonstrating that the life
limit of retraction brackets must be reduced to 19,800 Landings
(LDG), which is below the life limit stated in the following A330
and A340 Airbus ALS Part 4 revisions:
--Airbus A330 ALS Part 4 revision 02 approved by EASA on 16 December
2009.
--Airbus A340 ALS Part 4 revision 01 approved by EASA on 15 December
2009.
In order to maintain the structural integrity of the aeroplane,
this [EASA] AD requires the replacement of these MLG retraction
brackets before the accumulation of 19,800 total LDG.
You may obtain further information by examining the MCAI in the AD
docket.
Comments
We gave the public the opportunity to participate in developing
this AD. We received no comments on the NPRM (76 FR 61645, October 5,
2011) or on the determination of the cost to the public.
Explanation of Change Made to This AD
We have re-designated Notes 1 and 2 of the NPRM (76 FR 61645,
October 5, 2011) as paragraph (h) in this final rule, and re-identified
subsequent paragraphs accordingly.
Conclusion
We reviewed the relevant data, and determined that air safety and
the public interest require adopting the AD with the change described
previously--and minor editorial changes. We have determined that these
minor changes:
Are consistent with the intent that was proposed in the
NPRM (76 FR 61645, October 5, 2011) for correcting the unsafe
condition; and
Do not add any additional burden upon the public than was
already proposed in the NPRM (76 FR 61645, October 5, 2011).
We also determined that these changes will not increase the
economic burden on any operator or increase the scope of the AD.
Costs of Compliance
We estimate that this AD will affect 29 products of U.S. registry.
We also estimate that it will take about 25 work-hours per product to
comply with the basic requirements of this AD. The average labor rate
is $85 per work-hour. Required parts will cost about $200,000 per
product. Based on these figures, we estimate the cost of this AD to the
U.S. operators to be $5,861,625, or $202,125 per product.
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 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.
[[Page 12990]]
For the reasons discussed above, I certify this proposed
regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in Alaska; and
4. 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.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov; or in person at the Docket Operations office
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains the NPRM (76 FR 61645, October 5,
2011), the regulatory evaluation, any comments received, and other
information. The street address for the Docket Operations office
(telephone (800) 647-5527) is in the ADDRESSES section. Comments will
be available in the AD docket shortly after receipt.
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:
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]
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2. The FAA amends Sec. 39.13 by adding the following new AD:
2012-04-07 Airbus: Amendment 39-16963. Docket No. FAA-2011-0997;
Directorate Identifier 2011-NM-043-AD.
(a) Effective Date
This airworthiness directive (AD) becomes effective April 9,
2012.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Airbus Model A330-201, -202, -203, -223, -
243, -301, -302, -303, -321, -322, -323, -341, -342, and -343
airplanes; and Model A340-211, -212, -213, -311, -312, and -313
airplanes; certificated in any category, all manufacturer serial
numbers; except airplanes on which Airbus modification 54500 has
been embodied in production; and except airplanes on which Airbus
Service Bulletin A330-32-3212 or Airbus Service Bulletin A340-32-
4256 has been embodied in service; as applicable to airplane model.
(d) Subject
Air Transport Association (ATA) of America Code 32: Landing
Gear.
(e) Reason
This AD was prompted by a report that three failures of the
retraction bracket occurred during fatigue testing before the
calculated life limit of the main landing gear (MLG). We are issuing
this AD to prevent failure of the retraction bracket, which could
result in a MLG extension with no damping, and consequent structural
damage of the MLG.
(f) Compliance
You are responsible for having the actions required by this AD
performed within the compliance times specified, unless the actions
have already been done.
(g) Replacement
Before the accumulation of 19,800 total landings on the
retraction brackets of the MLG or within 900 flight hours after the
effective date of this AD, whichever occurs later: Replace the
affected retraction bracket of the MLG specified in table 1 of this
AD with a serviceable part, in accordance with a method approved by
the Manager, International Branch, ANM-116, FAA, or European
Aviation Safety Agency (EASA) (or its delegated agent). Thereafter,
before the accumulation of 19,800 total landings on any retraction
bracket of the MLG identified in table 1 of this AD, replace the
retraction bracket with a serviceable part, in accordance with a
method approved by the Manager, International Branch, ANM-116, FAA,
or EASA (or its delegated
Table 1--Retraction Bracket of the MLG
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Nomenclature Part No.
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Retraction Bracket of the MLG........................... 201478303
201478304
201478305
201478306
201478307
201478308
201428380
201428381
201428382
201428383
201428384
201428385
201428378
201428379
201428351
201428352
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Note 1 to paragraph (g) of this AD: Additional guidance for the
replacement can be found in Task 32-11-11-000-804-A, Removal of the
MLG Retraction Bracket Assembly, and Task 32-11-11-400-804-A,
Installation of the MLG Retraction Bracket Assembly, of Subsection
32-11-11 of Chapter 32 of the Airbus A330 or A340 Aircraft
Maintenance Manual, as applicable.
(h) Definitions
(1) For purposes of this AD, ``total landings'' is defined as
the accumulated landings since the initial entry of the MLG
retraction bracket into service on any airplane.
(2) For purposes of this AD, the initial entry into service for
the transferable systems components/items is defined as the date at
which the component/item accomplishes the first flight for which it
will undertake its intended function.
(i) Other FAA AD Provisions
The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
International Branch, ANM-116, FAA, has the authority to approve
AMOCs for this AD, if requested using the procedures found in 14 CFR
39.19. In accordance with 14 CFR 39.19, send your request to your
principal inspector or local Flight Standards District Office, as
appropriate. If sending information directly to the International
Branch, send it to ATTN: Vladimir Ulyanov, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, Washington 98057-3356; telephone (425)
227-1138; fax (425) 227-1149. Information may be emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. Before using any approved AMOC, notify
your appropriate principal inspector, or lacking a principal
inspector, the manager of the local flight standards district
office/certificate holding district office. The AMOC approval letter
must specifically reference this AD.
(2) Airworthy Product: For any requirement in this AD to obtain
corrective actions from a manufacturer or other source, use these
actions if they are FAA-approved. Corrective actions are considered
FAA-approved if they are approved by the State of Design Authority
(or their delegated agent). You are required to assure the product
is airworthy before it is returned to service.
(j) Related Information
(1) Refer to MCAI Airworthiness Directive EASA AD 2010-0205,
dated October 8, 2010, for related information.
(2) For Airbus service information identified in this AD contact
Airbus SAS--Airworthiness Office--EAL, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96;
fax +33 5 61 93 45 80; email airworthiness.A330-A340@airbus.com;
Internet https://www.airbus.com.
(k) Material Incorporated by Reference
None.
[[Page 12991]]
Issued in Renton, Washington, on February 14, 2012.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2012-4498 Filed 3-2-12; 8:45 am]
BILLING CODE 4910-13-P