Airworthiness Directives; Airbus Airplanes, 25664-25666 [2013-10366]
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Federal Register / Vol. 78, No. 85 / Thursday, May 2, 2013 / Proposed Rules
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Detailed and High Frequency Eddy
Current (HFEC) Inspections
Within 24 months after the effective date
of this AD: Do a detailed inspection for
cracking and corrosion of the left and right
side chords of the fin closure rib, and do a
HFEC inspection of the left- and right-side
chords for cracking, in accordance with the
Accomplishment Instructions of Boeing
Special Attention Service Bulletin 727–55–
0095, dated September 24, 2012. If any
cracking or corrosion is found, before further
flight, repair or replace the affected right or
left-side chord using a method approved in
accordance with the procedures specified in
paragraph (h) of this AD. Repeat the detailed
inspection and HFEC inspection thereafter at
intervals not to exceed 26 months.
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(h) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Seattle Aircraft
Certification Office (ACO), 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 manager of the ACO, send it to the
attention of the person identified in the
Related Information section of this AD.
Information may be emailed to: 9-ANMSeattle-ACO-AMOC-Requests@faa.gov.
(2) 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.
(3) An AMOC that provides an acceptable
level of safety may be used for any repair
required by this AD if it is approved by the
Boeing Commercial Airplanes Organization
Designation Authorization (ODA) that has
been authorized by the Manager, Seattle
ACO, to make those findings. For a repair
method to be approved, the repair must meet
the certification basis of the airplane, and the
approval must specifically refer to this AD.
(i) Related Information
(1) For more information about this AD,
contact Berhane Alazar, Aerospace Engineer,
Airframe Branch, ANM–120S, FAA, Seattle
Aircraft Certification Office, 1601 Lind
Avenue SW., Renton, Washington 98057–
3356; phone: 425–917–6577; fax: 425–917–
6590; email: berhane.alazar@faa.gov.
(2) For Boeing service information
identified in this AD, contact Boeing
Commercial Airplanes, Attention: Data &
Services Management, P.O. Box 3707, MC
2H–65, Seattle, WA 98124–2207; telephone
206- 544–5000, extension 1; fax 206–766–
5680; Internet https://
www.myboeingfleet.com. You may also
review copies of the referenced service
information at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue SW., Renton,
Washington. For information on the
availability of this material at the FAA, call
425–227–1221.
VerDate Mar<15>2010
16:43 May 01, 2013
Jkt 229001
Issued in Renton, Washington, on April 23,
2013.
Jeffrey E. Duven,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2013–10367 Filed 5–1–13; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2013–0335; Directorate
Identifier 2012–NM–187–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
SUMMARY: We propose to adopt a new
airworthiness directive (AD) for certain
Airbus Model A330–300, A340–200,
and A340–300 series airplanes. This
proposed AD was prompted by a
determination that ballscrew rupture
could occur on certain trimmable
horizontal stabilizer actuators (THSAs).
This proposed AD would require
repetitive THSA ballscrew shaft
integrity tests, and replacement if
necessary. We are proposing this AD to
detect and correct ballscrew rupture,
which, along with corrosion on the
ballscrew lower splines, may lead to
loss of transmission of THSA torque
loads from the ballscrew to the tie-bar
and consequent THSA blowback, which
could result in loss of control of the
airplane.
We must receive comments on
this proposed AD by June 17, 2013.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: (202) 493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations,
M–30, West Building Ground Floor,
Room W12–140, 1200 New Jersey
Avenue SE., Washington, DC 20590.
• Hand Delivery: U.S. Department of
Transportation, Docket Operations,
M–30, West Building Ground Floor,
Room W12–140, 1200 New Jersey
Avenue SE., Washington, DC, between 9
a.m. and 5 p.m., Monday through
Friday, except Federal holidays.
For service information identified in
this proposed AD, contact Airbus SAS—
DATES:
PO 00000
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Fmt 4702
Sfmt 4702
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. You
may review copies of the referenced
service information at the FAA,
Transport Airplane Directorate, 1601
Lind Avenue SW., Renton, WA. For
information on the availability of this
material at the FAA, call 425–227–1221.
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 proposed AD, 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.
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:
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposed AD. Send your comments
to an address listed under the
ADDRESSES section. Include ‘‘Docket No.
FAA–2013–0335; Directorate Identifier
2012–NM–187–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this proposed AD. We will
consider all comments received by the
closing date and may amend this
proposed AD based on those comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this proposed AD.
Discussion
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Community, has issued EASA
Airworthiness Directive 2012–0210,
dated October 11, 2012 (referred to after
this as the Mandatory Continuing
Airworthiness Information, or ‘‘the
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Federal Register / Vol. 78, No. 85 / Thursday, May 2, 2013 / Proposed Rules
MCAI’’), to correct an unsafe condition
for the specified products. The MCAI
states:
Since the issuance of EASA AD 2012–0061
which addresses the corrosion identified in
service on THSA [part number] P/N 47147–
500 and P/N 47147–700 at the level of the
ballscrew lower splines, further analyses
have been conducted to determine the need
for any additional action.
The ballscrew lower splines are not loaded
in normal operation, only in case of
ballscrew rupture. Analysis results have
shown that such rupture could happen
during the current inspection interval
imposed by the Maintenance Review Board
Report (MRBR), task 274000–12.
Corrosion on the lower splines, in case of
ballscrew rupture, may lead to loss of
transmission of THSA torque loads from the
ballscrew to the tie-bar and consequent
THSA blowback, which could result in loss
of control of the aeroplane.
For the reasons described above, this
[EASA] AD requires reduction of the check
interval of MRBR task 274000–12.
Required actions include repetitive
THSA ballscrew shaft integrity tests.
Corrective actions include replacement
of the THSA. You may obtain further
information by examining the MCAI in
the AD docket.
Relevant Service Information
Airbus has issued the following
service bulletins. The actions described
in this service information are intended
to correct the unsafe condition
identified in the MCAI.
• Airbus Mandatory Service Bulletin
A330–27–3191, dated June 7, 2012.
• Airbus Mandatory Service Bulletin
A340–27–4186, dated June 7, 2012.
FAA’s Determination and Requirements
of This Proposed AD
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This product has been approved by
the aviation authority of another
country, and is approved for operation
in the United States. Pursuant to our
bilateral agreement with the State of
Design Authority, we have been notified
of the unsafe condition described in the
MCAI and service information
referenced above. We are proposing this
AD because we evaluated all pertinent
information and determined an unsafe
condition exists and is likely to exist or
develop on other products of the same
type design.
Costs of Compliance
Based on the service information, we
estimate that this proposed AD would
affect about 30 products of U.S. registry.
We also estimate that it would take
about 7 work-hours per product to
comply with the basic requirements of
this proposed AD. The average labor
rate is $85 per work-hour. Based on
VerDate Mar<15>2010
16:43 May 01, 2013
Jkt 229001
25665
these figures, we estimate the cost of the
proposed AD on U.S. operators to be
$17,850, or $595 per product.
In addition, we estimate that any
necessary follow-on actions would take
about 8 work-hours and require parts
costing up to $722,556, for a cost of up
to $723,236 per product. We have no
way of determining the number of
products that may need these actions.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Authority for This Rulemaking
PART 39—AIRWORTHINESS
DIRECTIVES
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 proposed AD
would not have federalism implications
under Executive Order 13132. This
proposed AD would 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 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 proposed AD and placed it in the
AD docket.
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Fmt 4702
Sfmt 4702
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new AD:
■
Airbus: Docket No. FAA–2013–0335;
Directorate Identifier 2012–NM–187–AD.
(a) Comments Due Date
We must receive comments by June 17,
2013.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Airbus Model A330–
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; if fitted with a
trimmable horizontal stabilizer actuator
(THSA) having part number (P/N) 47147–500
or P/N 47147–700.
(d) Subject
Air Transport Association (ATA) of
America Code 27, Flight Controls.
(e) Reason
This AD was prompted by a determination
that ballscrew rupture could occur on certain
THSAs. We are issuing this AD to detect and
correct ballscrew rupture, which, along with
corrosion on the ballscrew lower splines,
may lead to loss of transmission of THSA
torque loads from the ballscrew to the tie-bar
and consequent THSA blowback, which
could result in loss of control of the airplane.
(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) Repetitive Integrity Tests
At the later of the times specified in
paragraph (g)(1) or (g)(2) of this AD, as
applicable, do a THSA ballscrew shaft
integrity test, in accordance with the
Accomplishment Instructions of Airbus
Mandatory Service Bulletin A330–27–3191,
dated June 7, 2012; or Airbus Mandatory
Service Bulletin A340–27–4186, dated June
7, 2012; as applicable. Repeat the integrity
test thereafter at intervals not to exceed
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Federal Register / Vol. 78, No. 85 / Thursday, May 2, 2013 / Proposed Rules
12,000 flight hours or 4,400 flight cycles,
whichever occurs first.
(1) At the latest of the times specified in
paragraph (g)(1)(i), (g)(1)(ii), or (g)(1)(iii) of
this AD.
(i) Within 12,000 flight hours since the
airplane’s first flight; or
(ii) Within 12,000 flight hours since the
most recent THSA ballscrew shaft integrity
test was done as specified in maintenance
review board report (MRBR) Task 274000–12;
or
(iii) Within 12,000 flight hours since the
most recent THSA ballscrew shaft integrity
test was done, as specified in Airbus
Mandatory Service Bulletin A330–27–3179
or Airbus Mandatory Service Bulletin A340–
27–4175, as applicable. (These service
bulletins specify testing in case of type II or
type III findings).
(2) Within 1,000 flight hours after the
effective date of this AD, but without
exceeding the latest of the times specified in
paragraphs (g)(2)(i), (g)(2)(ii), or (g)(2)(iii) of
this AD.
(i) 16,000 flight hours since the airplane’s
first flight.
(ii) 16,000 flight hours since the most
recent THSA ballscrew shaft integrity test
was done, as specified in MRBR task 274000–
12.
(iii) 16,000 flight hours since the most
recent THSA ballscrew shaft integrity test
was done, as specified in Airbus Mandatory
Service Bulletin A330–27–3179, or Airbus
Mandatory Service Bulletin A340–27–4175,
as applicable. (These service bulletins specify
testing in case of type II or type III findings).
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(h) Replacement
If the result from any test required by
paragraph (g) of this AD is not correct, as
specified in the Accomplishment
Instructions of Airbus Mandatory Service
Bulletin A330–27–3191, dated June 7, 2012;
or Airbus Mandatory Service Bulletin A340–
27–4186, dated June 7, 2012; as applicable:
Before further flight, replace the THSA with
a serviceable THSA, in accordance with the
Accomplishment Instructions of Airbus
Mandatory Service Bulletin A330–27–3191,
dated June 7, 2012; or Airbus Mandatory
Service Bulletin A340–27–4186, dated June
7, 2012; as applicable. Replacement of a
THSA, as required by this paragraph, with a
THSA having P/N 47147–500 or P/N 47147–
700, is not terminating action for the
repetitive tests required by paragraph (g) of
this AD.
(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, Transport Airplane
Directorate, 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
VerDate Mar<15>2010
16:43 May 01, 2013
Jkt 229001
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 Mandatory Continuing
Airworthiness Information (MCAI) European
Aviation Safety Agency Airworthiness
Directive 2012–0210, dated October 11, 2012,
and the service bulletins specified in
paragraphs (j)(1)(i) and (j)(1)(ii) of this AD,
for related information.
(i) Airbus Mandatory Service Bulletin
A330–27–3191, dated June 7, 2012.
(ii) Airbus Mandatory Service Bulletin
A340–27–4186, dated June 7, 2012.
(2) For 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. You may
review copies of the referenced service
information at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue SW., Renton,
WA. For information on the availability of
this material at the FAA, call 425–227–1221.
Issued in Renton, Washington, on April 23,
2013.
Jeffrey E. Duven,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2013–10366 Filed 5–1–13; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2013–0360; Directorate
Identifier 2013–NM–033–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
SUMMARY: We propose to supersede an
existing airworthiness directive (AD)
PO 00000
Frm 00047
Fmt 4702
Sfmt 4702
that applies to all Airbus Model A318,
A319, A320, and A321 series airplanes.
The existing AD currently requires
revising the airplane flight manual
(AFM) to advise the flightcrew of
emergency procedures for addressing
angle of attack (AoA) sensor blockage.
The existing AD also provides for
optional terminating action for the AFM
revision, which involves replacing AoA
sensor conic plates with AoA sensor flat
plates. Since we issued that AD, we
have determined that the replacement of
AoA sensor conic plates is necessary to
address the identified unsafe condition.
This proposed AD would mandate the
installation of AoA sensor flat plates
and removal of the AFM revision. We
are proposing this AD to prevent
reduced control of the airplane.
DATES: We must receive comments on
this proposed AD by June 17, 2013.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: (202) 493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC 20590.
• Hand Delivery: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC, between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
For service information identified in
this proposed AD, contact Airbus,
Airworthiness Office—EIAS, 1 Rond
Point Maurice Bellonte, 31707 Blagnac
Cedex, France; telephone +33 5 61 93 36
96; fax +33 5 61 93 44 51; email
account.airworth-eas@airbus.com;
Internet https://www.airbus.com. You
may review copies of the referenced
service information at the FAA,
Transport Airplane Directorate, 1601
Lind Avenue SW., Renton, WA. For
information on the availability of this
material at the FAA, call 425–227–1221.
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 proposed AD, 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
E:\FR\FM\02MYP1.SGM
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]]>Agencies
[Federal Register Volume 78, Number 85 (Thursday, May 2, 2013)]
[Proposed Rules]
[Pages 25664-25666]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-10366]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2013-0335; Directorate Identifier 2012-NM-187-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to adopt a new airworthiness directive (AD) for
certain Airbus Model A330-300, A340-200, and A340-300 series airplanes.
This proposed AD was prompted by a determination that ballscrew rupture
could occur on certain trimmable horizontal stabilizer actuators
(THSAs). This proposed AD would require repetitive THSA ballscrew shaft
integrity tests, and replacement if necessary. We are proposing this AD
to detect and correct ballscrew rupture, which, along with corrosion on
the ballscrew lower splines, may lead to loss of transmission of THSA
torque loads from the ballscrew to the tie-bar and consequent THSA
blowback, which could result in loss of control of the airplane.
DATES: We must receive comments on this proposed AD by June 17, 2013.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
Fax: (202) 493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC 20590.
Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
For service information identified in this proposed 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. You may review copies of the referenced service
information at the FAA, Transport Airplane Directorate, 1601 Lind
Avenue SW., Renton, WA. For information on the availability of this
material at the FAA, call 425-227-1221.
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 proposed AD, 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.
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:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2013-0335;
Directorate Identifier 2012-NM-187-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD based on those comments.
We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Community, has issued EASA
Airworthiness Directive 2012-0210, dated October 11, 2012 (referred to
after this as the Mandatory Continuing Airworthiness Information, or
``the
[[Page 25665]]
MCAI''), to correct an unsafe condition for the specified products. The
MCAI states:
Since the issuance of EASA AD 2012-0061 which addresses the
corrosion identified in service on THSA [part number] P/N 47147-500
and P/N 47147-700 at the level of the ballscrew lower splines,
further analyses have been conducted to determine the need for any
additional action.
The ballscrew lower splines are not loaded in normal operation,
only in case of ballscrew rupture. Analysis results have shown that
such rupture could happen during the current inspection interval
imposed by the Maintenance Review Board Report (MRBR), task 274000-
12.
Corrosion on the lower splines, in case of ballscrew rupture,
may lead to loss of transmission of THSA torque loads from the
ballscrew to the tie-bar and consequent THSA blowback, which could
result in loss of control of the aeroplane.
For the reasons described above, this [EASA] AD requires
reduction of the check interval of MRBR task 274000-12.
Required actions include repetitive THSA ballscrew shaft integrity
tests. Corrective actions include replacement of the THSA. You may
obtain further information by examining the MCAI in the AD docket.
Relevant Service Information
Airbus has issued the following service bulletins. The actions
described in this service information are intended to correct the
unsafe condition identified in the MCAI.
Airbus Mandatory Service Bulletin A330-27-3191, dated June
7, 2012.
Airbus Mandatory Service Bulletin A340-27-4186, dated June
7, 2012.
FAA's Determination and Requirements of This Proposed AD
This product has been approved by the aviation authority of another
country, and is approved for operation in the United States. Pursuant
to our bilateral agreement with the State of Design Authority, we have
been notified of the unsafe condition described in the MCAI and service
information referenced above. We are proposing this AD because we
evaluated all pertinent information and determined an unsafe condition
exists and is likely to exist or develop on other products of the same
type design.
Costs of Compliance
Based on the service information, we estimate that this proposed AD
would affect about 30 products of U.S. registry. We also estimate that
it would take about 7 work-hours per product to comply with the basic
requirements of this proposed AD. The average labor rate is $85 per
work-hour. Based on these figures, we estimate the cost of the proposed
AD on U.S. operators to be $17,850, or $595 per product.
In addition, we estimate that any necessary follow-on actions would
take about 8 work-hours and require parts costing up to $722,556, for a
cost of up to $723,236 per product. We have no way of determining the
number of products that may need these actions.
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 proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would 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 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 proposed AD and placed it in the AD docket.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 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 FAA amends Sec. 39.13 by adding the following new AD:
Airbus: Docket No. FAA-2013-0335; Directorate Identifier 2012-NM-
187-AD.
(a) Comments Due Date
We must receive comments by June 17, 2013.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Airbus Model A330-301, -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; if fitted with a trimmable
horizontal stabilizer actuator (THSA) having part number (P/N)
47147-500 or P/N 47147-700.
(d) Subject
Air Transport Association (ATA) of America Code 27, Flight
Controls.
(e) Reason
This AD was prompted by a determination that ballscrew rupture
could occur on certain THSAs. We are issuing this AD to detect and
correct ballscrew rupture, which, along with corrosion on the
ballscrew lower splines, may lead to loss of transmission of THSA
torque loads from the ballscrew to the tie-bar and consequent THSA
blowback, which could result in loss of control of the airplane.
(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) Repetitive Integrity Tests
At the later of the times specified in paragraph (g)(1) or
(g)(2) of this AD, as applicable, do a THSA ballscrew shaft
integrity test, in accordance with the Accomplishment Instructions
of Airbus Mandatory Service Bulletin A330-27-3191, dated June 7,
2012; or Airbus Mandatory Service Bulletin A340-27-4186, dated June
7, 2012; as applicable. Repeat the integrity test thereafter at
intervals not to exceed
[[Page 25666]]
12,000 flight hours or 4,400 flight cycles, whichever occurs first.
(1) At the latest of the times specified in paragraph (g)(1)(i),
(g)(1)(ii), or (g)(1)(iii) of this AD.
(i) Within 12,000 flight hours since the airplane's first
flight; or
(ii) Within 12,000 flight hours since the most recent THSA
ballscrew shaft integrity test was done as specified in maintenance
review board report (MRBR) Task 274000-12; or
(iii) Within 12,000 flight hours since the most recent THSA
ballscrew shaft integrity test was done, as specified in Airbus
Mandatory Service Bulletin A330-27-3179 or Airbus Mandatory Service
Bulletin A340-27-4175, as applicable. (These service bulletins
specify testing in case of type II or type III findings).
(2) Within 1,000 flight hours after the effective date of this
AD, but without exceeding the latest of the times specified in
paragraphs (g)(2)(i), (g)(2)(ii), or (g)(2)(iii) of this AD.
(i) 16,000 flight hours since the airplane's first flight.
(ii) 16,000 flight hours since the most recent THSA ballscrew
shaft integrity test was done, as specified in MRBR task 274000-12.
(iii) 16,000 flight hours since the most recent THSA ballscrew
shaft integrity test was done, as specified in Airbus Mandatory
Service Bulletin A330-27-3179, or Airbus Mandatory Service Bulletin
A340-27-4175, as applicable. (These service bulletins specify
testing in case of type II or type III findings).
(h) Replacement
If the result from any test required by paragraph (g) of this AD
is not correct, as specified in the Accomplishment Instructions of
Airbus Mandatory Service Bulletin A330-27-3191, dated June 7, 2012;
or Airbus Mandatory Service Bulletin A340-27-4186, dated June 7,
2012; as applicable: Before further flight, replace the THSA with a
serviceable THSA, in accordance with the Accomplishment Instructions
of Airbus Mandatory Service Bulletin A330-27-3191, dated June 7,
2012; or Airbus Mandatory Service Bulletin A340-27-4186, dated June
7, 2012; as applicable. Replacement of a THSA, as required by this
paragraph, with a THSA having P/N 47147-500 or P/N 47147-700, is not
terminating action for the repetitive tests required by paragraph
(g) of this AD.
(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, Transport Airplane Directorate, 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 Mandatory Continuing Airworthiness Information
(MCAI) European Aviation Safety Agency Airworthiness Directive 2012-
0210, dated October 11, 2012, and the service bulletins specified in
paragraphs (j)(1)(i) and (j)(1)(ii) of this AD, for related
information.
(i) Airbus Mandatory Service Bulletin A330-27-3191, dated June
7, 2012.
(ii) Airbus Mandatory Service Bulletin A340-27-4186, dated June
7, 2012.
(2) For 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. You may review copies of the
referenced service information at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue SW., Renton, WA. For information on
the availability of this material at the FAA, call 425-227-1221.
Issued in Renton, Washington, on April 23, 2013.
Jeffrey E. Duven,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2013-10366 Filed 5-1-13; 8:45 am]
BILLING CODE 4910-13-P
