[Federal Register Volume 78, Number 85 (Thursday, May 2, 2013)]
[Proposed Rules]
[Pages 25666-25669]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2013-10361]
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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
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: We propose to supersede an existing airworthiness directive
(AD) 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 http://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 [email protected]; Internet http://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 http://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
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be available in the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone (425) 227-1405;
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-2013-0360;
Directorate Identifier 2013-NM-033-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 http://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
On December 27, 2012, we issued AD 2012-26-51, Amendment 39-17312
(78 FR 1723, January 9, 2013). That AD required actions intended to
address an unsafe condition on all Airbus Model A318, A319, A320, and
A321 series airplanes.
Since we issued AD 2012-26-51, Amendment 39-17312 (78 FR 1723,
January 9, 2013), we have determined that the replacement of the AoA
sensor conic plates with flat plates is necessary to address the
identified unsafe condition. The European Aviation Safety Agency
(EASA), which is the Technical Agent for the Member States of the
European Community, has issued EASA Airworthiness Directive 2013-0022,
dated February 1, 2013 (referred to after this as the Mandatory
Continuing Airworthiness Information, or ``the MCAI''), to correct an
unsafe condition for the specified products. The MCAI states:
Recently, an Airbus A330 aeroplane equipped with Angle of Attack
(AoA) sensors with conic plates installed, experienced blockage of
all sensors during climb, leading to autopilot disconnection and
activation of the alpha protection (Alpha Prot) when Mach number was
increased.
Based on the results of the subsequent analysis, it is suspected
that these conic plates may have contributed to the event.
Investigations are on-going to determine what caused the blockage of
these AoA sensors.
Blockage of two or three AoA sensors at the same angle may cause
the Alpha Prot of the normal law to activate. Under normal flight
conditions (in normal law), if the Alpha Prot activates and Mach
number increases, the flight control laws order a pitch down of the
aeroplane that the flight crew may be unable to counteract with a
side stick deflection, even in the full backward position.
This condition, if not corrected, could result in reduced
control of the aeroplane.
AoA conic plates of similar design are also installed on A320
family aeroplanes, and installation of these AoA sensor conic plates
was required by EASA AD 2012-0236, making reference to Airbus
Service Bulletin (SB) A320-34-1521 for in-service modification.
That requirement was deleted by EASA AD 2012-0236R1.
To address this potential unsafe condition on A320 family
aeroplanes, Airbus developed an ``AOA Blocked'' emergency procedure,
published as a temporary revision (TR) of the Airplane Flight Manual
(AFM), to ensure that flight crews, in case of AoA sensors blockage,
apply the applicable emergency procedure.
Consequently, EASA issued Emergency AD 2012-0264-E [which
corresponds to FAA AD 2012-26-51, Amendment 39-17312 (78 FR 1723,
January 9, 2013)] to require amendment of the AFM by incorporating
the Airbus TR.
Since that [EASA] AD was issued, Airbus published approved
instructions to re-install AoA sensor flat plates on A320 family
aeroplanes.
For the reasons described above, this [EASA] AD retains the
requirements of EASA AD 2012-0264-E which is superseded, and
requires installation of AoA sensor flat plates, after which the AFM
operational procedure can be removed.
You may obtain further information by examining the MCAI in the AD
docket.
In AD 2012-26-51, Amendment 39-17312 (78 FR 1723, January 9, 2013),
we determined that the AFM operational procedure specified in Airbus
A318/A319/A320/A321 Temporary Revision TR286, Issue 1.0, dated December
17, 2012, mitigates risks associated with installation of conic plates.
This proposed AD would require installation of flat plates to address
the identified unsafe condition. After analysis of the safety benefit
of the AFM operational procedure, we determined that the previously
mandated AFM operational procedure must be removed after replacement of
the conic plates with flat plates.
Paragraph (h) of AD 2012-26-51, Amendment 39-17312 (78 FR 1723,
January 9, 2013), only specifies that Airbus A318/A319/A320/A321
Temporary Revision TR286, Issue 1.0, dated December 17, 2012, may be
removed after accomplishing the modification (installation of flat
plates). Therefore, we have revised paragraph (h) of this proposed AD
to require that after the modification for an airplane has been done,
Airbus A318/A319/A320/A321 Temporary Revision TR286, Issue 1.0, dated
December 17, 2012, must be removed before further flight. For airplanes
on which the modification has already been done, we have allowed a
compliance time of ``within 5 days after the effective date of this
AD'' for accomplishing the removal.
Relevant Service Information
Airbus has issued Mandatory Service Bulletin A320-34-1564,
including Appendix 01, dated January 25, 2013. The actions described in
this service information are intended to correct the unsafe condition
identified in the MCAI.
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 100 products of U.S. registry.
The actions that are required by AD 2012-26-51, Amendment 39-17312
(78 FR 1723, January 9, 2013), and retained in this proposed AD take
about 1 work-hour per product, at an average labor rate of $85 per work
hour. Based on these figures, the estimated cost of the currently
required actions is $85 per product.
We estimate that it would take about 7 work-hours per product to
comply with the new basic requirements of this proposed AD. The average
labor rate is $85 per work-hour. We have received no definitive data
that would enable us to provide part cost estimates. Where the service
information lists required parts costs that are covered under warranty,
we have assumed that there will be no charge for these parts. As we do
not control warranty coverage for affected parties, some parties may
incur costs higher than estimated here. Based on these figures, we
estimate the cost of the
[[Page 25668]]
proposed AD on U.S. operators to be $59,500, or $595 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 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 removing airworthiness directive (AD)
2012-26-51, Amendment 39-17312 (78 FR 1723, January 9, 2013), and
adding the following new AD:
Airbus: Docket No. FAA-2013-0360; Directorate Identifier 2013-NM-
033-AD.
(a) Comments Due Date
We must receive comments by June 17, 2013.
(b) Affected ADs
This AD supersedes AD 2012-26-51, Amendment 39-17312 (78 FR
1723, January 9, 2013).
(c) Applicability
This AD applies to the Airbus airplanes listed in paragraphs
(c)(1) through (c)(4) of this AD, certificated in any category, all
manufacturer serial numbers.
(1) Airbus Model A318-111, -112, -121, and -122 airplanes.
(2) Airbus Model A319-111, -112, -113, -114, -115, -131, -132,
and -133 airplanes.
(3) Airbus Model A320-111, -211, -212, -214, -231, -232, and -
233 airplanes.
(4) Airbus Model A321-111, -112, -131, -211, -212, -213, -231,
and -232 airplanes.
(d) Subject
Air Transport Association (ATA) of America Code 34, Navigation.
(e) Reason
This AD was prompted by a determination that replacement of
angle of attack (AoA) sensor conic plates is necessary to address
the identified unsafe condition. We are issuing this AD to prevent
reduced 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) Retained Airplane Flight Manual Revision With New Exception
This paragraph restates the requirements of paragraph (g) of AD
2012-26-51, Amendment 39-17312 (78 FR 1723, January 9, 2013), with a
new exception. Except as specified in paragraph (k) of this AD, for
airplanes on which an AoA sensor conic plate is installed in
production by Airbus modification 153213 or 153214, or in-service as
specified in Airbus Mandatory Service Bulletin A320-34-1521, dated
May 7, 2012; or Revision 01, dated September 12, 2012: Within 5 days
after January 24, 2013 (the effective date of AD 2012-26-51), revise
the Emergency Procedures of the Airbus A318/A319/A320/A321 Airplane
Flight Manual (AFM) by inserting Airbus A318/A319/A320/A321
Temporary Revision (TR) TR286, Issue 1.0, dated December 17, 2012,
to advise the flightcrew of emergency procedures for addressing AoA
sensor blockage. When the information in Airbus A318/A319/A320/A321
Temporary Revision TR286, Issue 1.0, dated December 17, 2012, is
included in the general revisions of the AFM, the general revisions
may be inserted in the AFM, and the TR may be removed.
Accomplishment of the new flat plate installation required by
paragraph (j) of this AD terminates the actions required by this
paragraph; and after the installation of new flat plates has been
done, Airbus A318/A319/A320/A321 Temporary Revision TR286, Issue
1.0, dated December 17, 2012, must be removed from the AFM before
further flight.
(h) Retained Optional Terminating Action With Revised TR Removal
Requirement
This paragraph restates the requirements of paragraph (h) of AD
2012-26-51, Amendment 39-17312 (78 FR 1723, January 9, 2013), with a
revised TR removal requirement. Modification of an airplane by
replacing AoA sensor conic plates with AoA sensor flat plates, in
accordance with a method approved by the Manager, International
Branch, ANM-116, Transport Airplane Directorate, FAA, constitutes
terminating action for the AFM revision required by paragraph (g) of
this AD; and after the modification has been done, Airbus A318/A319/
A320/A321 Temporary Revision TR286, Issue 1.0, dated December 17,
2012, must be removed from the AFM before further flight, except for
airplanes on which the modification has been done before the
effective date of this AD. For airplanes on which the modification
has been done before the effective date of this AD, Airbus A318/
A319/A320/A321 Temporary Revision TR286, Issue 1.0, dated December
17, 2012, must be removed from the AFM within 5 days after the
effective date of this AD. Accomplishment of the actions required by
paragraphs (j) and (l) of this AD terminate the actions specified in
this paragraph.
(i) Retained Parts Installation Prohibition
This paragraph restates the requirements of paragraph (i) of AD
2012-26-51, Amendment 39-17312 (78 FR 1723, January 9, 2013). As of
January 24, 2013 (the effective date of AD 2012-26-51), no person
may install an AoA sensor conic plate in service using Airbus
Mandatory Service Bulletin A320-34-1521, dated May 7, 2012; or
Revision 01, dated September 12, 2012; on any airplane.
(j) New Flat Plate Installation
Within 5 months after the effective date of this AD, remove all
AoA sensor conic plates having part number (P/N) F3411060200000 or
P/N F3411060900000 and install AoA sensor flat plates having part
numbers specified in paragraph (j)(1) or (j)(2) of this AD, except
as specified in paragraph (k) of this AD. Install the AoA sensor
plates in accordance with the applicable method specified in
paragraph (j)(1) or (j)(2) of this AD. Accomplishment of the AoA
sensor flat plate installation terminates the AFM revision required
by paragraph (g) of this AD; and after accomplishing the
installation, the
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actions specified in paragraph (l) of this AD must be done.
(1) Install P/N D3411013520200 in accordance with the
Accomplishment Instructions of Airbus Mandatory Service Bulletin
A320-34-1564, including Appendix 01, dated January 25, 2013.
(2) Install P/N D3411007620000 or P/N D3411013520000, in
accordance with a method approved by either the Manager,
International Branch, ANM-116, Transport Airplane Directorate, FAA;
or the European Aviation Safety Agency (EASA) (or its delegated
agent).
(k) New Exception to Paragraphs (g) and (j) of This AD
An airplane on which Airbus modification 154863 (installation of
AOA sensor flat plate) and modification 154864 (coating protection)
have been embodied in production is not affected by the requirements
of paragraph (g) or (j) of this AD, provided that, since first
flight, no AoA sensor conic plate having P/N F3411060200000 or P/N
F3411060900000 has been installed on that airplane.
(l) New Removal of AFM Revision
After modification of an airplane as required by paragraph (j)
of this AD, Airbus A318/A319/A320/A321 Temporary Revision TR286,
Issue 1.0, dated December 17, 2012, that was inserted into the
Airbus A318/A319/A320/A321 AFM as required by paragraph (g) of this
AD is no longer required and must be removed from the AFM of that
airplane before further flight.
(m) New Parts Installation Prohibition
(1) As of the effective date of this AD, for any airplane that
has AoA sensor flat plates installed: As of the effective date of
this AD, do not install any AoA sensor conic plate having P/N
F3411060200000 or P/N F3411060900000, and do not use any AoA
protection cover having P/N 98D34203003000.
(2) For any airplane that has AoA sensor conic plates installed:
As of the effective date of this AD, after modification of the
airplane as required by paragraph (j) of this AD, do not install any
AoA sensor conic plate having P/N F3411060200000 or P/N
F3411060900000, and do not use any AoA protection cover having P/N
98D34203003000.
(n) Special Flight Permits
Special flight permits may be issued in accordance with
Sec. Sec. 21.197 and 21.199 of the Federal Aviation Regulations (14
CFR 21.197 and 21.199) to operate the airplane to a location where
the airplane can be modified (if the operator elects to do so),
provided Airbus A318/A319/A320/A321 Temporary Revision TR286, Issue
1.0, dated December 17, 2012, has been inserted into the Emergency
Procedures of the Airbus A318/A319/A320/A321 AFM.
(o) 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: Sanjay
Ralhan, Aerospace Engineer, International Branch, ANM-116, Transport
Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-
3356; telephone (425) 227-1405; fax (425) 227-1149. Information may
be emailed to: [email protected]. 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.
(p) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA Airworthiness Directive 2013-0022, dated February 1,
2013; Airbus Mandatory Service Bulletin A320-34-1564, including
Appendix 01, dated January 25, 2013; and Airbus A318/A319/A320/A321
Temporary Revision TR286, Issue 1.0, dated December 17, 2012.
(2) For service information identified in this 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 [email protected]; Internet http://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. 2013-10361 Filed 5-1-13; 8:45 am]
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