[Federal Register Volume 78, Number 6 (Wednesday, January 9, 2013)]
[Rules and Regulations]
[Pages 1723-1726]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2012-31683]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2012-1314; Directorate Identifier 2012-NM-227-AD;
Amendment 39-17312; AD 2012-26-51]
RIN 2120-AA64
Airworthiness Directives; Airbus Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule; request for comments.
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SUMMARY: We are adopting a new airworthiness directive (AD) for all
Airbus Model A318, A319, A320, and A321 series airplanes. This
emergency AD was sent previously to all known U.S. owners and operators
of these airplanes. This AD requires revising the airplane flight
manual (AFM) to advise the flight crew of emergency procedures for
addressing Angle of Attack (AoA) sensor blockage. This AD also provides
for optional terminating action for the AFM revision, which involves
replacing AoA sensor conic plates with AoA sensor flat plates. This AD
was prompted by a report that an airplane equipped with AoA sensors
installed with conic plates recently experienced blockage of all
sensors during climb, leading to autopilot disconnection and activation
of the alpha protection (Alpha Prot) when Mach number was increased. We
are issuing this AD to prevent reduced control of the airplane.
DATES: This AD is effective January 24, 2013 to all persons except
those persons
[[Page 1724]]
to whom it was made immediately effective by Emergency AD 2012-26-51,
issued on December 17, 2012, which contained the requirements of this
amendment.
The Director of the Federal Register approved the incorporation by
reference of a certain publication identified in the AD as of January
24, 2013.
We must receive comments on this AD by February 25, 2013.
ADDRESSES: You may send comments, using the procedures found in 14 CFR
11.43 and 11.45, 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: Deliver to Mail address above between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
For service information identified in this AD, contact Airbus,
Airworthiness Office--EAS, 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.
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 AD, the regulatory evaluation,
any comments received, and other information. The street address for
the Docket Operations Office (phone: 800-647-5527) is in the ADDRESSES
section. Comments will 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; phone: 425-227-1405; fax:
425-227-1149; email: [email protected].
SUPPLEMENTARY INFORMATION:
Discussion
On December 17, 2012, we issued Emergency AD 2012-26-51, which
requires revising the airplane flight manual (AFM) to advise the flight
crew of emergency procedures for addressing AoA sensor blockage. This
emergency AD also provides for optional terminating action for the AFM
revision, which involves replacing AoA sensor conic plates with AoA
sensor flat plates. This emergency AD was sent previously to all known
U.S. owners and operators of these airplanes.
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Community, has issued EASA
Emergency Airworthiness Directive 2012-0264-E, dated December 17, 2012
(referred to after this as the Mandatory Continuing Airworthiness
Information or ``the MCAI''), to correct an unsafe condition for the
specified products.
EASA has advised that an Airbus Model A330 airplane equipped with
AoA sensors installed with conic plates recently 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 subsequent analysis, it is suspected
that these conic plates may have contributed to the event.
Investigations are ongoing 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 airplane
that the flight crew might not be able 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 airplane.
EASA also issued Emergency AD 2012-0258-E, dated December 4, 2012,
for Airbus Model A330 and A340 airplanes to require an amendment of the
AFM to ensure that flight crews apply the applicable emergency
procedure.
AoA sensor conic plates of similar design are also installed on
Model A320 series airplanes. Installation of these AoA sensor conic
plates was required for Model A318, A319, A320, and A321 series
airplanes by EASA AD 2012-0236, dated November 9, 2012 (corrected
November 12, 2012). Subsequently, EASA issued AD 2012-0236R1, dated
December 17, 2012, to remove the requirement to install AoA sensor
conic plates.
Relevant Service Information
We reviewed Airbus A318/A319/A320/A321 Temporary Revision TR286,
Issue 1.0, dated December 17, 2012, to the Airbus A318/A319/A320/A321
Airplane Flight Manual (AFM). The temporary revision provides
information to advise the flight crew of emergency procedures for
addressing AoA sensor blockage.
FAA's Determination
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 referenced
above. We are issuing this AD because we evaluated all pertinent
information and determined the unsafe condition exists and is likely to
exist or develop on other products of the same type design.
AD Requirements
This AD requires revising the Emergency Procedures section of the
Airbus A318/A319/A320/A321 AFM to incorporate Airbus A318/A319/A320/
A321 Temporary Revision TR286, Issue 1.0, dated December 17, 2012, to
advise the flight crew of emergency procedures for addressing AOA
sensor blockage. This AD also provides for optional terminating action
for the AFM revision, which involves replacing AoA sensor conic plates
with AoA sensor flat plates.
Interim Action
We consider this AD to be an interim measure to mitigate risks
associated with the installation of AoA sensor conic plates. Further AD
action might follow.
Clarification of Service Information References
In the ``Relevant Service Information'' section of this AD and
paragraph (h) of this AD, we have clarified that Airbus A318/A319/A320/
A321 Temporary Revision TR286, Issue 1.0, dated December 17, 2012, is
to the Airbus A318/A319/A320/A321 Airplane Flight Manual (AFM). We had
not specified ``to the Airbus A318/A319/A320/A321 Airplane Flight
Manual (AFM)'' in those locations in the emergency AD. This change does
not affect AD compliance.
We have also included Airbus A318/A319/A320/A321 Temporary Revision
TR286, Issue 1.0, dated December 17, 2012, to the Airbus A318/A319/
A320/A321 AFM in paragraph (l)(2) of this AD, which specifies
references for related information. We had not listed the temporary
revision in the corresponding paragraph of the emergency AD (paragraph
(l)(3) of the emergency AD). This change does not affect AD compliance.
[[Page 1725]]
We incorrectly referred to a service bulletin number as ``Airbus
Mandatory Service Bulletin A320-32-1521, dated * * * '' in the
``Differences Between the AD and the MCAI or Service Information''
section in the preamble of the emergency AD. The correct service
bulletin reference is ``Airbus Mandatory Service Bulletin A320-34-1521,
dated * * * '' That reference is correct in the regulatory section of
the emergency AD. We have revised the ``Differences Between the AD and
the MCAI or Service Information'' section of this AD accordingly. This
change does not affect AD compliance.
Differences Between the AD and the MCAI or Service Information
The applicability of EASA Emergency AD 2012-0264-E, dated December
17, 2012, is limited to airplanes having an AoA sensor conic plate
installed either in production or in service. However, this emergency
AD applies to all of the affected airplane models; and this AD
prohibits installation of an AoA sensor conic plate in service as
specified in Airbus Mandatory Service Bulletin A320-34-1521, dated May
7, 2012; and Revision 01, dated September 12, 2012; on any airplane as
of the effective date of this AD.
FAA's Determination of the Effective Date
An unsafe condition exists that requires the immediate adoption of
this AD. The FAA has found that the risk to the flying public justifies
waiving notice and comment prior to adoption of this rule because we
received a report indicating that an airplane equipped with AoA sensors
installed with conic plates recently experienced blockage of all
sensors during climb, leading to autopilot disconnection and activation
of the alpha protection (Alpha Prot) when Mach number was increased.
This condition could result in reduced control of the airplane.
Therefore, we find that notice and opportunity for prior public comment
are impracticable and that good cause exists for making this amendment
effective in less than 30 days.
Comments Invited
This AD is a final rule that involves requirements affecting flight
safety and was not preceded by notice and an opportunity for public
comment. However, we invite you to send any written data, views, or
arguments about this AD. Send your comments to an address listed under
the ADDRESSES section. Include the docket number FAA-2012-1314 and
Directorate Identifier 2012-NM-227-AD at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this AD. We will
consider all comments received by the closing date and may amend this
AD because of 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 AD.
Costs of Compliance
We estimate that this AD affects 793 airplanes of U.S. registry.
(We have confirmed that at least 65 airplanes have the affected
configuration; however, there could be as many as 100.)
We estimate the following costs to comply with this AD:
Estimated Costs
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Cost per Cost on U.S.
Action Labor cost Parts cost product operators
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AFM Revision (100 airplanes).......... 1 work-hour x $85 per $0 $85 $8,500
hour = $85.
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We have received no definitive data that would enable us to provide
cost estimates for the optional terminating action specified in this
AD.
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
This AD will not have federalism implications under Executive Order
13132. This AD will not have a substantial direct effect on the States,
on the relationship between the national government and the States, or
on the distribution of power and responsibilities among the various
levels of government.
For the reasons discussed above, I certify that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979),
(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.
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]
0
2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive (AD):
2012-26-51 Airbus: Amendment 39-17312; Docket No. FAA-2012-1314;
Directorate Identifier 2012-NM-227-AD.
(a) Effective Date
This AD is effective January 24, 2013 to all persons except
those persons to whom it was made immediately effective by Emergency
AD 2012-26-51, issued on December 17, 2012, which contained the
requirements of this amendment.
[[Page 1726]]
(b) Affected ADs
None.
(c) Applicability
This AD applies to Airbus Model A318-111, -112, -121, and -122
airplanes; Model A319-111, -112, -113, -114, -115, -131, -132, and -
133 airplanes; Model A320-111, -211, -212, -214, -231, -232, and -
233 airplanes; and Model A321-111, -112, -131, -211, -212, -213, -
231, and -232 airplanes; certificated in any category, all serial
numbers.
(d) Subject
Joint Aircraft System Component (JASC)/Air Transport Association
(ATA) of America Code 34: Navigation.
(e) Unsafe Condition
This AD was prompted by a report indicating that an airplane
equipped with Angle of Attack (AoA) sensors (with conic plates
installed) recently experienced blockage of all sensors during
climb, leading to autopilot disconnection and activation of the
alpha protection (Alpha Prot) when Mach number was increased. We are
issuing this AD to prevent reduced control of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Airplane Flight Manual Revision
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 the effective date of this AD, revise the Emergency Procedures
of the Airbus A318/A319/A320/A321 Airplane Flight Manual (AFM) by
inserting Airbus A318/A319/A320/A321 Temporary Revision TR286, Issue
1.0, dated December 17, 2012, to advise the flight crew 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
temporary revision may be removed.
(h) Optional Terminating Action
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, to the Airbus
A318/A319/A320/A321 AFM, may be removed from the AFM.
(i) Parts Installation Prohibition
As of the effective date of this AD, 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) Special Flight Permit
Special flight permits, as described in Section 21.197 and
Section 21.199 of the Federal Aviation Regulations (14 CFR 21.197
and 21.199), are not allowed.
(k) Alternative Methods of Compliance (AMOCs)
(1) 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 manager of the International Branch, send it to the
attention of the person identified in the Related Information
section of this AD. Information may be emailed to: [email protected].
(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.
(l) Related Information
(1) For further information about this AD, contact: Sanjay
Ralhan, Aerospace Engineer, International Branch, ANM-116, Transport
Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-
3356; phone: 425-227-1405; fax: 425-227-1149; email:
[email protected].
(2) Refer to Mandatory Continuing Airworthiness Information
European Aviation Safety Agency Emergency Airworthiness Directive
2012-0264-E, dated December 17, 2012; and Airbus A318/A319/A320/A321
Temporary Revision TR286, Issue 1.0, dated December 17, 2012, to the
Airbus A318/A319/A320/A321 AFM; for related information.
(m) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless the AD specifies otherwise.
(i) Airbus A318/A319/A320/A321 Temporary Revision TR286, Issue
1.0, dated December 17, 2012, to the Airbus A318/A319/A320/A321
Airplane Flight Manual.
(ii) Reserved.
(3) For Airbus service information identified in this AD,
contact Airbus, Airworthiness Office--EAS, 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.
(4) You may view this 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.
(5) You may view this service information that is incorporated
by reference at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Renton, Washington, on December 27, 2012.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2012-31683 Filed 1-8-13; 8:45 am]
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