Airworthiness Directives; Airbus Airplanes

[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]


=======================================================================
-----------------------------------------------------------------------

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.

-----------------------------------------------------------------------

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:
    <bullet> Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
    <bullet> Fax: 202-493-2251.
    <bullet> 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.
    <bullet> 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
----------------------------------------------------------------------------------------------------------------
                                                                                     Cost per      Cost on U.S.
                Action                         Labor cost           Parts cost        product        operators
----------------------------------------------------------------------------------------------------------------
AFM Revision (100 airplanes)..........  1 work-hour x $85 per                 $0             $85          $8,500
                                         hour = $85.
----------------------------------------------------------------------------------------------------------------

    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]
BILLING CODE 4910-13-P

The complete text was extracted from the official GovInfo HTML edition for this publication. Acquired 2026-10-09T02:57:43.535401+00:00. Text extraction preserves the recorded source wording; it does not determine current requirements.

Open the captured official edition

Source SHA-256

8793e946c5e7946903cd5d5e5d19e27030a692b1156fa76edbf52bad590929b9

Text SHA-256

701629fcd256ef6ae6a14cc59fe51356f4ded2dfc8962e9031b54e70d975ef34