[Federal Register Volume 80, Number 218 (Thursday, November 12, 2015)]
[Proposed Rules]
[Pages 69899-69903]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-28559]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-4810; Directorate Identifier 2015-NM-090-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 adopt a new airworthiness directive (AD) for all

[[Page 69900]]

Airbus Model A330-200, -200 Freighter, and -300 series airplanes; and 
all Airbus Model A340-200, -300, -500, and -600 series airplanes. This 
proposed AD was prompted by a report of blockage of Angle of Attack 
(AOA) probes during climb, leading to activation of the Alpha 
Protection (Alpha Prot) while the Mach number increased. This 
activation could cause a continuous nose-down pitch rate that cannot be 
stopped with backward sidestick input, even in the full backward 
position. For certain airplanes, this proposed AD would require 
replacing certain AOA sensors (probes) with certain new AOA sensors. 
For certain other airplanes, this proposed AD would also require 
inspections and functional heat testing of certain AOA sensors for 
discrepancies, and replacement if necessary. We are proposing this AD 
to prevent erroneous AOA information and Alpha Prot activation due to 
blocked AOA probes, which could result in a continuous nose-down 
command and consequent loss of control of the airplane.

DATES: We must receive comments on this proposed AD by December 28, 
2015.

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: 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 [email protected]; Internet http://www.airbus.com. You may view this 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 by searching for and locating Docket No. FAA-2015-
4810; or in person at the Docket Management Facility between 9 a.m. and 
5 p.m., Monday through Friday, except Federal holidays. The AD docket 
contains this 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, WA 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-2015-4810; 
Directorate Identifier 2015-NM-090-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

    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2015-0134, dated July 8, 2015 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for all Airbus Model 
A330-200, -200 Freighter, and -300 series airplanes; and Model A340-
200, -300, -500, and -600 series airplanes. The MCAI states:

    An occurrence was reported where an Airbus A321 aeroplane 
encountered a blockage of two Angle of Attack (AOA) probes during 
climb, leading to activation of the Alpha Protection (Alpha Prot) 
while the Mach number increased. The flight crew managed to regain 
full control and the flight landed uneventfully. It was determined 
that the affected AOA probes are also fitted on A330 and A340 
aeroplanes.
    When Alpha Prot is activated due to blocked AOA probes, the 
flight control laws order a continuous nose down pitch rate that, in 
a worst case scenario, cannot be stopped with backward sidestick 
inputs, even in the full backward position. If the Mach number 
increases during a nose down order, the AOA value of the Alpha Prot 
will continue to decrease. As a result, the flight control laws will 
continue to order a nose down pitch rate, even if the speed is above 
minimum selectable speed, known as VLS.
    This condition, if not corrected, could result in loss of 
control of the aeroplane.
    Investigation results indicated that aeroplanes equipped with 
certain UTC Aerospace (UTAS, formerly known as Goodrich) AOA 
sensors, or equipped with certain SEXTANT/THOMSON AOA sensors, 
appear to have a greater susceptibility to adverse environmental 
conditions than aeroplanes equipped with the latest Thales AOA 
sensor, Part Number (P/N) C16291AB, which was designed to improve 
AOA indication behaviour in heavy rain conditions.
    Having determined that replacement of these AOA sensors is 
necessary to achieve and maintain the required safety level of the 
aeroplane, EASA issued AD 2015-0089, to require modification of the 
aeroplanes by replacement of the affected P/N sensors, and, after 
modification, prohibits (re-) installation of those P/N AOA sensors. 
That [EASA] AD also required repetitive detailed visual inspections 
(DET) and functional heating tests of certain Thales AOA sensors and 
provided an optional terminating action for those inspections.
    Since EASA AD 2015-0089 was issued, based on further analysis 
results, Airbus issued Operators Information Transmission (OIT) Ref. 
999.0017/15 Revision 1, instructing operators to speed up the 
removal from service of UTAS P/N 0861ED2 AOA sensors.
    For the reasons described above, this [EASA] AD retains the 
requirements of EASA AD 2015-0089, which is superseded, but reduces 
the compliance times for aeroplanes with UTAS P/N 0861ED2 AOA 
sensors installed.

    You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-
4810.

Related Service Information Under 1 CFR Part 51

    Airbus has issued the following service information:
     Service Bulletin A330-34-3215, Revision 02, dated March 
29, 2010.
     Service Bulletin A330-34-3228, dated October 7, 2009.
     Service Bulletin A330-34-3315, dated March 26, 2015.
     Service Bulletin A340-34-4215, Revision 02, dated March 
29, 2010.

[[Page 69901]]

     Service Bulletin A340-34-4234, dated October 7, 2009.
     Service Bulletin A340-34-4294, dated March 26, 2015.
     Service Bulletin A340-34-5062, Revision 01, dated March 
29, 2010.
     Service Bulletin A340-34-5070, dated October 9, 2009.
     Service Bulletin A340-34-5105, dated March 26, 2015.
    The service information describes procedures for replacing certain 
pitot probes with certain new pitot probes. The service information 
also describes procedures for inspections and functional heat testing 
of certain pitot probes, and replacement if necessary. This service 
information is reasonably available because the interested parties have 
access to it through their normal course of business or by the means 
identified in the ADDRESSES section of this NPRM.

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 these 
same type designs.

Costs of Compliance

    We estimate that this proposed AD affects 55 airplanes of U.S. 
registry.

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                   Cost on U.S.
              Action                      Labor cost           Parts cost      Cost per product      operators
----------------------------------------------------------------------------------------------------------------
Replacement......................  5 work-hours x $85 per                $0  $425...............         $23,375
                                    hour = $425.
Inspection/test..................  3 work-hours x $85 per                 0  $255 per inspection/         14,025
                                    hour = $255.                              test cycle.
----------------------------------------------------------------------------------------------------------------

    We have received no definitive data that would enable us to provide 
a cost estimate for the on-condition actions specified in this proposed 
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

    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.

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 airworthiness 
directive (AD):

Airbus: Docket No. FAA-2015-4810; Directorate Identifier 2015-NM-
090-AD.

(a) Comments Due Date

    We must receive comments by December 28, 2015.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to the airplanes, certificated in any category, 
identified in paragraphs (c)(1) and (c)(2) of this AD, all 
manufacturer serial numbers.
    (1) Airbus Model A330-201, -202, -203, -223, -223F, -243, -243F, 
-301, -302, -303, -321, -322, -323, -341, -342, and -343 airplanes.
    (2) Airbus Model A340-211, -212, -213, -311, -312, -313, -541, 
and -642 airplanes.

(d) Subject

    Air Transport Association (ATA) of America Code 34, Navigation.

(e) Reason

    This AD was prompted by a report of blockage of two Angle of 
Attack (AOA) probes during climb, leading to activation of the Alpha 
Protection (Alpha Prot) while the Mach number increased. This 
activation could cause a continuous nose-down pitch rate that cannot 
be stopped with backward sidestick input, even in the full backward 
position. We are issuing this AD to prevent erroneous AOA 
information and Alpha Prot activation due to blocked AOA probes, 
which could result in a continuous nose-down command and consequent 
loss of control of the airplane.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Replacement of Certain UTAS AOA Sensors

    For airplanes on which any UTAS AOA sensor having part number 
(P/N) 0861ED or P/N 0861ED2 is installed: At the applicable time 
specified in paragraph (h) of this AD, replace all Captain and First 
Officer AOA sensors (probes) having P/N 0861ED or 0861ED2 with AOA 
sensors having Thales P/N C16291AB, in accordance with the 
Accomplishment Instructions of the applicable service information 
identified in paragraph (g)(1), (g)(2), or (g)(3) of this AD.
    (1) Airbus Service Bulletin A330-34-3315, dated March 26, 2015 
(for Model A330 airplanes).

[[Page 69902]]

    (2) Airbus Service Bulletin A340-34-4294, dated March 26, 2015 
(for Model A340-200 and -300 airplanes).
    (3) Airbus Service Bulletin A340-34-5105, dated March 26, 2015 
(for Model A340-500 and -600 airplanes).

(h) Compliance Times for the Requirements of Paragraph (g) of This AD

    Do the actions required by paragraph (g) of this AD at the 
applicable time specified in paragraph (h)(1) or (h)(2) of this AD.
    (1) For airplanes with AOA sensors having P/N 0861ED: Within 22 
months after the effective date of this AD.
    (2) For airplanes with AOA sensors having P/N 0861ED2: Within 7 
months after the effective date of this AD.

(i) Replacement of Certain SEXTANT/THOMSON AOA Sensors

    For airplanes on which any SEXTANT/THOMSON AOA sensor having P/N 
45150320 is installed: Within 22 months after the effective date of 
this AD, replace all SEXTANT/THOMSON AOA sensors (probes) having P/N 
45150320 with AOA sensors having Thales P/N C16291AB, in accordance 
with the Accomplishment Instructions of the applicable service 
information identified in paragraph (i)(1) or (i)(2) of this AD.
    (1) Airbus Service Bulletin A330-34-3228, dated October 7, 2009 
(for Model A330-200 and -300 airplanes).
    (2) Airbus Service Bulletin A340-34-4234, dated October 7, 2009 
(for Model A340-200 and -300 airplanes).

(j) Repetitive Inspections/Tests of Certain Thales AOA Sensors

    For airplanes on which one or more Thales AOA sensor having P/N 
C16291AA is installed: Before the accumulation of 17,000 total 
flight hours on the AOA sensor since first installation on an 
airplane, or within 6 months after the effective date of this AD, 
whichever occurs later; and thereafter at intervals not to exceed 
3,800 flight hours; do a detailed inspection of the three AOA 
sensors at FINs 3FP1, 3FP2, and 3FP3 for discrepancies (e.g., the 
vane of the sensor does not deice properly), and a functional 
heating test of each AOA sensor having P/N C16291AA, in accordance 
with the Accomplishment Instructions of the applicable service 
information identified in paragraph (j)(1), (j)(2), or (j)(3) of 
this AD.
    (1) Airbus Service Bulletin A330-34-3215, Revision 02, dated 
March 29, 2010 (for Model A330-200 and -300 airplanes).
    (2) Airbus Service Bulletin A340-34-4215, Revision 02, dated 
March 29, 2010 (for Model A340-200 and -300 airplanes).
    (3) Airbus Service Bulletin A340-34-5062, Revision 01, dated 
March 29, 2010 (for Model A340-500 and -600 airplanes).

(k) Corrective Actions

    If any discrepancy is found during any inspection required by 
paragraph (j) of this AD, or if any test is failed during the 
heating test required by paragraph (j) of this AD: Before further 
flight, replace all affected AOA sensors with sensors identified in 
paragraph (k)(1) or (k)(2) of this AD, in accordance with the 
Accomplishment Instructions of the applicable service information 
identified in paragraph (j)(1), (j)(2), or (j)(3) of this AD.
    (1) Replace with AOA sensors having Thales P/N C16291AA, on 
which the inspection and test required by paragraph (j) of this AD 
were passed.
    (2) Replace with AOA sensors having Thales P/N C16291AB.

(l) Airplanes Excluded From Certain Requirements

    (1) The actions specified in paragraphs (g), (i), (j), and (k) 
of this AD are not required, provided that the conditions specified 
in paragraphs (l)(1)(i), (l)(1)(ii), and (l)(1)(iii) of this AD are 
met.
    (i) Airbus Modification 58555 (installation of Thales P/N 
C16291AB AOA sensors) has been embodied in production.
    (ii) Airbus Modification 46921 (installation of UTAS AOA 
sensors) has not been embodied in production.
    (iii) No AOA sensor having SEXTANT/THOMSON P/N 45150320 or UTAS 
P/N 0861ED or P/N 0861ED2 has been installed on the airplane since 
date of issuance of the original airworthiness certificate or date 
of issuance of the original export certificate of airworthiness.
    (2) The actions specified in paragraphs (g) and (i) of this AD 
are not required, provided that all conditions specified in 
paragraphs (l)(2)(i), (l)(2)(ii), and (l)(2)(iii) of this AD are 
met.
    (i) Only AOA sensors with P/Ns approved after the effective date 
of this AD have been installed.
    (ii) The AOA sensor P/N is approved by the Manager, 
International Branch, ANM-116, Transport Airplane Directorate, FAA; 
the European Aviation Safety Agency (EASA); or Airbus's EASA Design 
Organization Approval (DOA).
    (iii) The installation is accomplished in accordance with 
airplane modification instructions approved by the Manager, 
International Branch, ANM-116, Transport Airplane Directorate, FAA; 
the EASA; or Airbus's EASA DOA.

(m) Optional Terminating Modification

    Replacement of all Thales AOA sensors having P/N C16291AA with 
Thales AOA sensors having P/N C16291AB, in accordance with the 
Accomplishment Instructions of the applicable service information 
identified in paragraph (m)(1), (m)(2), or (m)(3) of this AD, 
terminates the repetitive inspections and functional heating tests 
required by paragraph (j) of this AD.
    (1) Airbus Service Bulletin A330-34-3228, dated October 7, 2009 
(for Model A330-200 and -300 airplanes).
    (2) Airbus Service Bulletin A340-34-4234, dated October 7, 2009 
(for Model A340-200 and -300 airplanes).
    (3) Airbus Service Bulletin A340-34-5070, dated October 9, 2009 
(for Model A340-500 and -600 airplanes).

(n) Parts Installation Prohibitions

    (1) For airplanes on which only Thales P/N C16291AB AOA sensors 
are installed as of the effective date of this AD: No person may 
install, on any airplane, a Thales AOA sensor having P/N C16291AA as 
of the effective date of this AD.
    (2) For airplanes on which the modification specified in 
paragraph (m) of this AD has been done: No person may install, on 
any airplane, a Thales AOA sensor having P/N C16291AA after 
accomplishing the specified modification.
    (3) For airplanes on which Thales P/N C16291AA or P/N C16291AB 
AOA sensors are installed as of the effective date of this AD: No 
person may install, on any airplane, a UTAS AOA sensor having P/N 
0861ED or P/N 0861ED2, or a SEXTANT/THOMSON AOA sensor having P/N 
45150320, as of the effective date of this AD.
    (4) For airplanes on which the replacement required by paragraph 
(i) of this AD has been done: No person may install, on any 
airplane, a UTAS AOA sensor having P/N 0861ED or P/N 0861ED2, or a 
SEXTANT/THOMSON AOA sensor having P/N 45150320, after accomplishing 
the replacement.
    (5) For airplanes on which the replacement required by paragraph 
(g) of this AD has been done: No person may install, on any 
airplane, a UTAS AOA sensor having P/N 0861ED or P/N 0861ED2, or a 
SEXTANT/THOMSON AOA sensor having P/N 45150320, after accomplishing 
the replacement, except that a UTAS AOA sensor having P/N 0861ED may 
be installed in the standby position of that airplane.

(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: Vladimir 
Ulyanov, Aerospace Engineer, International Branch, ANM-116, 
Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, 
WA 98057-3356; telephone 425-227-1138; 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) Contacting the Manufacturer: For any requirement in this AD 
to obtain corrective actions from a manufacturer, the action must be 
accomplished using a method approved by the Manager, International 
Branch, ANM-116, Transport Airplane Directorate, FAA; or the EASA; 
or Airbus's EASA DOA. If approved by the DOA, the approval must 
include the DOA-authorized signature.

(p) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2015-0134, dated July 8, 2015, 
for related information. This MCAI may be found in the AD docket on 
the Internet at http://www.regulations.gov by

[[Page 69903]]

searching for and locating Docket No. FAA-2015-4810.
    (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 [email protected]; 
Internet http://www.airbus.com. You may view this 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 October 30, 2015.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-28559 Filed 11-10-15; 8:45 am]
BILLING CODE 4910-13-P