[Federal Register Volume 80, Number 44 (Friday, March 6, 2015)]
[Proposed Rules]
[Pages 12094-12097]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-04495]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-0250; Directorate Identifier 2014-NM-216-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 
Airbus Model A318, A319, A320, and A321 series airplanes. This proposed 
AD was prompted by reports of airspeed indication discrepancies while 
flying at high altitudes in inclement weather. This proposed AD would 
require replacing certain pitot probes on the captain, first officer, 
and standby sides with certain new pitot probes. We are proposing this 
AD to prevent airspeed indication discrepancies during inclement 
weather, which, depending on the prevailing altitude, could lead to 
unknown accumulation of ice crystals and consequent reduced 
controllability of the airplane.

DATES: We must receive comments on this proposed AD by April 20, 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, 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 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-
0250; 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: 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-2015-0250; 
Directorate Identifier 2014-NM-216-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy

[[Page 12095]]

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 2014-0237R1, dated December 5, 2014 (referred 
to after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for all Airbus Model 
A318, A319, A320, and A321 series airplanes. The MCAI states:

    Occurrences have been reported on A320 family aeroplanes of 
airspeed indication discrepancies while flying at high altitudes in 
inclement weather conditions. Investigation results indicated that 
A320 aeroplanes equipped with Thales Avionics Part Number (P/N) 
50620-10 or P/N C16195AA pitot probes appear to have a greater 
susceptibility to adverse environmental conditions that aeroplanes 
equipped with certain other pitot probes.
    Prompted by earlier occurrences, DGAC [Direction 
G[eacute]n[eacute]rale de l'Aviation Civile] France issued [DGAC] AD 
2001-362 [http://ad.easa.europa.eu/blob/easa_ad_2001_362.pdf/AD_2001-362] [which corresponds to paragraph (f) of FAA AD 2004-03-
33, Amendment 39-13477 (69 FR 9936, March 3, 2004)] to require 
replacement of Thales (formerly known as Sextant) P/N 50620-10 pitot 
probes with Thales P/N C16195AA probes.
    Since that [DGAC] AD was issued, Thales pitot probe P/N C15195BA 
was designed, which improved airspeed indication behavior in heavy 
rain conditions, but did not demonstrate the same level of 
robustness to withstand high-altitude ice crystals. Based on these 
findings, EASA have decided to implement replacement of the affected 
Thales [pitot] probes as a precautionary measure to improve the 
safety level of the affected aeroplanes.
    Consequently, EASA issued AD 2014-0237 [http://ad.easa.europa.eu/blob/easa_ad_2014_0237.pdf/AD_2014-0237], 
retaining the requirements of DGAC France AD 2001-362, which was 
superseded, to require replacement of Thales Avionics pitot probes 
P/N C16195AA and P/N C16195BA.
    The following related DGAC France ADs were also cancelled by 
EASA AD 2014-0237, without retaining any of their requirements:

     AD 91-227-021R1 [http://ad.easa.europa.eu/blob/easa_ad_91_227_021R1.pdf/AD_91_227_021R1], that required replacement 
of Titeflex hoses; and
     AD 2002-586R1 [http://ad.easa.europa.eu/blob/easa_ad_2002_586R1.pdf/AD_2002_586R1], that required cleaning of 
Thales P/N C16195AA probes.

    Since EASA issued AD 2014-0237, it was brought to the Agency's 
attention that Airbus modification (mod) 155737 was introduced to 
install Thales probes in production. This affects paragraph (4) of 
the [EASA] AD.
    For the reasons described above, this [EASA] AD is revised to 
amend paragraph (4), making reference to aeroplanes which are post-
mod 25578, but also post-mod 155737, as a result of which they have 
Thales probes 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-
0250.

Related Rulemaking

    On February 4, 2004, we issued AD 2004-03-33, Amendment 39-13477 
(69 FR 9936, March 3, 2004), applicable to certain Airbus Model A300 B2 
and B4 series airplanes; Model A300 B4-600, A300 B4-600R, and A300 F4-
600R series airplanes; Model A310 series Airplanes; Model A319, A320, 
and A321 series airplanes; Model A330-301, -321, -322, -341, and -342 
airplanes; and Model A340 series airplanes. That AD requires, among 
other actions, replacement of certain pitot probes with certain new 
pitot probes. That AD was issued to prevent loss or fluctuation of 
indicated airspeed, which could result in misleading information being 
provided to the flightcrew.

Related Service Information Under 1 CFR Part 51

    Airbus has issued Service Bulletin A320-34-1170, Revision 28, dated 
September 1, 2014; Service Bulletin A320-34-1456, Revision 01, dated 
May 15, 2012; and Service Bulletin A320-34-1463, Revision 01, dated May 
15, 2012. The service information describes procedures for replacing 
certain Thales Avionics pitot probes on the captain, first officer, and 
standby sides with certain other Goodrich pitot probes.
    The actions described in this service information are intended to 
correct the unsafe condition identified in the MCAI. This service 
information is reasonably available; see ADDRESSES for ways to access 
this service information.

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.

Difference Between This Proposed AD and the MCAI or Service Information

    The EASA MCAI specifies that installation of a pitot probe approved 
after the effective date of the EASA AD, and compliant with the ``new 
EASA icing requirements,'' is equal to compliance with the requirements 
in paragraph (h) of this proposed AD, provided the part is approved by 
EASA or Airbus's EASA Design Organization Approval (DOA). However, this 
proposed AD does not include that requirement because EASA regulations 
do not apply to airplanes type certificated for operation in the United 
States under the provisions of section 21.29 of the Federal Aviation 
Regulations (14 CFR 21.29).
    Paragraph (1) of the MCAI requires replacement of Thales part 
number (P/N) 50620-10 pitot probes with Thales P/N C16195AA pitot 
probes. However, that action is not included in this proposed AD. 
Paragraph (f) of AD 2004-03-33, Amendment 39-13477 (69 FR 9936, March 
3, 2004), requires that action.

Costs of Compliance

    We estimate that this proposed AD affects 953 airplanes of U.S. 
registry.
    We also estimate that it would take about 4 work-hours per product 
to comply with the basic requirements of this proposed AD. The average 
labor rate is $85 per work-hour. Required parts would cost about 
$21,930 per product. Based on these figures, we estimate the cost of 
this proposed AD on U.S. operators to be $21,223,310, or $22,270 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

[[Page 12096]]

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-2015-0250; Directorate Identifier 2014-NM-
216-AD.

(a) Comments Due Date

    We must receive comments by April 20, 2015.

(b) Affected ADs

    This AD affects AD 2004-03-33, Amendment 39-13477 (69 FR 9936, 
March 3, 2004).

(c) Applicability

    This AD applies to the airplanes identified in paragraphs 
(c)(1), (c)(2), (c)(3), and (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 A320-211, -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 reports of airspeed indication 
discrepancies while flying at high altitudes in inclement weather. 
We are issuing this AD to prevent airspeed indication discrepancies 
during inclement weather, which, depending on the prevailing 
altitude, could lead to unknown accumulation of ice crystals and 
consequent reduced controllability of the airplane.

(f) Compliance

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

(g) Replacement of Pitot Probes

    Within 48 months after the effective date of this AD: Replace 
any Thales pitot probe having part number (P/N) C16195AA or P/N 
C16195BA, with a Goodrich pitot probe having P/N 0851HL, in 
accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A320-34-1170, Revision 28, dated September 1, 2014. 
Accomplishing the replacement in this paragraph terminates the 
requirements of paragraph (f) of AD 2004-03-33, Amendment 39-13477 
(69 FR 9936, March 3, 2004), for that airplane only.

(h) Methods of Compliance for Replacement

    (1) Replacement of the pitot probes in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A320-34-1456, 
Revision 01, dated May 15, 2012 (pitot probes on the captain and 
standby sides); and Airbus Service Bulletin A320-34-1463, Revision 
01, dated May 15, 2012 (pitot probes on the first officer side); is 
an acceptable method of compliance with the requirements of 
paragraph (g) of this AD.
    (2) Airplanes on which Airbus Modification 25578 was embodied in 
production, except for post-modification 25578 airplanes on which 
Airbus Modification 155737 (installation of Thales pitot probes) was 
also embodied in production, are compliant with the requirements of 
paragraph (g) of this AD, provided it can be conclusively determined 
that no Thales pitot probe having P/N C16195AA, P/N C16195BA, or P/N 
50620-10 has been installed since the date of issuance of the 
original certificate of airworthiness or the date of issuance of the 
original export certificate of airworthiness. Post-modification 
25578 airplanes on which Airbus Modification 155737 (installation of 
Thales pitot probes) was also embodied in production must be in 
compliance with the requirements of paragraph (g) of this AD.

(i) Credit for Previous Actions

    (1) This paragraph provides credit for the actions required by 
paragraph (g) of this AD, if those actions were performed before the 
effective date of this AD using the service information identified 
in paragraph (i)(1)(i) through (i)(1)(xxiv) of this AD. This service 
information is not incorporated by reference in this AD.
    (i) Airbus Service Bulletin A320-34-1170, Revision 04, dated May 
24, 2000.
    (ii) Airbus Service Bulletin A320-34-1170, Revision 05, dated 
September 11, 2000.
    (iii) Airbus Service Bulletin A320-34-1170, Revision 06, dated 
October 18, 2001.
    (iv) Airbus Service Bulletin A320-34-1170, Revision 07, dated 
December 4, 2001.
    (v) Airbus Service Bulletin A320-34-1170, Revision 08, dated 
January 15, 2003.
    (vi) Airbus Service Bulletin A320-34-1170, Revision 09, dated 
February 17, 2003.
    (vii) Airbus Service Bulletin A320-34-1170, Revision 10, dated 
November 21, 2003.
    (viii) Airbus Service Bulletin A320-34-1170, Revision 11, dated 
August 18, 2004.
    (ix) Airbus Service Bulletin A320-34-1170, Revision 12, dated 
December 2, 2004.
    (x) Airbus Service Bulletin A320-34-1170, Revision 13, dated 
January 18, 2005.
    (xi) Airbus Service Bulletin A320-34-1170, Revision 14, dated 
April 21, 2005.
    (xii) Airbus Service Bulletin A320-34-1170, Revision 15, dated 
July 19, 2005.
    (xiii) Airbus Service Bulletin A320-34-1170, Revision 16, dated 
November 23, 2006.
    (xiv) Airbus Service Bulletin A320-34-1170, Revision 17, dated 
February 14, 2007.
    (xv) Airbus Service Bulletin A320-34-1170, Revision 18, dated 
October 9, 2009.
    (xvi) Airbus Service Bulletin A320-34-1170, Revision 19, dated 
November 9, 2009.
    (xvii) Airbus Service Bulletin A320-34-1170, Revision 20, dated 
December 1, 2010.
    (xviii) Airbus Service Bulletin A320-34-1170, Revision 21, dated 
March 24, 2011.
    (xix) Airbus Service Bulletin A320-34-1170, Revision 22, dated 
July 19, 2011.
    (xx) Airbus Service Bulletin A320-34-1170, Revision 23, dated 
February 3, 2012.
    (xxi) Airbus Service Bulletin A320-34-1170, Revision 24, dated 
April 12, 2012.
    (xxii) Airbus Service Bulletin A320-34-1170, Revision 25, dated 
September 4, 2012.
    (xxiii) Airbus Service Bulletin A320-34-1170, Revision 26, dated 
September 16, 2013.
    (xxiv) Airbus Service Bulletin A320-34-1170, Revision 27, dated 
March 18, 2014.
    (2) This paragraph provides credit for the replacement of pitot 
probes on the captain and standby sides specified in paragraph 
(h)(1) of this AD, if the replacement was performed before the 
effective date of this AD using Airbus Service Bulletin A320-34-
1456, dated December 2, 2009, which is not incorporated by reference 
in this AD.
    (3) This paragraph provides credit for the replacement of pitot 
probes on the first officer side specified in paragraph (h)(1) of 
this AD, if those actions were performed before the effective date 
of this AD using Airbus Service Bulletin A320-34-1463, dated March 
9, 2010, which is not incorporated by reference in this AD.

(j) Parts Installation Limitations

    (1) At the applicable time specified in paragraph (j)(1)(i) or 
(j)(1)(ii) of this AD: No person may install on any airplane a 
Thales pitot probe having P/N C16195AA or P/N C16195BA.

[[Page 12097]]

    (i) For airplanes with a Thales pitot probe having P/N C16195AA 
or P/N C16195BA installed: After accomplishing the replacement 
required by paragraph (g) of this AD.
    (ii) For airplanes without a Thales pitot probe having P/N 
C16195AA or P/N C16195BA installed: As of the effective date of this 
AD.
    (2) As of the effective date of this AD, no person may install 
on any airplane a Thales pitot probe having part number P/N 50620-
10.

(k) 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) 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 
European Aviation Safety Agency (EASA); or Airbus's EASA Design 
Organization Approval (DOA). If approved by the DOA, the approval 
must include the DOA-authorized signature.

(l) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2014-0237R1, dated December 5, 
2014, for related information. This MCAI may be found in the AD 
docket on the Internet at http://www.regulations.gov by searching 
for and locating Docket No. FAA-2015-0250.
    (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 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 February 19, 2015.
John P. Piccola, Jr.,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-04495 Filed 3-5-15; 8:45 am]
 BILLING CODE 4910-13-P