
[Federal Register Volume 81, Number 88 (Friday, May 6, 2016)]
[Rules and Regulations]
[Pages 27298-27300]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-10215]


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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; 
Amendment 39-18505; AD 2016-09-07]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

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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 AD was 
prompted by reports of airspeed indication discrepancies while flying 
at high altitudes in inclement weather. This AD requires replacing 
certain pitot probes on the captain, first officer, and standby sides 
with certain new pitot probes. 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.

DATES: This AD is effective June 10, 2016.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of June 10, 
2016.

ADDRESSES: For service information identified in this final rule, 
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: account.airworth-eas@airbus.com; 
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. It is also available on the 
Internet at http://www.regulations.gov by searching for and locating 
Docket No. FAA-2015-0250.

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 AD, the regulatory evaluation, any comments received, and 
other information. The address for the Docket Office (telephone: 800-
647-5527) is Docket Management Facility, U.S. Department of 
Transportation, Docket Operations, M-30, West Building Ground Floor, 
Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590.

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: 

Discussion

    We issued a supplemental notice of proposed rulemaking (SNPRM) 
(``the SNPRM'') to amend 14 CFR part 39 for all Airbus Model A318, 
A319, A320, and A321 series airplanes. The SNPRM published in the 
Federal Register on December 23, 2015 (80 FR 79750). We preceded the 
SNPRM with a notice of proposed rulemaking (NPRM) (``the NPRM'') that 
published in the Federal Register on March 6, 2015 (80 FR 12094). The 
NPRM proposed to require replacing certain pitot probes on the captain, 
first officer, and standby sides with certain new pitot probes. The 
NPRM was prompted by reports of airspeed indication discrepancies while 
flying at high altitudes in inclement weather. The SNPRM proposed to 
revise the NPRM by reducing the proposed compliance time for replacing 
certain pitot probes based on a risk assessment due to additional 
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.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, issued EASA 
Airworthiness Directive 2015-0205, dated October 9, 2015 (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/ad/F-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 (later revised) [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, and cancelling two other DGAC ADs, to require 
replacement of Thales Avionics pitot probes P/N C16195AA and P/N 
C16195BA.
    Since EASA issued AD 2014-0237R1 [http://ad.easa.europa.eu/ad/2014-0237R1] was issued, results of further analyses have determined 
that the compliance time (48 months) of that AD has to be reduced in 
relation to the risk assessment.
    For the reasons described above, this [EASA] AD retains the 
requirements of EASA AD 2014-0237R1, which is superseded, but 
reduces the compliance time.

    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.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We considered the comment received. United Airlines has no 
objection to the SNPRM.

[[Page 27299]]

Conclusion

    We reviewed the available data and determined that air safety and 
the public interest require adopting this AD as proposed except for 
minor editorial changes. We have determined that these minor changes:
     Are consistent with the intent that was proposed in the 
SNPRM for correcting the unsafe condition; and
     Do not add any additional burden upon the public than was 
already proposed in the SNPRM.

Related Service Information Under 1 CFR Part 51

    We reviewed the following Airbus service information:
     Airbus Service Bulletin A320-34-1170, Revision 30, dated 
June 18, 2015.
     Airbus Service Bulletin A320-34-1456, Revision 01, dated 
May 15, 2012.
     Airbus 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. 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.

Costs of Compliance

    We estimate that this AD affects 953 airplanes of U.S. registry.
    We also estimate that it takes about 4 work-hours per product to 
comply with the new basic requirements of this AD. The average labor 
rate is $85 per work-hour. Required parts will cost about $21,930 per 
product. Based on these figures, we estimate the cost of this 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 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 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 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.

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):

2016-09-07 Airbus: Amendment 39-18505. Docket No. FAA-2015-0250; 
Directorate Identifier 2014-NM-216-AD.

(a) Effective Date

    This AD is effective June 10, 2016.

(b) Affected ADs

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

(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 Certain Pitot Probes on the Captain, First Officer, 
and Standby Sides

    Within 24 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 30, dated June 18, 2015. 
Accomplishing the replacement in this paragraph terminates the 
requirements of paragraph (f) of AD 2004-03-33 for that airplane 
only.

(h) Optional Methods of Compliance for Replacement Required by 
Paragraph (g) of This AD

    (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

[[Page 27300]]

effective date of this AD using the service information identified 
in paragraph (i)(1)(i) through (i)(1)(xxvi) 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.
    (xxv) Airbus Service Bulletin A320-34-1170, Revision 28, dated 
September 1, 2014.
    (xxvi) Airbus Service Bulletin A320-34-1170, Revision 29, dated 
February 16, 2015.
    (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 as 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.
    (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: 9-ANM-116-AMOC-REQUESTS@faa.gov. 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.
    (3) Required for Compliance (RC): If any service information 
contains procedures or tests that are identified as RC, those 
procedures and tests must be done to comply with this AD; any 
procedures or tests that are not identified as RC are recommended. 
Those procedures and tests that are not identified as RC may be 
deviated from using accepted methods in accordance with the 
operator's maintenance or inspection program without obtaining 
approval of an AMOC, provided the procedures and tests identified as 
RC can be done and the airplane can be put back in an airworthy 
condition. Any substitutions or changes to procedures or tests 
identified as RC require approval of an AMOC.

(l) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2015-0205, dated October 9, 
2015, 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) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (m)(3) and (m)(4) of this AD.

(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 this AD specifies otherwise.
    (i) Airbus Service Bulletin A320-34-1170, Revision 30, dated 
June 18, 2015.
    (ii) Airbus Service Bulletin A320-34-1456, Revision 01, dated 
May 15, 2012.
    (iii) Airbus Service Bulletin A320-34-1463, Revision 01, dated 
May 15, 2012.
    (3) 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: account.airworth-eas@airbus.com; Internet: 
http://www.airbus.com.
    (4) 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.
    (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 April 20, 2016.
John P. Piccola, Jr.,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-10215 Filed 5-5-16; 8:45 am]
 BILLING CODE 4910-13-P


