Document ID: FAA-2012-0150-0012
Agency: faa
Document Type: Rule
Title: Airworthiness Directives: Airbus Airplanes
Posted Date: 2013-03-29T04:00Z

[Federal Register Volume 78, Number 61 (Friday, March 29, 2013)]
[Rules and Regulations]
[Pages 19085-19088]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-06172]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2012-0150; Directorate Identifier 2011-NM-234-AD; 
Amendment 39-17399; AD 2013-06-03]
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 oil residue between the stator and the rotor 
parts of the position resolvers of the angle of attack (AOA) vane, 
which was a result of incorrect removal of the machining oil during the 
manufacturing process of the AOA resolvers. This AD requires an 
inspection to determine if certain AOA probes are installed, and 
replacement of any affected AOA probe. We are issuing this AD to 
prevent erroneous AOA information and consequent delayed or non-
activation of the AOA protection systems, which during flight at a high 
AOA, could result in reduced control of the airplane.

DATES: This AD becomes effective May 3, 2013.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of May 3, 2013.

ADDRESSES: You may examine the AD docket on the Internet at http://www.regulations.gov or in person at the U.S. Department of 
Transportation, Docket Operations, M-30, West Building Ground Floor, 
Room W12-140, 1200 New Jersey Avenue SE., Washington, DC.

FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, Washington 98057-3356; telephone (425) 
227-1405; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a second supplemental notice of proposed rulemaking 
(SNPRM) to amend 14 CFR part 39 to include an AD that would apply to 
the specified products. That second SNPRM was published in the Federal 
Register on

[[Page 19086]]

December 10, 2012 (77 FR 73340). That second SNPRM proposed to correct 
an unsafe condition for the specified products. The Mandatory 
Continuing Airworthiness Information (MCAI) states:

    During Airbus Final Assembly Line flight tests, AoA [angle of 
attack] data from two different aeroplanes were found inaccurate, 
which was confirmed by flight data analysis.
    Investigation conducted by Airbus and Thales on the removed 
probes revealed oil residue between the stator and the rotor parts 
of the AoA vane position resolvers. This oil residue was the result 
of incorrect removal of machining oil during the manufacturing 
process of the AoA resolvers. At low temperatures, this oil residue 
becomes viscous (typically in cruise), causing delayed and/or 
reduced AoA vane movement. Multiple AOA probes could be 
simultaneously affected, providing incorrect indications of the AoA 
of the aeroplane.
    This condition, if not corrected, could lead to erroneous AoA 
information and consequent delayed or non-activation of the AoA 
protection systems which, during flight at a high angle of attack, 
could result in reduced control of the aeroplane.
    For the reasons described above, this [European Aviation Safety 
Agency (EASA)] AD requires the identification of the serial number 
(s/n) of each installed Thales Avionics Part Number (P/N) C16291AA 
AoA probe and the replacement of all suspect units with serviceable 
ones. This AD also prohibits the (re)installation of these same s/n 
probes on any aeroplane, unless corrective measures have been 
accomplished.

    You may obtain further information by examining the MCAI in the AD 
docket.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We considered the comment received.

Request to Update Service Information

    Airbus requested that the service information referenced in the 
second SNPRM (77 FR 73340, December 10, 2012) be updated to include 
recently added service information. Airbus stated that EASA has issued 
AD 2012-0236R1, dated December 17, 2012. In addition, Airbus stated 
that Thales Avionics has issued Service Bulletin C16291A-34-007, 
Revision 04, dated October 11, 2012.
    We partially agree with Airbus' request regarding using the most 
recent service information. Since the second SNPRM (77 FR 73340, 
December 10, 2012) was issued, we have reviewed Thales Avionics Service 
Bulletin C16291A-34-007, Revision 04, dated October 11, 2012. The 
actions in that service information remain unchanged from the previous 
service information. We have revised paragraphs (g), (i), and (k) of 
this AD accordingly to reflect the most current Thales Avionics service 
information.
    In addition, we have reviewed EASA AD 2012-0236, dated November 9, 
2012 (corrected November 12, 2012), and EASA AD 2012-0236R1, dated 
December 17, 2012. We have determined that no subsequent changes are 
required in this final rule as done to the EASA AD. We have not changed 
this final rule in this regard.

Conclusion

    We reviewed the available data, including the comment received, and 
determined that air safety and the public interest require adopting the 
AD with the changes described previously-and minor editorial changes. 
We have determined that these changes:
     Are consistent with the intent that was proposed in the 
second SNPRM (77 FR 73340, December 10, 2012) for correcting the unsafe 
condition; and
     Do not add any additional burden upon the public than was 
already proposed in the SNPRM (77 FR 73340, December 10, 2012).

Costs of Compliance

    We estimate that this AD will affect 755 products of U.S. registry. 
We also estimate that it will take about 2 work-hours per product to 
comply with the basic requirements of this AD. The average labor rate 
is $85 per work-hour. Based on these figures, we estimate the cost of 
this AD to the U.S. operators to be $128,350, or $170 per product.
    In addition, we estimate that any necessary follow-on actions would 
take about 3 work-hours and require parts costing $0, for a cost of 
$255 per product. We have no way of determining the number of products 
that may need these actions.

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.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this AD and placed it in the AD docket.

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 the second SNPRM (77 FR 73340, 
December 10, 2012), 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.

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 AD:

[[Page 19087]]

2013-06-03 Airbus: Amendment 39-17399. Docket No. FAA-2012-0150; 
Directorate Identifier 2011-NM-234-AD.

(a) Effective Date

    This airworthiness directive (AD) becomes effective May 3, 2013.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to all 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 
manufacturer serial numbers.

(d) Subject

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

(e) Reason

    This AD was prompted by reports of oil residue between the 
stator and the rotor parts of the position resolvers of the angle of 
attack (AOA) vane, which was a result of incorrect removal of the 
machining oil during the manufacturing process of the AOA resolvers. 
We are issuing this AD to prevent erroneous AOA information and 
consequent delayed or non-activation of the AOA protection systems, 
which during flight at a high angle of attack, could result in 
reduced control of the airplane.

(f) Compliance

    You are responsible for having the actions required by this AD 
performed within the compliance times specified, unless the actions 
have already been done.

(g) Inspection

    Within 12 months after the effective date of this AD, except as 
provided by paragraph (h) of this AD: Do the inspections specified 
in paragraphs (g)(1) and (g)(2) of this AD.
    (1) Inspect to determine the part number (P/N) and serial number 
of each Thales Avionics AOA probe, in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A320-34-1452, 
dated January 29, 2010. If any probe is found having P/N C16291AA 
and having a serial number listed in Thales Avionics Service 
Bulletin C16291A-34-007, Revision 04, dated October 11, 2012: Within 
12 months after the effective date of this AD, replace the AOA 
probe, in accordance with the Accomplishment Instructions of Airbus 
Service Bulletin A320-34-1452, provided that Thales Avionics Service 
Bulletin C16291A-34-009, dated September 10, 2009; or Airbus Service 
Bulletin A320-34-1444, dated October 7, 2009; have not been 
accomplished. Thales Avionics Service Bulletin C16291A-34-009, dated 
September 10, 2009; and Airbus Service Bulletin A320-34-1444, dated 
October 7, 2009; (which are not incorporated by reference in this 
AD) cannot be used for the installation of AOA probes having P/N 
C16291AB. A review of airplane maintenance records is acceptable in 
lieu of this inspection if the part number and serial number of the 
installed AOA probes can be conclusively determined from that 
review.
    (2) Inspect to determine the part number and serial number of 
each Thales Avionics AOA probe, in accordance with paragraph 
3.C.(1)(a) of the Accomplishment Instructions of Airbus Service 
Bulletin A320-34-1452, dated January 29, 2010. If any probe is found 
having P/N C16291AB, on which Thales Avionics Service Bulletin 
C16291A-34-009, dated September 10, 2009; or Airbus Service Bulletin 
A320-34-1444, dated October 7, 2009; (which are not incorporated by 
reference in this AD) has been accomplished: Within 12 months after 
the effective date of this AD, replace the AOA probe, in accordance 
with a method approved by the Manager, International Branch, ANM-
116, FAA, or European Aviation Safety Agency (EASA) (or its 
delegated agent). A review of airplane maintenance records is 
acceptable in lieu of the inspection specified in this paragraph if 
the part number of the installed AOA probes can be conclusively 
determined from that review.

    Note 1 to paragraph (g)(2) of this AD: Additional guidance for 
replacing the AOA probes may be found in Task 34-11-19-000-001-A, 
Removal of the Angle of Attack Sensor, of the Airbus A318/A319/A320/
A321 Aircraft Maintenance Manual, which is not incorporated by 
reference in this AD.

(h) Exception to the Requirements of Paragraph (g) of This AD

    For any airplane on which Airbus modification 150006 
(installation of Thales Avionics AOA probes P/N C16291AB) or 
modification 26934 (installation of Goodrich AOA probes P/N 0861ED) 
has been embodied in production, and on which no AOA probe 
replacement has been made since first flight: The actions specified 
in paragraph (g) of this AD are not required.

(i) Parts Installation Limitation and Prohibition

    (1) As of the effective date of this AD, no person may install a 
Thales Avionics AOA probe, P/N C16291AA, having a serial number 
listed in Thales Avionics Service Bulletin C16291A-34-007, Revision 
04, dated October 11, 2012, on any airplane, unless that Thales 
Avionics probe has been inspected, re-identified, and tested, in 
accordance with the Accomplishment Instructions of the service 
information specified in paragraphs (i)(1)(i) through (i)(1)(iv) of 
this AD.
    (i) Thales Avionics Service Bulletin C16291A-34-007, Revision 
04, dated October 11, 2012.
    (ii) Thales Avionics Service Bulletin C16291A-34-007, Revision 
03, dated April 10, 2012.
    (iii) Thales Avionics Service Bulletin C16291A-34-007, Revision 
02, dated December 16, 2011.
    (iv) Thales Avionics Service Bulletin C16291A-34-007, Revision 
01, dated December 3, 2009.
    (2) As of the effective date of this AD, no person may install a 
Thales Avionics AOA probe, P/N C16291AB, on which Thales Avionics 
Service Bulletin C16291A-34-009, dated September 10, 2009; or Airbus 
Service Bulletin A320-34-1444, dated October 7, 2009; (which are not 
incorporated by reference in this AD) has been incorporated.

(j) 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, Washington 
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) Airworthy Product: For any requirement in this AD to obtain 
corrective actions from a manufacturer or other source, use these 
actions if they are FAA-approved. Corrective actions are considered 
FAA-approved if they are approved by the State of Design Authority 
(or their delegated agent). You are required to assure the product 
is airworthy before it is returned to service.

(k) Related Information

    Refer to MCAI EASA AD 2011-0203, dated October 13, 2011, and the 
service information specified in paragraphs (k)(1) through (k)(5) of 
this AD, for related information.
    (1) Airbus Service Bulletin A320-34-1452, dated January 29, 
2010.
    (2) Thales Avionics Service Bulletin C16291A-34-007, Revision 
04, dated October 11, 2012.
    (3) Thales Avionics Service Bulletin C16291A-34-007, Revision 
03, dated April 10, 2012.
    (4) Thales Avionics Service Bulletin C16291A-34-007, Revision 
02, dated December 16, 2011.
    (5) Thales Avionics Service Bulletin C16291A-34-007, Revision 
01, dated December 3, 2009.

 (l) 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 Service Bulletin A320-34-1452, dated January 29, 
2010.

[[Page 19088]]

    (ii) Thales Avionics Service Bulletin C16291A-34-007, Revision 
04, dated October 11, 2012.
    (iii) Thales Avionics Service Bulletin C16291A-34-007, Revision 
03, dated April 10, 2012. Pages 1, 8, 10, 11, and 13 of this 
document are identified as Revision 03, dated April 10, 2012. Pages 
2, 7, and 12 are identified as Revision 01, dated December 3, 2009. 
Page 9 is identified as Revision 02, dated December 16, 2011.
    (iv) Thales Avionics Service Bulletin C16291A-34-007, Revision 
02, dated December 16, 2011. Pages 1, and pages 8 through 10 of this 
document are identified as Revision 02, dated December 16, 2011; 
pages 2 through 7, and pages 11 through 13 are identified as 
Revision 01, dated December 3, 2009.
    (v) Thales Avionics Service Bulletin C16291A-34-007, Revision 
01, dated December 3, 2009.
    (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 account.airworth-eas@airbus.com; 
Internet http://www.airbus.com. For Thales Avionics service 
information identified in this AD, contact Thales Avionics, Retrofit 
Manager, 105, Avenue du G[eacute]n[eacute]ral Eisenhower, BP 63647, 
31036 Toulouse Cedex 1, France; telephone +33 5 61 19 76 95; fax +33 
5 61 19 68 20; email retrofit.ata@fr.thalesgroup.com; Internet 
http://www.thalesgroup.com/aerospace.
    (4) You may review copies of the 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 March 8, 2013.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2013-06172 Filed 3-28-13; 8:45 am]
BILLING CODE 4910-13-P