Airworthiness Directives; Airbus Airplanes
Federal Register, Volume 80 Issue 44 (Friday, March 6, 2015)
Federal Register Volume 80, Number 44 (Friday, March 6, 2015)
Proposed Rules
Pages 12094-12097
From the Federal Register Online via the Government Printing Office www.gpo.gov
FR Doc No: 2015-04495
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
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 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.
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
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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 Geacuteneacuterale 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
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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
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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
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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.
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(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.
(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 account.airworth-eas@airbus.com; 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
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