81 FR 95531 - Airworthiness Directives; Airbus Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 81, Issue 249 (December 28, 2016)
Federal Aviation Administration
Federal Register Volume 81, Issue 249 (December 28, 2016)
| Page Range | 95531-95536 | |
| FR Document | 2016-30610 |
[Federal Register Volume 81, Number 249 (Wednesday, December 28, 2016)] [Proposed Rules] [Pages 95531-95536] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2016-30610] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2016-9518; Directorate Identifier 2015-NM-091-AD] RIN 2120-AA64 Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). ----------------------------------------------------------------------- SUMMARY: We propose to supersede Airworthiness Directive (AD) 2013-19- 09 and AD 2014-25-51, for all Airbus Model A318, A319, A320, and A321 series airplanes. AD 2013-19-09 currently requires replacing Angle of Attack (AOA) sensor conic plates with AOA sensor flat plates. AD 2014- 25-51 currently requires revising the airplane flight manual (AFM) to advise the flightcrew of emergency procedures for abnormal Alpha Protection (Alpha Prot). Since we issued AD 2013-19-09 and AD 2014-25- 51, we have received a report indicating that certain AOA sensors appear to have a greater susceptibility to adverse environmental conditions. This proposed AD would require replacing certain AOA sensors; and doing a detailed inspection and a functional heating test for discrepancies on certain AOA sensors, and replacing the affected AOA sensors. We are proposing this AD to address the unsafe condition on these products. DATES: We must receive comments on this proposed AD by February 13, 2017. ADDRESSES: You may send comments 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: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For Airbus service information identified in this NPRM, 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 [[Page 95532]] 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-2016- 9518; 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-2016-9518; Directorate Identifier 2015-NM-091-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 On March 8, 2013, we issued AD 2013-06-03, Amendment 39-17399 (78 FR 19085, March 29, 2013) (``AD 2013-06-03'') for all Airbus Model A318, A319, A320, and A321 series airplanes. AD 2013-06-03 was prompted by reports of oil residue between the stator and the rotor parts of the position resolvers of the AOA vane, which was a result of incorrect removal of the machining oil during the manufacturing process of the AOA resolvers. AD 2013-06-03 requires an inspection to determine if certain AOA probes are installed, and replacement of any affected AOA probe. We issued AD 2013-06-03 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. On September 13, 2013, we issued AD 2013-19-09, Amendment 39-17591 (78 FR 60667, October 2, 2013) (``AD 2013-19-09'') for all Airbus Model A318, A319, A320, and A321 series airplanes. AD 2013-19-09 was prompted by a determination that replacement of AOA sensor conic plates is necessary to address the identified unsafe condition. AD 2013-19-09 requires replacing AOA sensor conic plates with AOA sensor flat plates, and subsequent removal of an AFM revision. We issued AD 2013-19-09 to prevent reduced control of the airplane. On January 7, 2015, we issued AD 2014-25-51, Amendment 39-18067 (80 FR 3153, January 22, 2015) (``AD 2014-25-51'') for all Airbus Model A318, A319, A320, and A321 series airplanes. AD 2014-25-51 was prompted by a report of AOA probes jamming on an in-service Airbus Model A321 airplane. AD 2014-25-51 requires revising the AFM to advise the flight crew of emergency procedures for abnormal Alpha Prot. We issued AD 2014-25-51 to ensure that the flightcrew has procedures to counteract the pitch down order due to abnormal activation of the Alpha Prot. An abnormal Alpha Prot, if not corrected, could result in loss of control of the airplane. Since we issued AD 2013-06-03, AD 2013-19-09, and AD 2014-25-51, we have received a report indicating that certain AOA sensors appear to have a greater susceptibility to adverse environmental conditions. It has been determined that replacement of certain AOA sensors is necessary to address the unsafe condition on these airplanes. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2015-0135, 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 A318, A319, A320, and A321 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. 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 airplane. Investigation results indicated that A320 family airplanes 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 airplanes equipped with the latest Thales AOA sensor, Part Number (P/N) C16291AB, which was designed to improve A320 airplane 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 airplane, EASA issued AD 2015-0087, retaining the requirements of EASA AD 2012-0236R1 [which corresponds to FAA AD 2013-06-03], [EASA] AD 2013-0022 (partially) [which corresponds to FAA AD 2013-19-09], and [EASA] AD 2014-0266-E [which corresponds to FAA AD 2014-25-51], which were superseded, and requiring modification of the airplanes by replacement of the affected P/N sensors, and, after modification, prohibiting (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 2015-0087 was issued, based on further analysis results, Airbus issued Operators Information Transmission (OIT) Ref. 999.0015/15 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 2015-0087, which is superseded, but reduces the compliance times for airplanes 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-2016- 9518. Related Service Information Under 1 CFR Part 51 Airbus has issued the following service information: Service Bulletin A320-34-1415, Revision 03, dated July 8, 2010. This service information describes [[Page 95533]] procedures for a detailed inspection and a functional heating test for discrepancies on certain AOA sensors, and replacing the affected AOA sensors. Service Bulletin A320-34-1444, Revision 01, dated March 17, 2011. This service information describes procedures for replacing certain SEXTANT/THOMSON AOA sensors. Service Bulletin A320-34-1610, dated March 31, 2015. This service information describes procedures for replacing certain UTAS AOA sensors. 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. 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 the same type design. Differences Between This Proposed AD and the MCAI or Service Information The requirements specified in paragraphs (1), (2), (3), and (4) of the MCAI correspond to the requirements of AD 2013-06-03. We have determined that leaving AD 2013-06-03 as a stand-alone AD provides better clarification of the actions instead of superseding AD 2013-06- 03 as part of this proposed AD. Costs of Compliance We estimate that this proposed AD affects 959 airplanes of U.S. registry. The actions required by AD 2013-19-09, and retained in this proposed AD take about 8 work-hours per product, at an average labor rate of $85 per work-hour. Required parts cost about $0 per product. Based on these figures, the estimated cost of the actions that are required by AD 2013-19-09 is $680 per product. The actions required by AD 2014-25-51, and retained in this proposed AD take about 1 work-hour per product, at an average labor rate of $85 per work-hour. Required parts cost about $0 per product. Based on these figures, the estimated cost of the actions that are required by AD 2014-25-51 is $85 per product. We also estimate that it would take about 5 work-hours per product to comply with the basic requirements of this proposed AD. The average labor rate is $85 per work-hour. The parts cost is not available. Based on these figures, we estimate the cost of this proposed AD on U.S. operators to be at least $407,575, or $425 per product. In addition, we estimate that any necessary follow-on actions would take about 5 work-hours. The parts cost is not available. We have no way of determining the number of aircraft that might need these actions. According to the manufacturer, some of the costs of this proposed AD may be covered under warranty, thereby reducing the cost impact on affected individuals. We do not control warranty coverage for affected individuals. As a result, we have included all costs in our cost estimate. 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 removing Airworthiness Directive (AD) 2013-19-09, Amendment 39-17591 (78 FR 60667, October 2, 2013), and AD 2014-25-51, Amendment 39-18067 (80 FR 3153, January 22, 2015), and adding the following new AD: Airbus: Docket No. FAA-2016-9518; Directorate Identifier 2015-NM- 091-AD. (a) Comments Due Date We must receive comments by February 13, 2017. (b) Affected ADs (1) This AD replaces AD 2013-19-09, Amendment 39-17591 (78 FR 60667, October 2, 2013) (``AD 2013-19-09''), and AD 2014-25-51, Amendment 39-18067 (80 FR 3153, January 22, 2015) (``AD 2014-25- 51''). (2) This AD affects AD 2013-06-03, Amendment 39-17399 (78 FR 19085, March 29, 2013) (``AD 2013-06-03''). (c) Applicability This AD applies to the Airbus airplanes listed in paragraphs (c)(1) through (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 a report indicating that an Airbus Model A321 airplane encountered a blockage of two Angle of Attack (AOA) probes during climb, leading to activation of the Alpha Protection (Alpha [[Page 95534]] Prot) while the Mach number increased. We are issuing this AD to prevent a pitch down order due to abnormal activation of the Alpha Prot. An abnormal Alpha Prot, if not corrected, could result in loss of control of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Retained New Flat Plate Installation, With Removed Post- Installation Requirement and With Specific Delegation Approval Language This paragraph restates the requirements of paragraph (j) of AD 2013-19-09, with removed post-installation requirement and with specific delegation approval language. Within 5 months after November 6, 2013 (the effective date of AD 2013-19-09), remove all AOA sensor conic plates having part number (P/N) F3411060200000 or P/N F3411060900000 and install AOA sensor flat plates having part numbers specified in paragraph (g)(1) or (g)(2) of this AD, except as specified in paragraph (h) of this AD. Install the AOA sensor plates in accordance with the applicable method specified in paragraph (g)(1) or (g)(2) of this AD. (1) Install P/N D3411013520200 in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A320-34-1564, including Appendix 01, dated January 25, 2013. (2) Install P/N D3411007620000 or P/N D3411013520000, 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). (h) Retained Exception, With No Changes This paragraph restates the exception provided by paragraph (k) of AD 2013-19-09, with no changes. An airplane on which Airbus modification 154863 (installation of AOA sensor flat plate) and modification 154864 (coating protection) have been embodied in production is not affected by the requirements of paragraph (g) of this AD, provided that, since first flight, no AOA sensor conic plate having P/N F3411060200000 or P/N F3411060900000 has been installed on that airplane. (i) Retained Parts Installation Prohibition, With No Changes This paragraph restates the requirements of paragraph (m) of AD 2013-19-09, with no changes. (1) For any airplane that has AOA sensor flat plates installed: As of November 6, 2013 (the effective date of AD 2013-19-09), do not install any AOA sensor conic plate having P/N F3411060200000 or P/N F3411060900000, and do not use any AOA protection cover having P/N 98D34203003000. (2) For any airplane that has AOA sensor conic plates installed: As of November 6, 2013 (the effective date of AD 2013-19-09), after modification of the airplane as required by paragraph (g) of this AD, do not install any AOA sensor conic plate having P/N F3411060200000 or P/N F3411060900000, and do not use any AOA protection cover having P/N 98D34203003000. (j) Retained Revision of Airplane Flight Manual (AFM), With No Changes This paragraph restates the requirements of paragraph (g) of AD 2014-25-51, with no changes. Within 2 days after February 6, 2015 (the effective date of AD 2014-25-51), revise the AFM to incorporate procedures to address undue activation of Alpha Prot by inserting the text specified in figure 1 to paragraph (j) of this AD into the Emergency Procedures section of the applicable AFM, to advise the flight crew of emergency procedures for abnormal Alpha Prot. This may be accomplished by inserting a copy of this AD into the AFM. When a statement identical to the text specified in figure 1 to paragraph (j) of this AD is included in the general revisions of the AFM, the general revisions may be inserted in the AFM, and the text specified in figure 1 to paragraph (j) of this AD may be removed. [[Page 95535]] [GRAPHIC] [TIFF OMITTED] TP28DE16.009 (k) New Requirement of This AD: Replacement of Certain UTAS (formerly Goodrich) AOA Sensors For airplanes on which any UTAS AOA sensor, P/N 0861ED or P/N 0861ED2, is installed: Within the applicable compliance times specified in paragraphs (k)(1), (k)(2), (k)(3), and (k)(4) of this AD, replace the affected Captain and First Officer AOA sensors with Thales AOA sensors, P/N C16291AB, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-34-1610, dated March 31, 2015. (1) For Model A318 and A321 series airplanes on which any UTAS AOA sensor, P/N 0861ED, is installed: Replace within 7 months after the effective date of this AD. (2) For Model A319 and A320 series airplanes on which any UTAS AOA sensor, P/N 0861ED, is installed: Replace within 22 months after the effective date of this AD. (3) For Model A318 and A321 series airplanes on which any UTAS AOA sensor, P/N 0861ED2, is installed: Replace within 4 months after the effective date of this AD. (4) For Model A319 and A320 series airplanes on which any UTAS AOA sensor, P/N 0861ED2, is installed: Replace within 7 months after the effective date of this AD. (l) New Requirement of This AD: Replacement of Certain SEXTANT/THOMSON AOA Sensors For airplanes on which any SEXTANT/THOMSON AOA sensor, P/N 45150320 or P/N 16990568, is installed: Within the applicable compliance time specified in paragraph (l)(1) or (l)(2) of this AD, replace each SEXTANT/THOMSON AOA sensor, P/N 45150320 and P/N 16990568, with a Thales AOA sensor, P/N C16291AB, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-34- 1444, Revision 01, dated March 17, 2011; except AOA sensors modified in accordance with the Accomplishment Instructions of Thales Avionics Service Bulletin C16291A-34-009, dated September 10, 2009, cannot be used for the replacement. (1) For Model A318 and A321 series airplanes on which any SEXTANT/THOMSON AOA sensor, P/N 45150320 or P/N 16990568, is installed: Replace within 7 months after the effective date of this AD. (2) For Model A319 and A320 series airplanes on which any SEXTANT/THOMSON AOA sensor, P/N 45150320 or P/N 16990568, is installed: Replace within 22 months after the effective date of this AD. (m) New Requirement of This AD: Functional Heating Test, and Corrective Action for Certain AOA Sensors For an airplane on which any Thales AOA sensor, P/N C16291AA, is installed: Before exceeding 5,200 flight hours accumulated by each affected Thales AOA sensor since its first installation on an airplane, or within 6 months after the effective date of this AD, whichever occurs later, do a functional heating test of each AOA sensor, P/N C16291AA, to determine the maximum current (Imax) value, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-34-1415, Revision 03, dated July 8, 2010. If, during any functional heating test, any Imax value is below the flow chart value as specified in Airbus Service Bulletin A320-34-1415, Revision 03, dated July 8, 2010, before further flight, replace each discrepant AOA sensor with a sensor identified in paragraph (m)(1) or (m)(2) of this AD, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-34-1415, Revision 03, dated July 8, 2010. Repeat the functional heating test thereafter at intervals not to exceed 2,000 flight hours. (1) Replace with a Thales AOA sensor, P/N C16291AA, that has passed a functional [[Page 95536]] heating test as specified in the Accomplishment Instructions of Airbus Service Bulletin A320-34-1415, Revision 03, July 8, 2010. (2) Replace with a Thales AOA sensor, P/N C16291AB, except AOA sensors modified as specified in Thales Avionics Service Bulletin C16291A-34-009, dated September 10, 2009, cannot be used for the replacement. (n) Optional Terminating Action Modification of an airplane by replacing each Thales P/N C16291AA AOA sensor with a Thales P/N C16291AB AOA sensor, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-34-1444, Revision 01, dated March 17, 2011, terminates the repetitive functional heating tests required in paragraph (m) of this AD for that airplane; except AOA sensors modified in accordance with the Accomplishment Instructions of Thales Avionics Service Bulletin C16291A-34-009, dated September 10, 2009, cannot be used for the replacement. (o) New Provisions of This AD: Airplanes Not Affected An airplane with Airbus modification 150006 (installation of Thales P/N C16291AB AOA sensors), but without modification 26934 (installation of UTAS P/N 0861ED AOA sensors) embodied in production, is not affected by the requirements of paragraphs (k), (l), and (m) of this AD, provided it is determined that no AOA sensor having SEXTANT/THOMSON P/N 45150320 or 16990568, or UTAS P/N 0861ED or 0861ED2, has been installed on that airplane since its date of manufacture. (p) New Requirement of This AD: Parts Installation Prohibitions (1) As of the effective date of this AD: For an airplane on which only Thales AOA sensors, P/N C16291AB, are installed, do not install a Thales AOA sensor, P/N C16291AA, on that airplane. This parts installation prohibition terminates the requirements of paragraph (i)(1) of AD 2013-06-03, for the airplanes identified in this paragraph. (2) As of the effective date of this AD: For an airplane on which any combination of Thales AOA sensors, P/N C16291AA and Thales P/N C16291AB, are installed, do not install any SEXTANT/THOMSON AOA sensor, P/N 45150320 or 16990568, or UTAS AOA sensor, P/N 0861ED or 0861ED2, on that airplane. (3) After modification of an airplane as required by paragraph (k) of this AD, do not install any AOA sensor with a part number specified in paragraphs (p)(3)(i) and (p)(3)(ii) of this AD on that airplane, with the exception that installation of a UTAS P/N 0861ED AOA sensor is allowed in the standby position of that airplane. (i) SEXTANT/THOMSON AOA sensors, P/N 45150320 and P/N 16990568. (ii) UTAS AOA sensors, P/N 0861ED and P/N 0861ED2. (q) Credit for Previous Actions This paragraph provides credit for the actions required by paragraph (l) of this AD, if those actions were performed before the effective date of this AD using Airbus Service Bulletin A320-34- 1444, dated October 7, 2009; provided the replacement AOA sensors were not modified as specified in Thales Avionics Service Bulletin C16291A-34-009, dated September 10, 2009. (r) Acceptable Parts Installation of a version (part number) of an AOA sensor approved after the effective date of this AD is an approved method of compliance with the requirements of paragraph (k), (l), or (m) of this AD, as applicable, provided the requirements specified in paragraphs (r)(1) and (r)(2) of this AD are met. (1) The version (part number) must be approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA; or Airbus's EASA DOA. (2) The installation must be accomplished using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA; or Airbus's EASA DOA. (s) 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]. (i) 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. (ii) AMOCs approved previously for AD 2013-19-09, are approved as AMOCs for the corresponding provisions of paragraphs (g), (h), (i), and (t)(1) of this AD. (iii) AMOCs approved previously for AD 2014-25-51, are approved as AMOCs for the corresponding provisions of paragraph (j) of this AD. (2) Contacting the Manufacturer: As of the effective date of this AD, 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. (t) Retained Special Flight Permits (1) For AD 2013-19-09, Amendment 39-17591 (78 FR 60667, October 2, 2013): Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the airplane to a location where the airplane can be modified (if the operator elects to do so), provided Airbus A318/A319/A320/A321 TR TR286, Issue 1.0, dated December 17, 2012, has been inserted into the Emergency Procedures of the Airbus A318/A319/A320/A321 AFM. (2) For AD 2014-25-51, Amendment 39-18067 (80 FR 3153, January 22, 2015): Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the airplane to a location where the airplane can be modified (if the operator elects to do so), provided the revision required by paragraph (j) of this AD has been done. (u) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2015-0135, 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 searching for and locating Docket No. FAA-2016-9518. (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 December 8, 2016. Dionne Palermo, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016-30610 Filed 12-27-16; 8:45 am] BILLING CODE 4910-13-P
![Federal Register / Vol. 81, No. 249 / Wednesday, December 28, 2016 / Proposed Rules 95531
Maintenance Manual Temporary Revision Series Maintenance Manual Temporary DEPARTMENT OF TRANSPORTATION
71–03, dated March 15, 2016. Revision 71–02, dated March 15, 2016.
(iii) For Models SA227 Series Commuter (ii) For Models SA227 Series: Pages 206 Federal Aviation Administration
Category: Pages 206 and 206A from M7 and 207 from M7 Aerospace SA227 Series
Aerospace SA227 Series Commuter Category Maintenance Manual Temporary Revision
Maintenance Manual Temporary Revision 71–03, dated March 15, 2016.
14 CFR Part 39
71–02, dated March 15, 2016. (iii) For Models SA227 Series Commuter [Docket No. FAA–2016–9518; Directorate
(2) Installation of the secondary retention Category: Pages 206 and 206A from M7 Identifier 2015–NM–091–AD]
device required in paragraph (j) of this AD Aerospace SA227 Series Commuter Category
terminates the repetitive visual inspections of Maintenance Manual Temporary Revision RIN 2120–AA64
the PPC lever attachment required in 71–02, dated March 15, 2016.
paragraph (h)(1) of this AD. (2) Installation of the secondary retention Airworthiness Directives; Airbus
device terminates the requirement for the Airplanes
(i) Replace or Rework the Propeller Pitch repetitive inspections of the PPC lever torque
Assembly required in paragraph (h) of this AD. AGENCY: Federal Aviation
Within the next 600 hours TIS after the Administration (FAA), DOT.
effective date of this AD or within the next (k) Alternative Methods of Compliance
ACTION: Notice of proposed rulemaking
12 months after the effective date of this AD, (AMOCs)
(NPRM).
whichever occurs first, do the actions in (1) The Manager, Fort Worth Airplane
either paragraph (i)(1) or (2) of this AD Certification Office (ACO), FAA, has the SUMMARY: We propose to supersede
following the Accomplishment Instructions authority to approve AMOCs for this AD, if Airworthiness Directive (AD) 2013–19–
in Honeywell International Inc. Service requested using the procedures found in 14
09 and AD 2014–25–51, for all Airbus
Bulletin TPE331–72–2190, dated December CFR 39.19. In accordance with 14 CFR 39.19,
21, 2011, as referenced in the applicable send your request to your principal inspector Model A318, A319, A320, and A321
service information listed in paragraph (g)(1), or local Flight Standards District Office, as series airplanes. AD 2013–19–09
(2), or (3) this AD. appropriate. If sending information directly currently requires replacing Angle of
(1) Replace the PPC. Remove the PPC to the manager of the ACO, send it to the Attack (AOA) sensor conic plates with
assembly and replace with the applicable attention of the person identified in AOA sensor flat plates. AD 2014–25–51
new design PPC using the part numbers paragraph (l)(1), Related Information, of this currently requires revising the airplane
listed in table 1 to paragraph (i)(1) of this AD. AD. flight manual (AFM) to advise the
(2) Before using any approved AMOC,
flightcrew of emergency procedures for
TABLE 1 TO PARAGRAPH (I)(1) OF THIS notify your appropriate principal inspector,
or lacking a principal inspector, the manager abnormal Alpha Protection (Alpha Prot).
AD—PART NUMBER PPC ASSEMBLIES of the local flight standards district office/ Since we issued AD 2013–19–09 and
certificate holding district office. AD 2014–25–51, we have received a
Part No. PPC report indicating that certain AOA
Part No. PPC assembly to assembly to (l) Related Information
remove sensors appear to have a greater
install
(1) For more information about this AD, susceptibility to adverse environmental
869130–11 ............................. 70000295–11 contact one of the following individuals: conditions. This proposed AD would
869130–12 ............................. 70000295–12 (i) Justin Carter, ASW–142, Aerospace
Engineer, Fort Worth Airplane Certification
require replacing certain AOA sensors;
869130–13 ............................. 70000295–13 and doing a detailed inspection and a
869130–14 ............................. 70000295–14 Office (ACO), FAA, 2601 Meacham Blvd.,
Fort Worth, Texas 76137–4298; telephone: functional heating test for discrepancies
869130–16 ............................. 70000295–16
(817) 222–5146; fax: (817) 222–5960; email: on certain AOA sensors, and replacing
869130–17 ............................. 70000295–17
869130–18 ............................. 70000295–18 justin.carter@faa.gov; or the affected AOA sensors. We are
869130–19 ............................. 70000295–19 (ii) Kristin Bradley, ASW–143, Aerospace proposing this AD to address the unsafe
869130–30 ............................. 70000295–30 Engineer, Fort Worth ACO, FAA, 2601 condition on these products.
895481–1 ............................... 70000298–1 Meacham Blvd., Fort Worth, Texas 76137–
DATES: We must receive comments on
895481–2 ............................... 70000298–2 4298; telephone: (817) 222–5485; fax: (817)
222–5960; email: kristin.bradley@faa.gov. this proposed AD by February 13, 2017.
895481–4 ............................... 70000298–4
(2) For service information identified in ADDRESSES: You may send comments by
895481–5 ............................... 70000298–5
895481–6 ............................... 70000298–6 this AD, contact M7 Aerospace LLC, 10823 any of the following methods:
895481–7 ............................... 70000298–7 NE Entrance Road, San Antonio, Texas • Federal eRulemaking Portal: Go to
895481–17 ............................. 70000298–17 78216; phone: (210) 824–9421; fax: (210) http://www.regulations.gov. Follow the
895481–18 ............................. 70000298–18 804–7766; Internet: http://www.elbitsystems- instructions for submitting comments.
895481–19 ............................. 70000298–19 us.com; email: MetroTech@ • Fax: 202–493–2251.
M7Aerospace.com; or Honeywell
895481–20 ............................. 70000298–20
International Inc., 111 S. 34th Street,
• Mail: U.S. Department of
895481–22 ............................. 70000298–22 Transportation, Docket Operations, M–
Phoenix, Arizona 85034–2802; phone: (855)
808–6500; email: AeroTechSupport@ 30, West Building Ground Floor, Room
(2) Rework the PPC assembly. Inspect the W12–140, 1200 New Jersey Avenue SE.,
splined end of the shouldered shaft for the honeywell.com; Internet: https://
presence and good condition of a threaded aerospace.honeywell.com/en/services/ Washington, DC 20590.
hole, repairing or replacing the cam maintenance-and-monitoring.You may view • Hand Delivery: Deliver to Mail
assembly, and reworking the PPC assembly this referenced service information at the address above between 9 a.m. and 5
as necessary. FAA, Small Airplane Directorate, 901 Locust, p.m., Monday through Friday, except
Kansas City, Missouri 64106. For information Federal holidays.
(j) Secondary Retention Feature on the availability of this material at the
For Airbus service information
sradovich on DSK3GMQ082PROD with PROPOSALS
(1) Before further flight after the FAA, call 816–329–4148.
identified in this NPRM, contact Airbus,
replacement or rework of the PPC assembly Issued in Kansas City, Missouri on Airworthiness Office—EIAS, 1 Rond
required in paragraph (i) of this AD, install December 8, 2016. Point Maurice Bellonte, 31707 Blagnac
the secondary retention feature on the PPC Pat Mullen,
assembly following the applicable service Cedex, France; telephone +33 5 61 93 36
information listed in paragraph (j)(1)(i), (ii), Acting Manager, Small Airplane Directorate, 96; fax +33 5 61 93 44 51; email
or (iii) of this AD. Aircraft Certification Service. account.airworth-eas@airbus.com;
(i) For Models SA226 Series: Pages TR–224 [FR Doc. 2016–30292 Filed 12–27–16; 8:45 am] Internet http://www.airbus.com. You
through TR–228 from M7 Aerospace SA226 BILLING CODE 4910–13–P may view this referenced service
VerDate Sep<11>2014 18:33 Dec 27, 2016 Jkt 241001 PO 00000 Frm 00036 Fmt 4702 Sfmt 4702 E:\FR\FM\28DEP1.SGM 28DEP1](https://thefederalregister.org/doc/81_FR_95780/page/1.svg)
![95532 Federal Register / Vol. 81, No. 249 / Wednesday, December 28, 2016 / Proposed Rules
information at the FAA, Transport determine if certain AOA probes are managed to regain full control and the flight
Airplane Directorate, 1601 Lind Avenue installed, and replacement of any landed uneventfully.
SW., Renton, WA. For information on affected AOA probe. We issued AD When Alpha Prot is activated due to
the availability of this material at the 2013–06–03 to prevent erroneous AOA blocked AOA probes, the flight control laws
order a continuous nose down pitch rate that,
FAA, call 425–227–1221. information and consequent delayed or in a worst case scenario, cannot be stopped
Examining the AD Docket non-activation of the AOA protection with backward sidestick inputs, even in the
systems, which during flight at a high full backward position. If the Mach number
You may examine the AD docket on AOA, could result in reduced control of increases during a nose down order, the AOA
the Internet at http:// the airplane. value of the Alpha Prot will continue to
www.regulations.gov by searching for On September 13, 2013, we issued AD decrease. As a result, the flight control laws
and locating Docket No. FAA–2016– 2013–19–09, Amendment 39–17591 (78 will continue to order a nose down pitch
9518; or in person at the Docket FR 60667, October 2, 2013) (‘‘AD 2013– rate, even if the speed is above minimum
Management Facility between 9 a.m. selectable speed, known as VLS.
19–09’’) for all Airbus Model A318, This condition, if not corrected, could
and 5 p.m., Monday through Friday, A319, A320, and A321 series airplanes.
except Federal holidays. The AD docket result in loss of control of the airplane.
AD 2013–19–09 was prompted by a Investigation results indicated that A320
contains this proposed AD, the determination that replacement of AOA family airplanes equipped with certain UTC
regulatory evaluation, any comments sensor conic plates is necessary to Aerospace (UTAS, formerly known as
received, and other information. The address the identified unsafe condition. Goodrich) AOA sensors, or equipped with
street address for the Docket Operations AD 2013–19–09 requires replacing AOA certain SEXTANT/THOMSON AOA sensors,
office (telephone 800–647–5527) is in appear to have a greater susceptibility to
sensor conic plates with AOA sensor
the ADDRESSES section. Comments will adverse environmental conditions than
flat plates, and subsequent removal of
be available in the AD docket shortly airplanes equipped with the latest Thales
an AFM revision. We issued AD 2013– AOA sensor, Part Number (P/N) C16291AB,
after receipt.
19–09 to prevent reduced control of the which was designed to improve A320
FOR FURTHER INFORMATION CONTACT: airplane. airplane AOA indication behaviour in heavy
Sanjay Ralhan, Aerospace Engineer,
On January 7, 2015, we issued AD rain conditions.
International Branch, ANM–116, Having determined that replacement of
2014–25–51, Amendment 39–18067 (80
Transport Airplane Directorate, FAA, these AOA sensors is necessary to achieve
FR 3153, January 22, 2015) (‘‘AD 2014–
1601 Lind Avenue SW., Renton, WA and maintain the required safety level of the
25–51’’) for all Airbus Model A318,
98057–3356; telephone 425–227–1405; airplane, EASA issued AD 2015–0087,
A319, A320, and A321 series airplanes.
fax 425–227–1149. retaining the requirements of EASA AD
AD 2014–25–51 was prompted by a 2012–0236R1 [which corresponds to FAA AD
SUPPLEMENTARY INFORMATION:
report of AOA probes jamming on an in- 2013–06–03], [EASA] AD 2013–0022
Comments Invited service Airbus Model A321 airplane. AD (partially) [which corresponds to FAA AD
We invite you to send any written 2014–25–51 requires revising the AFM 2013–19–09], and [EASA] AD 2014–0266–E
relevant data, views, or arguments about to advise the flight crew of emergency [which corresponds to FAA AD 2014–25–51],
procedures for abnormal Alpha Prot. We which were superseded, and requiring
this proposed AD. Send your comments modification of the airplanes by replacement
to an address listed under the issued AD 2014–25–51 to ensure that
the flightcrew has procedures to of the affected P/N sensors, and, after
ADDRESSES section. Include ‘‘Docket No. modification, prohibiting (re-)installation of
FAA–2016–9518; Directorate Identifier counteract the pitch down order due to
those P/N AOA sensors. That [EASA] AD
2015–NM–091–AD’’ at the beginning of abnormal activation of the Alpha Prot. also required repetitive detailed visual
your comments. We specifically invite An abnormal Alpha Prot, if not inspections (DET) and functional heating
comments on the overall regulatory, corrected, could result in loss of control tests of certain Thales AOA sensors and
economic, environmental, and energy of the airplane. provided an optional terminating action for
aspects of this proposed AD. We will Since we issued AD 2013–06–03, AD those inspections.
consider all comments received by the 2013–19–09, and AD 2014–25–51, we Since EASA AD 2015–0087 was issued,
have received a report indicating that based on further analysis results, Airbus
closing date and may amend this issued Operators Information Transmission
proposed AD based on those comments. certain AOA sensors appear to have a
(OIT) Ref. 999.0015/15 Revision 1,
We will post all comments we greater susceptibility to adverse instructing operators to speed up the removal
receive, without change, to http:// environmental conditions. It has been from service of UTAS P/N 0861ED2 AOA
www.regulations.gov, including any determined that replacement of certain sensors.
personal information you provide. We AOA sensors is necessary to address the For the reasons described above, this
will also post a report summarizing each unsafe condition on these airplanes. [EASA] AD retains the requirements of EASA
substantive verbal contact we receive The European Aviation Safety Agency AD 2015–0087, which is superseded, but
about this proposed AD. (EASA), which is the Technical Agent reduces the compliance times for airplanes
for the Member States of the European with UTAS P/N 0861ED2 AOA sensors
Discussion installed.
Union, has issued EASA Airworthiness
On March 8, 2013, we issued AD Directive 2015–0135, dated July 8, 2015 You may examine the MCAI in the
2013–06–03, Amendment 39–17399 (78 (referred to after this as the Mandatory AD docket on the Internet at http://
FR 19085, March 29, 2013) (‘‘AD 2013– Continuing Airworthiness Information, www.regulations.gov by searching for
06–03’’) for all Airbus Model A318, or ‘‘the MCAI’’), to correct an unsafe and locating Docket No. FAA–2016–
A319, A320, and A321 series airplanes. 9518.
sradovich on DSK3GMQ082PROD with PROPOSALS
condition for all Airbus Model A318,
AD 2013–06–03 was prompted by A319, A320, and A321 series airplanes.
reports of oil residue between the stator Related Service Information Under 1
The MCAI states: CFR Part 51
and the rotor parts of the position
An occurrence was reported where an
resolvers of the AOA vane, which was Airbus A321 aeroplane encountered a Airbus has issued the following
a result of incorrect removal of the blockage of two Angle of Attack (AOA) service information:
machining oil during the manufacturing probes during climb, leading to activation of • Service Bulletin A320–34–1415,
process of the AOA resolvers. AD 2013– the Alpha Protection (Alpha Prot) while the Revision 03, dated July 8, 2010. This
06–03 requires an inspection to Mach number increased. The flight crew service information describes
VerDate Sep<11>2014 18:33 Dec 27, 2016 Jkt 241001 PO 00000 Frm 00037 Fmt 4702 Sfmt 4702 E:\FR\FM\28DEP1.SGM 28DEP1](https://thefederalregister.org/doc/81_FR_95780/page/2.svg)
![Federal Register / Vol. 81, No. 249 / Wednesday, December 28, 2016 / Proposed Rules 95533
procedures for a detailed inspection and We also estimate that it would take 4. Will not have a significant
a functional heating test for about 5 work-hours per product to economic impact, positive or negative,
discrepancies on certain AOA sensors, comply with the basic requirements of on a substantial number of small entities
and replacing the affected AOA sensors. this proposed AD. The average labor under the criteria of the Regulatory
• Service Bulletin A320–34–1444, rate is $85 per work-hour. The parts cost Flexibility Act.
Revision 01, dated March 17, 2011. This is not available. Based on these figures,
List of Subjects in 14 CFR Part 39
service information describes we estimate the cost of this proposed
procedures for replacing certain AD on U.S. operators to be at least Air transportation, Aircraft, Aviation
SEXTANT/THOMSON AOA sensors. $407,575, or $425 per product. safety, Incorporation by reference,
• Service Bulletin A320–34–1610, In addition, we estimate that any Safety.
dated March 31, 2015. This service necessary follow-on actions would take The Proposed Amendment
information describes procedures for about 5 work-hours. The parts cost is
replacing certain UTAS AOA sensors. not available. We have no way of Accordingly, under the authority
determining the number of aircraft that delegated to me by the Administrator,
This service information is reasonably
might need these actions. the FAA proposes to amend 14 CFR part
available because the interested parties
According to the manufacturer, some 39 as follows:
have access to it through their normal
course of business or by the means of the costs of this proposed AD may be
covered under warranty, thereby PART 39—AIRWORTHINESS
identified in the ADDRESSES section. DIRECTIVES
reducing the cost impact on affected
FAA’s Determination and Requirements individuals. We do not control warranty
of This Proposed AD ■ 1. The authority citation for part 39
coverage for affected individuals. As a
continues to read as follows:
This product has been approved by result, we have included all costs in our
cost estimate. Authority: 49 U.S.C. 106(g), 40113, 44701.
the aviation authority of another
country, and is approved for operation Authority for This Rulemaking § 39.13 [Amended]
in the United States. Pursuant to our ■ 2. The FAA amends § 39.13 by
Title 49 of the United States Code
bilateral agreement with the State of removing Airworthiness Directive (AD)
specifies the FAA’s authority to issue
Design Authority, we have been notified 2013–19–09, Amendment 39–17591 (78
rules on aviation safety. Subtitle I,
of the unsafe condition described in the FR 60667, October 2, 2013), and AD
section 106, describes the authority of
MCAI and service information 2014–25–51, Amendment 39–18067 (80
the FAA Administrator. ‘‘Subtitle VII:
referenced above. We are proposing this FR 3153, January 22, 2015), and adding
Aviation Programs,’’ describes in more
AD because we evaluated all pertinent the following new AD:
detail the scope of the Agency’s
information and determined an unsafe
authority. Airbus: Docket No. FAA–2016–9518;
condition exists and is likely to exist or
We are issuing this rulemaking under Directorate Identifier 2015–NM–091–AD.
develop on other products of the same
the authority described in ‘‘Subtitle VII, (a) Comments Due Date
type design.
Part A, Subpart III, Section 44701:
We must receive comments by February
Differences Between This Proposed AD General requirements.’’ Under that
13, 2017.
and the MCAI or Service Information section, Congress charges the FAA with
promoting safe flight of civil aircraft in (b) Affected ADs
The requirements specified in
air commerce by prescribing regulations (1) This AD replaces AD 2013–19–09,
paragraphs (1), (2), (3), and (4) of the
for practices, methods, and procedures Amendment 39–17591 (78 FR 60667, October
MCAI correspond to the requirements of 2, 2013) (‘‘AD 2013–19–09’’), and AD 2014–
the Administrator finds necessary for
AD 2013–06–03. We have determined 25–51, Amendment 39–18067 (80 FR 3153,
safety in air commerce. This regulation
that leaving AD 2013–06–03 as a stand- January 22, 2015) (‘‘AD 2014–25–51’’).
is within the scope of that authority
alone AD provides better clarification of (2) This AD affects AD 2013–06–03,
because it addresses an unsafe condition
the actions instead of superseding AD Amendment 39–17399 (78 FR 19085, March
that is likely to exist or develop on 29, 2013) (‘‘AD 2013–06–03’’).
2013–06–03 as part of this proposed AD.
products identified in this rulemaking
Costs of Compliance action. (c) Applicability
This AD applies to the Airbus airplanes
We estimate that this proposed AD Regulatory Findings listed in paragraphs (c)(1) through (c)(4) of
affects 959 airplanes of U.S. registry. We determined that this proposed AD this AD, certificated in any category, all
The actions required by AD 2013–19– would not have federalism implications manufacturer serial numbers.
09, and retained in this proposed AD under Executive Order 13132. This (1) Airbus Model A318–111, –112, –121,
take about 8 work-hours per product, at proposed AD would not have a and –122 airplanes.
an average labor rate of $85 per work- (2) Airbus Model A319–111, –112, –113,
substantial direct effect on the States, on
hour. Required parts cost about $0 per –114, –115, –131, –132, and –133 airplanes.
the relationship between the national (3) Airbus Model A320–211, –212, –214,
product. Based on these figures, the Government and the States, or on the –231, –232, and –233 airplanes.
estimated cost of the actions that are distribution of power and (4) Airbus Model A321–111, –112, –131,
required by AD 2013–19–09 is $680 per responsibilities among the various –211, –212, –213, –231, and –232 airplanes.
product. levels of government.
The actions required by AD 2014–25– (d) Subject
sradovich on DSK3GMQ082PROD with PROPOSALS
For the reasons discussed above, I
51, and retained in this proposed AD certify this proposed regulation: Air Transport Association (ATA) of
take about 1 work-hour per product, at 1. Is not a ‘‘significant regulatory America Code 34, Navigation.
an average labor rate of $85 per work- action’’ under Executive Order 12866; (e) Reason
hour. Required parts cost about $0 per 2. Is not a ‘‘significant rule’’ under the This AD was prompted by a report
product. Based on these figures, the DOT Regulatory Policies and Procedures indicating that an Airbus Model A321
estimated cost of the actions that are (44 FR 11034, February 26, 1979); airplane encountered a blockage of two Angle
required by AD 2014–25–51 is $85 per 3. Will not affect intrastate aviation in of Attack (AOA) probes during climb, leading
product. Alaska; and to activation of the Alpha Protection (Alpha
VerDate Sep<11>2014 18:33 Dec 27, 2016 Jkt 241001 PO 00000 Frm 00038 Fmt 4702 Sfmt 4702 E:\FR\FM\28DEP1.SGM 28DEP1](https://thefederalregister.org/doc/81_FR_95780/page/3.svg)
![95536 Federal Register / Vol. 81, No. 249 / Wednesday, December 28, 2016 / Proposed Rules
heating test as specified in the Bulletin A320–34–1444, dated October 7, accordance with sections 21.197 and 21.199
Accomplishment Instructions of Airbus 2009; provided the replacement AOA sensors of the Federal Aviation Regulations (14 CFR
Service Bulletin A320–34–1415, Revision 03, were not modified as specified in Thales 21.197 and 21.199) to operate the airplane to
July 8, 2010. Avionics Service Bulletin C16291A–34–009, a location where the airplane can be
(2) Replace with a Thales AOA sensor, P/ dated September 10, 2009. modified (if the operator elects to do so),
N C16291AB, except AOA sensors modified provided Airbus A318/A319/A320/A321 TR
(r) Acceptable Parts
as specified in Thales Avionics Service TR286, Issue 1.0, dated December 17, 2012,
Bulletin C16291A–34–009, dated September Installation of a version (part number) of an has been inserted into the Emergency
10, 2009, cannot be used for the replacement. AOA sensor approved after the effective date Procedures of the Airbus A318/A319/A320/
of this AD is an approved method of A321 AFM.
(n) Optional Terminating Action compliance with the requirements of (2) For AD 2014–25–51, Amendment 39–
Modification of an airplane by replacing paragraph (k), (l), or (m) of this AD, as 18067 (80 FR 3153, January 22, 2015):
each Thales P/N C16291AA AOA sensor with applicable, provided the requirements Special flight permits may be issued in
a Thales P/N C16291AB AOA sensor, in specified in paragraphs (r)(1) and (r)(2) of this accordance with sections 21.197 and 21.199
accordance with the Accomplishment AD are met. of the Federal Aviation Regulations (14 CFR
Instructions of Airbus Service Bulletin A320– (1) The version (part number) must be 21.197 and 21.199) to operate the airplane to
34–1444, Revision 01, dated March 17, 2011, approved by the Manager, International a location where the airplane can be
terminates the repetitive functional heating Branch, ANM–116, Transport Airplane modified (if the operator elects to do so),
tests required in paragraph (m) of this AD for Directorate, FAA; or EASA; or Airbus’s EASA provided the revision required by paragraph
that airplane; except AOA sensors modified DOA. (j) of this AD has been done.
in accordance with the Accomplishment (2) The installation must be accomplished
Instructions of Thales Avionics Service using a method approved by the Manager, (u) Related Information
Bulletin C16291A–34–009, dated September International Branch, ANM–116, Transport (1) Refer to Mandatory Continuing
10, 2009, cannot be used for the replacement. Airplane Directorate, FAA; or EASA; or Airworthiness Information (MCAI) EASA
Airbus’s EASA DOA. Airworthiness Directive 2015–0135, dated
(o) New Provisions of This AD: Airplanes
Not Affected (s) Other FAA AD Provisions July 8, 2015, for related information. This
MCAI may be found in the AD docket on the
An airplane with Airbus modification The following provisions also apply to this
Internet at http://www.regulations.gov by
150006 (installation of Thales P/N C16291AB AD:
searching for and locating Docket No. FAA–
AOA sensors), but without modification (1) Alternative Methods of Compliance
2016–9518.
26934 (installation of UTAS P/N 0861ED (AMOCs): The Manager, International
(2) For service information identified in
AOA sensors) embodied in production, is not Branch, ANM–116, Transport Airplane
this AD, contact Airbus, Airworthiness
affected by the requirements of paragraphs Directorate, FAA, has the authority to
Office—EIAS, 1 Rond Point Maurice
(k), (l), and (m) of this AD, provided it is approve AMOCs for this AD, if requested
Bellonte, 31707 Blagnac Cedex, France;
determined that no AOA sensor having using the procedures found in 14 CFR 39.19.
telephone +33 5 61 93 36 96; fax +33 5 61
SEXTANT/THOMSON P/N 45150320 or In accordance with 14 CFR 39.19, send your
93 44 51; email account.airworth-eas@
16990568, or UTAS P/N 0861ED or 0861ED2, request to your principal inspector or local
Flight Standards District Office, as airbus.com; Internet http://www.airbus.com.
has been installed on that airplane since its You may view this service information at the
date of manufacture. appropriate. If sending information directly
to the International Branch, send it to ATTN: FAA, Transport Airplane Directorate, 1601
(p) New Requirement of This AD: Parts Sanjay Ralhan, Aerospace Engineer, Lind Avenue SW., Renton, WA. For
Installation Prohibitions International Branch, ANM–116, Transport information on the availability of this
(1) As of the effective date of this AD: For Airplane Directorate, FAA, 1601 Lind material at the FAA, call 425–227–1221.
an airplane on which only Thales AOA Avenue SW., Renton, WA 98057–3356; Issued in Renton, Washington, on
sensors, P/N C16291AB, are installed, do not telephone 425–227–1405; fax 425–227–1149. December 8, 2016.
install a Thales AOA sensor, Information may be emailed to: 9-ANM-116- Dionne Palermo,
P/N C16291AA, on that airplane. This parts AMOC-REQUESTS@faa.gov.
(i) Before using any approved AMOC, Acting Manager, Transport Airplane
installation prohibition terminates the
notify your appropriate principal inspector, Directorate, Aircraft Certification Service.
requirements of paragraph (i)(1) of AD 2013–
06–03, for the airplanes identified in this or lacking a principal inspector, the manager [FR Doc. 2016–30610 Filed 12–27–16; 8:45 am]
paragraph. of the local flight standards district office/ BILLING CODE 4910–13–P
(2) As of the effective date of this AD: For certificate holding district office.
an airplane on which any combination of (ii) AMOCs approved previously for AD
Thales AOA sensors, P/N C16291AA and 2013–19–09, are approved as AMOCs for the DEPARTMENT OF TRANSPORTATION
Thales P/N C16291AB, are installed, do not corresponding provisions of paragraphs (g),
install any SEXTANT/THOMSON AOA (h), (i), and (t)(1) of this AD. Federal Aviation Administration
sensor, P/N 45150320 or 16990568, or UTAS (iii) AMOCs approved previously for AD
AOA sensor, P/N 0861ED or 0861ED2, on 2014–25–51, are approved as AMOCs for the
that airplane. corresponding provisions of paragraph (j) of 14 CFR Part 39
(3) After modification of an airplane as this AD. [Docket No. FAA–2016–9516; Directorate
required by paragraph (k) of this AD, do not (2) Contacting the Manufacturer: As of the Identifier 2016–NM–053–AD]
install any AOA sensor with a part number effective date of this AD, for any requirement
specified in paragraphs (p)(3)(i) and (p)(3)(ii) in this AD to obtain corrective actions from RIN 2120–AA64
of this AD on that airplane, with the a manufacturer, the action must be
exception that installation of a UTAS P/N accomplished using a method approved by Airworthiness Directives; The Boeing
0861ED AOA sensor is allowed in the the Manager, International Branch, ANM– Company Airplanes
standby position of that airplane. 116, Transport Airplane Directorate, FAA; or
(i) SEXTANT/THOMSON AOA sensors, P/ the European Aviation Safety Agency AGENCY: Federal Aviation
sradovich on DSK3GMQ082PROD with PROPOSALS
N 45150320 and P/N 16990568. (EASA); or Airbus’s EASA Design Administration (FAA), DOT.
(ii) UTAS AOA sensors, P/N 0861ED and Organization Approval (DOA). If approved by
ACTION: Notice of proposed rulemaking
P/N 0861ED2. the DOA, the approval must include the
DOA-authorized signature. (NPRM).
(q) Credit for Previous Actions
This paragraph provides credit for the (t) Retained Special Flight Permits SUMMARY: We propose to adopt a new
actions required by paragraph (l) of this AD, (1) For AD 2013–19–09, Amendment 39– airworthiness directive (AD) for certain
if those actions were performed before the 17591 (78 FR 60667, October 2, 2013): The Boeing Company Model 787–8 and
effective date of this AD using Airbus Service Special flight permits may be issued in 787–9 airplanes. This proposed AD was
VerDate Sep<11>2014 18:33 Dec 27, 2016 Jkt 241001 PO 00000 Frm 00041 Fmt 4702 Sfmt 4702 E:\FR\FM\28DEP1.SGM 28DEP1](https://thefederalregister.org/doc/81_FR_95780/page/6.svg)
Document Created: 2016-12-28 02:16:50
Document Modified: 2016-12-28 02:16:50
| Category | Regulatory Information | |
| Collection | Federal Register | |
| sudoc Class | AE 2.7: GS 4.107: AE 2.106: | |
| Publisher | Office of the Federal Register, National Archives and Records Administration | |
| Section | Proposed Rules | |
| Action | Notice of proposed rulemaking (NPRM). | |
| Dates | We must receive comments on this proposed AD by February 13, 2017. | |
| 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. | |
| FR Citation | 81 FR 95531 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
2025 Federal Register | Disclaimer | Privacy Policy
USC | CFR | eCFR