82 FR 40675 - Airworthiness Directives; Airbus Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 82, Issue 165 (August 28, 2017)
Federal Aviation Administration
Federal Register Volume 82, Issue 165 (August 28, 2017)
| Page Range | 40675-40681 | |
| FR Document | 2017-16860 |
[Federal Register Volume 82, Number 165 (Monday, August 28, 2017)] [Rules and Regulations] [Pages 40675-40681] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2017-16860] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2016-9518; Product Identifier 2015-NM-091-AD; Amendment 39-18989; AD 2017-16-12] RIN 2120-AA64 Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. ----------------------------------------------------------------------- SUMMARY: We are superseding Airworthiness Directive (AD) 2013-19-09 and AD 2014-25-51, which applied to all Airbus Model A318, A319, A320, and A321 series airplanes. AD 2013-19-09 required replacing Angle of Attack (AOA) sensor conic plates with AOA sensor flat plates. AD 2014-25-51 required revising the airplane flight manual (AFM) to advise the flightcrew of emergency procedures for abnormal Alpha Protection (Alpha Prot). This new AD requires 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. This AD was prompted by a report indicating that a Model A321 airplane encountered a blockage of two AOA probes during climb, leading to activation of the Alpha Prot while the Mach number increased. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective October 2, 2017. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of October 2, 2017. The Director of the Federal Register approved the incorporation by reference of certain other publications listed in this AD as of November 6, 2013 (78 FR 60667, October 2, 2013). ADDRESSES: For service information identified in this final rule, contact Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email [email protected]; Internet http://www.airbus.com. You may view this referenced service information at the FAA, Transport Standards Branch, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016- 9518. 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 AD, the regulatory evaluation, any comments received, and other information. The address for the Docket Office (telephone 800- 647-5527) is Docket Management Facility, U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1405; fax 425-227- 1149. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede 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''). AD 2013-19-09 and AD 2014-25-51 applied to all Airbus Model A318, A319, A320, and A321 series airplanes. The NPRM published in the Federal Register on December 28, 2016 (81 FR 95531). The NPRM was prompted by a report indicating that an Airbus Model A321 airplane encountered a blockage of two AOA probes during climb, leading to activation of the Alpha Prot while the Mach number increased. The NPRM proposed to continue to require replacing AOA sensor conic plates with AOA sensor flat plates and revising the AFM to advise the flight crew of emergency procedures for abnormal Alpha Prot. The NPRM also proposed to [[Page 40676]] continue to 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 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. 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. Comments We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the NPRM and the FAA's response to each comment. Air Line Pilots Association, International stated that it supported the NPRM. Request To Revise Certain Exceptions Airbus and Virgin America requested that the NPRM be revised to allow airplanes that have utilized FAA Alternative Methods of Compliance (AMOC) ANM-116-13-273R1 for probes having P/N C16291AB to be in compliance with the proposed requirements. Virgin America and Airbus stated that the language in paragraphs (l), (m)(2), (n), and (q) of the proposed AD conflict with the language specified in FAA AMOC ANM-116- 13-273R1. We agree to revise this AD to address the commenters' request. FAA AMOC ANM-116-13-273R1 is limited to certain serial numbers that have passed the inspection and test. We have revised paragraphs (l), (m)(2), (n), and (q) of this AD to clarify the exception in FAA AMOC ANM-116- 13-273R1. Request To Incorporate the Latest Service Information Airbus requested that the latest service information be used in the AD and credit given for previous actions done before the effective date of this AD. We agree to incorporate the latest service information in this AD. Accordingly, we have revised paragraph (g)(1) of this AD; the introductory text to paragraph (k) of this AD, and paragraphs (l)(1), (m), and (n) of this AD. For Airbus Service Bulletin A320-34-1415, Revision 04, dated July 30, 2015; Airbus Service Bulletin A320-34-1610, Revision 01, dated July 30, 2015; and Airbus Service Bulletin A320-34- 1564, Revision 01, dated August 26, 2013; the changes are minor and do not add work to this AD. Thales Service Bulletin C16291A-34-007, Revision 04, dated October 11, 2012, describes procedures for inspecting, re-identifying, and testing certain AOA sensors, and does not add work to this AD. We have also revised paragraph (q) of this AD to give credit for previous actions done before the effective date of this AD using earlier versions of service information. Request for Credit for Previous Actions Virgin America requested that the FAA include Airbus Service Bulletin A320-34-1452, dated January 29, 2010 (as specified in paragraph (g) of AD 2013-06-03 to inspect and replace the affected probe P/N C16291AA with P/N C16291AB), in paragraph (q), ``Credit for Previous Actions,'' of the proposed AD. Virgin America stated that these actions have resulted in installing compliant C16291AB probes in the affected positions prior to the effective date of the AD. We disagree with Virgin America with allowing use of Airbus Service Bulletin A320-34-1452, dated January 29, 2010, for accomplishment of the installation of the probe P/N C16291AB. There are certain probe P/ Ns C16291AB having a serial number specified in Thales Service Bulletin C16291A-34-007, Revision 04, dated October 11, 2012, and these probes may not be installed unless they have been inspected and re-identified, and have passed a functional test, in accordance with the following service information:Thales Service Bulletin C16291A-34-007, Revision 04, dated October 11, 2012. Thales Service Bulletin C16291A-34-007, Revision 03, dated April 10, 2012. Thales Service Bulletin C16291A-34-007, Revision 02, dated December 16, 2011. Thales Service Bulletin C16291A-34-007, Revision 01, dated December 03, 2009. Conclusion We reviewed the available data, including the comments received, and determined that air safety and the public interest require adopting this 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 NPRM for correcting the unsafe condition; and [[Page 40677]] Do not add any additional burden upon the public than was already proposed in the NPRM. We also determined that these changes will not increase the economic burden on any operator or increase the scope of this AD. Related Service Information Under 1 CFR Part 51 We have reviewed the following Airbus service information: Airbus Service Bulletin A320-34-1415, Revision 04, dated July 30, 2015. This service information describes procedures for performing a detailed inspection and a functional heating test for discrepancies on certain AOA sensors, and replacing the affected AOA sensors. Airbus Service Bulletin A320-34-1444, Revision 01, dated March 17, 2011. This service information describes procedures for replacing certain SEXTANT/THOMSON AOA sensors. Airbus Service Bulletin A320-34-1564, Revision 01, dated August 26, 2013. This service information describes procedures for installing AOA sensor plates having a certain part number. Airbus Service Bulletin A320-34-1610, Revision 01, dated July 30, 2015. This service information describes procedures for replacing certain UTAS AOA sensors. We have reviewed the following Thales service information, which describes procedures for inspecting, re-identifying, and testing certain AOA sensors. These documents are distinct due to editorial revisions. Thales Service Bulletin C16291A-34-007, Revision 04, dated October 11, 2012. Thales Service Bulletin C16291A-34-007, Revision 03, dated April 10, 2012. Thales Service Bulletin C16291A-34-007, Revision 02, dated December 16, 2011. Thales Service Bulletin C16291A-34-007, Revision 01, dated December 03, 2009. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section. Costs of Compliance We estimate that this AD affects 959 airplanes of U.S. registry. We estimate the following costs to comply with this AD: Estimated Costs ---------------------------------------------------------------------------------------------------------------- Cost per Cost on U.S. Action Labor cost Parts cost product operators ---------------------------------------------------------------------------------------------------------------- Replacement (retained actions from 8 work-hours x $85 $0................... $680 $652,120 AD 2013-19-09). per hour = $680. Revising the AFM (retained actions 1 work-hour x $85 per $0................... 85 81,515 from AD 2014-25-51). hour = $85. Replacement and Inspection (new 5 work-hours x $85 The parts cost is 425 407,575 action). per hour = $425. unavailable. ---------------------------------------------------------------------------------------------------------------- We estimate the following costs to do any necessary replacements that would be required based on the results of the inspection. We have no way of determining the number of aircraft that might need these replacements: On-Condition Costs ---------------------------------------------------------------------------------------------------------------- Cost per Action Labor cost Parts cost product ---------------------------------------------------------------------------------------------------------------- Replacement............................ 5 work-hours x $85 per The parts cost is $425 hour = $425. unavailable. ---------------------------------------------------------------------------------------------------------------- According to the manufacturer, some of the costs of this 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. This AD is issued in accordance with authority delegated by the Executive Director, Aircraft Certification Service, as authorized by FAA Order 8000.51C. In accordance with that order, issuance of ADs is normally a function of the Compliance and Airworthiness Division, but during this transition period, the Executive Director has delegated the authority to issue ADs applicable to transport category airplanes to the Director of the System Oversight Division. 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 [[Page 40678]] under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39--AIRWORTHINESS DIRECTIVES 0 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. Sec. 39.13 [Amended] 0 2. The FAA amends Sec. 39.13 by 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: 2017-16-12 Airbus: Amendment 39-18989; Docket No. FAA-2016-9518; Product Identifier 2015-NM-091-AD. (a) Effective Date This AD is effective October 2, 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 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, Specific Delegation Approval Language, and New Service Information This paragraph restates the requirements of paragraph (j) of AD 2013-19-09, with a removed post-installation requirement, specific delegation approval language, and revised service information. 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 P/Ns 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, or Airbus Service Bulletin A320-34-1564, Revision 01, dated August 26, 2013. As of the effective date of this AD, only Airbus Service Bulletin A320-34-1564, Revision 01, dated August 26, 2013, may be used for accomplishment of the actions required by this paragraph. (2) Install P/N D3411007620000 or P/N D3411013520000, using a method approved by the Manager, International Section, Transport Standards Branch, 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 40679]] [GRAPHIC] [TIFF OMITTED] TR28AU17.022 (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, Revision 01, dated July 30, 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 (1) 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 paragraphs (l)(1)(i) or (l)(1)(ii) 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 sensor probes P/N C16291AB having a serial number specified in Thales Service Bulletin C16291A-34-007, Revision 04, dated October 11, 2012, may not be installed unless the AOA probe sensors have been inspected and re-identified, and have passed a functional test, in accordance with the Thales service information specified in paragraphs (l)(2)(i), (l)(2)(ii), (l)(2)(iii), or (l)(2)(iv) of this AD. (i) 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. (ii) 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. (2) As specified in paragraph (l)(1) of this AD, use the following Thales service information specified in paragraphs (l)(2)(i), (l)(2)(ii), (l)(2)(iii), or (l)(2)(iv) of this AD. (i) Thales Service Bulletin C16291A-34-007, Revision 04, dated October 11, 2012. (ii) Thales Service Bulletin C16291A-34-007, Revision 03, dated April 10, 2012. (iii) Thales Service Bulletin C16291A-34-007, Revision 02, dated December 16, 2011. (iv) Thales Service Bulletin C16291A-34-007, Revision 01, dated December 03, 2009. (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 04, [[Page 40680]] dated July 30, 2015. 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 04, dated July 30, 2015, 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 04, dated July 30, 2015. 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 heating test as specified in the Accomplishment Instructions of Airbus Service Bulletin A320-34-1415, Revision 04, dated July 30, 2015. (2) Replace with a Thales AOA sensor, P/N C16291AB, except AOA sensor probes P/N C16291AB having a serial number specified in Thales Service Bulletin C16291A-34-007, Revision 04, dated October 11, 2012, may not be installed unless the AOA probe sensors have been inspected and re-identified, and have passed a functional test, in accordance with the Thales service information specified in paragraphs (l)(2)(i), (l)(2)(ii), (l)(2)(iii), or (l)(2)(iv) of this AD. (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 sensor probes P/N C16291AB having a serial number specified in Thales Service Bulletin C16291A- 34-007, Revision 04, dated October 11, 2012, may not be installed, unless the AOA probe sensors have been inspected and re-identified, and have passed a functional test, in accordance with the Thales service information specified in paragraphs (l)(2)(i), (l)(2)(ii), (l)(2)(iii), or (l)(2)(iv) of this AD. (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, is 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 (1) This paragraph provides credit for the actions required by paragraph (k) of this AD, if those actions were performed before the effective date of this AD using Airbus Service Bulletin A320-34- 1610, dated March 31, 2015. (2) 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; except AOA sensor probes P/N C16291AB having a serial number specified in Thales Service Bulletin C16291A- 34-007, Revision 04, dated October 11, 2012, may not be installed unless the AOA probe sensors have been inspected and re-identified, and have passed a functional test, using the Thales service information specified in paragraphs (l)(2)(i), (l)(2)(ii), (l)(2)(iii), or (l)(2)(iv) of this AD. (3) This paragraph provides credit for the actions required by paragraph (m) of this AD, if those actions were performed before the effective date of this AD using Airbus Service Bulletin A320-34- 1415, Revision 03, July 8, 2010. (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 Section, Transport Standards Branch, FAA; or EASA; or Airbus's EASA DOA. (2) The installation must be accomplished using a method approved by the Manager, International Section, Transport Standards Branch, 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 Section, Transport Standards Branch, 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 the attention of the person identified in paragraph (u)(2) of this AD. 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 Section, Transport Standards Branch, 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 Provisions for Special Flight Permits (1) For the requirements of paragraphs (g), (h), and (i) of this AD: 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 the requirements of paragraphs (j) of this AD: 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 more information about this AD, contact Sanjay Ralhan, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1405; fax 425-227-1149. [[Page 40681]] (3) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (v)(5) and (v)(6) of this AD. (v) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless this AD specifies otherwise. (3) The following service information was approved for IBR on October 2, 2017. (i) Airbus Service Bulletin A320-34-1415, Revision 04, dated July 30, 2015. (ii) Airbus Service Bulletin A320-34-1444, Revision 01, dated March 17, 2011. (iii) Airbus Service Bulletin A320-34-1564, Revision 01, dated August 26, 2013. (iv) Airbus Service Bulletin A320-34-1610, Revision 01, dated July 30, 2015. (v) Thales Service Bulletin C16291A-34-007, Revision 04, dated October 11, 2012. (vi) Thales Service Bulletin C16291A-34-007, Revision 03, dated April 10, 2012. (vii) Thales Service Bulletin C16291A-34-007, Revision 02, dated December 16, 2011. (viii) Thales Service Bulletin C16291A-34-007, Revision 01, dated December 03, 2009. (4) The following service information was approved for IBR on November 6, 2013, Amendment 39-17591 (78 FR 60667, October 2, 2013). (i) Airbus Mandatory Service Bulletin A320-34-1564, including Appendix 01, dated January 25, 2013. (ii) Reserved. (5) 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. (6) You may view this service information at the FAA, Transport Standards Branch, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221. (7) 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 August 2, 2017. Jeffrey E. Duven, Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2017-16860 Filed 8-25-17; 8:45 am] BILLING CODE P
![Federal Register / Vol. 82, No. 165 / Monday, August 28, 2017 / Rules and Regulations 40675
(3) An AMOC that provides an acceptable Issued in Renton, Washington, on August 61 93 36 96; fax +33 5 61 93 44 51; email
level of safety may be used for any repair, 11, 2017. account.airworth-eas@airbus.com;
modification, or alteration required by this Dionne Palermo, Internet http://www.airbus.com. You
AD if it is approved by the Boeing may view this referenced service
Acting Director, System Oversight Division,
Commercial Airplanes Organization
Aircraft Certification Service. information at the FAA, Transport
Designation Authorization (ODA) that has
been authorized by the Manager, Seattle ACO [FR Doc. 2017–17591 Filed 8–25–17; 8:45 am] Standards Branch, 1601 Lind Avenue
Branch, to make those findings. To be BILLING CODE 4910–13–P SW., Renton, WA. For information on
approved, the repair method, modification the availability of this material at the
deviation, or alteration deviation must meet FAA, call 425–227–1221. It is also
the certification basis of the airplane, and the DEPARTMENT OF TRANSPORTATION available on the Internet at http://
approval must specifically refer to this AD. www.regulations.gov by searching for
(4) Except as required by paragraph (h)(2) Federal Aviation Administration and locating Docket No. FAA–2016–
of this AD: For service information that 9518.
contains steps that are labeled as RC, the 14 CFR Part 39
provisions of paragraphs (i)(4)(i) and (i)(4)(ii) Examining the AD Docket
of this AD apply. [Docket No. FAA–2016–9518; Product
(i) The steps labeled as RC, including Identifier 2015–NM–091–AD; Amendment You may examine the AD docket on
substeps under an RC step and any figures 39–18989; AD 2017–16–12] the Internet at http://
identified in an RC step, must be done to www.regulations.gov by searching for
RIN 2120–AA64
comply with the AD. If a step or substep is and locating Docket No. FAA–2016–
labeled ‘‘RC Exempt,’’ then the RC 9518; or in person at the Docket
requirement is removed from that step or
Airworthiness Directives; Airbus
Airplanes Management Facility between 9 a.m.
substep. An AMOC is required for any and 5 p.m., Monday through Friday,
deviations to RC steps, including substeps AGENCY: Federal Aviation except Federal holidays. The AD docket
and identified figures.
(ii) Steps not labeled as RC may be
Administration (FAA), Department of contains this AD, the regulatory
deviated from using accepted methods in Transportation (DOT). evaluation, any comments received, and
accordance with the operator’s maintenance ACTION: Final rule. other information. The address for the
or inspection program without obtaining Docket Office (telephone 800–647–5527)
approval of an AMOC, provided the RC steps, SUMMARY: We are superseding is Docket Management Facility, U.S.
including substeps and identified figures, can Airworthiness Directive (AD) 2013–19– Department of Transportation, Docket
still be done as specified, and the airplane 09 and AD 2014–25–51, which applied Operations, M–30, West Building
can be put back in an airworthy condition. to all Airbus Model A318, A319, A320, Ground Floor, Room W12–140, 1200
(j) Related Information and A321 series airplanes. AD 2013–19– New Jersey Avenue SE., Washington,
For more information about this AD,
09 required replacing Angle of Attack DC 20590.
contact Wayne Lockett, Aerospace Engineer, (AOA) sensor conic plates with AOA FOR FURTHER INFORMATION CONTACT:
Airframe Section, FAA, Seattle ACO Branch, sensor flat plates. AD 2014–25–51 Sanjay Ralhan, Aerospace Engineer,
1601 Lind Avenue SW., Renton, WA 98057– required revising the airplane flight International Section, Transport
3356; phone: 425–917–6447; fax: 425–917– manual (AFM) to advise the flightcrew Standards Branch, FAA, 1601 Lind
6590; email: wayne.lockett@faa.gov. of emergency procedures for abnormal Avenue SW., Renton, WA 98057–3356;
(k) Material Incorporated by Reference Alpha Protection (Alpha Prot). This new telephone 425–227–1405; fax 425–227–
AD requires replacing certain AOA 1149.
(1) The Director of the Federal Register
approved the incorporation by reference
sensors; and doing a detailed inspection
SUPPLEMENTARY INFORMATION:
(IBR) of the service information listed in this and a functional heating test for
paragraph under 5 U.S.C. 552(a) and 1 CFR discrepancies on certain AOA sensors, Discussion
part 51. and replacing the affected AOA sensors. We issued a notice of proposed
(2) You must use this service information This AD was prompted by a report rulemaking (NPRM) to amend 14 CFR
as applicable to do the actions required by indicating that a Model A321 airplane
this AD, unless the AD specifies otherwise. part 39 to supersede AD 2013–19–09,
encountered a blockage of two AOA Amendment 39–17591 (78 FR 60667,
(i) Boeing Alert Service Bulletin 767– probes during climb, leading to
53A0275, dated January 5, 2017. October 2, 2013) (‘‘AD 2013–19–09’’),
activation of the Alpha Prot while the and AD 2014–25–51, Amendment 39–
(ii) Reserved.
(3) For Boeing service information
Mach number increased. We are issuing 18067 (80 FR 3153, January 22, 2015)
identified in this AD, contact Boeing this AD to address the unsafe condition (‘‘AD 2014–25–51’’). AD 2013–19–09
Commercial Airplanes, Attention: on these products. and AD 2014–25–51 applied to all
Contractual & Data Services (C&DS), 2600 DATES: This AD is effective October 2, Airbus Model A318, A319, A320, and
Westminster Blvd., MC 110–SK57, Seal 2017. A321 series airplanes. The NPRM
Beach, CA 90740–5600; telephone 562–797– The Director of the Federal Register
1717; Internet https://
published in the Federal Register on
approved the incorporation by reference December 28, 2016 (81 FR 95531). The
www.myboeingfleet.com.
(4) You may view this service information
of certain publications listed in this AD NPRM was prompted by a report
at the FAA, Transport Standards Branch, as of October 2, 2017. indicating that an Airbus Model A321
1601 Lind Avenue SW., Renton, WA. For The Director of the Federal Register airplane encountered a blockage of two
information on the availability of this approved the incorporation by reference AOA probes during climb, leading to
asabaliauskas on DSKBBXCHB2PROD with RULES
material at the FAA, call 425–227–1221. of certain other publications listed in activation of the Alpha Prot while the
(5) You may view this service information this AD as of November 6, 2013 (78 FR Mach number increased. The NPRM
that is incorporated by reference at the 60667, October 2, 2013). proposed to continue to require
National Archives and Records
Administration (NARA). For information on
ADDRESSES: For service information replacing AOA sensor conic plates with
the availability of this material at NARA, call identified in this final rule, contact AOA sensor flat plates and revising the
202–741–6030, or go to: http:// Airbus, Airworthiness Office—EIAS, 1 AFM to advise the flight crew of
www.archives.gov/federal-register/cfr/ibr- Rond Point Maurice Bellonte, 31707 emergency procedures for abnormal
locations.html. Blagnac Cedex, France; telephone +33 5 Alpha Prot. The NPRM also proposed to
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![40676 Federal Register / Vol. 82, No. 165 / Monday, August 28, 2017 / Rules and Regulations
continue to require replacing certain tests of certain Thales AOA sensors and 1610, Revision 01, dated July 30, 2015;
AOA sensors; and doing a detailed provided an optional terminating action for and Airbus Service Bulletin A320–34–
inspection and a functional heating test those inspections. 1564, Revision 01, dated August 26,
Since EASA AD 2015–0087 was issued, 2013; the changes are minor and do not
for discrepancies on certain AOA
based on further analysis results, Airbus
sensors, and replacing the affected AOA issued Operators Information Transmission
add work to this AD. Thales Service
sensors. We are issuing this AD to (OIT) Ref. 999.0015/15 Revision 1, Bulletin C16291A–34–007, Revision 04,
prevent a pitch down order due to instructing operators to speed up the removal dated October 11, 2012, describes
abnormal activation of the Alpha Prot. from service of UTAS P/N 0861ED2 AOA procedures for inspecting, re-
An abnormal Alpha Prot, if not sensors. identifying, and testing certain AOA
corrected, could result in loss of control For the reasons described above, this sensors, and does not add work to this
of the airplane. [EASA] AD retains the requirements of EASA AD. We have also revised paragraph (q)
The European Aviation Safety Agency AD 2015–0087, which is superseded, but of this AD to give credit for previous
(EASA), which is the Technical Agent reduces the compliance times for airplanes actions done before the effective date of
with UTAS P/N 0861ED2 AOA sensors
for the Member States of the European this AD using earlier versions of service
installed.
Union, has issued EASA Airworthiness information.
Directive 2015–0135, dated July 8, 2015 You may examine the MCAI in the
(referred to after this as the Mandatory AD docket on the Internet at http:// Request for Credit for Previous Actions
Continuing Airworthiness Information, www.regulations.gov by searching for Virgin America requested that the
or ‘‘the MCAI’’), to correct an unsafe and locating Docket No. FAA–2016– FAA include Airbus Service Bulletin
condition for all Airbus Model A318, 9518. A320–34–1452, dated January 29, 2010
A319, A320, and A321 series airplanes. Comments (as specified in paragraph (g) of AD
The MCAI states: 2013–06–03 to inspect and replace the
We gave the public the opportunity to affected probe P/N C16291AA with P/N
An occurrence was reported where an participate in developing this AD. The
Airbus A321 aeroplane encountered a C16291AB), in paragraph (q), ‘‘Credit for
blockage of two Angle of Attack (AOA) following presents the comments Previous Actions,’’ of the proposed AD.
probes during climb, leading to activation of received on the NPRM and the FAA’s Virgin America stated that these actions
the Alpha Protection (Alpha Prot) while the response to each comment. Air Line have resulted in installing compliant
Mach number increased. The flight crew Pilots Association, International stated C16291AB probes in the affected
managed to regain full control and the flight that it supported the NPRM. positions prior to the effective date of
landed uneventfully.
Request To Revise Certain Exceptions the AD.
When Alpha Prot is activated due to
blocked AOA probes, the flight control laws We disagree with Virgin America with
Airbus and Virgin America requested
order a continuous nose down pitch rate that, allowing use of Airbus Service Bulletin
that the NPRM be revised to allow
in a worst case scenario, cannot be stopped A320–34–1452, dated January 29, 2010,
airplanes that have utilized FAA
with backward sidestick inputs, even in the for accomplishment of the installation
Alternative Methods of Compliance
full backward position. If the Mach number of the probe P/N C16291AB. There are
increases during a nose down order, the AOA (AMOC) ANM–116–13–273R1 for
certain probe P/Ns C16291AB having a
value of the Alpha Prot will continue to probes having P/N C16291AB to be in
serial number specified in Thales
decrease. As a result, the flight control laws compliance with the proposed
Service Bulletin C16291A–34–007,
will continue to order a nose down pitch requirements. Virgin America and
Revision 04, dated October 11, 2012,
rate, even if the speed is above minimum Airbus stated that the language in
selectable speed, known as VLS. and these probes may not be installed
paragraphs (l), (m)(2), (n), and (q) of the
This condition, if not corrected, could unless they have been inspected and re-
proposed AD conflict with the language
result in loss of control of the airplane. identified, and have passed a functional
specified in FAA AMOC ANM–116–13–
Investigation results indicated that A320 test, in accordance with the following
273R1.
family airplanes equipped with certain UTC service information:
We agree to revise this AD to address
Aerospace (UTAS, formerly known as
the commenters’ request. FAA AMOC • Thales Service Bulletin C16291A–
Goodrich) AOA sensors, or equipped with 34–007, Revision 04, dated October 11,
certain SEXTANT/THOMSON AOA sensors, ANM–116–13–273R1 is limited to
certain serial numbers that have passed 2012.
appear to have a greater susceptibility to
adverse environmental conditions than the inspection and test. We have revised • Thales Service Bulletin C16291A–
airplanes equipped with the latest Thales paragraphs (l), (m)(2), (n), and (q) of this 34–007, Revision 03, dated April 10,
AOA sensor, Part Number (P/N) C16291AB, AD to clarify the exception in FAA 2012.
which was designed to improve A320 AMOC ANM–116–13–273R1. • Thales Service Bulletin C16291A–
airplane AOA indication behaviour in heavy 34–007, Revision 02, dated December
rain conditions. Request To Incorporate the Latest 16, 2011.
Having determined that replacement of Service Information • Thales Service Bulletin C16291A–
these AOA sensors is necessary to achieve
and maintain the required safety level of the Airbus requested that the latest 34–007, Revision 01, dated December
airplane, EASA issued AD 2015–0087, service information be used in the AD 03, 2009.
retaining the requirements of EASA AD and credit given for previous actions Conclusion
2012–0236R1 [which corresponds to FAA AD done before the effective date of this
2013–06–03], [EASA] AD 2013–0022 AD. We reviewed the available data,
(partially) [which corresponds to FAA AD We agree to incorporate the latest including the comments received, and
asabaliauskas on DSKBBXCHB2PROD with RULES
2013–19–09], and [EASA] AD 2014–0266–E service information in this AD. determined that air safety and the
[which corresponds to FAA AD 2014–25–51], Accordingly, we have revised paragraph public interest require adopting this AD
which were superseded, and requiring (g)(1) of this AD; the introductory text with the changes described previously
modification of the airplanes by replacement
to paragraph (k) of this AD, and and minor editorial changes. We have
of the affected P/N sensors, and, after
modification, prohibiting (re-)installation of paragraphs (l)(1), (m), and (n) of this determined that these changes:
those P/N AOA sensors. That [EASA] AD AD. For Airbus Service Bulletin A320– • Are consistent with the intent that
also required repetitive detailed visual 34–1415, Revision 04, dated July 30, was proposed in the NPRM for
inspections (DET) and functional heating 2015; Airbus Service Bulletin A320–34– correcting the unsafe condition; and
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![40678 Federal Register / Vol. 82, No. 165 / Monday, August 28, 2017 / Rules and Regulations
under the criteria of the Regulatory (4) Airbus Model A321–111, –112, –131, Airbus’s EASA Design Organization
Flexibility Act. –211, –212, –213, –231, and –232 airplanes. Approval (DOA).
List of Subjects in 14 CFR Part 39 (d) Subject (h) Retained Exception, With No Changes
Air Transport Association (ATA) of This paragraph restates the exception
Air transportation, Aircraft, Aviation America Code 34, Navigation. provided by paragraph (k) of AD 2013–19–09,
safety, Incorporation by reference, with no changes. An airplane on which
Safety. (e) Reason
Airbus modification 154863 (installation of
This AD was prompted by a report AOA sensor flat plate) and modification
Adoption of the Amendment indicating that an Airbus Model A321 154864 (coating protection) have been
Accordingly, under the authority airplane encountered a blockage of two Angle embodied in production is not affected by the
delegated to me by the Administrator, of Attack (AOA) probes during climb, leading requirements of paragraph (g) of this AD,
to activation of the Alpha Protection (Alpha provided that, since first flight, no AOA
the FAA amends 14 CFR part 39 as Prot) while the Mach number increased. We
follows: sensor conic plate having P/N
are issuing this AD to prevent a pitch down F3411060200000 or P/N F3411060900000
order due to abnormal activation of the has been installed on that airplane.
PART 39—AIRWORTHINESS Alpha Prot. An abnormal Alpha Prot, if not
DIRECTIVES corrected, could result in loss of control of (i) Retained Parts Installation Prohibition,
the airplane. With No Changes
■ 1. The authority citation for part 39
(f) Compliance This paragraph restates the requirements of
continues to read as follows: paragraph (m) of AD 2013–19–09, with no
Comply with this AD within the
Authority: 49 U.S.C. 106(g), 40113, 44701. changes.
compliance times specified, unless already
(1) For any airplane that has AOA sensor
§ 39.13 [Amended] done.
flat plates installed: As of November 6, 2013
■ 2. The FAA amends § 39.13 by (g) Retained New Flat Plate Installation, (the effective date of AD 2013–19–09), do not
removing Airworthiness Directive (AD) With Removed Post-Installation install any AOA sensor conic plate having P/
Requirement, Specific Delegation Approval N F3411060200000 or P/N F3411060900000,
2013–19–09, Amendment 39–17591 (78 Language, and New Service Information and do not use any AOA protection cover
FR 60667, October 2, 2013); and AD having P/N 98D34203003000.
2014–25–51, Amendment 39–18067 (80 This paragraph restates the requirements of
paragraph (j) of AD 2013–19–09, with a (2) For any airplane that has AOA sensor
FR 3153, January 22, 2015); and adding removed post-installation requirement, conic plates installed: As of November 6,
the following new AD: specific delegation approval language, and 2013 (the effective date of AD 2013–19–09),
2017–16–12 Airbus: Amendment 39–18989; revised service information. Within 5 months after modification of the airplane as required
Docket No. FAA–2016–9518; Product after November 6, 2013 (the effective date of by paragraph (g) of this AD, do not install any
Identifier 2015–NM–091–AD. AD 2013–19–09), remove all AOA sensor AOA sensor conic plate having P/N
conic plates having part number (P/N) F3411060200000 or P/N F3411060900000,
(a) Effective Date F3411060200000 or P/N F3411060900000, and do not use any AOA protection cover
This AD is effective October 2, 2017. and install AOA sensor flat plates having P/ having P/N 98D34203003000.
Ns specified in paragraph (g)(1) or (g)(2) of
(b) Affected ADs (j) Retained Revision of Airplane Flight
this AD, except as specified in paragraph (h)
Manual (AFM), With No Changes
(1) This AD replaces AD 2013–19–09, of this AD. Install the AOA sensor plates in
Amendment 39–17591 (78 FR 60667, October accordance with the applicable method This paragraph restates the requirements of
2, 2013) (‘‘AD 2013–19–09’’); and AD 2014– specified in paragraph (g)(1) or (g)(2) of this paragraph (g) of AD 2014–25–51, with no
25–51, Amendment 39–18067 (80 FR 3153, AD. changes. Within 2 days after February 6, 2015
January 22, 2015) (‘‘AD 2014–25–51’’). (1) Install P/N D3411013520200 in (the effective date of AD 2014–25–51), revise
(2) This AD affects AD 2013–06–03, accordance with the Accomplishment the AFM to incorporate procedures to
Amendment 39–17399 (78 FR 19085, March Instructions of Airbus Mandatory Service address undue activation of Alpha Prot by
29, 2013) (‘‘AD 2013–06–03’’). Bulletin A320–34–1564, including Appendix inserting the text specified in figure 1 to
01, dated January 25, 2013, or Airbus Service paragraph (j) of this AD into the Emergency
(c) Applicability Bulletin A320–34–1564, Revision 01, dated Procedures section of the applicable AFM, to
This AD applies to the Airbus airplanes August 26, 2013. As of the effective date of advise the flight crew of emergency
listed in paragraphs (c)(1) through (c)(4) of this AD, only Airbus Service Bulletin A320– procedures for abnormal Alpha Prot. This
this AD, certificated in any category, all 34–1564, Revision 01, dated August 26, 2013, may be accomplished by inserting a copy of
manufacturer serial numbers. may be used for accomplishment of the this AD into the AFM. When a statement
(1) Airbus Model A318–111, –112, –121, actions required by this paragraph. identical to the text specified in figure 1 to
and –122 airplanes. (2) Install P/N D3411007620000 or P/N paragraph (j) of this AD is included in the
(2) Airbus Model A319–111, –112, –113, D3411013520000, using a method approved general revisions of the AFM, the general
–114, –115, –131, –132, and –133 airplanes. by the Manager, International Section, revisions may be inserted in the AFM, and
(3) Airbus Model A320–211, –212, –214, Transport Standards Branch, FAA; or the the text specified in figure 1 to paragraph (j)
–231, –232, and –233 airplanes. European Aviation Safety Agency (EASA); or of this AD may be removed.
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(3) Service information identified in this DEPARTMENT OF TRANSPORTATION availability of this material at the FAA,
AD that is not incorporated by reference is call 781–238–7125. It is also available
available at the addresses specified in Federal Aviation Administration on the Internet at http://
paragraphs (v)(5) and (v)(6) of this AD. www.regulations.gov by searching for
(v) Material Incorporated by Reference
14 CFR Part 39 and locating Docket No. FAA–2017–
[Docket No. FAA–2017–0652; Product 0652.
(1) The Director of the Federal Register
approved the incorporation by reference Identifier 2017–NE–18–AD; Amendment 39– Examining the AD Docket
18997; AD 2017–17–07]
(IBR) of the service information listed in this You may examine the AD docket on
paragraph under 5 U.S.C. 552(a) and 1 CFR RIN 2120–AA64 the Internet at http://
part 51. www.regulations.gov by searching for
(2) You must use this service information Airworthiness Directives; Rolls-Royce
and locating Docket No. FAA–2017–
as applicable to do the actions required by plc Turbofan Engines
0652; or in person at the Docket
this AD, unless this AD specifies otherwise.
AGENCY: Federal Aviation Operations office between 9 a.m. and 5
(3) The following service information was
Administration (FAA), DOT. p.m., Monday through Friday, except
approved for IBR on October 2, 2017.
ACTION: Final rule; request for Federal holidays. The AD docket
(i) Airbus Service Bulletin A320–34–1415,
comments. contains this AD, the mandatory
Revision 04, dated July 30, 2015.
(ii) Airbus Service Bulletin A320–34–1444,
continuing airworthiness information
SUMMARY: We are adopting a new (MCAI), regulatory evaluation, any
Revision 01, dated March 17, 2011.
airworthiness directive (AD) for certain comments received, and other
(iii) Airbus Service Bulletin A320–34–
Rolls-Royce plc (RR) Trent XWB–75, information. The address for the Docket
1564, Revision 01, dated August 26, 2013.
Trent XWB–79, Trent XWB–79B, and Office (phone: 800–647–5527) is in the
(iv) Airbus Service Bulletin A320–34–
1610, Revision 01, dated July 30, 2015.
Trent XWB–84 turbofan engines. This ADDRESSES section. Comments will be
(v) Thales Service Bulletin C16291A–34–
AD requires inspection of the available in the AD docket shortly after
007, Revision 04, dated October 11, 2012.
intermediate-pressure (IP) turbine stage receipt.
(vi) Thales Service Bulletin C16291A–34– 2 locking plates. This AD was prompted FOR FURTHER INFORMATION CONTACT:
007, Revision 03, dated April 10, 2012. by a report of several IP turbine stage 2 Robert Green, Aerospace Engineer, FAA,
(vii) Thales Service Bulletin C16291A–34– locking plates cracked during module ECO Branch, Compliance and
007, Revision 02, dated December 16, 2011. assembly. We are issuing this AD to Airworthiness Division, 1200 District
(viii) Thales Service Bulletin C16291A–34– correct the unsafe condition on these Avenue, Burlington, MA 01803; phone:
007, Revision 01, dated December 03, 2009. products. 781–238–7754; fax: 781–238–7199;
(4) The following service information was DATES: This AD becomes effective email: robert.green@faa.gov.
approved for IBR on November 6, 2013, September 12, 2017. SUPPLEMENTARY INFORMATION:
Amendment 39–17591 (78 FR 60667, October The Director of the Federal Register
2, 2013). approved the incorporation by reference Comments Invited
(i) Airbus Mandatory Service Bulletin of a certain publication listed in this AD This AD is a final rule that involves
A320–34–1564, including Appendix 01, as of September 12, 2017. requirements affecting flight safety, and
dated January 25, 2013. We must receive comments on this we did not precede it by notice and
(ii) Reserved. AD by October 12, 2017. opportunity for public comment. We
(5) For service information identified in ADDRESSES: You may send comments by invite you to send any written relevant
this AD, contact Airbus, Airworthiness any of the following methods: data, views, or arguments about this AD.
Office—EIAS, 1 Rond Point Maurice • Federal eRulemaking Portal: Go to Send your comments to an address
Bellonte, 31707 Blagnac Cedex, France;
http://www.regulations.gov. Follow the listed under the ADDRESSES section.
telephone +33 5 61 93 36 96; fax +33 5 61
instructions for submitting comments. Include ‘‘Docket No. FAA–2017–0652;
93 44 51; email account.airworth-eas@
• Mail: U.S. Department of Directorate Identifier 2017–NE–18–AD’’
airbus.com; Internet http://www.airbus.com.
Transportation, 1200 New Jersey at the beginning of your comments. We
(6) You may view this service information
Avenue SE., West Building Ground specifically invite comments on the
at the FAA, Transport Standards Branch,
Floor, Room W12–140, Washington, DC overall regulatory, economic,
1601 Lind Avenue SW., Renton, WA. For
20590–0001. environmental, and energy aspects of
information on the availability of this
• Hand Delivery: Deliver to Mail this AD. We will consider all comments
material at the FAA, call 425–227–1221.
(7) You may view this service information
address above between 9 a.m. and 5 received by the closing date and may
that is incorporated by reference at the
p.m., Monday through Friday, except amend this AD because of those
National Archives and Records
Federal holidays. comments.
Administration (NARA). For information on
• Fax: 202–493–2251. We will post all comments we
the availability of this material at NARA, call
For service information identified in receive, without change, to http://
202–741–6030, or go to: http:// this AD, contact Rolls-Royce plc, www.regulations.gov, including any
www.archives.gov/federal-register/cfr/ibr- Corporate Communications, P.O. Box personal information you provide. We
locations.html. 31, Derby, England, DE24 8BJ; phone: will also post a report summarizing each
011–44–1332–242424; fax: 011–44– substantive verbal contact with FAA
Issued in Renton, Washington, on August 1332–249936; email: http://www.rolls- personnel concerning this AD.
asabaliauskas on DSKBBXCHB2PROD with RULES
2, 2017. royce.com/contact/civil_team.jsp;
Jeffrey E. Duven, Internet: https://customers.rolls- Discussion
Director, System Oversight Division, Aircraft royce.com/public/rollsroycecare. You The European Aviation Safety Agency
Certification Service. may view this service information at the (EASA), which is the Technical Agent
[FR Doc. 2017–16860 Filed 8–25–17; 8:45 am] FAA, Engine and Propeller Standards for the Member States of the European
BILLING CODE P Branch, Policy and Innovation Division, Community, has issued EASA AD 2017–
1200 District Avenue, Burlington, MA 0088, dated May 16, 2017 (referred to
01803. For information on the hereinafter as ‘‘the MCAI’’), to correct an
VerDate Sep<11>2014 17:58 Aug 25, 2017 Jkt 241001 PO 00000 Frm 00013 Fmt 4700 Sfmt 4700 E:\FR\FM\28AUR1.SGM 28AUR1](https://thefederalregister.org/doc/82_FR_40840/page/7.svg)
Document Created: 2017-08-28 11:29:50
Document Modified: 2017-08-28 11:29:50
| 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 | Rules and Regulations | |
| Action | Final rule. | |
| Dates | This AD is effective October 2, 2017. | |
| Contact | Sanjay Ralhan, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1405; fax 425-227- 1149. | |
| FR Citation | 82 FR 40675 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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