81 FR 21722 - Airworthiness Directives; Airbus Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 81, Issue 71 (April 13, 2016)
Federal Aviation Administration
Federal Register Volume 81, Issue 71 (April 13, 2016)
| Page Range | 21722-21726 | |
| FR Document | 2016-08267 |
[Federal Register Volume 81, Number 71 (Wednesday, April 13, 2016)] [Rules and Regulations] [Pages 21722-21726] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2016-08267] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2015-4810; Directorate Identifier 2015-NM-090-AD; Amendment 39-18475; AD 2016-07-30] RIN 2120-AA64 Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. ----------------------------------------------------------------------- SUMMARY: We are adopting a new airworthiness directive (AD) for all Airbus Model A330-200, -200 Freighter, and -300 series airplanes, and all Airbus Model A340-200, -300, -500, and -600 series airplanes. This AD was prompted by a report of blockage of Angle of Attack (AOA) probes during climb, leading to activation of the Alpha Protection (Alpha Prot) while the Mach number increased. This activation could cause a continuous nose-down pitch rate that cannot be stopped with backward sidestick input, even in the full backward position. For certain airplanes, this AD requires replacing certain AOA sensors (probes) with [[Page 21723]] certain new AOA sensors. For certain other airplanes, this AD also requires inspections and functional heat testing of certain AOA sensors for discrepancies, and replacement if necessary. We are issuing this AD to prevent erroneous AOA information and Alpha Prot activation due to blocked AOA probes, which could result in a continuous nose-down command and loss of control of the airplane. DATES: This AD becomes effective May 18, 2016. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of May 18, 2016. ADDRESSES: For service information identified in this final rule, contact Airbus SAS, Airworthiness Office--EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 80; email [email protected]; Internet http://www.airbus.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015- 4810. Examining the AD Docket You may examine the AD docket on the Internet at http://www.regulations.gov/#!docketDetail;D=FAA-2015-4810; 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 street address for the Docket Operations 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. FOR FURTHER INFORMATION CONTACT: Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1138; fax 425-227-1149. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to all Airbus Model A330-200, -200 Freighter, and -300 series airplanes; and all Airbus Model A340- 200, -300, -500, and -600 series airplanes. The NPRM published in the Federal Register on November 12, 2015 (80 FR 69899) (``the NPRM''). The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2015-0134, 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 A330-200, -200 Freighter, and -300 series airplanes; and all Model A340-200, -300, -500, and -600 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. It was determined that the affected AOA probes are also fitted on A330 and A340 aeroplanes. 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 aeroplane. Investigation results indicated that aeroplanes 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 aeroplanes equipped with the latest Thales AOA sensor, Part Number (P/N) C16291AB, which was designed to improve 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 aeroplane, EASA issued [an AD ***], to require modification of the aeroplanes by replacement of the affected P/N sensors, and, after modification, prohibits (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 2015-0089 was issued, based on further analysis results, Airbus issued Operators Information Transmission (OIT) Ref. 999.0017/15 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 ***], which is superseded, but reduces the compliance times for aeroplanes 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-2015- 4810. Actions Since the NPRM Was Issued Since we issued the NPRM Airbus has issued the following service information:Service Bulletin A330-34-3215, Revision 03, dated July 23, 2015. Service Bulletin A340-34-4215, Revision 03, dated July 27, 2015. Service Bulletin A340-34-5062, Revision 02, dated July 24, 2015. Explanation of Certain Changes to the NPRM We have revised paragraph (j) of this AD to refer to this revised service information. We have also added a new paragraph (l) to this AD, and reidentified subsequent paragraphs, to give credit for doing the actions using the following service information: Airbus Service Bulletin A330-34-3215, Revision 02, dated March 29, 2010. Airbus Service Bulletin A340-34-4215, Revision 02, dated March 29, 2010. Airbus Service Bulletin A340-34-5062, Revision 01, dated March 29, 2010. Comments We gave the public the opportunity to participate in developing this AD. The following presents the comment received on the NPRM and the FAA's response. Request To Reduce Certain Compliance Times Airbus asked that we reduce the compliance time from 22 months to 12 months for P/N 0861ED removal, and from 7 months to 3 months for P/N 0861ED2 removal. We do not agree with the request, as no supporting data was provided by the commenter. We contacted Airbus to determine if there was a justification for reducing the compliance times specified in the proposed AD. We noted that reducing the compliance times would necessitate (under the provisions of the Administrative Procedure Act) reissuing the notice, reopening the period for public comment, considering additional [[Page 21724]] comments subsequently received, and eventually issuing a final rule. Airbus stated it concurs with keeping the compliance times specified in the proposed AD. We have determined that further delay of this final rule is not appropriate. However, if additional data are presented that would justify a shorter compliance time, we may consider further rulemaking on this issue. In developing an appropriate compliance time, we considered the safety implications, parts availability, and normal maintenance schedules for timely accomplishment of replacing the AOA sensors, as well as the compliance times required by the EASA AD. In consideration of these factors, we have determined that the compliance time, as proposed, represents an appropriate time in which the AOA sensors can be replaced in a timely manner within the fleet, while still maintaining an adequate level of safety. Most ADs, including this one, permit operators to accomplish the requirements of an AD at a time earlier than the specified compliance time; therefore, an operator may choose to replace the AOA sensors earlier. We have not changed this final rule in this regard. Conclusion We reviewed the relevant data, considered the comment 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 minor changes: Are consistent with the intent that was proposed in the NPRM for correcting the unsafe condition; and Do not add any additional burden upon the public than was already proposed in the NPRM. Related Service Information Under 1 CFR Part 51 Airbus has issued the following service information: Service Bulletin A330-34-3215, Revision 03, dated July 23, 2015. Service Bulletin A330-34-3228, dated October 7, 2009. Service Bulletin A330-34-3315, dated March 26, 2015. Service Bulletin A340-34-4215, Revision 03, dated July 27, 2015. Service Bulletin A340-34-4234, dated October 7, 2009. Service Bulletin A340-34-4294, dated March 26, 2015. Service Bulletin A340-34-5062, Revision 02, dated July 24, 2015. Service Bulletin A340-34-5070, dated October 9, 2009. Service Bulletin A340-34-5105, dated March 26, 2015. The service information describes procedures for replacing certain pitot probes with certain new pitot probes. The service information also describes procedures for inspections and functional heat testing of certain pitot probes, and replacement if necessary. 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 55 airplanes of U.S. registry. We estimate the following costs to comply with this AD: Estimated Costs ---------------------------------------------------------------------------------------------------------------- Cost on U.S. Action Labor cost Parts cost Cost per product operators ---------------------------------------------------------------------------------------------------------------- Replacement....................... 5 work-hours x $85 $0 $425................. $23,375 per hour = $425. Inspection/test................... 3 work-hours x $85 0 255 per inspection/ 14,025 per hour = $255. test cycle. ---------------------------------------------------------------------------------------------------------------- We have received no definitive data that will enable us to provide a cost estimate for the on-condition actions specified in this AD. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA's authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. ``Subtitle VII: Aviation Programs,'' describes in more detail the scope of the Agency's authority. We are issuing this rulemaking under the authority described in ``Subtitle VII, Part A, Subpart III, Section 44701: General requirements.'' Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: 1. Is not a ``significant regulatory action'' under Executive Order 12866; 2. Is not a ``significant rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 3. Will not affect intrastate aviation in Alaska; and 4. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39--AIRWORTHINESS DIRECTIVES 0 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. Sec. 39.13 [Amended] 0 2. The FAA amends Sec. 39.13 by adding the following new airworthiness directive (AD): 2016-07-30 Airbus: Amendment 39-18475. Docket No. FAA-2015-4810; Directorate Identifier 2015-NM-090-AD. (a) Effective Date This AD becomes effective May 18, 2016. [[Page 21725]] (b) Affected ADs None. (c) Applicability This AD applies to the airplanes, certificated in any category, identified in paragraphs (c)(1) and (c)(2) of this AD, all manufacturer serial numbers. (1) Airbus Model A330-201, -202, -203, -223, -223F, -243, -243F, -301, -302, -303, -321, -322, -323, -341, -342, and -343 airplanes. (2) Airbus Model A340-211, -212, -213, -311, -312, -313, -541, and -642 airplanes. (d) Subject Air Transport Association (ATA) of America Code 34, Navigation. (e) Reason This AD was prompted by a report of blockage of two Angle of Attack (AOA) probes during climb, leading to activation of the Alpha Protection (Alpha Prot) while the Mach number increased. This activation could cause a continuous nose-down pitch rate that cannot be stopped with backward sidestick input, even in the full backward position. We are issuing this AD to prevent erroneous AOA information and Alpha Prot activation due to blocked AOA probes, which could result in a continuous nose-down command and consequent loss of control of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Replacement of Certain UTC Aerospace (UTAS) AOA Sensors For airplanes on which any UTAS AOA sensor having part number (P/N) 0861ED or P/N 0861ED2 is installed: At the applicable time specified in paragraph (h) of this AD, replace all Captain and First Officer AOA sensors (probes) having P/N 0861ED or 0861ED2 with AOA sensors having Thales P/N C16291AB, in accordance with the Accomplishment Instructions of the applicable service information identified in paragraph (g)(1), (g)(2), or (g)(3) of this AD. (1) Airbus Service Bulletin A330-34-3315, dated March 26, 2015 (for Model A330 airplanes). (2) Airbus Service Bulletin A340-34-4294, dated March 26, 2015 (for Model A340-200 and -300 airplanes). (3) Airbus Service Bulletin A340-34-5105, dated March 26, 2015 (for Model A340-500 and -600 airplanes). (h) Compliance Times for the Requirements of Paragraph (g) of This AD Do the actions required by paragraph (g) of this AD at the applicable time specified in paragraph (h)(1) or (h)(2) of this AD. (1) For airplanes with AOA sensors having P/N 0861ED: Within 22 months after the effective date of this AD. (2) For airplanes with AOA sensors having P/N 0861ED2: Within 7 months after the effective date of this AD. (i) Replacement of Certain SEXTANT/THOMSON AOA Sensors For airplanes on which any SEXTANT/THOMSON AOA sensor having P/N 45150320 is installed: Within 22 months after the effective date of this AD, replace all SEXTANT/THOMSON AOA sensors (probes) having P/N 45150320 with AOA sensors having Thales P/N C16291AB, in accordance with the Accomplishment Instructions of the applicable service information identified in paragraph (i)(1) or (i)(2) of this AD. (1) Airbus Service Bulletin A330-34-3228, dated October 7, 2009 (for Model A330 airplanes). (2) Airbus Service Bulletin A340-34-4234, dated October 7, 2009 (for Model A340-200 and -300 airplanes). (j) Repetitive Inspections/Tests of Certain Thales AOA Sensors For airplanes on which one or more Thales AOA sensor having P/N C16291AA is installed: Before the accumulation of 17,000 total flight hours on the AOA sensor since first installation on an airplane, or within 6 months after the effective date of this AD, whichever occurs later; and thereafter at intervals not to exceed 3,800 flight hours; do a detailed inspection of the three AOA sensors at FINs 3FP1, 3FP2, and 3FP3 for discrepancies (e.g., the vane of the sensor does not deice properly), and a functional heating test of each AOA sensor having P/N C16291AA, in accordance with the Accomplishment Instructions of the applicable service information identified in paragraph (j)(1), (j)(2), or (j)(3) of this AD. (1) Airbus Service Bulletin A330-34-3215, Revision 03, dated July 23, 2015 (for Model A330 airplanes). (2) Airbus Service Bulletin A340-34-4215, Revision 03, dated July 27, 2015 (for Model A340-200 and -300 airplanes). (3) Airbus Service Bulletin A340-34-5062, Revision 02, dated July 24, 2015 (for Model A340-500 and -600 airplanes). (k) Corrective Actions If any discrepancy is found during any inspection required by paragraph (j) of this AD, or if any test is failed during the heating test required by paragraph (j) of this AD: Before further flight, replace all affected AOA sensors with sensors identified in paragraph (k)(1) or (k)(2) of this AD, in accordance with the Accomplishment Instructions of the applicable service information identified in paragraph (j)(1), (j)(2), or (j)(3) of this AD. (1) Replace with AOA sensors having Thales P/N C16291AA, on which the inspection and test required by paragraph (j) of this AD were passed. (2) Replace with AOA sensors having Thales P/N C16291AB. (l) Credit for Previous Actions This paragraph provides credit for the actions required by paragraph (g) of this AD, if those actions were performed before the effective date of this AD using the applicable service information specified in paragraphs (l)(1), (l)(2), and (l)(3) of this AD, which are not incorporated by reference in this AD. (1) Airbus Service Bulletin A330-34-3215, Revision 02, dated March 29, 2010. (2) Airbus Service Bulletin A340-34-4215, Revision 02, dated March 29, 2010. (3) Airbus Service Bulletin A340-34-5062, Revision 01, dated March 29, 2010. (m) Airplanes Excluded From Certain Requirements (1) The actions specified in paragraphs (g), (i), (j), and (k) of this AD are not required, provided that the conditions specified in paragraphs (m)(1)(i), (m)(1)(ii), and (m)(1)(iii) of this AD are met. (i) Airbus Modification 58555 (installation of Thales P/N C16291AB AOA sensors) has been embodied in production. (ii) Airbus Modification 46921 (installation of UTAS AOA sensors) has not been embodied in production. (iii) No AOA sensor having SEXTANT/THOMSON P/N 45150320 or UTAS P/N 0861ED or P/N 0861ED2 has been installed on the airplane since date of issuance of the original airworthiness certificate or date of issuance of the original export certificate of airworthiness. (2) The actions specified in paragraphs (g) and (i) of this AD are not required, provided that all conditions specified in paragraphs (m)(2)(i), (m)(2)(ii), and (m)(2)(iii) of this AD are met. (i) Only AOA sensors with part numbers approved after the effective date of this AD have been installed. (ii) The AOA sensor part number is approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; the European Aviation Safety Agency (EASA); or Airbus's EASA Design Organization Approval (DOA). (iii) The installation is accomplished in accordance with airplane modification instructions approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; the EASA; or Airbus's EASA DOA. (n) Optional Terminating Modification Replacement of all Thales AOA sensors having P/N C16291AA with Thales AOA sensors having P/N C16291AB, in accordance with the Accomplishment Instructions of the applicable service information identified in paragraph (n)(1), (n)(2), or (n)(3) of this AD, terminates the repetitive inspections and functional heating tests required by paragraph (j) of this AD. (1) Airbus Service Bulletin A330-34-3228, dated October 7, 2009 (for Model A330 airplanes). (2) Airbus Service Bulletin A340-34-4234, dated October 7, 2009 (for Model A340-200 and -300 airplanes). (3) Airbus Service Bulletin A340-34-5070, dated October 9, 2009 (for Model A340-500 and -600 airplanes). (o) Parts Installation Prohibitions (1) For airplanes on which only Thales P/N C16291AB AOA sensors are installed as of the effective date of this AD: No person may install, on any airplane, a Thales AOA sensor having P/N C16291AA as of the effective date of this AD. (2) For airplanes on which the modification specified in paragraph (n) of this AD has been done: No person may install, on any airplane, a Thales AOA sensor [[Page 21726]] having P/N C16291AA after accomplishing the specified modification. (3) For airplanes on which Thales P/N C16291AA or P/N C16291AB AOA sensors are installed as of the effective date of this AD: No person may install, on any airplane, a UTAS AOA sensor having P/N 0861ED or P/N 0861ED2, or a SEXTANT/THOMSON AOA sensor having P/N 45150320, as of the effective date of this AD. (4) For airplanes on which the replacement required by paragraph (i) of this AD has been done: No person may install, on any airplane, a UTAS AOA sensor having P/N 0861ED or P/N 0861ED2, or a SEXTANT/THOMSON AOA sensor having P/N 45150320, after accomplishing the replacement. (5) For airplanes on which the replacement required by paragraph (g) of this AD has been done: No person may install, on any airplane, a UTAS AOA sensor having P/N 0861ED or P/N 0861ED2, or a SEXTANT/THOMSON AOA sensor having P/N 45150320, after accomplishing the replacement, except that a UTAS AOA sensor having P/N 0861ED may be installed in the standby position of that airplane. (p) 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: Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1138; fax 425-227-1149. Information may be emailed to: [email protected]. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. The AMOC approval letter must specifically reference this AD. (2) Contacting the Manufacturer: For any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the EASA; or Airbus's EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature. (3) Required for Compliance (RC): If any service information contains procedures or tests that are identified as RC, those procedures and tests must be done to comply with this AD; any procedures or tests that are not identified as RC are recommended. Those procedures and tests that are not identified as RC may be deviated from using accepted methods in accordance with the operator's maintenance or inspection program without obtaining approval of an AMOC, provided the procedures and tests identified as RC can be done and the airplane can be put back in an airworthy condition. Any substitutions or changes to procedures or tests identified as RC require approval of an AMOC. (q) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2015-0134, 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-2015-4810. (2) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (r)(3) and (r)(4) of this AD. (r) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless this AD specifies otherwise. (i) Airbus Service Bulletin A330-34-3215, Revision 03, dated July 23, 2015. (ii) Airbus Service Bulletin A330-34-3228, dated October 7, 2009. (iii) Airbus Service Bulletin A330-34-3315, dated March 26, 2015. (iv) Airbus Service Bulletin A340-34-4215, Revision 03, dated July 27, 2015. (v) Airbus Service Bulletin A340-34-4234, dated October 7, 2009. (vi) Airbus Service Bulletin A340-34-4294, dated March 26, 2015. (vii) Airbus Service Bulletin A340-34-5062, Revision 02, dated July 24, 2015. (viii) Airbus Service Bulletin A340-34-5070, dated October 9, 2009. (ix) Airbus Service Bulletin A340-34-5105, dated March 26, 2015. (3) For service information identified in this AD, contact Airbus SAS, Airworthiness Office--EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 80; email [email protected]; Internet http://www.airbus.com. (4) You may view this service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221. (5) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html. Issued in Renton, Washington, on March 26, 2016. Jeffrey E. Duven, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016-08267 Filed 4-12-16; 8:45 am] BILLING CODE 4910-13-P
![21722 Federal Register / Vol. 81, No. 71 / Wednesday, April 13, 2016 / Rules and Regulations
Adoption of the Amendment actions were performed before the effective (2) You must use this service information
date of this AD using Boeing Alert Service as applicable to do the actions required by
Accordingly, under the authority Bulletin B787–81205–SB290015–00, Issue this AD, unless the AD specifies otherwise.
delegated to me by the Administrator, 001, dated September 4, 2014, which is not (i) Boeing Alert Service Bulletin B787–
the FAA amends 14 CFR part 39 as incorporated by reference in this AD. 81205–SB290015–00, Issue 002, dated
follows: (i) Alternative Methods of Compliance
November 25, 2014.
(ii) Reserved.
(AMOCs)
PART 39—AIRWORTHINESS (3) For Boeing service information
DIRECTIVES (1) The Manager, Seattle Aircraft identified in this AD, contact Boeing
Certification Office (ACO), FAA, has the Commercial Airplanes, Attention: Data &
■ 1. The authority citation for part 39 authority to approve AMOCs for this AD, if Services Management, P.O. Box 3707, MC
requested using the procedures found in 14 2H–65, Seattle, WA 98124–2207; telephone
continues to read as follows: CFR 39.19. In accordance with 14 CFR 39.19, 206–544–5000, extension 1; fax 206–766–
Authority: 49 U.S.C. 106(g), 40113, 44701. send your request to your principal inspector 5680; Internet https://
or local Flight Standards District Office, as www.myboeingfleet.com.
§ 39.13 [Amended] appropriate. If sending information directly (4) You may view this service information
■ 2. The FAA amends § 39.13 by adding to the manager of the ACO, send it to the at FAA, 1601 Lind Avenue SW., Renton, WA.
attention of the person identified in For information on the availability of this
the following new airworthiness
paragraph (j)(1) of this AD. Information may material at the FAA, call 425–227–1221.
directive (AD): be emailed to: 9-ANM-Seattle-ACO-AMOC- (5) You may view this service information
2016–07–25 The Boeing Company: Requests@faa.gov. that is incorporated by reference at the
Amendment 39–18470; Docket No. (2) Before using any approved AMOC, National Archives and Records
FAA–2015–2959; Directorate Identifier notify your appropriate principal inspector, Administration (NARA). For information on
2015–NM–008–AD. or lacking a principal inspector, the manager the availability of this material at NARA, call
of the local flight standards district office/ 202–741–6030, or go to: http://
(a) Effective Date certificate holding district office. www.archives.gov/federal-register/cfr/ibr-
This AD is effective May 18, 2016. (3) An AMOC that provides an acceptable
locations.html.
level of safety may be used for any repair,
(b) Affected ADs modification, or alteration required by this Issued in Renton, Washington, on March
None. AD if it is approved by the Boeing 26, 2016.
Commercial Airplanes Organization Jeffrey E. Duven,
(c) Applicability
Designation Authorization (ODA) that has Manager, Transport Airplane Directorate,
This AD applies to The Boeing Company been authorized by the Manager, Seattle Aircraft Certification Service.
Model 787–8 airplanes, certificated in any ACO, to make those findings. To be
category, as identified in Boeing Alert approved, the repair method, modification [FR Doc. 2016–07839 Filed 4–12–16; 8:45 am]
Service Bulletin B787–81205–SB290015–00, deviation, or alteration deviation must meet BILLING CODE 4910–13–P
Issue 002, dated November 25, 2014. the certification basis of the airplane and the
approval must specifically refer to this AD.
(d) Subject
(4) For service information that contains DEPARTMENT OF TRANSPORTATION
Air Transport Association (ATA) of steps that are labeled as Required for
America Code 29, Hydraulic Power. Compliance (RC), the provisions of Federal Aviation Administration
(e) Unsafe Condition paragraphs (i)(4)(i) and (i)(4)(ii) of this AD
apply. 14 CFR Part 39
This AD was prompted by reports (i) The steps labeled as RC, including
indicating that the ram air turbine (RAT) substeps under an RC step and any figures [Docket No. FAA–2015–4810; Directorate
assembly may fail to operate if deployed at identified in an RC step, must be done to Identifier 2015–NM–090–AD; Amendment
low airspeeds. We are issuing this AD to comply with the AD. An AMOC is required 39–18475; AD 2016–07–30]
prevent failure of the RAT assembly to for any deviations to RC steps, including
operate at low air speeds. The volume fuse substeps and identified figures. RIN 2120–AA64
on the RAT assembly may be activated in- (ii) Steps not labeled as RC may be
flight before the RAT is deployed. This may deviated from using accepted methods in Airworthiness Directives; Airbus
lead to improper pump hydraulic pressure accordance with the operator’s maintenance Airplanes
offloading when the RAT is needed. Failure or inspection program without obtaining
of the RAT to operate in an all engine out AGENCY: Federal Aviation
approval of an AMOC, provided the RC steps,
event would result in loss of control of the including substeps and identified figures, can Administration (FAA), Department of
airplane. still be done as specified, and the airplane Transportation (DOT).
can be put back in an airworthy condition. ACTION: Final rule.
(f) Compliance
Comply with this AD within the (j) Related Information SUMMARY: We are adopting a new
compliance times specified, unless already (1) For more information about this AD, airworthiness directive (AD) for all
done. contact Sean J. Schauer, Aerospace Engineer, Airbus Model A330–200, –200
Systems and Equipment Branch, ANM 130S, Freighter, and –300 series airplanes, and
(g) Replacement
FAA, Seattle ACO, 1601 Lind Avenue SW., all Airbus Model A340–200, –300, –500,
Within 36 months after the effective date Renton, WA 98057–3356; phone: 425–917–
of this AD, replace the RAT pump and 6479; fax: 425–917–6590; email: and –600 series airplanes. This AD was
control module assembly or the RAT sean.schauer@faa.gov. prompted by a report of blockage of
assembly, including an installation test and (2) Service information identified in this Angle of Attack (AOA) probes during
applicable corrective actions, in accordance AD that is not incorporated by reference is climb, leading to activation of the Alpha
with the Accomplishment Instructions of available at the addresses specified in Protection (Alpha Prot) while the Mach
jstallworth on DSK7TPTVN1PROD with RULES
Boeing Alert Service Bulletin B787–81205– paragraphs (k)(3) and (k)(4) of this AD. number increased. This activation could
SB290015–00, Issue 002, dated November 25, cause a continuous nose-down pitch
2014. Do all applicable corrective actions (k) Material Incorporated by Reference
(1) The Director of the Federal Register
rate that cannot be stopped with
before further flight.
approved the incorporation by reference backward sidestick input, even in the
(h) Credit for Previous Actions (IBR) of the service information listed in this full backward position. For certain
This paragraph provides credit for actions paragraph under 5 U.S.C. 552(a) and 1 CFR airplanes, this AD requires replacing
required by paragraph (g) of this AD, if those part 51. certain AOA sensors (probes) with
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![Federal Register / Vol. 81, No. 71 / Wednesday, April 13, 2016 / Rules and Regulations 21723
certain new AOA sensors. For certain apply to all Airbus Model A330–200, from service of UTAS P/N 0861ED2 AOA
other airplanes, this AD also requires –200 Freighter, and –300 series sensors.
inspections and functional heat testing airplanes; and all Airbus Model A340– For the reasons described above, this
[EASA] AD retains the requirements of EASA
of certain AOA sensors for 200, –300, –500, and –600 series
[AD ***], which is superseded, but reduces
discrepancies, and replacement if airplanes. The NPRM published in the the compliance times for aeroplanes with
necessary. We are issuing this AD to Federal Register on November 12, 2015 UTAS P/N 0861ED2 AOA sensors installed.
prevent erroneous AOA information and (80 FR 69899) (‘‘the NPRM’’).
Alpha Prot activation due to blocked The European Aviation Safety Agency You may examine the MCAI in the
AOA probes, which could result in a (EASA), which is the Technical Agent AD docket on the Internet at http://
continuous nose-down command and for the Member States of the European www.regulations.gov by searching for
loss of control of the airplane. Union, has issued EASA Airworthiness and locating Docket No. FAA–2015–
Directive 2015–0134, dated July 8, 2015 4810.
DATES: This AD becomes effective May
18, 2016. (referred to after this as the Mandatory Actions Since the NPRM Was Issued
The Director of the Federal Register Continuing Airworthiness Information,
or ‘‘the MCAI’’), to correct an unsafe Since we issued the NPRM Airbus has
approved the incorporation by reference
condition for all Airbus Model A330– issued the following service
of certain publications listed in this AD
200, –200 Freighter, and –300 series information:
as of May 18, 2016.
airplanes; and all Model A340–200, • Service Bulletin A330–34–3215,
ADDRESSES: For service information Revision 03, dated July 23, 2015.
identified in this final rule, contact –300, –500, and –600 series airplanes.
The MCAI states: • Service Bulletin A340–34–4215,
Airbus SAS, Airworthiness Office— Revision 03, dated July 27, 2015.
EAL, 1 Rond Point Maurice Bellonte, An occurrence was reported where an • Service Bulletin A340–34–5062,
31707 Blagnac Cedex, France; telephone Airbus A321 aeroplane encountered a
blockage of two Angle of Attack (AOA)
Revision 02, dated July 24, 2015.
+33 5 61 93 36 96; fax +33 5 61 93 45
80; email airworthiness.A330-A340@ probes during climb, leading to activation of Explanation of Certain Changes to the
the Alpha Protection (Alpha Prot) while the NPRM
airbus.com; Internet http:// Mach number increased. The flight crew
www.airbus.com. You may view this managed to regain full control and the flight We have revised paragraph (j) of this
referenced service information at the landed uneventfully. It was determined that AD to refer to this revised service
FAA, Transport Airplane Directorate, the affected AOA probes are also fitted on information.
1601 Lind Avenue SW., Renton, WA. A330 and A340 aeroplanes. We have also added a new paragraph
For information on the availability of When Alpha Prot is activated due to
(l) to this AD, and reidentified
this material at the FAA, call 425–227– blocked AOA probes, the flight control laws
order a continuous nose down pitch rate that, subsequent paragraphs, to give credit for
1221. It is also available on the Internet in a worst case scenario, cannot be stopped doing the actions using the following
at http://www.regulations.gov by with backward sidestick inputs, even in the service information:
searching for and locating Docket No. full backward position. If the Mach number • Airbus Service Bulletin A330–34–
FAA–2015–4810. increases during a nose down order, the AOA 3215, Revision 02, dated March 29,
value of the Alpha Prot will continue to 2010.
Examining the AD Docket decrease. As a result, the flight control laws • Airbus Service Bulletin A340–34–
You may examine the AD docket on will continue to order a nose down pitch
rate, even if the speed is above minimum
4215, Revision 02, dated March 29,
the Internet at http:// 2010.
www.regulations.gov/ selectable speed, known as VLS.
This condition, if not corrected, could • Airbus Service Bulletin A340–34–
#!docketDetail;D=FAA-2015-4810; or in result in loss of control of the aeroplane. 5062, Revision 01, dated March 29,
person at the Docket Management Investigation results indicated that 2010.
Facility between 9 a.m. and 5 p.m., aeroplanes equipped with certain UTC
Monday through Friday, except Federal Aerospace (UTAS, formerly known as Comments
holidays. The AD docket contains this Goodrich) AOA sensors, or equipped with We gave the public the opportunity to
AD, the regulatory evaluation, any certain SEXTANT/THOMSON AOA sensors, participate in developing this AD. The
comments received, and other appear to have a greater susceptibility to
adverse environmental conditions than
following presents the comment
information. The street address for the received on the NPRM and the FAA’s
aeroplanes equipped with the latest Thales
Docket Operations office (telephone AOA sensor, Part Number (P/N) C16291AB, response.
800–647–5527) is Docket Management which was designed to improve AOA
Facility, U.S. Department of Request To Reduce Certain Compliance
indication behaviour in heavy rain
Transportation, Docket Operations, M– conditions. Times
30, West Building Ground Floor, Room Having determined that replacement of Airbus asked that we reduce the
W12–140, 1200 New Jersey Avenue SE., these AOA sensors is necessary to achieve compliance time from 22 months to 12
Washington, DC. and maintain the required safety level of the months for P/N 0861ED removal, and
aeroplane, EASA issued [an AD ***], to
FOR FURTHER INFORMATION CONTACT:
require modification of the aeroplanes by
from 7 months to 3 months for P/N
Vladimir Ulyanov, Aerospace Engineer, replacement of the affected P/N sensors, and, 0861ED2 removal.
International Branch, ANM–116, after modification, prohibits (re-) installation We do not agree with the request, as
Transport Airplane Directorate, FAA, of those P/N AOA sensors. That [EASA] AD no supporting data was provided by the
1601 Lind Avenue SW., Renton, WA also required repetitive detailed visual commenter. We contacted Airbus to
98057–3356; telephone 425–227–1138; inspections (DET) and functional heating determine if there was a justification for
jstallworth on DSK7TPTVN1PROD with RULES
fax 425–227–1149. tests of certain Thales AOA sensors and reducing the compliance times specified
provided an optional terminating action for in the proposed AD. We noted that
SUPPLEMENTARY INFORMATION:
those inspections.
Since EASA AD 2015–0089 was issued,
reducing the compliance times would
Discussion necessitate (under the provisions of the
based on further analysis results, Airbus
We issued a notice of proposed issued Operators Information Transmission Administrative Procedure Act) reissuing
rulemaking (NPRM) to amend 14 CFR (OIT) Ref. 999.0017/15 Revision 1, the notice, reopening the period for
part 39 by adding an AD that would instructing operators to speed up the removal public comment, considering additional
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![21724 Federal Register / Vol. 81, No. 71 / Wednesday, April 13, 2016 / Rules and Regulations
comments subsequently received, and earlier. We have not changed this final • Service Bulletin A340–34–4234,
eventually issuing a final rule. Airbus rule in this regard. dated October 7, 2009.
stated it concurs with keeping the • Service Bulletin A340–34–4294,
Conclusion
compliance times specified in the dated March 26, 2015.
proposed AD. We have determined that We reviewed the relevant data,
further delay of this final rule is not considered the comment received, and • Service Bulletin A340–34–5062,
appropriate. However, if additional data determined that air safety and the Revision 02, dated July 24, 2015.
are presented that would justify a public interest require adopting this AD • Service Bulletin A340–34–5070,
shorter compliance time, we may with the changes described previously dated October 9, 2009.
consider further rulemaking on this and minor editorial changes. We have • Service Bulletin A340–34–5105,
issue. determined that these minor changes: dated March 26, 2015.
In developing an appropriate • Are consistent with the intent that The service information describes
compliance time, we considered the was proposed in the NPRM for procedures for replacing certain pitot
safety implications, parts availability, correcting the unsafe condition; and probes with certain new pitot probes.
and normal maintenance schedules for • Do not add any additional burden The service information also describes
timely accomplishment of replacing the upon the public than was already procedures for inspections and
AOA sensors, as well as the compliance proposed in the NPRM. functional heat testing of certain pitot
times required by the EASA AD. In
Related Service Information Under 1 probes, and replacement if necessary.
consideration of these factors, we have
CFR Part 51 This service information is reasonably
determined that the compliance time, as
available because the interested parties
proposed, represents an appropriate Airbus has issued the following
have access to it through their normal
time in which the AOA sensors can be service information:
• Service Bulletin A330–34–3215, course of business or by the means
replaced in a timely manner within the
fleet, while still maintaining an Revision 03, dated July 23, 2015. identified in the ADDRESSES section.
adequate level of safety. Most ADs, • Service Bulletin A330–34–3228, Costs of Compliance
including this one, permit operators to dated October 7, 2009.
accomplish the requirements of an AD • Service Bulletin A330–34–3315, We estimate that this AD affects 55
at a time earlier than the specified dated March 26, 2015. airplanes of U.S. registry.
compliance time; therefore, an operator • Service Bulletin A340–34–4215, We estimate the following costs to
may choose to replace the AOA sensors Revision 03, dated July 27, 2015. comply with this AD:
ESTIMATED COSTS
Cost on U.S.
Action Labor cost Parts cost Cost per product operators
Replacement ................................... 5 work-hours × $85 per hour = $0 $425 ............................................... $23,375
$425.
Inspection/test ................................. 3 work-hours × $85 per hour = 0 255 per inspection/test cycle ......... 14,025
$255.
We have received no definitive data products identified in this rulemaking List of Subjects in 14 CFR Part 39
that will enable us to provide a cost action. Air transportation, Aircraft, Aviation
estimate for the on-condition actions safety, Incorporation by reference,
Regulatory Findings
specified in this AD. Safety.
We determined that this AD will not
Authority for This Rulemaking Adoption of the Amendment
have federalism implications under
Title 49 of the United States Code Executive Order 13132. This AD will Accordingly, under the authority
specifies the FAA’s authority to issue not have a substantial direct effect on delegated to me by the Administrator,
rules on aviation safety. Subtitle I, the States, on the relationship between the FAA amends 14 CFR part 39 as
section 106, describes the authority of the national government and the States, follows:
the FAA Administrator. ‘‘Subtitle VII: or on the distribution of power and
Aviation Programs,’’ describes in more responsibilities among the various PART 39—AIRWORTHINESS
detail the scope of the Agency’s levels of government. DIRECTIVES
authority. For the reasons discussed above, I
■ 1. The authority citation for part 39
We are issuing this rulemaking under certify that this AD:
continues to read as follows:
the authority described in ‘‘Subtitle VII, 1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866; Authority: 49 U.S.C. 106(g), 40113, 44701.
Part A, Subpart III, Section 44701:
General requirements.’’ Under that 2. Is not a ‘‘significant rule’’ under the § 39.13 [Amended]
section, Congress charges the FAA with DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979); ■ 2. The FAA amends § 39.13 by adding
promoting safe flight of civil aircraft in the following new airworthiness
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air commerce by prescribing regulations 3. Will not affect intrastate aviation in
directive (AD):
for practices, methods, and procedures Alaska; and
the Administrator finds necessary for 4. Will not have a significant 2016–07–30 Airbus: Amendment 39–18475.
Docket No. FAA–2015–4810; Directorate
safety in air commerce. This regulation economic impact, positive or negative, Identifier 2015–NM–090–AD.
is within the scope of that authority on a substantial number of small entities
because it addresses an unsafe condition under the criteria of the Regulatory (a) Effective Date
that is likely to exist or develop on Flexibility Act. This AD becomes effective May 18, 2016.
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![21726 Federal Register / Vol. 81, No. 71 / Wednesday, April 13, 2016 / Rules and Regulations
having P/N C16291AA after accomplishing be done and the airplane can be put back in DEPARTMENT OF TRANSPORTATION
the specified modification. an airworthy condition. Any substitutions or
(3) For airplanes on which Thales P/N changes to procedures or tests identified as Federal Aviation Administration
C16291AA or P/N C16291AB AOA sensors RC require approval of an AMOC.
are installed as of the effective date of this
AD: No person may install, on any airplane, (q) Related Information 14 CFR Part 39
a UTAS AOA sensor having P/N 0861ED or (1) Refer to Mandatory Continuing [Docket No. FAA–2015–2464; Directorate
P/N 0861ED2, or a SEXTANT/THOMSON Airworthiness Information (MCAI) EASA Identifier 2014–NM–195–AD; Amendment
AOA sensor having P/N 45150320, as of the Airworthiness Directive 2015–0134, dated 39–18476; AD 2016–07–31]
effective date of this AD. July 8, 2015, for related information. This
(4) For airplanes on which the replacement RIN 2120–AA64
MCAI may be found in the AD docket on the
required by paragraph (i) of this AD has been Internet at http://www.regulations.gov by
done: No person may install, on any airplane, Airworthiness Directives; The Boeing
searching for and locating Docket No. FAA–
a UTAS AOA sensor having P/N 0861ED or Company Airplanes
2015–4810.
P/N 0861ED2, or a SEXTANT/THOMSON (2) Service information identified in this
AOA sensor having P/N 45150320, after AGENCY: Federal Aviation
AD that is not incorporated by reference is Administration (FAA), DOT.
accomplishing the replacement.
available at the addresses specified in
(5) For airplanes on which the replacement ACTION: Final rule.
paragraphs (r)(3) and (r)(4) of this AD.
required by paragraph (g) of this AD has been
done: No person may install, on any airplane, (r) Material Incorporated by Reference SUMMARY: We are superseding
a UTAS AOA sensor having P/N 0861ED or
(1) The Director of the Federal Register Airworthiness Directive (AD) 2013–22–
P/N 0861ED2, or a SEXTANT/THOMSON 11 for certain The Boeing Company
approved the incorporation by reference
AOA sensor having P/N 45150320, after Model 747–400 and –400D series
(IBR) of the service information listed in this
accomplishing the replacement, except that a airplanes. AD 2013–22–11 required
paragraph under 5 U.S.C. 552(a) and 1 CFR
UTAS AOA sensor having P/N 0861ED may
be installed in the standby position of that
part 51. repetitive inspections to detect cracks in
airplane. (2) You must use this service information the floor panel attachment fastener
as applicable to do the actions required by holes of certain upper deck floor beam
(p) Other FAA AD Provisions this AD, unless this AD specifies otherwise. upper chords, repetitive inspections,
The following provisions also apply to this (i) Airbus Service Bulletin A330–34–3215, corrective actions if necessary, and
AD: Revision 03, dated July 23, 2015. replacement of the upper deck floor
(1) Alternative Methods of Compliance (ii) Airbus Service Bulletin A330–34–3228,
beam upper chords. Since we issued AD
(AMOCs): The Manager, International dated October 7, 2009.
(iii) Airbus Service Bulletin A330–34– 2013–22–11, we received a report that
Branch, ANM–116, Transport Airplane
Directorate, FAA, has the authority to 3315, dated March 26, 2015. certain fastener holes in the upper deck
approve AMOCs for this AD, if requested (iv) Airbus Service Bulletin A340–34– floor beam upper chords may not have
using the procedures found in 14 CFR 39.19. 4215, Revision 03, dated July 27, 2015. been inspected in accordance with AD
In accordance with 14 CFR 39.19, send your (v) Airbus Service Bulletin A340–34–4234, 2013–22–11. This AD adds additional
request to your principal inspector or local dated October 7, 2009. repetitive inspections for cracks for
Flight Standards District Office, as (vi) Airbus Service Bulletin A340–34– certain airplanes, and corrective actions
appropriate. If sending information directly 4294, dated March 26, 2015. if necessary. We are issuing this AD to
to the International Branch, send it to ATTN: (vii) Airbus Service Bulletin A340–34– detect and correct fatigue cracking in
Vladimir Ulyanov, Aerospace Engineer, 5062, Revision 02, dated July 24, 2015. certain upper chords of the upper deck
International Branch, ANM–116, Transport (viii) Airbus Service Bulletin A340–34–
Airplane Directorate, FAA, 1601 Lind
floor beam. Such cracks could become
5070, dated October 9, 2009.
Avenue SW., Renton, WA 98057–3356; (ix) Airbus Service Bulletin A340–34–
large and cause the floor beams to
telephone 425–227–1138; fax 425–227–1149. 5105, dated March 26, 2015. become severed and result in rapid
Information may be emailed to: 9-ANM-116- (3) For service information identified in decompression or reduced
AMOC-REQUESTS@faa.gov. Before using this AD, contact Airbus SAS, Airworthiness controllability of the airplane.
any approved AMOC, notify your appropriate Office—EAL, 1 Rond Point Maurice Bellonte, DATES: This AD is effective May 18,
principal inspector, or lacking a principal 31707 Blagnac Cedex, France; telephone +33 2016.
inspector, the manager of the local flight 5 61 93 36 96; fax +33 5 61 93 45 80; email The Director of the Federal Register
standards district office/certificate holding airworthiness.A330-A340@airbus.com;
district office. The AMOC approval letter approved the incorporation by reference
Internet http://www.airbus.com. of a certain publication listed in this AD
must specifically reference this AD. (4) You may view this service information
(2) Contacting the Manufacturer: For any as of May 18, 2016.
at the FAA, Transport Airplane Directorate,
requirement in this AD to obtain corrective 1601 Lind Avenue SW., Renton, WA. For ADDRESSES: For service information
actions from a manufacturer, the action must information on the availability of this identified in this final rule, contact
be accomplished using a method approved material at the FAA, call 425–227–1221. Boeing Commercial Airplanes,
by the Manager, International Branch, ANM– (5) You may view this service information Attention: Data & Services Management,
116, Transport Airplane Directorate, FAA; or that is incorporated by reference at the
the EASA; or Airbus’s EASA DOA. If P.O. Box 3707, MC 2H–65, Seattle, WA
National Archives and Records 98124–2207; telephone 206–544–5000,
approved by the DOA, the approval must
Administration (NARA). For information on extension 1; fax 206–766–5680; Internet
include the DOA-authorized signature.
the availability of this material at NARA, call https://www.myboeingfleet.com. You
(3) Required for Compliance (RC): If any
202–741–6030, or go to: http://
service information contains procedures or may view this referenced service
www.archives.gov/federal-register/cfr/ibr-
tests that are identified as RC, those information at the FAA, Transport
procedures and tests must be done to comply locations.html.
Airplane Directorate, 1601 Lind Avenue
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with this AD; any procedures or tests that are Issued in Renton, Washington, on March SW., Renton, WA. For information on
not identified as RC are recommended. Those 26, 2016. the availability of this material at the
procedures and tests that are not identified Jeffrey E. Duven,
as RC may be deviated from using accepted FAA, call 425–227–1221. It is also
Manager, Transport Airplane Directorate, available on the Internet at http://
methods in accordance with the operator’s
Aircraft Certification Service. www.regulations.gov by searching for
maintenance or inspection program without
obtaining approval of an AMOC, provided [FR Doc. 2016–08267 Filed 4–12–16; 8:45 am] and locating Docket No. FAA–2015–
the procedures and tests identified as RC can BILLING CODE 4910–13–P 2464.
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Document Created: 2016-04-13 03:10:31
Document Modified: 2016-04-13 03:10:31
| 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 becomes effective May 18, 2016. | |
| Contact | Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1138; fax 425-227-1149. | |
| FR Citation | 81 FR 21722 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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