Airworthiness Directives; Airbus Airplanes, 91882-91888 [2016-29683]

Download as PDF 91882 Federal Register / Vol. 81, No. 243 / Monday, December 19, 2016 / Proposed Rules service after July 29, 2016, whichever occurs later. (ii) Thereafter, perform a USI of the stage 8 aft web upper face every 500 cycles since last inspection. (iii) Compliance with paragraph (f)(2)(i) of this AD is terminating action for the initial and repetitive USIs specified by paragraphs (f)(1)(i) and (f)(1)(ii) of this AD. FIGURE 1 TO PARAGRAPH (f)—HPC STAGE 8–10 SPOOL S/NS Part Nos. Serial Nos. 1844M90G01 ...................................................................... 1844M90G02 ...................................................................... (2) For all HPC stage 8–10 spools, P/N 1694M80G04, 1844M90G01, or 1844M90G02, perform an eddy current inspection (ECI) of the stage 8 aft upper face as follows: (i) Perform an initial ECI of the stage 8 aft web upper face at the next shop visit after the effective date of this AD. (ii) Thereafter, perform an ECI of the stage 8 aft web upper face at each subsequent shop visit. (3) Remove from service any HPC stage 8– 10 spool that fails the inspection required by paragraphs (f)(1) or (f)(2) of this AD, and replace with a spool eligible for installation. sradovich on DSK3GMQ082PROD with PROPOSALS (g) Definition For the purpose of this AD, an engine shop visit is the induction of an engine into the shop for maintenance during which the compressor discharge pressure seal face is exposed. (h) Alternative Methods of Compliance (AMOCs) The Manager, Engine Certification Office, FAA, may approve AMOCs for this AD. Use the procedures found in 14 CFR 39.19 to make your request. You may email your request to: ANE-AD-AMOC@faa.gov. (i) Related Information (1) For more information about this AD, contact John Frost, Aerospace Engineer, Engine Certification Office, FAA, 1200 District Avenue, Burlington, MA 01803; phone: 781–238–7756; fax: 781–238–7199; email: john.frost@faa.gov. VerDate Sep<11>2014 20:29 Dec 16, 2016 Jkt 241001 GWN005MF GWN005MG GWN0087M GWN0087N GWN00DGK GWN00DGL GWNBJ992 GWNBK667 GWNBK674 GWNBK675 GWNBK743 GWNBK744 GWNBK751 GWNBK752 GWN00C2T GWN00C2V GWN00G2N GWN00G2P GWN00PFP GWN00PFR GWN00T2N GWN00YHV GWN0125G GWN0125H GWN0166K GWN01C5K GWN01C5L GWN01C5M GWNBK753 GWNBK754 GWNBK841 GWNBK842 GWNBK843 GWNBK844 GWNBK952 GWNBK953 GWNBK954 GWNBK955 GWNBK956 GWNBK957 GWNBK958 GWNBK959 GWN01C5N GWN01GE2 GWN01GE3 GWN01GE4 GWN01GE6 GWN01WH1 GWN02688 GWN02689 GWN0268A GWN02DP2 GWN02DP3 GWN02F9F GWN02F9G GWN02L9T GWNBS077 GWNBS078 GWNBS079 GWNBS080 GWNBS081 GWNBS157 GWNBS158 GWNBS159 GWNBS160 GWNBS266 GWNBS267 GWNBS268 GWNBS269 GWNBS270 GWN02N8D GWN02T3R GWN02WGM GWN0311K GWN035PP GWN038TD GWN039TG GWN03G2R GWN03G2W GWN03G30 GWN03JPC GWN03JPD GWN03N8P GWN03N8R (2) GE GE90 Service Bulletin (SB) SB 72– 1151 R00, dated June 10, 2016, and Chapter 72–31–08, Special Procedures 003, and Chapter 72–00–31, Special Procedures 006, in GE GE90 Engine Manual, GEK100700, Revision 68, dated September 1, 2016, can be obtained from GE using the contact information in paragraph (i)(3) of this AD. This SB describes procedures for an on-wing USI of the stage 8 web of the stage 8–10 spool. These engine manual procedures describe how to perform ECI of the stage 8 aft web of the stage 8–10 spool. (3) For service information identified in this proposed AD, contact General Electric Company, GE-Aviation, Room 285, 1 Neumann Way, Cincinnati, OH 45215, phone: 513–552–3272; fax: 513–552–3329; email: geae.aoc@ge.com. (4) You may view this service information at the FAA, Engine & Propeller Directorate, 1200 District Avenue, Burlington, MA. For information on the availability of this material at the FAA, call 781–238–7125. (j) Material Incorporated by Reference None. Issued in Burlington, Massachusetts, on November 29, 2016. Colleen M. D’Alessandro, Manager, Engine & Propeller Directorate, Aircraft Certification Service. [FR Doc. 2016–29679 Filed 12–16–16; 8:45 am] BILLING CODE 4910–13–P PO 00000 Frm 00003 Fmt 4702 Sfmt 4702 GWNBS497 GWNBS499 GWNBS500 GWNBS501 GWNBS502 GWNBS609 GWNBS610 GWNBS611 GWNBS612 GWNBS613 GWNBS614 GWNBS721 GWNBS722 GWNBS723 GWN03RTM GWN03RTP GWN040RL GWN040RM GWN040RN GWN040RP GWN04202 GWN0435W GWN04360 GWN04361 GWN04362 GWN04ATG GWN04ATH GWN04E20 GWNBS724 GWNBS794 GWNBS810 GWNBS811 GWNBS812 GWNBS813 GWNBS814 GWNBS910 GWNBS911 GWNBS912 GWNBS914 GWNBS915 GWNBS982 GWNBS983 GWN04E21 GWN04GHT GWN04GHW GWN04GJ0 GWN04JW6 GWN04JW7 GWN04JW8 GWN04L7K GWN04L7L GWN04MT7 GWN04MT8 GWNBS984 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2016–9393; Directorate Identifier 2014–NM–199–AD] RIN 2120–AA64 Airworthiness Directives; Airbus Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to supersede Airworthiness Directive (AD) 2013–13– 16, which applies to all Airbus Model A330–200, A330–200 Freighter, A330– 300 series airplanes, and all Airbus Model A340–200, –300, –500, and –600 series airplanes. AD 2013–13–16 currently requires repetitive inspections for discrepancies of the ball-screw assembly of the trimmable horizontal stabilizer actuator (THSA), repetitive greasing of the THSA ball-nut, and replacement of the THSA if necessary; and modification or replacement (as applicable) of the ball-nut assembly, SUMMARY: E:\FR\FM\19DEP1.SGM 19DEP1 Federal Register / Vol. 81, No. 243 / Monday, December 19, 2016 / Proposed Rules which ends certain repetitive inspections. Since we issued AD 2013– 13–16, we have determined that a modification that automatically detects failure of the ball-screw assembly is necessary. This proposed AD would require an inspection, corrective actions if necessary, lubrication of the ball-nut, modification of the THSA, and removal of certain airplanes from the applicability. We are proposing this AD to address the unsafe condition on these products. DATES: We must receive comments on this proposed AD by February 2, 2017. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. • Hand Delivery: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this NPRM, 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 airworthiness.A330-A340@airbus.com; Internet https://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. sradovich on DSK3GMQ082PROD with PROPOSALS Examining the AD Docket You may examine the AD docket on the Internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2016– 9393; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone 800–647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM–116, VerDate Sep<11>2014 20:29 Dec 16, 2016 Jkt 241001 Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–1138; fax 425–227–1149. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2016–9393; Directorate Identifier 2014–NM–199–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD based on those comments. We will post all comments we receive, without change, to https:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion On June 21, 2013, we issued AD 2013–13–16, Amendment 39–17504 (78 FR 47537, August 6, 2013) (‘‘AD 2013– 13–16’’). AD 2013–13–16 requires actions intended to address an unsafe condition on all Airbus Model A330– 200, A330–200 Freighter, and A330–300 series airplanes, and all Airbus Model A340–200, –300, –500, and –600 series airplanes. Since we issued AD 2013–13–16, Airbus transferred most of the requirements of AD 2013–13–16 into airworthiness limitations, except the requirements for ECAM fault messages. The European Aviation Safety Agency (EASA) which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2014–0219, dated September 29, 2014 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition on all Airbus Model A330 and Model A340 series airplanes. The MCAI states: Several cases of transfer tube disconnection from the ball-nut of the trimmable horizontal stabilizer actuator (THSA) part number (P/N) 47172 and 47147– 400 were detected on the ground during greasing and maintenance. Investigation results showed that this was caused by water ingress into the ball-nut, resulting in the jamming of the ball transfer circuit when the water froze. If the three (independent) ball circuits fail, then the THSA operates on a fail-safe nut (which operates without balls), which jams after several movements on the ball-screw of the THSA. PO 00000 Frm 00004 Fmt 4702 Sfmt 4702 91883 This condition, if not detected and corrected, could damage the ball-screw and the fail-safe nut, possibly resulting in jamming of the THSA and consequent reduced control of the aeroplane. To detect at an early stage any distortion or initiation of disconnection, [Directorate General for Civil Aviation] DGAC France issued AD 2001–356 and AD 2001–357 to require repetitive inspections of the transfer tubes and their collars and, depending on findings, corrective action(s). Prompted by another case of transfer tube disconnection, DGAC France issued AD 2001–356R2 and AD 2001–357R2 to require additional repetitive greasing and reinforcement of the ball-nut maintenance greasing instructions. Subsequently, DGAC France issued AD 2002–037 and AD 2002–038 to require a modification that was also terminating action for the repetitive inspections and greasing tasks required by DGAC France AD 2001– 356R2 and AD 2001–357R2 for the THSA P/ N 47172 by application of Service Bulletin (SB) A330–27–3085 or SB A340–27–4089 (equivalent to Airbus production modification 49590), as applicable, changing the THSA P/N from 47172 to 47172–300. Later on, DGAC France issued AD 2002– 414 (later revised to R3) and AD 2002–415 (later revised to R2), which superseded the DGAC France AD 2001–356R2, AD 2001– 357R2, AD 2002–037, and AD 2002–038, requiring: —Repetitive inspections of all THSA P/N in service, —repetitive lubrication of some THSA P/N, and —replacement of THSA P/N 47172, 47147– 400 and 47147–2XX/–3XX. In addition, the electrical flight control computers monitor the operation of the THSA and the jamming of this actuator could be detected and indicated by messages on the maintenance system and on the [electronic centralized aircraft monitor] ECAM. For that reason, DGAC France AD 2002–414 and AD 2002–415 also required inspection of the THSA after display of such message(s). After those [DGAC France] ADs were issued, Airbus introduced 4 new THSA, P/N 47172–500, P/N 47172–510, P/N 47172–520 and P/N 47172–530. As these new THSA also needed to be inspected/lubricated, EASA issued [EASA] AD 2010–0192 and [EASA] AD 2010–0193, which retained the requirements of DGAC France AD F–2002–414R3 and AD F–2002– 415R2 respectively, which were superseded, to add required repetitive inspections and lubrications of the new THSA P/N. Since those [EASA] ADs were issued, all requirements of EASA AD 2010–0192 and AD 2010–0193 were transferred into Airbus Airworthiness Limitations Section (ALS) Part 4, except the requirement of paragraph (2.3) of those [EASA] ADs. At this time, compliance with ALS Part 4 tasks is required by EASA AD 2013–0268 (A330 aeroplanes) and [EASA] AD 2013–0269 (A340 aeroplanes), respectively [which correspond to FAA AD 2015–16–02, Amendment 39– 18227 (80 FR 48019, August 11, 2015); and AD 2014–23–17, Amendment 39–18033 (79 FR 71304, December 2, 2014) (A340 airplanes); respectively.] E:\FR\FM\19DEP1.SGM 19DEP1 91884 Federal Register / Vol. 81, No. 243 / Monday, December 19, 2016 / Proposed Rules sradovich on DSK3GMQ082PROD with PROPOSALS In addition, Airbus developed a Checkable Shear Pin (CSP) for the THSA and an associated additional electrical harness, which consists of installation of two Electrical Detection Devices (EDD) on the lower attachment secondary load path, which gives an indication to the Flight Control Primary Computers of secondary load path engagement. After embodiment of these modifications on an aeroplane, the repetitive inspections of the ball-screw assembly for integrity of the primary and secondary load paths is no longer required, because the failure is detected automatically by this new device. For the reasons described above, this [EASA] AD retains only the requirement of paragraph (2.3) of EASA AD 2010–0192 and 2010–0193 [actions following ECAM fault messages], which are superseded, and requires the installation of CSP and associated additional electrical harness on the THSA of the aeroplane. This [EASA] AD also requires, for A340–500/–600 aeroplanes that are post-SB A340–92–5008 (at Revision 06 or earlier), accomplishment of A340 ALS Part 3 task 274000–B0002–1–C, providing a grace period of 3 months for aeroplanes that have exceeded the applicable threshold or interval. The unsafe condition is the degraded operation of the THSA, which could result in reduced control of the airplane. Model A330–223F and A330–243F airplanes have been removed from the applicability of this proposed AD to correspond with the MCAI. Required actions include a detailed inspection and corrective actions if an ECAM fault message is displayed, repetitive lubrication of the THSA ballnut, and a modification of the THSA by installing a CSP and associated electrical harness. Required actions also include certain ‘‘Additional Work’’ that is described in the following service information. • ‘‘Additional Work’’ in Airbus Service Bulletin A330–27–3143, Revision 01, dated July 10, 2012, is described as removing the closing plug from the electrical harness 4515VB and connecting the electrical harness 4515VB to the THSA. • ‘‘Additional Work’’ in Airbus Service Bulletin A330–92–3046, Revision 06, dated November 15, 2013; and Airbus Service Bulletin A340–92– 4056, Revision 04, dated December 5, 2013; is described as replacement of a certain harness item, installation of placards and cable support, modification of a certain bracket, and installation of a certain spacer. • ‘‘Additional Work’’ in Airbus Service Bulletin A340–92–5008, Revision 07, dated February 8, 2013, is described as replacing a certain wiring harness, replacing a certain THSA harness, installing additional placards, and modifying a certain wire harness installation order. VerDate Sep<11>2014 20:29 Dec 16, 2016 Jkt 241001 You may examine the MCAI in the AD docket on the Internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2016– 9393. Related Service Information Under 1 CFR Part 51 Airbus has issued the following service information. The following service information describes procedures for doing repetitive inspections for integrity of the primary and secondary load paths of the ball-screw assembly of the THSA. These service bulletins are distinct because they apply to different airplane models. • Airbus Service Bulletin A330–27– 3102, Revision 09, dated March 29, 2016. • Airbus Service Bulletin A340–27– 4107, Revision 09, dated March 29, 2016. The following service information describes procedures for installing two electrical detection devices, also called CSPs, on the lower attachment secondary load path of the THSA, and modifying the THSA. These service bulletins are distinct because they apply to different airplane models equipped with THS actuators having different part numbers. • Airbus Service Bulletin A330–27– 3137, dated March 20, 2007; Revision 01, dated December 6, 2007; and Revision 02, dated January 18, 2010. These service bulletins are distinct because each revision contains unique editorial changes. • Airbus Service Bulletin A330–27– 3143, Revision 01, dated July 10, 2012. • Airbus Service Bulletin A340–27– 4136, including Appendix 1, dated March 20, 2007; Revision 01, including Appendix 1, dated December 6, 2007; and Revision 02, including Appendix 1, dated February 24, 2010. These service bulletins are distinct because each revision contains unique editorial changes. • Airbus Service Bulletin A340–27– 4143, dated February 21, 2012. • Airbus Service Bulletin A340–27– 5030, Revision 01, including Appendix 1, dated November 20, 2009. The following service information describes procedures for installing electrical wiring harnesses and brackets to connect the secondary nut detection device to the monitoring systems. These service bulletins are distinct because they apply to different airplane models. • Airbus Service Bulletin A330–92– 3046, Revision 04, dated July 15, 2010; Revision 05, dated November 7, 2011; and Revision 06, dated November 15, 2013. These service bulletins are PO 00000 Frm 00005 Fmt 4702 Sfmt 4702 distinct because each revision contains unique editorial changes. • Airbus Service Bulletin A340–92– 4056, Revision 03, dated July 16, 2010; and Revision 04, dated December 5, 2013. These service bulletins are distinct because each revision contains unique editorial changes. • Airbus Service Bulletin A340–92– 5008, Revision 07, dated February 8, 2013. This service information describes procedures for lubrication of the THSA ball-nut. These documents are distinct because they apply to different airplane models. • Airbus A330 Airworthiness Limitations Section (ALS) Part 4— System Equipment Maintenance Requirements (SEMRs), Revision 05, dated October 19, 2015, Task 274400– 00002–1–E, Lubrication of the THSA ball-nut. • Airbus A340 ALS Part 4—SEMRs, Revision 04, dated October 19, 2015, Task 274400–00002–1–E, Lubrication of the THSA ball-nut. • Airbus A340 ALS Part 3— Certification Maintenance Requirements (CMRs), Revision 03, dated October 19, 2015, Task 274000–B0003–1–C, Lubrication of THS Actuator Ball-screw Nut. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section. FAA’s Determination and Requirements of This Proposed AD This product has been approved by the aviation authority of another country, and is approved for operation in the United States. Pursuant to our bilateral agreement with the State of Design Authority, we have been notified of the unsafe condition described in the MCAI and service information referenced above. We are proposing this AD because we evaluated all pertinent information and determined an unsafe condition exists and is likely to exist or develop on other products of the same type design. Explanation of Proposed Compliance Times The MCAI requires operators to modify certain airplanes by installing a CSP by a certain date. In order to provide operators with sufficient time to accomplish the modification, we have determined that a 12-month period from the effective date of this AD is acceptable. This difference had been coordinated with the EASA. E:\FR\FM\19DEP1.SGM 19DEP1 Federal Register / Vol. 81, No. 243 / Monday, December 19, 2016 / Proposed Rules Costs of Compliance We estimate that this proposed AD affects 33 airplanes of U.S. registry. The actions required by AD 2013–13– 16, and retained in this proposed AD take about 1 work-hour per product, at an average labor rate of $85 per workhour. Based on these figures, the estimated cost of the actions that are required by AD 2013–13–16 is $85 per product. We also estimate that it would take about 67 work-hours per product to comply with the basic requirements of this proposed AD. The average labor rate is $85 per work-hour. Required parts would cost about $14,198 per product. Based on these figures, we estimate the cost of this proposed AD on U.S. operators to be $656,469, or $19,893 per product. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. ‘‘Subtitle VII: Aviation Programs,’’ describes in more detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in ‘‘Subtitle VII, Part A, Subpart III, Section 44701: General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. sradovich on DSK3GMQ082PROD with PROPOSALS Regulatory Findings We determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify this proposed regulation: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; 2. Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 3. Will not affect intrastate aviation in Alaska; and VerDate Sep<11>2014 20:29 Dec 16, 2016 Jkt 241001 4. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by removing Airworthiness Directive (AD) 2013–13–16, Amendment 39–17504 (78 FR 47537, August 6, 2013), and adding the following new AD: ■ Airbus: Docket No. FAA–2016–9393; Directorate Identifier 2014–NM–199–AD. (a) Comments Due Date We must receive comments by February 2, 2017. (b) Affected ADs This AD replaces AD 2013–13–16, Amendment 39–17504 (78 FR 47537, August 6, 2013) (‘‘AD 2013–13–16’’). (c) Applicability This AD applies to the airplanes identified in paragraphs (c)(1) and (c)(2) of this AD, certificated in any category. (1) Airbus Model A330–201, –202, –203, –223, –243, –301, –302, –303, –321, –322, –323, –341, –342, and –343 airplanes, all manufacturer serial numbers. (2) Airbus Model A340–211, –212, –213, –311, –312, –313, –541, and –642 airplanes, all manufacturer serial numbers. (d) Subject Air Transport Association (ATA) of America Code 27, Flight Controls. (e) Reason This AD was prompted by the determination that a modification that automatically detects failure of the ball-screw assembly is necessary. We are issuing this AD to detect and correct wear on the trimmable horizontal stabilizer actuator (THSA), possibly resulting in damage to the ball-screw and fail-safe nut, which could jam the THSA and result in reduced control of the airplane. PO 00000 Frm 00006 Fmt 4702 Sfmt 4702 91885 (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Actions for Electronic Centralized Aircraft Monitor (ECAM) Fault Messages For airplanes other than those identified in figure 1 to paragraphs (g), (h), and (p) of this AD: If, during any flight, one of the ‘‘PRIM X PITCH FAULT’’ or ‘‘STAB CTL FAULT’’ messages is displayed on the ECAM associated with the ‘‘PITCH TRIM ACTR (1CS)’’ maintenance message, before further flight after each time the message is displayed on the ECAM, do the actions specified in paragraphs (g)(1) and (g)(2) of this AD. (1) Do the applicable detailed inspection of the ball-screw assembly for integrity of the primary and secondary load path; check the checkable shear pins (CSP), if installed; and do all applicable corrective actions; as specified in paragraph (g)(1)(i), (g)(1)(ii), or (g)(1)(iii) of this AD. Do all applicable corrective actions before further flight. (i) For Model A330 series airplanes: Do the actions in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330–27–3102, Revision 09, dated March 29, 2016, except as required by paragraph (n)(1) of this AD. (ii) For Model A340–200 and –300 series airplanes: Do the actions in accordance with the Accomplishment Instructions of Airbus Service Bulletin A340–27–4107, Revision 09, dated March 29, 2016, except as required by paragraph (n)(1) of this AD. (iii) For Model A340–500 and –600 series airplanes: Do the actions using a method approved by the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA); or Airbus’s EASA Design Organization Approval (DOA). Note 1 to paragraph (g)(1)(iii) of this AD: Guidance for the inspection of the ball-screw assembly can be found in Task 274000– B0002–1–C, Inspection of the Ball-screw Assembly for Integrity of the Primary and Secondary Load Paths, of the Airbus A340 Airworthiness Limitations Section (ALS) Part 3—Certification Maintenance Requirements (CMR), Revision 03, dated October 19, 2015. (2) Lubricate the THSA ball-nut in accordance with the applicable service information specified in paragraph (g)(2)(i), (g)(2)(ii), or (g)(2)(iii) of this AD. (i) Task 274400–00002–1–E, Lubrication of the THSA ball-nut, of Airbus A330 ALS Part 4—System Equipment Maintenance Requirements (SEMR), Revision 05, dated October 19, 2015 (for Model A330 series airplanes). (ii) Task 274400–00002–1–E, Lubrication of the THSA ball-nut, of Airbus A340 ALS Part 4—SEMR, Revision 04, dated October 19, 2015 (for Model A340–200 and –300 series airplanes). (iii) Task 274000–B0003–1–C, Lubrication of THS Actuator Ball-screw Nut, of Airbus A340 ALS Part 3—CMR, Revision 03, dated October 19, 2015 (for Model A340–500 and –600 series airplanes). E:\FR\FM\19DEP1.SGM 19DEP1 91886 Federal Register / Vol. 81, No. 243 / Monday, December 19, 2016 / Proposed Rules FIGURE 1 TO PARAGRAPHS (g), (h), AND (p) OF THIS AD—DEFINITION OF AIRPLANE GROUPS Group Airplane models On which the following actions or modifications have been done Group 1 airplanes ............ Airbus Model A330–200 and –300 series airplanes. On which the actions specified in Airbus Service Bulletin A330– 27–3137, dated March 20, 2007, or Revision 01, dated December 6, 2007; and Airbus Service Bulletin A330–92–3046, Revision 04, dated July 16, 2010, or Revision 05, dated November 7, 2011; have been embodied in service. On which the actions specified in Airbus Service Bulletin A340– 27–4136, including Appendix 1, dated March 20, 2007, or Revision 01, including Appendix 1, dated December 6, 2007; and Airbus Service Bulletin A340–92–4056, Revision 03, dated July 16, 2010; have been embodied in service. On which Airbus Modifications 55780, 52269, and 56056 have been embodied in production. Airbus Model A340–200 and –300 series airplanes. Group 2 airplanes ............ Group 3 airplanes ............ Airbus Model A330–200 and –300 series airplanes and Model A340–200 and –300 series airplanes. Airbus Model A340–500 and –600 series airplanes. Airbus Model A330–200 and –300 series airplanes. Airbus Model A330–200 and –300 series airplanes. Airbus Model A340–200 and –300 series airplanes. Airbus Model A340–200 and –300 series airplanes. (h) Installation of CSP and Electrical Harness For all airplanes, except Group 2 airplanes specified in figure 1 to paragraphs (g), (h), and (p) of this AD, and except for airplanes On which Airbus Modifications 54882, 52191, and 56058 have been embodied in production. On which Airbus Service Bulletin A330–27–3137, dated March 20, 2007; or Revision 01, dated December 6, 2007; has been embodied in service and Airbus Modifications 52269 and 56056 have been embodied in production. On which Airbus Modification 55780 has been embodied in production and Airbus Service Bulletin A330–92–3046 Revision 04, dated July 16, 2010; or Revision 05, dated November 07, 2011 has been embodied in service. On which Airbus Service Bulletin A340–27–4136, including Appendix 1, dated March 20, 2007; or Revision 01, including Appendix 1, dated December 6, 2007; has been embodied in service and Airbus Modifications 52269 and 56056 have been embodied in production. On which Airbus Modification 55780 has been embodied in production and Airbus Service Bulletin A340–92–4056, Revision 03, dated July 16, 2010, has been embodied in service. identified in paragraphs (i), (j), and (n)(2) of this AD: Within 12 months after the effective date of this AD, modify the airplane by installing a CSP on the THSA and an additional electrical harness, in accordance with the Accomplishment Instructions of the Airbus service information specified in figure 2 to paragraph (h) of this AD, as applicable to the part number of the THSA installed on the airplane, except as provided by paragraph (n)(2) of this AD. FIGURE 2 TO PARAGRAPH (h) OF THIS AD—APPLICABLE SERVICE INFORMATION FOR MODIFICATION THSA Part No. (P/N) Service Bulletin for CSP installation Service Bulletin for electrical harness installation 47172–300 ......... Airbus Service Bulletin A330–27–3137, Revision 02, dated January 18, 2010, for Airbus Model A330–200 and –300 series airplanes; and Airbus Service Bulletin A330–27–4136, including Appendix 1, Revision 02, dated February 24, 2010, for Airbus Model A340–200 and –300 series airplanes Airbus Service Bulletin A330–27–3143, Revision 01, dated July 10, 2012, for Airbus Model A330–200 and –300 series airplanes; and Airbus Service Bulletin A340–27–4143, dated February 21, 2012, for Airbus Model A340–200 and –300 series airplanes. Airbus Service Bulletin A340–27–5030, Revision 01, including Appendix 1, dated November 20, 2009, for Airbus Model A340–541 and –642 airplanes. Airbus Service Bulletin A330–92–3046, Revision 06, dated November 15, 2013, for Airbus Model A330–200 and –300 series airplanes; and 47147–500 ......... sradovich on DSK3GMQ082PROD with PROPOSALS 47175–200 ......... 47175–300 ......... (i) ‘‘Additional Work’’ on Previously Modified Airplanes For airplanes that have already been modified (installation of CSP on the THSA and electrical harness) before the effective date of this AD in accordance with the Accomplishment Instructions of any previous revision of an Airbus service VerDate Sep<11>2014 20:29 Dec 16, 2016 Jkt 241001 Airbus Service Bulletin A340–92–4056, Revision 04, dated December 5, 2013, for Airbus Model A340–200 and –300 series airplanes. Airbus Service Bulletin A340–92–5008, Revision 07, dated February 8, 2013, for Airbus Model A340–541 and –642 airplanes. bulletin specified in figure 2 to paragraph (h) of this AD, as applicable: Within 12 months after the effective date of this AD, do the ‘‘Additional Work’’ specified in, and in accordance with, the Accomplishment Instructions of the applicable Airbus service information specified in figure 2 to paragraph (h) of this AD. PO 00000 Frm 00007 Fmt 4702 Sfmt 4702 (j) Installation of Electrical Harness on Airplanes Equipped With a CSP For airplanes having one of the THSAs installed with a part number listed in figure 3 to paragraph (j) of this AD, and which have been modified by installing a CSP on the THSA as required by paragraph (h) of this AD: Within 12 months after the effective date E:\FR\FM\19DEP1.SGM 19DEP1 Federal Register / Vol. 81, No. 243 / Monday, December 19, 2016 / Proposed Rules of this AD, inspect to determine if the electrical harness identified in the applicable Airbus service information specified in figure 3 to paragraph (j) of this AD is installed on the airplane, and if found not to be installed, modify the airplane by installing an electrical harness, in accordance with the Accomplishment Instructions of the Airbus service information specified in figure 3 to paragraph (j) of this AD, as applicable to the part number of the THSA installed on the airplane. Airplanes having one of the THSAs 91887 installed with a part number listed in figure 3 to paragraph (j) of this AD already have the CSP installed on the THSA, and only the electrical harness must be installed on the airplane. FIGURE 3 TO PARAGRAPH (j) OF THIS AD—ELECTRICAL HARNESS INSTALLATION THSA P/N Service Information for Electrical Harness Installation 47172–500, 47172–510, 47172–520, 47172– 530, 47147–700, 47147–710. Airbus Service Bulletin A330–92–3046, Revision 06, dated November 15, 2013, for Airbus Model A330–200 and –300 series airplanes. Airbus Service Bulletin A340–92–4056, Revision 04, dated December 5, 2013, for Airbus Model A340–200 and –300 series airplanes. Airbus Service Bulletin A340–92–5008, Revision 07, dated February 8, 2013, for Airbus Model A340–541 and –642 airplanes. 47175–500, 47175–520, 47175–530 .................. sradovich on DSK3GMQ082PROD with PROPOSALS (k) Terminating Action for Repetitive Inspections of Airbus Model A330–200 and –300 Series Airplanes Accomplishment of a modification before the effective date of this AD in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330–27–3137, dated March 20, 2007, or Revision 01, dated December 6, 2007; and Airbus Service Bulletin A330–92–3046, Revision 04, dated July 15, 2010, or Revision 05, dated November 7, 2011; terminates the repetitive inspections specified in paragraphs (k)(1) through (k)(4) of this AD. Modification of an airplane as required by this paragraph does not constitute terminating action for the actions specified in paragraph (g)(2) of this AD or the additional work specified in paragraph (i) of this AD. (1) Task 274400–00001–1–E, Detailed inspection of the ball-screw assembly for integrity of the primary and secondary load path and check the gap at the secondary nut trunnion, of Airbus A330 ALS Part 4—SEMR, Revision 05, dated October 19, 2015. (2) Task 274400–00001–2–E, Detailed inspection of the ball-screw assembly for integrity of the primary and secondary load path and check the CSPs, of Airbus A330 ALS Part 4—SEMR, Revision 05, dated October 19, 2015. (3) Task 274400–00001–3–E, Detailed inspection of the ball-screw assembly for integrity of the primary and secondary load path and check the CSPs, of Airbus A330 ALS Part 4—SEMR, Revision 05, dated October 19, 2015. (4) Task 274400–00001–4–E, Detailed inspection of the ball-screw assembly for integrity of the primary and secondary load path and check the CSPs, of Airbus A330 ALS Part 4—SEMR, Revision 05, dated October 19, 2015. (l) Terminating Action for Repetitive Inspections of Airbus Model A340–200 and –300 Series Airplanes Accomplishment of a modification in accordance with the Accomplishment Instructions of Airbus Service Bulletin A340– 27–4143, dated February 21, 2012; and Airbus Service Bulletin A340–92–4056, Revision 03, dated July 16, 2010; terminates the actions required by paragraph (g)(1) of this AD for modified Airbus Model A340– 200 and –300 series airplanes only. Modification of an airplane as specified in VerDate Sep<11>2014 20:29 Dec 16, 2016 Jkt 241001 this paragraph does not constitute terminating action for the actions specified in paragraph (g)(2) of this AD, or the additional work specified in paragraph (i) of this AD. (m) Terminating Action for Repetitive Inspections of Airbus Model A340–200 and –300 Series Airplanes Accomplishment of a modification before the effective date of this AD in accordance with the Accomplishment Instructions of Airbus Service Bulletin A340–27–4136, including Appendix 1, dated March 20, 2007, or Revision 01, including Appendix 1, dated December 6, 2007; and Airbus Service Bulletin A340–92–4056, Revision 03, dated July 16, 2010; terminates the repetitive inspections specified in paragraphs (m)(1) through (m)(4) of this AD. Modification of an airplane as required by this paragraph does not constitute terminating action for the actions specified in paragraph (g)(2) of this AD, or the additional work specified in paragraph (i) of this AD. (1) Task 274400–00001–1–E, Detailed inspection of the ball-screw assembly for integrity of the primary and secondary load path and gap check at the secondary nut trunnion, of Airbus A340 ALS Part 4—SEMR, Revision 04, dated October 19, 2015. (2) Task 274400–00001–2–E, Detailed inspection of the ball-screw assembly for integrity of the primary and secondary load path and CSP check, of Airbus A340 ALS Part 4—SEMR, Revision 04, dated October 19, 2015. (3) Task 274400–00001–3–E, Detailed inspection of the ball-screw assembly for integrity of the primary and secondary load path and CSP check, of Airbus A340 ALS Part 4—SEMR, Revision 04, dated October 19, 2015. (4) Task 274400–00001–4–E, Detailed inspection of the ball-screw assembly for integrity of the primary and secondary load path and CSP check, of A340 ALS Part 4— SEMR, Revision 04, dated October 19, 2015. (n) Exceptions to the Actions in Certain Service Information and Paragraph (h) of This AD (1) Where Airbus Service Bulletin A330– 27–3102, Revision 09, dated March 29, 2016 (for Model A330 series airplanes); or Airbus Service Bulletin A340–27–4107, Revision 09, dated March 29, 2016 (for Model A340 series airplanes); specifies to contact Airbus for a PO 00000 Frm 00008 Fmt 4702 Sfmt 4702 damage assessment: Before further flight, accomplish the required actions in accordance with the procedures specified in paragraph (s)(2) of this AD. (2) For airplanes that already had the electrical harness installed during production using Airbus Modifications 52269 and 56056 for Airbus Model A330–200 and –300 series airplanes and Airbus Model A340–200 and –300 series airplanes, and using Airbus Modifications 52191 and 56058 for Model A340–500 and –600 series airplanes: Only the CSP must be installed on the THSA in accordance with applicable Airbus service bulletins and within the compliance time specified in paragraph (h) of this AD. (o) Terminating Action for Repetitive Inspections for Airplanes on Which Actions Required by Paragraph (h), (i), or (j) of This AD Are Done Modification of an airplane as required by paragraph (h), (i), or (j) of this AD, as applicable, constitutes terminating action for that airplane for the applicable actions identified in paragraphs (o)(1) through (o)(4) of this AD. (1) For all airplanes: The actions required by paragraph (g) of this AD. (2) For Model A340–500 and –600 series airplanes: Task 274000–B0002–1–C, Inspection of the Ball-screw Assembly for Integrity of the Primary and Secondary Load Paths, of Airbus A340 ALS Part 3—CMR, Revision 03, dated October 19, 2015. (3) For Model A330–200 and –300 series airplanes: The ALS tasks identified in paragraphs (k)(1) through (k)(4) of this AD. (4) For Model A340–200 and –300 series airplanes: The ALS tasks identified in paragraphs (m)(1) through (m)(4) of this AD. (p) Ball-Screw Assembly Inspection for Certain Airplanes For Model A340–500 and –600 airplanes that are in post-Airbus Service Bulletin A340–92–5008, at Revision 06 or earlier, configuration: Before exceeding the threshold or interval, as applicable, of Task 274000– B0002–1–C, Inspection of the Ball-screw Assembly for Integrity of the Primary and Secondary Load Paths, of Airbus A340 ALS Part 3—CMR, Revision 03, dated October 19, 2015, or within 3 months after the effective date of this AD, whichever occurs later, accomplish Task 274000–B0002–1–C, Inspection of the Ball-screw Assembly for E:\FR\FM\19DEP1.SGM 19DEP1 91888 Federal Register / Vol. 81, No. 243 / Monday, December 19, 2016 / Proposed Rules Integrity of the Primary and Secondary Load Paths, of Airbus A340 ALS Part 3—CMR, Revision 03, dated October 19, 2015; and do all applicable corrective actions. Do all applicable corrective actions before further flight using a method approved by the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA; or the EASA; or Airbus’s EASA DOA. Repeat Task 274000–B0002–1–C, Inspection of the Ballscrew Assembly for Integrity of the Primary and Secondary Load Paths, thereafter at the applicable intervals specified in Airbus A340 ALS Part 3—CMR, Revision 03, dated October 19, 2015. (q) Parts Installation Prohibitions (1) For all airplanes except Group 2 airplanes as identified in figure 1 to paragraphs (g), (h), and (p) of this AD: After modification of the airplane as required by paragraph (h), (i), or (j) of this AD, as applicable, no person may install any THSA having P/N 47172–300, P/N 47147–500, P/N 47175–200, or P/N 47175–300. (2) For Group 2 airplanes, as identified in figure 1 to paragraphs (g), (h), and (p) of this AD: As of the effective date of this AD, no person may install on any Group 2 airplane any THSA having P/N 47172–300, P/N 47147–500, P/N 47175–200, or P/N 47175– 300. sradovich on DSK3GMQ082PROD with PROPOSALS (r) Credit for Previous Actions This paragraph provides credit for actions required by paragraph (g)(2) of this AD, if those actions were performed before the effective date of this AD using the applicable service information specified in paragraphs (r)(1) through (r)(4) of this AD. (1) Task 274400–00002–1–E, Lubrication of the THSA ball-nut, of Airbus A330 ALS Part 4—Ageing Systems Maintenance, Revision 03, dated September 9, 2011 (for Model A330 series airplanes). (2) Task 274400–00002–1–E, Lubrication of the THSA ball-nut, of Airbus A330 ALS Part 4—Ageing Systems Maintenance, Revision 04, dated August 27, 2013 (for Model A330 series airplanes). (3) Task 274400–00002–1–E, Lubrication of the THSA ball-nut, of Airbus A340 ALS Part 4—Ageing Systems Maintenance, Revision 02, dated October 12, 2011 (for Model A340– 200 and –300 series airplanes). (4) Task 274400–00002–1–E, Lubrication of the THSA ball-nut, of Airbus A340 ALS Part 4—Ageing Systems Maintenance, Revision 03, dated November 15, 2012 (for Model A340–200 and –300 series airplanes). (s) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the International Branch, send it to ATTN: Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM–116, Transport VerDate Sep<11>2014 20:29 Dec 16, 2016 Jkt 241001 Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–1138; fax 425–227–1149. Information may be emailed to: 9-ANM-116ACO-AMOC-REQUESTS@faa.gov. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. The AMOC approval letter must specifically reference this AD. (2) Contacting the Manufacturer: As of the effective date of this AD, for any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, International Branch, ANM– 116, Transport Airplane Directorate, FAA; or EASA; or Airbus’s EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature. (t) Related Information (1) Refer to Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2014–0219, dated September 29, 2014, for related information. This MCAI may be found in the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA– 2016–9393. (2) 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 airworthiness.A330-A340@airbus.com; Internet https://www.airbus.com. (3) You may view this service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. Issued in Renton, Washington, on November 10, 2016. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016–29683 Filed 12–16–16; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF THE TREASURY Internal Revenue Service 26 CFR Part 1 [REG–140328–15] RIN 1545–BN17 Guidance Regarding Predecessors and Successors Under Section 355(e); Limitation on Gain Recognition; Guidance Under Section 355(f) Internal Revenue Service (IRS), Treasury. ACTION: Withdrawal of notice of proposed rulemaking, notice of proposed rulemaking by cross-reference to temporary regulations. AGENCY: PO 00000 Frm 00009 Fmt 4702 Sfmt 4702 In the Rules and Regulations section of this issue of the Federal Register, the IRS is issuing temporary regulations that provide guidance regarding the distribution by a distributing corporation of stock or securities of a controlled corporation without the recognition of income, gain, or loss. The temporary regulations provide guidance in determining whether a corporation is a predecessor or successor of a distributing or controlled corporation for purposes of the exception under section 355(e) of the Internal Revenue Code to the nonrecognition treatment afforded qualifying distributions, and they provide certain limitations on the recognition of gain in certain cases involving a predecessor of a distributing corporation. The temporary regulations also provide rules regarding the extent to which section 355(f) causes a distributing corporation (and in certain cases its shareholders) to recognize income or gain on the distribution of stock or securities of a controlled corporation. Those temporary regulations affect corporations that distribute the stock or securities of controlled corporations and their shareholders or security holders of those distributing corporations. The text of those temporary regulations serves as the text of these proposed regulations. DATES: Comments and requests for a public hearing must be received by March 20, 2017. ADDRESSES: Send submissions to: CC:PA:LPD:PR (REG–140328–15), Room 5203, Internal Revenue Service, P.O. Box 7604, Ben Franklin Station, Washington, DC 20044. Submissions may be hand-delivered Monday through Friday between the hours of 8 a.m. and 4 p.m. to CC:PA:LPD:PR (REG–140328– 15), Courier’s Desk, Internal Revenue Service, 1111 Constitution Avenue NW., Washington, DC 20224, or sent electronically, via the Federal eRulemaking Portal at https:// www.regulations.gov/ (REG–140328– 15). FOR FURTHER INFORMATION CONTACT: Concerning the proposed regulations, Richard K. Passales at (202) 317–5024 or Marie C. Milnes-Vasquez, (202) 317– 7700; concerning submission of comments, and/or requests for public hearing, Regina Johnson at (202) 317– 6901 (not toll-free numbers). SUPPLEMENTARY INFORMATION: SUMMARY: Background and Explanation of Provisions On November 22, 2004, the Treasury Department and the IRS published in the Federal Register (69 FR 67873) a E:\FR\FM\19DEP1.SGM 19DEP1

Agencies

[Federal Register Volume 81, Number 243 (Monday, December 19, 2016)]
[Proposed Rules]
[Pages 91882-91888]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-29683]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-9393; Directorate Identifier 2014-NM-199-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

-----------------------------------------------------------------------

SUMMARY: We propose to supersede Airworthiness Directive (AD) 2013-13-
16, which applies to all Airbus Model A330-200, A330-200 Freighter, 
A330-300 series airplanes, and all Airbus Model A340-200, -300, -500, 
and -600 series airplanes. AD 2013-13-16 currently requires repetitive 
inspections for discrepancies of the ball-screw assembly of the 
trimmable horizontal stabilizer actuator (THSA), repetitive greasing of 
the THSA ball-nut, and replacement of the THSA if necessary; and 
modification or replacement (as applicable) of the ball-nut assembly,

[[Page 91883]]

which ends certain repetitive inspections. Since we issued AD 2013-13-
16, we have determined that a modification that automatically detects 
failure of the ball-screw assembly is necessary. This proposed AD would 
require an inspection, corrective actions if necessary, lubrication of 
the ball-nut, modification of the THSA, and removal of certain 
airplanes from the applicability. We are proposing this AD to address 
the unsafe condition on these products.

DATES: We must receive comments on this proposed AD by February 2, 
2017.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday 
through Friday, except Federal holidays.
    For service information identified in this NPRM, 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 airworthiness.A330-A340@airbus.com; Internet https://www.airbus.com. You may view this referenced service information at the 
FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. 
For information on the availability of this material at the FAA, call 
425-227-1221.

Examining the AD Docket

    You may examine the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2016-
9393; or in person at the Docket Management Facility between 9 a.m. and 
5 p.m., Monday through Friday, except Federal holidays. The AD docket 
contains this proposed AD, the regulatory evaluation, any comments 
received, and other information. The street address for the Docket 
Operations office (telephone 800-647-5527) is in the ADDRESSES section. 
Comments will be available in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: 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:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2016-9393; 
Directorate Identifier 2014-NM-199-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD based on those comments.
    We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    On June 21, 2013, we issued AD 2013-13-16, Amendment 39-17504 (78 
FR 47537, August 6, 2013) (``AD 2013-13-16''). AD 2013-13-16 requires 
actions intended to address an unsafe condition on all Airbus Model 
A330-200, A330-200 Freighter, and A330-300 series airplanes, and all 
Airbus Model A340-200, -300, -500, and -600 series airplanes.
    Since we issued AD 2013-13-16, Airbus transferred most of the 
requirements of AD 2013-13-16 into airworthiness limitations, except 
the requirements for ECAM fault messages.
    The European Aviation Safety Agency (EASA) which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2014-0219, dated September 29, 2014 (referred 
to after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition on all Airbus Model A330 
and Model A340 series airplanes. The MCAI states:

    Several cases of transfer tube disconnection from the ball-nut 
of the trimmable horizontal stabilizer actuator (THSA) part number 
(P/N) 47172 and 47147-400 were detected on the ground during 
greasing and maintenance. Investigation results showed that this was 
caused by water ingress into the ball-nut, resulting in the jamming 
of the ball transfer circuit when the water froze. If the three 
(independent) ball circuits fail, then the THSA operates on a fail-
safe nut (which operates without balls), which jams after several 
movements on the ball-screw of the THSA.
    This condition, if not detected and corrected, could damage the 
ball-screw and the fail-safe nut, possibly resulting in jamming of 
the THSA and consequent reduced control of the aeroplane.
    To detect at an early stage any distortion or initiation of 
disconnection, [Directorate General for Civil Aviation] DGAC France 
issued AD 2001-356 and AD 2001-357 to require repetitive inspections 
of the transfer tubes and their collars and, depending on findings, 
corrective action(s).
    Prompted by another case of transfer tube disconnection, DGAC 
France issued AD 2001-356R2 and AD 2001-357R2 to require additional 
repetitive greasing and reinforcement of the ball-nut maintenance 
greasing instructions.
    Subsequently, DGAC France issued AD 2002-037 and AD 2002-038 to 
require a modification that was also terminating action for the 
repetitive inspections and greasing tasks required by DGAC France AD 
2001-356R2 and AD 2001-357R2 for the THSA P/N 47172 by application 
of Service Bulletin (SB) A330-27-3085 or SB A340-27-4089 (equivalent 
to Airbus production modification 49590), as applicable, changing 
the THSA P/N from 47172 to 47172-300.
    Later on, DGAC France issued AD 2002-414 (later revised to R3) 
and AD 2002-415 (later revised to R2), which superseded the DGAC 
France AD 2001-356R2, AD 2001-357R2, AD 2002-037, and AD 2002-038, 
requiring:

--Repetitive inspections of all THSA P/N in service,
--repetitive lubrication of some THSA P/N, and
--replacement of THSA P/N 47172, 47147-400 and 47147-2XX/-3XX.

    In addition, the electrical flight control computers monitor the 
operation of the THSA and the jamming of this actuator could be 
detected and indicated by messages on the maintenance system and on 
the [electronic centralized aircraft monitor] ECAM. For that reason, 
DGAC France AD 2002-414 and AD 2002-415 also required inspection of 
the THSA after display of such message(s).
    After those [DGAC France] ADs were issued, Airbus introduced 4 
new THSA, P/N 47172-500, P/N 47172-510, P/N 47172-520 and P/N 47172-
530.
    As these new THSA also needed to be inspected/lubricated, EASA 
issued [EASA] AD 2010-0192 and [EASA] AD 2010-0193, which retained 
the requirements of DGAC France AD F-2002-414R3 and AD F-2002-415R2 
respectively, which were superseded, to add required repetitive 
inspections and lubrications of the new THSA P/N.
    Since those [EASA] ADs were issued, all requirements of EASA AD 
2010-0192 and AD 2010-0193 were transferred into Airbus 
Airworthiness Limitations Section (ALS) Part 4, except the 
requirement of paragraph (2.3) of those [EASA] ADs. At this time, 
compliance with ALS Part 4 tasks is required by EASA AD 2013-0268 
(A330 aeroplanes) and [EASA] AD 2013-0269 (A340 aeroplanes), 
respectively [which correspond to FAA AD 2015-16-02, Amendment 39-
18227 (80 FR 48019, August 11, 2015); and AD 2014-23-17, Amendment 
39-18033 (79 FR 71304, December 2, 2014) (A340 airplanes); 
respectively.]

[[Page 91884]]

    In addition, Airbus developed a Checkable Shear Pin (CSP) for 
the THSA and an associated additional electrical harness, which 
consists of installation of two Electrical Detection Devices (EDD) 
on the lower attachment secondary load path, which gives an 
indication to the Flight Control Primary Computers of secondary load 
path engagement.
    After embodiment of these modifications on an aeroplane, the 
repetitive inspections of the ball-screw assembly for integrity of 
the primary and secondary load paths is no longer required, because 
the failure is detected automatically by this new device.
    For the reasons described above, this [EASA] AD retains only the 
requirement of paragraph (2.3) of EASA AD 2010-0192 and 2010-0193 
[actions following ECAM fault messages], which are superseded, and 
requires the installation of CSP and associated additional 
electrical harness on the THSA of the aeroplane. This [EASA] AD also 
requires, for A340-500/-600 aeroplanes that are post-SB A340-92-5008 
(at Revision 06 or earlier), accomplishment of A340 ALS Part 3 task 
274000-B0002-1-C, providing a grace period of 3 months for 
aeroplanes that have exceeded the applicable threshold or interval.

    The unsafe condition is the degraded operation of the THSA, which 
could result in reduced control of the airplane.
    Model A330-223F and A330-243F airplanes have been removed from the 
applicability of this proposed AD to correspond with the MCAI.
    Required actions include a detailed inspection and corrective 
actions if an ECAM fault message is displayed, repetitive lubrication 
of the THSA ball-nut, and a modification of the THSA by installing a 
CSP and associated electrical harness.
    Required actions also include certain ``Additional Work'' that is 
described in the following service information.
     ``Additional Work'' in Airbus Service Bulletin A330-27-
3143, Revision 01, dated July 10, 2012, is described as removing the 
closing plug from the electrical harness 4515VB and connecting the 
electrical harness 4515VB to the THSA.
     ``Additional Work'' in Airbus Service Bulletin A330-92-
3046, Revision 06, dated November 15, 2013; and Airbus Service Bulletin 
A340-92-4056, Revision 04, dated December 5, 2013; is described as 
replacement of a certain harness item, installation of placards and 
cable support, modification of a certain bracket, and installation of a 
certain spacer.
     ``Additional Work'' in Airbus Service Bulletin A340-92-
5008, Revision 07, dated February 8, 2013, is described as replacing a 
certain wiring harness, replacing a certain THSA harness, installing 
additional placards, and modifying a certain wire harness installation 
order.
    You may examine the MCAI in the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2016-
9393.

Related Service Information Under 1 CFR Part 51

    Airbus has issued the following service information.
    The following service information describes procedures for doing 
repetitive inspections for integrity of the primary and secondary load 
paths of the ball-screw assembly of the THSA. These service bulletins 
are distinct because they apply to different airplane models.
     Airbus Service Bulletin A330-27-3102, Revision 09, dated 
March 29, 2016.
     Airbus Service Bulletin A340-27-4107, Revision 09, dated 
March 29, 2016.
    The following service information describes procedures for 
installing two electrical detection devices, also called CSPs, on the 
lower attachment secondary load path of the THSA, and modifying the 
THSA. These service bulletins are distinct because they apply to 
different airplane models equipped with THS actuators having different 
part numbers.
     Airbus Service Bulletin A330-27-3137, dated March 20, 
2007; Revision 01, dated December 6, 2007; and Revision 02, dated 
January 18, 2010. These service bulletins are distinct because each 
revision contains unique editorial changes.
     Airbus Service Bulletin A330-27-3143, Revision 01, dated 
July 10, 2012.
     Airbus Service Bulletin A340-27-4136, including Appendix 
1, dated March 20, 2007; Revision 01, including Appendix 1, dated 
December 6, 2007; and Revision 02, including Appendix 1, dated February 
24, 2010. These service bulletins are distinct because each revision 
contains unique editorial changes.
     Airbus Service Bulletin A340-27-4143, dated February 21, 
2012.
     Airbus Service Bulletin A340-27-5030, Revision 01, 
including Appendix 1, dated November 20, 2009.
    The following service information describes procedures for 
installing electrical wiring harnesses and brackets to connect the 
secondary nut detection device to the monitoring systems. These service 
bulletins are distinct because they apply to different airplane models.
     Airbus Service Bulletin A330-92-3046, Revision 04, dated 
July 15, 2010; Revision 05, dated November 7, 2011; and Revision 06, 
dated November 15, 2013. These service bulletins are distinct because 
each revision contains unique editorial changes.
     Airbus Service Bulletin A340-92-4056, Revision 03, dated 
July 16, 2010; and Revision 04, dated December 5, 2013. These service 
bulletins are distinct because each revision contains unique editorial 
changes.
     Airbus Service Bulletin A340-92-5008, Revision 07, dated 
February 8, 2013.
    This service information describes procedures for lubrication of 
the THSA ball-nut. These documents are distinct because they apply to 
different airplane models.
     Airbus A330 Airworthiness Limitations Section (ALS) Part 
4--System Equipment Maintenance Requirements (SEMRs), Revision 05, 
dated October 19, 2015, Task 274400-00002-1-E, Lubrication of the THSA 
ball-nut.
     Airbus A340 ALS Part 4--SEMRs, Revision 04, dated October 
19, 2015, Task 274400-00002-1-E, Lubrication of the THSA ball-nut.
     Airbus A340 ALS Part 3--Certification Maintenance 
Requirements (CMRs), Revision 03, dated October 19, 2015, Task 274000-
B0003-1-C, Lubrication of THS Actuator Ball-screw Nut.
    This service information is reasonably available because the 
interested parties have access to it through their normal course of 
business or by the means identified in the ADDRESSES section.

FAA's Determination and Requirements of This Proposed AD

    This product has been approved by the aviation authority of another 
country, and is approved for operation in the United States. Pursuant 
to our bilateral agreement with the State of Design Authority, we have 
been notified of the unsafe condition described in the MCAI and service 
information referenced above. We are proposing this AD because we 
evaluated all pertinent information and determined an unsafe condition 
exists and is likely to exist or develop on other products of the same 
type design.

Explanation of Proposed Compliance Times

    The MCAI requires operators to modify certain airplanes by 
installing a CSP by a certain date. In order to provide operators with 
sufficient time to accomplish the modification, we have determined that 
a 12-month period from the effective date of this AD is acceptable. 
This difference had been coordinated with the EASA.

[[Page 91885]]

Costs of Compliance

    We estimate that this proposed AD affects 33 airplanes of U.S. 
registry.
    The actions required by AD 2013-13-16, and retained in this 
proposed AD take about 1 work-hour per product, at an average labor 
rate of $85 per work-hour. Based on these figures, the estimated cost 
of the actions that are required by AD 2013-13-16 is $85 per product.
    We also estimate that it would take about 67 work-hours per product 
to comply with the basic requirements of this proposed AD. The average 
labor rate is $85 per work-hour. Required parts would cost about 
$14,198 per product. Based on these figures, we estimate the cost of 
this proposed AD on U.S. operators to be $656,469, or $19,893 per 
product.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. ``Subtitle VII: Aviation 
Programs,'' describes in more detail the scope of the Agency's 
authority.
    We are issuing this rulemaking under the authority described in 
``Subtitle VII, Part A, Subpart III, Section 44701: General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would not 
have a substantial direct effect on the States, on the relationship 
between the national Government and the States, or on the distribution 
of power and responsibilities among the various levels of government.
    For the reasons discussed above, I certify this proposed 
regulation:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979);
    3. Will not affect intrastate aviation in Alaska; and
    4. Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13   [Amended]

0
2. The FAA amends Sec.  39.13 by removing Airworthiness Directive (AD) 
2013-13-16, Amendment 39-17504 (78 FR 47537, August 6, 2013), and 
adding the following new AD:

Airbus: Docket No. FAA-2016-9393; Directorate Identifier 2014-NM-
199-AD.

(a) Comments Due Date

    We must receive comments by February 2, 2017.

(b) Affected ADs

    This AD replaces AD 2013-13-16, Amendment 39-17504 (78 FR 47537, 
August 6, 2013) (``AD 2013-13-16'').

(c) Applicability

    This AD applies to the airplanes identified in paragraphs (c)(1) 
and (c)(2) of this AD, certificated in any category.
    (1) Airbus Model A330-201, -202, -203, -223, -243, -301, -302, -
303, -321, -322, -323, -341, -342, and -343 airplanes, all 
manufacturer serial numbers.
    (2) Airbus Model A340-211, -212, -213, -311, -312, -313, -541, 
and -642 airplanes, all manufacturer serial numbers.

(d) Subject

    Air Transport Association (ATA) of America Code 27, Flight 
Controls.

(e) Reason

    This AD was prompted by the determination that a modification 
that automatically detects failure of the ball-screw assembly is 
necessary. We are issuing this AD to detect and correct wear on the 
trimmable horizontal stabilizer actuator (THSA), possibly resulting 
in damage to the ball-screw and fail-safe nut, which could jam the 
THSA and result in reduced control of the airplane.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Actions for Electronic Centralized Aircraft Monitor (ECAM) Fault 
Messages

    For airplanes other than those identified in figure 1 to 
paragraphs (g), (h), and (p) of this AD: If, during any flight, one 
of the ``PRIM X PITCH FAULT'' or ``STAB CTL FAULT'' messages is 
displayed on the ECAM associated with the ``PITCH TRIM ACTR (1CS)'' 
maintenance message, before further flight after each time the 
message is displayed on the ECAM, do the actions specified in 
paragraphs (g)(1) and (g)(2) of this AD.
    (1) Do the applicable detailed inspection of the ball-screw 
assembly for integrity of the primary and secondary load path; check 
the checkable shear pins (CSP), if installed; and do all applicable 
corrective actions; as specified in paragraph (g)(1)(i), (g)(1)(ii), 
or (g)(1)(iii) of this AD. Do all applicable corrective actions 
before further flight.
    (i) For Model A330 series airplanes: Do the actions in 
accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A330-27-3102, Revision 09, dated March 29, 2016, except as 
required by paragraph (n)(1) of this AD.
    (ii) For Model A340-200 and -300 series airplanes: Do the 
actions in accordance with the Accomplishment Instructions of Airbus 
Service Bulletin A340-27-4107, Revision 09, dated March 29, 2016, 
except as required by paragraph (n)(1) of this AD.
    (iii) For Model A340-500 and -600 series airplanes: Do the 
actions using a method approved by the Manager, International 
Branch, ANM-116, Transport Airplane Directorate, FAA; or the 
European Aviation Safety Agency (EASA); or Airbus's EASA Design 
Organization Approval (DOA).

    Note 1 to paragraph (g)(1)(iii) of this AD: Guidance for the 
inspection of the ball-screw assembly can be found in Task 274000-
B0002-1-C, Inspection of the Ball-screw Assembly for Integrity of 
the Primary and Secondary Load Paths, of the Airbus A340 
Airworthiness Limitations Section (ALS) Part 3--Certification 
Maintenance Requirements (CMR), Revision 03, dated October 19, 2015.

    (2) Lubricate the THSA ball-nut in accordance with the 
applicable service information specified in paragraph (g)(2)(i), 
(g)(2)(ii), or (g)(2)(iii) of this AD.
    (i) Task 274400-00002-1-E, Lubrication of the THSA ball-nut, of 
Airbus A330 ALS Part 4--System Equipment Maintenance Requirements 
(SEMR), Revision 05, dated October 19, 2015 (for Model A330 series 
airplanes).
    (ii) Task 274400-00002-1-E, Lubrication of the THSA ball-nut, of 
Airbus A340 ALS Part 4--SEMR, Revision 04, dated October 19, 2015 
(for Model A340-200 and -300 series airplanes).
    (iii) Task 274000-B0003-1-C, Lubrication of THS Actuator Ball-
screw Nut, of Airbus A340 ALS Part 3--CMR, Revision 03, dated 
October 19, 2015 (for Model A340-500 and -600 series airplanes).

[[Page 91886]]



   Figure 1 to Paragraphs (g), (h), and (p) of This AD--Definition of
                             Airplane Groups
------------------------------------------------------------------------
                                                        On which the
                                                    following actions or
             Group               Airplane models     modifications have
                                                         been done
------------------------------------------------------------------------
Group 1 airplanes.............  Airbus Model A330- On which the actions
                                 200 and -300       specified in Airbus
                                 series airplanes.  Service Bulletin
                                                    A330-27-3137, dated
                                                    March 20, 2007, or
                                                    Revision 01, dated
                                                    December 6, 2007;
                                                    and Airbus Service
                                                    Bulletin A330-92-
                                                    3046, Revision 04,
                                                    dated July 16, 2010,
                                                    or Revision 05,
                                                    dated November 7,
                                                    2011; have been
                                                    embodied in service.
                                Airbus Model A340- On which the actions
                                 200 and -300       specified in Airbus
                                 series airplanes.  Service Bulletin
                                                    A340-27-4136,
                                                    including Appendix
                                                    1, dated March 20,
                                                    2007, or Revision
                                                    01, including
                                                    Appendix 1, dated
                                                    December 6, 2007;
                                                    and Airbus Service
                                                    Bulletin A340-92-
                                                    4056, Revision 03,
                                                    dated July 16, 2010;
                                                    have been embodied
                                                    in service.
Group 2 airplanes.............  Airbus Model A330- On which Airbus
                                 200 and -300       Modifications 55780,
                                 series airplanes   52269, and 56056
                                 and Model A340-    have been embodied
                                 200 and -300       in production.
                                 series airplanes.
                                Airbus Model A340- On which Airbus
                                 500 and -600       Modifications 54882,
                                 series airplanes.  52191, and 56058
                                                    have been embodied
                                                    in production.
Group 3 airplanes.............  Airbus Model A330- On which Airbus
                                 200 and -300       Service Bulletin
                                 series airplanes.  A330-27-3137, dated
                                                    March 20, 2007; or
                                                    Revision 01, dated
                                                    December 6, 2007;
                                                    has been embodied in
                                                    service and Airbus
                                                    Modifications 52269
                                                    and 56056 have been
                                                    embodied in
                                                    production.
                                Airbus Model A330- On which Airbus
                                 200 and -300       Modification 55780
                                 series airplanes.  has been embodied in
                                                    production and
                                                    Airbus Service
                                                    Bulletin A330-92-
                                                    3046 Revision 04,
                                                    dated July 16, 2010;
                                                    or Revision 05,
                                                    dated November 07,
                                                    2011 has been
                                                    embodied in service.
                                Airbus Model A340- On which Airbus
                                 200 and -300       Service Bulletin
                                 series airplanes.  A340-27-4136,
                                                    including Appendix
                                                    1, dated March 20,
                                                    2007; or Revision
                                                    01, including
                                                    Appendix 1, dated
                                                    December 6, 2007;
                                                    has been embodied in
                                                    service and Airbus
                                                    Modifications 52269
                                                    and 56056 have been
                                                    embodied in
                                                    production.
                                Airbus Model A340- On which Airbus
                                 200 and -300       Modification 55780
                                 series airplanes.  has been embodied in
                                                    production and
                                                    Airbus Service
                                                    Bulletin A340-92-
                                                    4056, Revision 03,
                                                    dated July 16, 2010,
                                                    has been embodied in
                                                    service.
------------------------------------------------------------------------

(h) Installation of CSP and Electrical Harness

    For all airplanes, except Group 2 airplanes specified in figure 
1 to paragraphs (g), (h), and (p) of this AD, and except for 
airplanes identified in paragraphs (i), (j), and (n)(2) of this AD: 
Within 12 months after the effective date of this AD, modify the 
airplane by installing a CSP on the THSA and an additional 
electrical harness, in accordance with the Accomplishment 
Instructions of the Airbus service information specified in figure 2 
to paragraph (h) of this AD, as applicable to the part number of the 
THSA installed on the airplane, except as provided by paragraph 
(n)(2) of this AD.

Figure 2 to Paragraph (h) of This AD--Applicable Service Information for
                              Modification
------------------------------------------------------------------------
                                                    Service Bulletin for
    THSA Part No. (P/N)      Service Bulletin for    electrical harness
                               CSP installation         installation
------------------------------------------------------------------------
47172-300.................  Airbus Service         Airbus Service
                             Bulletin A330-27-      Bulletin A330-92-
                             3137, Revision 02,     3046, Revision 06,
                             dated January 18,      dated November 15,
                             2010, for Airbus       2013, for Airbus
                             Model A330-200 and -   Model A330-200 and -
                             300 series             300 series
                             airplanes; and         airplanes; and
                            Airbus Service
                             Bulletin A330-27-
                             4136, including
                             Appendix 1, Revision
                             02, dated February
                             24, 2010, for Airbus
                             Model A340-200 and -
                             300 series airplanes
47147-500.................  Airbus Service         Airbus Service
                             Bulletin A330-27-      Bulletin A340-92-
                             3143, Revision 01,     4056, Revision 04,
                             dated July 10, 2012,   dated December 5,
                             for Airbus Model       2013, for Airbus
                             A330-200 and -300      Model A340-200 and -
                             series airplanes;      300 series
                             and                    airplanes.
                            Airbus Service
                             Bulletin A340-27-
                             4143, dated February
                             21, 2012, for Airbus
                             Model A340-200 and -
                             300 series airplanes.
47175-200.................  Airbus Service         Airbus Service
47175-300.................   Bulletin A340-27-      Bulletin A340-92-
                             5030, Revision 01,     5008, Revision 07,
                             including Appendix     dated February 8,
                             1, dated November      2013, for Airbus
                             20, 2009, for Airbus   Model A340-541 and -
                             Model A340-541 and -   642 airplanes.
                             642 airplanes.
------------------------------------------------------------------------

(i) ``Additional Work'' on Previously Modified Airplanes

    For airplanes that have already been modified (installation of 
CSP on the THSA and electrical harness) before the effective date of 
this AD in accordance with the Accomplishment Instructions of any 
previous revision of an Airbus service bulletin specified in figure 
2 to paragraph (h) of this AD, as applicable: Within 12 months after 
the effective date of this AD, do the ``Additional Work'' specified 
in, and in accordance with, the Accomplishment Instructions of the 
applicable Airbus service information specified in figure 2 to 
paragraph (h) of this AD.

(j) Installation of Electrical Harness on Airplanes Equipped With a CSP

    For airplanes having one of the THSAs installed with a part 
number listed in figure 3 to paragraph (j) of this AD, and which 
have been modified by installing a CSP on the THSA as required by 
paragraph (h) of this AD: Within 12 months after the effective date

[[Page 91887]]

of this AD, inspect to determine if the electrical harness 
identified in the applicable Airbus service information specified in 
figure 3 to paragraph (j) of this AD is installed on the airplane, 
and if found not to be installed, modify the airplane by installing 
an electrical harness, in accordance with the Accomplishment 
Instructions of the Airbus service information specified in figure 3 
to paragraph (j) of this AD, as applicable to the part number of the 
THSA installed on the airplane. Airplanes having one of the THSAs 
installed with a part number listed in figure 3 to paragraph (j) of 
this AD already have the CSP installed on the THSA, and only the 
electrical harness must be installed on the airplane.

  Figure 3 to Paragraph (j) of This AD--Electrical Harness Installation
------------------------------------------------------------------------
                                     Service Information for Electrical
             THSA P/N                       Harness Installation
------------------------------------------------------------------------
47172-500, 47172-510, 47172-520,    Airbus Service Bulletin A330-92-
 47172-530, 47147-700, 47147-710.    3046, Revision 06, dated November
                                     15, 2013, for Airbus Model A330-200
                                     and -300 series airplanes.
                                    Airbus Service Bulletin A340-92-
                                     4056, Revision 04, dated December
                                     5, 2013, for Airbus Model A340-200
                                     and -300 series airplanes.
47175-500, 47175-520, 47175-530...  Airbus Service Bulletin A340-92-
                                     5008, Revision 07, dated February
                                     8, 2013, for Airbus Model A340-541
                                     and -642 airplanes.
------------------------------------------------------------------------

(k) Terminating Action for Repetitive Inspections of Airbus Model A330-
200 and -300 Series Airplanes

    Accomplishment of a modification before the effective date of 
this AD in accordance with the Accomplishment Instructions of Airbus 
Service Bulletin A330-27-3137, dated March 20, 2007, or Revision 01, 
dated December 6, 2007; and Airbus Service Bulletin A330-92-3046, 
Revision 04, dated July 15, 2010, or Revision 05, dated November 7, 
2011; terminates the repetitive inspections specified in paragraphs 
(k)(1) through (k)(4) of this AD. Modification of an airplane as 
required by this paragraph does not constitute terminating action 
for the actions specified in paragraph (g)(2) of this AD or the 
additional work specified in paragraph (i) of this AD.
    (1) Task 274400-00001-1-E, Detailed inspection of the ball-screw 
assembly for integrity of the primary and secondary load path and 
check the gap at the secondary nut trunnion, of Airbus A330 ALS Part 
4--SEMR, Revision 05, dated October 19, 2015.
    (2) Task 274400-00001-2-E, Detailed inspection of the ball-screw 
assembly for integrity of the primary and secondary load path and 
check the CSPs, of Airbus A330 ALS Part 4--SEMR, Revision 05, dated 
October 19, 2015.
    (3) Task 274400-00001-3-E, Detailed inspection of the ball-screw 
assembly for integrity of the primary and secondary load path and 
check the CSPs, of Airbus A330 ALS Part 4--SEMR, Revision 05, dated 
October 19, 2015.
    (4) Task 274400-00001-4-E, Detailed inspection of the ball-screw 
assembly for integrity of the primary and secondary load path and 
check the CSPs, of Airbus A330 ALS Part 4--SEMR, Revision 05, dated 
October 19, 2015.

(l) Terminating Action for Repetitive Inspections of Airbus Model A340-
200 and -300 Series Airplanes

    Accomplishment of a modification in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A340-27-4143, 
dated February 21, 2012; and Airbus Service Bulletin A340-92-4056, 
Revision 03, dated July 16, 2010; terminates the actions required by 
paragraph (g)(1) of this AD for modified Airbus Model A340-200 and -
300 series airplanes only. Modification of an airplane as specified 
in this paragraph does not constitute terminating action for the 
actions specified in paragraph (g)(2) of this AD, or the additional 
work specified in paragraph (i) of this AD.

(m) Terminating Action for Repetitive Inspections of Airbus Model A340-
200 and -300 Series Airplanes

    Accomplishment of a modification before the effective date of 
this AD in accordance with the Accomplishment Instructions of Airbus 
Service Bulletin A340-27-4136, including Appendix 1, dated March 20, 
2007, or Revision 01, including Appendix 1, dated December 6, 2007; 
and Airbus Service Bulletin A340-92-4056, Revision 03, dated July 
16, 2010; terminates the repetitive inspections specified in 
paragraphs (m)(1) through (m)(4) of this AD. Modification of an 
airplane as required by this paragraph does not constitute 
terminating action for the actions specified in paragraph (g)(2) of 
this AD, or the additional work specified in paragraph (i) of this 
AD.
    (1) Task 274400-00001-1-E, Detailed inspection of the ball-screw 
assembly for integrity of the primary and secondary load path and 
gap check at the secondary nut trunnion, of Airbus A340 ALS Part 4--
SEMR, Revision 04, dated October 19, 2015.
    (2) Task 274400-00001-2-E, Detailed inspection of the ball-screw 
assembly for integrity of the primary and secondary load path and 
CSP check, of Airbus A340 ALS Part 4--SEMR, Revision 04, dated 
October 19, 2015.
    (3) Task 274400-00001-3-E, Detailed inspection of the ball-screw 
assembly for integrity of the primary and secondary load path and 
CSP check, of Airbus A340 ALS Part 4--SEMR, Revision 04, dated 
October 19, 2015.
    (4) Task 274400-00001-4-E, Detailed inspection of the ball-screw 
assembly for integrity of the primary and secondary load path and 
CSP check, of A340 ALS Part 4--SEMR, Revision 04, dated October 19, 
2015.

(n) Exceptions to the Actions in Certain Service Information and 
Paragraph (h) of This AD

    (1) Where Airbus Service Bulletin A330-27-3102, Revision 09, 
dated March 29, 2016 (for Model A330 series airplanes); or Airbus 
Service Bulletin A340-27-4107, Revision 09, dated March 29, 2016 
(for Model A340 series airplanes); specifies to contact Airbus for a 
damage assessment: Before further flight, accomplish the required 
actions in accordance with the procedures specified in paragraph 
(s)(2) of this AD.
    (2) For airplanes that already had the electrical harness 
installed during production using Airbus Modifications 52269 and 
56056 for Airbus Model A330-200 and -300 series airplanes and Airbus 
Model A340-200 and -300 series airplanes, and using Airbus 
Modifications 52191 and 56058 for Model A340-500 and -600 series 
airplanes: Only the CSP must be installed on the THSA in accordance 
with applicable Airbus service bulletins and within the compliance 
time specified in paragraph (h) of this AD.

(o) Terminating Action for Repetitive Inspections for Airplanes on 
Which Actions Required by Paragraph (h), (i), or (j) of This AD Are 
Done

    Modification of an airplane as required by paragraph (h), (i), 
or (j) of this AD, as applicable, constitutes terminating action for 
that airplane for the applicable actions identified in paragraphs 
(o)(1) through (o)(4) of this AD.
    (1) For all airplanes: The actions required by paragraph (g) of 
this AD.
    (2) For Model A340-500 and -600 series airplanes: Task 274000-
B0002-1-C, Inspection of the Ball-screw Assembly for Integrity of 
the Primary and Secondary Load Paths, of Airbus A340 ALS Part 3--
CMR, Revision 03, dated October 19, 2015.
    (3) For Model A330-200 and -300 series airplanes: The ALS tasks 
identified in paragraphs (k)(1) through (k)(4) of this AD.
    (4) For Model A340-200 and -300 series airplanes: The ALS tasks 
identified in paragraphs (m)(1) through (m)(4) of this AD.

(p) Ball-Screw Assembly Inspection for Certain Airplanes

    For Model A340-500 and -600 airplanes that are in post-Airbus 
Service Bulletin A340-92-5008, at Revision 06 or earlier, 
configuration: Before exceeding the threshold or interval, as 
applicable, of Task 274000-B0002-1-C, Inspection of the Ball-screw 
Assembly for Integrity of the Primary and Secondary Load Paths, of 
Airbus A340 ALS Part 3--CMR, Revision 03, dated October 19, 2015, or 
within 3 months after the effective date of this AD, whichever 
occurs later, accomplish Task 274000-B0002-1-C, Inspection of the 
Ball-screw Assembly for

[[Page 91888]]

Integrity of the Primary and Secondary Load Paths, of Airbus A340 
ALS Part 3--CMR, Revision 03, dated October 19, 2015; and do all 
applicable corrective actions. Do all applicable corrective actions 
before further flight using a method approved by the Manager, 
International Branch, ANM-116, Transport Airplane Directorate, FAA; 
or the EASA; or Airbus's EASA DOA. Repeat Task 274000-B0002-1-C, 
Inspection of the Ball-screw Assembly for Integrity of the Primary 
and Secondary Load Paths, thereafter at the applicable intervals 
specified in Airbus A340 ALS Part 3--CMR, Revision 03, dated October 
19, 2015.

(q) Parts Installation Prohibitions

    (1) For all airplanes except Group 2 airplanes as identified in 
figure 1 to paragraphs (g), (h), and (p) of this AD: After 
modification of the airplane as required by paragraph (h), (i), or 
(j) of this AD, as applicable, no person may install any THSA having 
P/N 47172-300, P/N 47147-500, P/N 47175-200, or P/N 47175-300.
    (2) For Group 2 airplanes, as identified in figure 1 to 
paragraphs (g), (h), and (p) of this AD: As of the effective date of 
this AD, no person may install on any Group 2 airplane any THSA 
having P/N 47172-300, P/N 47147-500, P/N 47175-200, or P/N 47175-
300.

(r) Credit for Previous Actions

    This paragraph provides credit for actions required by paragraph 
(g)(2) of this AD, if those actions were performed before the 
effective date of this AD using the applicable service information 
specified in paragraphs (r)(1) through (r)(4) of this AD.
    (1) Task 274400-00002-1-E, Lubrication of the THSA ball-nut, of 
Airbus A330 ALS Part 4--Ageing Systems Maintenance, Revision 03, 
dated September 9, 2011 (for Model A330 series airplanes).
    (2) Task 274400-00002-1-E, Lubrication of the THSA ball-nut, of 
Airbus A330 ALS Part 4--Ageing Systems Maintenance, Revision 04, 
dated August 27, 2013 (for Model A330 series airplanes).
    (3) Task 274400-00002-1-E, Lubrication of the THSA ball-nut, of 
Airbus A340 ALS Part 4--Ageing Systems Maintenance, Revision 02, 
dated October 12, 2011 (for Model A340-200 and -300 series 
airplanes).
    (4) Task 274400-00002-1-E, Lubrication of the THSA ball-nut, of 
Airbus A340 ALS Part 4--Ageing Systems Maintenance, Revision 03, 
dated November 15, 2012 (for Model A340-200 and -300 series 
airplanes).

(s) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
has the authority to approve AMOCs for this AD, if requested using 
the procedures found in 14 CFR 39.19. In accordance with 14 CFR 
39.19, send your request to your principal inspector or local Flight 
Standards District Office, as appropriate. If sending information 
directly to the International Branch, send it to ATTN: 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: 9-ANM-116-ACO-AMOC-REQUESTS@faa.gov. Before using 
any approved AMOC, notify your appropriate principal inspector, or 
lacking a principal inspector, the manager of the local flight 
standards district office/certificate holding district office. The 
AMOC approval letter must specifically reference this AD.
    (2) Contacting the Manufacturer: As of the effective date of 
this AD, for any requirement in this AD to obtain corrective actions 
from a manufacturer, the action must be accomplished using a method 
approved by the Manager, International Branch, ANM-116, Transport 
Airplane Directorate, FAA; or EASA; or Airbus's EASA DOA. If 
approved by the DOA, the approval must include the DOA-authorized 
signature.

(t) Related Information

    (1) Refer to Continuing Airworthiness Information (MCAI) EASA 
Airworthiness Directive 2014-0219, dated September 29, 2014, for 
related information. This MCAI may be found in the AD docket on the 
Internet at https://www.regulations.gov by searching for and locating 
Docket No. FAA-2016-9393.
    (2) 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 airworthiness.A330-A340@airbus.com; 
Internet https://www.airbus.com.
    (3) You may view this service information at the FAA, Transport 
Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For 
information on the availability of this material at the FAA, call 
425-227-1221.

    Issued in Renton, Washington, on November 10, 2016.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-29683 Filed 12-16-16; 8:45 am]
BILLING CODE 4910-13-P