81 FR 91882 - Airworthiness Directives; Airbus Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 81, Issue 243 (December 19, 2016)
Federal Aviation Administration
Federal Register Volume 81, Issue 243 (December 19, 2016)
| Page Range | 91882-91888 | |
| FR Document | 2016-29683 |
[Federal Register Volume 81, Number 243 (Monday, December 19, 2016)] [Proposed Rules] [Pages 91882-91888] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2016-29683] ----------------------------------------------------------------------- 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 http://www.regulations.gov. Follow the instructions for submitting comments. Fax: 202-493-2251. Mail: U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590. Hand Delivery: U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this 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 [email protected]; Internet http://www.airbus.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221. Examining the AD Docket You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016- 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 http://www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion On 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 http://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: [email protected]. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. The AMOC approval letter must specifically reference this AD. (2) Contacting the Manufacturer: 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 http://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 [email protected]; Internet http://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
![91882 Federal Register / Vol. 81, No. 243 / Monday, December 19, 2016 / Proposed Rules
service after July 29, 2016, whichever occurs (ii) Thereafter, perform a USI of the stage (iii) Compliance with paragraph (f)(2)(i) of
later. 8 aft web upper face every 500 cycles since this AD is terminating action for the initial
last inspection. 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 ...................................................................... GWN005MF GWNBK753 GWNBS077 GWNBS497 GWNBS724
GWN005MG GWNBK754 GWNBS078 GWNBS499 GWNBS794
GWN0087M GWNBK841 GWNBS079 GWNBS500 GWNBS810
GWN0087N GWNBK842 GWNBS080 GWNBS501 GWNBS811
GWN00DGK GWNBK843 GWNBS081 GWNBS502 GWNBS812
GWN00DGL GWNBK844 GWNBS157 GWNBS609 GWNBS813
GWNBJ992 GWNBK952 GWNBS158 GWNBS610 GWNBS814
GWNBK667 GWNBK953 GWNBS159 GWNBS611 GWNBS910
GWNBK674 GWNBK954 GWNBS160 GWNBS612 GWNBS911
GWNBK675 GWNBK955 GWNBS266 GWNBS613 GWNBS912
GWNBK743 GWNBK956 GWNBS267 GWNBS614 GWNBS914
GWNBK744 GWNBK957 GWNBS268 GWNBS721 GWNBS915
GWNBK751 GWNBK958 GWNBS269 GWNBS722 GWNBS982
GWNBK752 GWNBK959 GWNBS270 GWNBS723 GWNBS983
1844M90G02 ...................................................................... GWN00C2T GWN01C5N GWN02N8D GWN03RTM GWN04E21
GWN00C2V GWN01GE2 GWN02T3R GWN03RTP GWN04GHT
GWN00G2N GWN01GE3 GWN02WGM GWN040RL GWN04GHW
GWN00G2P GWN01GE4 GWN0311K GWN040RM GWN04GJ0
GWN00PFP GWN01GE6 GWN035PP GWN040RN GWN04JW6
GWN00PFR GWN01WH1 GWN038TD GWN040RP GWN04JW7
GWN00T2N GWN02688 GWN039TG GWN04202 GWN04JW8
GWN00YHV GWN02689 GWN03G2R GWN0435W GWN04L7K
GWN0125G GWN0268A GWN03G2W GWN04360 GWN04L7L
GWN0125H GWN02DP2 GWN03G30 GWN04361 GWN04MT7
GWN0166K GWN02DP3 GWN03JPC GWN04362 GWN04MT8
GWN01C5K GWN02F9F GWN03JPD GWN04ATG GWNBS984
GWN01C5L GWN02F9G GWN03N8P GWN04ATH
GWN01C5M GWN02L9T GWN03N8R GWN04E20
(2) For all HPC stage 8–10 spools, P/N (2) GE GE90 Service Bulletin (SB) SB 72– DEPARTMENT OF TRANSPORTATION
1694M80G04, 1844M90G01, or 1844M90G02, 1151 R00, dated June 10, 2016, and Chapter
perform an eddy current inspection (ECI) of 72–31–08, Special Procedures 003, and Federal Aviation Administration
the stage 8 aft upper face as follows: Chapter 72–00–31, Special Procedures 006,
(i) Perform an initial ECI of the stage 8 aft in GE GE90 Engine Manual, GEK100700,
web upper face at the next shop visit after the
14 CFR Part 39
Revision 68, dated September 1, 2016, can be
effective date of this AD. obtained from GE using the contact [Docket No. FAA–2016–9393; Directorate
(ii) Thereafter, perform an ECI of the stage information in paragraph (i)(3) of this AD. Identifier 2014–NM–199–AD]
8 aft web upper face at each subsequent shop This SB describes procedures for an on-wing
visit. RIN 2120–AA64
USI of the stage 8 web of the stage 8–10
(3) Remove from service any HPC stage 8–
10 spool that fails the inspection required by spool. These engine manual procedures
describe how to perform ECI of the stage 8 Airworthiness Directives; Airbus
paragraphs (f)(1) or (f)(2) of this AD, and
replace with a spool eligible for installation. aft web of the stage 8–10 spool. Airplanes
(3) For service information identified in
(g) Definition this proposed AD, contact General Electric
AGENCY: Federal Aviation
For the purpose of this AD, an engine shop Company, GE-Aviation, Room 285, 1 Administration (FAA), DOT.
visit is the induction of an engine into the Neumann Way, Cincinnati, OH 45215, ACTION: Notice of proposed rulemaking
shop for maintenance during which the phone: 513–552–3272; fax: 513–552–3329; (NPRM).
compressor discharge pressure seal face is email: geae.aoc@ge.com.
exposed. (4) You may view this service information SUMMARY: We propose to supersede
(h) Alternative Methods of Compliance at the FAA, Engine & Propeller Directorate, Airworthiness Directive (AD) 2013–13–
(AMOCs) 1200 District Avenue, Burlington, MA. For 16, which applies to all Airbus Model
information on the availability of this A330–200, A330–200 Freighter, A330–
The Manager, Engine Certification Office, material at the FAA, call 781–238–7125.
FAA, may approve AMOCs for this AD. Use 300 series airplanes, and all Airbus
the procedures found in 14 CFR 39.19 to (j) Material Incorporated by Reference Model A340–200, –300, –500, and –600
make your request. You may email your series airplanes. AD 2013–13–16
sradovich on DSK3GMQ082PROD with PROPOSALS
None.
request to: ANE-AD-AMOC@faa.gov. currently requires repetitive inspections
Issued in Burlington, Massachusetts, on for discrepancies of the ball-screw
(i) Related Information November 29, 2016. assembly of the trimmable horizontal
(1) For more information about this AD, Colleen M. D’Alessandro,
contact John Frost, Aerospace Engineer,
stabilizer actuator (THSA), repetitive
Manager, Engine & Propeller Directorate, greasing of the THSA ball-nut, and
Engine Certification Office, FAA, 1200
Aircraft Certification Service. replacement of the THSA if necessary;
District Avenue, Burlington, MA 01803;
phone: 781–238–7756; fax: 781–238–7199; [FR Doc. 2016–29679 Filed 12–16–16; 8:45 am] and modification or replacement (as
email: john.frost@faa.gov. BILLING CODE 4910–13–P applicable) of the ball-nut assembly,
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![Federal Register / Vol. 81, No. 243 / Monday, December 19, 2016 / Proposed Rules 91883
which ends certain repetitive Transport Airplane Directorate, FAA, This condition, if not detected and
inspections. Since we issued AD 2013– 1601 Lind Avenue SW., Renton, WA corrected, could damage the ball-screw and
13–16, we have determined that a 98057–3356; telephone 425–227–1138; the fail-safe nut, possibly resulting in
jamming of the THSA and consequent
modification that automatically detects fax 425–227–1149. reduced control of the aeroplane.
failure of the ball-screw assembly is SUPPLEMENTARY INFORMATION: To detect at an early stage any distortion
necessary. This proposed AD would or initiation of disconnection, [Directorate
require an inspection, corrective actions Comments Invited
General for Civil Aviation] DGAC France
if necessary, lubrication of the ball-nut, We invite you to send any written issued AD 2001–356 and AD 2001–357 to
modification of the THSA, and removal relevant data, views, or arguments about require repetitive inspections of the transfer
of certain airplanes from the this proposed AD. Send your comments tubes and their collars and, depending on
to an address listed under the findings, corrective action(s).
applicability. We are proposing this AD
Prompted by another case of transfer tube
to address the unsafe condition on these ADDRESSES section. Include ‘‘Docket No.
disconnection, DGAC France issued AD
products. FAA–2016–9393; Directorate Identifier 2001–356R2 and AD 2001–357R2 to require
DATES: We must receive comments on 2014–NM–199–AD’’ at the beginning of additional repetitive greasing and
this proposed AD by February 2, 2017. your comments. We specifically invite reinforcement of the ball-nut maintenance
ADDRESSES: You may send comments by
comments on the overall regulatory, greasing instructions.
economic, environmental, and energy Subsequently, DGAC France issued AD
any of the following methods: 2002–037 and AD 2002–038 to require a
• Federal eRulemaking Portal: Go to aspects of this proposed AD. We will
modification that was also terminating action
http://www.regulations.gov. Follow the consider all comments received by the
for the repetitive inspections and greasing
instructions for submitting comments. closing date and may amend this tasks required by DGAC France AD 2001–
• Fax: 202–493–2251. proposed AD based on those comments. 356R2 and AD 2001–357R2 for the THSA P/
• Mail: U.S. Department of We will post all comments we N 47172 by application of Service Bulletin
Transportation, Docket Operations, M– receive, without change, to http:// (SB) A330–27–3085 or SB A340–27–4089
30, West Building Ground Floor, Room www.regulations.gov, including any (equivalent to Airbus production
personal information you provide. We modification 49590), as applicable, changing
W12–140, 1200 New Jersey Avenue SE., the THSA P/N from 47172 to 47172–300.
Washington, DC 20590. will also post a report summarizing each
Later on, DGAC France issued AD 2002–
• Hand Delivery: U.S. Department of substantive verbal contact we receive
414 (later revised to R3) and AD 2002–415
Transportation, Docket Operations, M– about this proposed AD. (later revised to R2), which superseded the
30, West Building Ground Floor, Room Discussion DGAC France AD 2001–356R2, AD 2001–
W12–140, 1200 New Jersey Avenue SE., 357R2, AD 2002–037, and AD 2002–038,
On June 21, 2013, we issued AD requiring:
Washington, DC, between 9 a.m. and 5 2013–13–16, Amendment 39–17504 (78
p.m., Monday through Friday, except —Repetitive inspections of all THSA P/N in
FR 47537, August 6, 2013) (‘‘AD 2013– service,
Federal holidays. 13–16’’). AD 2013–13–16 requires —repetitive lubrication of some THSA P/N,
For service information identified in and
actions intended to address an unsafe
this NPRM, contact Airbus SAS, —replacement of THSA P/N 47172, 47147–
condition on all Airbus Model A330–
Airworthiness Office—EAL, 1 Rond 400 and 47147–2XX/–3XX.
200, A330–200 Freighter, and A330–300
Point Maurice Bellonte, 31707 Blagnac In addition, the electrical flight control
series airplanes, and all Airbus Model
Cedex, France; telephone +33 5 61 93 36 computers monitor the operation of the
A340–200, –300, –500, and –600 series
96; fax +33 5 61 93 45 80; email THSA and the jamming of this actuator could
airplanes. be detected and indicated by messages on the
airworthiness.A330-A340@airbus.com; Since we issued AD 2013–13–16,
Internet http://www.airbus.com. You maintenance system and on the [electronic
Airbus transferred most of the centralized aircraft monitor] ECAM. For that
may view this referenced service requirements of AD 2013–13–16 into reason, DGAC France AD 2002–414 and AD
information at the FAA, Transport airworthiness limitations, except the 2002–415 also required inspection of the
Airplane Directorate, 1601 Lind Avenue requirements for ECAM fault messages. THSA after display of such message(s).
SW., Renton, WA. For information on The European Aviation Safety Agency After those [DGAC France] ADs were
the availability of this material at the (EASA) which is the Technical Agent issued, Airbus introduced 4 new THSA, P/N
FAA, call 425–227–1221. 47172–500, P/N 47172–510, P/N 47172–520
for the Member States of the European
and P/N 47172–530.
Examining the AD Docket Union, has issued EASA Airworthiness As these new THSA also needed to be
Directive 2014–0219, dated September inspected/lubricated, EASA issued [EASA]
You may examine the AD docket on 29, 2014 (referred to after this as the AD 2010–0192 and [EASA] AD 2010–0193,
the Internet at http:// Mandatory Continuing Airworthiness which retained the requirements of DGAC
www.regulations.gov by searching for Information, or ‘‘the MCAI’’), to correct France AD F–2002–414R3 and AD F–2002–
and locating Docket No. FAA–2016– an unsafe condition on all Airbus Model 415R2 respectively, which were superseded,
9393; or in person at the Docket A330 and Model A340 series airplanes. to add required repetitive inspections and
Management Facility between 9 a.m. The MCAI states:
lubrications of the new THSA P/N.
and 5 p.m., Monday through Friday, Since those [EASA] ADs were issued, all
except Federal holidays. The AD docket Several cases of transfer tube requirements of EASA AD 2010–0192 and
disconnection from the ball-nut of the AD 2010–0193 were transferred into Airbus
contains this proposed AD, the
trimmable horizontal stabilizer actuator Airworthiness Limitations Section (ALS) Part
regulatory evaluation, any comments (THSA) part number (P/N) 47172 and 47147– 4, except the requirement of paragraph (2.3)
received, and other information. The 400 were detected on the ground during of those [EASA] ADs. At this time,
sradovich on DSK3GMQ082PROD with PROPOSALS
street address for the Docket Operations greasing and maintenance. Investigation compliance with ALS Part 4 tasks is required
office (telephone 800–647–5527) is in results showed that this was caused by water by EASA AD 2013–0268 (A330 aeroplanes)
the ADDRESSES section. Comments will ingress into the ball-nut, resulting in the and [EASA] AD 2013–0269 (A340
be available in the AD docket shortly jamming of the ball transfer circuit when the aeroplanes), respectively [which correspond
after receipt. water froze. If the three (independent) ball to FAA AD 2015–16–02, Amendment 39–
circuits fail, then the THSA operates on a 18227 (80 FR 48019, August 11, 2015); and
FOR FURTHER INFORMATION CONTACT: fail-safe nut (which operates without balls), AD 2014–23–17, Amendment 39–18033 (79
Vladimir Ulyanov, Aerospace Engineer, which jams after several movements on the FR 71304, December 2, 2014) (A340
International Branch, ANM–116, ball-screw of the THSA. airplanes); respectively.]
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![91884 Federal Register / Vol. 81, No. 243 / Monday, December 19, 2016 / Proposed Rules
In addition, Airbus developed a Checkable You may examine the MCAI in the distinct because each revision contains
Shear Pin (CSP) for the THSA and an AD docket on the Internet at http:// unique editorial changes.
associated additional electrical harness,
which consists of installation of two
www.regulations.gov by searching for • Airbus Service Bulletin A340–92–
Electrical Detection Devices (EDD) on the
and locating Docket No. FAA–2016– 4056, Revision 03, dated July 16, 2010;
lower attachment secondary load path, which 9393. and Revision 04, dated December 5,
gives an indication to the Flight Control Related Service Information Under 1 2013. These service bulletins are
Primary Computers of secondary load path distinct because each revision contains
engagement.
CFR Part 51
unique editorial changes.
After embodiment of these modifications Airbus has issued the following
on an aeroplane, the repetitive inspections of • Airbus Service Bulletin A340–92–
service information. 5008, Revision 07, dated February 8,
the ball-screw assembly for integrity of the The following service information
primary and secondary load paths is no 2013.
longer required, because the failure is describes procedures for doing
This service information describes
detected automatically by this new device. repetitive inspections for integrity of the
procedures for lubrication of the THSA
For the reasons described above, this primary and secondary load paths of the
ball-nut. These documents are distinct
[EASA] AD retains only the requirement of ball-screw assembly of the THSA. These
paragraph (2.3) of EASA AD 2010–0192 and because they apply to different airplane
service bulletins are distinct because
2010–0193 [actions following ECAM fault models.
they apply to different airplane models.
messages], which are superseded, and • Airbus Service Bulletin A330–27– • Airbus A330 Airworthiness
requires the installation of CSP and Limitations Section (ALS) Part 4—
associated additional electrical harness on 3102, Revision 09, dated March 29,
2016. System Equipment Maintenance
the THSA of the aeroplane. This [EASA] AD Requirements (SEMRs), Revision 05,
also requires, for A340–500/–600 aeroplanes • Airbus Service Bulletin A340–27–
that are post-SB A340–92–5008 (at Revision 4107, Revision 09, dated March 29, dated October 19, 2015, Task 274400–
06 or earlier), accomplishment of A340 ALS 2016. 00002–1–E, Lubrication of the THSA
Part 3 task 274000–B0002–1–C, providing a The following service information ball-nut.
grace period of 3 months for aeroplanes that describes procedures for installing two • Airbus A340 ALS Part 4—SEMRs,
have exceeded the applicable threshold or Revision 04, dated October 19, 2015,
interval. electrical detection devices, also called
CSPs, on the lower attachment Task 274400–00002–1–E, Lubrication of
The unsafe condition is the degraded secondary load path of the THSA, and the THSA ball-nut.
operation of the THSA, which could modifying the THSA. These service • Airbus A340 ALS Part 3—
result in reduced control of the airplane. bulletins are distinct because they apply Certification Maintenance Requirements
Model A330–223F and A330–243F to different airplane models equipped (CMRs), Revision 03, dated October 19,
airplanes have been removed from the with THS actuators having different part 2015, Task 274000–B0003–1–C,
applicability of this proposed AD to numbers. Lubrication of THS Actuator Ball-screw
correspond with the MCAI.
• Airbus Service Bulletin A330–27– Nut.
Required actions include a detailed
inspection and corrective actions if an 3137, dated March 20, 2007; Revision This service information is reasonably
ECAM fault message is displayed, 01, dated December 6, 2007; and available because the interested parties
repetitive lubrication of the THSA ball- Revision 02, dated January 18, 2010. have access to it through their normal
nut, and a modification of the THSA by These service bulletins are distinct course of business or by the means
installing a CSP and associated because each revision contains unique identified in the ADDRESSES section.
electrical harness. editorial changes.
FAA’s Determination and Requirements
Required actions also include certain • Airbus Service Bulletin A330–27–
of This Proposed AD
‘‘Additional Work’’ that is described in 3143, Revision 01, dated July 10, 2012.
the following service information. • Airbus Service Bulletin A340–27– This product has been approved by
• ‘‘Additional Work’’ in Airbus 4136, including Appendix 1, dated the aviation authority of another
Service Bulletin A330–27–3143, March 20, 2007; Revision 01, including country, and is approved for operation
Revision 01, dated July 10, 2012, is Appendix 1, dated December 6, 2007; in the United States. Pursuant to our
described as removing the closing plug and Revision 02, including Appendix 1, bilateral agreement with the State of
from the electrical harness 4515VB and dated February 24, 2010. These service Design Authority, we have been notified
connecting the electrical harness bulletins are distinct because each of the unsafe condition described in the
4515VB to the THSA. revision contains unique editorial MCAI and service information
• ‘‘Additional Work’’ in Airbus changes. referenced above. We are proposing this
Service Bulletin A330–92–3046, • Airbus Service Bulletin A340–27– AD because we evaluated all pertinent
Revision 06, dated November 15, 2013; 4143, dated February 21, 2012. information and determined an unsafe
and Airbus Service Bulletin A340–92– • Airbus Service Bulletin A340–27– condition exists and is likely to exist or
4056, Revision 04, dated December 5, 5030, Revision 01, including Appendix develop on other products of the same
2013; is described as replacement of a 1, dated November 20, 2009. type design.
certain harness item, installation of The following service information
Explanation of Proposed Compliance
placards and cable support, describes procedures for installing
Times
modification of a certain bracket, and electrical wiring harnesses and brackets
installation of a certain spacer. to connect the secondary nut detection The MCAI requires operators to
sradovich on DSK3GMQ082PROD with PROPOSALS
• ‘‘Additional Work’’ in Airbus device to the monitoring systems. These modify certain airplanes by installing a
Service Bulletin A340–92–5008, service bulletins are distinct because CSP by a certain date. In order to
Revision 07, dated February 8, 2013, is they apply to different airplane models. provide operators with sufficient time to
described as replacing a certain wiring • Airbus Service Bulletin A330–92– accomplish the modification, we have
harness, replacing a certain THSA 3046, Revision 04, dated July 15, 2010; determined that a 12-month period from
harness, installing additional placards, Revision 05, dated November 7, 2011; the effective date of this AD is
and modifying a certain wire harness and Revision 06, dated November 15, acceptable. This difference had been
installation order. 2013. These service bulletins are coordinated with the EASA.
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![Federal Register / Vol. 81, No. 243 / Monday, December 19, 2016 / Proposed Rules 91885
Costs of Compliance 4. Will not have a significant (f) Compliance
We estimate that this proposed AD economic impact, positive or negative, Comply with this AD within the
affects 33 airplanes of U.S. registry. on a substantial number of small entities compliance times specified, unless already
under the criteria of the Regulatory done.
The actions required by AD 2013–13–
16, and retained in this proposed AD Flexibility Act. (g) Actions for Electronic Centralized
take about 1 work-hour per product, at List of Subjects in 14 CFR Part 39 Aircraft Monitor (ECAM) Fault Messages
an average labor rate of $85 per work- For airplanes other than those identified in
hour. Based on these figures, the Air transportation, Aircraft, Aviation figure 1 to paragraphs (g), (h), and (p) of this
estimated cost of the actions that are safety, Incorporation by reference, AD: If, during any flight, one of the ‘‘PRIM
required by AD 2013–13–16 is $85 per Safety. X PITCH FAULT’’ or ‘‘STAB CTL FAULT’’
product. messages is displayed on the ECAM
The Proposed Amendment associated with the ‘‘PITCH TRIM ACTR
We also estimate that it would take (1CS)’’ maintenance message, before further
about 67 work-hours per product to Accordingly, under the authority flight after each time the message is
comply with the basic requirements of delegated to me by the Administrator, displayed on the ECAM, do the actions
this proposed AD. The average labor the FAA proposes to amend 14 CFR part specified in paragraphs (g)(1) and (g)(2) of
rate is $85 per work-hour. Required 39 as follows: this AD.
parts would cost about $14,198 per (1) Do the applicable detailed inspection of
product. Based on these figures, we PART 39—AIRWORTHINESS the ball-screw assembly for integrity of the
estimate the cost of this proposed AD on DIRECTIVES primary and secondary load path; check the
U.S. operators to be $656,469, or checkable shear pins (CSP), if installed; and
do all applicable corrective actions; as
$19,893 per product. ■ 1. The authority citation for part 39 specified in paragraph (g)(1)(i), (g)(1)(ii), or
Authority for This Rulemaking continues to read as follows: (g)(1)(iii) of this AD. Do all applicable
Authority: 49 U.S.C. 106(g), 40113, 44701. corrective actions before further flight.
Title 49 of the United States Code (i) For Model A330 series airplanes: Do the
specifies the FAA’s authority to issue § 39.13 [Amended] actions in accordance with the
rules on aviation safety. Subtitle I, Accomplishment Instructions of Airbus
section 106, describes the authority of ■ 2. The FAA amends § 39.13 by Service Bulletin A330–27–3102, Revision 09,
the FAA Administrator. ‘‘Subtitle VII: removing Airworthiness Directive (AD) dated March 29, 2016, except as required by
Aviation Programs,’’ describes in more 2013–13–16, Amendment 39–17504 (78 paragraph (n)(1) of this AD.
detail the scope of the Agency’s FR 47537, August 6, 2013), and adding (ii) For Model A340–200 and –300 series
the following new AD: airplanes: Do the actions in accordance with
authority. the Accomplishment Instructions of Airbus
We are issuing this rulemaking under Airbus: Docket No. FAA–2016–9393; Service Bulletin A340–27–4107, Revision 09,
the authority described in ‘‘Subtitle VII, Directorate Identifier 2014–NM–199–AD. dated March 29, 2016, except as required by
Part A, Subpart III, Section 44701: (a) Comments Due Date paragraph (n)(1) of this AD.
General requirements.’’ Under that (iii) For Model A340–500 and –600 series
section, Congress charges the FAA with We must receive comments by February 2, airplanes: Do the actions using a method
2017. approved by the Manager, International
promoting safe flight of civil aircraft in
air commerce by prescribing regulations (b) Affected ADs Branch, ANM–116, Transport Airplane
for practices, methods, and procedures Directorate, FAA; or the European Aviation
This AD replaces AD 2013–13–16, Safety Agency (EASA); or Airbus’s EASA
the Administrator finds necessary for Amendment 39–17504 (78 FR 47537, August Design Organization Approval (DOA).
safety in air commerce. This regulation 6, 2013) (‘‘AD 2013–13–16’’). Note 1 to paragraph (g)(1)(iii) of this AD:
is within the scope of that authority Guidance for the inspection of the ball-screw
(c) Applicability
because it addresses an unsafe condition assembly can be found in Task 274000–
that is likely to exist or develop on This AD applies to the airplanes identified B0002–1–C, Inspection of the Ball-screw
products identified in this rulemaking in paragraphs (c)(1) and (c)(2) of this AD, Assembly for Integrity of the Primary and
action. certificated in any category. Secondary Load Paths, of the Airbus A340
(1) Airbus Model A330–201, –202, –203, Airworthiness Limitations Section (ALS) Part
Regulatory Findings –223, –243, –301, –302, –303, –321, –322, 3—Certification Maintenance Requirements
We determined that this proposed AD –323, –341, –342, and –343 airplanes, all (CMR), Revision 03, dated October 19, 2015.
manufacturer serial numbers. (2) Lubricate the THSA ball-nut in
would not have federalism implications
(2) Airbus Model A340–211, –212, –213, accordance with the applicable service
under Executive Order 13132. This –311, –312, –313, –541, and –642 airplanes,
proposed AD would not have a information specified in paragraph (g)(2)(i),
all manufacturer serial numbers. (g)(2)(ii), or (g)(2)(iii) of this AD.
substantial direct effect on the States, on
(d) Subject (i) Task 274400–00002–1–E, Lubrication of
the relationship between the national the THSA ball-nut, of Airbus A330 ALS Part
Government and the States, or on the Air Transport Association (ATA) of 4—System Equipment Maintenance
distribution of power and America Code 27, Flight Controls. Requirements (SEMR), Revision 05, dated
responsibilities among the various (e) Reason October 19, 2015 (for Model A330 series
levels of government. airplanes).
For the reasons discussed above, I This AD was prompted by the (ii) Task 274400–00002–1–E, Lubrication
determination that a modification that of the THSA ball-nut, of Airbus A340 ALS
certify this proposed regulation:
sradovich on DSK3GMQ082PROD with PROPOSALS
automatically detects failure of the ball-screw Part 4—SEMR, Revision 04, dated October
1. Is not a ‘‘significant regulatory assembly is necessary. We are issuing this
action’’ under Executive Order 12866; 19, 2015 (for Model A340–200 and –300
AD to detect and correct wear on the series airplanes).
2. Is not a ‘‘significant rule’’ under the trimmable horizontal stabilizer actuator (iii) Task 274000–B0003–1–C, Lubrication
DOT Regulatory Policies and Procedures (THSA), possibly resulting in damage to the of THS Actuator Ball-screw Nut, of Airbus
(44 FR 11034, February 26, 1979); ball-screw and fail-safe nut, which could jam A340 ALS Part 3—CMR, Revision 03, dated
3. Will not affect intrastate aviation in the THSA and result in reduced control of October 19, 2015 (for Model A340–500 and
Alaska; and the airplane. –600 series airplanes).
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![91888 Federal Register / Vol. 81, No. 243 / Monday, December 19, 2016 / Proposed Rules
Integrity of the Primary and Secondary Load Airplane Directorate, FAA, 1601 Lind SUMMARY: In the Rules and Regulations
Paths, of Airbus A340 ALS Part 3—CMR, Avenue SW., Renton, WA 98057–3356; section of this issue of the Federal
Revision 03, dated October 19, 2015; and do telephone 425–227–1138; fax 425–227–1149. Register, the IRS is issuing temporary
all applicable corrective actions. Do all Information may be emailed to: 9-ANM-116- regulations that provide guidance
applicable corrective actions before further ACO-AMOC-REQUESTS@faa.gov. Before
flight using a method approved by the using any approved AMOC, notify your
regarding the distribution by a
Manager, International Branch, ANM–116, appropriate principal inspector, or lacking a distributing corporation of stock or
Transport Airplane Directorate, FAA; or the principal inspector, the manager of the local securities of a controlled corporation
EASA; or Airbus’s EASA DOA. Repeat Task flight standards district office/certificate without the recognition of income, gain,
274000–B0002–1–C, Inspection of the Ball- holding district office. The AMOC approval or loss. The temporary regulations
screw Assembly for Integrity of the Primary letter must specifically reference this AD. provide guidance in determining
and Secondary Load Paths, thereafter at the (2) Contacting the Manufacturer: As of the whether a corporation is a predecessor
applicable intervals specified in Airbus A340 effective date of this AD, for any requirement or successor of a distributing or
ALS Part 3—CMR, Revision 03, dated in this AD to obtain corrective actions from
October 19, 2015.
controlled corporation for purposes of
a manufacturer, the action must be the exception under section 355(e) of
(q) Parts Installation Prohibitions accomplished using a method approved by
the Manager, International Branch, ANM–
the Internal Revenue Code to the
(1) For all airplanes except Group 2 116, Transport Airplane Directorate, FAA; or nonrecognition treatment afforded
airplanes as identified in figure 1 to EASA; or Airbus’s EASA DOA. If approved qualifying distributions, and they
paragraphs (g), (h), and (p) of this AD: After by the DOA, the approval must include the provide certain limitations on the
modification of the airplane as required by DOA-authorized signature. recognition of gain in certain cases
paragraph (h), (i), or (j) of this AD, as involving a predecessor of a distributing
applicable, no person may install any THSA (t) Related Information
having P/N 47172–300, P/N 47147–500, P/N
corporation. The temporary regulations
(1) Refer to Continuing Airworthiness also provide rules regarding the extent
47175–200, or P/N 47175–300. Information (MCAI) EASA Airworthiness
(2) For Group 2 airplanes, as identified in to which section 355(f) causes a
Directive 2014–0219, dated September 29,
figure 1 to paragraphs (g), (h), and (p) of this 2014, for related information. This MCAI
distributing corporation (and in certain
AD: As of the effective date of this AD, no may be found in the AD docket on the cases its shareholders) to recognize
person may install on any Group 2 airplane Internet at http://www.regulations.gov by income or gain on the distribution of
any THSA having P/N 47172–300, P/N searching for and locating Docket No. FAA– stock or securities of a controlled
47147–500, P/N 47175–200, or P/N 47175– 2016–9393. corporation. Those temporary
300. (2) For service information identified in regulations affect corporations that
(r) Credit for Previous Actions this AD, contact Airbus SAS, Airworthiness distribute the stock or securities of
Office—EAL, 1 Rond Point Maurice Bellonte, controlled corporations and their
This paragraph provides credit for actions
31707 Blagnac Cedex, France; telephone +33 shareholders or security holders of those
required by paragraph (g)(2) of this AD, if
5 61 93 36 96; fax +33 5 61 93 45 80; email
those actions were performed before the distributing corporations. The text of
effective date of this AD using the applicable airworthiness.A330-A340@airbus.com;
Internet http://www.airbus.com. those temporary regulations serves as
service information specified in paragraphs the text of these proposed regulations.
(r)(1) through (r)(4) of this AD. (3) You may view this service information
at the FAA, Transport Airplane Directorate, DATES: Comments and requests for a
(1) Task 274400–00002–1–E, Lubrication of
the THSA ball-nut, of Airbus A330 ALS Part 1601 Lind Avenue SW., Renton, WA. For public hearing must be received by
4—Ageing Systems Maintenance, Revision information on the availability of this March 20, 2017.
03, dated September 9, 2011 (for Model A330 material at the FAA, call 425–227–1221. ADDRESSES: Send submissions to:
series airplanes). Issued in Renton, Washington, on CC:PA:LPD:PR (REG–140328–15), Room
(2) Task 274400–00002–1–E, Lubrication of November 10, 2016. 5203, Internal Revenue Service, P.O.
the THSA ball-nut, of Airbus A330 ALS Part Michael Kaszycki, Box 7604, Ben Franklin Station,
4—Ageing Systems Maintenance, Revision
04, dated August 27, 2013 (for Model A330 Acting Manager, Transport Airplane Washington, DC 20044. Submissions
series airplanes). Directorate, Aircraft Certification Service. may be hand-delivered Monday through
(3) Task 274400–00002–1–E, Lubrication of [FR Doc. 2016–29683 Filed 12–16–16; 8:45 am] Friday between the hours of 8 a.m. and
the THSA ball-nut, of Airbus A340 ALS Part BILLING CODE 4910–13–P 4 p.m. to CC:PA:LPD:PR (REG–140328–
4—Ageing Systems Maintenance, Revision 15), Courier’s Desk, Internal Revenue
02, dated October 12, 2011 (for Model A340– Service, 1111 Constitution Avenue NW.,
200 and –300 series airplanes). Washington, DC 20224, or sent
(4) Task 274400–00002–1–E, Lubrication of DEPARTMENT OF THE TREASURY
electronically, via the Federal
the THSA ball-nut, of Airbus A340 ALS Part
4—Ageing Systems Maintenance, Revision Internal Revenue Service eRulemaking Portal at http://
03, dated November 15, 2012 (for Model www.regulations.gov/ (REG–140328–
A340–200 and –300 series airplanes). 26 CFR Part 1 15).
(s) Other FAA AD Provisions [REG–140328–15] FOR FURTHER INFORMATION CONTACT:
The following provisions also apply to this
Concerning the proposed regulations,
RIN 1545–BN17 Richard K. Passales at (202) 317–5024 or
AD:
(1) Alternative Methods of Compliance Marie C. Milnes-Vasquez, (202) 317–
Guidance Regarding Predecessors and 7700; concerning submission of
(AMOCs): The Manager, International
Branch, ANM–116, Transport Airplane
Successors Under Section 355(e); comments, and/or requests for public
Directorate, FAA, has the authority to Limitation on Gain Recognition; hearing, Regina Johnson at (202) 317–
sradovich on DSK3GMQ082PROD with PROPOSALS
approve AMOCs for this AD, if requested Guidance Under Section 355(f) 6901 (not toll-free numbers).
using the procedures found in 14 CFR 39.19.
AGENCY: Internal Revenue Service (IRS), SUPPLEMENTARY INFORMATION:
In accordance with 14 CFR 39.19, send your
request to your principal inspector or local Treasury. Background and Explanation of
Flight Standards District Office, as ACTION: Withdrawal of notice of Provisions
appropriate. If sending information directly proposed rulemaking, notice of
to the International Branch, send it to ATTN: On November 22, 2004, the Treasury
proposed rulemaking by cross-reference
Vladimir Ulyanov, Aerospace Engineer, Department and the IRS published in
to temporary regulations.
International Branch, ANM–116, Transport the Federal Register (69 FR 67873) a
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Document Created: 2016-12-17 03:15:44
Document Modified: 2016-12-17 03:15:44
| Category | Regulatory Information | |
| Collection | Federal Register | |
| sudoc Class | AE 2.7: GS 4.107: AE 2.106: | |
| Publisher | Office of the Federal Register, National Archives and Records Administration | |
| Section | Proposed Rules | |
| Action | Notice of proposed rulemaking (NPRM). | |
| Dates | We must receive comments on this proposed AD by February 2, 2017. | |
| Contact | Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1138; fax 425-227-1149. | |
| FR Citation | 81 FR 91882 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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