Airworthiness Directives; Bombardier, Inc., Airplanes, 3522-3525 [2015-00958]

Download as PDF 3522 Federal Register / Vol. 80, No. 15 / Friday, January 23, 2015 / Proposed Rules paragraphs (c)(1), (c)(2), and (c)(3) of this AD, all manufacturer serial numbers on which Airbus modification (mod) 160500 or mod 160023 has been embodied in production, and those that have been modified in service through the Airbus Service Bulletin A320– 57–1173, A320–57–1186, and A320–57–1187 except those on which Airbus mod 156108 has been embodied in production. (1) Model A319–111, –112, –113, –114, –115, –131, –132, and –133 airplanes. (2) Model A320–211, –212, –214, –231, –232, and –233 airplanes. (3) Model A321–111, –112, –131, –211, –212, –213, –231, and –232 airplanes. (d) Subject Air Transport Association (ATA) of America Code 27, Flight Controls. (e) Reason This AD was prompted by reports that on airplanes equipped with sharklets, discretes (used to activate the load alleviation function) are connected on various flight computers using the same ground point. In these cases, the ground point segregation is no longer effective and a single failure could lead to loss of sharklet identification by flight computers causing a return to the wing tip fence (no sharklet configuration) performance. We are issuing this AD to prevent loss of sharklet identification by the flight computers and subsequent reduced control of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. emcdonald on DSK67QTVN1PROD with PROPOSALS (g) Modification Within 24 months after the effective date of this AD, modify the sharklet ground connection, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320–27–1240, dated June 18, 2014. (h) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM–116, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the International Branch, send it to ATTN: Sanjay Ralhan, Aerospace Engineer, International Branch, ANM 116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–1405; fax 425–227–1149. Information may be emailed to: 9-ANM-116AMOC-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: For any requirement in this AD to obtain corrective VerDate Sep<11>2014 19:56 Jan 22, 2015 Jkt 235001 actions from a manufacturer, the action must be accomplished using a method approved by the Manager, International Branch, ANM– 116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA); or Airbus’s EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature. (i) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) European Aviation Safety Agency Airworthiness Directive 2014–0186, dated August 19, 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–2014–1051. (2) For service information identified in this AD, contact Airbus, Airworthiness Office–EIAS, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email account.airworth-eas@airbus.com; Internet http://www.airbus.com. You may view this service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. Issued in Renton, Washington, on January 13, 2015. John P. Piccola, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015–00945 Filed 1–22–15; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2014–1049; Directorate Identifier 2013–NM–110–AD] RIN 2120–AA64 Airworthiness Directives; Bombardier, Inc., Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for certain Bombardier, Inc. Model CL–600–2B19 (Regional Jet Series 100 & 440) airplanes. This proposed AD was prompted by reports of the horizontal stabilizer trim actuator (HSTA) spur gear bolts inside the gearbox found loose, broken, or backed out due to incorrect bending of the anti-rotation tab washer and the improper application of glue during installation. This proposed AD would require replacing certain HSTAs with a new HSTA. This SUMMARY: PO 00000 Frm 00025 Fmt 4702 Sfmt 4702 proposed AD would also require revising the airplane flight manual (AFM) and the maintenance or inspection program, as applicable. We are proposing this AD to prevent failure of the HSTA and subsequent loss of control of the airplane. DATES: We must receive comments on this proposed AD by March 9, 2015. 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 proposed AD, contact Bombardier, ˆ Inc., 400 Cote-Vertu Road West, Dorval, ´ Quebec H4S 1Y9, Canada; telephone 514–855–5000; fax 514–855–7401; email thd.crj@aero.bombardier.com; Internet http://www.bombardier.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; 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 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: Luke Walker, Aerospace Engineer, Airframe and Propulsion Branch, ANE– 171, FAA, New York Aircraft Certification Office, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516–228–7363; fax 516–794–5531. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about E:\FR\FM\23JAP1.SGM 23JAP1 Federal Register / Vol. 80, No. 15 / Friday, January 23, 2015 / Proposed Rules this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2014–1049; Directorate Identifier 2013–NM–110–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 Transport Canada Civil Aviation (TCCA), which is the aviation authority for Canada, has issued Canadian Airworthiness Directive CF–2013–14, dated June 4, 2013 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for certain Bombardier, Inc. Model CL– 600–2B19 (Regional Jet Series 100 & 440) airplanes. The MCAI states: There have been a number of reports where the HSTA spur gear bolts inside the gearbox were found loose, broken or backed out. Investigation revealed that the root cause is incorrect bending of the anti-rotation tab washer and the improper application of Loctite glue during installation. The function of these bolts is to generate sufficient preload between the two spur gears such that the full torque is transferred by friction between the two spur gears. Loosening of the bolts would reduce the preload between two spur gears and decrease the torque transfer. Partial or full torque would be re-distributed to the secondary load path (Tie-Rod) in torsion. The Tie-Rod is designed to withstand axial load only in case of failure of the primary load path (ACME screw), and not torsional load. The secondary load path (Tie-Rod) is therefore considered ineffective and no longer provides protection as a failsafe design of the system. Loose bolt(s) on the HSTA spur gear combined with the failure of the primary load path, could lead to failure of the HSTA and subsequent loss of the aeroplane. In addition, Bombardier Aerospace (BA) has introduced a modified HSTA [part number] P/N 601R92305–5 (vendor P/N 8396–4) to rectify the loose bolt problem. However, this modified HSTA, has several quality control problems which could affect safety. This [Canadian] AD is issued to mandate the replacement of the affected HSTA(s) with the new HSTA P/N 601R92305–7 (vendor P/ N 8396–5). This proposed AD also would require revising the AFM and maintenance or inspection program, as applicable. 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–2014– 1049. Related Service Information Bombardier has issued the following service information. • Bombardier Service Bulletin 601R– 27–161, Revision A, dated January 30, 2014. This service information describes procedures for installing an HSTA. • Bombardier CL–600–2B19, Temporary Revision 2A–56, dated June 4, 2012, to Appendix A, Certification Maintenance Requirements (CMR), of Part 2, Airworthiness Requirements, of the Bombardier CL–600–2B19 Maintenance Requirements Manual (MRM). This service information adds 3523 new CMR tasks to the Airworthiness Requirements of the MRM. These CMR tasks include an inspection, functional check, and operational check. • Bombardier Model CL–600–2B19 Airplane Flight Manual, CSP A–012, Volume 3, Revision 61, dated April 2, 2013. This service information revises the Limitations section of the AFM to include a horizontal stabilizer trim check before the first flight of the day. In addition, this service information revises the Normal Procedures section of the AFM to include details for the horizontal stabilizer trim check portion of the procedure. The actions described in this service information are intended to correct the unsafe condition identified in the MCAI. 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. Costs of Compliance We estimate that this proposed AD affects 85 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: ESTIMATED COSTS Action Labor cost HSTA replacement ................. Revise airplane flight manual Revise maintenance or inspection program. 8 work-hours × $85 per hour = $680 ..................................... 1 work-hour × $85 per hour = $85 ......................................... 1 work-hour × $85 per hour = $85 ......................................... emcdonald on DSK67QTVN1PROD with PROPOSALS 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: VerDate Sep<11>2014 19:56 Jan 22, 2015 Jkt 235001 Parts cost 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. PO 00000 Frm 00026 Fmt 4702 Sfmt 4702 $38,569 0 0 Cost per product $39,249 85 85 Cost on U.S. operators $3,336,165 7,225 7,225 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. E:\FR\FM\23JAP1.SGM 23JAP1 3524 Federal Register / Vol. 80, No. 15 / Friday, January 23, 2015 / Proposed Rules 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. (f) Compliance Comply with this AD within the compliance times specified, unless already done. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. (h) Maintenance/Inspection Program Revision Within 30 days after the effective date of this AD, revise the maintenance or inspection program, as applicable, to incorporate Task C27–40–103–04, ‘‘Operational Check (ground maintenance test) of the horizontal stabilizer trim control unit,’’ specified in Bombardier CL–600–2B19 Temporary Revision 2A–56, dated June 4, 2012, to Appendix A, Certification Maintenance Requirements, of Part 2, Airworthiness Requirements, of the Bombardier CL–600–2B19 Maintenance Requirements Manual (MRM). The compliance time for the initial operational check is within 500 flight hours after the effective date of this AD. 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 adding the following new airworthiness directive (AD): ■ Bombardier, Inc.: Docket No. FAA–2014– 1049; Directorate Identifier 2013–NM– 110–AD. (a) Comments Due Date We must receive comments by March 9, 2015. (b) Affected ADs None. (c) Applicability This AD applies to Bombardier, Inc. Model CL–600–2B19 (Regional Jet Series 100 & 440) airplanes, certificated in any category, serial numbers 7003 and subsequent, equipped with horizontal stabilizer trim actuator (HSTA) part number (P/N) 601R92305–1 (vendor P/N 8396–2), 601R92305–3 (vendor P/N 8396–3), or 601R92305–5 (vendor P/N 8396–4). emcdonald on DSK67QTVN1PROD with PROPOSALS (d) Subject Air Transport Association (ATA) of America Code 27, Flight Controls. (e) Reason This AD was prompted by reports of the HSTA spur gear bolts inside the gearbox found loose, broken, or backed out due to incorrect bending of the anti-rotation tab washer and the improper application of Loctite glue during installation. We are issuing this AD to prevent failure of the HSTA and subsequent loss of control of the airplane. VerDate Sep<11>2014 19:56 Jan 22, 2015 Jkt 235001 (g) Airplane Flight Manual (AFM) Revision Within 30 days after the effective date of this AD, revise the Limitations section and Normal Procedures section of the AFM to include the information in Supplement 23, ‘‘Horizontal Stabilizer Trim Check,’’ of Chapter 7 ‘‘Supplements,’’ of Bombardier CL–600–2B19 Airplane Flight Manual CSP A–012, Volume 3, Revision 61, dated April 2, 2013. (i) No Alternative Actions or Intervals After accomplishing the revision required by paragraph (h) of this AD, no alternative actions (e.g., inspections) and/or intervals may be used unless the actions and/or intervals are approved as an alternative method of compliance (AMOC) in accordance with the procedures specified in paragraph (m) of this AD. (j) HSTA Replacement (1) For airplanes equipped with an HSTA having P/N 601R92305–1 (vendor P/N 8396– 2) or P/N 601R92305–3 (vendor P/N 8396–3): At the earlier of the times specified in paragraphs (j)(1)(i) and (j)(1)(ii) of this AD, replace the HSTA with a new HSTA having P/N 601R92305–7 (vendor P/N 8396–5), in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 601R–27–161, Revision A, dated January 30, 2014. The compliance times specified in paragraphs (j)(1)(i) and (j)(1)(ii) of this AD do not alleviate any existing life limit requirements. (i) Within 3,700 flight hours after the effective date of this AD. (ii) Within 27 months after the effective date of this AD. (2) For airplanes equipped with an HSTA having P/N 601R92305–5 (vendor P/N 8396– 4): At the earlier of the times specified in paragraphs (j)(2)(i), (j)(2)(ii), and (j)(2)(iii) of this AD, replace the HSTA with a new HSTA having P/N 601R92305–7 (vendor P/N 8396– 5), in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 601R–27–161, Revision A, dated January 30, 2014. The compliance times specified in paragraphs (j)(2)(i), (j)(2)(ii), and (j)(2)(iii) of this AD do not alleviate any existing life limit requirements. PO 00000 Frm 00027 Fmt 4702 Sfmt 4702 (i) Within 4,400 flight hours after the effective date of this AD. (ii) Within 32 months after the effective date of this AD. (iii) Before the accumulation of 10,000 total flight hours on HSTA P/N 60192305–5 (vendor P/N 8396–4). (k) Credit for Previous Actions This paragraph provides credit for the actions required by paragraph (j) of this AD, if those actions were performed before the effective date of this AD using Bombardier Service Bulletin 601R–27–161, dated May 31, 2012, which is not incorporated by reference in this AD. (l) Parts Installation Limitations (1) As of the effective date of this AD, no person may install an HSTA, P/N 601R92305–1 (vendor P/N 8396–2) or P/N 601R92305–3 (vendor P/N 8396–3) on any Model CL–600–2B19 airplane. (2) As of the effective date of this AD, no person may install an HSTA, P/N 601R92305–5 (vendor P/N 8396–4) having serial number (S/N) 287, 724, 813, 841, 998, 1031, 1035, 1049, 1053, 1067, 1068, 1136, 1252, 1268, 1303, 1319, 1338, 1354, 1374, 1378, 1445, 1470, 1498, 1513, 1546, 1632, 1736, 1766, 1846, 1849, 2002 through 2009 inclusive, 2011, 2013 through 2016 inclusive, 2019, 2020, or 2022, on any Model CL–600– 2B19 airplane. (3) As of the effective date of this AD: Replacement of an HSTA, P/N 601R92305–1 (vendor P/N 8396–2), P/N 601R92305–3 (vendor P/N 8396–3), or P/N 601R92305–5 (vendor P/N 8396–4), with an HSTA having P/N 601R92305–5 (vendor P/N 8396–4) that is not identified in paragraph (l)(2) of this AD, is acceptable, provided the actions required by paragraph (j)(2) of this AD are accomplished within the compliance time specified in that paragraph. (m) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, New York Aircraft Certification Office (ACO), ANE–170, 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 ACO, send it to ATTN: Program Manager, Continuing Operational Safety, FAA, New York ACO, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516–228–7300; fax 516–794–5531. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/ certificate holding district office. The AMOC approval letter must specifically reference this AD. (2) Contacting the Manufacturer: For any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, New York ACO, ANE–170, Engine and Propeller Directorate, FAA; or Transport Canada Civil Aviation (TCCA); or E:\FR\FM\23JAP1.SGM 23JAP1 Federal Register / Vol. 80, No. 15 / Friday, January 23, 2015 / Proposed Rules Bombardier, Inc.’s TCCA Design Approval Organization (DAO). If approved by the DAO, the approval must include the DAOauthorized signature. damage of the rudder, which could result in reduced structural integrity of the rudder and consequent reduced controllability of the airplane. (n) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) Canadian Airworthiness Directive CF–2013–14, dated June 4, 2013, 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– 2014–1049. (2) For service information identified in ˆ this AD, contact Bombardier, Inc., 400 Cote´ Vertu Road West, Dorval, Quebec H4S 1Y9, Canada; telephone 514–855–5000; fax 514– 855–7401; email thd.crj@ aero.bombardier.com; Internet http:// www.bombardier.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. DATES: Issued in Renton, Washington, on January 13, 2015. John P. Piccola, Jr., Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015–00958 Filed 1–22–15; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2014–1045; Directorate Identifier 2014–NM–031–AD] RIN 2120–AA64 Airworthiness Directives; Airbus Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). We propose to adopt a new airworthiness directive (AD) for all Airbus Model A310 and Airbus Model A300 B4–600, B4–600R, and F4–600R series airplanes, and Model A300 C4– 605R Variant F airplanes (collectively called Model A300–600 series airplanes) series airplanes. This proposed AD was prompted by a report of skin disbonding and damage found on the composite side panel of the rudder, located between the rudder core and skin of a previously repaired area. This proposed AD would require an inspection for disbonding or damage of certain rudders, and related investigative actions and corrective actions if necessary. We are proposing this AD to detect and correct disbonding and emcdonald on DSK67QTVN1PROD with PROPOSALS VerDate Sep<11>2014 19:56 Jan 22, 2015 Jkt 235001 You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, 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 proposed AD, contact Airbus SAS, Airworthiness Office—EAW, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email account.airworth-eas@airbus.com; 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. ADDRESSES: Examining the AD Docket AGENCY: SUMMARY: We must receive comments on this proposed AD by March 9, 2015. You may examine the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2014– 1045; 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. Dan Rodina, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–2125; fax 425- 227–1149. FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: PO 00000 Frm 00028 Fmt 4702 Sfmt 4702 3525 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–2014–1045; Directorate Identifier 2014–NM–031–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 The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2014–0026, dated January 28, 2014 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The MCAI states: A case of skin disbonding was reported on a composite side of a rudder installed on an A310 aeroplane. The investigation results revealed that this disbonding started from a skin panel area previously repaired in-service in accordance with the Structural Repair Manual (SRM). The initial damage has been identified as a disbonding between the core and the repaired area. This damage may not be visually detectable and likely propagates during normal operation due to the variation of pressure during ground-air-ground cycles. This condition, if not detected and corrected, could affect the structural integrity of the rudder, possibly resulting in reduced control of the aeroplane. For the reasons described above, this [EASA] AD requires a one-time thermography inspection of each repaired rudder or rudder whose maintenance records are incomplete and, depending on findings, accomplishment of applicable corrective and follow-up actions. Related investigative actions include doing a pulse thermography inspection for disbonding or damage of the leftand right-hand rudder side shells; a core ventilation through the inner skin, an elasticity laminate checker or ultrasonic inspection around the identified repairs in the booster area, and around identified fluid ingress; and a Tap test inspection of the glass fiber reinforced plastic area to identify skin-to-core disbonding and on identified repairs. E:\FR\FM\23JAP1.SGM 23JAP1

Agencies

[Federal Register Volume 80, Number 15 (Friday, January 23, 2015)]
[Proposed Rules]
[Pages 3522-3525]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2015-00958]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-1049; Directorate Identifier 2013-NM-110-AD]
RIN 2120-AA64


Airworthiness Directives; Bombardier, Inc., Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to adopt a new airworthiness directive (AD) for 
certain Bombardier, Inc. Model CL-600-2B19 (Regional Jet Series 100 & 
440) airplanes. This proposed AD was prompted by reports of the 
horizontal stabilizer trim actuator (HSTA) spur gear bolts inside the 
gearbox found loose, broken, or backed out due to incorrect bending of 
the anti-rotation tab washer and the improper application of glue 
during installation. This proposed AD would require replacing certain 
HSTAs with a new HSTA. This proposed AD would also require revising the 
airplane flight manual (AFM) and the maintenance or inspection program, 
as applicable. We are proposing this AD to prevent failure of the HSTA 
and subsequent loss of control of the airplane.

DATES: We must receive comments on this proposed AD by March 9, 2015.

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 proposed AD, contact 
Bombardier, Inc., 400 C[ocirc]te-Vertu Road West, Dorval, Qu[eacute]bec 
H4S 1Y9, Canada; telephone 514-855-5000; fax 514-855-7401; email 
thd.crj@aero.bombardier.com; Internet http://www.bombardier.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; 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 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: Luke Walker, Aerospace Engineer, 
Airframe and Propulsion Branch, ANE-171, FAA, New York Aircraft 
Certification Office, 1600 Stewart Avenue, Suite 410, Westbury, NY 
11590; telephone 516-228-7363; fax 516-794-5531.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about

[[Page 3523]]

this proposed AD. Send your comments to an address listed under the 
ADDRESSES section. Include ``Docket No. FAA-2014-1049; Directorate 
Identifier 2013-NM-110-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

    Transport Canada Civil Aviation (TCCA), which is the aviation 
authority for Canada, has issued Canadian Airworthiness Directive CF-
2013-14, dated June 4, 2013 (referred to after this as the Mandatory 
Continuing Airworthiness Information, or ``the MCAI''), to correct an 
unsafe condition for certain Bombardier, Inc. Model CL-600-2B19 
(Regional Jet Series 100 & 440) airplanes. The MCAI states:

    There have been a number of reports where the HSTA spur gear 
bolts inside the gearbox were found loose, broken or backed out. 
Investigation revealed that the root cause is incorrect bending of 
the anti-rotation tab washer and the improper application of Loctite 
glue during installation.
    The function of these bolts is to generate sufficient preload 
between the two spur gears such that the full torque is transferred 
by friction between the two spur gears. Loosening of the bolts would 
reduce the pre-load between two spur gears and decrease the torque 
transfer. Partial or full torque would be re-distributed to the 
secondary load path (Tie-Rod) in torsion. The Tie-Rod is designed to 
withstand axial load only in case of failure of the primary load 
path (ACME screw), and not torsional load. The secondary load path 
(Tie-Rod) is therefore considered ineffective and no longer provides 
protection as a failsafe design of the system. Loose bolt(s) on the 
HSTA spur gear combined with the failure of the primary load path, 
could lead to failure of the HSTA and subsequent loss of the 
aeroplane.
    In addition, Bombardier Aerospace (BA) has introduced a modified 
HSTA [part number] P/N 601R92305-5 (vendor P/N 8396-4) to rectify 
the loose bolt problem. However, this modified HSTA, has several 
quality control problems which could affect safety.
    This [Canadian] AD is issued to mandate the replacement of the 
affected HSTA(s) with the new HSTA P/N 601R92305-7 (vendor P/N 8396-
5).

This proposed AD also would require revising the AFM and maintenance or 
inspection program, as applicable. 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-2014-1049.

Related Service Information

    Bombardier has issued the following service information.
     Bombardier Service Bulletin 601R-27-161, Revision A, dated 
January 30, 2014. This service information describes procedures for 
installing an HSTA.
     Bombardier CL-600-2B19, Temporary Revision 2A-56, dated 
June 4, 2012, to Appendix A, Certification Maintenance Requirements 
(CMR), of Part 2, Airworthiness Requirements, of the Bombardier CL-600-
2B19 Maintenance Requirements Manual (MRM). This service information 
adds new CMR tasks to the Airworthiness Requirements of the MRM. These 
CMR tasks include an inspection, functional check, and operational 
check.
     Bombardier Model CL-600-2B19 Airplane Flight Manual, CSP 
A-012, Volume 3, Revision 61, dated April 2, 2013. This service 
information revises the Limitations section of the AFM to include a 
horizontal stabilizer trim check before the first flight of the day. In 
addition, this service information revises the Normal Procedures 
section of the AFM to include details for the horizontal stabilizer 
trim check portion of the procedure.
    The actions described in this service information are intended to 
correct the unsafe condition identified in the MCAI.

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.

Costs of Compliance

    We estimate that this proposed AD affects 85 airplanes of U.S. 
registry. We estimate the following costs to comply with this proposed 
AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                     Cost per      Cost on U.S.
               Action                         Labor cost            Parts cost        product        operators
----------------------------------------------------------------------------------------------------------------
HSTA replacement...................  8 work-hours x $85 per hour         $38,569         $39,249      $3,336,165
                                      = $680.
Revise airplane flight manual......  1 work-hour x $85 per hour                0              85           7,225
                                      = $85.
Revise maintenance or inspection     1 work-hour x $85 per hour                0              85           7,225
 program.                             = $85.
----------------------------------------------------------------------------------------------------------------

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.

[[Page 3524]]

    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 adding the following new airworthiness 
directive (AD):

Bombardier, Inc.: Docket No. FAA-2014-1049; Directorate Identifier 
2013-NM-110-AD.

(a) Comments Due Date

    We must receive comments by March 9, 2015.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Bombardier, Inc. Model CL-600-2B19 (Regional 
Jet Series 100 & 440) airplanes, certificated in any category, 
serial numbers 7003 and subsequent, equipped with horizontal 
stabilizer trim actuator (HSTA) part number (P/N) 601R92305-1 
(vendor P/N 8396-2), 601R92305-3 (vendor P/N 8396-3), or 601R92305-5 
(vendor P/N 8396-4).

(d) Subject

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

(e) Reason

    This AD was prompted by reports of the HSTA spur gear bolts 
inside the gearbox found loose, broken, or backed out due to 
incorrect bending of the anti-rotation tab washer and the improper 
application of Loctite glue during installation. We are issuing this 
AD to prevent failure of the HSTA and subsequent loss of control of 
the airplane.

(f) Compliance

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

(g) Airplane Flight Manual (AFM) Revision

    Within 30 days after the effective date of this AD, revise the 
Limitations section and Normal Procedures section of the AFM to 
include the information in Supplement 23, ``Horizontal Stabilizer 
Trim Check,'' of Chapter 7 ``Supplements,'' of Bombardier CL-600-
2B19 Airplane Flight Manual CSP A-012, Volume 3, Revision 61, dated 
April 2, 2013.

(h) Maintenance/Inspection Program Revision

    Within 30 days after the effective date of this AD, revise the 
maintenance or inspection program, as applicable, to incorporate 
Task C27-40-103-04, ``Operational Check (ground maintenance test) of 
the horizontal stabilizer trim control unit,'' specified in 
Bombardier CL-600-2B19 Temporary Revision 2A-56, dated June 4, 2012, 
to Appendix A, Certification Maintenance Requirements, of Part 2, 
Airworthiness Requirements, of the Bombardier CL-600-2B19 
Maintenance Requirements Manual (MRM). The compliance time for the 
initial operational check is within 500 flight hours after the 
effective date of this AD.

(i) No Alternative Actions or Intervals

    After accomplishing the revision required by paragraph (h) of 
this AD, no alternative actions (e.g., inspections) and/or intervals 
may be used unless the actions and/or intervals are approved as an 
alternative method of compliance (AMOC) in accordance with the 
procedures specified in paragraph (m) of this AD.

(j) HSTA Replacement

    (1) For airplanes equipped with an HSTA having P/N 601R92305-1 
(vendor P/N 8396-2) or P/N 601R92305-3 (vendor P/N 8396-3): At the 
earlier of the times specified in paragraphs (j)(1)(i) and 
(j)(1)(ii) of this AD, replace the HSTA with a new HSTA having P/N 
601R92305-7 (vendor P/N 8396-5), in accordance with the 
Accomplishment Instructions of Bombardier Service Bulletin 601R-27-
161, Revision A, dated January 30, 2014. The compliance times 
specified in paragraphs (j)(1)(i) and (j)(1)(ii) of this AD do not 
alleviate any existing life limit requirements.
    (i) Within 3,700 flight hours after the effective date of this 
AD.
    (ii) Within 27 months after the effective date of this AD.
    (2) For airplanes equipped with an HSTA having P/N 601R92305-5 
(vendor P/N 8396-4): At the earlier of the times specified in 
paragraphs (j)(2)(i), (j)(2)(ii), and (j)(2)(iii) of this AD, 
replace the HSTA with a new HSTA having P/N 601R92305-7 (vendor P/N 
8396-5), in accordance with the Accomplishment Instructions of 
Bombardier Service Bulletin 601R-27-161, Revision A, dated January 
30, 2014. The compliance times specified in paragraphs (j)(2)(i), 
(j)(2)(ii), and (j)(2)(iii) of this AD do not alleviate any existing 
life limit requirements.
    (i) Within 4,400 flight hours after the effective date of this 
AD.
    (ii) Within 32 months after the effective date of this AD.
    (iii) Before the accumulation of 10,000 total flight hours on 
HSTA P/N 60192305-5 (vendor P/N 8396-4).

(k) Credit for Previous Actions

    This paragraph provides credit for the actions required by 
paragraph (j) of this AD, if those actions were performed before the 
effective date of this AD using Bombardier Service Bulletin 601R-27-
161, dated May 31, 2012, which is not incorporated by reference in 
this AD.

(l) Parts Installation Limitations

    (1) As of the effective date of this AD, no person may install 
an HSTA, P/N 601R92305-1 (vendor P/N 8396-2) or P/N 601R92305-3 
(vendor P/N 8396-3) on any Model CL-600-2B19 airplane.
    (2) As of the effective date of this AD, no person may install 
an HSTA, P/N 601R92305-5 (vendor P/N 8396-4) having serial number 
(S/N) 287, 724, 813, 841, 998, 1031, 1035, 1049, 1053, 1067, 1068, 
1136, 1252, 1268, 1303, 1319, 1338, 1354, 1374, 1378, 1445, 1470, 
1498, 1513, 1546, 1632, 1736, 1766, 1846, 1849, 2002 through 2009 
inclusive, 2011, 2013 through 2016 inclusive, 2019, 2020, or 2022, 
on any Model CL-600-2B19 airplane.
    (3) As of the effective date of this AD: Replacement of an HSTA, 
P/N 601R92305-1 (vendor P/N 8396-2), P/N 601R92305-3 (vendor P/N 
8396-3), or P/N 601R92305-5 (vendor P/N 8396-4), with an HSTA having 
P/N 601R92305-5 (vendor P/N 8396-4) that is not identified in 
paragraph (l)(2) of this AD, is acceptable, provided the actions 
required by paragraph (j)(2) of this AD are accomplished within the 
compliance time specified in that paragraph.

(m) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, New 
York Aircraft Certification Office (ACO), ANE-170, 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 ACO, send it to ATTN: Program Manager, Continuing 
Operational Safety, FAA, New York ACO, 1600 Stewart Avenue, Suite 
410, Westbury, NY 11590; telephone 516-228-7300; fax 516-794-5531. 
Before using any approved AMOC, notify your appropriate principal 
inspector, or lacking a principal inspector, the manager of the 
local flight standards district office/certificate holding district 
office. The AMOC approval letter must specifically reference this 
AD.
    (2) Contacting the Manufacturer: For any requirement in this AD 
to obtain corrective actions from a manufacturer, the action must be 
accomplished using a method approved by the Manager, New York ACO, 
ANE-170, Engine and Propeller Directorate, FAA; or Transport Canada 
Civil Aviation (TCCA); or

[[Page 3525]]

Bombardier, Inc.'s TCCA Design Approval Organization (DAO). If 
approved by the DAO, the approval must include the DAO-authorized 
signature.

(n) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) Canadian Airworthiness Directive CF-2013-14, dated June 4, 
2013, 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-2014-1049.
    (2) For service information identified in this AD, contact 
Bombardier, Inc., 400 C[ocirc]te-Vertu Road West, Dorval, 
Qu[eacute]bec H4S 1Y9, Canada; telephone 514-855-5000; fax 514-855-
7401; email thd.crj@aero.bombardier.com; Internet http://www.bombardier.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.

    Issued in Renton, Washington, on January 13, 2015.
John P. Piccola, Jr.,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-00958 Filed 1-22-15; 8:45 am]
BILLING CODE 4910-13-P