Airworthiness Directives; Viking Air Limited (Type Certificate Previously Held by Bombardier, Inc.; Canadair Limited) Airplanes, 42024-42029 [2017-17838]

Download as PDF 42024 Federal Register / Vol. 82, No. 171 / Wednesday, September 6, 2017 / Rules and Regulations Issued in Renton, Washington, on July 28, 2017. John P. Piccola, Jr., Acting Director, System Oversight Division, Aircraft Certification Service. (m) Material Incorporated by Reference nlaroche on DSKBBV9HB2PROD with RULES AD 2016–04–01, effective April 4, 2016, 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–2014–0008. (2) For more information about this AD, contact Ana Martinez Hueto, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–1622; fax 425–227–1320. Federal Aviation Administration technical.publications@vikingair.com; Internet http://www.vikingair.com. You may view this referenced service information at the FAA, Transport Standards Branch, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. It is also available on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2017– 0474. 14 CFR Part 39 Examining the AD Docket [Docket No. FAA–2017–0474; Product Identifier 2016–NM–096–AD; Amendment 39–19007; AD 2017–17–17] You may examine the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2017– 0474; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The address for the Docket Office (telephone 800–647–5527) is Docket Management Facility, U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Cesar A. Gomez, Aerospace Engineer, Airframe and Mechanical Systems Section, FAA, New York ACO Branch, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516– 228–7318; fax 516–794–5531. SUPPLEMENTARY INFORMATION: (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless this AD specifies otherwise. (3) The following service information was approved for IBR on October 11, 2017. (i) Appendix A, Airworthiness Limitations (AL), of the EMBRAER ERJ 190/195 Maintenance Review Board Report, MRB– 1928, Revision 9, dated August 14, 2015. (ii) Appendix A, Airworthiness Limitations (AL), of the EMBRAER Lineage 1000/1000E Maintenance Planning Guide, MPG–2928, Revision 4, dated July 14, 2014. (iii) EMBRAER MPG—Temporary Revision 4–2, dated February 13, 2015. (iv) EMBRAER MPG—Temporary Revision 4–3, dated October 30, 2015. (v) EMBRAER MRB—Temporary Revision 9–1, dated October 27, 2015. (vi) EMBRAER MRB—Temporary Revision 9–3, dated October 27, 2015. (4) The following service information was approved for IBR on January 14, 2013 (77 FR 73270, December 10, 2012). (i) EMBRAER Temporary Revision (TR) 5– 1, dated February 11, 2011, to Part 2— Airworthiness Limitation Inspections (ALI)— Structures, of Appendix A, Airworthiness Limitations (AL), of the EMBRAER 190 Maintenance Review Board Report, MRB– 1928, Revision 5, dated November 11, 2010. (ii) Appendix A, Airworthiness Limitation (AL), of the EMBRAER 190 Maintenance Review Board Report, MRB–1928, Revision 5, dated November 11, 2010. (5) For service information identified in this AD, contact Embraer S.A., Technical Publications Section (PC 060), Av. Brigadeiro ˜ Faria Lima, 2170—Putim—12227–901 Sao Jose dos Campos—SP—BRASIL; telephone +55 12 3927–5852 or +55 12 3309–0732; fax +55 12 3927–7546; email distrib@ embraer.com.br; Internet http:// www.flyembraer.com. (6) You may view this service information at the FAA, Transport Standards Branch, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. (7) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: http:// www.archives.gov/federal-register/cfr/ibrlocations.html. VerDate Sep<11>2014 15:36 Sep 05, 2017 Jkt 241001 [FR Doc. 2017–16667 Filed 9–5–17; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION RIN 2120–AA64 Airworthiness Directives; Viking Air Limited (Type Certificate Previously Held by Bombardier, Inc.; Canadair Limited) Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: We are superseding Airworthiness Directive (AD) 2011–03– 08, which applied to certain Bombardier, Inc., Model CL–215–1A10 (CL–215), CL–215–6B11 (CL–215T Variant), and CL–215–6B11 (CL–415 Variant) airplanes. AD 2011–03–08 required an inspection to determine the number of flight cycles accumulated by certain accumulators installed on the airplane, and repetitive inspections of the accumulators for cracks, and replacement if necessary. This AD retains those inspections and the accumulator replacement if necessary, and adds a new terminating action to address the identified unsafe condition. This AD was prompted by the development of a terminating action for the repetitive inspections. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective October 11, 2017. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of October 11, 2017. The Director of the Federal Register approved the incorporation by reference of certain other publications listed in this AD as of March 14, 2011 (76 FR 6536, February 7, 2011). ADDRESSES: For service information identified in this final rule, contact Viking Air Limited, 1959 de Havilland Way, Sidney, British Columbia V8L 5V5, Canada; telephone +1–250–656– 7227; fax +1–250–656–0673; email acsSUMMARY: PO 00000 Frm 00004 Fmt 4700 Sfmt 4700 Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 2011–03–08, Amendment 39–16592 (76 FR 6536, February 7, 2011) (‘‘AD 2011–03–08’’). AD 2011–03–08 applied to certain Bombardier, Inc., Model CL–215–1A10 (CL–215), CL–215–6B11 (CL–215T Variant), and CL–215–6B11 (CL–415 Variant) airplanes. The NPRM published in the Federal Register on May 18, 2017 (82 FR 22766). The NPRM was prompted by the development of a terminating action (relocation of the affected accumulators, and incorporation of new airworthiness limitations), which addresses the unsafe condition. The NPRM proposed to continue to require an inspection to determine the number of flight cycles accumulated by applicable accumulators (i.e., brake, aileron, elevator, and rudder accumulators) installed on the airplane, repetitive ultrasonic inspections of the accumulators for cracks, and E:\FR\FM\06SER1.SGM 06SER1 Federal Register / Vol. 82, No. 171 / Wednesday, September 6, 2017 / Rules and Regulations replacement of any accumulator in which a crack is detected. The NPRM also proposed to require a new terminating action for the repetitive inspections. We are issuing this AD to prevent failure of the screw cap or end cap of certain accumulators, which could result in impact damage to various components, potentially resulting in fuel spillage, uncommanded flap movement, or loss of aileron control. Transport Canada Civil Aviation (TCCA), which is the aviation authority for Canada, has issued Canadian Airworthiness Directive CF–2009–42R2, dated May 30, 2016 (referred to after this as the Mandatory Continuing Airworthiness Information, or ’’the MCAI’’), to correct an unsafe condition for certain Viking Air Limited Model CL–215–1A10 (CL–215), CL–215–6B11 (CL–215T Variant), and CL–215–6B11 (CL–415 Variant) airplanes. The MCAI states: Seven cases of on-ground hydraulic accumulator screw cap or end cap failure have been experienced on CL–600–2B19 (CRJ) aeroplane, resulting in loss of the associated hydraulic system and high-energy impact damage to adjacent systems and structure. To date, the lowest number of flight cycles accumulated at the time of failure has been 6991. Although there have been no failures to date on any CL–215–1A10 (CL–215) or CL– 215–6B11 (CL–215T and CL–415) aeroplane, similar accumulators, Part Number (P/N) 08– 8423–010 (MS28700–3), to those installed on the CL–600–2B19, are installed on the aeroplane models listed in the Applicability section of this [Canadian] AD. A detailed analysis of the systems and structure in the potential line of trajectory of a failed screw cap/end cap for each accumulator has been conducted. It has identified that the worst-case scenarios would be impact damage to various components, potentially resulting in fuel spillage, uncommanded flap movement, or loss of aileron control. This [Canadian] AD mandates repetitive [ultrasonic] inspections of the accumulators for cracks and replacement of any accumulator in which a crack is detected. Revision 1 of this [Canadian] AD clarified the text of the [Canadian] AD, including the P/N of the affected accumulators. This revision provides the terminating action [relocation of affected accumulators and incorporation of new airworthiness limitations] to this [Canadian] AD. It also modifies the applicability range for the CL– 215–1A10 (CL–215); the CL–215 is out of production and the last aeroplane produced was serial number 1125. 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–2017– 0474. Comments We gave the public the opportunity to participate in developing this AD. We received no comments on the NPRM or on the determination of the cost to the public. Explanation of Changes Made to This Final Rule We have revised this final rule to identify the legal name of the manufacturer as published in the most recent type certificate data sheet for the affected airplane models. In the proposed AD, we inadvertently listed the wrong publication dates for service information in two places. Table 4 to paragraph (o) of the proposed AD referred to Bombardier Service Bulletin 215–4470, Revision 1, dated December 13, 2013. We have corrected the publication date for this document to June 27, 2014, in this AD. Additionally, paragraph (r)(1)(iii) of the proposed AD referred to Bombardier Service Bulletin 215–3158, dated March 28, 2012. We have corrected the publication date for this document to March 21, 2012, in this AD. 42025 • Bombardier Service Bulletin 215– 552, Revision 2, dated June 18, 2015. This service information describes procedures to relocate the aileron hydraulic accumulator aft of its current location. • Bombardier Service Bulletin 215– 3158, Revision 2, dated April 15, 2014; and Bombardier Service Bulletin 215– 4423, Revision 5, dated March 17, 2016. This service information describes procedures to relocate the aileron, elevator, and rudder hydraulic accumulators aft and outboard of their current locations. These documents are distinct since they apply to different airplane models. • Bombardier Service Bulletin 215– 557, Revision 1, dated June 27, 2014; Bombardier Service Bulletin 215–3182, Revision 1, dated June 27, 2014; and Bombardier Service Bulletin 215–4470, Revision 1, dated June 27, 2014. This service information describes procedures to establish the number of flight hours for each accumulator and determine if it has been used on another type of aircraft. These documents are distinct since they apply to different airplane models. • Bombardier Temporary Revision 5– 56, dated December 13, 2013; Bombardier Temporary Revision 295/7, dated December 13, 2013; Bombardier Temporary Revision LLC–1, dated December 13, 2013; and Bombardier Temporary Revision LLC–3, dated December 13, 2013. This service information provides a 10,000-hour accumulator life limitation for certain accumulators. These documents are distinct since they apply to different airplane models. 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. Conclusion We reviewed the available data and determined that air safety and the public interest require adopting this AD with the changes described previously and minor editorial changes. We have determined that these changes: • Are consistent with the intent that was proposed in the NPRM for correcting the unsafe condition; and • Do not add any additional burden upon the public than was already proposed in the NPRM. Costs of Compliance Related Service Information Under 1 CFR Part 51 Bombardier, Inc., has issued the following service information: We estimate that this AD affects 7 airplanes of U.S. registry. We estimate the following costs to comply with this AD: nlaroche on DSKBBV9HB2PROD with RULES ESTIMATED COSTS Cost per product Labor cost Ultrasonic inspection (retained action from AD 2011–03–08). Relocation, determination of accumulator hours and usage, and maintenance or inspection program revision (new action). 7 work-hours × $85 per hour = $595 ............. $0 $595 $4,165 56 work-hours × $85 per hour = $4,760 ........ 0 4,760 33,320 VerDate Sep<11>2014 15:36 Sep 05, 2017 Jkt 241001 PO 00000 Frm 00005 Fmt 4700 Sfmt 4700 Parts cost Cost on U.S. operators Action E:\FR\FM\06SER1.SGM 06SER1 42026 Federal Register / Vol. 82, No. 171 / Wednesday, September 6, 2017 / Rules and Regulations We estimate the following costs to do any necessary replacement that would be required based on the results of the inspection. We have no way of determining the number of aircraft that might need this replacement. ON-CONDITION COSTS Action Labor cost Replacement of cracked part (retained action from AD 2011–03–08). 6 work-hours × $85 per hour = $510 ........................... According to the manufacturer, some of the costs of this AD may be covered under warranty, thereby reducing the cost impact on affected individuals. We do not control warranty coverage for affected individuals. As a result, we have included all costs in our cost estimate. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. ‘‘Subtitle VII: Aviation Programs,’’ describes in more detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in ‘‘Subtitle VII, Part A, Subpart III, Section 44701: General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. This AD is issued in accordance with authority delegated by the Executive Director, Aircraft Certification Service, as authorized by FAA Order 8000.51C. In accordance with that order, issuance of ADs is normally a function of the Compliance and Airworthiness Division, but during this transition period, the Executive Director has delegated the authority to issue ADs applicable to transport category airplanes to the Director of the System Oversight Division. nlaroche on DSKBBV9HB2PROD with RULES Regulatory Findings We determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. VerDate Sep<11>2014 15:36 Sep 05, 2017 Jkt 241001 For the reasons discussed above, I certify that this AD: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; 2. Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 3. Will not affect intrastate aviation in Alaska; and 4. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by removing Airworthiness Directive (AD) 2011–03–08, Amendment 39–16592 (76 FR 6536, February 7, 2011), and adding the following new AD: ■ 2017–17–17 Viking Air Limited (Type Certificate Previously Held by Bombardier, Inc.; Canadair Limited): Amendment 39–19007; Docket No. FAA–2017–0474; Product Identifier 2016–NM–096–AD. (a) Effective Date This AD is effective October 11, 2017. (b) Affected ADs This AD replaces AD 2011–03–08, Amendment 39–16592 (76 FR 6536, February 7, 2011) (‘‘AD 2011–03–08’’). (c) Applicability This AD applies to Viking Air Limited (Type Certificate previously held by Bombardier, Inc.; Canadair Limited) airplanes, certificated in any category, as PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 Parts cost Cost per product $4,055 $4,565 identified in paragraphs (c)(1) through (c)(3) of this AD. (1) Model CL–215–1A10 (CL–215) airplanes, serial numbers 1001 through 1125 inclusive. (2) Model CL–215–6B11 (CL–215T Variant) airplanes, serial numbers 1056 through 1125 inclusive. (3) Model CL–215–6B11 (CL–415 Variant) airplanes, serial numbers 2001 through 2990 inclusive. (d) Subject Air Transport Association (ATA) of America Code 29, Hydraulic power. (e) Reason This AD was prompted by reports of onground hydraulic accumulator screw cap or end cap failure resulting in a loss of the associated hydraulic system and high-energy impact damage to adjacent systems and structure. We are issuing this AD to prevent failure of the screw cap or end cap, which could result in impact damage to various components, potentially resulting in fuel spillage, uncommanded flap movement, or loss of aileron control. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Retained Inspection To Determine Flight Cycles, With No Changes This paragraph restates the requirements of paragraph (g) of AD 2011–03–08, with no changes. Within 50 flight hours after March 14, 2011 (the effective date of AD 2011–03– 08), inspect to determine the number of flight cycles accumulated by each of the applicable accumulators (i.e., brake, aileron, elevator, and rudder accumulators) having part number 08–8423–010 (MS28700–3) installed on the airplane. A review of airplane maintenance records is acceptable in lieu of this inspection if the number of flight cycles accumulated can be conclusively determined from that review. (h) Retained Initial Ultrasonic Inspection for Model CL–215–1A10 (CL–215) and CL–215– 6B11 (CL–215T Variant) Airplanes, With No Changes This paragraph restates the requirements of paragraph (h) of AD 2011–03–08, with no changes. For Model CL–215–1A10 (CL–215) and CL–215–6B11 (CL–215T Variant) airplanes: Do an ultrasonic inspection for cracking of the accumulator at the applicable time specified in paragraph (h)(1) or (h)(2) of this AD, in accordance with Part B of the Accomplishment Instructions of the E:\FR\FM\06SER1.SGM 06SER1 Federal Register / Vol. 82, No. 171 / Wednesday, September 6, 2017 / Rules and Regulations applicable service bulletin listed in table 1 to paragraphs (h), (i), and (k) of this AD. TABLE 1 TO PARAGRAPHS (h), (i), AND (k) OF THIS AD—SERVICE BULLETINS For model— Use bombardier service bulletin— CL–215–1A10 (CL–215) 215–541, Revision 1, dated March 12, 2010. 215–3155, Revision 1, dated March 12, 2010. 215–4414, Revision 1, dated March 12, 2010. CL–215–6B11 (CL–215T Variant). CL–215–6B11 (CL–415 Variant). (1) For any accumulator on which the inspection required by paragraph (g) of this AD shows an accumulation of more than 875 total flight cycles, or on which it is not possible to determine the number of total accumulated flight cycles, do the inspection within 125 flight cycles after March 14, 2011 (the effective date of AD 2011–03–08). (2) For any accumulator on which the inspection required by paragraph (g) of this AD shows an accumulation of 875 total flight cycles or fewer, do the inspection before the accumulation of 1,000 flight cycles on the accumulator. (i) Retained Initial Ultrasonic Inspection for Model CL–215–6B11 (CL–415 Variant) Airplanes, With No Changes This paragraph restates the requirements of paragraph (i) of AD 2011–03–08, with no changes. For Model CL–215–6B11 (CL–415 Variant) airplanes, do an ultrasonic inspection for cracking of the accumulator at the applicable time specified in paragraph (i)(1) or (i)(2) of this AD, in accordance with Part B of the Accomplishment Instructions of the applicable service bulletin listed in table 1 to paragraphs (h), (i), and (k) of this AD. (1) For any accumulator on which the inspection required by paragraph (g) of this AD shows an accumulation of more than 750 flight cycles, or on which it is not possible to determine the number of total accumulated flight cycles, do the inspection within 250 flight cycles after March 14, 2011 (the effective date of AD 2011–03–08). (2) For any accumulator on which the inspection required by paragraph (g) of this AD shows an accumulation of 750 total flight cycles or fewer, do the inspection before the accumulation of 1,000 flight cycles on the accumulator. (j) Retained Repetitive Inspections, With New Terminating Action This paragraph restates the requirements of paragraph (j) of AD 2011–03–08, with new terminating action. If no cracking is found during any inspection required by paragraph (h) or (i) of this AD, repeat the inspection thereafter at intervals not to exceed 750 flight cycles until the actions required by paragraphs (n), (o), and (p) of this AD have been done. (k) Retained Replacement of Cracked Accumulators and Repetitive Inspections, With New Terminating Action This paragraph restates the requirements of paragraph (k) of AD 2011–03–08, with new terminating action. If any cracking is found during any inspection required by paragraph (h) or (i) of this AD, before further flight, replace the accumulator with a serviceable accumulator, in accordance with Part B of the Accomplishment Instructions of the applicable service bulletin listed in table 1 to paragraphs (h), (i), and (k) of this AD. Doing the replacement does not end the inspection requirements of paragraphs (h) and (i) of this AD. Repeat the inspections required by paragraph (h) or (i) of this AD, as applicable, at intervals not to exceed 750 flight cycles until the actions required by paragraphs (n), (o), and (p) of this AD have been done. (l) Retained Parts Installation Limitation, With No Changes This paragraph restates the parts installation limitation in paragraph (l) of AD 42027 2011–03–08, with no changes. As of March 14, 2011 (the effective date of AD 2011–03– 08), no person may install an accumulator, part number 08–8423–010 (MS28700–3), on any airplane unless the accumulator has been inspected in accordance with the requirements of paragraph (h) or (i) of this AD. (m) Retained Credit for Previous Actions, With No Changes This paragraph restates the credit provided in paragraph (m) of AD 2011–03–08, with no changes. Inspections accomplished before March 14, 2011 (the effective date of AD 2011–03–08), in accordance with the applicable service bulletin listed in table 2 to paragraph (m) of this AD are considered acceptable for compliance with the corresponding action specified in paragraph (h), (i), (j), or (k) of this AD. TABLE 2 TO PARAGRAPH (m) OF THIS AD—CREDIT SERVICE BULLETINS For model— Use Bombardier Service Bulletin— CL–215–1A10 (CL–215) 215–541, dated July 9, 2009. 215–3155, dated July 9, 2009. 215–4414, dated July 9, 2009. CL–215–6B11 (CL–215T Variant). CL–600–6B11 (CL–415 Variant). (n) New Relocation of Affected Accumulators Within 12 months after the effective date of this AD, relocate affected hydraulic accumulators, in accordance with the Accomplishment Instructions of the applicable Bombardier service bulletin specified in table 3 to paragraph (n) of this AD. TABLE 3 TO PARAGRAPH (n) OF THIS AD—SERVICE INFORMATION FOR RELOCATING ACCUMULATORS For model— Affected accumulators— Use Service Bulletin— CL–215–1A10 (CL–215) ................. Aileron, if installed ......................... CL–215–6B11 (CL–215T Variant) .. Aileron, rudder, and elevator ......... CL–215–6B11 (CL–415 Variant) ..... Aileron, rudder, and elevator ......... Bombardier Service Bulletin 215–552, Revision 2, dated June 18, 2015. Bombardier Service Bulletin 215–3158, Revision 2, dated April 15, 2014. Bombardier Service Bulletin 215–4423, Revision 5, dated March 17, 2016. nlaroche on DSKBBV9HB2PROD with RULES (o) New Establishment of Flight Hours on the Accumulator, Determination of Previous Use of the Accumulator, and Replacement if Necessary Within 12 months after the effective date of this AD, establish the number of flight hours for each accumulator, and determine whether any accumulator has been used in service on another type of airplane other than Model CL–215–1A10 (CL–215), CL–215– 6B11 (CL–215T Variant), or CL–215–6B11 (CL–415 Variant), in accordance with the Accomplishment Instructions in the applicable Bombardier service bulletin specified in table 4 to paragraph (o) of this AD. If any accumulator is found that has been in service on another type of airplane other than Model CL–215–1A10 (CL–215), CL–215–6B11 (CL–215T Variant), or CL–215– 6B11 (CL–415 Variant), replace the accumulator within 50 flight hours after determining an affected accumulator is installed. TABLE 4 TO PARAGRAPH (o) OF THIS AD—ESTABLISHMENT OF NUMBER OF FLIGHT HOURS ON THE ACCUMULATOR For model— Use Service Bulletin— CL–215–1A10 (CL–215) ..................................... Bombardier Service Bulletin 215–557, Revision 1, dated June 27, 2014 (applicable to MS28700–3 accumulator). VerDate Sep<11>2014 15:36 Sep 05, 2017 Jkt 241001 PO 00000 Frm 00007 Fmt 4700 Sfmt 4700 E:\FR\FM\06SER1.SGM 06SER1 42028 Federal Register / Vol. 82, No. 171 / Wednesday, September 6, 2017 / Rules and Regulations TABLE 4 TO PARAGRAPH (o) OF THIS AD—ESTABLISHMENT OF NUMBER OF FLIGHT HOURS ON THE ACCUMULATOR— Continued For model— Use Service Bulletin— CL–215–6B11 (CL–215T Variant) ...................... CL–215–6B11 (CL–415 Variant) ........................ Bombardier Service Bulletin 215–3182, Revision 1, dated June 27, 2014. Bombardier Service Bulletin 215–4470, Revision 1, dated June 27, 2014. (p) New Airworthiness Limitations Within 30 days after the effective date of this AD, revise the maintenance or inspection program, as applicable, to incorporate the 10,000-hour accumulator life limitation replacement of the accumulator is within the limitation specified in the applicable TR specified in table 5 to paragraph (p) of this AD, or within 30 days after the effective date of this AD, whichever occurs later. specified in the applicable Time Limits/ Maintenance Checks (TLMC) Manual temporary revisions (TRs) listed in table 5 to paragraph (p) of this AD. The initial compliance time for accomplishing the TABLE 5 TO PARAGRAPH (p) OF THIS AD—AIRWORTHINESS LIMITATIONS Comply with Bombardier TLMC manual— For model— CL–215–1A10 CL–215–6B11 CL–215–6B11 CL–215–6B11 (CL–215) ................................................................. (CL–215T Variant) .................................................. (CL–215T Variant) .................................................. (CL–415 Variant) .................................................... Bombardier TR No.— Dated— PSP PSP PSP PSP 295/7 .............................. LLC–3 ............................ LLC–1 ............................ 5–56 ............................... December December December December 295 ......................... 395 ......................... 395–1 ..................... 495 ......................... (q) No Alternative Actions and Intervals (s) Other FAA AD Provisions After accomplishment of the revision required by paragraph (p) of this AD, no alternative actions (e.g., inspections) or intervals may be used unless the actions and intervals are approved as an alternative method of compliance (AMOC) in accordance with the procedures specified in paragraph (s)(1) of this AD. The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, New York ACO Branch, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the certification office, send it to ATTN: Program Manager, Continuing Operational Safety, FAA, New York ACO Branch, 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. (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 Branch, FAA; or Transport Canada Civil Aviation (TCCA); or Viking Air Limited’s TCCA Design Approval Organization (DAO). If approved by the DAO, the approval must include the DAO-authorized signature. nlaroche on DSKBBV9HB2PROD with RULES (r) Credit for Previous Actions (1) This paragraph provides credit for actions required by paragraph (n) of this AD, if those actions were performed before the effective date of this AD using any applicable service information specified in paragraphs (r)(1)(i) through (r)(1)(ix) of this AD. (i) Bombardier Service Bulletin 215–552, dated December 16, 2013. (ii) Bombardier Service Bulletin 215–552, Revision 1, dated September 12, 2014. (iii) Bombardier Service Bulletin 215–3158, dated March 21, 2012. (iv) Bombardier Service Bulletin 215–3158, Revision 1, dated December 16, 2013. (v) Bombardier Service Bulletin 215–4423, Revision NC, dated April 4, 2011. (vi) Bombardier Service Bulletin 215–4423, Revision 1, dated September 28, 2011. (vii) Bombardier Service Bulletin 215– 4423, Revision 2, dated May 30, 2012. (viii) Bombardier Service Bulletin 215– 4423, Revision 3, dated December 16, 2013. (ix) Bombardier Service Bulletin 215–4423, Revision 4, dated December 3, 2015. (2) This paragraph provides credit for actions required by paragraph (o) of this AD, if those actions were performed before the effective date of this AD using any applicable service information specified in paragraphs (r)(2)(i) through (r)(2)(iii) of this AD. (i) Bombardier Service Bulletin 215–557, Revision NC, dated December 13, 2013. (ii) Bombardier Service Bulletin 215–3182, Revision NC, dated December 13, 2013. (iii) Bombardier Service Bulletin 215–4470, Revision NC, dated December 13, 2013. VerDate Sep<11>2014 15:36 Sep 05, 2017 Jkt 241001 (t) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) Canadian Airworthiness Directive CF–2009–42R2, dated May 30, 2016, 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–2017–0474. (2) For more information about this AD, contact Cesar A. Gomez, Aerospace Engineer, Airframe and Mechanical Systems Section, FAA, New York ACO Branch, 1600 Stewart PO 00000 Frm 00008 Fmt 4700 Sfmt 4700 13, 13, 13, 13, 2013. 2013. 2013. 2013. Avenue, Suite 410, Westbury, NY 11590; telephone 516–228–7318; fax 516–794–5531. (3) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (u)(5) and (u)(6) of this AD. (u) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless this AD specifies otherwise. (3) The following service information was approved for IBR on October 11, 2017. (i) Bombardier Service Bulletin 215–552, Revision 2, dated June 18, 2015. (ii) Bombardier Service Bulletin 215–557, Revision 1, dated June 27, 2014. (iii) Bombardier Service Bulletin 215–3158, Revision 2, dated April 15, 2014. (iv) Bombardier Service Bulletin 215–3182, Revision 1, dated June 27, 2014. (v) Bombardier Service Bulletin 215–4423, Revision 5, dated March 17, 2016. (vi) Bombardier Service Bulletin 215–4470, Revision 1, dated June 27, 2014. (vii) Bombardier Temporary Revision 5–56, dated December 13, 2013. (viii) Bombardier Temporary Revision 295/ 7, dated December 13, 2013. (ix) Bombardier Temporary Revision LLC– 1, dated December 13, 2013. (x) Bombardier Temporary Revision LLC– 3, dated December 13, 2013. (4) The following service information was approved for IBR on March 14, 2011 (76 FR 6536, February 7, 2011). (i) Bombardier Service Bulletin 215–541, Revision 1, dated March 12, 2010. (ii) Bombardier Service Bulletin 215–3155, Revision 1, dated March 12, 2010. (iii) Bombardier Service Bulletin 215–4414, Revision 1, dated March 12, 2010. (5) For service information identified in this AD, contact Viking Air Limited, 1959 de E:\FR\FM\06SER1.SGM 06SER1 Federal Register / Vol. 82, No. 171 / Wednesday, September 6, 2017 / Rules and Regulations Havilland Way, Sidney, British Columbia V8L 5V5, Canada; telephone +1–250–656– 7227; fax +1–250–656–0673; email acstechnical.publications@vikingair.com; Internet http://www.vikingair.com. (6) You may view this service information at the FAA, Transport Standards Branch, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. (7) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: http:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued in Renton, Washington, on August 16, 2017. Jeffrey E. Duven, Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2017–17838 Filed 9–5–17; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2017–0638; Product Identifier 2017–CE–018–AD; Amendment 39–19019; AD 2017–18–10] RIN 2120–AA64 Airworthiness Directives; Diamond Aircraft Industries GmbH Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for certain Diamond Aircraft Industries GmbH Models DA 42, DA 42 M–NG, and DA 42 NG airplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as crack formation on the flap bell crank, which could cause the flap bell crank to fail. We are issuing this AD to require actions to address the unsafe condition on these products. DATES: This AD is effective October 11, 2017. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of October 11, 2017. ADDRESSES: You may examine the AD docket on the Internet at http:// www.regulations.gov by searching for nlaroche on DSKBBV9HB2PROD with RULES SUMMARY: VerDate Sep<11>2014 15:36 Sep 05, 2017 Jkt 241001 and locating Docket No. FAA–2017– 0638; or in person at Document Management Facility, U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. For service information identified in this AD, contact Diamond Aircraft Industries GmbH, N.A. Otto-Stra+e 5, A–2700 Wiener Neustadt, Austria, telephone: +43 2622 26700; fax: +43 2622 26780; email: office@diamondair.at; Internet: http:// www.diamondaircraft.com. You may view this referenced service information at the FAA, Policy and Innovation Division, 901 Locust, Kansas City, Missouri 64106. For information on the availability of this material at the FAA, call (816) 329–4148. It is also available on the Internet at http:// www.regulations.gov by searching for Docket No. FAA–2017–0638. FOR FURTHER INFORMATION CONTACT: Mike Kiesov, Aerospace Engineer, FAA, Small Airplane Standards Branch, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329– 4144; fax: (816) 329–4090; email: mike.kiesov@faa.gov. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to certain Diamond Aircraft Industries GmbH Models DA 42, DA 42 M–NG, and DA 42 NG airplanes. The NPRM was published in the Federal Register on June 23, 2017 (82 FR 28594). The NPRM proposed to correct an unsafe condition for the specified products and was based on mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country. The MCAI states: Cracks and deformation have been found on the flap bell crank Part Number (P/N) D60–2757–11–00. Frequent high load conditions have been identified as the root cause. This condition, if not detected and corrected, could lead to failure of the flap bell crank and consequent reduced control of the aeroplane. To address this potential unsafe condition, Diamond Aircraft Industries (DAI) issued Mandatory Service Bulletin (MSB) 42–126/ MSB 42NG–066 and the corresponding Work Instruction (WI) MSB 42–126/WI–MSB 42NG–066 (single document), hereafter referred to as ‘the applicable MSB’ in this [EASA] AD, providing inspection and modification instructions. For the reason described above, this [EASA] AD requires modification of the flap control system by installing two spacers to PO 00000 Frm 00009 Fmt 4700 Sfmt 4700 42029 replace a single long spacer, repetitive inspections of the flap bell crank, and, depending on findings, replacement of the flap bell crank with an improved part. Installation of an improved flap bell crank constitutes terminating action for the repetitive inspections required by this [EASA] AD. The MCAI can be found in the AD docket on the Internet at https:// www.regulations.gov/ document?D=FAA-2017-0638-0002. Comments We gave the public the opportunity to participate in developing this AD. We received no comments on the NPRM or on the determination of the cost to the public. Conclusion We reviewed the relevant data and determined that air safety and the public interest require adopting this AD as proposed except for minor editorial changes. We have determined that these minor changes: • Are consistent with the intent that was proposed in the NPRM for correcting the unsafe condition; and • Do not add any additional burden upon the public than was already proposed in the NPRM. Related Service Information Under 1 CFR Part 51 We reviewed Diamond Aircraft Industries GmbH Mandatory Service Bulletin MSB 42–126 MSB/42NG–066, dated March 27, 2017 (single document), and Work Instruction WI– MSB 42–126/WI–MSB 42NG–066, dated March 27, 2017 (single document). In combination, this service information describes procedures for repetitively inspecting the flap bell crank for cracks, replacing the flap bell crank if cracks are found, and modification of the flap control system. 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 of this AD. Costs of Compliance We estimate that this AD will affect 190 products of U.S. registry. We also estimate that it will take about 4 workhours per product to comply with the initial inspection requirement of this AD. The average labor rate is $85 per work-hour. Based on these figures, we estimate the cost of the initial inspection requirement of this AD on U.S. operators to be $64,000, or $340 per product. We also estimate that it will take about 2 work-hours per product to E:\FR\FM\06SER1.SGM 06SER1

Agencies

[Federal Register Volume 82, Number 171 (Wednesday, September 6, 2017)]
[Rules and Regulations]
[Pages 42024-42029]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-17838]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2017-0474; Product Identifier 2016-NM-096-AD; Amendment 
39-19007; AD 2017-17-17]
RIN 2120-AA64


Airworthiness Directives; Viking Air Limited (Type Certificate 
Previously Held by Bombardier, Inc.; Canadair Limited) Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

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

SUMMARY: We are superseding Airworthiness Directive (AD) 2011-03-08, 
which applied to certain Bombardier, Inc., Model CL-215-1A10 (CL-215), 
CL-215-6B11 (CL-215T Variant), and CL-215-6B11 (CL-415 Variant) 
airplanes. AD 2011-03-08 required an inspection to determine the number 
of flight cycles accumulated by certain accumulators installed on the 
airplane, and repetitive inspections of the accumulators for cracks, 
and replacement if necessary. This AD retains those inspections and the 
accumulator replacement if necessary, and adds a new terminating action 
to address the identified unsafe condition. This AD was prompted by the 
development of a terminating action for the repetitive inspections. We 
are issuing this AD to address the unsafe condition on these products.

DATES: This AD is effective October 11, 2017.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of October 11, 
2017.
    The Director of the Federal Register approved the incorporation by 
reference of certain other publications listed in this AD as of March 
14, 2011 (76 FR 6536, February 7, 2011).

ADDRESSES: For service information identified in this final rule, 
contact Viking Air Limited, 1959 de Havilland Way, Sidney, British 
Columbia V8L 5V5, Canada; telephone +1-250-656-7227; fax +1-250-656-
0673; email acs-technical.publications@vikingair.com; Internet http://www.vikingair.com. You may view this referenced service information at 
the FAA, Transport Standards Branch, 1601 Lind Avenue SW., Renton, WA. 
For information on the availability of this material at the FAA, call 
425-227-1221. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2017-
0474.

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-2017-
0474; or in person at the Docket Management Facility between 9 a.m. and 
5 p.m., Monday through Friday, except Federal holidays. The AD docket 
contains this AD, the regulatory evaluation, any comments received, and 
other information. The address for the Docket Office (telephone 800-
647-5527) is Docket Management Facility, U.S. Department of 
Transportation, Docket Operations, M-30, West Building Ground Floor, 
Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Cesar A. Gomez, Aerospace Engineer, 
Airframe and Mechanical Systems Section, FAA, New York ACO Branch, 1600 
Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516-228-7318; 
fax 516-794-5531.

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to supersede AD 2011-03-08, Amendment 39-16592 (76 FR 6536, 
February 7, 2011) (``AD 2011-03-08''). AD 2011-03-08 applied to certain 
Bombardier, Inc., Model CL-215-1A10 (CL-215), CL-215-6B11 (CL-215T 
Variant), and CL-215-6B11 (CL-415 Variant) airplanes. The NPRM 
published in the Federal Register on May 18, 2017 (82 FR 22766). The 
NPRM was prompted by the development of a terminating action 
(relocation of the affected accumulators, and incorporation of new 
airworthiness limitations), which addresses the unsafe condition. The 
NPRM proposed to continue to require an inspection to determine the 
number of flight cycles accumulated by applicable accumulators (i.e., 
brake, aileron, elevator, and rudder accumulators) installed on the 
airplane, repetitive ultrasonic inspections of the accumulators for 
cracks, and

[[Page 42025]]

replacement of any accumulator in which a crack is detected. The NPRM 
also proposed to require a new terminating action for the repetitive 
inspections. We are issuing this AD to prevent failure of the screw cap 
or end cap of certain accumulators, which could result in impact damage 
to various components, potentially resulting in fuel spillage, 
uncommanded flap movement, or loss of aileron control.
    Transport Canada Civil Aviation (TCCA), which is the aviation 
authority for Canada, has issued Canadian Airworthiness Directive CF-
2009-42R2, dated May 30, 2016 (referred to after this as the Mandatory 
Continuing Airworthiness Information, or ''the MCAI''), to correct an 
unsafe condition for certain Viking Air Limited Model CL-215-1A10 (CL-
215), CL-215-6B11 (CL-215T Variant), and CL-215-6B11 (CL-415 Variant) 
airplanes. The MCAI states:

    Seven cases of on-ground hydraulic accumulator screw cap or end 
cap failure have been experienced on CL-600-2B19 (CRJ) aeroplane, 
resulting in loss of the associated hydraulic system and high-energy 
impact damage to adjacent systems and structure. To date, the lowest 
number of flight cycles accumulated at the time of failure has been 
6991.
    Although there have been no failures to date on any CL-215-1A10 
(CL-215) or CL-215-6B11 (CL-215T and CL-415) aeroplane, similar 
accumulators, Part Number (P/N) 08-8423-010 (MS28700-3), to those 
installed on the CL-600-2B19, are installed on the aeroplane models 
listed in the Applicability section of this [Canadian] AD.
    A detailed analysis of the systems and structure in the 
potential line of trajectory of a failed screw cap/end cap for each 
accumulator has been conducted. It has identified that the worst-
case scenarios would be impact damage to various components, 
potentially resulting in fuel spillage, uncommanded flap movement, 
or loss of aileron control.
    This [Canadian] AD mandates repetitive [ultrasonic] inspections 
of the accumulators for cracks and replacement of any accumulator in 
which a crack is detected.
    Revision 1 of this [Canadian] AD clarified the text of the 
[Canadian] AD, including the P/N of the affected accumulators.
    This revision provides the terminating action [relocation of 
affected accumulators and incorporation of new airworthiness 
limitations] to this [Canadian] AD. It also modifies the 
applicability range for the CL-215-1A10 (CL-215); the CL-215 is out 
of production and the last aeroplane produced was serial number 
1125.

    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-2017-
0474.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We received no comments on the NPRM or on the determination of 
the cost to the public.

Explanation of Changes Made to This Final Rule

    We have revised this final rule to identify the legal name of the 
manufacturer as published in the most recent type certificate data 
sheet for the affected airplane models.
    In the proposed AD, we inadvertently listed the wrong publication 
dates for service information in two places. Table 4 to paragraph (o) 
of the proposed AD referred to Bombardier Service Bulletin 215-4470, 
Revision 1, dated December 13, 2013. We have corrected the publication 
date for this document to June 27, 2014, in this AD. Additionally, 
paragraph (r)(1)(iii) of the proposed AD referred to Bombardier Service 
Bulletin 215-3158, dated March 28, 2012. We have corrected the 
publication date for this document to March 21, 2012, in this AD.

Conclusion

    We reviewed the available data and determined that air safety and 
the public interest require adopting this AD with the changes described 
previously and minor editorial changes. We have determined that these 
changes:
     Are consistent with the intent that was proposed in the 
NPRM for correcting the unsafe condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM.

Related Service Information Under 1 CFR Part 51

    Bombardier, Inc., has issued the following service information:
     Bombardier Service Bulletin 215-552, Revision 2, dated 
June 18, 2015. This service information describes procedures to 
relocate the aileron hydraulic accumulator aft of its current location.
     Bombardier Service Bulletin 215-3158, Revision 2, dated 
April 15, 2014; and Bombardier Service Bulletin 215-4423, Revision 5, 
dated March 17, 2016. This service information describes procedures to 
relocate the aileron, elevator, and rudder hydraulic accumulators aft 
and outboard of their current locations. These documents are distinct 
since they apply to different airplane models.
     Bombardier Service Bulletin 215-557, Revision 1, dated 
June 27, 2014; Bombardier Service Bulletin 215-3182, Revision 1, dated 
June 27, 2014; and Bombardier Service Bulletin 215-4470, Revision 1, 
dated June 27, 2014. This service information describes procedures to 
establish the number of flight hours for each accumulator and determine 
if it has been used on another type of aircraft. These documents are 
distinct since they apply to different airplane models.
     Bombardier Temporary Revision 5-56, dated December 13, 
2013; Bombardier Temporary Revision 295/7, dated December 13, 2013; 
Bombardier Temporary Revision LLC-1, dated December 13, 2013; and 
Bombardier Temporary Revision LLC-3, dated December 13, 2013. This 
service information provides a 10,000-hour accumulator life limitation 
for certain accumulators. These documents are distinct since they apply 
to different airplane models.
    This service information is reasonably available because the 
interested parties have access to it through their normal course of 
business or by the means identified in the ADDRESSES section.

Costs of Compliance

    We estimate that this AD affects 7 airplanes of U.S. registry.
    We estimate the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                     Cost per      Cost on U.S.
                Action                         Labor cost           Parts cost        product        operators
----------------------------------------------------------------------------------------------------------------
Ultrasonic inspection (retained action  7 work-hours x $85 per                $0            $595          $4,165
 from AD 2011-03-08).                    hour = $595.
Relocation, determination of            56 work-hours x $85 per                0           4,760          33,320
 accumulator hours and usage, and        hour = $4,760.
 maintenance or inspection program
 revision (new action).
----------------------------------------------------------------------------------------------------------------


[[Page 42026]]

    We estimate the following costs to do any necessary replacement 
that would be required based on the results of the inspection. We have 
no way of determining the number of aircraft that might need this 
replacement.

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                    Action                                 Labor cost               Parts cost        product
----------------------------------------------------------------------------------------------------------------
Replacement of cracked part (retained action    6 work-hours x $85 per hour =             $4,055          $4,565
 from AD 2011-03-08).                            $510.
----------------------------------------------------------------------------------------------------------------

    According to the manufacturer, some of the costs of this AD may be 
covered under warranty, thereby reducing the cost impact on affected 
individuals. We do not control warranty coverage for affected 
individuals. As a result, we have included all costs in our cost 
estimate.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. ``Subtitle VII: Aviation 
Programs,'' describes in more detail the scope of the Agency's 
authority.
    We are issuing this rulemaking under the authority described in 
``Subtitle VII, Part A, Subpart III, Section 44701: General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.
    This AD is issued in accordance with authority delegated by the 
Executive Director, Aircraft Certification Service, as authorized by 
FAA Order 8000.51C. In accordance with that order, issuance of ADs is 
normally a function of the Compliance and Airworthiness Division, but 
during this transition period, the Executive Director has delegated the 
authority to issue ADs applicable to transport category airplanes to 
the Director of the System Oversight Division.

Regulatory Findings

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

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

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

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


Sec.  39.13   [Amended]

0
2. The FAA amends Sec.  39.13 by removing Airworthiness Directive (AD) 
2011-03-08, Amendment 39-16592 (76 FR 6536, February 7, 2011), and 
adding the following new AD:

2017-17-17 Viking Air Limited (Type Certificate Previously Held by 
Bombardier, Inc.; Canadair Limited): Amendment 39-19007; Docket No. 
FAA-2017-0474; Product Identifier 2016-NM-096-AD.

(a) Effective Date

    This AD is effective October 11, 2017.

(b) Affected ADs

    This AD replaces AD 2011-03-08, Amendment 39-16592 (76 FR 6536, 
February 7, 2011) (``AD 2011-03-08'').

(c) Applicability

    This AD applies to Viking Air Limited (Type Certificate 
previously held by Bombardier, Inc.; Canadair Limited) airplanes, 
certificated in any category, as identified in paragraphs (c)(1) 
through (c)(3) of this AD.
    (1) Model CL-215-1A10 (CL-215) airplanes, serial numbers 1001 
through 1125 inclusive.
    (2) Model CL-215-6B11 (CL-215T Variant) airplanes, serial 
numbers 1056 through 1125 inclusive.
    (3) Model CL-215-6B11 (CL-415 Variant) airplanes, serial numbers 
2001 through 2990 inclusive.

(d) Subject

    Air Transport Association (ATA) of America Code 29, Hydraulic 
power.

(e) Reason

    This AD was prompted by reports of on-ground hydraulic 
accumulator screw cap or end cap failure resulting in a loss of the 
associated hydraulic system and high-energy impact damage to 
adjacent systems and structure. We are issuing this AD to prevent 
failure of the screw cap or end cap, which could result in impact 
damage to various components, potentially resulting in fuel 
spillage, uncommanded flap movement, or loss of aileron control.

(f) Compliance

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

(g) Retained Inspection To Determine Flight Cycles, With No Changes

    This paragraph restates the requirements of paragraph (g) of AD 
2011-03-08, with no changes. Within 50 flight hours after March 14, 
2011 (the effective date of AD 2011-03-08), inspect to determine the 
number of flight cycles accumulated by each of the applicable 
accumulators (i.e., brake, aileron, elevator, and rudder 
accumulators) having part number 08-8423-010 (MS28700-3) installed 
on the airplane. A review of airplane maintenance records is 
acceptable in lieu of this inspection if the number of flight cycles 
accumulated can be conclusively determined from that review.

(h) Retained Initial Ultrasonic Inspection for Model CL-215-1A10 (CL-
215) and CL-215-6B11 (CL-215T Variant) Airplanes, With No Changes

    This paragraph restates the requirements of paragraph (h) of AD 
2011-03-08, with no changes. For Model CL-215-1A10 (CL-215) and CL-
215-6B11 (CL-215T Variant) airplanes: Do an ultrasonic inspection 
for cracking of the accumulator at the applicable time specified in 
paragraph (h)(1) or (h)(2) of this AD, in accordance with Part B of 
the Accomplishment Instructions of the

[[Page 42027]]

applicable service bulletin listed in table 1 to paragraphs (h), 
(i), and (k) of this AD.

  Table 1 to Paragraphs (h), (i), and (k) of This AD--Service Bulletins
------------------------------------------------------------------------
                                               Use bombardier service
                For model--                          bulletin--
------------------------------------------------------------------------
CL-215-1A10 (CL-215)......................  215-541, Revision 1, dated
                                             March 12, 2010.
CL-215-6B11 (CL-215T Variant).............  215-3155, Revision 1, dated
                                             March 12, 2010.
CL-215-6B11 (CL-415 Variant)..............  215-4414, Revision 1, dated
                                             March 12, 2010.
------------------------------------------------------------------------

    (1) For any accumulator on which the inspection required by 
paragraph (g) of this AD shows an accumulation of more than 875 
total flight cycles, or on which it is not possible to determine the 
number of total accumulated flight cycles, do the inspection within 
125 flight cycles after March 14, 2011 (the effective date of AD 
2011-03-08).
    (2) For any accumulator on which the inspection required by 
paragraph (g) of this AD shows an accumulation of 875 total flight 
cycles or fewer, do the inspection before the accumulation of 1,000 
flight cycles on the accumulator.

(i) Retained Initial Ultrasonic Inspection for Model CL-215-6B11 (CL-
415 Variant) Airplanes, With No Changes

    This paragraph restates the requirements of paragraph (i) of AD 
2011-03-08, with no changes. For Model CL-215-6B11 (CL-415 Variant) 
airplanes, do an ultrasonic inspection for cracking of the 
accumulator at the applicable time specified in paragraph (i)(1) or 
(i)(2) of this AD, in accordance with Part B of the Accomplishment 
Instructions of the applicable service bulletin listed in table 1 to 
paragraphs (h), (i), and (k) of this AD.
    (1) For any accumulator on which the inspection required by 
paragraph (g) of this AD shows an accumulation of more than 750 
flight cycles, or on which it is not possible to determine the 
number of total accumulated flight cycles, do the inspection within 
250 flight cycles after March 14, 2011 (the effective date of AD 
2011-03-08).
    (2) For any accumulator on which the inspection required by 
paragraph (g) of this AD shows an accumulation of 750 total flight 
cycles or fewer, do the inspection before the accumulation of 1,000 
flight cycles on the accumulator.

(j) Retained Repetitive Inspections, With New Terminating Action

    This paragraph restates the requirements of paragraph (j) of AD 
2011-03-08, with new terminating action. If no cracking is found 
during any inspection required by paragraph (h) or (i) of this AD, 
repeat the inspection thereafter at intervals not to exceed 750 
flight cycles until the actions required by paragraphs (n), (o), and 
(p) of this AD have been done.

(k) Retained Replacement of Cracked Accumulators and Repetitive 
Inspections, With New Terminating Action

    This paragraph restates the requirements of paragraph (k) of AD 
2011-03-08, with new terminating action. If any cracking is found 
during any inspection required by paragraph (h) or (i) of this AD, 
before further flight, replace the accumulator with a serviceable 
accumulator, in accordance with Part B of the Accomplishment 
Instructions of the applicable service bulletin listed in table 1 to 
paragraphs (h), (i), and (k) of this AD. Doing the replacement does 
not end the inspection requirements of paragraphs (h) and (i) of 
this AD. Repeat the inspections required by paragraph (h) or (i) of 
this AD, as applicable, at intervals not to exceed 750 flight cycles 
until the actions required by paragraphs (n), (o), and (p) of this 
AD have been done.

(l) Retained Parts Installation Limitation, With No Changes

    This paragraph restates the parts installation limitation in 
paragraph (l) of AD 2011-03-08, with no changes. As of March 14, 
2011 (the effective date of AD 2011-03-08), no person may install an 
accumulator, part number 08-8423-010 (MS28700-3), on any airplane 
unless the accumulator has been inspected in accordance with the 
requirements of paragraph (h) or (i) of this AD.

(m) Retained Credit for Previous Actions, With No Changes

    This paragraph restates the credit provided in paragraph (m) of 
AD 2011-03-08, with no changes. Inspections accomplished before 
March 14, 2011 (the effective date of AD 2011-03-08), in accordance 
with the applicable service bulletin listed in table 2 to paragraph 
(m) of this AD are considered acceptable for compliance with the 
corresponding action specified in paragraph (h), (i), (j), or (k) of 
this AD.

      Table 2 to Paragraph (m) of This AD--Credit Service Bulletins
------------------------------------------------------------------------
                                               Use Bombardier Service
                For model--                          Bulletin--
------------------------------------------------------------------------
CL-215-1A10 (CL-215)......................  215-541, dated July 9, 2009.
CL-215-6B11 (CL-215T Variant).............  215-3155, dated July 9,
                                             2009.
CL-600-6B11 (CL-415 Variant)..............  215-4414, dated July 9,
                                             2009.
------------------------------------------------------------------------

(n) New Relocation of Affected Accumulators

    Within 12 months after the effective date of this AD, relocate 
affected hydraulic accumulators, in accordance with the 
Accomplishment Instructions of the applicable Bombardier service 
bulletin specified in table 3 to paragraph (n) of this AD.

 Table 3 to Paragraph (n) of This AD--Service Information for Relocating
                              Accumulators
------------------------------------------------------------------------
                                     Affected      Use Service Bulletin--
          For model--             accumulators--
------------------------------------------------------------------------
CL-215-1A10 (CL-215)..........  Aileron, if        Bombardier Service
                                 installed.         Bulletin 215-552,
                                                    Revision 2, dated
                                                    June 18, 2015.
CL-215-6B11 (CL-215T Variant).  Aileron, rudder,   Bombardier Service
                                 and elevator.      Bulletin 215-3158,
                                                    Revision 2, dated
                                                    April 15, 2014.
CL-215-6B11 (CL-415 Variant)..  Aileron, rudder,   Bombardier Service
                                 and elevator.      Bulletin 215-4423,
                                                    Revision 5, dated
                                                    March 17, 2016.
------------------------------------------------------------------------

(o) New Establishment of Flight Hours on the Accumulator, Determination 
of Previous Use of the Accumulator, and Replacement if Necessary

    Within 12 months after the effective date of this AD, establish 
the number of flight hours for each accumulator, and determine 
whether any accumulator has been used in service on another type of 
airplane other than Model CL-215-1A10 (CL-215), CL-215-6B11 (CL-215T 
Variant), or CL-215-6B11 (CL-415 Variant), in accordance with the 
Accomplishment Instructions in the applicable Bombardier service 
bulletin specified in table 4 to paragraph (o) of this AD. If any 
accumulator is found that has been in service on another type of 
airplane other than Model CL-215-1A10 (CL-215), CL-215-6B11 (CL-215T 
Variant), or CL-215-6B11 (CL-415 Variant), replace the accumulator 
within 50 flight hours after determining an affected accumulator is 
installed.

 Table 4 to Paragraph (o) of This AD--Establishment of Number of Flight
                        Hours on the Accumulator
------------------------------------------------------------------------
         For model--                     Use Service Bulletin--
------------------------------------------------------------------------
CL-215-1A10 (CL-215).........  Bombardier Service Bulletin 215-557,
                                Revision 1, dated June 27, 2014
                                (applicable to MS28700-3 accumulator).

[[Page 42028]]

 
CL-215-6B11 (CL-215T Variant)  Bombardier Service Bulletin 215-3182,
                                Revision 1, dated June 27, 2014.
CL-215-6B11 (CL-415 Variant).  Bombardier Service Bulletin 215-4470,
                                Revision 1, dated June 27, 2014.
------------------------------------------------------------------------

(p) New Airworthiness Limitations

    Within 30 days after the effective date of this AD, revise the 
maintenance or inspection program, as applicable, to incorporate the 
10,000-hour accumulator life limitation specified in the applicable 
Time Limits/Maintenance Checks (TLMC) Manual temporary revisions 
(TRs) listed in table 5 to paragraph (p) of this AD. The initial 
compliance time for accomplishing the replacement of the accumulator 
is within the limitation specified in the applicable TR specified in 
table 5 to paragraph (p) of this AD, or within 30 days after the 
effective date of this AD, whichever occurs later.

                                             Table 5 to Paragraph (p) of This AD--Airworthiness Limitations
--------------------------------------------------------------------------------------------------------------------------------------------------------
             For model--               Comply with Bombardier TLMC manual--             Bombardier TR No.--                         Dated--
--------------------------------------------------------------------------------------------------------------------------------------------------------
CL-215-1A10 (CL-215)................  PSP 295...............................  295/7.................................  December 13, 2013.
CL-215-6B11 (CL-215T Variant).......  PSP 395...............................  LLC-3.................................  December 13, 2013.
CL-215-6B11 (CL-215T Variant).......  PSP 395-1.............................  LLC-1.................................  December 13, 2013.
CL-215-6B11 (CL-415 Variant)........  PSP 495...............................  5-56..................................  December 13, 2013.
--------------------------------------------------------------------------------------------------------------------------------------------------------

(q) No Alternative Actions and Intervals

    After accomplishment of the revision required by paragraph (p) 
of this AD, no alternative actions (e.g., inspections) or intervals 
may be used unless the actions and intervals are approved as an 
alternative method of compliance (AMOC) in accordance with the 
procedures specified in paragraph (s)(1) of this AD.

(r) Credit for Previous Actions

    (1) This paragraph provides credit for actions required by 
paragraph (n) of this AD, if those actions were performed before the 
effective date of this AD using any applicable service information 
specified in paragraphs (r)(1)(i) through (r)(1)(ix) of this AD.
    (i) Bombardier Service Bulletin 215-552, dated December 16, 
2013.
    (ii) Bombardier Service Bulletin 215-552, Revision 1, dated 
September 12, 2014.
    (iii) Bombardier Service Bulletin 215-3158, dated March 21, 
2012.
    (iv) Bombardier Service Bulletin 215-3158, Revision 1, dated 
December 16, 2013.
    (v) Bombardier Service Bulletin 215-4423, Revision NC, dated 
April 4, 2011.
    (vi) Bombardier Service Bulletin 215-4423, Revision 1, dated 
September 28, 2011.
    (vii) Bombardier Service Bulletin 215-4423, Revision 2, dated 
May 30, 2012.
    (viii) Bombardier Service Bulletin 215-4423, Revision 3, dated 
December 16, 2013.
    (ix) Bombardier Service Bulletin 215-4423, Revision 4, dated 
December 3, 2015.
    (2) This paragraph provides credit for actions required by 
paragraph (o) of this AD, if those actions were performed before the 
effective date of this AD using any applicable service information 
specified in paragraphs (r)(2)(i) through (r)(2)(iii) of this AD.
    (i) Bombardier Service Bulletin 215-557, Revision NC, dated 
December 13, 2013.
    (ii) Bombardier Service Bulletin 215-3182, Revision NC, dated 
December 13, 2013.
    (iii) Bombardier Service Bulletin 215-4470, Revision NC, dated 
December 13, 2013.

(s) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, New 
York ACO Branch, FAA, has the authority to approve AMOCs for this 
AD, if requested using the procedures found in 14 CFR 39.19. In 
accordance with 14 CFR 39.19, send your request to your principal 
inspector or local Flight Standards District Office, as appropriate. 
If sending information directly to the manager of the certification 
office, send it to ATTN: Program Manager, Continuing Operational 
Safety, FAA, New York ACO Branch, 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.
    (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 
Branch, FAA; or Transport Canada Civil Aviation (TCCA); or Viking 
Air Limited's TCCA Design Approval Organization (DAO). If approved 
by the DAO, the approval must include the DAO-authorized signature.

(t) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) Canadian Airworthiness Directive CF-2009-42R2, dated May 30, 
2016, 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-2017-0474.
    (2) For more information about this AD, contact Cesar A. Gomez, 
Aerospace Engineer, Airframe and Mechanical Systems Section, FAA, 
New York ACO Branch, 1600 Stewart Avenue, Suite 410, Westbury, NY 
11590; telephone 516-228-7318; fax 516-794-5531.
    (3) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (u)(5) and (u)(6) of this AD.

(u) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless this AD specifies otherwise.
    (3) The following service information was approved for IBR on 
October 11, 2017.
    (i) Bombardier Service Bulletin 215-552, Revision 2, dated June 
18, 2015.
    (ii) Bombardier Service Bulletin 215-557, Revision 1, dated June 
27, 2014.
    (iii) Bombardier Service Bulletin 215-3158, Revision 2, dated 
April 15, 2014.
    (iv) Bombardier Service Bulletin 215-3182, Revision 1, dated 
June 27, 2014.
    (v) Bombardier Service Bulletin 215-4423, Revision 5, dated 
March 17, 2016.
    (vi) Bombardier Service Bulletin 215-4470, Revision 1, dated 
June 27, 2014.
    (vii) Bombardier Temporary Revision 5-56, dated December 13, 
2013.
    (viii) Bombardier Temporary Revision 295/7, dated December 13, 
2013.
    (ix) Bombardier Temporary Revision LLC-1, dated December 13, 
2013.
    (x) Bombardier Temporary Revision LLC-3, dated December 13, 
2013.
    (4) The following service information was approved for IBR on 
March 14, 2011 (76 FR 6536, February 7, 2011).
    (i) Bombardier Service Bulletin 215-541, Revision 1, dated March 
12, 2010.
    (ii) Bombardier Service Bulletin 215-3155, Revision 1, dated 
March 12, 2010.
    (iii) Bombardier Service Bulletin 215-4414, Revision 1, dated 
March 12, 2010.
    (5) For service information identified in this AD, contact 
Viking Air Limited, 1959 de

[[Page 42029]]

Havilland Way, Sidney, British Columbia V8L 5V5, Canada; telephone 
+1-250-656-7227; fax +1-250-656-0673; email acs-technical.publications@vikingair.com; Internet http://www.vikingair.com.
    (6) You may view this service information at the FAA, Transport 
Standards Branch, 1601 Lind Avenue SW., Renton, WA. For information 
on the availability of this material at the FAA, call 425-227-1221.
    (7) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on August 16, 2017.
Jeffrey E. Duven,
Director, System Oversight Division, Aircraft Certification Service.
[FR Doc. 2017-17838 Filed 9-5-17; 8:45 am]
 BILLING CODE 4910-13-P