Airworthiness Directives; Bombardier, Inc. (Type Certificate Previously Held by Canadair Limited) Airplanes, 22766-22771 [2017-10030]

Download as PDF 22766 Federal Register / Vol. 82, No. 95 / Thursday, May 18, 2017 / Proposed Rules jstallworth on DSK7TPTVN1PROD with PROPOSALS been authorized by the Manager, Los Angeles ACO, to make those findings. To be approved, the repair method, modification deviation, or alteration deviation must meet the certification basis of the airplane, and the approval must specifically refer to this AD. (4) Except as required by paragraph (j)(2) of this AD: For service information that contains steps that are labeled as Required for Compliance (RC), the provisions of paragraphs (m)(4)(i) and (m)(4)(ii) of this AD apply. (i) The steps labeled as RC, including substeps under an RC step and any figures identified in an RC step, must be done to comply with the AD. If a step or substep is labeled ‘‘RC Exempt,’’ then the RC requirement is removed from that step or substep. An AMOC is required for any deviations to RC steps, including substeps and identified figures. (ii) Steps not labeled as RC may be deviated from using accepted methods in accordance with the operator’s maintenance or inspection program without obtaining approval of an AMOC, provided the RC steps, including substeps and identified figures, can still be done as specified, and the airplane can be put back in an airworthy condition. DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2017–0474; Directorate Identifier 2016–NM–096–AD] RIN 2120–AA64 Airworthiness Directives; Bombardier, Inc. (Type Certificate Previously Held by Canadair Limited) Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to supersede Airworthiness Directive (AD) 2011–03– 08, for 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 currently requires an inspection to determine the number of flight cycles accumulated by certain accumulators installed on the airplane, and repetitive inspections of the accumulators for (n) Related Information cracks and replacement if necessary. Since we issued AD 2011–03–08, we (1) For more information about this AD, contact Lu Lu, Aerospace Engineer, Airframe determined that a terminating action is Branch, ANM–120S, FAA, Seattle ACO, 1601 necessary to address the identified unsafe condition. This proposed AD Lind Avenue SW., Renton, WA 98057–3356; would add a requirement for the phone: 425–917–6478; fax: 425–917–6590; terminating action. We are proposing email: lu.lu@faa.gov. this AD to address the unsafe condition (2) For information about AMOCs, contact on these products. George Garrido, Aerospace Engineer, Airframe Branch, ANM–120L, FAA, Los DATES: We must receive comments on Angeles ACO, 3960 Paramount Boulevard, this proposed AD by July 3, 2017. Lakewood, CA 90712–4137; phone: 562–627– ADDRESSES: You may send comments, 5357; fax: 562–627–5210; email: using the procedures found in 14 CFR george.garrido@faa.gov. 11.43 and 11.45, by any of the following (3) For service information identified in methods: this AD, contact Boeing Commercial • Federal eRulemaking Portal: Go to Airplanes, Attention: Contractual & Data http://www.regulations.gov. Follow the Services (C&DS), 2600 Westminster Blvd., instructions for submitting comments. MC 110–SK57, Seal Beach, CA 90740–5600; • Fax: 202–493–2251. telephone 562–797–1717; Internet https:// • Mail: U.S. Department of www.myboeingfleet.com. You may view this Transportation, Docket Operations, M– referenced service information at the FAA, 30, West Building Ground Floor, Room Transport Airplane Directorate, 1601 Lind W12–140, 1200 New Jersey Avenue SE., Avenue SW., Renton, WA. For information Washington, DC 20590. on the availability of this material at the • Hand Delivery: U.S. Department of FAA, call 425–227–1221. Transportation, Docket Operations, M– Issued in Renton, Washington, on May 10, 30, West Building Ground Floor, Room 2017. W12–140, 1200 New Jersey Avenue SE., Jeffrey E. Duven, Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Manager, Transport Airplane Directorate, Federal holidays. Aircraft Certification Service. For service information identified in [FR Doc. 2017–10031 Filed 5–17–17; 8:45 am] this NPRM, contact Bombardier, Inc., BILLING CODE 4910–13–P ˆ 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 VerDate Sep<11>2014 12:41 May 17, 2017 Jkt 241001 SUMMARY: PO 00000 Frm 00005 Fmt 4702 Sfmt 4702 at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. Examining the AD Docket You may examine the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–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 proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone 800–647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Cesar A. Gomez, Aerospace Engineer, Airframe and Mechanical Systems Branch, ANE–171, FAA, New York Aircraft Certification Office (ACO), 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516–228–7318; fax 516–794–5531. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2017–0474; Directorate Identifier 2016–NM–096–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD based on those comments. We will post all comments we receive, without change, to http:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion On January 26, 2011, we issued AD 2011–03–08, Amendment 39–16592 (76 FR 6536, February 7, 2011) (‘‘AD 2011– 03–08’’), for 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 was prompted by reports of seven cases of on-ground hydraulic accumulator screw cap or end cap failure, which have resulted in loss of the associated hydraulic system and E:\FR\FM\18MYP1.SGM 18MYP1 22767 Federal Register / Vol. 82, No. 95 / Thursday, May 18, 2017 / Proposed Rules high-energy impact damage to adjacent systems and structure. AD 2011–03–08 requires 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. AD 2011–03–08 also requires repetitive ultrasonic inspections of the accumulators for cracks and replacement of any accumulator in which a crack is detected. We issued AD 2011–03–08 to detect and correct cracking of the accumulator, which could result in loss of the associated hydraulic system and high-energy impact damage to adjacent systems and structure, potentially resulting in fuel spillage, uncommanded flap movement, or loss of aileron control. Since we issued AD 2011–03–08, terminating action for the repetitive inspections has been developed. We have determined that a terminating action (relocation of the affected accumulators, and incorporation of new airworthiness limitations) is necessary to address the identified unsafe condition. Transport Canada Civil Aviation (TCCA), which is the aviation authority for Canada, has issued Canadian Airworthiness Directive CF–2009–42R2, dated June 13, 2016 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for certain Bombardier, Inc., 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 the affected accumulators, and incorporating 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. Related Service Information Under 1 CFR Part 51 We reviewed the following Bombardier, Inc., service information: • Bombardier Canadair 215 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 Canadair 215T Service Bulletin 215–3158, Revision 2, dated April 15, 2014; and Bombardier 415 Service Bulletin 215–4423, Revision 5, dated March 17, 2016. These documents are distinct since they apply to different airplane models. This service information describes procedures to relocate the aileron, elevator, and rudder hydraulic accumulators aft and outboard of their current locations. • Bombardier Canadair 215 Service Bulletin 215–557, Revision 1, dated June 27, 2014; Bombardier Canadair 215T Service Bulletin 215–3182, Revision 1, dated June 27, 2014; and Bombardier 415 Service Bulletin 215– 4470, Revision 1, dated June 27, 2014. These documents are distinct since they apply to different airplane models. This service information provides procedures to establish the number of flight hours for each accumulator and determine if it has been used on another type of aircraft. • Bombardier Model CL–215–1A10 (CL–215), Time Limits/Maintenance Checks (TLMC) Manual PSP 295, TR 295–7, dated December 13, 2013; Bombardier Model CL–215–6B11 (CL– 215T), TLMC Manual PSP 395, TR LLC– 3, dated December 13, 2013; Bombardier Model CL–215–6B11 (CL–215T), TLMC Manual PSP 395–1, TR LLC–1, dated December 13, 2013; and Bombardier Model CL–600–6B11 (CL–415), TLMC Manual PSP 495, TR 5–56, dated December 13, 2013. These documents are distinct since they apply to different airplane models. This service information provides a 10,000-hour accumulator life limitation for certain accumulators. 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. 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 these same type designs. Costs of Compliance We estimate that this proposed AD affects 7 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: ESTIMATED COSTS jstallworth on DSK7TPTVN1PROD with PROPOSALS Action Labor cost Ultrasonic inspection [retained action from AD 2011–03–08] 7 work-hours × $85 per hour = $595. 56 work-hours × $85 per hour = $4,760. Relocation, determination of accumulator hours and usage, and maintenance or inspection program revision [new proposed action]. VerDate Sep<11>2014 12:41 May 17, 2017 Jkt 241001 PO 00000 Frm 00006 Fmt 4702 Sfmt 4702 Cost per product Parts cost E:\FR\FM\18MYP1.SGM Cost on U.S. operators $0 $595 $4,165 0 4,760 33,320 18MYP1 22768 Federal Register / Vol. 82, No. 95 / Thursday, May 18, 2017 / Proposed Rules We estimate the following costs to do any necessary replacement that would be required based on the results of the proposed inspection. We have no way of determining the number of airplanes that might need this replacement. ON-CONDITION COSTS Action Labor cost Parts cost Cost per product Replacement of cracked part [retained actions from AD 2011–03–08] .... 6 work-hours × $85 per hour = $510. $4,055 $4,565 According to the manufacturer, some of the costs of this proposed 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. jstallworth on DSK7TPTVN1PROD 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: General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify this proposed regulation: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; 2. Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 3. Will not affect intrastate aviation in Alaska; and VerDate Sep<11>2014 12:41 May 17, 2017 Jkt 241001 4. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] (3) Model CL–215–6B11 (CL–415) 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 Bombardier, Inc. (Type Certificate Previously Held by Canadair Limited): Docket No. FAA–2017–0474; Directorate Identifier 2016–NM–096–AD. 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. 2. The FAA amends § 39.13 by removing Airworthiness Directive (AD) 2011–03–08, Amendment 39–16592 (76 FR 6536, February 7, 2011) (‘‘AD 2011– 03–08’’), and adding the following new AD: (a) Comments Due Date We must receive comments by July 3, 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 Bombardier, Inc. (Type Certificate previously held by Canadair Limited) airplanes, certificated in any category, 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) airplanes, serial numbers 1056 through 1125 inclusive. PO 00000 Frm 00007 Fmt 4702 Sfmt 4702 (h) Retained Initial Ultrasonic Inspection for Model CL–215–1A10 (CL–215) and CL–215– 6B11 (CL–215T) 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) 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 applicable service bulletin listed in table 1 to paragraphs (h), (i), and (k) of this AD. E:\FR\FM\18MYP1.SGM 18MYP1 Federal Register / Vol. 82, No. 95 / Thursday, May 18, 2017 / Proposed Rules 22769 TABLE 1 TO PARAGRAPHS (h), (i), AND (k) OF THIS AD—SERVICE BULLETINS For model— Use Bombardier service bulletin— CL–215–1A10 (CL–215) .................................................... CL–215–6B11 (CL–215T) .................................................. CL–215–6B11 (CL–415) .................................................... 215–541, Revision 1, dated March 12, 2010. 215–3155, Revision 1, dated March 12, 2010. 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) 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) 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 total 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 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 Bombardier 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 Revised Compliance Language This paragraph restates the parts installation limitation in paragraph (l) of AD 2011–03–08, with revised compliance language. 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) ........................................................................... CL–215–6B11 (CL–215T) ........................................................................ CL–600–6B11 (CL–415) ........................................................................... 215–541, dated July 9, 2009. 215–3155, July 9, 2009. 215–4414, 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 accumulators— Use service bulletin— CL–215–1A10 (CL–215) .................................... Aileron, if installed ............................................ CL–215–6B11 (CL–215T) .................................. jstallworth on DSK7TPTVN1PROD with PROPOSALS For model— Aileron, Rudder, and Elevator ......................... CL–215–6B11 (CL–415) .................................... Aileron, Rudder, and Elevator ......................... Bombardier Canadair 215 Service Bulletin 215–552, Revision 2, dated June 18, 2015. Bombardier Canadair 215T Service Bulletin 215–3158, Revision 2, dated April 15, 2014. Bombardier 415 Service Bulletin 215–4423, Revision 5, dated March 17, 2016. VerDate Sep<11>2014 12:41 May 17, 2017 Jkt 241001 PO 00000 Frm 00008 Fmt 4702 Sfmt 4702 E:\FR\FM\18MYP1.SGM 18MYP1 22770 Federal Register / Vol. 82, No. 95 / Thursday, May 18, 2017 / Proposed Rules (o) New Establishment of Accumulator Number of Flight Hours and Determination of Previous Use of the Accumulator 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), and 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 ACCUMULATOR NUMBER OF FLIGHT HOURS For model— Use service bulletin— CL–215–1A10 (CL–215) ..................................... Bombardier Canadair 215 Service Bulletin 215–557, Revision 1, dated June 27, 2014 (Applicable to MS28700–3 accumulator). Bombardier Canadair 215T Service Bulletin 215–3182, Revision 1, dated June 27, 2014. Bombardier 415 Service Bulletin 215–4470, Revision 1, dated December 13, 2013. CL–215–6B11 (CL–215T) ................................... CL–215–6B11 (CL–415) ..................................... (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 Comply with TLMC manual— For model— CL–215–1A10 CL–215–6B11 CL–215–6B11 CL–215–6B11 (CL–215) ..................................................... (CL–215T) ................................................... (CL–215T) ................................................... (CL–415) ..................................................... jstallworth on DSK7TPTVN1PROD with PROPOSALS (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 Canadair 215 Service Bulletin 215–552, dated December 16, 2013. (ii) Bombardier Canadair 215 Service Bulletin 215–552, Revision 1, dated September 12, 2014. (iii) Bombardier Canadair 215T Service Bulletin 215–3158, dated March 28, 2012. (iv) Bombardier Canadair 215T Service Bulletin 215–3158, Revision 1, dated December 16, 2013. (v) Bombardier 415 Service Bulletin 215– 4423, dated April 4, 2011. (vi) Bombardier 415 Service Bulletin 215– 4423, Revision 1, dated September 28, 2011. (vii) Bombardier 415 Service Bulletin 215– 4423, Revision 2, dated May 30, 2012. (viii) Bombardier 415 Service Bulletin 215– 4423, Revision 3, dated December 16, 2013. (ix) Bombardier 415 Service Bulletin 215– 4423, Revision 4, dated December 3, 2015. (2) This paragraph provides credit for actions required by paragraph (o) of this AD, VerDate Sep<11>2014 12:41 May 17, 2017 Jkt 241001 Temporary revision (TR) number— Dated— PSP PSP PSP PSP 295–7 ................................... LLC–3 .................................. LLC–1 .................................. 5–56 ..................................... December December December December 295 .............................. 395 .............................. 395–1 .......................... 495 .............................. 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 Canadair 215 Service Bulletin 215–557, dated December 13, 2013. (ii) Bombardier Canadair 215T Service Bulletin 215–3182, dated December 13, 2013. (iii) Bombardier 415 Service Bulletin 215– 4470, 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, 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 manager of 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. (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, FAA; or Transport Canada Civil Aviation PO 00000 Frm 00009 Fmt 4702 Sfmt 4702 13, 13, 13, 13, 2013. 2013. 2013. 2013. (TCCA); or Bombardier, Inc.’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 June 13, 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 Branch, ANE–171, FAA, New York ACO, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516–228–7318; fax 516– 794–5531; email: Cesar.Gomez.faa.gov. (3) 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 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. E:\FR\FM\18MYP1.SGM 18MYP1 Federal Register / Vol. 82, No. 95 / Thursday, May 18, 2017 / Proposed Rules Issued in Renton, Washington, on May 10, 2017. Jeffrey E. Duven, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2017–10030 Filed 5–17–17; 8:45 am] BILLING CODE 4910–13–P LIBRARY OF CONGRESS Copyright Office 37 CFR Part 201 [Docket No. 2017–7] Modernizing Copyright Recordation U.S. Copyright Office, Library of Congress. ACTION: Notice of proposed rulemaking. AGENCY: The United States Copyright Office is proposing to amend its regulations governing recordation of transfers of copyright ownership, notices of termination, and other documents pertaining to a copyright. These amendments are being proposed in conjunction with the anticipated commencement of development effort for a modernized electronic recordation system. DATES: Written comments must be received no later than 11:59 p.m. Eastern Time on July 17, 2017. ADDRESSES: For reasons of government efficiency, the Copyright Office is using the regulations.gov system for the submission and posting of public comments in this proceeding. All comments are therefore to be submitted electronically through regulations.gov. Specific instructions for submitting comments are available on the Copyright Office Web site at https:// www.copyright.gov/rulemaking/ recordation-modernization. If electronic submission of comments is not feasible due to lack of access to a computer and/ or the internet, please contact the Office using the contact information below for special instructions. FOR FURTHER INFORMATION CONTACT: Sarang V. Damle, General Counsel and Associate Register of Copyrights, by email at sdam@loc.gov, or Jason E. Sloan, Attorney-Advisor, by email at jslo@loc.gov. Each can be contacted by telephone by calling (202) 707–8350. SUPPLEMENTARY INFORMATION: jstallworth on DSK7TPTVN1PROD with PROPOSALS SUMMARY: I. Background Since 1870, the U.S. Copyright Office has recorded documents pertaining to works under copyright, such as assignments, licenses, and grants of security interests. Relevant here are the VerDate Sep<11>2014 12:41 May 17, 2017 Jkt 241001 three primary types of documents submitted to the Copyright Office for recordation: Transfers of copyright ownership,1 other documents pertaining to a copyright,2 and notices of termination.3 Pursuant to 17 U.S.C. 205(a), ‘‘[a]ny transfer of copyright ownership or other document pertaining to a copyright may be recorded in the Copyright Office if’’ certain conditions are met.4 Under the Copyright Act’s notice of termination provisions in sections 203(a)(4) and 304(c)(4), ‘‘[a] copy of the notice shall be recorded in the Copyright Office before the effective date of termination, as a condition to its taking effect,’’ and such ‘‘notice shall comply, in form, content, and manner of service, with requirements that the Register of Copyrights shall prescribe by regulation.’’ 5 These provisions also apply to section 304(d)(1), another termination provision, which incorporates section 304(c)(4) by reference.6 More broadly, section 702 of the Act authorizes the Register of Copyrights to ‘‘establish regulations . . . for the administration of the functions and duties made the responsibility of the Register under [title 17],’’ and section 705(a) requires that the Register ‘‘ensure that records of . . . recordations . . . are maintained, and that indexes of such records are prepared.’’ 7 Congress has encouraged the submission of documents for recordation by providing certain legal entitlements as a consequence of 1 A ‘‘transfer of copyright ownership’’ is defined in section 101 of the Copyright Act as ‘‘an assignment, mortgage, exclusive license, or any other conveyance, alienation, or hypothecation of a copyright or of any of the exclusive rights comprised in a copyright, whether or not it is limited in time or place of effect, but not including a nonexclusive license.’’ 17 U.S.C. 101. Their validity is governed by 17 U.S.C. 204. 2 A document ‘‘pertaining to a copyright’’ is currently defined by the Office as one that ‘‘has a direct or indirect relationship to the existence, scope, duration, or identification of a copyright, or to the ownership, division, allocation, licensing, transfer, or exercise of rights under a copyright. That relationship may be past, present, future, or potential.’’ 37 CFR 201.4(a)(2). 3 A ‘‘notice of termination’’ is a notice that terminates a grant to a third party of a copyright in a work or any rights under a copyright. Only certain grants may be terminated, and only in certain circumstances. Termination is governed by three separate provisions of the Copyright Act, with the relevant one depending on a number of factors, including when the grant was made, who executed it, and when copyright was originally secured for the work. See 17 U.S.C. 203, 304(c), 304(d). 4 17 U.S.C. 205(a); see also id. at 205(b) (‘‘The Register of Copyrights shall, upon receipt of a document as provided by subsection (a) and of the fee provided by section 708, record the document and return it with a certificate of recordation.’’). 5 Id. at 203(a)(4), 304(c)(4). 6 Id. at 304(d)(1). 7 Id. at 702, 705(a). PO 00000 Frm 00010 Fmt 4702 Sfmt 4702 22771 recordation. For example, recordation provides constructive notice of the facts stated in the recorded document when certain conditions are met.8 In addition, recordation is a condition for the legal effectiveness of notices of termination.9 Thus, the Office has an important interest in ensuring that the public record of copyright transactions is as timely, complete, and accurate as possible. The current recordation process is a time-consuming and labor-intensive paper-based one, requiring remitters to submit their documents in hard copy. Once received, Office staff must, among other things, digitize the paper document, process the fee payment including confirming that the correct fee was submitted, examine the document to confirm its eligibility for recordation, search through the document for various and often extensive indexing information, manually input such information into the Office’s public catalog, and print and mail back to the remitter a copy of the document marked as having been recorded along with a certificate of recordation. This process can also involve considerable correspondence with remitters to remedy deficient submissions before they can be recorded. Since late 2014, the Office has permitted remitters to submit some indexing information in electronic form, limited to lists of titles of the works associated with the submitted document, but this too can involve a significant amount of correspondence with remitters and manual input on the part of staff to complete the recordation.10 Furthermore, electronic submission of documents remains unavailable. The Office is seeking to modernize this process in coming years by developing a fully electronic, online system through which remitters will be able to submit their documents and all applicable indexing information to the Office for recordation. The amendments proposed today are designed to update the Office’s current regulations to govern the submission of documents to the Office for recordation once the new electronic system is developed and launched. Though the Office cannot currently estimate how long it will take to complete the new system, the Office is seeking public comments at this time because the Office must, at present, make a number of policy decisions critical to the design of the to-bedeveloped system. Additionally, while 8 Id. at 205(c). at 203(a)(4)(A), 304(c)(4)(A), 304(d)(1). 10 See 37 CFR 201.4(c)(4); 79 FR 55633 (Sept. 17, 2014). 9 Id. E:\FR\FM\18MYP1.SGM 18MYP1

Agencies

[Federal Register Volume 82, Number 95 (Thursday, May 18, 2017)]
[Proposed Rules]
[Pages 22766-22771]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-10030]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2017-0474; Directorate Identifier 2016-NM-096-AD]
RIN 2120-AA64


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

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to supersede Airworthiness Directive (AD) 2011-03-
08, for 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 currently requires 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. Since we issued AD 2011-03-08, we determined 
that a terminating action is necessary to address the identified unsafe 
condition. This proposed AD would add a requirement for the terminating 
action. We are proposing this AD to address the unsafe condition on 
these products.

DATES: We must receive comments on this proposed AD by July 3, 2017.

ADDRESSES: 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 NPRM, 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 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 proposed AD, the regulatory evaluation, any comments 
received, and other information. The street address for the Docket 
Operations office (telephone 800-647-5527) is in the ADDRESSES section. 
Comments will be available in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Cesar A. Gomez, Aerospace Engineer, 
Airframe and Mechanical Systems Branch, ANE-171, FAA, New York Aircraft 
Certification Office (ACO), 1600 Stewart Avenue, Suite 410, Westbury, 
NY 11590; telephone 516-228-7318; fax 516-794-5531.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2017-0474; 
Directorate Identifier 2016-NM-096-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD based on those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    On January 26, 2011, we issued AD 2011-03-08, Amendment 39-16592 
(76 FR 6536, February 7, 2011) (``AD 2011-03-08''), for 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 was 
prompted by reports of seven cases of on-ground hydraulic accumulator 
screw cap or end cap failure, which have resulted in loss of the 
associated hydraulic system and

[[Page 22767]]

high-energy impact damage to adjacent systems and structure. AD 2011-
03-08 requires 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. AD 2011-03-08 also 
requires repetitive ultrasonic inspections of the accumulators for 
cracks and replacement of any accumulator in which a crack is detected. 
We issued AD 2011-03-08 to detect and correct cracking of the 
accumulator, which could result in loss of the associated hydraulic 
system and high-energy impact damage to adjacent systems and structure, 
potentially resulting in fuel spillage, uncommanded flap movement, or 
loss of aileron control.
    Since we issued AD 2011-03-08, terminating action for the 
repetitive inspections has been developed. We have determined that a 
terminating action (relocation of the affected accumulators, and 
incorporation of new airworthiness limitations) is necessary to address 
the identified unsafe condition.
    Transport Canada Civil Aviation (TCCA), which is the aviation 
authority for Canada, has issued Canadian Airworthiness Directive CF-
2009-42R2, dated June 13, 2016 (referred to after this as the Mandatory 
Continuing Airworthiness Information, or ``the MCAI''), to correct an 
unsafe condition for certain Bombardier, Inc., 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 the 
affected accumulators, and incorporating 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.

Related Service Information Under 1 CFR Part 51

    We reviewed the following Bombardier, Inc., service information:
     Bombardier Canadair 215 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 Canadair 215T Service Bulletin 215-3158, 
Revision 2, dated April 15, 2014; and Bombardier 415 Service Bulletin 
215-4423, Revision 5, dated March 17, 2016. These documents are 
distinct since they apply to different airplane models. This service 
information describes procedures to relocate the aileron, elevator, and 
rudder hydraulic accumulators aft and outboard of their current 
locations.
     Bombardier Canadair 215 Service Bulletin 215-557, Revision 
1, dated June 27, 2014; Bombardier Canadair 215T Service Bulletin 215-
3182, Revision 1, dated June 27, 2014; and Bombardier 415 Service 
Bulletin 215-4470, Revision 1, dated June 27, 2014. These documents are 
distinct since they apply to different airplane models. This service 
information provides procedures to establish the number of flight hours 
for each accumulator and determine if it has been used on another type 
of aircraft.
     Bombardier Model CL-215-1A10 (CL-215), Time Limits/
Maintenance Checks (TLMC) Manual PSP 295, TR 295-7, dated December 13, 
2013; Bombardier Model CL-215-6B11 (CL-215T), TLMC Manual PSP 395, TR 
LLC-3, dated December 13, 2013; Bombardier Model CL-215-6B11 (CL-215T), 
TLMC Manual PSP 395-1, TR LLC-1, dated December 13, 2013; and 
Bombardier Model CL-600-6B11 (CL-415), TLMC Manual PSP 495, TR 5-56, 
dated December 13, 2013. These documents are distinct since they apply 
to different airplane models. This service information provides a 
10,000-hour accumulator life limitation for certain accumulators.
    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.

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 these 
same type designs.

Costs of Compliance

    We estimate that this proposed AD affects 7 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
----------------------------------------------------------------------------------------------------------------
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 proposed action].
----------------------------------------------------------------------------------------------------------------


[[Page 22768]]

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

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                    Action                                Labor cost               Parts cost        product
----------------------------------------------------------------------------------------------------------------
Replacement of cracked part [retained actions  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 proposed 
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.

Regulatory Findings

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

List of Subjects in 14 CFR Part 39

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

The Proposed Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

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

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


Sec.  39.13  [Amended]

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

Bombardier, Inc. (Type Certificate Previously Held by Canadair 
Limited): Docket No. FAA-2017-0474; Directorate Identifier 2016-NM-
096-AD.

(a) Comments Due Date

    We must receive comments by July 3, 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 Bombardier, Inc. (Type Certificate previously 
held by Canadair Limited) airplanes, certificated in any category, 
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) airplanes, serial numbers 1056 
through 1125 inclusive.
    (3) Model CL-215-6B11 (CL-415) 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) 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) 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 applicable service bulletin 
listed in table 1 to paragraphs (h), (i), and (k) of this AD.

[[Page 22769]]



  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.
CL-215-6B11 (CL-215T).............  215-3155, Revision 1, dated March
                                     12, 2010.
CL-215-6B11 (CL-415)..............  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) 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) 
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 
total 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

    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 Bombardier 
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 Revised Compliance 
Language

    This paragraph restates the parts installation limitation in 
paragraph (l) of AD 2011-03-08, with revised compliance language. 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)..................  215-3155, July 9, 2009.
CL-600-6B11 (CL-415)...................  215-4414, 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
         For model--             accumulators--          bulletin--
------------------------------------------------------------------------
CL-215-1A10 (CL-215)........  Aileron, if           Bombardier Canadair
                               installed.            215 Service
                                                     Bulletin 215-552,
                                                     Revision 2, dated
                                                     June 18, 2015.
CL-215-6B11 (CL-215T).......  Aileron, Rudder, and  Bombardier Canadair
                               Elevator.             215T Service
                                                     Bulletin 215-3158,
                                                     Revision 2, dated
                                                     April 15, 2014.
CL-215-6B11 (CL-415)........  Aileron, Rudder, and  Bombardier 415
                               Elevator.             Service Bulletin
                                                     215-4423, Revision
                                                     5, dated March 17,
                                                     2016.
------------------------------------------------------------------------


[[Page 22770]]

(o) New Establishment of Accumulator Number of Flight Hours and 
Determination of Previous Use of the Accumulator

    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), and 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 Accumulator Number
                             of Flight Hours
------------------------------------------------------------------------
         For model--                     Use service bulletin--
------------------------------------------------------------------------
CL-215-1A10 (CL-215).........  Bombardier Canadair 215 Service Bulletin
                                215-557, Revision 1, dated June 27, 2014
                                (Applicable to MS28700-3 accumulator).
CL-215-6B11 (CL-215T)........  Bombardier Canadair 215T Service Bulletin
                                215-3182, Revision 1, dated June 27,
                                2014.
CL-215-6B11 (CL-415).........  Bombardier 415 Service Bulletin 215-4470,
                                Revision 1, dated December 13, 2013.
------------------------------------------------------------------------

(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
----------------------------------------------------------------------------------------------------------------
                                       Comply with TLMC     Temporary revision
            For model--                    manual--            (TR) number--                 Dated--
----------------------------------------------------------------------------------------------------------------
CL-215-1A10 (CL-215)..............  PSP 295..............  295-7...............  December 13, 2013.
CL-215-6B11 (CL-215T).............  PSP 395..............  LLC-3...............  December 13, 2013.
CL-215-6B11 (CL-215T).............  PSP 395-1............  LLC-1...............  December 13, 2013.
CL-215-6B11 (CL-415)..............  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 Canadair 215 Service Bulletin 215-552, dated 
December 16, 2013.
    (ii) Bombardier Canadair 215 Service Bulletin 215-552, Revision 
1, dated September 12, 2014.
    (iii) Bombardier Canadair 215T Service Bulletin 215-3158, dated 
March 28, 2012.
    (iv) Bombardier Canadair 215T Service Bulletin 215-3158, 
Revision 1, dated December 16, 2013.
    (v) Bombardier 415 Service Bulletin 215-4423, dated April 4, 
2011.
    (vi) Bombardier 415 Service Bulletin 215-4423, Revision 1, dated 
September 28, 2011.
    (vii) Bombardier 415 Service Bulletin 215-4423, Revision 2, 
dated May 30, 2012.
    (viii) Bombardier 415 Service Bulletin 215-4423, Revision 3, 
dated December 16, 2013.
    (ix) Bombardier 415 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 Canadair 215 Service Bulletin 215-557, dated 
December 13, 2013.
    (ii) Bombardier Canadair 215T Service Bulletin 215-3182, dated 
December 13, 2013.
    (iii) Bombardier 415 Service Bulletin 215-4470, 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, 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 manager of 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.
    (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, FAA; or Transport Canada Civil Aviation (TCCA); or 
Bombardier, Inc.'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 June 13, 
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 Branch, ANE-171, 
FAA, New York ACO, 1600 Stewart Avenue, Suite 410, Westbury, NY 
11590; telephone 516-228-7318; fax 516-794-5531; email: 
Cesar.Gomez.faa.gov.
    (3) 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 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.


[[Page 22771]]


    Issued in Renton, Washington, on May 10, 2017.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2017-10030 Filed 5-17-17; 8:45 am]
BILLING CODE 4910-13-P