Airworthiness Directives; Sikorsky Aircraft Corporation Helicopters, 3941-3944 [2018-01572]

Download as PDF Federal Register / Vol. 83, No. 19 / Monday, January 29, 2018 / Rules and Regulations 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 adding the following new airworthiness directive (AD): ■ 2018–02–16 Bombardier, Inc.: Amendment 39–19169; Docket No. FAA–2017–0621; Product Identifier 2017–NM–049–AD. (a) Effective Date This AD is effective March 5, 2018. (b) Affected ADs None. (c) Applicability This AD applies to Bombardier, Inc., Model DHC–8–400, –401, and –402 airplanes, certificated in any category, serial numbers 4001 and 4003 through 4488 inclusive, except those incorporating Bombardier ModSum IS4Q5200050. sradovich on DSK3GMQ082PROD with RULES (d) Subject Air Transport Association (ATA) of America Code 52, Doors. (e) Reason This AD was prompted by reports of interrupted operation of translating fuselage doors caused by corrosion in the door lift and latch shaft roller bearings. We are issuing this AD to detect and correct bearing corrosion and prevent door operation interruptions that could inhibit safe evacuation of the airplane in an emergency. (f) Compliance Comply with this AD within the compliance times specified, unless already done. VerDate Sep<11>2014 16:12 Jan 26, 2018 Jkt 244001 (g) Inspection and Replacement of Bearings Within 6,000 flight hours or 36 months after the effective date of this AD, whichever occurs earlier, do a detailed visual inspection of all translating fuselage door lift and latch shaft roller bearings for signs of corrosion, damaged seals, and loss of lubricant; replace any corroded bearings; and apply corrosioninhibiting compound (CIC); in accordance with paragraph 3.B., ‘‘Procedure,’’ of the Accomplishment Instructions of Bombardier Service Bulletin 84–52–88, dated April 14, 2016. (h) Credit for Previous Actions This paragraph provides credit for actions required by paragraph (g) of this AD, if those actions were performed before the effective date of this AD using Bombardier Service Bulletin 84–52–85, dated September 23, 2015; or Bombardier Service Bulletin 84–52– 85, Revision A, dated January 22, 2016. (i) 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 Bombardier, Inc.’s TCCA Design Approval Organization (DAO). If approved by the DAO, the approval must include the DAO-authorized signature. (j) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) Canadian Airworthiness Directive CF–2016–18, dated June 6, 2016, for related information. This MCAI may be found in the AD docket on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA– 2017–0621. (2) For more information about this AD, contact Aziz Ahmed, Aerospace Engineer, Airframe and Mechanical Systems Section, FAA, New York ACO Branch, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516–228–7329; 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 (k)(3) and (k)(4) of this AD. PO 00000 Frm 00005 Fmt 4700 Sfmt 4700 3941 (k) 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. (i) Bombardier Service Bulletin 84–52–88, dated April 14, 2016. (ii) Reserved. (3) For service information identified in this AD, contact Bombardier, Inc., Q-Series Technical Help Desk, 123 Garratt Boulevard, Toronto, Ontario M3K 1Y5, Canada; telephone 416–375–4000; fax 416–375–4539; email thd.qseries@aero.bombardier.com; internet https://www.bombardier.com. (4) 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. (5) 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: https:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued in Renton, Washington, on January 17, 2018. Michael Kaszycki, Acting Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2018–01317 Filed 1–26–18; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2017–0896; Product Identifier 2017–SW–034–AD; Amendment 39–19166; AD 2018–02–13] RIN 2120–AA64 Airworthiness Directives; Sikorsky Aircraft Corporation Helicopters Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: We are superseding Airworthiness Directive (AD) 2017–07– 02 for Sikorsky Aircraft Corporation (Sikorsky) Model 269D and Model 269D Configuration A helicopters. AD 2017– 07–02 required reducing the life limit of and inspecting certain drive shafts. This new AD retains the requirements of AD 2017–07–02 and requires repeating the inspections. The actions of this AD are intended to detect and prevent an unsafe condition on these products. DATES: This AD is effective March 5, 2018. SUMMARY: E:\FR\FM\29JAR1.SGM 29JAR1 3942 Federal Register / Vol. 83, No. 19 / Monday, January 29, 2018 / Rules and Regulations For service information identified in this final rule, contact Sikorsky Aircraft Corporation, Customer Service Engineering, 124 Quarry Road, Trumbull, CT 06611; telephone 1–800– Winged–S or 203–416–4299; email wcs_ cust_service_eng.gr-sik@lmco.com. You may view this referenced service information at the FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy, Room 6N–321, Fort Worth, TX 76177. ADDRESSES: sradovich on DSK3GMQ082PROD with RULES Examining the AD Docket You may examine the AD docket on the internet at https:// www.regulations.gov in Docket No. FAA–2017–0896; or in person at Docket Operations between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the economic evaluation, any comments received, and other information. The address for Docket Operations (phone: 800–647–5527) is Document Operations, 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: Michael Schwetz, Aviation Safety Engineer, Boston ACO Branch, Compliance and Airworthiness Division, FAA, 1200 District Avenue, Burlington, Massachusetts 01803; telephone (781) 238–7761; email michael.schwetz@faa.gov. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to remove AD 2017–07–02, Amendment 39–18840 (82 FR 15120, March 27, 2017) and add a new AD. AD 2017–07–02 applied to Sikorsky Model 269D and Model 269D Configuration A helicopters with a KAflex engine side drive shaft part number (P/N) SKCP2738–7 and KAflex pulley side drive shaft P/N SKCP2738–5 installed. AD 2017–07–02 required reducing the life limit of the drive shafts and performing several inspections of the drive shafts within 25 hours time-inservice (TIS). AD 2017–07–02 also specified replacing the drive shaft assemblies as an optional terminating action for the requirements of the AD. AD 2017–07–02 was prompted by four incidents involving failure of the engine side drive shaft. The actions required by AD 2017–07–02 were intended to prevent failure of the drive shaft, loss of rotor drive, and subsequent loss of control of the helicopter. The NPRM published in the Federal Register on September 22, 2017 (82 FR VerDate Sep<11>2014 16:12 Jan 26, 2018 Jkt 244001 44353) to provide the public an opportunity to comment on proposed requirements with longer intervals. The NPRM proposed to retain the requirements of AD 2017–07–02 and repeat some of the inspections every 100 hours TIS or 400 hours TIS. Repeating these inspections is necessary to detect and prevent the unsafe condition. Comments We gave the public the opportunity to participate in developing this AD, but we did not receive any comments on the NPRM. FAA’s Determination We have reviewed the relevant information and determined that an unsafe condition exists and is likely to exist or develop on other helicopters of these same type designs and that air safety and the public interest require adopting the AD requirements as proposed. Related Service Information We reviewed Appendix B to Sikorsky S–330 Model 269D Helicopter Basic Handbook of Maintenance Instructions No. CSP–D–2, dated February 1, 1993, and revised October 15, 2014; and Appendix B to Sikorsky S–333 Model 269D Config. ‘‘A’’ Helicopter Basic Handbook of Maintenance Instructions No. CSP–D–9, dated July 20, 2001, and revised October 15, 2014. This service information specifies repetitive inspection procedures, overhaul and retirement schedules, and weight and balance procedures. The Airworthiness Limitations section, which is included in this service information, contains the life limits for drive shaft assembly P/Ns SKCP2738–5 and SKCP2738–7. We also reviewed Sikorsky 269D Helicopter Alert Service Bulletin DB– 052, Basic Issue, dated January 16, 2014, for Sikorsky Model 269D and Model 269D Configuration A helicopters. This service information distributes the service life reduction information and implements a new 1,200-hour overhaul inspection for drive shaft assembly P/Ns SKCP2738–3, SKCP2738–5, and SKCP2738–7. Differences Between This AD and the Service Information The Sikorsky service information specifies a drive shaft assembly service life of 3,000 hours TIS with a 1,200 hour overhaul inspection for Model 269D Configuration A helicopters, while this AD specifies a service life of 1,200 hours TIS. The Sikorsky service information specifies different inspection procedures if there is spline engagement PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 interference or resistance while inspecting the drive shaft alignment. This AD specifies replacing both the engine side and pulley side drive shafts if there is any spline engagement interference or resistance. The Sikorsky service information specifies inspecting the working fastener condition without any specific succeeding action regarding the inspection. This AD specifies replacing both the engine side and pulley side drive shafts if there is any joint movement. The Sikorsky service information specifies returning the drive shaft assembly to Sikorsky if there is fretting dust or red metallic residue at a joint. This AD specifies replacing both the engine side and pulley side drive shafts if there is any fretting corrosion. Costs of Compliance We estimate that this AD will affect 18 helicopters of U.S. Registry. We estimate that operators may incur the following costs in order to comply with this AD. Removing the engine side and pulley side drive shafts that have reached the new life limit will take about 4 workhours for a cost of $340 per helicopter. Inspecting the lower pulley to engine alignment using the belt alignment tool will take about 0.5 work-hour for an estimated cost of $43 per helicopter and $774 for the U.S. fleet per inspection cycle. Adjusting the engine elevation alignment will take about 0.5 work-hour for an estimated cost of $43 per helicopter. Inspecting the drive shaft alignment by checking spline engagement will take about 1 work-hour for a cost of $85 per helicopter and $1,530 for the U.S. fleet per inspection cycle. Inspecting the drive shafts for damage will take about 1 work-hour for an estimated cost of $85 per helicopter and $1,530 for the U.S. fleet per inspection cycle. Inspecting the joints will take about 1 work-hour for an estimated cost of $85 per helicopter and $1,530 for the U.S. fleet per inspection cycle. Replacing the engine side and pulley side drive shafts, if required, will take about 8 work-hours and parts will cost about $20,000, for an estimated cost of $20,680 per helicopter. 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. E:\FR\FM\29JAR1.SGM 29JAR1 Federal Register / Vol. 83, No. 19 / Monday, January 29, 2018 / Rules and Regulations 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 have 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 DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979), (3) Will not affect intrastate aviation in Alaska to the extent that a regulatory distinction is required, 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) 2017–07–02, Amendment 39–18840 (82 FR 15120, March 27, 2017), and adding the following new AD: sradovich on DSK3GMQ082PROD with RULES ■ 2018–02–13 Sikorsky Aircraft Corporation (Sikorsky): Amendment 39–19166; Docket No. FAA–2017–0896; Product Identifier 2017–SW–034–AD. VerDate Sep<11>2014 16:12 Jan 26, 2018 Jkt 244001 (a) Applicability This AD applies to Sikorsky Model 269D and Model 269D Configuration A helicopters with a KAflex engine side drive shaft part number (P/N) SKCP2738–7 and KAflex pulley side drive shaft P/N SKCP2738–5 installed, certificated in any category. (b) Unsafe Condition This AD defines the unsafe condition as failure of a drive shaft. This condition could result in loss of rotor drive and subsequent loss of control of the helicopter. (c) Affected ADs This AD supersedes AD 2017–07–02, Amendment 39–18840 (82 FR 15120, March 27, 2017). (d) Effective Date This AD becomes effective March 5, 2018. (e) Compliance You are responsible for performing each action required by this AD within the specified compliance time unless it has already been accomplished prior to that time. (f) Required Actions (1) Before further flight: (i) For Model 269D helicopters, remove from service any KAflex engine side drive shaft P/N SKCP2738–7 and any KAflex pulley side drive shaft P/N SKCP2738–5 that has 6,000 or more hours time-in-service (TIS). Thereafter, remove from service any KAflex engine side drive shaft P/N SKCP2738–7 and any KAflex pulley side drive shaft P/N SKCP2738–5 before accumulating 6,000 hours TIS. (ii) For Model 269D Configuration A helicopters, remove from service any KAflex engine side drive shaft P/N SKCP2738–7 and any KAflex pulley side drive shaft P/N SKCP2738–5 that has 1,200 or more hours TIS. Thereafter, remove from service any KAflex engine side drive shaft P/N SKCP2738–7 and any KAflex pulley side drive shaft P/N SKCP2738–5 before accumulating 1,200 hours TIS. (iii) If interchanged between Model 269D and Model 269D Configuration A helicopters, remove from service any KAflex engine side drive shaft P/N SKCP2738–7 and any KAflex pulley side drive shaft P/N SKCP2738–5 that has 1,200 or more hours TIS. Thereafter, if interchanged between Model 269D and Model 269D Configuration A helicopters, remove from service any KAflex engine side drive shaft P/N SKCP2738–7 and any KAflex pulley side drive shaft P/N SKCP2738–5 before accumulating 1,200 hours TIS. (2) Within 25 hours TIS, and thereafter at intervals not to exceed 25 hours TIS, using a belt drive alignment tool 269T3303–003, inspect the lower pulley to engine alignment by engaging the tool on the drive shaft and inserting in the lower pulley bore. Rotate the tool 360° around the drive shaft and inspect for interference. If there is any interference with the rotation of the tool, before further flight, adjust the engine elevation alignment to eliminate the interference. (3) Within 25 hours TIS, and thereafter at intervals not to exceed 100 hours TIS: (i) Remove the drive shaft to adapter bolt and inspect the drive shaft alignment. Engage PO 00000 Frm 00007 Fmt 4700 Sfmt 4700 3943 and disengage the splines a minimum of 3 times by sliding the engine power output shaft in and out of the engine. Inspect the alignment at each 90° interval by rotating the lower pulley with the power shaft disengaged. Determine whether the adapter slides on and off the drive shaft splines without spline engagement interference or resistance along the entire length of movement. If there is any spline engagement interference or resistance, before further flight, replace both the engine side and pulley side drive shafts. (ii) Inspect each drive shaft for a crack, any corrosion or pitting, a nick, a dent, and a scratch. If there is a crack, any corrosion or pitting, a nick, a dent, or a scratch that exceeds allowable limits, before further flight, replace both the engine side and pulley side drive shafts. (4) Within 25 hours TIS, and thereafter at intervals not to exceed 400 hours TIS, remove the engine side drive shaft and pulley side drive shaft and perform the following: (i) Inspect each flex frame (frame) bolted joint (joint) for movement by hand. If there is any movement, before further flight, replace both the engine side and pulley side drive shafts. (ii) Visually inspect each joint for fretting corrosion (which might be indicated by metallic particles) and each frame and mount bolt torque stripe for movement. If there is any fretting corrosion or torque stripe movement, before further flight, replace both the engine side and pulley side drive shafts. (iii) Using a 10x or higher power magnifying glass, visually inspect each joint for fretting and for a crack around the bolt head and washer side, and around the nut and washer side. Also inspect both sides of each frame for a crack on the inside and outside corner radii and radii edge (four). If there is any fretting, a crack at any point over the full circumference (360°) of the bolt head and washer side or the nut and washer side, or a crack in any of the corner radii edges, before further flight, replace both the engine side and pulley side drive shafts. (5) As an optional terminating action to the repetitive inspections in this AD, you may install KAflex engine side drive shaft P/N SKCP2738–9 and KAflex pulley side drive shaft P/N SKCP2738–101. (g) Alternative Methods of Compliance (AMOCs) (1) The Manager, Boston ACO Branch, FAA, may approve AMOCs for this AD. Send your proposal to: Michael Schwetz, Aviation Safety Engineer, Boston ACO Branch, Compliance and Airworthiness Division, FAA, 1200 District Avenue, Burlington, Massachusetts 01803; telephone (781) 238– 7761; email michael.schwetz@faa.gov. (2) For operations conducted under a 14 CFR part 119 operating certificate or under 14 CFR part 91, subpart K, we suggest that you notify your principal inspector, or lacking a principal inspector, the manager of the local flight standards district office or certificate holding district office, before operating any aircraft complying with this AD through an AMOC. E:\FR\FM\29JAR1.SGM 29JAR1 3944 Federal Register / Vol. 83, No. 19 / Monday, January 29, 2018 / Rules and Regulations (h) Additional Information Appendix B of Sikorsky S–330 Model 269D Helicopter Basic Handbook of Maintenance Instructions, No. CSP–D–2, dated February 1, 1993, and revised October 15, 2014; Appendix B of Sikorsky S–330 Model 269D Config. ‘‘A’’ Helicopter Basic Handbook of Maintenance Instructions, No. CSP–D–9, dated July 20, 2001, and revised October 15, 2014; and Sikorsky 269D Helicopter Alert Service Bulletin DB–052, Basic Issue, dated January 16, 2014, which are not incorporated by reference, contain additional information about the subject of this AD. For service information identified in this AD, contact Sikorsky Aircraft Corporation, Customer Service Engineering, 124 Quarry Road, Trumbull, CT 06611; telephone 1–800– Winged–S or 203–416–4299; email wcs_cust_ service_eng.gr-sik@lmco.com. You may review a copy of the service information at the FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy, Room 6N–321, Fort Worth, TX 76177. (i) Subject Joint Aircraft Service Component (JASC) Code: 6310, Engine/Transmission Coupling. Issued in Fort Worth, Texas, on January 17, 2018. Lance T. Gant, Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2018–01572 Filed 1–26–18; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF JUSTICE 28 CFR Part 85 [Docket No. OAG 159; AG Order No. 4093– 2018] Civil Monetary Penalties Inflation Adjustment I. Statutory Process for Implementing Annual Inflation Adjustments Section 701 of the Bipartisan Budget Act of 2015, Public Law 114–74 (Nov. 2, 2015) (‘‘BBA’’), 28 U.S.C. 2461 note, substantially revised the prior provisions of the Federal Civil Monetary Penalties Inflation Adjustment Act of 1990, Public Law 101–410 (the ‘‘Inflation Adjustment Act’’), and substituted a different statutory formula for calculating inflation adjustments on an annual basis. In accordance with the provisions of the BBA, on June 30, 2016 (81 FR 42491), the Department of Justice published an interim rule to adjust for inflation the civil monetary penalties assessed or enforced by components of the Department after August 1, 2016, with respect to violations occurring after November 2, 2015, the date of enactment of the BBA. Readers may refer to the Supplementary Information (also known as the preamble) of the Department’s 2016 interim rule for additional background information regarding the statutory authority for adjustments of civil monetary penalty amounts to take account of inflation and the Department’s past implementation of inflation adjustments. The BBA also provides for agencies to adjust their civil penalties on January 15 of each year to account for inflation during the preceding year, rounded to the nearest dollar. Accordingly, on February 3, 2017 (82 FR 9131), the Department published a final rule to adjust for inflation the civil monetary penalties assessed or enforced by components of the Department after that date, with respect to violations occurring after November 2, 2015. AGENCY: II. Inflation Adjustments Made by This Rule The Department of Justice is adjusting for inflation the civil monetary penalties assessed or enforced by components of the Department, in accordance with the provisions of the Bipartisan Budget Act of 2015, for penalties assessed after January 29, 2018, with respect to violations occurring after November 2, 2015. DATES: This rule is effective January 29, 2018. FOR FURTHER INFORMATION CONTACT: Robert Hinchman, Senior Counsel, Office of Legal Policy, U.S. Department of Justice, Room 4252 RFK Building, 950 Pennsylvania Avenue NW, Washington, DC 20530, telephone (202) 514–8059 (not a toll-free number). SUPPLEMENTARY INFORMATION: As required, the Department is publishing this final rule to adjust the civil penalties that were most recently adjusted as of February 3, 2017. Under the statutory formula, the adjustments made by this rule are based on the Bureau of Labor Statistics’ Consumer Price Index for October 2017. The OMB Memorandum for the Heads of Executive Departments and Agencies M–18–03 (Dec. 15, 2017), https:// www.whitehouse.gov/wp-content/ uploads/2017/11/M-18-03.pdf (last visited Jan. 1, 2018), instructs that the applicable inflation factor for this adjustment is 1.02041. Accordingly, this rule adjusts the civil penalty amounts in 28 CFR 85.5 by applying this inflation factor mechanically to each of the civil penalty amounts listed (rounded to the nearest dollar). Department of Justice. ACTION: Final rule. sradovich on DSK3GMQ082PROD with RULES SUMMARY: VerDate Sep<11>2014 16:12 Jan 26, 2018 Jkt 244001 PO 00000 Frm 00008 Fmt 4700 Sfmt 4700 Example: • In 2016, the Program Fraud Civil Remedies Act penalty was increased to $10,781 in accordance with the adjustment requirements of the BBA. • For 2017, where the applicable inflation factor was 1.01636, the existing penalty of $10,781 was multiplied by 1.01636 and revised to $10,957 (rounded to the nearest dollar). • For this final rule in 2018, where the applicable inflation factor is 1.02041, the existing penalty of $10,957 is multiplied by 1.02041 and revised to $11,181 (rounded to the nearest dollar). This rule adjusts for inflation civil monetary penalties within the jurisdiction of the Department of Justice for purposes of the Inflation Adjustment Act, as amended. Other agencies are responsible for the inflation adjustments of certain other civil monetary penalties that the Department’s litigating components bring suit to collect. The reader should consult the regulations of those other agencies for inflation adjustments to those penalties. III. Effective Date of Adjusted Civil Penalty Amounts Under this rule, the adjusted civil penalty amounts are applicable only to civil penalties assessed after January 29, 2018, with respect to violations occurring after November 2, 2015, the date of enactment of the BBA. The penalty amounts set forth in the existing table in 28 CFR 85.5 are applicable to civil penalties assessed after August 1, 2016, and on or before the effective date of this rule, with respect to violations occurring after November 2, 2015. Civil penalties for violations occurring on or before November 2, 2015, and assessments made on or before August 1, 2016, will continue to be subject to the civil monetary penalty amounts set forth in the Department’s regulations in 28 CFR parts 20, 22, 36, 68, 71, 76, and 85 as such regulations were in effect prior to August 1, 2016 (or as set forth by statute if the amount had not yet been adjusted by regulation prior to August 1, 2016). Statutory and Regulatory Analyses Administrative Procedure Act The BBA provides that, for each annual adjustment made after the initial adjustments of civil penalties in 2016, the head of an agency shall adjust the civil monetary penalties each year notwithstanding 5 U.S.C. 553. Accordingly, this rule is being issued as a final rule without prior notice and public comment, and without a delayed effective date. E:\FR\FM\29JAR1.SGM 29JAR1

Agencies

[Federal Register Volume 83, Number 19 (Monday, January 29, 2018)]
[Rules and Regulations]
[Pages 3941-3944]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-01572]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2017-0896; Product Identifier 2017-SW-034-AD; Amendment 
39-19166; AD 2018-02-13]
RIN 2120-AA64


Airworthiness Directives; Sikorsky Aircraft Corporation 
Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: We are superseding Airworthiness Directive (AD) 2017-07-02 for 
Sikorsky Aircraft Corporation (Sikorsky) Model 269D and Model 269D 
Configuration A helicopters. AD 2017-07-02 required reducing the life 
limit of and inspecting certain drive shafts. This new AD retains the 
requirements of AD 2017-07-02 and requires repeating the inspections. 
The actions of this AD are intended to detect and prevent an unsafe 
condition on these products.

DATES: This AD is effective March 5, 2018.

[[Page 3942]]


ADDRESSES: For service information identified in this final rule, 
contact Sikorsky Aircraft Corporation, Customer Service Engineering, 
124 Quarry Road, Trumbull, CT 06611; telephone 1-800-Winged-S or 203-
416-4299; email [email protected]. You may view this 
referenced service information at the FAA, Office of the Regional 
Counsel, Southwest Region, 10101 Hillwood Pkwy, Room 6N-321, Fort 
Worth, TX 76177.

Examining the AD Docket

    You may examine the AD docket on the internet at https://www.regulations.gov in Docket No. FAA-2017-0896; or in person at Docket 
Operations between 9 a.m. and 5 p.m., Monday through Friday, except 
Federal holidays. The AD docket contains this AD, the economic 
evaluation, any comments received, and other information. The address 
for Docket Operations (phone: 800-647-5527) is Document Operations, 
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: Michael Schwetz, Aviation Safety 
Engineer, Boston ACO Branch, Compliance and Airworthiness Division, 
FAA, 1200 District Avenue, Burlington, Massachusetts 01803; telephone 
(781) 238-7761; email [email protected].

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to remove AD 2017-07-02, Amendment 39-18840 (82 FR 15120, March 
27, 2017) and add a new AD. AD 2017-07-02 applied to Sikorsky Model 
269D and Model 269D Configuration A helicopters with a KAflex engine 
side drive shaft part number (P/N) SKCP2738-7 and KAflex pulley side 
drive shaft P/N SKCP2738-5 installed. AD 2017-07-02 required reducing 
the life limit of the drive shafts and performing several inspections 
of the drive shafts within 25 hours time-in-service (TIS). AD 2017-07-
02 also specified replacing the drive shaft assemblies as an optional 
terminating action for the requirements of the AD. AD 2017-07-02 was 
prompted by four incidents involving failure of the engine side drive 
shaft. The actions required by AD 2017-07-02 were intended to prevent 
failure of the drive shaft, loss of rotor drive, and subsequent loss of 
control of the helicopter.
    The NPRM published in the Federal Register on September 22, 2017 
(82 FR 44353) to provide the public an opportunity to comment on 
proposed requirements with longer intervals. The NPRM proposed to 
retain the requirements of AD 2017-07-02 and repeat some of the 
inspections every 100 hours TIS or 400 hours TIS. Repeating these 
inspections is necessary to detect and prevent the unsafe condition.

Comments

    We gave the public the opportunity to participate in developing 
this AD, but we did not receive any comments on the NPRM.

FAA's Determination

    We have reviewed the relevant information and determined that an 
unsafe condition exists and is likely to exist or develop on other 
helicopters of these same type designs and that air safety and the 
public interest require adopting the AD requirements as proposed.

Related Service Information

    We reviewed Appendix B to Sikorsky S-330 Model 269D Helicopter 
Basic Handbook of Maintenance Instructions No. CSP-D-2, dated February 
1, 1993, and revised October 15, 2014; and Appendix B to Sikorsky S-333 
Model 269D Config. ``A'' Helicopter Basic Handbook of Maintenance 
Instructions No. CSP-D-9, dated July 20, 2001, and revised October 15, 
2014. This service information specifies repetitive inspection 
procedures, overhaul and retirement schedules, and weight and balance 
procedures. The Airworthiness Limitations section, which is included in 
this service information, contains the life limits for drive shaft 
assembly P/Ns SKCP2738-5 and SKCP2738-7.
    We also reviewed Sikorsky 269D Helicopter Alert Service Bulletin 
DB-052, Basic Issue, dated January 16, 2014, for Sikorsky Model 269D 
and Model 269D Configuration A helicopters. This service information 
distributes the service life reduction information and implements a new 
1,200-hour overhaul inspection for drive shaft assembly P/Ns SKCP2738-
3, SKCP2738-5, and SKCP2738-7.

Differences Between This AD and the Service Information

    The Sikorsky service information specifies a drive shaft assembly 
service life of 3,000 hours TIS with a 1,200 hour overhaul inspection 
for Model 269D Configuration A helicopters, while this AD specifies a 
service life of 1,200 hours TIS.
    The Sikorsky service information specifies different inspection 
procedures if there is spline engagement interference or resistance 
while inspecting the drive shaft alignment. This AD specifies replacing 
both the engine side and pulley side drive shafts if there is any 
spline engagement interference or resistance.
    The Sikorsky service information specifies inspecting the working 
fastener condition without any specific succeeding action regarding the 
inspection. This AD specifies replacing both the engine side and pulley 
side drive shafts if there is any joint movement.
    The Sikorsky service information specifies returning the drive 
shaft assembly to Sikorsky if there is fretting dust or red metallic 
residue at a joint. This AD specifies replacing both the engine side 
and pulley side drive shafts if there is any fretting corrosion.

Costs of Compliance

    We estimate that this AD will affect 18 helicopters of U.S. 
Registry. We estimate that operators may incur the following costs in 
order to comply with this AD.
    Removing the engine side and pulley side drive shafts that have 
reached the new life limit will take about 4 work-hours for a cost of 
$340 per helicopter. Inspecting the lower pulley to engine alignment 
using the belt alignment tool will take about 0.5 work-hour for an 
estimated cost of $43 per helicopter and $774 for the U.S. fleet per 
inspection cycle. Adjusting the engine elevation alignment will take 
about 0.5 work-hour for an estimated cost of $43 per helicopter. 
Inspecting the drive shaft alignment by checking spline engagement will 
take about 1 work-hour for a cost of $85 per helicopter and $1,530 for 
the U.S. fleet per inspection cycle. Inspecting the drive shafts for 
damage will take about 1 work-hour for an estimated cost of $85 per 
helicopter and $1,530 for the U.S. fleet per inspection cycle. 
Inspecting the joints will take about 1 work-hour for an estimated cost 
of $85 per helicopter and $1,530 for the U.S. fleet per inspection 
cycle. Replacing the engine side and pulley side drive shafts, if 
required, will take about 8 work-hours and parts will cost about 
$20,000, for an estimated cost of $20,680 per helicopter.

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.

[[Page 3943]]

    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 have 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 DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979),
    (3) Will not affect intrastate aviation in Alaska to the extent 
that a regulatory distinction is required, 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) 
2017-07-02, Amendment 39-18840 (82 FR 15120, March 27, 2017), and 
adding the following new AD:

2018-02-13 Sikorsky Aircraft Corporation (Sikorsky): Amendment 39-
19166; Docket No. FAA-2017-0896; Product Identifier 2017-SW-034-AD.

(a) Applicability

    This AD applies to Sikorsky Model 269D and Model 269D 
Configuration A helicopters with a KAflex engine side drive shaft 
part number (P/N) SKCP2738-7 and KAflex pulley side drive shaft P/N 
SKCP2738-5 installed, certificated in any category.

(b) Unsafe Condition

    This AD defines the unsafe condition as failure of a drive 
shaft. This condition could result in loss of rotor drive and 
subsequent loss of control of the helicopter.

(c) Affected ADs

    This AD supersedes AD 2017-07-02, Amendment 39-18840 (82 FR 
15120, March 27, 2017).

(d) Effective Date

    This AD becomes effective March 5, 2018.

(e) Compliance

    You are responsible for performing each action required by this 
AD within the specified compliance time unless it has already been 
accomplished prior to that time.

(f) Required Actions

    (1) Before further flight:
    (i) For Model 269D helicopters, remove from service any KAflex 
engine side drive shaft P/N SKCP2738-7 and any KAflex pulley side 
drive shaft P/N SKCP2738-5 that has 6,000 or more hours time-in-
service (TIS). Thereafter, remove from service any KAflex engine 
side drive shaft P/N SKCP2738-7 and any KAflex pulley side drive 
shaft P/N SKCP2738-5 before accumulating 6,000 hours TIS.
    (ii) For Model 269D Configuration A helicopters, remove from 
service any KAflex engine side drive shaft P/N SKCP2738-7 and any 
KAflex pulley side drive shaft P/N SKCP2738-5 that has 1,200 or more 
hours TIS. Thereafter, remove from service any KAflex engine side 
drive shaft P/N SKCP2738-7 and any KAflex pulley side drive shaft P/
N SKCP2738-5 before accumulating 1,200 hours TIS.
    (iii) If interchanged between Model 269D and Model 269D 
Configuration A helicopters, remove from service any KAflex engine 
side drive shaft P/N SKCP2738-7 and any KAflex pulley side drive 
shaft P/N SKCP2738-5 that has 1,200 or more hours TIS. Thereafter, 
if interchanged between Model 269D and Model 269D Configuration A 
helicopters, remove from service any KAflex engine side drive shaft 
P/N SKCP2738-7 and any KAflex pulley side drive shaft P/N SKCP2738-5 
before accumulating 1,200 hours TIS.
    (2) Within 25 hours TIS, and thereafter at intervals not to 
exceed 25 hours TIS, using a belt drive alignment tool 269T3303-003, 
inspect the lower pulley to engine alignment by engaging the tool on 
the drive shaft and inserting in the lower pulley bore. Rotate the 
tool 360[deg] around the drive shaft and inspect for interference. 
If there is any interference with the rotation of the tool, before 
further flight, adjust the engine elevation alignment to eliminate 
the interference.
    (3) Within 25 hours TIS, and thereafter at intervals not to 
exceed 100 hours TIS:
    (i) Remove the drive shaft to adapter bolt and inspect the drive 
shaft alignment. Engage and disengage the splines a minimum of 3 
times by sliding the engine power output shaft in and out of the 
engine. Inspect the alignment at each 90[deg] interval by rotating 
the lower pulley with the power shaft disengaged. Determine whether 
the adapter slides on and off the drive shaft splines without spline 
engagement interference or resistance along the entire length of 
movement. If there is any spline engagement interference or 
resistance, before further flight, replace both the engine side and 
pulley side drive shafts.
    (ii) Inspect each drive shaft for a crack, any corrosion or 
pitting, a nick, a dent, and a scratch. If there is a crack, any 
corrosion or pitting, a nick, a dent, or a scratch that exceeds 
allowable limits, before further flight, replace both the engine 
side and pulley side drive shafts.
    (4) Within 25 hours TIS, and thereafter at intervals not to 
exceed 400 hours TIS, remove the engine side drive shaft and pulley 
side drive shaft and perform the following:
    (i) Inspect each flex frame (frame) bolted joint (joint) for 
movement by hand. If there is any movement, before further flight, 
replace both the engine side and pulley side drive shafts.
    (ii) Visually inspect each joint for fretting corrosion (which 
might be indicated by metallic particles) and each frame and mount 
bolt torque stripe for movement. If there is any fretting corrosion 
or torque stripe movement, before further flight, replace both the 
engine side and pulley side drive shafts.
    (iii) Using a 10x or higher power magnifying glass, visually 
inspect each joint for fretting and for a crack around the bolt head 
and washer side, and around the nut and washer side. Also inspect 
both sides of each frame for a crack on the inside and outside 
corner radii and radii edge (four). If there is any fretting, a 
crack at any point over the full circumference (360[deg]) of the 
bolt head and washer side or the nut and washer side, or a crack in 
any of the corner radii edges, before further flight, replace both 
the engine side and pulley side drive shafts.
    (5) As an optional terminating action to the repetitive 
inspections in this AD, you may install KAflex engine side drive 
shaft P/N SKCP2738-9 and KAflex pulley side drive shaft P/N 
SKCP2738-101.

(g) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Boston ACO Branch, FAA, may approve AMOCs for 
this AD. Send your proposal to: Michael Schwetz, Aviation Safety 
Engineer, Boston ACO Branch, Compliance and Airworthiness Division, 
FAA, 1200 District Avenue, Burlington, Massachusetts 01803; 
telephone (781) 238-7761; email [email protected].
    (2) For operations conducted under a 14 CFR part 119 operating 
certificate or under 14 CFR part 91, subpart K, we suggest that you 
notify your principal inspector, or lacking a principal inspector, 
the manager of the local flight standards district office or 
certificate holding district office, before operating any aircraft 
complying with this AD through an AMOC.

[[Page 3944]]

(h) Additional Information

    Appendix B of Sikorsky S-330 Model 269D Helicopter Basic 
Handbook of Maintenance Instructions, No. CSP-D-2, dated February 1, 
1993, and revised October 15, 2014; Appendix B of Sikorsky S-330 
Model 269D Config. ``A'' Helicopter Basic Handbook of Maintenance 
Instructions, No. CSP-D-9, dated July 20, 2001, and revised October 
15, 2014; and Sikorsky 269D Helicopter Alert Service Bulletin DB-
052, Basic Issue, dated January 16, 2014, which are not incorporated 
by reference, contain additional information about the subject of 
this AD. For service information identified in this AD, contact 
Sikorsky Aircraft Corporation, Customer Service Engineering, 124 
Quarry Road, Trumbull, CT 06611; telephone 1-800-Winged-S or 203-
416-4299; email [email protected]. You may review 
a copy of the service information at the FAA, Office of the Regional 
Counsel, Southwest Region, 10101 Hillwood Pkwy, Room 6N-321, Fort 
Worth, TX 76177.

(i) Subject

    Joint Aircraft Service Component (JASC) Code: 6310, Engine/
Transmission Coupling.


    Issued in Fort Worth, Texas, on January 17, 2018.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification 
Service.
[FR Doc. 2018-01572 Filed 1-26-18; 8:45 am]
 BILLING CODE 4910-13-P

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