83 FR 3941 - Airworthiness Directives; Sikorsky Aircraft Corporation Helicopters
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 83, Issue 19 (January 29, 2018)
Federal Aviation Administration
Federal Register Volume 83, Issue 19 (January 29, 2018)
| Page Range | 3941-3944 | |
| FR Document | 2018-01572 |
[Federal Register Volume 83, Number 19 (Monday, January 29, 2018)] [Rules and Regulations] [Pages 3941-3944] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2018-01572] ----------------------------------------------------------------------- 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. ----------------------------------------------------------------------- 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 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. Examining the AD Docket You may examine the AD docket on the internet at http://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-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 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. [[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 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
![Federal Register / Vol. 83, No. 19 / Monday, January 29, 2018 / Rules and Regulations 3941
1. Is not a ‘‘significant regulatory (g) Inspection and Replacement of Bearings (k) Material Incorporated by Reference
action’’ under Executive Order 12866; Within 6,000 flight hours or 36 months (1) The Director of the Federal Register
2. Is not a ‘‘significant rule’’ under the after the effective date of this AD, whichever approved the incorporation by reference
DOT Regulatory Policies and Procedures occurs earlier, do a detailed visual inspection (IBR) of the service information listed in this
of all translating fuselage door lift and latch paragraph under 5 U.S.C. 552(a) and 1 CFR
(44 FR 11034, February 26, 1979); part 51.
shaft roller bearings for signs of corrosion,
3. Will not affect intrastate aviation in damaged seals, and loss of lubricant; replace (2) You must use this service information
Alaska; and any corroded bearings; and apply corrosion- as applicable to do the actions required by
4. Will not have a significant inhibiting compound (CIC); in accordance this AD, unless this AD specifies otherwise.
with paragraph 3.B., ‘‘Procedure,’’ of the (i) Bombardier Service Bulletin 84–52–88,
economic impact, positive or negative, dated April 14, 2016.
Accomplishment Instructions of Bombardier
on a substantial number of small entities Service Bulletin 84–52–88, dated April 14, (ii) Reserved.
under the criteria of the Regulatory 2016. (3) For service information identified in
Flexibility Act. this AD, contact Bombardier, Inc., Q-Series
(h) Credit for Previous Actions Technical Help Desk, 123 Garratt Boulevard,
List of Subjects in 14 CFR Part 39 This paragraph provides credit for actions Toronto, Ontario M3K 1Y5, Canada;
Air transportation, Aircraft, Aviation required by paragraph (g) of this AD, if those telephone 416–375–4000; fax 416–375–4539;
actions were performed before the effective email thd.qseries@aero.bombardier.com;
safety, Incorporation by reference, internet http://www.bombardier.com.
date of this AD using Bombardier Service
Safety. Bulletin 84–52–85, dated September 23, (4) You may view this service information
Adoption of the Amendment 2015; or Bombardier Service Bulletin 84–52– at the FAA, Transport Standards Branch,
85, Revision A, dated January 22, 2016. 1601 Lind Avenue SW, Renton, WA. For
Accordingly, under the authority information on the availability of this
(i) Other FAA AD Provisions material at the FAA, call 425–227–1221.
delegated to me by the Administrator,
The following provisions also apply to this (5) You may view this service information
the FAA amends 14 CFR part 39 as
AD: that is incorporated by reference at the
follows: National Archives and Records
(1) Alternative Methods of Compliance
(AMOCs): The Manager, New York ACO Administration (NARA). For information on
PART 39—AIRWORTHINESS the availability of this material at NARA, call
Branch, FAA, has the authority to approve
DIRECTIVES AMOCs for this AD, if requested using the 202–741–6030, or go to: http://
procedures found in 14 CFR 39.19. In www.archives.gov/federal-register/cfr/ibr-
■ 1. The authority citation for part 39 accordance with 14 CFR 39.19, send your locations.html.
continues to read as follows: request to your principal inspector or local Issued in Renton, Washington, on January
Authority: 49 U.S.C. 106(g), 40113, 44701. Flight Standards District Office, as 17, 2018.
appropriate. If sending information directly Michael Kaszycki,
§ 39.13 [Amended] to the manager of the certification office,
send it to ATTN: Program Manager, Acting Director, System Oversight Division,
■ 2. The FAA amends § 39.13 by adding Aircraft Certification Service.
Continuing Operational Safety, FAA, New
the following new airworthiness York ACO Branch, 1600 Stewart Avenue, [FR Doc. 2018–01317 Filed 1–26–18; 8:45 am]
directive (AD): Suite 410, Westbury, NY 11590; telephone BILLING CODE 4910–13–P
516–228–7300; fax 516–794–5531. Before
2018–02–16 Bombardier, Inc.: Amendment using any approved AMOC, notify your
39–19169; Docket No. FAA–2017–0621; appropriate principal inspector, or lacking a
Product Identifier 2017–NM–049–AD.
DEPARTMENT OF TRANSPORTATION
principal inspector, the manager of the local
(a) Effective Date flight standards district office/certificate Federal Aviation Administration
holding district office.
This AD is effective March 5, 2018.
(2) Contacting the Manufacturer: For any 14 CFR Part 39
(b) Affected ADs requirement in this AD to obtain corrective
actions from a manufacturer, the action must [Docket No. FAA–2017–0896; Product
None.
be accomplished using a method approved Identifier 2017–SW–034–AD; Amendment
(c) Applicability by the Manager, New York ACO Branch, 39–19166; AD 2018–02–13]
This AD applies to Bombardier, Inc., FAA; or Transport Canada Civil Aviation RIN 2120–AA64
Model DHC–8–400, –401, and –402 (TCCA); or Bombardier, Inc.’s TCCA Design
airplanes, certificated in any category, serial Approval Organization (DAO). If approved by Airworthiness Directives; Sikorsky
numbers 4001 and 4003 through 4488 the DAO, the approval must include the
DAO-authorized signature.
Aircraft Corporation Helicopters
inclusive, except those incorporating
Bombardier ModSum IS4Q5200050. (j) Related Information AGENCY: Federal Aviation
(d) Subject
Administration (FAA), DOT.
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) Canadian ACTION: Final rule.
Air Transport Association (ATA) of
America Code 52, Doors. Airworthiness Directive CF–2016–18, dated
SUMMARY: We are superseding
June 6, 2016, for related information. This
(e) Reason MCAI may be found in the AD docket on the Airworthiness Directive (AD) 2017–07–
This AD was prompted by reports of internet at http://www.regulations.gov by 02 for Sikorsky Aircraft Corporation
interrupted operation of translating fuselage searching for and locating Docket No. FAA– (Sikorsky) Model 269D and Model 269D
doors caused by corrosion in the door lift and 2017–0621. Configuration A helicopters. AD 2017–
latch shaft roller bearings. We are issuing this (2) For more information about this AD, 07–02 required reducing the life limit of
AD to detect and correct bearing corrosion contact Aziz Ahmed, Aerospace Engineer, and inspecting certain drive shafts. This
sradovich on DSK3GMQ082PROD with RULES
and prevent door operation interruptions that Airframe and Mechanical Systems Section, new AD retains the requirements of AD
could inhibit safe evacuation of the airplane FAA, New York ACO Branch, 1600 Stewart 2017–07–02 and requires repeating the
in an emergency. Avenue, Suite 410, Westbury, NY 11590; inspections. The actions of this AD are
telephone 516–228–7329; fax 516–794–5531.
(f) Compliance (3) Service information identified in this
intended to detect and prevent an
Comply with this AD within the AD that is not incorporated by reference is unsafe condition on these products.
compliance times specified, unless already available at the addresses specified in DATES: This AD is effective March 5,
done. paragraphs (k)(3) and (k)(4) of this AD. 2018.
VerDate Sep<11>2014 16:12 Jan 26, 2018 Jkt 244001 PO 00000 Frm 00005 Fmt 4700 Sfmt 4700 E:\FR\FM\29JAR1.SGM 29JAR1](https://thefederalregister.org/doc/83_FR_3960/page/1.svg)
![Federal Register / Vol. 83, No. 19 / Monday, January 29, 2018 / Rules and Regulations 3943
We are issuing this rulemaking under (a) Applicability and disengage the splines a minimum of 3
the authority described in Subtitle VII, This AD applies to Sikorsky Model 269D times by sliding the engine power output
Part A, Subpart III, Section 44701, and Model 269D Configuration A helicopters shaft in and out of the engine. Inspect the
‘‘General requirements.’’ Under that with a KAflex engine side drive shaft part alignment at each 90° interval by rotating the
section, Congress charges the FAA with number (P/N) SKCP2738–7 and KAflex lower pulley with the power shaft
pulley side drive shaft P/N SKCP2738–5 disengaged. Determine whether the adapter
promoting safe flight of civil aircraft in
installed, certificated in any category. slides on and off the drive shaft splines
air commerce by prescribing regulations
without spline engagement interference or
for practices, methods, and procedures (b) Unsafe Condition
resistance along the entire length of
the Administrator finds necessary for This AD defines the unsafe condition as movement. If there is any spline engagement
safety in air commerce. This regulation failure of a drive shaft. This condition could interference or resistance, before further
is within the scope of that authority result in loss of rotor drive and subsequent flight, replace both the engine side and
because it addresses an unsafe condition loss of control of the helicopter. pulley side drive shafts.
that is likely to exist or develop on (c) Affected ADs (ii) Inspect each drive shaft for a crack, any
products identified in this rulemaking This AD supersedes AD 2017–07–02, corrosion or pitting, a nick, a dent, and a
action. Amendment 39–18840 (82 FR 15120, March scratch. If there is a crack, any corrosion or
27, 2017). pitting, a nick, a dent, or a scratch that
Regulatory Findings exceeds allowable limits, before further
We have determined that this AD will (d) Effective Date flight, replace both the engine side and
not have federalism implications under This AD becomes effective March 5, 2018. pulley side drive shafts.
Executive Order 13132. This AD will (4) Within 25 hours TIS, and thereafter at
(e) Compliance
not have a substantial direct effect on intervals not to exceed 400 hours TIS,
You are responsible for performing each remove the engine side drive shaft and pulley
the States, on the relationship between action required by this AD within the
the national government and the States, side drive shaft and perform the following:
specified compliance time unless it has (i) Inspect each flex frame (frame) bolted
or on the distribution of power and already been accomplished prior to that time. joint (joint) for movement by hand. If there
responsibilities among the various
(f) Required Actions is any movement, before further flight,
levels of government. replace both the engine side and pulley side
For the reasons discussed above, I (1) Before further flight:
(i) For Model 269D helicopters, remove drive shafts.
certify that this AD: (ii) Visually inspect each joint for fretting
(1) Is not a ‘‘significant regulatory from service any KAflex engine side drive
shaft P/N SKCP2738–7 and any KAflex corrosion (which might be indicated by
action’’ under Executive Order 12866, metallic particles) and each frame and mount
(2) Is not a ‘‘significant rule’’ under pulley side drive shaft P/N SKCP2738–5 that
has 6,000 or more hours time-in-service bolt torque stripe for movement. If there is
DOT Regulatory Policies and Procedures (TIS). Thereafter, remove from service any any fretting corrosion or torque stripe
(44 FR 11034, February 26, 1979), KAflex engine side drive shaft P/N movement, before further flight, replace both
(3) Will not affect intrastate aviation SKCP2738–7 and any KAflex pulley side the engine side and pulley side drive shafts.
in Alaska to the extent that a regulatory drive shaft P/N SKCP2738–5 before (iii) Using a 10x or higher power
distinction is required, and accumulating 6,000 hours TIS. magnifying glass, visually inspect each joint
(4) Will not have a significant (ii) For Model 269D Configuration A for fretting and for a crack around the bolt
economic impact, positive or negative, helicopters, remove from service any KAflex head and washer side, and around the nut
on a substantial number of small entities engine side drive shaft P/N SKCP2738–7 and and washer side. Also inspect both sides of
under the criteria of the Regulatory any KAflex pulley side drive shaft P/N each frame for a crack on the inside and
Flexibility Act. SKCP2738–5 that has 1,200 or more hours outside corner radii and radii edge (four). If
TIS. Thereafter, remove from service any there is any fretting, a crack at any point over
List of Subjects in 14 CFR Part 39 KAflex engine side drive shaft P/N the full circumference (360°) of the bolt head
SKCP2738–7 and any KAflex pulley side and washer side or the nut and washer side,
Air transportation, Aircraft, Aviation drive shaft P/N SKCP2738–5 before
safety, Incorporation by reference, or a crack in any of the corner radii edges,
accumulating 1,200 hours TIS. before further flight, replace both the engine
Safety. (iii) If interchanged between Model 269D side and pulley side drive shafts.
Adoption of the Amendment and Model 269D Configuration A helicopters, (5) As an optional terminating action to the
remove from service any KAflex engine side repetitive inspections in this AD, you may
Accordingly, under the authority drive shaft P/N SKCP2738–7 and any KAflex install KAflex engine side drive shaft P/N
delegated to me by the Administrator, pulley side drive shaft P/N SKCP2738–5 that
SKCP2738–9 and KAflex pulley side drive
the FAA amends 14 CFR part 39 as has 1,200 or more hours TIS. Thereafter, if
shaft P/N SKCP2738–101.
follows: interchanged between Model 269D and
Model 269D Configuration A helicopters, (g) Alternative Methods of Compliance
PART 39—AIRWORTHINESS remove from service any KAflex engine side (AMOCs)
DIRECTIVES drive shaft P/N SKCP2738–7 and any KAflex
(1) The Manager, Boston ACO Branch,
pulley side drive shaft P/N SKCP2738–5
FAA, may approve AMOCs for this AD. Send
■ 1. The authority citation for part 39 before accumulating 1,200 hours TIS.
your proposal to: Michael Schwetz, Aviation
continues to read as follows: (2) Within 25 hours TIS, and thereafter at
intervals not to exceed 25 hours TIS, using Safety Engineer, Boston ACO Branch,
Authority: 49 U.S.C. 106(g), 40113, 44701. a belt drive alignment tool 269T3303–003, Compliance and Airworthiness Division,
inspect the lower pulley to engine alignment FAA, 1200 District Avenue, Burlington,
§ 39.13 [Amended] by engaging the tool on the drive shaft and Massachusetts 01803; telephone (781) 238–
■ 2. The FAA amends § 39.13 by inserting in the lower pulley bore. Rotate the 7761; email michael.schwetz@faa.gov.
tool 360° around the drive shaft and inspect (2) For operations conducted under a 14
removing Airworthiness Directive (AD)
sradovich on DSK3GMQ082PROD with RULES
for interference. If there is any interference CFR part 119 operating certificate or under
2017–07–02, Amendment 39–18840 (82 14 CFR part 91, subpart K, we suggest that
with the rotation of the tool, before further
FR 15120, March 27, 2017), and adding you notify your principal inspector, or
flight, adjust the engine elevation alignment
the following new AD: to eliminate the interference. lacking a principal inspector, the manager of
2018–02–13 Sikorsky Aircraft Corporation (3) Within 25 hours TIS, and thereafter at the local flight standards district office or
(Sikorsky): Amendment 39–19166; intervals not to exceed 100 hours TIS: certificate holding district office, before
Docket No. FAA–2017–0896; Product (i) Remove the drive shaft to adapter bolt operating any aircraft complying with this
Identifier 2017–SW–034–AD. and inspect the drive shaft alignment. Engage AD through an AMOC.
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![3944 Federal Register / Vol. 83, No. 19 / Monday, January 29, 2018 / Rules and Regulations
(h) Additional Information I. Statutory Process for Implementing Example:
Appendix B of Sikorsky S–330 Model 269D Annual Inflation Adjustments • In 2016, the Program Fraud Civil
Helicopter Basic Handbook of Maintenance Section 701 of the Bipartisan Budget Remedies Act penalty was increased to
Instructions, No. CSP–D–2, dated February 1, $10,781 in accordance with the
1993, and revised October 15, 2014;
Act of 2015, Public Law 114–74 (Nov.
2, 2015) (‘‘BBA’’), 28 U.S.C. 2461 note, adjustment requirements of the BBA.
Appendix B of Sikorsky S–330 Model 269D
Config. ‘‘A’’ Helicopter Basic Handbook of substantially revised the prior • For 2017, where the applicable
Maintenance Instructions, No. CSP–D–9, provisions of the Federal Civil Monetary inflation factor was 1.01636, the existing
dated July 20, 2001, and revised October 15, Penalties Inflation Adjustment Act of penalty of $10,781 was multiplied by
2014; and Sikorsky 269D Helicopter Alert 1990, Public Law 101–410 (the 1.01636 and revised to $10,957
Service Bulletin DB–052, Basic Issue, dated ‘‘Inflation Adjustment Act’’), and (rounded to the nearest dollar).
January 16, 2014, which are not incorporated substituted a different statutory formula • For this final rule in 2018, where
by reference, contain additional information for calculating inflation adjustments on the applicable inflation factor is
about the subject of this AD. For service
information identified in this AD, contact
an annual basis. 1.02041, the existing penalty of $10,957
Sikorsky Aircraft Corporation, Customer In accordance with the provisions of is multiplied by 1.02041 and revised to
Service Engineering, 124 Quarry Road, the BBA, on June 30, 2016 (81 FR $11,181 (rounded to the nearest dollar).
Trumbull, CT 06611; telephone 1–800– 42491), the Department of Justice This rule adjusts for inflation civil
Winged–S or 203–416–4299; email wcs_cust_ published an interim rule to adjust for monetary penalties within the
service_eng.gr-sik@lmco.com. You may inflation the civil monetary penalties jurisdiction of the Department of Justice
review a copy of the service information at assessed or enforced by components of for purposes of the Inflation Adjustment
the FAA, Office of the Regional Counsel, the Department after August 1, 2016, Act, as amended. Other agencies are
Southwest Region, 10101 Hillwood Pkwy, with respect to violations occurring after
Room 6N–321, Fort Worth, TX 76177. responsible for the inflation adjustments
November 2, 2015, the date of of certain other civil monetary penalties
(i) Subject enactment of the BBA. Readers may that the Department’s litigating
Joint Aircraft Service Component (JASC) refer to the Supplementary Information components bring suit to collect. The
Code: 6310, Engine/Transmission Coupling. (also known as the preamble) of the reader should consult the regulations of
Department’s 2016 interim rule for those other agencies for inflation
Issued in Fort Worth, Texas, on January 17, additional background information adjustments to those penalties.
2018. regarding the statutory authority for
Lance T. Gant, adjustments of civil monetary penalty III. Effective Date of Adjusted Civil
Director, Compliance & Airworthiness amounts to take account of inflation and Penalty Amounts
Division, Aircraft Certification Service. the Department’s past implementation Under this rule, the adjusted civil
[FR Doc. 2018–01572 Filed 1–26–18; 8:45 am] of inflation adjustments. penalty amounts are applicable only to
BILLING CODE 4910–13–P The BBA also provides for agencies to civil penalties assessed after January 29,
adjust their civil penalties on January 15 2018, with respect to violations
of each year to account for inflation occurring after November 2, 2015, the
during the preceding year, rounded to date of enactment of the BBA.
DEPARTMENT OF JUSTICE the nearest dollar. Accordingly, on The penalty amounts set forth in the
February 3, 2017 (82 FR 9131), the existing table in 28 CFR 85.5 are
28 CFR Part 85 Department published a final rule to applicable to civil penalties assessed
adjust for inflation the civil monetary after August 1, 2016, and on or before
[Docket No. OAG 159; AG Order No. 4093– penalties assessed or enforced by the effective date of this rule, with
2018] components of the Department after that respect to violations occurring after
date, with respect to violations November 2, 2015. Civil penalties for
Civil Monetary Penalties Inflation occurring after November 2, 2015.
Adjustment violations occurring on or before
II. Inflation Adjustments Made by This November 2, 2015, and assessments
AGENCY: Department of Justice. Rule made on or before August 1, 2016, will
ACTION: Final rule. continue to be subject to the civil
As required, the Department is
monetary penalty amounts set forth in
SUMMARY: The Department of Justice is publishing this final rule to adjust the
the Department’s regulations in 28 CFR
adjusting for inflation the civil monetary civil penalties that were most recently
parts 20, 22, 36, 68, 71, 76, and 85 as
penalties assessed or enforced by adjusted as of February 3, 2017. Under
such regulations were in effect prior to
components of the Department, in the statutory formula, the adjustments
August 1, 2016 (or as set forth by statute
accordance with the provisions of the made by this rule are based on the
if the amount had not yet been adjusted
Bipartisan Budget Act of 2015, for Bureau of Labor Statistics’ Consumer
by regulation prior to August 1, 2016).
penalties assessed after January 29, Price Index for October 2017. The OMB
2018, with respect to violations Memorandum for the Heads of Statutory and Regulatory Analyses
occurring after November 2, 2015. Executive Departments and Agencies
Administrative Procedure Act
M–18–03 (Dec. 15, 2017), https://
DATES: This rule is effective January 29,
www.whitehouse.gov/wp-content/ The BBA provides that, for each
2018. uploads/2017/11/M-18-03.pdf (last annual adjustment made after the initial
FOR FURTHER INFORMATION CONTACT: visited Jan. 1, 2018), instructs that the adjustments of civil penalties in 2016,
sradovich on DSK3GMQ082PROD with RULES
Robert Hinchman, Senior Counsel, applicable inflation factor for this the head of an agency shall adjust the
Office of Legal Policy, U.S. Department adjustment is 1.02041. Accordingly, this civil monetary penalties each year
of Justice, Room 4252 RFK Building, rule adjusts the civil penalty amounts in notwithstanding 5 U.S.C. 553.
950 Pennsylvania Avenue NW, 28 CFR 85.5 by applying this inflation Accordingly, this rule is being issued as
Washington, DC 20530, telephone (202) factor mechanically to each of the civil a final rule without prior notice and
514–8059 (not a toll-free number). penalty amounts listed (rounded to the public comment, and without a delayed
SUPPLEMENTARY INFORMATION: nearest dollar). effective date.
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Document Created: 2018-01-27 00:57:56
Document Modified: 2018-01-27 00:57:56
| Category | Regulatory Information | |
| Collection | Federal Register | |
| sudoc Class | AE 2.7: GS 4.107: AE 2.106: | |
| Publisher | Office of the Federal Register, National Archives and Records Administration | |
| Section | Rules and Regulations | |
| Action | Final rule. | |
| Dates | This AD is effective March 5, 2018. | |
| 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] | |
| FR Citation | 83 FR 3941 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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