Federal Register / Vol. 82, No. 176 / Wednesday, September 13, 2017 / Proposed Rules 42957 

(2) Bombardier, Inc., Model CL–600–2D15 

(Regional Jet Series 705) airplanes and Model 

CL–600–2D24 (Regional Jet Series 900) 

airplanes, serial numbers 15326 through 

15370 inclusive. 

(3) Bombardier, Inc., Model CL–600–2E25 

(Regional Jet Series 1000) airplanes, serial 

numbers 19041 and 19042. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 27, Flight controls. 

(e) Reason 

This AD was prompted by a report of 

rudder yoke components that had not been 

properly inspected at the supplier. We are 

issuing this AD to prevent a cracked rudder 

yoke, which may affect rudder function on 

the affected side and could result in 

difficulties in maneuvering the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Replacement of Left and Right Rudder 

Yoke Assemblies 

Within 6,600 flight hours after the effective 

date of this AD, replace the left and right 

rudder yoke assemblies, in accordance with 

the Accomplishment Instructions of 

Bombardier Service Bulletin 670BA–27–073, 

dated November 23, 2016. 

(h) 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 ACO, 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. 

(i) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) Canadian 

AD CF–2017–10, dated February 27, 2017, 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–2017–0811. 

(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) For service information identified in 

this AD, contact Bombardier, Inc., 400 Coˆte 

Vertu Road West, Dorval, Que ́bec H4S 1Y9, 

Canada; Widebody Customer Response 

Center North America toll-free telephone: 1– 

866–538–1247 or direct-dial telephone: 1– 

514–855–2999; fax: 514–855–7401; email: 

ac.yul@aero.bombardier.com; Internet: 

http://www.bombardier.com. 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. 

Issued in Renton, Washington, on August 

31, 2017. 

Dionne Palermo, 

Acting Director, System Oversight Division, 

Aircraft Certification Service. 

[FR Doc. 2017–19306 Filed 9–12–17; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2016–9450; Product 

Identifier 2016–NE–25–AD] 

RIN 2120–AA64 

Airworthiness Directives; Honeywell 

International Inc. Turboprop and 

Turboshaft Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for certain 

Honeywell International Inc. TPE331 

turboprop and TSE331 turboshaft 

engines. This proposed AD was 

prompted by recent reports of failures of 

the direct drive fuel control gears and 

bearings in the hydraulic torque sensor 

gear assembly, part number (P/N) 

3101726–3. This proposed AD would 

require initial and repetitive engine oil 

filter sampling and analysis of the 

affected engines. This proposed AD 

would also require inspection of 

hydraulic torque sensor gear assemblies 

that do not meet oil filter inspection 

requirements. This proposed AD would 

further require improved component 

overhaul procedures that would remove 

from service, by attrition, certain P/N 

hydraulic torque sensor gear assemblies. 

We are proposing this AD to correct the 

unsafe condition on these products. 

DATES: We must receive comments on 

this proposed AD by October 30, 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: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this NPRM, contact Honeywell 

International Inc., 111 S 34th Street, 

Phoenix, AZ 85034–2802; phone: 800– 

601–3099; Internet: https://

myaerospace.honeywell.com/wps/ 

portal. You may view this service 

information at the FAA, Engine and 

Propeller Standards Branch, Policy and 

Innovation Division, 1200 District 

Avenue, Burlington, MA. For 

information on the availability of this 

material at the FAA, call 781–238–7125. 

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–2016– 

9450; or in person at the Docket 

Management Facility between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains this proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Office 

(phone: 800–647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: 

Joseph Costa, Aerospace Engineer, FAA, 

Los Angeles ACO Branch, Compliance 

and Airworthiness Division, 3960 

Paramount Blvd., Lakewood, CA 90712– 

4137; phone: 562–627–5246; fax: 562– 

627–5210; email: joseph.costa@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this NPRM. Send your comments to an 

address listed under the ADDRESSES

section. Include ‘‘Docket No. FAA– 

2016–9450; Directorate Identifier 2016– 

NE–25–AD’’ at the beginning of your 

comments. We specifically invite 


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42958 Federal Register / Vol. 82, No. 176 / Wednesday, September 13, 2017 / Proposed Rules 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this NPRM. We will consider 

all comments received by the closing 

date and may amend this NPRM 

because of 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 NPRM. 

Discussion 

We received reports of failures of the 

direct drive fuel control gears and 

bearings in the hydraulic torque sensor 

gear assembly, P/N 3101726–3. These 

failures are similar to previous failures 

in hydraulic torque sensor gear 

assemblies, P/Ns 3101726–1 and 

3101726–2, that resulted in in-flight 

shutdowns and accidents in single and 

twin-engine airplanes. 

After recent failures of the hydraulic 

torque sensor gear assembly, P/N 

3101726–3, installed in six engines, we 

re-performed oil filter analyses on 

samples taken prior to these failures. We 

found the wear metals, including, but 

not limited to, M50 steel platelets, in the 

engine oil filter samples. The FAA has 

found that the oil filter analysis for wear 

metals provides an effective means of 

identifying premature wear of the 

components in the hydraulic torque 

sensor gear assembly. 

This proposed AD would require 

initial and repetitive oil filter analysis 

for wear metals from the hydraulic 

torque sensor gear assembly. This AD 

also requires the use of later revisions of 

the hydraulic torque sensor gear 

assembly component overhaul manuals 

that provide improved maintenance 

instructions and removes from service, 

by attrition, hydraulic torque sensor 

gear assemblies, P/N 3101726–1 and 

certain P/N 3101726–2 of a pre-Series 9 

configuration. This condition, if not 

corrected, could result in failure of the 

hydraulic torque sensor gear assembly, 

in-flight shutdown, and reduced control 

of the airplane. 

Related Service Information Under 1 

CFR Part 51 

Honeywell has issued Honeywell 

Service Information Letter (SIL) P331– 

97, Revision 11, dated July 23, 2008. 

The SIL describes procedures for 

conducting the spectrometric oil and 

filter analysis program to sample and 

analyze metal particles in the engine 

lubricating system. This service 

information is reasonably available 

because the interested parties have 

access to it through their normal course 

of business or by the means identified 

in the ADDRESSES section. 

Other Related Service Information 

We reviewed the improved 

procedures and limitations in the 

Honeywell Torque Sensor Gear 

Assembly Overhaul Manual with 

Illustrated Parts List, 72–00–17, 

Revision 10, dated October 31, 2013, for 

the TPE331 and TSE331 torque sensor 

gear assemblies. We also reviewed 

Honeywell’s TPE331 Line Maintenance 

Training Manual which provides 

guidance for obtaining oil filter samples. 

In addition, we reviewed Honeywell 

Service Bulletins (SBs) TPE331–72– 

0402, Revision 6, dated November 26, 

1997; TPE331–72–0403, Revision 5, 

dated January 20, 1989; TPE331–72– 

0404, Revision 8, dated September 13, 

2016; TPE331–72–0823, Revision 3, 

dated September 13, 1996; TSE331–72– 

5003, Revision 3, dated January 20, 

1989; and TPE331–72–0180, Revision 

36, dated April 7, 2016. The SBs address 

the inspection intervals for the oil and 

filter analysis for the affected TPE331 

and TSE331 engines. 

FAA’s Determination 

We are proposing this AD because we 

evaluated all the relevant information 

and determined the unsafe condition 

described previously is likely to exist or 

develop in other products of the same 

type design. 

Proposed AD Requirements 

This proposed AD requires initial and 

repetitive engine oil filter analysis of the 

affected TPE331 and TSE331 engines. 

This proposed AD also requires 

inspection of affected hydraulic torque 

sensor gear assemblies, and replacement 

or overhaul of those torque sensor gear 

assemblies that do not meet inspection 

requirements. This proposed AD 

restricts the use of earlier versions of the 

hydraulic sensor gear component 

overhaul manual. 

Differences Between This Proposed AD 

and the Service Information 

Honeywell service information does 

not recommend oil filter sampling and 

analysis and hydraulic torque sensor 

gear assembly inspection within 

specified times for applicable engines. 

Because of recent failures, this proposed 

AD defines specific time requirements 

for performing engine oil filter sampling 

and analysis for all applicable TPE331 

and TSE331 engines and, if necessary, 

hydraulic torque sensor gear assembly 

inspections. This proposed AD would 

require the oil filter sample analysis, 

which is only part of Honeywell’s 

recommended spectrometric oil and oil 

filter analysis program. 

Costs of Compliance 

We estimate that this proposed AD 

affects 3,831 engines installed on 

airplanes of U.S. registry. We estimate 

the following costs to comply with this 

proposed AD: 

We estimate that 3,831 engines will 

require a records review to determine if 

they have an affected hydraulic torque 

sensor gear assembly installed. 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Records review ............................................... 1 work-hour × $85 per hour = $85 ................. $0 $85 $325,635 

We estimate that 2,542 engines 

operating under Parts 121 or 135 and 

544 engines operating under Part 91 will 

be required to perform oil filter 

sampling and analysis. 


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Federal Register / Vol. 82, No. 176 / Wednesday, September 13, 2017 / Proposed Rules 42959 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Oil filter sampling and analysis: Part 91 

operators.

4 work-hours × $85 per hour = $340 ....... $844 $1184 $644,096 per year. 

Oil filter sampling and analysis: Part 121 

and 135 operators.

1 work-hour × $85 per hour = $85 ........... 211 296 752,432 per year. 

We estimate that 242 engines will 

require that the hydraulic torque sensor 

gear assembly be overhauled during the 

first year of inspection. 

ESTIMATED OVERHAUL COSTS

Action Labor cost Parts cost Cost per 

product 

Replace or overhaul hydraulic torque sensor gear assembly.10 work-hours × $85 per hour = $850 ......................... $10,000 $10,850 

We estimate that 217 engines will 

require hydraulic torque sensor gear 

assembly inspection after an 

unacceptable oil filter analysis during 

the first year of inspection. 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per 

product 

Inspect and reassemble hydraulic torque sensor gear 

assembly.

5 work-hours × $85 per hour = $425 ........................... $3,000 $3,425 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. Subtitle VII: 

Aviation Programs, describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in Subtitle VII, 

Part A, Subpart III, Section 44701: 

‘‘General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

This AD is issued in accordance with 

authority delegated by the Executive 

Director, Aircraft Certification Service, 

as authorized by FAA Order 8000.51C. 

In accordance with that order, issuance 

of ADs is normally a function of the 

Compliance and Airworthiness 

Division, but during this transition 

period, the Executive Director has 

delegated the authority to issue ADs 

applicable to engines, propellers, and 

appliances to the Manager, Engine and 

Propeller Standards Branch, Policy and 

Innovation Division. 

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 to the extent that it justifies 

making a regulatory distinction, 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 

■ 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): 

Honeywell International Inc. (Type 

Certificate previously held by 

AlliedSignal, Garrett Engine Division; 

Garrett Turbine Engine Company; and 

AiResearch Manufacturing Company of 

Arizona): Docket No. FAA–2016–9450; 

Product Identifier 2016–NE–25–AD. 

(a) Comments Due Date 

We must receive comments by October 30, 

2017. 


jstallworth on DSKBBY8HB2PROD with PROPOSALS
42960 Federal Register / Vol. 82, No. 176 / Wednesday, September 13, 2017 / Proposed Rules 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Honeywell 

International Inc. (Honeywell) TPE331–1, –2, 

–2UA, –3U, –3UW, –5, –5B, –6, –6A, –8, –10, 

–10AV, –10N, –10P, –10R, –10T, –10U, 

–10UA, –10UF, –10UR model turboprop and 

TSE331–3U turboshaft engines with 

hydraulic torque sensor gear assemblies, part 

numbers (P/Ns) 3101726–1, –2, or –3, 

installed. 

(d) Subject 

Joint Aircraft System Component (JASC) 

Code 7210, Turbine Engine Reduction Gear. 

(e) Unsafe Condition 

This AD was prompted by recent reports of 

failures of the direct drive fuel control gears 

and bearings in the hydraulic torque sensor 

gear assembly, P/N 3101726–3. We are 

issuing this AD to prevent failure of the 

hydraulic torque sensor gear assembly, inflight shutdown, and reduced control of the 

airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Oil Filter Sampling and Analysis 

(1) Obtain an initial engine oil filter sample 

of the affected engines within 150 hours time 

in service after the effective date of this AD. 

Guidance for obtaining oil filter samples can 

be found in Honeywell’s engine training 

manuals; for example, see the TPE331 Line 

Maintenance Training Manual. 

(2) Submit engine oil filter sample within 

3 days of sampling to an ISO/IEC 17025- 

accredited laboratory capable of performing 

analysis using ASTM D5185, Standard Test 

Method for Multielement Determination of 

Used and Unused Lubricating Oils and Base 

Oils by Inductively Coupled Plasma Atomic 

Emission Spectrometry (ICP–AES). A list of 

Honeywell-authorized laboratories capable of 

performing this analysis can be found in 

paragraph 1.D.(10) of Honeywell Service 

Information Letter (SIL) P331–97, Revision 

11, dated July 23, 2008. 

(3) Perform an oil filter analysis for wear 

metals and evaluate filter contents using 

paragraphs 1.D.(4) and (5) of Honeywell SIL 

P331–97, Revision 11, dated July 23, 2008. 

Guidelines for interpreting analysis results 

can be found in paragraph (8) of Honeywell 

SIL P331–97. 

(4) For those engines where the oil filter 

analysis indicates the need for an inspection 

or resample, as specified in Figures 1, 2 or 

3 of the Honeywell SIL P331–97, Revision 11, 

dated July 23, 2008, accomplish the 

following: 

(i) If Figures 1, 2, or 3 indicate an 

inspection is required, within 5 days, inspect 

the torque sensor gear assembly using 

paragraph (g)(5) of this AD. 

(ii) If Figures 1, 2, or 3 indicate a resample 

is required, perform a repeat oil filter sample 

and analysis, within 25 hours time in service 

from the previous sample, to evaluate for 

wear metals in accordance with paragraphs 

(g)(1), (2) and (3) of this AD. 

(A) If the resample indicates a second 

resample or inspection is required, within 5 

days, inspect the hydraulic torque sensor 

gear assembly using paragraph (g)(5) of this 

AD. 

(B) Reserved. 

(5) Inspect the hydraulic torque sensor gear 

assembly using the following steps: 

(i) Remove bearings, P/Ns 358893–1, 

3103035–1, 3103585–1 or 70100168–1, from 

the assembled spur gear and fuel control 

drive gearshaft and inspect or replace. 

Guidance for performing the inspection can 

be found in Section 70–00–00, Standard 

Practices of the applicable TPE331 engine 

maintenance manual. For example, see 

paragraph 5., ‘‘Bearing Inspection,’’ on pages 

11–12 of Honeywell Maintenance Manual 

70–00–00, TPE331–10 (Report No. 72–00– 

27), dated February 29, 2000. 

(ii) Visually inspect the gearshaft teeth for 

scoring, pitting, chipping, metal deposits or 

corner breakage. Visual defects on gear teeth 

are acceptable if defects cannot be felt using 

a 0.031 inch diameter stylus. No corner 

breakage is allowed. 

(iii) For any hydraulic torque sensor gear 

assembly that fails the inspection required by 

paragraph (g)(5) of this AD, remove the 

affected hydraulic torque sensor gear 

assembly and, before further flight, replace 

with a part eligible for installation. 

(6) Thereafter, repeat the steps identified in 

paragraphs (g)(1) through (5) of this AD every 

additional 150 hours time in service after last 

oil filter sampling. 

(h) Hydraulic Torque Sensor Gear Assembly 

Overhaul 

After the effective date of this AD, do not 

use the Honeywell Torque Sensor Gear 

Assembly Overhaul Manual with Illustrated 

Parts List, 72–00–17, Revision No. 9, dated, 

July 20, 1992, or earlier versions, to overhaul 

TPE331 or TSE331 hydraulic torque sensor 

gear assemblies, P/Ns 3101726–1, –2, or –3. 

(i) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, FAA, Los Angeles ACO 

Branch, Compliance and Airworthiness 

Division, 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 Los Angeles ACO 

Branch, send it to the attention of the person 

identified in paragraph (j)(1) of this AD. 

(2) 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. 

(j) Related Information 

(1) For more information about this AD, 

contact Joseph Costa, Aerospace Engineer, 

FAA, Los Angeles ACO Branch, Compliance 

and Airworthiness Division, 3960 Paramount 

Blvd., Lakewood, CA 90712–4137; phone: 

562–627–5246; fax: 562–627–5210; email: 

joseph.costa@faa.gov. 

(2) For service information identified in 

this proposed AD, contact Honeywell 

International Inc., 111 S 34th Street, Phoenix, 

AZ 85034–2802; phone: 800–601–3099; 

Internet: https://

myaerospace.honeywell.com/wps/portal. 

(3) You may view this service information 

at the FAA, Engine and Propeller Standards 

Branch, Policy and Innovation Division, 1200 

District Avenue, Burlington, MA. For 

information on the availability of this 

material at the FAA, call 781–238–7125. 

Issued in Burlington, Massachusetts, on 

September 7, 2017. 

Robert J. Ganley, 

Manager, Engine and Propeller Standards 

Branch, Aircraft Certification Service. 

[FR Doc. 2017–19314 Filed 9–12–17; 8:45 am] 

BILLING CODE 4910–13–P 

CONSUMER PRODUCT SAFETY 

COMMISSION 

16 CFR Parts 1420 

[CPSC Docket No. 2017–0032] 

Amendment to Standard for All-Terrain 

Vehicles; Notice of Proposed 

Rulemaking 

AGENCY: Consumer Product Safety 

Commission. 

ACTION: Notice of proposed rulemaking. 

SUMMARY: The Consumer Product Safety 

Improvement Act of 2008 (CPSIA) 

required the Consumer Product Safety 

Commission (CPSC or the Commission) 

to publish, as a mandatory consumer 

product safety standard, the American 

National Standard for Four-Wheel AllTerrain Vehicles Equipment 

Configuration, and Performance 

Requirements, developed by the 

Specialty Vehicle Institute of America 

(ANSI/SVIA 1–2007). CPSC published 

that mandatory consumer product safety 

standard on November 14, 2008. ANSI/ 

SVIA issued a 2017 edition of its 

standard in June 2017. In accordance 

with the CPSIA, CPSC proposes to 

amend the Commission’s mandatory 

ATV standard to reference the 2017 

edition of the ANSI/SVIA standard. 

DATES: Submit comments by November 

27, 2017. 

ADDRESSES: Comments related to the 

proposed rule, identified by Docket No. 

CPSC–2017–0032, may be submitted 

electronically or in writing: 

Electronic Submissions: Submit 

electronic comments to the Federal 

eRulemaking Portal at: http://

www.regulations.gov. Follow the 

instructions for submitting comments. 

The Commission does not accept 

comments submitted by email, except 

through www.regulations.gov. The 

Commission encourages you to submit 

electronic comments by using the 


jstallworth on DSKBBY8HB2PROD with PROPOSALS