This section of the FEDERAL REGISTER

contains regulatory documents having general

applicability and legal effect, most of which

are keyed to and codified in the Code of

Federal Regulations, which is published under

50 titles pursuant to 44 U.S.C. 1510.

The Code of Federal Regulations is sold by

the Superintendent of Documents.

Rules and Regulations Federal Register

28763 

Vol. 83, No. 120 

Thursday, June 21, 2018 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2016–9450; Product 

Identifier 2016–NE–25–AD; Amendment 39– 

19317; AD 2018–13–05] 

RIN 2120–AA64 

Airworthiness Directives; Honeywell 

International Inc. Turboprop and 

Turboshaft Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Honeywell International Inc. 

(Honeywell) TPE331 turboprop and 

TSE331 turboshaft engines. 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, part 

number (P/N) 3101726–3. This AD 

requires initial and repetitive engine oil 

filter sampling and analysis of the 

affected engines and inspections of 

certain hydraulic torque sensor gear 

assemblies. We are issuing this AD to 

address the unsafe condition on these 

products. 

DATES: This AD is effective July 26, 

2018. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of July 26, 2018. 

ADDRESSES: For service information 

identified in this final rule, 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 781–238–7759. 

It is also available on the internet at 

http://www.regulations.gov by searching 

for and locating Docket No. FAA–2016– 

9450. 

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 Docket Operations 

between 9 a.m. and 5 p.m., Monday 

through Friday, except Federal holidays. 

The AD docket contains this final rule, 

the regulatory evaluation, any 

comments received, and other 

information. The address for the Docket 

Operations (phone: 800–647–5527) is 

Docket 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: 

Joseph Costa, Aerospace Engineer, Los 

Angeles ACO Branch, FAA, 3960 

Paramount Blvd., Lakewood, CA 90712– 

4137; phone: 562–627–5246; fax: 562– 

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

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to certain Honeywell 

International Inc. TPE331 turboprop and 

TSE331 turboshaft engines. The NPRM 

published in the Federal Register on 

September 13, 2017 (82 FR 42957). The 

NPRM 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. The NPRM proposed to 

require initial and repetitive engine oil 

filter sampling and analysis of the 

affected engines. The NPRM also 

proposed to require inspection of the 

hydraulic torque sensor gear assemblies 

that do not meet oil filter inspection 

requirements and improved component 

overhaul procedures that would remove 

from service, by attrition, certain P/N 

hydraulic torque sensor gear assemblies. 

We are issuing this AD to address the 

unsafe condition on these products. 

Comments 

We gave the public the opportunity to 

participate in developing this final rule. 

The following presents the comments 

received on the NPRM and the FAA’s 

response to each comment. 

Request To Revise Compliance Time for 

Resampling 

The National Agricultural Aviation 

Association (NAAA) commented that 

additional compliance time may be 

required for oil filter analysis 

resampling beyond the 25 hours timein-service proposed by the NPRM. The 

NAAA noted that the engine may reenter service after oil sampling. 

Therefore, the 25 hours time-in-service 

may be exceeded prior to the operators 

receiving notification from the 

laboratory that performed the oil filter 

analysis. 

We agree that the proposed 

compliance time may have resulted in 

operators exceeding the 25 hours timein-service before receiving the results of 

the oil filter analysis. We, therefore, 

revised the requirement time for 

resampling in this AD to 25 hours time 

in service after receiving notification 

from the accredited laboratory 

performing the oil filter analysis. We 

determined that allowing this additional 

time in service will improve the quality 

of the sample. We also clarified that if 

an inspection or resample is required, 

then the inspection must occur within 

5 days after receiving notification from 

the laboratory that performed the oil 

filter analysis. 

Request To Revise Compliance Time for 

Initial Sample 

Honeywell requested that we increase 

the compliance time for obtaining an oil 

filter sample from 150 to 200 hours. 

Honeywell commented that Honeywell 

Service Bulletin (SB) TPE331–72–0180 

indicates a 200-hours compliance time 

for TPE331–10 operators with at least 

800 operating hours per year. 

Honeywell noted that this compliance 

time coincides with scheduled 

maintenance intervals for operators. 

We disagree. We are attempting to 

detect impending torque sensor failures 

using set response times and reduced oil 

filter sampling and analysis intervals. 

We find, therefore, that the 150-hour 

compliance time meets the safety 

objectives of this AD. Further, we did 

not receive any comments from part 121 


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or part 135 operators indicating a 

concern with the inspection interval of 

150 hours. We did not change this AD. 

Request To Revise Number of 

Resampling Tests 

NAAA and Copperstate Turbine 

Engine Company commented that a 

single resampling allowance that may 

lead to a gearbox inspection is too 

stringent. They indicated that oil filter 

resampling experience has shown that 

multiple resampling tests may be 

necessary. NAAA commented that the 

source of the contamination may not 

always be the material caused by the 

torque sensor failure. In this situation, 

NAAA indicated that another 

resampling, without the inspection, may 

be warranted. NAAA commented that 

the sample analysis should guide 

maintenance personnel in the proper 

direction without having to tear down 

an engine unnecessarily. 

We partially agree. We agree that 

some wear elements, such as silver and 

aluminum, found during the initial oil 

filter analysis could permit more than 

one resampling before a required 

gearbox inspection. We also agree 

because these elements or alloys may 

not cause accelerated wear and possible 

failure of the torque sensor assembly. 

We disagree with changing the AD 

because the commenters have not 

produced evidence that the presence of 

certain elements may not contribute to 

the failure of the torque sensor. We will 

consider AMOC requests to allow 

additional oil filter resamples before 

requiring a gearbox inspection provided 

we receive acceptable technical 

justification. We did not change this 

AD. 

Request To Update Service Information 

Honeywell requested that we revise 

our reference to the service bulletin to 

refer to the latest revision. 

We agree. We updated the reference 

in the Other Related Service Information 

paragraph in this AD to Revision 38 of 

Honeywell SB TPE331–72–0180. 

Request To Clarify Differences 

Paragraph 

Honeywell requested that we clarify 

the ‘‘Differences Between This Proposed 

AD and the Service Information’’ 

section in the NPRM. 

We disagree. The referenced 

paragraph does not exist in the final rule 

and the compliance requirements were 

clearly defined in the NPRM. We did 

not change this AD. 

Conclusion 

We reviewed the relevant data, 

considered the comments received, and 

determined that air safety and the 

public interest require adopting this 

final rule with the changes described 

previously and minor editorial changes. 

We have determined that these minor 

changes: 

• Are consistent with the intent that 

was proposed in the NPRM for 

correcting the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM. 

We also determined that these 

changes will not increase the economic 

burden on any operator or increase the 

scope of this final rule. 

Related Service Information Under 

1 CFR Part 51 

We reviewed 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 

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 38, dated August 15, 2017. The 

SBs address the inspection intervals for 

the oil and filter analysis for the affected 

TPE331 and TSE331 engines. 

Costs of Compliance 

We estimate that this AD affects 3,831 

engines installed on airplanes of U.S. 

registry. We estimate the following costs 

to comply with this 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. 

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 $1,184 $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. 


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Federal Register / Vol. 83, No. 120 / Thursday, June 21, 2018 / Rules and Regulations 28765 

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 

Paperwork Reduction Act 

A federal agency may not conduct or 

sponsor, and a person is not required to 

respond to, nor shall a person be subject 

to penalty for failure to comply with a 

collection of information subject to the 

requirements of the Paperwork 

Reduction Act unless that collection of 

information displays a current valid 

OMB control number. The control 

number for the collection of information 

required by this AD is 2120–0056. The 

paperwork cost associated with this AD 

has been detailed in the Costs of 

Compliance section of this document 

and includes time for reviewing 

instructions, as well as completing and 

reviewing the collection of information. 

Therefore, all reporting associated with 

this AD is mandatory. Comments 

concerning the accuracy of this burden 

and suggestions for reducing the burden 

should be directed to the FAA at 800 

Independence Ave. SW, Washington, 

DC 20591. ATTN: Information 

Collection Clearance Officer, AES–200. 

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 

associated appliances to the Manager, 

Engine and Propeller Standards Branch, 

Policy and Innovation Division. 

Regulatory Findings 

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, 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): 

2018–13–05 Honeywell International Inc. 

(Type Certificate previously held by 

AlliedSignal, Garrett Engine Division; 

Garrett Turbine Engine Company; and 

AiResearch Manufacturing Company of 

Arizona): Amendment 39–19317; Docket 

No. FAA–2016–9450; Product Identifier 

2016–NE–25–AD. 

(a) Effective Date 

This AD is effective July 26, 2018. 

(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. 


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(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. The 

unsafe condition, if not addressed, could 

result in failure of the hydraulic torque 

sensor gear assembly, in-flight 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. 

You can find guidance for obtaining oil filter 

samples in Honeywell’s engine training 

manuals; for example, see the TPE331 Line 

Maintenance Training Manual. 

(2) Submit the 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). You can find a list 

of Honeywell-authorized laboratories capable 

of performing this analysis 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 after 

receiving notification from the laboratory that 

performed the analysis, inspect the torque 

sensor gear assembly using paragraph 

(g)(4)(iii) 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 

after receiving notification from the 

laboratory that performs the analysis 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 after receiving notification from the 

laboratory that performed the analysis, 

inspect the hydraulic torque sensor gear 

assembly using paragraph (g)(4)(iii) of this 

AD. 

(B) Reserved. 

(iii) Inspect the hydraulic torque sensor 

gear assembly using the following steps: 

(A) 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. 

(B) 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. 

(5) Thereafter, repeat the steps identified in 

paragraphs (g)(1) through (4) of this AD every 

additional 150 hours time in service after last 

oil filter sampling. 

(6) For any hydraulic torque sensor gear 

assembly that fails the inspection required by 

paragraph (g) of this AD, remove the affected 

hydraulic torque sensor gear assembly and, 

before further flight, replace with a part 

eligible for installation. 

(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, Los Angeles 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 the attention of 

the person identified in paragraph (j) 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 

For more information about this AD, 

contact Joseph Costa, Aerospace Engineer, 

Los Angeles ACO Branch, FAA, 3960 

Paramount Blvd., Lakewood, CA 90712– 

4137; phone: 562–627–5246; fax: 562–627– 

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

(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 the AD specifies otherwise. 

(i) Honeywell Service Information Letter 

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

(ii) Reserved. 

(3) For Honeywell service information 

identified in this AD, contact Honeywell 

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

AZ 85034–2802; phone: 800–601–3099; 

internet: https://

myaerospace.honeywell.com/wps/portal. 

(4) You may view this service information 

at 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 781–238–7759. 

(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: http://

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Burlington, Massachusetts, on 

June 14, 2018. 

Robert J. Ganley, 

Manager, Engine and Propeller Standards 

Branch, Aircraft Certification Service. 

[FR Doc. 2018–13266 Filed 6–20–18; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF HOMELAND 

SECURITY 

Coast Guard 

33 CFR Part 165 

[Docket Number USCG–2018–0333] 

RIN 165–AA00 

Safety Zones; Marine Events Held in 

the Captain of the Port Long Island 

Sound Zone 

AGENCY: Coast Guard, DHS. 

ACTION: Temporary final rule. 

SUMMARY: The Coast Guard is 

establishing nine temporary safety zones 

for fireworks displays within the 

Captain of the Port (COTP) Long Island 

Sound (LIS) Zone. This temporary final 

rule is necessary to provide for the 

safety of life on navigable waters during 

these events. Entry into, transit through, 

mooring or anchoring within these 

limited access areas is prohibited unless 

authorized by the COTP LIS. 

DATES: This rule is effective without 

actual notice from June 21, 2018 

through July 15, 2018. For the purposes 

of enforcement, actual notice will be 

used from May 27, 2018, through June 

21, 2018. 

ADDRESSES: To view documents 

mentioned in this preamble as being 


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