67100 Federal Register / Vol. 81, No. 190 / Friday, September 30, 2016 / Rules and Regulations 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

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 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. 

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): 

2016–19–09 General Electric Company: 

Amendment 39–18658; Docket No. 

FAA–2016–5307; Directorate Identifier 

2016–NE–08–AD. 

(a) Effective Date 

This AD is effective November 4, 2016. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to General Electric 

Company (GE) GE90–76B, GE90–77B, GE90– 

85B, GE90–90B, and GE90–94B turbofan 

engines with a high-pressure compressor 

(HPC) stage 8–10 spool, part numbers 

1694M80G04, 1844M90G01, or 1844M90G02, 

installed. 

(d) Unsafe Condition 

This AD was prompted by reports of cracks 

found on the seal teeth of the HPC stage 8– 

10 spool. We are issuing this AD to prevent 

failure of the HPC stage 8–10 spool, 

uncontained rotor release, damage to the 

engine, and damage to the airplane. 

(e) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(1) Perform an eddy current inspection 

(ECI) or fluorescent penetrant inspection 

(FPI) of the seal teeth of the HPC stage 8–10 

spool as follows: 

(i) For HPC stage 8–10 spools with fewer 

than 11,000 cycles since new (CSN) on the 

effective day of this AD, inspect at the next 

shop visit after reaching 6,000 CSN, not to 

exceed 12,500 CSN. 

(ii) For HPC stage 8–10 spools with 11,000 

CSN or more on the effective day of this AD, 

inspect within the next 1,500 cycles in 

service. 

(iii) Thereafter, inspect the seal teeth of the 

HPC stage 8–10 spool at each shop visit. 

(2) Remove from service any HPC stage 8– 

10 spool that fails the ECI or FPI required by 

paragraph (e)(1) of this AD and replace with 

a part eligible for installation. 

(3) Guidance on performing the ECI and 

the FPI can be found in GE Service Bulletins 

(SBs) SB 72–1141 R00, dated December 2, 

2015 and SB 72–1142 R00, dated November 

30, 2015. 

(f) Definition 

For the purpose of this AD, an engine shop 

visit is the induction of an engine into the 

shop for maintenance during which the 

compressor discharge pressure seal face is 

exposed. 

(g) Alternative Methods of Compliance 

(AMOCs) 

The Manager, Engine Certification Office, 

FAA, may approve AMOCs for this AD. Use 

the procedures found in 14 CFR 39.19 to 

make your request. You may email your 

request to: ANE-AD-AMOC@faa.gov. 

(h) Related Information 

(1) For more information about this AD, 

contact John Frost, Aerospace Engineer, 

Engine Certification Office, FAA, 1200 

District Avenue, Burlington, MA 01803; 

phone: 781–238–7756; fax: 781–238–7199; 

email: john.frost@faa.gov. 

(2) GE SB 72–1141, R00, dated December 

2, 2015 and GE SB 72–1142, R00, dated 

November 30, 2015, which are not 

incorporated by reference in this AD, can be 

obtained from GE, using the contact 

information in paragraph (h)(3) of this AD. 

(3) For service information identified in 

this AD, contact General Electric Company, 

GE-Aviation, Room 285, 1 Neumann Way, 

Cincinnati, OH 45215, phone: 513–552–3272; 

email: aviation.fleetsupport@ge.com. 

(4) You may view this service information 

at the FAA, Engine & Propeller Directorate, 

1200 District Avenue, Burlington, MA. For 

information on the availability of this 

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

(i) Material Incorporated by Reference 

None. 

Issued in Burlington, Massachusetts, on 

September 26, 2016. 

Colleen M. D’Alessandro, 

Manager, Engine & Propeller Directorate, 

Aircraft Certification Service. 

[FR Doc. 2016–23740 Filed 9–29–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–4866; Directorate 

Identifier 2015–NE–33–AD; Amendment 39– 

18648; AD 2016–18–17] 

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 model turboprop 

engines and TSE331–3U model 

turboshaft engines. This AD was 

prompted by the discovery of cracks in 

a 2nd stage compressor impeller during 

a routine shop visit. This AD requires 

removal of the 2nd stage compressor 

impeller. We are issuing this AD to 

prevent failure of the compressor 

impeller, uncontained part release, 

damage to the engine, and damage to the 

airplane. 

DATES: This AD is effective November 4, 

2016. 

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–2015– 

4866; 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 AD, the regulatory 

evaluation, any comments received, and 

other information. The address for the 

Docket Office (phone: 800–647–5527) is 

Document Management Facility, 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 


asabaliauskas on DSK3SPTVN1PROD with RULES
Federal Register / Vol. 81, No. 190 / Friday, September 30, 2016 / Rules and Regulations 67101 

Angeles Aircraft Certification Office, 

FAA, Transport Airplane Directorate, 

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 TPE331 

model turboprop engines and TSE331– 

3U model turboshaft engines. The 

NPRM published in the Federal 

Register on March 15, 2016 (81 FR 

13764) (‘‘the NPRM’’). The NPRM was 

prompted by the discovery of cracks in 

a 2nd stage compressor impeller during 

a routine shop visit. The NPRM 

proposed to require removal of the 2nd 

stage compressor impeller. We are 

issuing this AD to prevent failure of the 

compressor impeller, uncontained part 

release, damage to the engine, and 

damage to the airplane. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the NPRM and the FAA’s 

response to each comment. 

Request To Change Compliance 

Bearskin Airlines and Turbine 

Standard, LTD requested that the 

compliance time interval be changed 

because many TPE331 engine operators 

are on a Continuous Airworthiness 

Maintenance (CAM) program. This 

program does not require impeller 

inspections per the overhaul manual 

and the impeller is not considered as 

‘‘overhauled’’. AD compliance under 

CAM may be interpreted as being within 

200 cycles or 30 to 45 days. 

Other commenters requested that the 

compliance time be changed to a less 

aggressive time interval appropriate to 

the unsafe condition. Many high-usage 

operators have suspect impellers that 

currently exceed 7,000 cycles since the 

last compressor inspection. 

We agree. We changed compliance 

interval in paragraph (e)(1) of this AD. 

Request To Allow Other Inspection 

Facilities To Return Impellers to 

Service 

Turbine Standard, LTD requested that 

this AD allow other inspection facilities 

to return impellers to service. There are 

many inspection facilities that are 

capable of inspecting the 2nd stage 

compressor impeller. 

We partially agree. We agree that 

many inspection facilities are capable of 

performing a focused inspection of the 

2nd stage compressor impeller. We 

disagree with allowing other inspection 

and regrinding facilities to return 

impellers to service. This AD does not 

address inspection or regrinding of the 

curvic area of the 2nd stage compressor 

impeller. Regrinding of the curvic area 

of the 2nd stage compressor impeller 

involves machining of a critical rotating 

part, which must be approved by the 

FAA. We did not change this AD. 

Request To Change Costs of Compliance 

Honeywell; Perimeter Aviation, LP; 

and Intercontinental Jet Service Corp. 

requested that the costs of compliance 

be changed because the NPRM is not 

representative of the impeller’s 

replacement costs. Honeywell quotes 

the cost of a new 2nd stage compressor 

impeller at $11,922.50. 

We partially agree. We agree with the 

comment because the costs were not 

clearly defined. We disagree with the 

comment because replacement costs are 

based on pro-rated costs that are 

estimated at 50% of new parts costs. 

Since issuing the NPRM, the FAA 

estimated that 30% of impellers will be 

scrapped; therefore, we changed the 

costs of compliance accordingly. 

Request To Include Service Information 

The European Aviation Safety 

Agency, Honeywell, and Candler & 

Associates, Inc. requested that service 

information be included in this AD. 

Having the service information available 

would aid in understanding any 

differences between this AD and the 

service information. 

We agree. We added Honeywell 

Service Bulletin (SB) TPE331–72–2208, 

dated July 29, 2014, as related 

information in this AD. 

Conclusion 

We reviewed the relevant data, 

considered the comments received, and 

determined that air safety and the 

public interest require adopting this AD 

with the changes described previously. 

We also determined that these 

changes will not increase the economic 

burden on any operator or increase the 

scope of this AD. 

Related Service Information 

We reviewed Honeywell SB TPE331– 

72–2208, dated July 29, 2014. The SB 

describes procedures for replacing the 

2nd stage compressor impeller. 

Costs of Compliance 

We estimate that this AD will affect 

4,000 engines installed on airplanes of 

U.S. registry. We estimate that it will 

take 2 hours per engine to comply with 

this AD. The average labor rate is $85 

per hour. We also estimate that required 

parts will cost about $4,404.50 per 

engine. Based on these figures, we 

estimate the total cost of this AD on U.S. 

operators to be $18,298,000. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. Subtitle VII: 

Aviation Programs, describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in Subtitle VII, 

Part A, Subpart III, Section 44701: 

‘‘General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

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 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. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 


asabaliauskas on DSK3SPTVN1PROD with RULES
67102 Federal Register / Vol. 81, No. 190 / Friday, September 30, 2016 / Rules and Regulations 

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): 

2016–18–17 Honeywell International Inc. 

(Type Certificate Previously Held by 

AlliedSignal Inc., Garrett Engine 

Division; Garrett Turbine Engine 

Company; and AiResearch 

Manufacturing Company of Arizona): 

Amendment 39–18648; Docket No. 

FAA–2015–4866; Directorate Identifier 

2015–NE–33–AD. 

(a) Effective Date 

This AD is effective November 4, 2016. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Honeywell 

International Inc. (Honeywell) TPE331–3U, 

–3UW, –5, –5A, –5AB, –5B, –6, –6A, –8, –10, 

–10AV, –10GP, –10GT, –10N, –10P, –10R, 

–10T, –10U, –10UA, –10UF, –10UG, 

–10UGR, –10UR, and –11U model turboprop 

engines, and TSE331–3U model turboshaft 

engines, with a 2nd stage compressor 

impeller, part number (P/N) 893482–1 

through –5, inclusive, or P/N 3107056–1 or 

P/N 3107056–2, installed. 

(d) Unsafe Condition 

This AD was prompted by the discovery of 

cracks in a 2nd stage compressor impeller 

during a routine shop visit. We are issuing 

this AD to prevent failure of the compressor 

impeller, uncontained part release, damage to 

the engine, and damage to the airplane. 

(e) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(1) Remove from service the 2nd stage 

compressor impeller at next removal of the 

2nd stage compressor impeller from the 

engine or before exceeding 11,500 cycles in 

service after the effective date of this AD, 

whichever occurs first. 

(2) Reserved. 

(f) Installation Prohibition 

After the effective date of this AD, do not 

install a 2nd stage compressor impeller, part 

number (P/N) 893482–1 through –5, 

inclusive, or P/N 3107056–1 or P/N 

3107056–2, into any engine. 

(g) Alternative Methods of Compliance 

(AMOCs) 

The Manager, Los Angeles Aircraft 

Certification Office, FAA, may approve 

AMOCs for this AD. Use the procedures 

found in 14 CFR 39.19 to make your request. 

(h) Related Information 

(1) For more information about this AD, 

contact Joseph Costa, Aerospace Engineer, 

Los Angeles Aircraft Certification Office, 

FAA, Transport Airplane Directorate, 3960 

Paramount Blvd., Lakewood, CA 90712– 

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

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

(2) Honeywell SB TPE331–72–2208, dated 

July 29, 2014, which is not incorporated by 

reference in this AD, can be obtained from 

Honeywell, using the contact information in 

paragraph (h)(3) of this AD. 

(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/!ut/. 

(4) You may view this service information 

at FAA, Engine & Propeller Directorate, 1200 

District Avenue, Burlington, MA. For 

information on the availability of this 

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

(i) Material Incorporated by Reference 

None. 

Issued in Burlington, Massachusetts, on 

August 26, 2016. 

Colleen M. D’Alessandro, 

Manager, Engine & Propeller Directorate, 

Aircraft Certification Service. 

[FR Doc. 2016–23263 Filed 9–29–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2016–9144; Directorate 

Identifier 2016–SW–014–AD; Amendment 

39–18667; AD 2016–20–01] 

RIN 2120–AA64 

Airworthiness Directives; Bell 

Helicopter Textron Canada Limited 

(Bell) Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for Bell 

Model 427 and Model 429 helicopters. 

This AD requires replacing certain 

engine and transmission oil check 

valves. This AD also prohibits installing 

the affected check valves on any 

helicopter. This AD is prompted by a 

report of several cracked or leaking 

check valves. These actions are 

intended to detect and prevent a 

cracked or leaking check valve which 

could result in loss of lubrication to the 

engine or transmission, failure of the 

engine or transmission, and subsequent 

loss of control of the helicopter. 

DATES: This AD becomes effective 

October 17, 2016. 

We must receive comments on this 

AD by November 29, 2016. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Docket: Go to 

http://www.regulations.gov. Follow the 

online instructions for sending your 

comments electronically. 

• Fax: 202–493–2251. 

• Mail: Send comments to the U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590–0001. 

• Hand Delivery: Deliver to the 

‘‘Mail’’ address between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

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– 

9144; or in person at the Docket 

Operations Office between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. The AD docket 

contains this AD, the Transport Canada 

AD, the economic evaluation, any 

comments received, and other 

information. The street address for the 

Docket Operations Office (telephone 

800–647–5527) is in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after receipt. 

For service information identified in 

this final rule, contact Bell Helicopter 

Textron Canada Limited, 12,800 Rue de 

l’Avenir, Mirabel, Quebec J7J1R4; 

telephone (450) 437–2862 or (800) 363– 

8023; fax (450) 433–0272; or at http://

www.bellcustomer.com/files/. You may 

review the referenced service 

information at the FAA, Office of the 

Regional Counsel, Southwest Region, 

10101 Hillwood Pkwy., Room 6N–321, 

Fort Worth, TX 76177. 

FOR FURTHER INFORMATION CONTACT: Rao 

Edupuganti, Aviation Safety Engineer, 

Regulations and Policy Group, 

Rotorcraft Directorate, FAA, 10101 

Hillwood Pkwy., Fort Worth, TX 76177; 

telephone (817) 222–5110; email 

rao.edupuganti@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety, and 

we did not provide you with notice and 

an opportunity to provide your 

comments prior to it becoming effective. 


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