Federal Register / Vol. 82, No. 173 / Friday, September 8, 2017 / Rules and Regulations 42443 

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. 

We prepared an economic evaluation 

of the estimated costs to comply with 

this AD and placed it in the AD docket. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by 

removing Airworthiness Directive (AD) 

2015–22–51, Amendment 39–18386 (81 

FR 5037, February 1, 2016), and adding 

the following new AD: 

2017–18–13 Agusta S.p.A.: Amendment 39– 

19022; Docket No. FAA–2017–0308; 

Product Identifier 2016–SW–083–AD. 

(a) Applicability 

This AD applies to Model A109A and 

A109A II helicopters with a main rotor blade 

(blade) part number (P/N) 109–0103–01–7, 

P/N 109–0103–01–9, or P/N 109–0103–01– 

115 that has 500 or more hours time-inservice (TIS) installed, certificated in any 

category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as a 

crack in a blade. This condition could result 

in failure of a blade and subsequent loss of 

control of the helicopter. 

(c) Affected ADs 

This AD supersedes AD 2015–22–51, 

Amendment 39–18386 (81 FR 5037, February 

1, 2016). 

(d) Effective Date 

This AD becomes effective September 25, 

2017. 

(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 

Before further flight, unless already done 

within the last 5 hours TIS, and thereafter at 

intervals not to exceed 5 hours TIS: 

(1) Using a 3X or higher power magnifying 

glass, visually inspect the top and bottom 

surface of each blade for a crack in the area 

between the station at the end of the doublers 

(station 1550) and the station at the 

beginning of the abrasion strip (station 3100). 

(2) If there is a crack, replace the blade 

before further flight. Replacing the blade with 

blade P/N 109–0103–01–7, P/N 109–0103– 

01–9, or P/N 109–0103–01–115 does not 

constitute terminating action for the 

repetitive inspections required by this AD. 

(g) Special Flight Permits 

Special flight permits are prohibited. 

(h) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Section, FAA, may approve AMOCs for this 

AD. Send your proposal to: Matt Fuller, 

Senior Aviation Safety Engineer, Safety 

Management Section, Rotorcraft Standards 

Branch, FAA, 10101 Hillwood Pkwy, Fort 

Worth, TX 76177; telephone (817) 222–5110; 

email 9-ASW-FTW-AMOC-Requests@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. 

(i) Additional Information 

(1) Leonardo Helicopters Alert Bollettino 

Tecnico No. 109–150, Revision B, dated 

October 21, 2016, which is not incorporated 

by reference, contains additional information 

about the subject of this AD. For service 

information identified in this AD, contact 

Leonardo S.p.A. Helicopters, Matteo Ragazzi, 

Head of Airworthiness, Viale G.Agusta 520, 

21017 C.Costa di Samarate (Va) Italy; 

telephone +39–0331–711756; fax +39–0331– 

229046; or at http://www.leonardo

company.com/-/bulletins. 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. 

(2) The subject of this AD is addressed in 

European Aviation Safety Agency (EASA) AD 

No. 2016–0213, dated October 26, 2016. You 

may view the EASA AD on the Internet at 

http://www.regulations.gov by searching for 

and locating it in Docket No. FAA–2017– 

0308. 

(j) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6210, Main Rotor Blade. 

Issued in Fort Worth, Texas, on August 30, 

2017. 

Lance T. Gant, 

Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2017–18972 Filed 9–7–17; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0961; Product 

Identifier 2011–NE–22–AD; Amendment 39– 

19023; AD 2017–18–14] 

RIN 2120–AA64 

Airworthiness Directives; Rolls-Royce 

Corporation Turboshaft Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are superseding 

Airworthiness Directive (AD) 2015–02– 

22 for certain Rolls-Royce Corporation 

(RRC) model 250 turboprop and 

turboshaft engines. AD 2015–02–22 

required repetitive visual inspections 

and fluorescent-penetrant inspection 

(FPIs) on certain 3rd-stage and 4th-stage 

turbine wheels for cracks in the turbine 

wheel blades. This AD requires 

repetitive visual inspections and FPIs of 

3rd-stage turbine wheels while 

removing from service 4th-stage turbine 

wheels. We are also revising the 

applicability to remove all RRC 

turboprop engines and add additional 

turboshaft engines. This AD was 

prompted by our finding that it is 

necessary to remove the 4th-stage 

wheels at the next inspection. We are 

issuing this AD to address the unsafe 

condition on these products. 

DATES: This AD is effective October 13, 

2017. 

ADDRESSES: See the FOR FURTHER

INFORMATION CONTACT section. 

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–2011– 

0961; 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 final rule, 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: John 

Tallarovic, Aerospace Engineer, FAA, 

Chicago ACO Branch, Compliance and 

Airworthiness Division, 2300 E. Devon 

Ave., Des Plaines, IL 60018; phone: 


sradovich on DSK3GMQ082PROD with RULES
42444 Federal Register / Vol. 82, No. 173 / Friday, September 8, 2017 / Rules and Regulations 

847–294–8180; fax: 847–294–7834; 

email: john.m.tallarovic@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2015–02–22, 

Amendment 39–18090 (80 FR 5452, 

February 2, 2015), (‘‘AD 2015–02–22’’). 

AD 2015–02–22 applied to certain RRC 

250–B17, –B17B, –B17C, –B17D, –B17E, 

–B17F, –B17F/1, –B17F/2, turboprop 

engines; and 250–C20, –C20B, –C20F, 

–C20J, –C20R, –C20R/1, –C20R/2, 

–C20R/4, –C20S, and –C20W turboshaft 

engines. The NPRM published in the 

Federal Register on March 29, 2017 (82 

FR 15474). The NPRM was prompted by 

our determination that it is necessary to 

remove the 4th-stage wheels at the next 

inspection. The NPRM proposed to 

require repetitive visual inspections and 

FPIs of 3rd-stage turbine wheels while 

removing from service 4th-stage turbine 

wheels. We are also revising the 

applicability to remove all RRC 

turboprop engines and add additional 

turboshaft engines. We are issuing this 

AD to prevent failure of the 3rd-stage 

and 4th-stage turbine wheel blades, 

damage to the engine, and damage to the 

aircraft. 

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 Remove Certain 3rd Stage 

Turbine Wheel From AD 

RRC requested that we remove 

references in this AD to the 3rd stage 

turbine wheel, part number (P/N) 

RR30000236, installed on the RRC 250– 

C300/A1 and 250–C300/B1 turboshaft 

engines. RRC indicated that 3rd stage 

turbine wheels, P/N RR30000236, are 

not susceptible to cracks. RRC noted 

that there have been no cracks observed 

on 3rd stage wheels installed on RRC 

250–C300/A1 or 250–C300B/1 engines. 

We agree. The 3rd stage turbine 

wheel, P/N RR30000236, installed on 

RRC 250–C300/A1 and 250–C300/B1 

engines does not require inspections. 

They are subject to less severe operating 

conditions and are not susceptible to 

this type of failure. We removed 

references to the 3rd stage turbine 

wheel, P/N RR30000236, from this AD. 

Request To Revise Power Turbine 

Reference 

RRC requested that we change 

references in this AD from ‘‘power 

turbine’’ to ‘‘turbine.’’ RRC noted that 

this AD should refer to the entire 

turbine module rather than just to the 

power turbine. RRC also commented 

that the risk analysis for this AD is 

based on changing the parts anytime the 

turbine is being serviced, not just the 

power turbine. Revising the reference in 

this AD to ‘‘turbine’’ would remove the 

affected 4th stage turbine wheels from 

the fleet in a shorter time period since 

the actions specified in this AD are to 

be complied with whenever the turbine 

is at the shop and is dissembled for any 

reason, or at the next turbine wheel 

replacement, whichever occurs first. 

We agree. We changed the reference 

in the Compliance section of this AD 

from ‘‘power turbine’’ to ‘‘turbine.’’ 

RRC also commented that changing 

the references to ‘‘turbine’’ would allow 

for removal of the Definition section 

from this AD. 

We disagree. The term ‘‘engine shop 

visit’’ is used as one of the criteria in 

this AD to determine when an 

inspection of affected applicable turbine 

wheels is required. Given that ‘‘engine 

shop visit’’ may be interpreted in 

different ways, we provide a definition 

for this term in this AD. We did not 

change this AD. 

Request To Clarify Removal of Blades 

With Cracks From Service 

RRC requested that we revise the 

Compliance section of this AD so that it 

does not require removal from service 

all turbine wheels found with cracks. 

RRC commented that only certain cracks 

are related to this AD and are a safety 

concern. 

We agree. The intent of this AD is to 

address cracks at the trailing edge of the 

turbine wheel blades, near the fillet at 

the rim. The maintenance manuals for 

these engines allow certain cracks in 

areas of the turbine wheels not subject 

to this AD. Engines may still operate 

safety with turbine wheels that have 

allowable cracks. We revised paragraph 

(f)(3) of this AD to refer to cracks found 

at the trailing edge, near the fillet at the 

rim, of the turbine blades. 

Revision to Costs of Compliance 

We reduced the estimated cost of 

inspection of 3rd stage wheels from 

$320,365 to $288,320 since we removed 

the 3rd stage wheel, P/N RR30000236, 

from the applicability of this AD. As 

noted in our previous comment 

response, these P/N 3rd stage wheels are 

not subject to the unsafe condition 

identified 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 

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 AD. 

Costs of Compliance 

We estimate that this AD affects 3,769 

engines installed on airplanes of U.S. 

registry. 

We estimate the following costs to 

comply with this AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Inspect 3rd-stage wheels, P/N 23065818 ....... 1 work-hour × $85 per hour = $85 ................. $0 .................. $85 $288,320 

Replace 4th-stage wheel, P/N 23055944 or 

RR30000240.

0 work-hours × $85 per hour = $0 ................. 5,653 (prorated cost 

of part).

5,653 21,306,157 

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, 


sradovich on DSK3GMQ082PROD with RULES
Federal Register / Vol. 82, No. 173 / Friday, September 8, 2017 / Rules and Regulations 42445 

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 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 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 

removing Airworthiness Directive (AD) 

2015–02–22, Amendment 39–18090 (80 

FR 5452, February 2, 2015), and adding 

the following new AD: 

2017–18–14 Rolls-Royce Corporation: 

Amendment 39–19023; Docket No. 

FAA–2011–0961; Product Identifier 

2011–NE–22–AD. 

(a) Effective Date 

This AD is effective October 13, 2017. 

(b) Affected ADs 

This AD replaces Airworthiness Directive 

(AD) 2015–02–22, Amendment 39–18090 (80 

FR 5452, February 2, 2015). 

(c) Applicability 

This AD applies to Rolls-Royce 

Corporation (RRC) 250–C20, –C20B, –C20F, 

–C20J, –C20R, –C20R/1, –C20R/2, –C20R/4, 

–C20W, –C300/A1, and –C300/B1 turboshaft 

engines with either a 3rd-stage turbine wheel, 

part number (P/N) 23065818, or a 4th-stage 

turbine wheel, P/N 23055944 or RR30000240, 

installed. 

(d) Subject 

Joint Aircraft System Component (JASC) 

Code 7250, Turbine Section. 

(e) Unsafe Condition 

This AD was prompted by in-service 

turbine wheel blade failures that revealed the 

need for changes to the inspections of certain 

3rd-stage turbine wheels and removal from 

service of certain 4th-stage turbine wheels. 

We are issuing this AD to prevent failure of 

the 3rd-stage and 4th-stage turbine wheel 

blades, damage to the engine, and damage to 

the aircraft. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(1) Within 1,775 hours since last visual 

inspection and fluorescent-penetrant 

inspection (FPI) or before the next flight after 

the effective date of this AD, whichever 

occurs later: 

(i) Remove 3rd-stage turbine wheels, P/N 

23065818, and perform a visual inspection 

and an FPI on the removed turbine wheels 

for cracks at the trailing edge of the turbine 

blades, near the fillet at the rim. 

(ii) Thereafter, re-inspect the affected 

turbine wheels every 1,775 hours since last 

inspection (HSLI). 

(2) Any time the turbine is disassembled, 

perform a visual inspection and an FPI on 

3rd-stage turbine wheels, P/N 23065818, for 

cracks at the trailing edge of the turbine 

blades, near the fillet at the rim. 

(3) Do not return to service any turbine 

wheels found to have cracks at the trailing 

edge, near the fillet at the rim, of the turbine 

blades. 

(4) Within 1,775 HSLI, or at the next 

engine shop visit, whichever occurs later, 

remove 4th-stage turbine wheels, P/N 

23055944, from service. 

(5) Within 2,025 HSLI, or at the next 

engine shop visit, whichever occurs later, 

remove 4th-stage turbine wheels, P/N 

RR30000240, from service. 

(g) Definition 

For the purpose of this AD, an ‘‘engine 

shop visit’’ is the induction of an engine into 

the shop for maintenance involving the 

separation of pairs of major mating engine 

flanges, except that the separation of engine 

flanges solely for the purposes of 

transportation without subsequent engine 

maintenance does not constitute an engine 

shop visit. 

(h) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, FAA, Chicago 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 ACO Branch, send it 

to the attention of the person identified in 

paragraph (i) 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. 

(i) Related Information 

For more information about this AD, 

contact John Tallarovic, Aerospace Engineer, 

FAA, Chicago ACO Branch, Compliance and 

Airworthiness Division, 2300 E. Devon Ave., 

Des Plaines, IL 60018; phone: 847–294–8180; 

fax: 847–294–7834; email: john.m.tallarovic@

faa.gov. 

(j) Material Incorporated by Reference 

None. 

Issued in Burlington, Massachusetts, on 

August 31, 2017. 

Robert J. Ganley, 

Manager, Engine and Propeller Standards 

Branch, Aircraft Certification Service. 

[FR Doc. 2017–18910 Filed 9–7–17; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 71 

[Docket No. FAA–2016–9593; Airspace 

Docket No. 16–ACE–12] 

Amendment of Class E Airspace; Falls 

City, NE 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: This action modifies Class E 

airspace extending upward from 700 

feet above the surface at Brenner Field 


sradovich on DSK3GMQ082PROD with RULES