Federal Register / Vol. 82, No. 183 / Friday, September 22, 2017 / Proposed Rules 44355 

2017–07–02, Amendment 39–18840 (82 

FR 15120, March 27, 2017), and adding 

the following new AD: 

Sikorsky Aircraft Corporation (Sikorsky): 

Docket No. FAA–2017–0896; Product 

Identifier 2017–SW–034–AD. 

(a) Applicability 

This AD applies to Sikorsky Model 269D 

and Model 269D Configuration A helicopters 

with a KAflex engine side drive shaft part 

number (P/N) SKCP2738–7 and KAflex 

pulley side drive shaft P/N SKCP2738–5 

installed, certificated in any category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as 

failure of a drive shaft. This condition could 

result in loss of rotor drive and subsequent 

loss of control of the helicopter. 

(c) Affected ADs 

This AD supersedes AD 2017–07–02, 

Amendment 39–18840 (82 FR 15120, March 

27, 2017). 

(d) Comments Due Date 

We must receive comments by November 

21, 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 

(1) Before further flight: 

(i) For Model 269D helicopters, remove 

from service any KAflex engine side drive 

shaft P/N SKCP2738–7 and any KAflex 

pulley side drive shaft P/N SKCP2738–5 that 

has 6,000 or more hours time-in-service 

(TIS). Thereafter, remove from service any 

KAflex engine side drive shaft P/N 

SKCP2738–7 and any KAflex pulley side 

drive shaft P/N SKCP2738–5 before 

accumulating 6,000 hours TIS. 

(ii) For Model 269D Configuration A 

helicopters, remove from service any KAflex 

engine side drive shaft P/N SKCP2738–7 and 

any KAflex pulley side drive shaft P/N 

SKCP2738–5 that has 1,200 or more hours 

TIS. Thereafter, remove from service any 

KAflex engine side drive shaft P/N 

SKCP2738–7 and any KAflex pulley side 

drive shaft P/N SKCP2738–5 before 

accumulating 1,200 hours TIS. 

(iii) If interchanged between Model 269D 

and Model 269D Configuration A helicopters, 

remove from service any KAflex engine side 

drive shaft P/N SKCP2738–7 and any KAflex 

pulley side drive shaft P/N SKCP2738–5 that 

has 1,200 or more hours TIS. Thereafter, if 

interchanged between Model 269D and 

Model 269D Configuration A helicopters, 

remove from service any KAflex engine side 

drive shaft P/N SKCP2738–7 and any KAflex 

pulley side drive shaft P/N SKCP2738–5 

before accumulating 1,200 hours TIS. 

(2) Within 25 hours TIS, and thereafter at 

intervals not to exceed 25 hours TIS, using 

a belt drive alignment tool 269T3303–003, 

inspect the lower pulley to engine alignment 

by engaging the tool on the drive shaft and 

inserting in the lower pulley bore. Rotate the 

tool 360° around the drive shaft and inspect 

for interference. If there is any interference 

with the rotation of the tool, before further 

flight, adjust the engine elevation alignment 

to eliminate the interference. 

(3) Within 25 hours TIS, and thereafter at 

intervals not to exceed 100 hours TIS: 

(i) Remove the drive shaft to adapter bolt 

and inspect the drive shaft alignment. Engage 

and disengage the splines a minimum of 3 

times by sliding the engine power output 

shaft in and out of the engine. Inspect the 

alignment at each 90° interval by rotating the 

lower pulley with the power shaft 

disengaged. Determine whether the adapter 

slides on and off the drive shaft splines 

without spline engagement interference or 

resistance along the entire length of 

movement. If there is any spline engagement 

interference or resistance, before further 

flight, replace both the engine side and 

pulley side drive shafts. 

(ii) Inspect each drive shaft for a crack, any 

corrosion or pitting, a nick, a dent, and a 

scratch. If there is a crack, any corrosion or 

pitting, a nick, a dent, or a scratch that 

exceeds allowable limits, before further 

flight, replace both the engine side and 

pulley side drive shafts. 

(4) Within 25 hours TIS, and thereafter at 

intervals not to exceed 400 hours TIS, 

remove the engine side drive shaft and pulley 

side drive shaft and perform the following: 

(i) Inspect each flex frame (frame) bolted 

joint (joint) for movement by hand. If there 

is any movement, before further flight, 

replace both the engine side and pulley side 

drive shafts. 

(ii) Visually inspect each joint for fretting 

corrosion (which might be indicated by 

metallic particles) and each frame and mount 

bolt torque stripe for movement. If there is 

any fretting corrosion or torque stripe 

movement, before further flight, replace both 

the engine side and pulley side drive shafts. 

(iii) Using a 10x or higher power 

magnifying glass, visually inspect each joint 

for fretting and for a crack around the bolt 

head and washer side, and around the nut 

and washer side. Also inspect both sides of 

each frame for a crack on the inside and 

outside corner radii and radii edge (four). If 

there is any fretting, a crack at any point over 

the full circumference (360°) of the bolt head 

and washer side or the nut and washer side, 

or a crack in any of the corner radii edges, 

before further flight, replace both the engine 

side and pulley side drive shafts. 

(5) As an optional terminating action to the 

repetitive inspections in this AD, you may 

install KAflex engine side drive shaft P/N 

SKCP2738–9 and KAflex pulley side drive 

shaft P/N SKCP2738–101. 

(g) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Boston ACO Branch, 

FAA, may approve AMOCs for this AD. Send 

your proposal to: Michael Schwetz, Aviation 

Safety Engineer, Boston ACO Branch, 

Compliance and Airworthiness Division, 

FAA, 1200 District Avenue, Burlington, 

Massachusetts 01803; telephone (781) 238– 

7761; email michael.schwetz@faa.gov. 

(2) For operations conducted under a 14 

CFR part 119 operating certificate or under 

14 CFR part 91, subpart K, we suggest that 

you notify your principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office or 

certificate holding district office before 

operating any aircraft complying with this 

AD through an AMOC. 

(h) Additional Information 

Appendix B of Sikorsky S–330 Model 269D 

Helicopter Basic Handbook of Maintenance 

Instructions, No. CSP–D–2, dated February 1, 

1993, and revised October 15, 2014; 

Appendix B of Sikorsky S–330 Model 269D 

Config. ‘‘A’’ Helicopter Basic Handbook of 

Maintenance Instructions, No. CSP–D–9, 

dated July 20, 2001, and revised October 15, 

2014; and Sikorsky 269D Helicopter Alert 

Service Bulletin DB–052, Basic Issue, dated 

January 16, 2014, which are not incorporated 

by reference, contain additional information 

about the subject of this AD. For service 

information identified in this AD, contact 

Sikorsky Aircraft Corporation, Customer 

Service Engineering, 124 Quarry Road, 

Trumbull, CT 06611; telephone 1–800– 

Winged–S or 203–416–4299; email wcs_cust_

service_eng.gr-sik@lmco.com. You may 

review the service information at the FAA, 

Office of the Regional Counsel, Southwest 

Region, 10101 Hillwood Pkwy., Room 6N– 

321, Fort Worth, TX 76177. 

(i) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6310, Engine/Transmission Coupling. 

Issued in Fort Worth, Texas, on September 

11, 2017. 

Lance T. Gant, 

Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2017–19945 Filed 9–21–17; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2017–0658; Product 

Identifier 2017–NE–20–AD] 

RIN 2120–AA64 

Airworthiness Directives; GE Aviation 

Czech s.r.o. Turboprop 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 

GE Aviation Czech s.r.o. M601D–11, 

M601E–11, M601E–11A, M601E–11AS, 

M601E–11S, and M601F turboprop 

engines. This proposed AD was 

prompted by a review that determined 

that certain power turbine (PT) rotors 

have less overspeed margin than 

originally declared during product 

44356 Federal Register / Vol. 82, No. 183 / Friday, September 22, 2017 / Proposed Rules 

certification. This proposed AD would 

require removal of the affected PT disks. 

We are proposing this AD to correct the 

unsafe condition on these products. 

DATES: We must receive comments on 

this NPRM by November 6, 2017. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

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

instructions for submitting comments. 

• Mail: Docket Management Facility, 

U.S. Department of Transportation, 1200 

New Jersey Avenue SE., West Building 

Ground Floor, Room W12–140, 

Washington, DC 20590–0001. 

• Hand Delivery: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

• Fax: 202–493–2251. 

For service information identified in 

this proposed AD, contact GE Aviation 

Czech s.r.o., Beranovy ́ch 65, 199 02 

Praha 9—Letnˇ any, Czech Republic; 

phone: +420 222 538 111; fax: +420 222 

538 222. You may view this service 

information at the FAA, Engine and 

Propeller Standards Branch, 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–2017– 

0658; 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 proposed AD, the 

mandatory continuing airworthiness 

information (MCAI), the regulatory 

evaluation, any comments received, and 

other information. The 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: 

Robert Green, Aerospace Engineer, ECO 

Branch, FAA, 1200 District Avenue, 

Burlington, MA 01803; phone: 781– 

238–7754; fax: 781–238–7199; email: 

robert.green@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– 

2017–0658; Directorate Identifier 2017– 

NE–20–AD’’ at the beginning of your 

comments. We specifically invite 

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 with FAA 

personnel concerning this NPRM. 

Discussion 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA AD 2017– 

0100, dated June 8, 2017 (referred to 

hereinafter as ‘‘the MCAI’’), to correct an 

unsafe condition for the specified 

products. The MCAI states: 

It was identified during a recent design 

review that power turbine (PT) rotors with 

certain disks, part number (P/N) M601– 

3220.6 and P/N M601–3220.7, have a 

reduction in the declared theoretical PT rotor 

overspeed limit. 

This condition, if not corrected, may lead 

to high energy debris release in case of PT 

rotor overspeed occurrence, possibly 

resulting in damage to, and/or reduced 

control of, the aeroplane. 

You may obtain further information 

by examining the MCAI in the AD 

docket on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2017– 

0658. 

Related Service Information 

GE Aviation Czech s.r.o. has issued 

Alert Service Bulletin (ASB) No. ASB– 

M601E–72–50–00–0069, ASB–M601D– 

72–50–00–0052, ASB–M601F–72–50– 

00–0035, ASB–M601T–72–50–00–0028, 

and ASB–M601Z–72–50–00–0038, 

(single document), dated February 21, 

2017. The ASB describe procedures for 

replacing the PT disk. 

FAA’s Determination and Requirements 

of This Proposed AD 

This product has been approved by 

the aviation authority of Czech 

Republic, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with the European 

Community, EASA has notified us of 

the unsafe condition described in the 

MCAI and service information 

referenced above. We are proposing this 

AD because we evaluated all 

information provided by EASA and 

determined the unsafe condition exists 

and is likely to exist or develop on other 

products of the same type design. This 

proposed AD would require removal of 

the affected PT disks. 

Costs of Compliance 

We estimate that this proposed AD 

affects 50 engines installed on airplanes 

of U.S. registry. 

We estimate the following costs to 

comply with this proposed AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Disk removal and replacement ....................... 56 work-hours × $85 per hour = $4,760 ........ $6,989 $14,749 $587,450 

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 

Federal Register / Vol. 82, No. 183 / Friday, September 22, 2017 / Proposed Rules 44357 

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): 

GE Aviation Czech s.r.o. (Type Certificate 

previously held by WALTER Engines 

a.s., Walter a.s., and MOTORLET a.s.): 

Docket No. FAA–2017–0658; Product 

Identifier 2017–NE–20–AD. 

(a) Comments Due Date 

We must receive comments by November 

6, 2017. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to certain GE Aviation 

Czech s.r.o. M601D–11, M601E–11, M601E– 

11A, M601E–11AS, M601E–11S, and M601F 

turboprop engines, with power turbine (PT) 

rotor disks, part number (P/N) M601–3220.6 

or P/N M601–3220.7, installed. 

(d) Subject 

Joint Aircraft System Component (JASC) 

Code 7250, Turbine Section. 

(e) Reason 

This AD was prompted by a review that 

determined that PT rotors with certain disks, 

P/N M601–3220.6 or P/N M601–3220.7, have 

less overspeed margin than originally 

declared during product certification. We are 

issuing this AD to prevent failure of the PT 

rotor, uncontained release of the PT rotor 

disk, damage to the engine, and damage to 

the airplane. 

(f) Compliance 

(1) Comply with this AD within the 

compliance times specified, unless already 

done. 

(2) After the effective date of this AD, 

remove the affected PT disk from service 

during the next engine shop visit, or within 

5 years, whichever occurs first. 

(g) Installation Prohibition 

After the effective date of this AD, do not 

install an affected PT disk on any engine. 

(h) Definition 

For the purpose of this AD, an engine shop 

visit is when an engine is overhauled or 

rebuilt. 

(i) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, ECO 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)(1) of this AD. You 

may email your request to: ANE-AD-AMOC@

faa.gov. 

(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 Robert Green, Aerospace Engineer, 

ECO Branch, FAA, 1200 District Avenue, 

Burlington, MA 01803; phone: 781–238– 

7754; fax: 781–238–7199; email: 

robert.green@faa.gov. 

(2) Refer to MCAI European Aviation 

Safety Agency AD 2017–0100, dated June 8, 

2017, for more information. You may 

examine the MCAI in the AD docket on the 

Internet at http://www.regulations.gov by 

searching for and locating it in Docket No. 

FAA–2017–0658. 

(3) GE Aviation Czech s.r.o. Alert Service 

Bulletin No. ASB–M601E–72–50–00–0069, 

ASB–M601D–72–50–00–0052, ASB–M601F– 

72–50–00–0035, ASB–M601T–72–50–00– 

0028, and ASB–M601Z–72–50–00–0038, 

(single document), dated February 21, 2017, 

can be obtained from GE Aviation Czech 

s.r.o, using the contact information in 

paragraph (j)(4) of this proposed AD. 

(4) For service information identified in 

this proposed AD, contact GE Aviation Czech 

s.r.o., Beranovy ́ch 65, 199 02 Praha 9— 

Letnˇ any, Czech Republic; phone: +420–222– 

538–111; fax: +420–222–538–222. 

(5) You may view this service information 

at the FAA, Engine and Propeller Standards 

Branch, 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 13, 2017. 

Robert J. Ganley, 

Manager, Engine and Propeller Standards 

Branch, Aircraft Certification Service. 

[FR Doc. 2017–19969 Filed 9–21–17; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2017–0750; Product 

Identifier 2017–NE–24–AD] 

RIN 2120–AA64 

Airworthiness Directives; Rolls-Royce 

Corporation Turbofan 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 

Rolls-Royce Corporation (RRC) AE 

3007A and AE 3007C model turbofan 

engines. This proposed AD was 

prompted by an updated analysis that 

lowered the life limit of fan wheels 

installed on the affected engines. This 

proposed AD would require removal of 

the affected fan wheel at new, lower life 

limits. We are proposing this AD to 

address the unsafe condition on these 

products. 

DATES: We must receive comments on 

this proposed AD by November 6, 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