Federal Register / Vol. 82, No. 183 / Friday, September 22, 2017 / Proposed Rules 44353 

Issued in Washington, DC, on August 29, 

2017. 

Kathleen B. Hogan, 

Deputy Assistant Secretary for Energy 

Efficiency, Energy Efficiency and Renewable 

Energy. 

[FR Doc. 2017–20225 Filed 9–21–17; 8:45 am] 

BILLING CODE 6450–01–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2017–0896; Product 

Identifier 2017–SW–034–AD] 

RIN 2120–AA64 

Airworthiness Directives; Sikorsky 

Aircraft Corporation Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede 

airworthiness directive (AD) 2017–07– 

02 for Sikorsky Aircraft Corporation 

(Sikorsky) Model 269D and Model 269D 

Configuration A helicopters. AD 2017– 

07–02 currently requires reducing the 

life limit of and inspecting certain drive 

shafts. This proposed AD would retain 

the requirements of AD 2017–07–02 and 

propose repeating the inspections. The 

actions of this proposed AD are 

intended to detect and prevent an 

unsafe condition on these products. 

DATES: We must receive comments on 

this proposed AD by November 21, 

2017. 

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–2017– 

0896; 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 

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 proposed rule, 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 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: 

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. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to participate in this 

rulemaking by submitting written 

comments, data, or views. We also 

invite comments relating to the 

economic, environmental, energy, or 

federalism impacts that might result 

from adopting the proposals in this 

document. The most helpful comments 

reference a specific portion of the 

proposal, explain the reason for any 

recommended change, and include 

supporting data. To ensure the docket 

does not contain duplicate comments, 

commenters should send only one copy 

of written comments, or if comments are 

filed electronically, commenters should 

submit only one time. 

We will file in the docket all 

comments that we receive, as well as a 

report summarizing each substantive 

public contact with FAA personnel 

concerning this proposed rulemaking. 

Before acting on this proposal, we will 

consider all comments we receive on or 

before the closing date for comments. 

We will consider comments filed after 

the comment period has closed if it is 

possible to do so without incurring 

expense or delay. We may change this 

proposal in light of the comments we 

receive. 

Discussion 

On March 20, 2017, we issued a Final 

rule; request for comments to add AD 

2017–07–02, Amendment 39–18840 (82 

FR 15120, March 27, 2017) for 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. AD 2017–07–02 requires 

reducing the life limit of the drive shafts 

and performing several inspections of 

the drive shafts within 25 hours time-inservice (TIS). AD 2017–07–02 also 

specifies replacing the drive shaft 

assemblies as an optional terminating 

action for the requirements of the AD. 

AD 2017–07–02 was prompted by four 

incidents involving failure of the engine 

side drive shaft. The actions required by 

AD 2017–07–02 are intended to prevent 

failure of the drive shaft, loss of rotor 

drive, and subsequent loss of control of 

the helicopter. 

This NPRM would retain the 

requirements of AD 2017–07–02 but 

would require that some of the 

inspections be repeated every 100 hours 

TIS or 400 hours TIS. Repeating these 

inspections is necessary to detect and 

prevent the unsafe condition. Because 

these proposed requirements are for 

longer intervals, we are providing the 

public an opportunity to comment. 

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 these same 

type designs. 

Related Service Information 

We reviewed Appendix B to Sikorsky 

S–330 Model 269D Helicopter Basic 

Handbook of Maintenance Instructions 

No. CSP–D–2, dated February 1, 1993, 

and revised October 15, 2014; and 

Appendix B to Sikorsky S–333 Model 

269D Config. ‘‘A’’ Helicopter Basic 

Handbook of Maintenance Instructions 

No. CSP–D–9, dated July 20, 2001, and 

revised October 15, 2014. This service 

information specifies repetitive 

inspection procedures, overhaul and 

retirement schedules, and weight and 

balance procedures. The Airworthiness 

Limitations section, which is included 

in this service information, contains the 

life limits for drive shaft assembly P/Ns 

SKCP2738–5 and SKCP2738–7. 

We also reviewed Sikorsky 269D 

Helicopter Alert Service Bulletin DB– 

052, Basic Issue, dated January 16, 2014, 

which distributes the service life 

reduction information and implements a 

new 1,200-hour overhaul inspection for 

drive shaft assembly P/Ns SKCP2738–3, 

SKCP2738–5, and SKCP2738–7. 

44354 Federal Register / Vol. 82, No. 183 / Friday, September 22, 2017 / Proposed Rules 

Proposed AD Requirements 

This proposed AD would require, 

before further flight: 

• Removing from service any engine 

side drive shaft P/N SKCP2738–7 and 

pulley side drive shaft P/N SKCP2738– 

5 that has reached or exceeded its new 

life limit as follows: 

Æ 6,000 hours TIS for Model 269D 

helicopters; 

Æ 1,200 hours TIS for Model 269D 

Configuration A helicopters; and 

Æ 1,200 hours TIS if the parts have 

ever been interchanged between the two 

model configurations. 

This proposed AD would also require: 

• Within 25 hours TIS, and thereafter 

at intervals not to exceed 25 hours TIS, 

inspecting the lower pulley to engine 

alignment, and if there is any 

interference with the rotation of the belt 

drive alignment tool, adjusting the 

engine elevation alignment before 

further flight. 

• Within 25 hours TIS, and thereafter 

at intervals not to exceed 100 hours TIS, 

inspecting the KAflex drive shaft 

alignment and inspecting the engine 

side and pulley side drive shafts for a 

crack, any corrosion or pitting, a nick, 

a dent, and a scratch. 

• Within 25 hours TIS, and thereafter 

at intervals not to exceed 400 hours TIS, 

inspecting each joint for movement; 

inspecting each joint for fretting 

corrosion and each frame and mount 

bolt torque stripe for movement; and 

inspecting each joint for fretting, for a 

crack around both the bolt head and 

washer side, and around the nut and 

washer side, and each inside and 

outside corner radii and radii edges on 

both sides of each frame for a crack. 

If the drive shaft fails any of the above 

inspections, this proposed AD would 

require replacing both the engine side 

and pulley side drive shafts before 

further flight. 

This proposed AD also specifies 

installing KAflex engine side coupling 

assembly P/N SKCP2738–9 and KAflex 

pulley side coupling assembly P/N 

SKCP2738–101 as an optional 

terminating action for the requirements 

of this AD. 

Differences Between This Proposed AD 

and the Service Information 

The Sikorsky service information 

specifies a drive shaft assembly service 

life of 3,000 hours TIS with a 1,200 hour 

overhaul inspection for Model 269D 

Configuration A helicopters, while this 

proposed AD specifies a service life of 

1,200 hours TIS. 

The Sikorsky service information 

specifies different inspection 

procedures if there is spline engagement 

interference or resistance while 

inspecting the drive shaft alignment. 

This proposed AD specifies replacing 

both the engine side and pulley side 

drive shafts if there is any spline 

engagement interference or resistance. 

The Sikorsky service information 

specifies inspecting the working 

fastener condition without any specific 

succeeding action regarding the 

inspection. This proposed AD specifies 

replacing both the engine side and 

pulley side drive shafts if there is any 

joint movement. 

The Sikorsky service information 

specifies returning the drive shaft 

assembly to Sikorsky if there is fretting 

dust or red metallic residue at a joint. 

This proposed AD specifies replacing 

both the engine side and pulley side 

drive shafts if there is any fretting 

corrosion. 

Costs of Compliance 

We estimate that this proposed AD 

would affect 18 helicopters of U.S. 

Registry. We estimate that operators 

may incur the following costs in order 

to comply with this AD. Labor costs are 

estimated at $85 per work-hour. 

Removing the engine side and pulley 

side drive shafts that have reached the 

new life limit would take about 4 workhours for a cost of $340 per helicopter. 

Inspecting the lower pulley to engine 

alignment using the belt alignment tool 

would take about 0.5 work-hour for an 

estimated cost of $43 per helicopter and 

$774 for the U.S. fleet per inspection 

cycle. Adjusting the engine elevation 

alignment would take about 0.5 workhour for an estimated cost of $43 per 

helicopter. Inspecting the drive shaft 

alignment by checking spline 

engagement would take about 1 workhour for a cost of $85 per helicopter and 

$1,530 for the U.S. fleet per inspection 

cycle. Inspecting the drive shafts for 

damage would take about 1 work-hour 

for an estimated cost of $85 per 

helicopter and $1,530 for the U.S. fleet 

per inspection cycle. Inspecting the 

joints would take about 1 work-hour for 

an estimated cost of $85 per helicopter 

and $1,530 for the U.S. fleet per 

inspection cycle. Replacing the engine 

side and pulley side drive shafts, if 

required, would take about 8 workhours and parts would cost about 

$20,000, for an estimated cost of 

$20,680 per helicopter. 

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 

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, 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. 

We prepared an economic evaluation 

of the estimated costs to comply with 

this proposed 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. 

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 

removing Airworthiness Directive (AD) 

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