This section of the FEDERAL REGISTER

contains notices to the public of the proposed

issuance of rules and regulations. The

purpose of these notices is to give interested

persons an opportunity to participate in the

rule making prior to the adoption of the final

rules.

Proposed Rules Federal Register

34070 

Vol. 83, No. 139 

Thursday, July 19, 2018 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2018–0368; Product 

Identifier 2018–NE–12–AD] 

RIN 2120–AA64 

Airworthiness Directives; Pratt & 

Whitney Division (PW) 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 all Pratt 

& Whitney Division (PW) PW4074D, 

PW4077D, PW4084D, PW4090, and 

PW4090–3 turbofan engines with a low 

pressure compressor (LPC) fan hub, part 

number (P/N) 51B821 or P/N 52B521, 

installed. This proposed AD was 

prompted by updated low cycle fatigue 

analysis techniques that indicate certain 

LPC fan hubs could crack prior to their 

published life limit. This proposed AD 

would require repetitive eddy current 

inspections (ECIs) and fluorescent 

penetrant inspections (FPIs) for cracks 

in certain LPC fan hubs and removal of 

hubs from service that fail inspection. 

We are proposing this AD to address the 

unsafe condition on these products. 

DATES: We must receive comments on 

this proposed AD by September 4, 2018. 

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 W12–140, 1200 New Jersey 

Avenue SE, Washington, DC 20590. 

• Hand Delivery: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this NPRM, contact Pratt & Whitney 

Division, 400 Main St., East Hartford, 

CT 06118; phone: 800–565–0140; fax: 

860–565–5442. You may view this 

service information at the FAA, Engine 

and Propeller Standards Branch, 1200 

District Avenue, Burlington, MA 01803. 

For information on the availability of 

this material at the FAA, call 781–238– 

7759. 

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–2018– 

0368; 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 NPRM, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for Docket Operations 

(phone: 800–647–5527) is listed above. 

Comments will be available in the AD 

docket shortly after receipt. 

FOR FURTHER INFORMATION CONTACT: JoAnn Theriault, Aerospace Engineer, 

ECO Branch, FAA, 1200 District 

Avenue, Burlington, MA 01803; phone: 

781–238–7105; fax: 781–238–7199; 

email: jo-ann.theriault@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposal. Send your comments to 

an address listed under the ADDRESSES

section. Include ‘‘Docket No. FAA– 

2018–0368; Product Identifier 2018– 

NE–12–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 we receive 

about this NPRM. 

Discussion 

We received information concerning 

an updated analysis by the engine 

manufacturer, which indicated certain 

triple-bore LPC fan hubs installed in 

high-thrust models of the PW4000–112′′ 

series turbofan engine could crack prior 

to their published life limit. This 

proposed AD would add additional 

inspections of affected triple-bore LPC 

fan hubs until they are removed from 

service and replaced with a part eligible 

for installation. This condition, if not 

addressed, could result in fatigue 

cracking of the LPC fan hub, 

uncontained hub failure, damage to the 

engine, and damage to the airplane. 

Related Service Information Under 1 

CFR Part 51 

We reviewed PW Alert Service 

Bulletin (ASB) PW4G–112–A72–351, 

dated February 22, 2018. This PW ASB 

describes procedures for performing 

LPC fan hub ECIs and FPIs. 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 PW PW4000 Series 112 

Inch Turbofan Engines Cleaning, 

Inspection and Repair (CIR) Manual, P/ 

N 51A750, Chapter/Section 72–31–07, 

Inspection/Check-02, Revision No. 76, 

dated March 15, 2018. The CIR Manual 

contains additional information 

regarding FPI and ECI of the LPC fan 

hub. 

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 the same 

type design. 

Proposed AD Requirements 

This proposed AD would require 

repetitive ECIs and FPIs of the LPC fan 

hub. 

Costs of Compliance 

We estimate that this proposed AD 

affects 32 engines installed on airplanes 

of U.S. registry. We estimate the 

following costs to comply with this 

proposed AD: 


sradovich on DSK3GMQ082PROD with PROPOSALS
Federal Register / Vol. 83, No. 139 / Thursday, July 19, 2018 / Proposed Rules 34071 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Pro-rated part cost .......................................... 0 work-hours × $85 per hour = $0 ................. $288,000 $288,000 $288,000 

Inspection ........................................................ 40 work-hours × $85 per hour = $3,400 ........ 0 3,400 108,800 

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 

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, 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): 

Pratt & Whitney Division: Docket No. FAA– 

2018–0368; Product Identifier 2018–NE– 

12–AD. 

(a) Comments Due Date 

We must receive comments by September 

4, 2018. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to all Pratt & Whitney 

Division (PW) PW4074D, PW4077D, 

PW4084D, PW4090, and PW4090–3 turbofan 

engines with low-pressure compressor (LPC) 

fan hub, part number (P/N) 51B821 or P/N 

52B521, installed. 

(d) Subject 

Joint Aircraft System Component (JASC) 

Code 7230, Turbine Engine Compressor 

Section. 

(e) Unsafe Condition 

This AD was prompted by low cycle 

fatigue analysis techniques, updated by the 

engine manufacturer, which indicated certain 

LPC fan hubs could crack prior to their 

published life limit. We are issuing this AD 

to prevent failure of the LPC fan hub. The 

unsafe condition, if not addressed, could 

result in uncontained hub release, damage to 

the engine, and damage to the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Required Actions 

(1) After the effective date of this AD, 

perform a fluorescent penetrant inspection 

(FPI) and eddy current inspection (ECI) of the 

LPC fan hub the next time the engine is 

separated at the M-flange and the LPC fan 

hub has accumulated 2,000 or more flight 

cycles since the last FPI and ECI. 

(2) Thereafter, perform an FPI and an ECI 

of the LPC fan hub every time the engine is 

separated at the M-flange and the LPC fan 

hub has accumulated 2,000 or more flight 

cycles since the last LPC fan hub ECI and FPI 

inspections. 

(3) Use the Accomplishment Instructions, 

Step No. 11, in PW Alert Service Bulletin 

PW4G–112–A72–351, dated February 22, 

2018, to do the eddy current inspections. 

(4) If a crack is found during the 

inspections required by paragraphs (g)(1) or 

(2) of this AD, remove the LPC fan hub from 

service before further flight and replace with 

a part eligible for installation. 

(h) 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 (i)(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. 

(i) Related Information 

(1) For more information about this AD, 

contact Jo-Ann Theriault, Aerospace 

Engineer, ECO Branch, FAA, 1200 District 

Avenue, Burlington, MA 01803; phone: 781– 

238–7105; fax: 781–238–7199; email: joann.theriault@faa.gov. 

(2) For service information identified in 

this AD, contact Pratt & Whitney Division, 

400 Main St., East Hartford, CT 06118; 

phone: 800–565–0140; fax: 860–565–5442. 

You may view this referenced service 

information at the FAA, Engine and Propeller 

Standards Branch, 1200 District Avenue, 

Burlington, MA 01803. For information on 

the availability of this material at the FAA, 

call 781–238–7759. 


sradovich on DSK3GMQ082PROD with PROPOSALS
34072 Federal Register / Vol. 83, No. 139 / Thursday, July 19, 2018 / Proposed Rules 

Issued in Burlington, Massachusetts, on 

July 12, 2018. 

Robert J. Ganley, 

Acting Manager, Engine and Propeller 

Standards Branch, Aircraft Certification 

Service. 

[FR Doc. 2018–15291 Filed 7–18–18; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2018–0648; Product 

Identifier 2017–SW–087–AD] 

RIN 2120–AA64 

Airworthiness Directives; Leonardo 

S.p.A. Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for 

Leonardo S.p.A. (Leonardo) Model 

AB139 and AW139 helicopters. This 

proposed AD would require replacing 

screws installed on the left and right 

main landing gear (MLG) shock absorber 

assembly. This proposed AD is 

prompted by a report that some screws 

may have been manufactured without 

meeting specifications. The actions of 

this proposed AD are intended to 

correct an unsafe condition on these 

helicopters. 

DATES: We must receive comments on 

this proposed AD by September 17, 

2018. 

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–2018– 

0648; 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 proposed 

AD, the European Aviation Safety 

Agency (EASA) AD, the economic 

evaluation, any comments received, and 

other information. The street address for 

Docket Operations (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 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.leonardocompany.com/-/bulletins. 

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: 

David Hatfield, Aviation Safety 

Engineer, Safety Management Section, 

Rotorcraft Standards Branch, FAA, 

10101 Hillwood Pkwy., Fort Worth, TX 

76177; telephone (817) 222–5110; email 

david.hatfield@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 

EASA, which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA AD No. 2016– 

077, dated April 19, 2016, to correct an 

unsafe condition for Finmeccanica 

S.p.A. (previously Agusta) Model 

AB139 and AW139 helicopters if 

equipped with kit ‘‘Increased Gross 

Weight 6800 kg’’ part number (P/N) 

4G0000F00111 (kit). EASA advises of a 

manufacturing issue with the standard 

screws (P/N NAS1351–5H12P) installed 

on MLG shock absorber assembly P/N 

1652B0000–01. According to EASA, a 

material analysis shows that the MLG 

shock absorber screws may have a lower 

fatigue life than the screws used during 

the certification fatigue tests. EASA 

states the affected MLG units have been 

identified by serial number. EASA also 

advises that this unsafe condition, if not 

detected and corrected, could result in 

failure of the MLG shock absorber, 

collapse or retraction of the MLG, and 

subsequent damage to the helicopter 

and injury to occupants. 

To correct this condition, the EASA 

AD requires replacing each standard 

screw with a new screw P/N 

1652A0001–01 and re-identifying the 

serial number of each MLG shock 

absorber assembly that has the new 

screw installed, and prohibits installing 

any affected MLG shock absorber 

assembly unless the screw has been 

replaced. 

FAA’s Determination 

These helicopters have been approved 

by the aviation authority of Italy and are 

approved for operation in the United 

States. Pursuant to our bilateral 

agreement with Italy, EASA, its 

technical representative, has notified us 

of the unsafe condition described in its 

AD. We are proposing this AD because 

we evaluated all known relevant 

information and determined that an 

unsafe condition is likely to exist or 

develop on other products of the same 

type design. 

Related Service Information 

We reviewed Finmeccanica Bollettino 

Tecnico No. 139–397, dated April 7, 

2016, which contains procedures for 

replacing the standard screws installed 

on the left and right MLG assembly and 

for re-identifying the MLG shock 

absorber assembly P/N and the MLG 

assembly S/N. 

Proposed AD Requirements 

This proposed AD would require 

replacing each standard screw P/N 

NAS1351–5H12P with a screw P/N 

1652A0001–01 and re-identifying the 

serial number of the MLG assembly 

within the following compliance times: 


sradovich on DSK3GMQ082PROD with PROPOSALS