Federal Register / Vol. 81, No. 246 / Thursday, December 22, 2016 / Proposed Rules 93855 

based on mortality rates for annuitants 

paid from the Civil Service Retirement 

and Disability Fund; and increases each 

year at an assumed rate of cost-of-living 

adjustment. Assumed rates of interest, 

mortality, and cost-of-living adjustments 

used in computing the present value are 

those used by the Board of Actuaries of 

the Civil Service Retirement System for 

valuation of the Federal Employees’ 

Retirement System based on dynamic 

assumptions. The present value factors 

are unisex factors obtained as a 

composite of sex-distinct present value 

factors. Separate present value factors 

apply for FERS annuities that receive 

cost-of-living adjustments before the 

retiree attains age 62, versus FERS 

annuities that do not receive cost-ofliving adjustments before the retiree 

attains age 62. 

* * * * * 

■ 21. Add § 842.616 to subpart F to read 

as follows: 

§ 842.616 Publication of present value 

factors. 

When OPM publishes in the Federal 

Register notice of normal cost 

percentages under § 841.407 of this 

chapter, it will also publish updated 

present value factors. 

■ 22. Amend § 842.702 by revising the 

definition of ‘‘present value factor’’ to 

read as follows: 

§ 842.702 Definitions. 

* * * * * 

Present value factor has the same 

meaning in this subpart as defined in 

§ 842.602. 

* * * * * 

PART 847—ELECTIONS OF 

RETIREMENT COVERAGE BY 

CURRENT AND FORMER EMPLOYEES 

OF NONAPPROPRIATED FUND 

INSTRUMENTALITIES 

■ 23. The authority citation for part 847 

continues to read as follows: 

Authority: 5 U.S.C. 8332(b)(17) and 

8411(b)(6) and sections 1131 and 1132 of 

Pub. L. 107–107, December 28, 2001, 115 Stat 

1242; 5 U.S.C. 8347(a) and 8461(g) and 

section 1043(b) of Pub. L. 104–106, Div. A, 

Title X, Feb. 10, 1996, 110 Stat. 434. Subpart 

B also issued under 5 U.S.C. 8347(q) and 

8461(n). 

Subpart A—General Provisions 

■ 24. Amend § 847.103(b) by revising 

the definition of ‘‘actuarial present 

value’’ and adding the definition of 

‘‘present value factor’’ in alphabetical 

order as follows: 

§ 847.103 Definitions. 

* * * * * 

(b) * * * 

Actuarial present value means the 

amount of monthly annuity at time of 

retirement multiplied by the applicable 

present value factor. 

* * * 

Present value factor has the same 

meaning in this part as defined in 

§ 842.602. 

* * * * * 

§ 847.602 [Removed and Reserved] 

■ 25. Remove and reserve § 847.602. 

[FR Doc. 2016–30487 Filed 12–21–16; 8:45 am] 

BILLING CODE 6325–38–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0740; Directorate 

Identifier 2013–NE–24–AD] 

RIN 2120–AA64 

Airworthiness Directives; Pratt & 

Whitney Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede 

Airworthiness Directive (AD) 2014–05– 

32, which applies to all Pratt & Whitney 

(PW) PW2037, PW2037D, PW2037M, 

PW2040, PW2040D, PW2043, PW2143, 

PW2643, and F117–PW–100 turbofan 

engines. AD 2014–05–32 currently 

requires one-time eddy current 

inspection (ECI) of affected engines with 

certain diffuser and HPT cases installed. 

AD 2014–05–32 also requires a 

fluorescent-penetrant inspection (FPI) of 

the diffuser case rear flange and the HPT 

case front flange. Since we issued AD 

2014–05–32, the manufacturer 

determined through analysis that the 

inspections required by AD 2014–05–32 

are not adequate to maintain safety. This 

proposed AD would add additional 

repetitive, on-wing ECI inspections. We 

are proposing this AD to correct the 

unsafe condition on these products. 

DATES: We must receive comments on 

this proposed AD by February 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 

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, 

400 Main St., East Hartford, CT 06108; 

phone: 860–565–8770; fax: 860–565– 

4503. 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. 

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–2013– 

0740; 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 proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street 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: 

Brian Kierstead, Aerospace Engineer, 

Engine Certification Office, FAA, Engine 

& Propeller Directorate, 1200 District 

Avenue, Burlington, MA 01803; phone: 

781–238–7772; fax: 781–238–7199; 

email: brian.kierstead@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2013–0740; Directorate Identifier 

2013–NE–24–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD 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 proposed AD. 


Lhorne on DSK30JT082PROD with PROPOSALS
93856 Federal Register / Vol. 81, No. 246 / Thursday, December 22, 2016 / Proposed Rules 

Discussion 

On March 6, 2014, we issued AD 

2014–05–32, Amendment 39–17804 (79 

FR 17856, March 31, 2014), (‘‘AD 2014– 

05–32’’), for all PW PW2037, PW2037D, 

PW2037M, PW2040, PW2040D, 

PW2043, PW2143, PW2643, and F117– 

PW–100 turbofan engines. AD 2014–05– 

32 requires a one-time ECI of affected 

engines with certain diffuser and HPT 

cases installed. AD 2014–05–32 also 

requires an FPI of the diffuser case rear 

flange and HPT case front flange. AD 

2014–05–32 resulted from a rupture of 

the diffuser-to-HPT case flange. We 

issued AD 2014–05–32 to prevent 

failure of the diffuser-to-HPT case 

flange, which could lead to uncontained 

engine failure and damage to the 

airplane. 

Actions Since AD 2014–05–32 Was 

Issued 

Since we issued AD 2014–05–32, the 

manufacturer identified a subpopulation 

of diffuser cases installed on the 

affected engines with a repaired flange 

that has a lower fatigue capability. The 

repaired flange cannot be distinguished 

from non-repaired flanges on diffuser 

cases installed on the affected engines. 

We determined, therefore, that the 

inspections required by AD 2014–05–32 

are not adequate to maintain safety. To 

correct this unsafe condition, we are 

now proposing additional, repetitive 

ECI inspections. 

Related Service Information Under 1 

CFR Part 51 

We reviewed PW Service Bulletin No. 

PW2000 72–763, Revision No. 1, dated 

August 30, 2013; and PW Alert Service 

Bulletin No. PW2000 A72–765, Revision 

No. 1, dated July 13, 2016. This service 

information describes procedures for a 

one-time ECI inspection of the engine 

diffuser case and the HPT case, and 

repetitive on-wing ECIs of the engine 

diffuser case assembly, respectively. 

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. 

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 retain the 

requirements of AD 2014–05–32 except 

it would eliminate the Prohibition 

Statement. We determined that this 

statement is unnecessary for compliance 

with the AD. In addition, this proposed 

AD would require repetitive, on-wing 

ECI inspections. This proposed AD 

would also remove the PW2240 and 

PW2337 engines from the applicability 

section since these engines were 

removed from PW Type Certificate 

Number E17NE. 

Costs of Compliance 

We estimate that this proposed AD 

will affect 910 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 

On-wing/module ECI Inspection.8 work-hours × $85 per hour 

= $680.

$0 $680 ....................................... $230,520 per inspection 

cycle. 

FPI Inspection ........................ 3 work-hours × $85 per hour 

= $255.

20 $275 per inspection cycle ...... $250,250 per inspection 

cycle. 

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 have 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 that the 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 

removing Airworthiness Directive (AD) 

2014–05–32, Amendment 39–17804 (79 

FR 17856, March 31, 2014), and adding 

the following new AD: 

Pratt & Whitney: Docket No. FAA–2013– 

0740; Directorate Identifier 2013–NE– 

24–AD. 

(a) Comments Due Date 

The FAA must receive comments on this 

AD action by February 6, 2017. 


Lhorne on DSK30JT082PROD with PROPOSALS
Federal Register / Vol. 81, No. 246 / Thursday, December 22, 2016 / Proposed Rules 93857 

(b) Affected ADs 

This AD replaces AD 2014–05–32, 

Amendment 39–17804 (79 FR 17856, March 

31, 2014). 

(c) Applicability 

This AD applies to all Pratt & Whitney 

(PW) PW2037, PW2037D, PW2037M, 

PW2040, PW2040D, PW2043, PW2143, 

PW2643, and F117–PW–100 turbofan 

engines. 

(d) Subject 

Joint Aircraft System Component (JASC) 

Code 72, Turbine/Turboprop Engine. 

(e) Unsafe Condition 

This AD was prompted by a rupture of the 

diffuser-to-high-pressure turbine (HPT) case 

flange. We are issuing this AD to prevent 

failure of the diffuser-to-HPT case flange, 

which could lead to uncontained engine 

failure and damage to the airplane. 

(f) Compliance 

Unless already done, comply with this AD 

within the compliance times specified. 

(1) For diffuser case, part number (P/N) 

1B7461, serial numbers (S/Ns) DGGUAK1306 

and DGGUAK1308, and HPT case, P/N 

1B2440, S/N DKLBCS1032: 

(i) Within 100 flight cycles or 30 days after 

May 5, 2014, whichever is later, eddy current 

inspect the diffuser case and the HPT case Mflange. Use PW Service Bulletin (SB) No. 

PW2000 72–763, Revision No. 1, dated 

August 30, 2013, to do the inspection. 

(ii) Reserved. 

(2) For all diffuser and HPT cases, at the 

next piece-part opportunity and every piecepart opportunity thereafter, perform a high 

sensitivity fluorescent-penetrant inspection 

(FPI) of the entire diffuser case rear flange 

(M-flange) and bolt holes, and the entire HPT 

case forward flange (M-flange) and bolt holes. 

(3) For diffuser cases that have not 

incorporated PW SB PW2000–72–364 or have 

incorporated either PW SB PW2000–72–700 

or PW2000 Series Engine Manual, Repair-28, 

Task 72–41–01–300–028 (M-flange 

replacement), perform initial and repetitive 

eddy current inspections (ECIs) of the Mflange of the diffuser case in accordance with 

paragraph (f)(4) of this AD. 

(4) Use, as applicable, either the 

Accomplishment Instructions, ‘‘For Engines 

Installed on the Aircraft,’’ paragraphs 3.(I) 

through 3.(J), or the Accomplishment 

Instructions, ‘‘For Engines Removed from the 

Aircraft,’’ paragraphs 3.(D) through 3.(E), of 

PW Alert Service Bulletin (ASB) No. PW2000 

A72–765, Revision No. 1, dated July 13, 

2016, to do the ECI as follows: 

(i) Perform an initial inspection within the 

following period, whichever occurs later: 

(A) Within 5,500 cycles since new or since 

M-flange replacement, or 

(B) Within 2,500 cycles since last piecepart FPI inspection, or 

(C) Within 500 cycles from the effective 

date of this AD. 

(ii) If no crack indications are found, reinspect within 2,500 cycles since last ECI or 

last piece-part FPI inspection, whichever 

occurs first. 

(iii) If crack indications are found, measure 

the crack length and determine the re-inspect 

interval in accordance with: 

(A) Paragraphs 5.(C) through 5.(D) of PW 

ASB No. PW2000 A72–765, Revision No. 1, 

dated July 13, 2016, ‘‘For Engines Installed 

on the Aircraft’’; or 

(B) Paragraphs 4.(C) through 4.(D) of PW 

ASB No. PW2000 A72–765, Revision No. 1, 

dated July 13, 2016, ‘‘For Engines Removed 

from the Aircraft.’’ 

(iv) Remove from service diffuser cases 

with cracks exceeding 0.170 inches. 

(g) Definition 

For the purpose of this AD, piece-part 

opportunity is defined as when the part is 

completely disassembled. 

(h) Credit for Previous Actions 

If you performed an ECI of the diffuser case 

and HPT case M-flange using the 

Accomplishment Instructions of PW SB No. 

PW2000 72–763, Revision No. 1, dated 

August 13, 2013, or an earlier version, or you 

performed a high sensitivity FPI of the 

diffuser case and HPT case at the piece-part 

opportunity after January 1, 2010, you met 

the requirements of paragraph (f)(1) of this 

AD. 

(i) 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. 

(j) Related Information 

(1) For more information about this 

proposed AD, contact Brian Kierstead, 

Aerospace Engineer, Engine Certification 

Office, FAA, Engine & Propeller Directorate, 

1200 District Avenue, Burlington, MA 01803; 

phone: 781–238–7772; fax: 781–238–7199; 

email: brian.kierstead@faa.gov. 

(2) PW SB No. PW2000 72–763, Revision 

No. 1, dated August 30, 2013; and PW ASB 

No. PW2000 A72–765, Revision No. 1, dated 

July 13, 2016, can be obtained from PW using 

the contact information in paragraph (j)(3) of 

this AD. 

(3) For service information identified in 

this proposed AD, contact Pratt & Whitney, 

United Technologies Corporation, 400 Main 

St., East Hartford, CT 06108; phone: 860– 

565–8770; fax: 860–565–4503. 

(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. 

Issued in Burlington, Massachusetts, on 

December 1, 2016. 

Colleen M. D’Alessandro, 

Manager, Engine & Propeller Directorate, 

Aircraft Certification Service. 

[FR Doc. 2016–30114 Filed 12–21–16; 8:45 am] 

BILLING CODE 4910–13–P 

OFFICE OF THE UNITED STATES 

TRADE REPRESENTATIVE 

15 CFR Parts 2004 and 2005 

[Docket Number USTR–2016–0027] 

RIN 0350–AA09 

Privacy Act Policies and Procedures 

AGENCY: Office of the United States 

Trade Representative. 

ACTION: Proposed rule. 

SUMMARY: As part of a comprehensive 

review of agency practices related to the 

disclosure of records and information, 

the Office of the United States Trade 

Representative (USTR) is updating both 

its systems of records and implementing 

rule under the Privacy Act of 1974 

(Privacy Act). This proposed rule 

describes how individuals can find out 

if a USTR system of records contains 

information about them and, if so, how 

to access or amend a record. The 

proposed rule would move the Privacy 

Act regulation from part 2005 into a 

new subpart C to part 2004. USTR 

previously renamed and reorganized 

part 2004 to include all of the rules 

governing disclosure of USTR records 

and information. Elsewhere in this issue 

of the Federal Register, USTR is 

publishing a notice concerning updates 

to its Privacy Act systems of records. 

DATES: We must receive your written 

comments on or before January 23, 

2017. 

ADDRESSES: You should submit written 

comments through the Federal 

eRulemaking Portal: http://

www.regulations.gov. The docket 

number for this rulemaking is USTR– 

2016–0027. USTR invites comments on 

all aspects of the proposed rule, and 

will revise the language as appropriate 

after taking all timely comments into 

consideration. Copies of all comments 

will be available for public viewing at 

www.regulations.gov upon completion 

of processing. You can view a 

submission by entering the docket 

number USTR–2016–0027 in the search 

field at http://www.regulations.gov. We 

will post comments without change and 

will include any personal information 

you provide, such as your name, 

mailing address, email address, and 

telephone number. 

FOR FURTHER INFORMATION CONTACT: 

Janice Kaye, Monique Ricker or Melissa 

Keppel, Office of General Counsel, 

Office of the US Trade Representative, 

Anacostia Naval Annex, Building 410/ 

Door 123, 250 Murray Lane SW., 

Washington DC 20509, jkaye@ustr.eop.

gov; mricker@ustr.eop.gov; mkeppel@

ustr.eop.gov; 202–395–3150. 


Lhorne on DSK30JT082PROD with PROPOSALS