Federal Register / Vol. 78, No. 209 / Tuesday, October 29, 2013 / Proposed Rules 64419 

legitimate domestic objective, such as 

the protection of safety, and does not 

operate in a manner that excludes 

imports that meet this objective. The 

statute also requires consideration of 

international standards and, where 

appropriate, that they be the basis for 

U.S. standards. The FAA assessed the 

potential effect of the AD and 

determined that because it addresses an 

immediate safety issue the AD is not 

considered an unnecessary obstacle to 

the foreign commerce of the United 

States. 

Unfunded Mandates Assessment 

Title II of the Unfunded Mandates 

Reform Act of 1995 (Pub. L. 104–4) 

requires each Federal agency to prepare 

a written statement assessing the effects 

of any Federal mandate in a proposed or 

final agency rule that may result in an 

expenditure of $100 million or more (in 

1995 dollars) in any one year by State, 

local, and tribal governments, in the 

aggregate, or by the private sector; such 

a mandate is deemed to be a ‘‘significant 

regulatory action.’’ The FAA currently 

uses an inflation-adjusted value of 

$143.1 million in lieu of $100 million. 

The AD does not contain such a 

mandate; therefore, the requirements of 

Title II of the Act do not apply. 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this IRFA. Send your comments to an 

address listed under the ADDRESSES

section. Include ‘‘Docket No. FAA– 

2013–0393; Directorate Identifier 2012– 

CE–025–AD’’ at the beginning of your 

comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of the IRFA as related to the AD 

action. The most helpful comments will 

reference a specific portion of the IRFA 

or related rulemaking document, 

explain the reason for any 

recommended change, and include 

supporting data. 

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 the AD. 

Issued in Kansas City, Missouri, on 

October 22, 2013. 

Earl Lawrence, 

Manager, Small Airplane Directorate, Aircraft 

Certification Service. 

[FR Doc. 2013–25526 Filed 10–28–13; 8:45 am] 

BILLING CODE 4910–13–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 adopt a new 

airworthiness directive (AD) for all Pratt 

& Whitney (PW) PW2037, PW2037D, 

PW2037M, PW2040, PW2040D, 

PW2043, PW2146, PW2240, PW2337, 

PW2643, and F117–PW–100 turbofan 

engines. This proposed AD was 

prompted by a rupture of the diffuserto-high-pressure turbine (HPT) case 

flange. This proposed AD would require 

a one-time eddy current inspection (ECI) 

of affected engines with certain diffuser 

and HPT cases installed. This AD also 

proposes to require a fluorescentpenetrant inspection (FPI) of the 

diffuser case rear flange and HPT case 

front flange. We are proposing this AD 

to prevent failure of the diffuser-to-HPT 

case flange, which could lead to 

uncontained engine failure and damage 

to the airplane. 

DATES: We must receive comments on 

this proposed AD by December 30, 

2013. 

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 proposed AD, 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, 12 New England 

Executive Park, 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; 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: 

Robert Morlath, Aerospace Engineer, 

Engine Certification Office, FAA, Engine 

& Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

phone: 781–238–7154; fax: 781–238– 

7199; email: robert.c.morlath@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– 

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. 

Discussion 

We received a report of an engine 

event in October 2011 that resulted in 

a rupture of the engine diffuser-to-HPT 

case flange. The rupture caused the 

engine cowl doors to break open, which 

resulted in damage to the underside of 

the airplane’s wing. Subsequent 

investigation revealed that the root 

cause of this rupture was a crack that 

originated in HPT case M-flange 

boltholes (the forward flange of the HPT 

case that mates with the rear outer 

flange of the diffuser case). This 

condition, if not corrected, could result 

in failure of the diffuser-to-HPT case 

flange, which may cause an 

uncontained engine failure and damage 

to the airplane. 

mstockstill on DSK4VPTVN1PROD with PROPOSALS

64420 Federal Register / Vol. 78, No. 209 / Tuesday, October 29, 2013 / Proposed Rules 

Relevant Service Information 

We reviewed PW Service Bulletin 

(SB) No. PW2000 72–763, Revision 1, 

dated August 30, 2013, and PW PW2000 

Series Engine Manual part number 

1A6231. The SB describes procedures 

for inspecting the flanges of the HPT 

case and the diffuser case. 

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 an 

on-wing ECI of the diffuser case and 

HPT case flanges. This proposed AD 

would also require an FPI of all engine 

diffuser cases and all HPT cases. 

Differences Between the Proposed AD 

and the Service Information 

PW SB No. PW2000 72–763, Revision 

1, dated August 30, 2013, requires that 

operators complete an on-wing ECI by 

August 31, 2013. We are proposing that 

the ECI be performed within 100 flight 

cycles or 30 days after the effective date 

of this AD, whichever is earlier. 

Costs of Compliance 

We estimate that this proposed AD 

will affect 638 engines installed on 

airplanes of U.S. registry. Of the 638 

engines, we estimate that about 58 

engines will be subject to ECI and all 

engines will be subject to the FPI. We 

also estimate that it would take about 5 

hours to perform the ECI and 3 hours to 

perform the FPI required by this 

proposed AD. Materials cost for the FPI 

will be about $20 per engine. The 

average labor rate is $85 per hour. Based 

on these figures, we estimate the total 

cost of this proposed AD to U.S. 

operators to be $200,100. 

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 proposed 

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 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): 

Pratt & Whitney: Docket No. FAA–2013– 

0740; Directorate Identifier 2013–NE– 

24–AD. 

(a) Comments Due Date 

We must receive comments by December 

30, 2013. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to all Pratt & Whitney 

(PW) PW2037, PW2037D, PW2037M, 

PW2040, PW2040D, PW2043, PW2146, 

PW2240, PW2337, PW2643, and F117–PW– 

100 turbofan engines. 

(d) 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. 

(e) Compliance 

Unless already done, comply with this AD 

within the compliance times specified. 

(1) For diffuser and HPT cases identified 

by serial number (S/N) in Table 1 to 

paragraph (e) of this AD: 

(i) Within 100 flight cycles or 30 days after 

the effective date of this AD, whichever is 

earlier, eddy current inspect the diffuser case 

and the HPT case M-flange. 

(ii) For engines installed on the aircraft, 

use paragraphs 3.G. through 3.L. in the ‘‘For 

Engines Installed on the Aircraft’’ section of 

the Accomplishment Instructions of PW 

Service Bulletin (SB) No. PW2000 72–763, 

Revision 1, dated August 30, 2013, to 

perform the inspection. 

(iii) For engines removed from the aircraft, 

use paragraphs 3.B. through 3.G. in the ‘‘For 

Engines Removed From the Aircraft’’ section 

of the Accomplishment Instructions of PW 

Service Bulletin (SB) No. PW2000 72–763, 

Revision 1, dated August 30, 2013, to 

perform the inspection. 

TABLE 1 TO PARAGRAPH (e)—DIFFUSER AND HPT CASE P/NS AND SERIAL NUMBERS

Diffuser case part No. (P/N) Diffuser case S/N HPT case P/N HPT case S/N 

1B7407–001 ................................... DGUSAA0114 ............................... 1A9030 ......................................... RM6300 

1B7407 ........................................... WE2452 ........................................ 1B2440 ......................................... DKLBB40125 

1B7407 ........................................... DGUSAA0097 ............................... 1B2440 ......................................... DKLBCH3429 

1B7407 ........................................... DGUSAA0670 ............................... 1B2440 ......................................... DKLBCS1032 

1B7407–001 ................................... DGUSAA0622 ............................... 1B2440 ......................................... DKLBC00030 

1B3055–001 ................................... DGUSAA0247 ............................... 1B2440 ......................................... DKLBC07691 

1B7461 ........................................... DGGUAK1308 .............................. 1B2440 ......................................... DKLBDB5108 

mstockstill on DSK4VPTVN1PROD with PROPOSALS

Federal Register / Vol. 78, No. 209 / Tuesday, October 29, 2013 / Proposed Rules 64421 

TABLE 1 TO PARAGRAPH (e)—DIFFUSER AND HPT CASE P/NS AND SERIAL NUMBERS—Continued 

Diffuser case part No. (P/N) Diffuser case S/N HPT case P/N HPT case S/N 

1B7461 ........................................... DGGUAK1306 .............................. 1B2440 ......................................... DKLBDB5153 

1B7461 ........................................... DGGUAK1356 .............................. 1B2440 ......................................... DKLBDU3358 

1B7477 ........................................... DGGUAL1445 ............................... 1A9030 ......................................... RM6353 

1B7477 ........................................... DGGUAL1492 ............................... 1A9030 ......................................... PD3348 

1B7477 ........................................... DGGUAL1501 ............................... 1A9030 ......................................... PD3280 

1B7477 ........................................... DGGUAL1597 ............................... 1A9030 ......................................... ND5644 

1B4091–001 ................................... RT6356 ......................................... 1B2440 ......................................... DKLBBP0225 

1B4091–002 ................................... ST2044 ......................................... 1A9030 ......................................... DKLBBR3621 

1B4091–005 ................................... PF3203 ......................................... 1A9030 ......................................... PD3290 

1B7461 ........................................... DGGUAK1377 .............................. 1B2440 ......................................... WG6904 

1B7477 ........................................... DGGUAL1548 ............................... 1B2440 ......................................... WV1807 

1B7407 ........................................... DGGUAK0189 .............................. 1B2440 ......................................... WX2639 

1B7407 ........................................... DGUSAA0443 ............................... 1B2440 ......................................... WZ4057 

1B7477 ........................................... DGGUAL1441 ............................... 1B2440 ......................................... WX2664 

1B7477 ........................................... DGGUAL1560 ............................... 1A9030 ......................................... RM6359 

1B7407–001 ................................... DGUSAA0329 ............................... 1B2440 ......................................... DKLBCM8956 

1B7407 ........................................... DGUSAA0334 ............................... 1B2440 ......................................... DKLBCM0214 

1B2440 ......................................... DKLBDB5069 

1B2440 ......................................... DKLBB02548 

1B2440 ......................................... DKLBDC7336 

1B2440 ......................................... DKLBDU3372 

1B2440 ......................................... WM6913 

1B2440 ......................................... DKLBBF6606 

1B2440 ......................................... DKLBBB2861 

1B2440 ......................................... DKLBCT1660 

1B2440 ......................................... DKLBB94641 

1B2440 ......................................... DKLBBX8092 

(2) For all diffuser and HPT cases: 

(i) At the next piece part exposure and 

every piece part exposure thereafter, perform 

a high sensitivity fluorescent-penetrant 

inspection (FPI) of the entire diffuser case 

rear flange (M-flange) and bolt holes. 

(ii) At the next piece part exposure and 

every piece part exposure thereafter, perform 

a high sensitivity FPI of the entire HPT case 

forward flange (M-flange) and bolt holes. 

(f) Prohibition Statement 

After the effective date of this AD, do not 

install any engine with a diffuser or HPT case 

with serial number listed in Table 1 to 

paragraph (e) of this AD, onto any aircraft, 

that was not inspected per paragraph (e) of 

this AD. 

(g) Credit for Previous Actions 

If you performed an eddy current 

inspection of the diffuser case and HPT case 

M-flange using paragraphs 3.G. through 3.L. 

in the ‘‘For Engines Installed on the Aircraft’’ 

section or paragraphs 3.B. through 3.G. in the 

‘‘For Engines Removed from the Aircraft’’ 

section of the Accomplishment Instructions 

of PW SB PW2000 72–763, dated March 22, 

2013, you met the requirements of paragraph 

(e)(1) of this AD. 

(h) 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. 

(i) Related Information 

(1) For more information about this AD, 

contact Robert Morlath, Aerospace Engineer, 

Engine Certification Office, FAA, Engine & 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

phone: 781–238–7154; fax: 781–238–7199; 

email: robert.c.morlath@faa.gov. 

(2) Pratt & Whitney Engine Manual, part 

number 1A6231, Chapter 72–41–00, 

Inspection/Check-02, (Task 72–41–00–230– 

002) and Chapter 72–52–00, Inspection/

Check-02 (Task 72–52–00–230–000), which 

are not incorporated by reference in this AD, 

can be obtained from Pratt & Whitney, using 

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

this AD. 

(3) For service information identified in 

this 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, 

12 New England Executive Park, Burlington, 

MA. For information on the availability of 

this material at the FAA, call 781–238–7125. 

Issued in Burlington, Massachusetts, on 

October 7, 2013. 

Colleen M. D’Alessandro, 

Assistant Directorate Manager, Engine & 

Propeller Directorate, Aircraft Certification 

Service. 

[FR Doc. 2013–25459 Filed 10–28–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0766; Directorate 

Identifier 2013–NE–26–AD] 

RIN 2120–AA64 

Airworthiness Directives; Pratt & 

Whitney Canada Corp. 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 all Pratt 

& Whitney Canada Corp. (P&WC) PT6A– 

114 and PT6A–114A turboprop engines. 

This proposed AD was prompted by 

several incidents of compressor turbine 

(CT) blade failure, including two 

fatalities, resulting in power loss and inflight shutdown (IFSD) of the engine. 

This proposed AD would require initial 

and repetitive borescope inspections 

(BSIs) of CT blades, and the removal 

from service of blades that fail 

inspection. We are proposing this AD to 

prevent failure of CT blades, which 

could lead to damage to the engine or 

to the airplane. 

DATES: We must receive comments on 

this proposed AD by December 30, 

2013. 

mstockstill on DSK4VPTVN1PROD with PROPOSALS