Federal Register / Vol. 77, No. 42 / Friday, March 2, 2012 / Proposed Rules 12755 

Issued in Washington, DC, on February 27, 

2012. 

Paul Bosco, 

Director, Office of Procurement and 

Assistance Management, Department of 

Energy. 

Barbara Stearrett, 

Deputy Director, Office of Acquisition, 

Management, National Nuclear Security 

Administration. 

[FR Doc. 2012–5113 Filed 3–1–12; 8:45 am] 

BILLING CODE 6450–01–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0060; Directorate 

Identifier 2012–NE–02–AD] 

RIN 2120–AA64 

Airworthiness Directives; Pratt & 

Whitney (PW) Division 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 

PW4000 series turbofan engines. This 

proposed AD was prompted by reports 

of 3rd and 4th stage vane fractures in 

the low pressure turbine (LPT) of certain 

PW4000–94′′ and PW4000–100′′ 

turbofan engines. These fractures caused 

an uncontained engine failure, an LPT 

case puncture, and multiple in flight 

shutdowns. We are proposing this AD to 

prevent 3rd and 4th stage vane fractures 

in the LPT, which could damage the 

LPT rotor and lead to an uncontained 

engine failure and damage to the 

airplane. 

DATES: We must receive comments on 

this proposed AD by May 1, 2012. 

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: 860–565–4321. You 

may review copies of the referenced 

service information at the FAA, Engine 

& Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803. 

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: 

James Gray, Aerospace Engineer, Engine 

Certification Office, FAA, 12 New 

England Executive Park; phone: 781– 

238–7742; fax: 781–238–7199; email: 

james.e.gray@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– 

2012–0060; Directorate Identifier 2012– 

NE–02–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 have received reports of 3rd and 

4th stage vane fractures in the LPT of 

certain PW4000–94′′ and PW4000–100′′ 

turbofan engines. These fractures caused 

an uncontained engine failure, an LPT 

case puncture, and multiple in flight 

shutdowns. We have identified four 

primary root causes for LPT vane 

failures: 

1. Inadequate retention of the vane in 

the case due to dimensional tolerances 

which causes 3rd stage vane liberations. 

This AD requires dimensional 

inspections of the 3rd stage vanes at 

their retention points and case at LPT 

assembly after overhaul. 

2. Non-uniform airfoil fillet radii 

found on vanes produced prior to 2005 

which causes 4th stage vane fractures. 

This AD removes these vanes, identified 

by the casting identifier, from service at 

the next LPT overhaul. 

3. Multiple strip-and-recoat repairs of 

the 4th stage vanes which degrade the 

structural integrity of the vanes and 

cause 4th stage vane fractures. This AD 

removes from service 4th stage vanes 

with multiple strip-and-recoat repairs. 

This AD also prohibits approving for 

return to service any 4th stage vane with 

more than one strip-and-recoat repair. 

4. Aerodynamic excitation of the 

vanes which causes 4th stage vane 

fractures. The excitation is attributed to 

the rotor assembly methods for the 

upstream rotor stages. This AD requires 

reassembling the 2nd stage HPT blades 

at the next HPT overhaul and the 3rd 

stage LPT blades at the next LPT 

overhaul, using the latest assembly 

technique. 

The actions proposed in this AD are 

intended to address each of the root 

causes identified above. This condition, 

if not corrected, could result in 3rd and 

4th stage vane fractures in the LPT, 

which could damage the LPT rotor and 

lead to an uncontained engine failure 

and damage to the airplane. 

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 designs. 

Proposed AD Requirements 

This proposed AD would require 

dimensional inspections of 3rd stage 

vanes and the rear turbine case. This AD 

also requires inspection of 4th stage 

vanes at the next LPT overhaul and 

removal of vanes with non-conforming 

airfoil fillet radii and vanes with more 

than one strip and recoat repair. This 

AD also requires disassembly and 

reassembly of the 2nd stage HPT rotor 

and 3rd stage LPT rotor at the next HPT 

and LPT overhauls. 

Costs of Compliance 

We estimate that this proposed AD 

affects 807 engines installed on 

airplanes of U.S. registry. We estimate 

that it would take 2 work-hours per 

engine to perform the LPT 3rd stage 

vane cluster assembly and rear turbine 

case inspections. The average labor rate 

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12756 Federal Register / Vol. 77, No. 42 / Friday, March 2, 2012 / Proposed Rules 

is $85 per work-hour. We expect that 

approximately 1,870 LPT 4th stage vane 

cluster assemblies will be found with 

the non-conforming casting 

identification. Replacement parts cost 

about $4,854. We estimate that limiting 

4th stage vanes to one strip-and-recoat 

repair will remove 1⁄3 of the useful part 

life expectancy of the vanes on 323 

engines at a prorated cost of $71,000 per 

engine. We do not associate any 

additional costs with reassembling 2nd 

stage HPT blades and 3rd stage LPT 

blades using the latest procedures as 

this is done at overhaul. Based on these 

figures, we estimate the cost of the 

proposed AD on U.S. operators to be 

$32,147,170. 

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 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– 

2012–0060; Directorate Identifier 2012– 

NE–02–AD. 

(a) Comments Due Date 

We must receive comments by May 1, 

2012. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to the following Pratt & 

Whitney Division (PW) turbofan engines: 

(1) PW4000–94′′ engine models PW4050, 

PW4052, PW4056, PW4152, PW4156, 

PW4650, PW4060, PW4060A, PW4060C, 

PW4062, PW4062A, PW4156A, PW4158, 

PW4160, PW4460, and PW4462 including 

models with any dash number suffix. 

(2) PW4000–100′′ engine models PW4164, 

PW4164C, PW4164C/B, PW4168, PW4168A, 

PW4164–1D, PW4164C–1D, PW4164C/B–1D, 

PW4168–1D, PW4168A–1D, and PW4170. 

(d) Unsafe Condition 

This AD was prompted by reports of 3rd 

and 4th stage vane fractures in the low 

pressure turbine (LPT) of certain PW4000– 

94′′ and PW4000–100′′ turbofan engines. 

These fractures caused an uncontained 

engine failure and an LPT case puncture, and 

resulted in multiple in flight shutdowns. We 

are issuing this AD to prevent 3rd and 4th 

stage vane fractures in the LPT, which could 

damage the LPT rotor and lead to an 

uncontained engine failure and damage to 

the airplane. 

(e) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(1) At the next LPT overhaul do the 

following: 

(i) Remove LPT 4th stage vanes from 

service if more than one strip and recoat 

repair has been performed, or if the number 

of strip and recoat repairs are unknown. After 

the effective date of this AD, do not install 

or reinstall into any engine any LPT 4th stage 

vanes that have had more than one strip and 

recoat repair. 

(ii) Re-assemble the 3rd stage LPT rotor 

blades using a method that will alternate 

heavy blades next to light blades and balance 

blades of similar weights 180 degrees across 

the rotor. 

(iii) Inspect the LPT 3rd stage vane cluster 

assembly. Ensure adequate engagement 

between the vane cluster assembly and the 

rear turbine case. 

(iv) Examine the vane and airseal 

engagement slots on the rear turbine case 

where the 3rd stage vane is installed. Ensure 

adequate engagement exists for assembly of 

the 3rd stage vane cluster assembly and the 

rear turbine case. 

(v) Inspect the 44 LPT 4th stage vane 

cluster assemblies PN 52N774–01 for casting 

identification ‘‘51N554AT 1447 2S1C1’’ and 

PN 52N674–01 for casting identification 

‘‘51N454AT 655 2S1C1.’’ Remove the vane 

cluster assembly from service if either of 

these casting identifications is found. 

(2) At the next HPT overhaul, re-assemble 

the 2nd stage HPT rotor blades using a 

method that will alternate heavy blades next 

to light blades and balance blades of similar 

weights 180 degrees across the rotor. 

(f) Alternative Methods of Compliance 

(AMOCs) 

The Manager, Engine Certification Office, 

may approve AMOCs for this AD. Use the 

procedures found in 14 CFR 39.19 to make 

your request. 

(g) Related Information 

(1) Guidance on the assembly method of 

paragraph (e)(1)(ii) of this AD can be found 

in the applicable engine manual: PN 50A605 

or PN 50A822 Task 72–53–03–440–001, 

dated September 15, 2006; or PN 50A443 

Task 72–53–03–440–001, dated May 1, 2007; 

or PN 51A342 Task 72–53–03–440–002–003, 

dated September 15, 2006. 

(2) Guidance on the dimensional 

inspection of paragraph (e)(1)(iii) of this AD 

can be found in the Clean Inspect Repair 

Manual, PN 51A357 Task 72–53–23–200– 

004, dated January 15, 2011. 

(3) Guidance on the dimensional 

inspections of paragraph (e)(1)(iv) of this AD 

can be found in the Clean Inspect Repair 

Manual, PN 51A357 Subtask 72–53–17–220– 

060, dated September 15, 2009. 

(4) Guidance on the assembly method of 

paragraph (e)(2) of this AD can be found in 

the applicable engine manual: PN 50A605, 

PN50A822, or PN50A443 Task 72–52–02– 

440–001, dated May 1, 2010; or PN 51A342 

Task 72–52–02–440–001, dated September 

15, 2011. 

(5) For more information about this AD, 

contact James Gray, Aerospace Engineer, 

Engine Certification Office, FAA, 12 New 

England Executive Park; phone: 781–238– 

7742; fax: 781–238–7199; email: james.e.

gray@faa.gov. 

(6) For service information identified in 

this AD, contact Pratt & Whitney, 400 Main 

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

565–4321. You may review copies of the 

referenced service information at the FAA, 

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Federal Register / Vol. 77, No. 42 / Friday, March 2, 2012 / Proposed Rules 12757 

Engine & Propeller Directorate, 12 New 

England Executive Park, Burlington, MA 

01803. For information on the availability of 

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

Issued in Burlington, Massachusetts, on 

February 27, 2012. 

Peter A. White, 

Manager, Engine & Propeller Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–5094 Filed 3–1–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0218; Directorate 

Identifier 2012–CE–003–AD] 

RIN 2120–AA64 

Airworthiness Directives; Hawker 

Beechcraft Corporation Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for certain 

Hawker Beechcraft Corporation Models 

58 and G58 airplanes. This proposed AD 

was prompted by installation of 

oversized clamps on fuel vapor return 

and/or fuel vent lines in the outboard 

sections of the left and right wings. This 

proposed AD would require inspecting 

for oversized or deformed fuel hose 

clamps and replacing as necessary. We 

are proposing this AD to correct the 

unsafe condition on these products. 

DATES: We must receive comments on 

this proposed AD by April 16, 2012. 

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 Hawker 

Beechcraft Corporation, B091–A04, 

10511 E. Central Ave., Wichita, Kansas 

67206; telephone: 1 (800) 429–5372 or 

(316) 676–3140; fax: (316) 676–8027; 

email: tmdc@hawkerbeechcraft.com; or 

Internet: http:// 

www.hawkerbeechcraft.com/ 

customer_support/ 

technical_and_field_support/. You may 

review copies of the referenced service 

information at the FAA, Small Airplane 

Directorate, 901 Locust, Kansas City, 

Missouri 64106. For information on the 

availability of this material at the FAA, 

call (816) 329–4148. 

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: 

Thomas Teplik, Aerospace Engineer, 

Wichita Aircraft Certification Office, 

FAA, 1801 Airport Road, Room 100, 

Wichita, Kansas 67209; phone: (316) 

946–4196; fax: (316) 329–4090; email: 

thomas.teplik@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–12– 

0218; Directorate Identifier 2012–CE– 

003–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 reports of installation of 

oversized clamps on fuel vapor return 

and/or fuel vent lines in the outboard 

sections of the left and right wings on 

Hawker Beechcraft Corporation Models 

58 and G58 airplanes. This condition, if 

not corrected, could result in leakage of 

fuel or vapor in areas where electrical 

wiring and other potential ignition 

sources are present, which could lead to 

an inflight fire. 

Relevant Service Information 

We reviewed Hawker Beechcraft 

Mandatory Service Bulletin No. SB 28– 

4039, Revision 1, dated October 2011. 

The service bulletin describes 

procedures for inspecting for oversized 

or deformed fuel hose clamps and 

replacing as necessary. 

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 

accomplishing the actions specified in 

the service information described 

previously. 

Costs of Compliance 

We estimate that this proposed AD 

affects 244 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 

Defueling, inspection of the fuel hose 

clamps, and refueling.

3.5 work-hours × $85 per hour = $297.50 Not applicable ......... $297.50 $72,590 

We estimate the following costs to do 

any necessary replacements that would 

be required based on the results of the 

proposed inspection. We have no way of 

determining the number of aircraft that 

might need these replacements: 

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