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

23637 

Vol. 77, No. 77 

Friday, April 20, 2012 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0228; Directorate 

Identifier 2012–NE–09–AD] 

RIN 2120–AA64 

Airworthiness Directives; Pratt & 

Whitney 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 

Pratt & Whitney Division PW4000–94’’ 

and PW4000–100’’ turbofan engines 

having a 1st stage high-pressure turbine 

(HPT) seal support, part number (P/N) 

55K601 or P/N 50K532, installed. This 

proposed AD was prompted by 58 

reports of cracked 1st stage HPT air seal 

rings, including 15 in-flight engine 

shutdowns. This proposed AD would 

require installation of a redesigned 1st 

stage HPT seal support that was 

introduced to the PW4000 engine fleet 

through service bulletins issued in the 

year 2000. We are proposing this AD to 

prevent failure of the 1st stage HPT air 

seal ring, which could lead to an 

internal oil fire, uncontained engine 

failure, and damage to the airplane. 

DATES: We must receive comments on 

this proposed AD by June 19, 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: 860–565–8770; fax: 

860–565–4503. You may review copies 

of the referenced 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: 

James Gray, Aerospace Engineer, Engine 

& Propeller Directorate, FAA, 12 New 

England Executive Park, Burlington, MA 

01803; 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– 

2012–0228; Directorate Identifier 2012– 

NE–09–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 58 reports of cracked 1st 

stage HPT air seal rings, including 15 inflight engine shutdowns, in certain 

PW4000–94’’ and PW4000–100’’ 

turbofan engines. Pratt & Whitney’s 

investigation has revealed that vibratory 

excitation causes the 1st stage HPT air 

seal ring to crack when a 1st stage HPT 

seal support, P/N 55K601 or P/N 

50K532, is installed. Installing the 

redesigned 1st stage HPT seal support, 

P/N 50K153, that was introduced to the 

PW4000 engine fleet for another reason 

through service bulletins issued in the 

year 2000 also prevents cracking of the 

1st stage HPT air seal ring. Cracking of 

the 1st stage HPT air seal ring, if not 

corrected, could result in failure of the 

1st stage HPT air seal ring, which could 

lead to an internal oil fire, uncontained 

engine failure, and damage to the 

airplane. 

Relevant Service Information 

We reviewed Pratt & Whitney Service 

Bulletin (SB) No. PW4ENG 72–721, 

Revision 2, dated November 30, 2011, 

and SB No. PW4G–100–72–166, 

Revision 2, dated December 2, 2011. 

The service information describes 

procedures for replacing the 1st stage 

HPT seal support, P/N 55K601, or P/N 

50K532, with a redesigned 1st stage 

HPT seal support, P/N 50K153. 

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. This proposed AD would 

also require fluorescent-penetrantinspection or eddy current-inspection of 

the 1st stage HPT air seal ring for cracks, 

and replacing it if found cracked. 

Costs of Compliance 

We estimate that this proposed AD 

would affect 446 Pratt & Whitney 

Division PW4000–94′′ and PW4000– 

100′′ turbofan engines installed on 

airplanes of U.S. registry. We also 

estimate that it would take about 3 

work-hours to perform the actions 


tkelley on DSK3SPTVN1PROD with PROPOSALS
23638 Federal Register / Vol. 77, No. 77 / Friday, April 20, 2012 / Proposed Rules 

required by this AD. The average labor 

rate is $85 per work-hour. Required 

parts would cost about $45,723 per 

engine. Based on these figures, we 

estimate the total cost of the AD to U.S. 

operators to be $20,506,188. 

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– 

2012–0228; Directorate Identifier 2012– 

NE–09–AD. 

(a) Comments Due Date 

We must receive comments by June 19, 

2012. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to the following Pratt & 

Whitney Division 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, with a 

1st stage high-pressure turbine (HPT) seal 

support part number (P/N) 55K601 or P/N 

50K532, installed. 

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

PW4164C, PW4164C/B, PW4168, and 

PW4168A with a 1st stage HPT seal support 

P/N 55K601 or P/N 50K532, installed. 

(d) Unsafe Condition 

This AD was prompted by 58 reports of 

cracked 1st stage HPT air seal rings, 

including 15 in-flight engine shutdowns. We 

are issuing this AD to prevent failure of the 

1st stage HPT air seal ring, which could lead 

to an internal oil fire, uncontained engine 

failure, and damage to the airplane. 

(e) Compliance 

Comply with this AD the next time that the 

engine is separated at the M-flange and the 

HPT module is removed from the engine. 

(1) Remove the 1st stage HPT seal support, 

P/N 55K601 or P/N 50K532, from service and 

replace it with a 1st stage HPT seal support, 

P/N 50K153. 

(2) Remove the 1st stage HPT air seal ring 

from the engine and fluorescent-penetrantinspect, or eddy current-inspect, it for cracks. 

If found cracked, remove the 1st stage HPT 

air seal ring from service. 

(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) For more information about this AD, 

contact James Gray, Aerospace Engineer, 

Engine & Propeller Directorate, FAA, 12 New 

England Executive Park, Burlington, MA 

01803; phone: 781–238–7742; fax: 781–238– 

7199; email: james.e.gray@faa.gov. 

(2) Pratt & Whitney Service Bulletin (SB) 

No. PW4ENG 72–721, Revision 2, dated 

November 30, 2011, and SB No. PW4G–100– 

72–166, Revision 2, dated December 2, 2011, 

pertain to the subject of this AD. 

(3) For service information identified in 

this AD, contact Pratt & Whitney, 400 Main 

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

565–8770; fax: 860–565–4503. 

(4) You may review copies of the service 

information at the FAA, New England 

Region, 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 

April 16, 2012. 

Peter A. White, 

Manager, Engine & Propeller Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–9545 Filed 4–19–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0415; Directorate 

Identifier 2008–SW–065–AD] 

RIN 2120–AA64 

Airworthiness Directives; Bell 

Helicopter Textron, Incorporated 

Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede an 

existing airworthiness directive (AD) for 

Bell Helicopter Textron, Inc. (BHTI) 

Model 204B, 205A, 205A–1, 205B, and 

212 helicopters. The existing AD 

currently requires conducting various 

inspections associated with the main 

rotor grip (grip). If a crack is found, that 

AD requires replacing the grip before 

further flight. If delamination of the 

buffer pad on the grip tang inner surface 

is found, that AD requires inspecting the 

grip surface for corrosion or other 

damage and repairing or replacing the 

grip if corrosion or other damage is 

found. That AD also requires 

determining and recording the hours 

time-in-service (TIS) and the engine 

start/stop cycles for each grip on a 

component history card or equivalent 

record. Additionally, that AD requires 

you to report certain inspection results 

to the FAA. Since we issued that AD, 

additional cracks in grips have been 

found. Analysis of these events has 

shown that a retirement life is needed 

for certain grips, and the AD 


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