Federal Register / Vol. 75, No. 57 / Thursday, March 25, 2010 / Proposed Rules 14377 

airworthiness directive (AD) action by May 

24, 2010. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Pratt & Whitney 

(PW) PW4052, PW4056, PW4060, PW4062, 

PW4062A, PW4074, PW4077, PW4077D, 

PW4084D, PW4090, PW4090–3, PW4152, 

PW4156, PW4156A, PW4158, PW4164, 

PW4168, PW4168A, PW4460, and PW4462 

turbofan engines. These engines are installed 

on, but not limited to, Boeing 747–400, 767– 

200, 767–300, 777–200, and 777–300 

airplanes; McDonnell Douglas MD–11 

airplanes; and Airbus A300–600, A310–300, 

and A330–200 airplanes. 

Unsafe Condition 

(d) This AD results from reports of cracked 

locking and loading slots in the high-pressure 

compressor (HPC) drum rotor disk assembly. 

We are issuing this AD to detect cracks in the 

locking and loading slots in the HPC drum 

rotor disk assemblies, which could result in 

rupture of the HPC drum rotor disk assembly 

and damage to the airplane. 

Compliance 

(e) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified unless the 

actions have already been done. 

Local Fluorescent Penetrant Inspection 

(f) Perform a local fluorescent penetrant 

inspection for cracks in the HPC drum rotor 

disk assembly blade locking and loading slots 

of the specific stages of the HPC drum rotor 

disk assemblies from which any of the blades 

are removed as specified in Table 1 of this 

AD. 

TABLE 1—COMPLIANCE TIMES AND SERVICE BULLETINS BY ENGINE MODEL

For engine model Inspect whenever— Use— 

(1) PW4074, PW4077, PW4077D, PW4084D, 

PW4090, and PW4090–3.

Any of the 13th or 14th stage blades are removed during a shop visit.Paragraphs 1.A. through 1.B. of the Accomplishment Instructions of PW4G–112–72– 

264, Revision 1, dated September 2, 2004. 

(2) PW4164, PW4168, and PW4168A ............... Any of the 13th, 14th, or 15th stage blades 

are removed during a shop visit.

Paragraphs 1.A. through 1.C of the Accomplishment Instructions of PW4G–100–72– 

186, Revision 1, dated September 2, 2004. 

(3) PW4052, PW4056, PW4060, PW4062, 

PW4062A, PW4152, PW4156, PW4156A, 

PW4158, PW4460, and PW4462.

Any of the 13th, 14th, or 15th stage blades 

are removed during a shop visit.

Paragraphs 1.A. through 1.C. of the Accomplishment Instructions of PW4ENG 72–796, 

dated June 11, 2009. 

(g) Remove from service any HPC drum 

rotor disk assembly found with a crack in the 

blade loading and locking slots of the HPC 

drum rotor disk assembly. 

Alternative Methods of Compliance 

(h) The Manager, Engine Certification 

Office, has the authority to approve 

alternative methods of compliance for this 

AD if requested using the procedures found 

in 14 CFR 39.19. 

Related Information 

(i) Contact Rose Len, Aerospace Engineer, 

Engine Certification Office, FAA, Engine & 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

e-mail: rose.len@faa.gov; telephone (781) 

238–7772; fax (781) 238–7199, for more 

information about this AD. 

(j) Pratt & Whitney Service Bulletins 

PW4ENG 72–796, dated June 11, 2009, 

PW4G–100–72–186, Revision 1, dated 

September 2, 2004, and PW4G–112–72–264, 

Revision 1, dated September 2, 2004, pertain 

to the subject of this AD. Contact Pratt & 

Whitney, 400 Main St., East Hartford, CT 

06108; telephone (860) 565–7700; fax (860) 

565–1605, for a copy of this service 

information. 

Issued in Burlington, Massachusetts, on 

March 16, 2010. 

Francis A. Favara, 

Manager, Engine and Propeller Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–6581 Filed 3–24–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2008–1095; Directorate 

Identifier 2008–NE–34–AD] 

RIN 2120–AA64 

Airworthiness Directives; Pratt & 

Whitney (PW) Model PW2037, 

PW2037(M), and PW2040 Turbofan 

Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: The FAA proposes to adopt a 

new airworthiness directive (AD) for 

PW Model PW2037, PW2037(M), and 

PW2040 turbofan engines. This 

proposed AD would require removing 

erosion damage on fan blades with 

cutback leading edges and restoring the 

leading edge contour. This proposed AD 

results from reports from PW that fan 

blade leading edge erosion can result in 

a fan thrust deterioration mode (FTDM) 

condition, which reduces the engine’s 

capability of producing full rated takeoff thrust. We are proposing this AD to 

prevent loss of engine thrust from an 

FTDM condition, which could result in 

an inability to maintain safe flight. 

DATES: We must receive any comments 

on this proposed AD by May 24, 2010. 

ADDRESSES: Use one of the following 

addresses to comment on this proposed 

AD. 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov and follow 

the instructions for sending your 

comments electronically. 

• Mail: Docket Management Facility, 

U.S. Department of Transportation, 1200 

New Jersey Avenue, SE., West Building 

Ground Floor, Room W12–140, 

Washington, DC 20590–0001. 

• Hand Delivery: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

• Fax: (202) 493–2251. 

You can get the service information 

identified in this proposed AD from 

Pratt & Whitney, 400 Main St., East 

Hartford, CT 06108; telephone (860) 

565–8770; fax (860) 565–4503. 

FOR FURTHER INFORMATION CONTACT: 

Mark Riley, Aerospace Engineer, Engine 

Certification Office, FAA, Engine and 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

e-mail: mark.riley@faa.gov; telephone 

(781) 238–7758; fax (781) 238–7199. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send us any written 

relevant data, views, or arguments 

regarding this proposal. Send your 

comments to an address listed under 

ADDRESSES. Include ‘‘Docket No. FAA– 

2008–1095; Directorate Identifier 2008– 

NE–34–AD’’ in the subject line of your 

comments. We specifically invite 

mstockstill on DSKH9S0YB1PROD with PROPOSALS

14378 Federal Register / Vol. 75, No. 57 / Thursday, March 25, 2010 / Proposed Rules 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of the proposed AD. We will 

consider all comments received by the 

closing date and may amend the 

proposed AD in light 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 with FAA 

personnel concerning this proposed AD. 

Using the search function of the Web 

site, anyone can find and read the 

comments in any of our dockets, 

including, if provided, the name of the 

individual who sent the comment (or 

signed the comment on behalf of an 

association, business, labor union, etc.). 

You may review the DOT’s complete 

Privacy Act Statement in the Federal 

Register published on April 11, 2000 

(65 FR 19477–78). 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Operations office 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 Operations 

office (telephone (800) 647–5527) is the 

same as the Mail address provided in 

the ADDRESSES section. Comments will 

be available in the AD docket shortly 

after receipt. 

Discussion 

We have received reports from PW of 

leading edge erosion on PW2000 fan 

blades (LPC STG 1 Blade) with a 

cutback leading edge, part numbers 

(P/Ns) 1B6531, 1B6231–001, and 

1A9031–001 (LPC STG1 Blade Set P/Ns 

1B6521, 1B6221–001, and 1A9721–001). 

Leading edge erosion can result in an 

FTDM condition. Pratt & Whitney has 

found evidence of FTDM from engine 

test cell data, and on installed engines 

from PW2000 engine health monitoring 

data. The FTDM condition can result in 

an inability of the engine to meet full 

rated take off thrust and maintain safe 

flight. 

Relevant Service Information 

We have reviewed and approved the 

technical contents of PW Alert Service 

Bulletin (ASB) PW2000 A72–729, 

Revision 1, dated December 8, 2009, 

that describes procedures for removing 

erosion from the leading edge of the fan 

blades, and restoring the leading edge 

contour. 

Differences Between the Proposed AD 

and the Manufacturer’s Service 

Information 

The PW ASB PW2000 A72–729, 

Revision 1, dated December 8, 2009, 

requires initial compliance by December 

1, 2008, for PW2040 engines and by 

March 1, 2009, for PW2037 and 

PW2037(M) engines. This proposed AD 

would require initial compliance within 

500 cycles-in-service after the effective 

date of this proposed AD for PW2037, 

PW2037(M) and PW2040 engines. 

FAA’s Determination and Requirements 

of the Proposed AD 

We have evaluated all pertinent 

information and identified an unsafe 

condition that is likely to exist or 

develop on other products of this same 

type design. We are proposing this AD, 

which would require initial and 

repetitive maintenance to restore the 

leading edge contour of PW2000 fan 

blade P/Ns 1B6531, 1B6231–001, and 

1A9031–001 (LPC STG1 blade set P/Ns 

1B6521, 1B6221–001, and 1A9721–001. 

The proposed AD would require you 

to use the service information described 

previously to perform these actions. 

Costs of Compliance 

We estimate that this proposed AD 

would affect 480 engines installed on 

airplanes of U.S. registry. We also 

estimate that it would take about 12 

work-hours per engine to perform the 

proposed actions, and that the average 

labor rate is $85 per work-hour. No parts 

are required. Based on these figures, we 

estimate the total cost of the proposed 

AD to U.S. operators to be $489,600 per 

year. 

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 AD: 

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); and 

3. Would not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

We prepared a regulatory evaluation 

of the estimated costs to comply with 

this proposed AD. You may get a copy 

of this summary at the address listed 

under ADDRESSES. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

The Proposed Amendment 

Under the authority delegated to me 

by the Administrator, the Federal 

Aviation Administration 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: 

Pratt & Whitney: Docket No. FAA–2008– 

1095; Directorate Identifier 2008–NE– 

34–AD. 

Comments Due Date 

(a) The Federal Aviation Administration 

(FAA) must receive comments on this 

airworthiness directive (AD) action by May 

24, 2010. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Pratt & Whitney 

(PW) PW2037, PW2037(M), and PW2040 

turbofan engines with six or more fan blade 

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Federal Register / Vol. 75, No. 57 / Thursday, March 25, 2010 / Proposed Rules 14379 

(LPC STG1 blade), part numbers (P/Ns) 

1B6531, 1B6231–001, or 1A9031–001 (LPC 

STG1 blade set P/Ns 1B6521, 1B6221–001, 

and 1A9721–001), with a cutback leading 

edge, installed. These engines are installed 

on, but not limited to, Boeing 757 airplanes. 

Unsafe Condition 

(d) This AD results from reports from PW 

that fan blade leading edge erosion can result 

in a fan thrust deterioration mode (FTDM) 

condition, which reduces the engine’s 

capability of producing full rated take-off 

thrust. We are issuing this AD to prevent loss 

of engine thrust from an FTDM condition, 

which could result in an inability to maintain 

safe flight. 

Compliance 

(e) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified unless the 

actions have already been done. 

Restoring the Fan Blade Leading Edge 

Contour 

(f) Within 500 cycles-in-service after the 

effective date of this AD, restore the fan blade 

leading edge contour using one of the 

following: 

(1) For engines installed on the airplane, 

use the Accomplishment Instructions, For 

Engines Installed on Aircraft, paragraphs 1. 

through 1.T. of PW Alert Service Bulletin 

(ASB) PW2000 A72–729, Revision 1, dated 

December 8, 2009. 

(2) For engines that are not installed on the 

airplane, use the Accomplishment 

Instructions, For Engines Not Installed on 

Aircraft, paragraphs 1. through 1.S. of PW 

ASB PW2000 A72–729, Revision 1, dated 

December 8, 2009. 

(g) Thereafter, repeat paragraphs (f)(1) or 

(f)(2) of this AD, within intervals of 1,000 

cycles-since-last repair. 

Alternative Methods of Compliance 

(h) Pratt & Whitney PW2037, PW2040, 

PW2240, PW2337 Turbofan Engine Manual, 

Part No. 1A6231, Chapter/Section 72–31–12, 

Repair 14, is an approved alternative method 

of compliance to paragraphs (f)(1) and (f)(2) 

of this AD. 

(i) Boeing 757 Airplane Flight Manual 

Document D631N002, Appendix 24, 

(Performance For Operation Of PW2000 

Series Engines With Cutback Fan Blades 

Installed), is an approved alternative method 

of compliance to paragraphs (f)(1) and (f)(2) 

and (g) of this AD. 

(j) The Manager, Engine Certification 

Office, has the authority to approve 

alternative methods of compliance for this 

AD if requested using the procedures found 

in 14 CFR 39.19. 

Related Information 

(k) Contact Mark Riley, Aerospace 

Engineer, Engine Certification Office, FAA, 

Engine and Propeller Directorate, 12 New 

England Executive Park, Burlington, MA 

01803; e-mail: mark.riley@faa.gov; telephone 

(781) 238–7758, fax (781) 238–7199, for more 

information about this AD. 

(l) Pratt & Whitney ASB PW2000 A72–729, 

Revision 1, dated December 8, 2009, pertains 

to the subject of this AD. Contact Pratt & 

Whitney, 400 Main St., East Hartford, CT 

06108; telephone (860) 565–8770; fax (860) 

565–4503, for a copy of this service 

information. 

Issued in Burlington, Massachusetts, on 

March 18, 2010. 

Francis A. Favara, 

Manager, Engine and Propeller Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–6583 Filed 3–24–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0301; Directorate 

Identifier 2009–NE–22–AD] 

RIN 2120–AA64 

Airworthiness Directives; Rolls-Royce 

Deutschland Ltd & Co KG (RRD) 

Models Tay 620–15, Tay 650–15, and 

Tay 651–54 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 the 

products listed above. This proposed 

AD results from mandatory continuing 

airworthiness information (MCAI) 

issued by an aviation authority of 

another country to identify and correct 

an unsafe condition on an aviation 

product. The MCAI describes the unsafe 

condition as: Following a review of 

operational data of the Tay 651–54 

engine, it has been found that the actual 

stress levels in the Tay 651–54 engine 

High Pressure Compressor (HPC) stages 

1, 3, 6, 7 and 12 discs were higher than 

those originally assumed and therefore 

the approved lives needed to be 

reduced. 

We are proposing this AD to prevent 

HPC stages 1, 3, 6, 7, and 12 discs from 

exceeding the approved reduced life 

limits, which could result in an 

uncontained failure of a disc and 

damage to the airplane. 

DATES: We must receive comments on 

this proposed AD by April 26, 2010. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov and follow 

the instructions for sending your 

comments electronically. 

• Mail: Docket Management Facility, 

U.S. Department of Transportation, 1200 

New Jersey Avenue, SE., West Building 

Ground Floor, Room W12–140, 

Washington, DC 20590–0001. 

• Hand Delivery: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

• Fax: (202) 493–2251. 

Contact Rolls-Royce Deutschland Ltd 

& Co KG; Eschenweg 11, D–15827 

Blankenfelde-Mahlow, Germany; 

telephone +49 (0) 33 7086 1768; fax +49 

(0) 33 7086 3356 for the service 

information identified in this proposed 

AD. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Operations office 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 Operations 

office (telephone (800) 647–5527) is the 

same as the Mail address provided in 

the ADDRESSES section. Comments will 

be available in the AD docket shortly 

after receipt. 

FOR FURTHER INFORMATION CONTACT: Tara 

Chaidez, Aerospace Engineer, Engine 

Certification Office, FAA, Engine and 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

e-mail: tara.chaidez@faa.gov; telephone 

(781) 238–7773; fax (781) 238–7199. 

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–2010–0301; Directorate Identifier 

2009–NE–22–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 based on 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 with FAA 

personnel concerning this proposed AD. 

Using the search function of the Web 

site, anyone can find and read the 

comments in any of our dockets, 

including, if provided, the name of the 

individual who sent the comment (or 

signed the comment on behalf of an 

association, business, labor union, etc.). 

You may review the DOT’s complete 

mstockstill on DSKH9S0YB1PROD with PROPOSALS