27972 Federal Register / Vol. 75, No. 96 / Wednesday, May 19, 2010 / Proposed Rules 

Boeing Commercial Airplanes Organization 

Delegation Authorization (ODA) that has 

been authorized by the Manager, Seattle 

ACO, to make those findings. For a repair 

method to be approved, the repair must meet 

the certification basis of the airplane. 

Issued in Renton, Washington, on May 5, 

2010. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–11905 Filed 5–18–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0514; Directorate 

Identifier 2010–NE–02–AD] 

RIN 2120–AA64 

Airworthiness Directives; Pratt & 

Whitney JT8D–9, –9A, –11, –15, –17, 

and –17R 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 

Pratt & Whitney (PW) JT8D–9, –9A, –11, 

–15, –17, and –17R turbofan engines. 

This proposed AD would require 

overhauling fan blade leading edges at 

the first shop visit after 4,000 cycles-inservice (CIS) since the last total fan 

blade overhaul was performed. This 

proposed AD results from reports of 

failed fan blades. We are proposing this 

AD to prevent high-cycle fatigue 

cracking at the blade root, which could 

result in uncontained failures of first 

stage fan blades and damage to the 

airplane. 

DATES: We must receive any comments 

on this proposed AD by July 19, 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. 

Contact Pratt & Whitney, 400 Main 

St., East Hartford, CT 06108; telephone 

(860) 565–7700; fax (860) 565–1605, for 

a copy of the service information 

identified in this proposed AD. 

FOR FURTHER INFORMATION CONTACT: 

James Gray, Aerospace Engineer, Engine 

Certification Office, FAA, Engine & 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

e-mail: james.gray@faa.gov; telephone 

(781) 238–7742; 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– 

2010–0514; Directorate Identifier 2010– 

NE–02–AD’’ in the subject line of your 

comments. We specifically invite 

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 of 16 first 

stage fan blade root fractures, two of 

which resulted in penetration of the 

cowl and minor damage to the fuselage. 

Engineering investigation has 

determined that increased vibratory 

stress in the root and airfoil from eroded 

and blunt leading edges caused the fan 

blade failures. The primary cause of 

leading edge erosion is the operating 

environment, particularly rain and sand. 

The aerodynamic performance of the 

blade is diminished and vibratory stress 

in the airfoil and root is increased. This 

condition, if not corrected, could result 

in uncontained failures of first stage fan 

blades and damage to the airplane. 

Relevant Service Information 

We have reviewed and approved the 

technical contents of PW JT8D 

Maintenance Advisory Notice MAN– 

JT8D–2–06, dated November 20, 2006, 

that describes procedures for 

overhauling the first stage fan blades at 

every shop visit where pairs of major 

mating flanges are separated. 

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 overhauling the 

total set of stage 1 fan blades at: 

• The first shop visit after 4,000 CIS 

since the last total stage 1 fan blade 

overhaul or 

• The next shop visit after the 

effective date of this proposed AD if the 

CIS since the last total stage 1 fan blade 

overhaul is unknown and 

• Thereafter, at the next shop visit 

after 4,000 CIS since the last total stage 

fan blade overhaul. 

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 1,527 engines installed on 

airplanes of U.S. registry. We also 

estimate that it would take about 63 

work-hours per engine to perform the 

proposed actions, and that the average 

labor rate is $85 per work-hour. There 

would be no required parts. Based on 

these figures, we estimate the total cost 

of the proposed AD to U.S. operators to 

be $8,177,085. 

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 


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Federal Register / Vol. 75, No. 96 / Wednesday, May 19, 2010 / Proposed Rules 27973 

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, 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–2010– 

0514; Directorate Identifier 2010–NE– 

02–AD. 

Comments Due Date 

(a) The Federal Aviation Administration 

(FAA) must receive comments on this 

airworthiness directive (AD) action by July 

19, 2010. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Pratt & Whitney 

(PW) JT8D–9, –9A, –11, –15, –17, and –17R 

turbofan engines. These engines are installed 

on, but not limited to, Boeing 727 series, 

Boeing 737–200 series and McDonnell 

Douglas DC–9 airplanes. 

Unsafe Condition 

(d) This AD results from reports of failed 

fan blades. We are issuing this AD to prevent 

high-cycle fatigue cracking at the blade root, 

which could result in uncontained failures of 

first stage fan blades 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. 

Initial Overhaul 

(f) For engines where the cycles-in-service 

(CIS) since last overhaul are known, overhaul 

the total set of stage 1 fan blades at the first 

shop visit after 4,000 CIS since the last total 

stage 1 fan blade overhaul, or the next shop 

visit after the effective date of this AD, 

whichever occurs later. Guidance on 

performing a fan blade overhaul can be found 

in Pratt & Whitney JT8D Maintenance 

Advisory Notice, MAN–JT8D–2–06 and the 

Engine Manual Chapter/Section 72–33–21, 

Inspection 00. 

(g) For engines where the CIS since last 

overhaul are unknown, overhaul the total set 

of stage 1 fan blades at the next shop visit 

after the effective date of this AD. Guidance 

on performing a fan blade overhaul can be 

found in Pratt & Whitney JT8D Maintenance 

Advisory Notice, MAN–JT8D–2–06 and the 

Engine Manual Chapter/Section 72–33–21, 

Inspection 00. 

Repetitive Overhaul 

(h) Thereafter, overhaul the total set of 

stage 1 fan blades at the first shop visit after 

4,000 CIS since the last total stage 1 fan blade 

overhaul. Guidance on performing a fan 

blade overhaul can be found in Pratt & 

Whitney JT8D Maintenance Advisory Notice, 

MAN–JT8D–2–06 and the Engine Manual 

Chapter/Section 72–33–21, Inspection 00. 

Definitions 

(i) For the purpose of this AD, a shop visit 

is the induction of an engine into the shop 

for maintenance involving the separation of 

pairs of major mating engine flanges, except 

that the separation of engine flanges solely 

for the purposes of transporting the engine 

without subsequent engine maintenance does 

not constitute an engine shop visit. 

Alternative Methods of Compliance 

(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 James Gray, Aerospace 

Engineer, Engine Certification Office, FAA, 

Engine & Propeller Directorate, 12 New 

England Executive Park, Burlington, MA 

01803; e-mail: james.gray@faa.gov; telephone 

(781) 238–7742; fax (781) 238–7199, for more 

information about this AD. 

(l) Pratt & Whitney JT8D Maintenance 

Advisory Notice MAN–JT8D–2–06, dated 

November 20, 2006, pertains 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 

May 13, 2010. 

Peter A. White, 

Assistant Manager, Engine and Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 2010–11999 Filed 5–18–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0521; Directorate 

Identifier 2009–NE–21–AD] 

RIN 2120–AA64 

Airworthiness Directives; Rolls-Royce 

plc RB211–524C2 Series 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: A number of LPT casings 

have been found cracked during engine 

shop visit. Cracking of the LPT casing 

reduces the capability of the casing to 

contain debris in the event of an LPT 

stage 1 blade failure. Therefore, blade 

failure in an engine featuring a cracked 

LPT casing may result in release of 

uncontained high energy debris. For the 

reason described above, this AD 

requires repetitive inspections and 

corrective actions, depending on 


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