Federal Register / Vol. 75, No. 176 / Monday, September 13, 2010 / Rules and Regulations 55459 

(11) Include with the operator’s proposed 

procedures any relevant information or 

additional steps that are deemed necessary 

by the operator to comply with the 

deactivation and return the airplane to 

service. 

Issued in Renton, Washington, on 

September 3, 2010. 

Jeffrey E. Duven, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2010–22679 Filed 9–10–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0217; Directorate 

Identifier 2009–NE–23–AD; Amendment 39– 

16427; AD 2010–18–13] 

RIN 2120–AA64 

Airworthiness Directives; Pratt & 

Whitney (PW) PW4000 Series Turbofan 

Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for PW 

PW4052, PW4056, PW4060, PW4062, 

PW4062A, PW4074, PW4077, 

PW4077D, PW4084D, PW4090, 

PW4090–3, PW4152, PW4156A, 

PW4158, PW4164, PW4168, PW4168A, 

PW4460, and PW4462 turbofan engines. 

This AD requires initial and repetitive 

fluorescent penetrant inspections (FPI) 

for cracks in the blade locking and 

loading slots of the high-pressure 

compressor (HPC) drum rotor disk 

assembly. This AD results from reports 

of cracked locking and loading slots in 

the 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. 

DATES: This AD becomes effective 

October 18, 2010. The Director of the 

Federal Register approved the 

incorporation by reference of certain 

publications listed in the regulations as 

of October 18, 2010. 

ADDRESSES: You can get the service 

information identified in this AD from 

Pratt & Whitney, 400 Main St., East 

Hartford, CT 06108; telephone (860) 

565–7700; fax (860) 565–1605. 

The Docket Operations office is 

located at Docket Management Facility, 

U.S. Department of Transportation, 1200 

New Jersey Avenue, SE., West Building 

Ground Floor, Room W12–140, 

Washington, DC 20590–0001. 

FOR FURTHER INFORMATION 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. 

SUPPLEMENTARY INFORMATION: The FAA 

proposed to amend 14 CFR part 39 with 

a proposed AD. The proposed AD 

applies to PW PW4000 series turbofan 

engines. We published the proposed AD 

in the Federal Register on March 25, 

2010 (75 FR 14375). That action 

proposed to require initial and 

repetitive FPI for cracks in the blade 

locking and loading slots of the HPC 

drum rotor disk assembly. 

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 AD, the regulatory 

evaluation, any comments received, and 

other information. The street address for 

the Docket Operations office (telephone 

(800) 647–5527) is provided in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

Comments 

We provided the public the 

opportunity to participate in the 

development of this AD. We have 

considered the comments received. 

Concur With the AD as Proposed 

Two commenters, United Services 

and Boeing, concurred with the AD as 

proposed. 

Request To Reference the Latest Service 

Bulletin (SB) 

One commenter, a private citizen, 

requested that we reference the latest SB 

in the AD, which is Pratt & Whitney SB 

No. PW4G–112–72–264, Revision 2, 

dated February 23, 2010. 

We agree. We changed the AD to use 

the most current version of the SB. 

Request To Change the Inspection 

Compliance Time 

One commenter, Delta Tech Ops, 

requested that we change the inspection 

compliance time to be done only when 

all of the blades of a specific stage are 

removed, rather than when any of the 

blades from a specific stage are 

removed, as written in the proposed AD. 

The commenter states that doing the 

inspection when any blades are 

removed is an added maintenance 

burden. 

We do not agree. Our risk assessment 

establishes that, because the rotating 

life-limited parts addressed by this AD 

action have a known cracking problem, 

the parts must be inspected at the times 

stated in the AD. Inspection can be done 

without removing all of the blades, by 

sliding remaining installed blades to 

expose the locking and loading slots for 

local fluorescent penetrant inspection. 

We did not change the AD. 

Engine Model Removed 

Since we issued the proposed AD, we 

became aware that we inadvertently 

listed engine model PW4156. We 

removed that engine model from the 

AD. 

Conclusion 

We have carefully reviewed the 

available data, including the comments 

received, and determined that air safety 

and the public interest require adopting 

the AD with the changes described 

previously. We have determined that 

these changes will neither increase the 

economic burden on any operator nor 

increase the scope of the AD. 

Costs of Compliance 

We estimate that this AD will affect 

1,038 engines installed on airplanes of 

U.S. registry. We also estimate that it 

will take about 1 work-hour per engine 

to perform the 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 

AD to U.S. operators to be $88,230. 

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. 


srobinson on DSKHWCL6B1PROD with RULES
55460 Federal Register / Vol. 75, No. 176 / Monday, September 13, 2010 / Rules and Regulations 

Regulatory Findings 

We have determined that this AD will 

not have federalism implications under 

Executive Order 13132. This AD will 

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 this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

(2) Is not a ‘‘significant rule’’ under 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); and 

(3) 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. 

We prepared a summary of the costs 

to comply with this AD and placed it in 

the AD Docket. 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. 

Adoption of the Amendment 

■ Accordingly, under the authority 

delegated to me by the Administrator, 

the Federal Aviation Administration 

amends 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: 

2010–18–13 Pratt & Whitney: Amendment 

39–16427. Docket No. FAA–2010–0217; 

Directorate Identifier 2009–NE–23–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective October 18, 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, 

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 2, dated February 23, 2010. 

(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, 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. 

Material Incorporated by Reference 

(j) You must use the service information 

specified in the following Table 2 to perform 

the inspections required by this AD. The 

Director of the Federal Register approved the 

incorporation by reference of the documents 

listed in the following Table 2 in accordance 

with 5 U.S.C. 552(a) and 1 CFR part 51. 

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. You may review copies 

at the FAA, New England Region, 12 New 

England Executive Park, Burlington, MA; or 

at the National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http:// 

www.archives.gov/federal-register/cfr/ibrlocations.html. 

TABLE 2—INCORPORATION BY REFERENCE

Pratt & Whitney Service Bulletin No. Page Revision Date 

PW4G–100–72–186; Total Pages: 11 ............................... ALL ...................................... 1 .......................................... September 2, 2004. 

PW4G–112–72–264; Total Pages: 11 ............................... ALL ...................................... 2 .......................................... February 23, 2010. 

PW4ENG 72–796; Total Pages: 22 ................................... ALL ...................................... Original ................................ June 11, 2009. 


srobinson on DSKHWCL6B1PROD with RULES
Federal Register / Vol. 75, No. 176 / Monday, September 13, 2010 / Rules and Regulations 55461 

Issued in Burlington, Massachusetts, on 

August 26, 2010. 

Thomas A. Boudreau, 

Acting Manager, Engine and Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 2010–21869 Filed 9–10–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0432; Directorate 

Identifier 2010–NM–001–AD; Amendment 

39–16430; AD 2010–19–02] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc. Model DHC–8–200 and DHC–8–300 

Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for the 

products listed above. This AD results 

from mandatory continuing 

airworthiness information (MCAI) 

originated 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: 

During a recent production fuel system 

test, it was found that all three flapper valves 

located in each collector tank did not 

conform to the design requirements, due to 

the fact that a valve spring was installed on 

the flapper hinge pin. This valve spring 

should have been removed prior to 

installation of the valves. 

* * * * * 

With the valve spring installed, the flapper 

valve is held closed by the valve spring, 

preventing gravity feed. In the event of 

scavenge system failure, the collector tank 

fuel level can no longer be maintained, 

potentially leading to an in-flight engine 

shutdown. 

* * * * * 

We are issuing this AD to require 

actions to correct the unsafe condition 

on these products. 

DATES: This AD becomes effective 

October 18, 2010. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of October 18, 2010. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov or in person at the 

U.S. Department of Transportation, 

Docket Operations, M–30, West 

Building Ground Floor, Room W12–140, 

1200 New Jersey Avenue, SE., 

Washington, DC. 

FOR FURTHER INFORMATION CONTACT: Kent 

Fredrickson, Aerospace Engineer, 

Propulsion and Services Branch, ANE– 

173, FAA, New York Aircraft 

Certification Office (ACO), 1600 Stewart 

Avenue, Suite 410, Westbury, New York 

11590; telephone (516) 228–7364; fax 

(516) 794–5531. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to the specified products. That 

NPRM was published in the Federal 

Register on April 26, 2010 (75 FR 

21530). That NPRM proposed to correct 

an unsafe condition for the specified 

products. The MCAI states: 

During a recent production fuel system 

test, it was found that all three flapper valves 

located in each collector tank did not 

conform to the design requirements, due to 

the fact that a valve spring was installed on 

the flapper hinge pin. This valve spring 

should have been removed prior to 

installation of the valves. 

It was subsequently determined that this 

condition is restricted to the 21 aircraft listed 

in the Applicability section above. 

With the valve spring installed, the flapper 

valve is held closed by the valve spring, 

preventing gravity feed. In the event of 

scavenge system failure, the collector tank 

fuel level can no longer be maintained, 

potentially leading to an in-flight engine 

shutdown. 

In order to ensure adequate fuel transfer to 

the collector tank at all times, this directive 

mandates a one-time [detailed] inspection of 

each of the six flapper valves, removal of the 

valve spring, if installed, and application of 

an identification mark on each inspected 

valve. 

You may obtain further information 

by examining the MCAI in the AD 

docket. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM or 

on the determination of the cost to the 

public. 

Conclusion 

We reviewed the available data and 

determined that air safety and the 

public interest require adopting the AD 

as proposed. 

Differences Between This AD and the 

MCAI or Service Information 

We have reviewed the MCAI and 

related service information and, in 

general, agree with their substance. But 

we might have found it necessary to use 

different words from those in the MCAI 

to ensure the AD is clear for U.S. 

operators and is enforceable. In making 

these changes, we do not intend to differ 

substantively from the information 

provided in the MCAI and related 

service information. 

We might also have required different 

actions in this AD from those in the 

MCAI in order to follow our FAA 

policies. Any such differences are 

highlighted in a NOTE within the AD. 

Costs of Compliance 

We estimate that this AD will affect 4 

products of U.S. registry. We also 

estimate that it will take about 30 workhours per product to comply with the 

basic requirements of this AD. The 

average labor rate is $85 per work-hour. 

Based on these figures, we estimate the 

cost of this AD to the U.S. operators to 

be $10,200, or $2,550 per product. 

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 AD will not 

have federalism implications under 

Executive Order 13132. This AD will 

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 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. Will not have a significant 

economic impact, positive or negative, 


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