32262 Federal Register / Vol. 75, No. 109 / Tuesday, June 8, 2010 / Rules and Regulations 

Issued in Burlington, Massachusetts, on 

May 24, 2010. 

Peter A. White, 

Assistant Manager, Engine and Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 2010–13433 Filed 6–7–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0606; Directorate 

Identifier 2009–NE–11–AD; Amendment 39– 

16324; AD 2010–12–03] 

RIN 2120–AA64 

Airworthiness Directives; CFM 

International, S.A. Models CFM56–3 

and –3B Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for certain 

CFM International, S.A. models 

CFM56–3 and –3B turbofan engines. 

This AD requires initial and repetitive 

inspections for damage to the fan 

blades. This AD results from a report of 

a failed fan blade with severe out-oflimit wear on the underside of the blade 

platform where it contacts the damper. 

We are issuing this AD to prevent 

failure of multiple fan blades, which 

could result in an uncontained failure of 

the engine and damage to the airplane. 

DATES: This AD becomes effective July 

13, 2010. The Director of the Federal 

Register approved the incorporation by 

reference of certain publications listed 

in the regulations as of July 13, 2010. 

ADDRESSES: You can get the service 

information identified in this AD from 

CFM International, S. A., Technical 

Publication Department, 1 Neumann 

Way, Cincinnati, OH 45215; telephone 

(513) 552–2800; fax (513) 552–2816. 

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: 

Antonio Cancelliere, Aerospace 

Engineer, Engine Certification Office, 

FAA, Engine & Propeller Directorate, 12 

New England Executive Park, 

Burlington, MA 01803; e-mail: 

antonio.cancelliere@faa.gov; telephone 

(781) 238–7751; fax (781) 238–7199. 

SUPPLEMENTARY INFORMATION: The FAA 

proposed to amend 14 CFR part 39 with 

a proposed AD. The proposed AD 

applies to certain CFM International, 

S.A. models CFM56–3 and –3B turbofan 

engines. We published the proposed AD 

in the Federal Register on July 23, 2009 

(74 FR 36420), and published a 

supplemental proposed AD in the 

Federal Register on April 1, 2010 (75 

16361). Those actions proposed to 

require initial and repetitive inspections 

for damage to the fan blades. 

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 previously 

responded to the comments received on 

the original proposed AD in the 

supplemental proposed AD. We have 

considered the one comment received 

on the supplemental proposed AD. The 

commenter supports the proposal. 

Conclusion 

We have carefully reviewed the 

available data, including the comment 

received, and determined that air safety 

and the public interest require adopting 

the AD as proposed. 

Costs of Compliance 

We estimate that this AD will affect 

50 engines installed on airplanes of U.S. 

registry. We also estimate that it will 

take about 8 work-hours per engine to 

perform the AD actions, and that the 

average labor rate is $80 per work-hour. 

Required parts will cost about $38,000 

per engine. Based on these figures, we 

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

operators to be $1,932,000. 

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 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: 

2010–12–03 CFM International, S.A.: 

Amendment 39–16324. Docket No. 

FAA–2009–0606; Directorate Identifier 

2009–NE–11–AD. 


srobinson on DSKHWCL6B1PROD with RULES
Federal Register / Vol. 75, No. 109 / Tuesday, June 8, 2010 / Rules and Regulations 32263 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective July 13, 2010. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to CFM International, 

S.A. models CFM56–3 and –3B turbofan 

engines with 25 degrees midspan shroud fan 

blades, part numbers (P/Ns) 9527M99P08, 

9527M99P09, 9527M99P10, 9527M99P11, 

1285M39P01, or fan blade pairs, P/Ns 335– 

088–901–0, 335–088–902–0, 335–088–903–0, 

and 335–088–904–0 installed. These engines 

are installed on, but not limited to, Boeing 

737 series airplanes. 

(d) CFM International, S.A. has added to 

the basic engine model number on the engine 

nameplate to identify minor variations in 

engine configuration, installation 

components, or reduced ratings peculiar to 

aircraft installation requirements. 

(e) Those engines marked on the engine 

data plate as CFM56–3–B1 are included in 

this AD as CFM56–3 turbofan engines. 

(f) Those engines marked on the engine 

data plate as CFM56–3B–2 are included in 

this AD as CFM56–3B turbofan engines. 

Unsafe Condition 

(g) This AD results from a report of a failed 

fan blade with severe out-of-limit wear on the 

underside of the blade platform where it 

contacts the damper. We are issuing this AD 

to prevent failure of multiple fan blades, 

which could result in an uncontained failure 

of the engine and damage to the airplane. 

Compliance 

(h) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified, unless the 

actions have already been done. 

Inspection for Wear 

(i) Within 900 cycles-in-service after the 

effective date of this AD, perform an on-wing 

or in-shop inspection of the fan blade and 

damper for wear. Use paragraphs 3.A.(1) 

through 3.A.(5) or paragraphs 3.B.(1) through 

3.B.(5) respectively, of the Accomplishment 

Instructions of CFM International Service 

Bulletin (SB) No. CFM56–3/3B/3C S/B 72– 

1067, dated February 15, 2007. 

(j) If you find out-of-limit wear on at least 

one fan blade platform underside, perform 

the additional inspections and disposition 

the parts, as specified in paragraphs 3.A.(3) 

and 3.A.(5) or paragraphs 3.B.(3) and 3.B.(5) 

respectively, of the Accomplishment 

Instructions of CFM International SB No. 

CFM56–3/3B/3C S/B 72–1067, dated 

February 15, 2007. 

(k) Thereafter, within intervals not to 

exceed 3,000 cycles-since-last inspection, 

perform an on-wing or in-shop inspection for 

wear. Use paragraphs 3.A.(1) through 3.A.(5) 

or paragraphs 3.B.(1) through 3.B.(5) 

respectively, of the Accomplishment 

Instructions of CFM International SB No. 

CFM56–3/3B/3C S/B 72–1067, dated 

February 15, 2007. 

(l) If you find wear on at least one fan blade 

platform underside, perform additional 

inspections and disposition the parts, as 

specified in paragraphs 3.A.(3) and 3.A.(5) or 

paragraphs 3.B.(3) and 3.B.(5) respectively, of 

the Accomplishment Instructions of CFM 

International SB No. CFM56–3/3B/3C S/B 

72–1067, dated February 15, 2007. 

Installation Prohibition 

(m) After the effective date of this AD, 

don’t install any 25 degrees midspan shroud 

fan blades, P/Ns 9527M99P08, 9527M99P09, 

9527M99P10, 9527M99P11, 1285M39P01, or 

fan blade pairs, P/Ns 335–088–901–0, 335– 

088–902–0, 335–088–903–0, and 335–088– 

904–0, unless they have passed an inspection 

specified in paragraph 3. of the 

Accomplishment Instructions of CFM 

International SB No. CFM56–3/3B/3C S/B 

72–1067, dated February 15, 2007. 

Optional Terminating Action 

(n) Replacing the 25 degrees midspan 

shroud fan blade set with a 37 degrees 

midspan shroud fan blade set terminates the 

repetitive inspection requirements specified 

in paragraph (k) of this AD. 

Alternative Methods of Compliance 

(o) 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 

(p) Contact Antonio Cancelliere, Aerospace 

Engineer, Engine Certification Office, FAA, 

Engine & Propeller Directorate, 12 New 

England Executive Park, Burlington, MA 

01803; e-mail: antonio.cancelliere@faa.gov; 

telephone (781) 238–7751; fax (781) 238– 

7199, for more information about this AD. 

(q) European Aviation Safety Agency AD 

2009–0036, dated February 20, 2009, also 

addresses the subject of this AD. 

Material Incorporated by Reference 

(r) You must use CFM International Service 

Bulletin No. CFM56–3/3B/3C S/B 72–1067, 

dated February 15, 2007, to perform the 

inspections and parts dispositions required 

by this AD. The Director of the Federal 

Register approved the incorporation by 

reference of this service bulletin in 

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

part 51. Contact CFM International, S. A., 

Technical Publication Department, 1 

Neumann Way, Cincinnati, OH 45215; 

telephone (513) 552–2800; fax (513) 552– 

2816, 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/federalregister/cfr/ibr-locations.html. 

Issued in Burlington, Massachusetts, on 

May 25, 2010. 

Peter A. White, 

Assistant Manager, Engine and Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 2010–13432 Filed 6–7–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–1223; Directorate 

Identifier 2009–NM–114–AD; Amendment 

39–16327; AD 2010–12–06] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc. Model DHC–8–400 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 final Acceptance Test Procedure 

(ATP), a small oil leak was discovered on the 

Spoiler Unload Valve and Rudder Shutoff 

Valve bodies. Investigation revealed that a 

number of valves were manufactured with an 

incorrect wall thickness. This thin wall 

condition caused cracking, subsequent 

external weeping and pressure loss from the 

subject valves. 

This condition, if not corrected, will cause 

a loss of hydraulic fluid and subsequent loss 

of spoiler and/or rudder control. 

* * * * * 

We are issuing this AD to require 

actions to correct the unsafe condition 

on these products. 

DATES: This AD becomes effective July 

13, 2010. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of July 13, 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: 

Cesar Gomez, Aerospace Engineer, 

Airframe and Mechanical Systems 

Branch, ANE–171, FAA, New York 

Aircraft Certification Office, 1600 

Stewart Avenue, Suite 410, Westbury, 

New York 11590; telephone (516) 228– 

7318; fax (516) 794–5531. 

SUPPLEMENTARY INFORMATION: 


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